This three-sentence summary provides the key details about the document:
The document announces a three-day short course on tactical missile design integration that will cover fundamentals of missile configuration, propulsion, weight, performance, and integration considerations. The course, taught by experienced instructor Eugene Fleeman, will use analytical expressions and examples to illustrate the primary design drivers and tradeoffs. Attendees will learn missile design processes and parameters, participate in a small rocket design exercise, and receive course notes and a textbook on tactical missile design.
This is Part 1 of 3 covering my work on my Future Deep Strike Aircraft project, to inspire interest in aerospace engineering for the RAeS, the A&SPA(UK) and AIAA.
This document defines and describes missiles. It begins by explaining that a missile is any object thrown at a target to hit it, such as a stone thrown at a bird. Modern missiles are precision-guided munitions with propulsion, guidance, and control systems. The key components of a missile are a warhead, propulsion system, guidance system, and control system. Missiles are classified based on their method of launching and range. Guidance systems include command, homing, beam rider, and inertial guidance. Early guided missiles included the German V-1 and V-2 rockets from World War II.
1. Guided missiles are objects that can be directed to a target through various guidance technologies. They incorporate a propulsion system to provide force, an intelligence system to guide it correctly, and control technologies.
2. Early developments included rockets used in China and India over 1000 years ago and unguided rockets used against the British in the 18th century. Modern guided missiles began with German V-1 and V-2 missiles in World War II.
3. Missiles can be guided through different methods including command guidance, homing guidance, beam rider guidance, inertial guidance, and stellar guidance. India's Integrated Guided Missile Development Program from the 1980s-2008 developed strategic missiles like Agni 3 under
This document provides an overview of missiles and their components. It discusses the history of missiles beginning with rockets invented in medieval China. Modern Indian missiles are then discussed, highlighting programs like Agni and Prithvi. The key components of missiles are described as the warhead, guidance system, propulsion, and fins. Common guidance methods include laser, infrared homing and GPS. Propulsion systems can include turbojets, ramjets and pulsejets. In summary, the document provides a high-level history and technical overview of missiles and their components.
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
This document provides information about a professional development course on fundamentals of rockets and missiles. The course will be held from March 11-13, 2009 in Laurel, Maryland and will cost $1590. It will provide a practical foundation of knowledge on rocket and missile issues and technologies. The 14-part course outline covers topics like rocket propulsion, liquid and solid propellant systems, foreign and domestic rocket comparisons, and reusable launch vehicles. The instructor, Edward L. Keith, has extensive experience in the rocket field. Attendees will learn about rocket fundamentals and receive printed course notes. The course is intended for engineers, managers, military personnel, and others involved in rocket projects.
Stealth technology uses various methods and materials to reduce an aircraft's detection by radar and other sensors. Radar absorbent surfaces (RAS) and radar absorbent materials (RAM) are used to deflect or absorb radar signals, making aircraft appear smaller or invisible to radar. Infrared signatures are also reduced through engine placement and other design features. Active stealth techniques like plasma stealth aim to inject plasma around an aircraft to absorb electromagnetic waves. While stealth aircraft have advantages like reduced detection, they also have limitations such as reduced payload and increased costs. The first stealth aircraft was the F-117, introduced in 1981.
This document presents the design of a conceptual dual-role aircraft capable of short-haul and long-haul missions. It describes the initial weight estimation, aerodynamic analysis, performance modeling, geometry design, stability and control assessment, and conclusion that the aircraft meets the mission requirements. The appendices provide details on the mission profiles, weight breakdown, aerodynamic calculations, drag polars, performance parameters, geometry dimensions, propulsion specifications, and stability analysis.
This is Part 1 of 3 covering my work on my Future Deep Strike Aircraft project, to inspire interest in aerospace engineering for the RAeS, the A&SPA(UK) and AIAA.
This document defines and describes missiles. It begins by explaining that a missile is any object thrown at a target to hit it, such as a stone thrown at a bird. Modern missiles are precision-guided munitions with propulsion, guidance, and control systems. The key components of a missile are a warhead, propulsion system, guidance system, and control system. Missiles are classified based on their method of launching and range. Guidance systems include command, homing, beam rider, and inertial guidance. Early guided missiles included the German V-1 and V-2 rockets from World War II.
1. Guided missiles are objects that can be directed to a target through various guidance technologies. They incorporate a propulsion system to provide force, an intelligence system to guide it correctly, and control technologies.
2. Early developments included rockets used in China and India over 1000 years ago and unguided rockets used against the British in the 18th century. Modern guided missiles began with German V-1 and V-2 missiles in World War II.
3. Missiles can be guided through different methods including command guidance, homing guidance, beam rider guidance, inertial guidance, and stellar guidance. India's Integrated Guided Missile Development Program from the 1980s-2008 developed strategic missiles like Agni 3 under
This document provides an overview of missiles and their components. It discusses the history of missiles beginning with rockets invented in medieval China. Modern Indian missiles are then discussed, highlighting programs like Agni and Prithvi. The key components of missiles are described as the warhead, guidance system, propulsion, and fins. Common guidance methods include laser, infrared homing and GPS. Propulsion systems can include turbojets, ramjets and pulsejets. In summary, the document provides a high-level history and technical overview of missiles and their components.
This document discusses the V-n diagram, which plots the velocity of an aircraft against the load factor it experiences. It outlines how load factors are calculated based on the lift and weight of the aircraft. Limit, proof and ultimate load factors are explained which specify the maximum loads aircraft structures must be designed to withstand. Typical load factors for different aircraft types are shown, with fighters experiencing the highest positive load factors due to high-performance maneuvering. The V-n diagram defines the flight envelope and structural limits for an aircraft.
This document provides information about a professional development course on fundamentals of rockets and missiles. The course will be held from March 11-13, 2009 in Laurel, Maryland and will cost $1590. It will provide a practical foundation of knowledge on rocket and missile issues and technologies. The 14-part course outline covers topics like rocket propulsion, liquid and solid propellant systems, foreign and domestic rocket comparisons, and reusable launch vehicles. The instructor, Edward L. Keith, has extensive experience in the rocket field. Attendees will learn about rocket fundamentals and receive printed course notes. The course is intended for engineers, managers, military personnel, and others involved in rocket projects.
Stealth technology uses various methods and materials to reduce an aircraft's detection by radar and other sensors. Radar absorbent surfaces (RAS) and radar absorbent materials (RAM) are used to deflect or absorb radar signals, making aircraft appear smaller or invisible to radar. Infrared signatures are also reduced through engine placement and other design features. Active stealth techniques like plasma stealth aim to inject plasma around an aircraft to absorb electromagnetic waves. While stealth aircraft have advantages like reduced detection, they also have limitations such as reduced payload and increased costs. The first stealth aircraft was the F-117, introduced in 1981.
This document presents the design of a conceptual dual-role aircraft capable of short-haul and long-haul missions. It describes the initial weight estimation, aerodynamic analysis, performance modeling, geometry design, stability and control assessment, and conclusion that the aircraft meets the mission requirements. The appendices provide details on the mission profiles, weight breakdown, aerodynamic calculations, drag polars, performance parameters, geometry dimensions, propulsion specifications, and stability analysis.
The document outlines the aircraft design process from initial requirements definition through detailed design, testing, and certification. It discusses establishing basic and general requirements, conducting feasibility studies, specifying detailed requirements, conceptual and preliminary design phases involving configuration selection, performance modeling, and optimization. Later phases include detailed design, ground and flight testing, and certification to clear the aircraft for intended operations. The process is iterative with frequent trade-offs and refinement of requirements and design.
Thank you for all video clips.
https://www.youtube.com/watch?v=HWZXinRwCaE (icbm)
https://www.youtube.com/watch?v=mE-q1IaPIUk (how missiles launch)
https://www.youtube.com/watch?v=SOXmVi3A_PI (satan R36)
https://www.youtube.com/watch?v=LvHlW1h_0XQ (LRASM)
THIS IS A SEMINAR REPORT ON GUIDED MISSILE. IN THIS REPORT YOU WILL FIND A BRIEF INTRODUCTION LIKE WHAT IS GUIDED MISSILE , TYPES OF MISSILE ,TYPES OF CONTROL AND GUIDANCE SYSTEM, WARHEAD , FUZES.
The document discusses the design and development of quadcopter unmanned aerial vehicles (UAVs). It describes the prototypes created, including improvements made to reduce weight and increase lift. Sensors and controllers are discussed, including sensors for position, proximity, and navigation. The final prototype achieved stable hovering with a weight of 43 grams and incorporated an inertial measurement unit, ultrasonic sensors, GPS, and radio frequency transmission for control and data transmission.
Cruise missile technology By shailesh shukla pptSHAILESH SHUKLA
Cruise missiles are small, pilotless airplanes powered by turbofan engines that can precisely deliver bombs up to 1,000 miles away. They use various guidance systems like inertial navigation, terrain contour matching, and digital scene mapping to navigate to their targets. Inertial navigation uses accelerometers and gyroscopes to measure movement, while terrain contour matching compares onboard radar measurements to pre-recorded terrain maps to determine location. Cruise missiles offer advantages like low cost and small size, but also have disadvantages like lack of reusability and vulnerability to defenses. Their guidance systems require careful design for accurate target interception.
This document provides an overview of anti-ballistic missiles and missile technology. It begins with classifications of different types of missiles based on their range and propulsion, including ballistic missiles and cruise missiles. It then discusses key components of missiles like propulsion systems, guidance and control systems, aerodynamics, warheads and fuzes. Emerging technologies like hypersonic cruise missiles are also mentioned. The document serves to introduce the topic of anti-ballistic missiles and provide a technical overview of missile design and components.
Morphing Aircraft Technology – New Shapes for Aircraft Wing DesignMani5436
Morphing aircraft are multi-role aircraft that change their external shape substantially to adapt to a changing mission environment during flight.
Morphing poses several unique challenges when the wing loading is high. Very flexible materials are the designer’s first choice because they are easily reshaped.
he current use of multiple aerodynamic devices (such as flaps and slats) represents a simplification of the general idea behind morphing. Traditional control systems (with fixed geometry and/or location) give high aerodynamic performance over a fixed range and for a limited set of flight conditions.
This document provides an overview of ballistic missile systems. It begins with definitions of missiles and their classification. It then discusses the key components of ballistic missiles, including warheads, fuses, guidance systems, and propulsion systems. The document outlines the working principle of ballistic missiles and describes their flight in different phases. It also briefly discusses the history of ballistic missile development in India.
The document presents the design of the LAT-1 large air tanker aircraft by Ember Aviation in response to the 2015-2016 AIAA Foundation Undergraduate Team Aircraft Design Competition. The LAT-1 is designed to carry 5,000 gallons of water or retardant with a maximum weight of 45,000 lbs and perform 3 drops per sortie within a 200 nm radius of the base, as well as have a ferry range of 2,500 nm. The LAT-1 features a retardant tank fuselage shape with two engines mounted on top of the wings. Ember Aviation's goal was to eliminate wasted space on the aircraft by integrating all components, such as the cockpit and payload tank, directly into the aircraft structure
VHF communication systems are used for air traffic control communications between aircraft and ground stations. They operate in the 118-136.975 MHz frequency range and use line-of-sight signals. Modern VHF systems have 720-760 channels and use digital technologies like ARINC 429 data buses for frequency selection and data transfer. VHF systems consist of a transceiver, control head, antennas, and interface to the aircraft audio system.
This presentation summarizes a Congressional Budget Office report on U.S. hypersonic weapons and alternatives. It discusses the technological challenges of developing hypersonic missiles, including managing extreme heat from high-speed atmospheric flight. Both hypersonic missiles and ballistic missiles with maneuverable warheads could penetrate adversaries' anti-access/area denial zones, but hypersonic missiles would be most useful against well-defended, time-sensitive threats. Hypersonic missiles may have shorter flight times than other weapons but would likely cost more than comparable ballistic missiles.
Pakistan has developed an advanced missile program. It has short-range missiles like Ghaznavi (300km) and Shaheen-I (750-900km), and medium-range missiles like Ghauri-I (1,500km) and Shaheen-III (2,750km). Pakistan also has the tactical Nasr missile (60km) and the cruise missile Babur (450+km). Missiles work using rocket propulsion and guidance systems, and can have different payloads like conventional, chemical, biological or nuclear warheads. Pakistan's missiles demonstrate its growing indigenous defense capabilities.
General Atomics Presentation to Williams Foundation Seminar on Air-Land Integ...ICSA, LLC
In this presentation by Mr Ken Loving, General Atomics Aeronautical Systems, to the Williams Foundation, the focus was upon the evolving capabilities of the unmanned segment of the air combat force.
The seminar focused on the way ahead with regard to air-land integration.
Air Force needs to be capable of delivering air and space power effects to support conventional and special operations in the land domain. Air Force’s Plan Jericho and Army’s Plan Beersheba need to align if there is to be a coordinated approach to integrating air base operations, air mobility, close air support, intelligence, surveillance and reconnaissance (ISR) and rotary wing aviation. To date, little attention has been paid to the integration of technology across service lines, the development of integrated tactics, techniques and procedures (TTPs) and a coherent joint collective training program. Air Force and Army need to remediate existing deficiencies and implement a capability management process that leaves it postured to take advantage of the transformative nature of fifth generation technology. The seminar explored the art of the possible in future Air-Land operations.
Drones and their Increasing Number of ApplicationsJeffrey Funk
These slides use concepts from my (Jeff Funk) course entitled analyzing hi-tech opportunities to analyze how drones are becoming economic feasible for an increasing number of applications as their costs fall. The costs of drones are falling as the costs of various ICs (controllers, GPS) and MEMS sensors rapidly fall, their performance rises (e.g., accuracy of GPS) and as the cost of carbon fibers fall at a somewhat slower pace than do ICs and MEMS. These falling costs are making drones economically feasible for a number of applications such as producing movies, TV reporting, surveillance, and delivery.
An unmanned aerial vehicle (UAV), commonly known as a Drone, is an aircraft without a human pilot on board. UAVs can be remote controlled aircraft (e.g. flown by a pilot at a ground control station) or can fly autonomously based on pre-programmed flight plans or more complex dynamic automation systems
A UAV is defined as being capable of controlled, sustained level flight and powered by a jet or reciprocating engine. In addition, a cruise missile can be considered to be a UAV, but is treated separately on the basis that the vehicle is the weapon.
Unmanned Aerial Vehicles (UAVs) are aircrafts that fly without any humans being onboard. They are either remotely piloted, or piloted by an onboard computer. This kind of aircrafts can be used in different military missions such as surveillance, reconnaissance, battle damage assessment, communications relay, minesweeping, hazardous substances detection and radar jamming. However they can be used in other than military missions like detection of hazardous objects on train rails and investigation of infected areas. Aircrafts that are able of hovering and vertical flying can also be used for indoor missions like counter terrorist operations
To download this ppt click on this link
https://adf.ly/PdL4V
This document defines and categorizes different types of powered guided munitions. It outlines their key parts like guidance and propulsion systems. It then describes different modes like air-to-air and surface-to-surface. Finally, it details various guidance systems for powered munitions including line-of-sight homing, inertial navigation, and satellite guidance as well as ballistic and cruise missiles.
Avionics systems include the electronic systems used on aircraft and spacecraft to manage communications, navigation, and all other onboard systems. The document discusses six key avionics systems: 1) Basic flight instruments like the altimeter, attitude indicator, magnetic compass, airspeed indicator, and vertical speed indicator provide pilots with critical aircraft data. 2) Cabin pressurization and 3) air conditioning systems are necessary for crew and passenger safety and comfort. 4) The aircraft fuel system manages fuel storage and delivery to engines. 5) Autopilot systems use gyroscopes, servos, and controllers to automatically guide and fly aircraft without constant pilot assistance. 6) Electrical power systems use batteries for starting aircraft and emergencies.
This document provides information about a quadcopter drone project completed by four students. It includes a certificate of completion, table of contents, and chapters covering the quadcopter materials and design. The main components discussed are the frame, KK2.1.5 circuit board, DC brushless motors, electronic speed controls, Li-Po battery, remote control, and receiver. The document provides details on the purpose and functioning of these various components that make up the quadcopter.
Geoffrey Wardle has over 40 years of experience in air and space research and development. His career began in 1982 with designing coatings to protect rocket engine parts from corrosion for the LEROS liquid fuel rocket engine. In the 1980s and early 1990s, he conducted structural qualification testing for components of Eurofighter Typhoon and developed test methodologies at establishments including RAE Farnborough and BAe. Currently, he is researching advanced composite airframe technologies and supersonic bomber design using simulation tools from his graduate studies.
This document recommends an insight/oversight model for NASA's Commercial Crew Program. It suggests using technical expert engagement similar to other programs, with a focus on high-risk subsystems. The model includes discrete oversight at key decision points rather than continuous oversight. Insight teams would provide expertise and recommendations, while the Program Office makes oversight decisions.
ATI Courses Professional Development Short Course Spacecraft Quality Assuranc...Jim Jenkins
Quality assurance, reliability, and testing are critical elements in low-cost space missions. The selection of lower cost parts and the most effective use of redundancy require careful tradeoff analysis when designing new space missions. Designing for low cost and allowing some risk are new ways of doing business in today's cost-conscious environment. This course uses case studies and examples from recent space missions to pinpoint the key issues and tradeoffs in design, reviews, quality assurance, and testing of spacecraft. Lessons learned from past successes and failures are discussed and trends for future missions are highlighted.
The document outlines the aircraft design process from initial requirements definition through detailed design, testing, and certification. It discusses establishing basic and general requirements, conducting feasibility studies, specifying detailed requirements, conceptual and preliminary design phases involving configuration selection, performance modeling, and optimization. Later phases include detailed design, ground and flight testing, and certification to clear the aircraft for intended operations. The process is iterative with frequent trade-offs and refinement of requirements and design.
Thank you for all video clips.
https://www.youtube.com/watch?v=HWZXinRwCaE (icbm)
https://www.youtube.com/watch?v=mE-q1IaPIUk (how missiles launch)
https://www.youtube.com/watch?v=SOXmVi3A_PI (satan R36)
https://www.youtube.com/watch?v=LvHlW1h_0XQ (LRASM)
THIS IS A SEMINAR REPORT ON GUIDED MISSILE. IN THIS REPORT YOU WILL FIND A BRIEF INTRODUCTION LIKE WHAT IS GUIDED MISSILE , TYPES OF MISSILE ,TYPES OF CONTROL AND GUIDANCE SYSTEM, WARHEAD , FUZES.
The document discusses the design and development of quadcopter unmanned aerial vehicles (UAVs). It describes the prototypes created, including improvements made to reduce weight and increase lift. Sensors and controllers are discussed, including sensors for position, proximity, and navigation. The final prototype achieved stable hovering with a weight of 43 grams and incorporated an inertial measurement unit, ultrasonic sensors, GPS, and radio frequency transmission for control and data transmission.
Cruise missile technology By shailesh shukla pptSHAILESH SHUKLA
Cruise missiles are small, pilotless airplanes powered by turbofan engines that can precisely deliver bombs up to 1,000 miles away. They use various guidance systems like inertial navigation, terrain contour matching, and digital scene mapping to navigate to their targets. Inertial navigation uses accelerometers and gyroscopes to measure movement, while terrain contour matching compares onboard radar measurements to pre-recorded terrain maps to determine location. Cruise missiles offer advantages like low cost and small size, but also have disadvantages like lack of reusability and vulnerability to defenses. Their guidance systems require careful design for accurate target interception.
This document provides an overview of anti-ballistic missiles and missile technology. It begins with classifications of different types of missiles based on their range and propulsion, including ballistic missiles and cruise missiles. It then discusses key components of missiles like propulsion systems, guidance and control systems, aerodynamics, warheads and fuzes. Emerging technologies like hypersonic cruise missiles are also mentioned. The document serves to introduce the topic of anti-ballistic missiles and provide a technical overview of missile design and components.
Morphing Aircraft Technology – New Shapes for Aircraft Wing DesignMani5436
Morphing aircraft are multi-role aircraft that change their external shape substantially to adapt to a changing mission environment during flight.
Morphing poses several unique challenges when the wing loading is high. Very flexible materials are the designer’s first choice because they are easily reshaped.
he current use of multiple aerodynamic devices (such as flaps and slats) represents a simplification of the general idea behind morphing. Traditional control systems (with fixed geometry and/or location) give high aerodynamic performance over a fixed range and for a limited set of flight conditions.
This document provides an overview of ballistic missile systems. It begins with definitions of missiles and their classification. It then discusses the key components of ballistic missiles, including warheads, fuses, guidance systems, and propulsion systems. The document outlines the working principle of ballistic missiles and describes their flight in different phases. It also briefly discusses the history of ballistic missile development in India.
The document presents the design of the LAT-1 large air tanker aircraft by Ember Aviation in response to the 2015-2016 AIAA Foundation Undergraduate Team Aircraft Design Competition. The LAT-1 is designed to carry 5,000 gallons of water or retardant with a maximum weight of 45,000 lbs and perform 3 drops per sortie within a 200 nm radius of the base, as well as have a ferry range of 2,500 nm. The LAT-1 features a retardant tank fuselage shape with two engines mounted on top of the wings. Ember Aviation's goal was to eliminate wasted space on the aircraft by integrating all components, such as the cockpit and payload tank, directly into the aircraft structure
VHF communication systems are used for air traffic control communications between aircraft and ground stations. They operate in the 118-136.975 MHz frequency range and use line-of-sight signals. Modern VHF systems have 720-760 channels and use digital technologies like ARINC 429 data buses for frequency selection and data transfer. VHF systems consist of a transceiver, control head, antennas, and interface to the aircraft audio system.
This presentation summarizes a Congressional Budget Office report on U.S. hypersonic weapons and alternatives. It discusses the technological challenges of developing hypersonic missiles, including managing extreme heat from high-speed atmospheric flight. Both hypersonic missiles and ballistic missiles with maneuverable warheads could penetrate adversaries' anti-access/area denial zones, but hypersonic missiles would be most useful against well-defended, time-sensitive threats. Hypersonic missiles may have shorter flight times than other weapons but would likely cost more than comparable ballistic missiles.
Pakistan has developed an advanced missile program. It has short-range missiles like Ghaznavi (300km) and Shaheen-I (750-900km), and medium-range missiles like Ghauri-I (1,500km) and Shaheen-III (2,750km). Pakistan also has the tactical Nasr missile (60km) and the cruise missile Babur (450+km). Missiles work using rocket propulsion and guidance systems, and can have different payloads like conventional, chemical, biological or nuclear warheads. Pakistan's missiles demonstrate its growing indigenous defense capabilities.
General Atomics Presentation to Williams Foundation Seminar on Air-Land Integ...ICSA, LLC
In this presentation by Mr Ken Loving, General Atomics Aeronautical Systems, to the Williams Foundation, the focus was upon the evolving capabilities of the unmanned segment of the air combat force.
The seminar focused on the way ahead with regard to air-land integration.
Air Force needs to be capable of delivering air and space power effects to support conventional and special operations in the land domain. Air Force’s Plan Jericho and Army’s Plan Beersheba need to align if there is to be a coordinated approach to integrating air base operations, air mobility, close air support, intelligence, surveillance and reconnaissance (ISR) and rotary wing aviation. To date, little attention has been paid to the integration of technology across service lines, the development of integrated tactics, techniques and procedures (TTPs) and a coherent joint collective training program. Air Force and Army need to remediate existing deficiencies and implement a capability management process that leaves it postured to take advantage of the transformative nature of fifth generation technology. The seminar explored the art of the possible in future Air-Land operations.
Drones and their Increasing Number of ApplicationsJeffrey Funk
These slides use concepts from my (Jeff Funk) course entitled analyzing hi-tech opportunities to analyze how drones are becoming economic feasible for an increasing number of applications as their costs fall. The costs of drones are falling as the costs of various ICs (controllers, GPS) and MEMS sensors rapidly fall, their performance rises (e.g., accuracy of GPS) and as the cost of carbon fibers fall at a somewhat slower pace than do ICs and MEMS. These falling costs are making drones economically feasible for a number of applications such as producing movies, TV reporting, surveillance, and delivery.
An unmanned aerial vehicle (UAV), commonly known as a Drone, is an aircraft without a human pilot on board. UAVs can be remote controlled aircraft (e.g. flown by a pilot at a ground control station) or can fly autonomously based on pre-programmed flight plans or more complex dynamic automation systems
A UAV is defined as being capable of controlled, sustained level flight and powered by a jet or reciprocating engine. In addition, a cruise missile can be considered to be a UAV, but is treated separately on the basis that the vehicle is the weapon.
Unmanned Aerial Vehicles (UAVs) are aircrafts that fly without any humans being onboard. They are either remotely piloted, or piloted by an onboard computer. This kind of aircrafts can be used in different military missions such as surveillance, reconnaissance, battle damage assessment, communications relay, minesweeping, hazardous substances detection and radar jamming. However they can be used in other than military missions like detection of hazardous objects on train rails and investigation of infected areas. Aircrafts that are able of hovering and vertical flying can also be used for indoor missions like counter terrorist operations
To download this ppt click on this link
https://adf.ly/PdL4V
This document defines and categorizes different types of powered guided munitions. It outlines their key parts like guidance and propulsion systems. It then describes different modes like air-to-air and surface-to-surface. Finally, it details various guidance systems for powered munitions including line-of-sight homing, inertial navigation, and satellite guidance as well as ballistic and cruise missiles.
Avionics systems include the electronic systems used on aircraft and spacecraft to manage communications, navigation, and all other onboard systems. The document discusses six key avionics systems: 1) Basic flight instruments like the altimeter, attitude indicator, magnetic compass, airspeed indicator, and vertical speed indicator provide pilots with critical aircraft data. 2) Cabin pressurization and 3) air conditioning systems are necessary for crew and passenger safety and comfort. 4) The aircraft fuel system manages fuel storage and delivery to engines. 5) Autopilot systems use gyroscopes, servos, and controllers to automatically guide and fly aircraft without constant pilot assistance. 6) Electrical power systems use batteries for starting aircraft and emergencies.
This document provides information about a quadcopter drone project completed by four students. It includes a certificate of completion, table of contents, and chapters covering the quadcopter materials and design. The main components discussed are the frame, KK2.1.5 circuit board, DC brushless motors, electronic speed controls, Li-Po battery, remote control, and receiver. The document provides details on the purpose and functioning of these various components that make up the quadcopter.
Geoffrey Wardle has over 40 years of experience in air and space research and development. His career began in 1982 with designing coatings to protect rocket engine parts from corrosion for the LEROS liquid fuel rocket engine. In the 1980s and early 1990s, he conducted structural qualification testing for components of Eurofighter Typhoon and developed test methodologies at establishments including RAE Farnborough and BAe. Currently, he is researching advanced composite airframe technologies and supersonic bomber design using simulation tools from his graduate studies.
This document recommends an insight/oversight model for NASA's Commercial Crew Program. It suggests using technical expert engagement similar to other programs, with a focus on high-risk subsystems. The model includes discrete oversight at key decision points rather than continuous oversight. Insight teams would provide expertise and recommendations, while the Program Office makes oversight decisions.
ATI Courses Professional Development Short Course Spacecraft Quality Assuranc...Jim Jenkins
Quality assurance, reliability, and testing are critical elements in low-cost space missions. The selection of lower cost parts and the most effective use of redundancy require careful tradeoff analysis when designing new space missions. Designing for low cost and allowing some risk are new ways of doing business in today's cost-conscious environment. This course uses case studies and examples from recent space missions to pinpoint the key issues and tradeoffs in design, reviews, quality assurance, and testing of spacecraft. Lessons learned from past successes and failures are discussed and trends for future missions are highlighted.
This document provides a summary of an individual's experience as a senior structural engineer including:
- Over 8 years of experience performing finite element analysis for structures in defence, aerospace, and rail transportation using various CAE software.
- Experience leading projects involving structural analysis, testing, and documentation for clients such as DRDO, UTC, and Bombardier.
- Education includes a Bachelor's degree in Mechanical Engineering and diploma in Mechanical Engineering.
The document summarizes a training conference on long-range strike capabilities to be held from September 12-14, 2011 in Washington DC. The conference will discuss requirements for the next generation bomber, development concepts for conventional prompt global strike systems, advancements in long-range unmanned systems, and modernization of current nuclear weapons systems. Specific topics include Air Force requirements for long-range strike systems, acquisition plans for bombers and other capabilities, increasing the range of carrier-based aircraft, and the Air-Sea Battle concept.
A BRIEF REVIEW OF FUTURE PRECISION STRIKE MISSILE SYSTEMSAM Publications
This article is prepared after studying the report prepared by the NATO RESEARCH AND TECHNOLOGY (RTO).The primary purpose of the article is disseminating the state-of-the art developments in the enabling technologies. It also addressed the challenging requirements in areas such as adverse weather capability, time critical targets, high kill probability and advances in future seekers.
Mick L Blackledge had an extensive career in the aerospace industry and government service spanning missile defense technology. He received engineering degrees from St. Louis University and University of Colorado. In government service, he led development of early miniaturized interceptor technologies as Director of Interceptor Technology. He conceived programs that advanced missile defense capabilities. He also worked for 20 years in the aerospace industry before joining the government.
Riannon Stenberg has over 15 years of experience in engineering roles related to solid rocket motors and missile defense systems. She has held positions as a reliability engineer, systems engineering specialist, ballistician, and solid rocket motor components engineer. Her security clearance is top secret and remains active.
Kagisano Marumo has over 4 years of experience as a mechanical designer for aircraft interiors. He has designed mechanical installations, tooling, and fixtures and prepared engineering drawings. He also has experience performing maintenance on aircraft as an Aircraft Maintenance Engineer and has a mechanical engineering degree specializing in aerospace.
ATI Professional Development Technical Training Short Course on Missile Autop...Jim Jenkins
This document provides information about a 4-day professional development course on missile autopilots taught by Paul Jackson. The course covers topics such as missile equations of motion, linear systems theory, autopilot hardware, pitch autopilot design, and advanced concepts. It includes examples from real-world missile systems. Attendees will learn fundamentals of autopilot design and analysis with an emphasis on linear systems and feedback control applied to missile dynamics and aerodynamic modeling.
Frank McDaniel has over 39 years of experience in mechanical design and CAD/CAM modeling using various software packages. He has extensive experience in aerospace, automotive, marine, and defense industries designing mechanical parts, assemblies, and drawings. His resume lists his educational background and professional experience working for companies like Boeing, General Dynamics, Northrop Grumman, and Orbital Sciences where he performed mechanical design, modeling, drawing checking, and logistical support roles.
1) EMMO Safety Engineering provides engineering services for offshore and shipping structures, including structural design, fabrication support, and operational optimization.
2) Their capabilities include structural design verification, fabrication evaluations to ensure structures are fit for purpose, and risk/reliability analyses to optimize inspection costs.
3) Their engineering support addresses tasks such as module connection design, fabrication mismatch evaluations, and cost-optimal inspection planning using reliability-based methods.
Mr. Neiman has over 50 years of experience in business development, marketing, program management, and
engineering for space, military, and government contractors. He has been responsible for over $4 billion in contract
awards during his career. He has worked in leadership and management roles for companies including Grumman,
Douglas Aircraft, General Dynamics, and NASA. He has extensive experience in business development, contract
procurement, and management of engineering programs for aircraft, spacecraft, and launch vehicles.
Krishnraj Nellikunje is seeking a position where he can contribute his 13 years of experience in technology and leadership. He has extensive professional experience in product engineering, design for reliability, and program management for automotive and aerospace products at Honeywell Technology Solutions. He also has prior experience in materials testing and analysis. He is a Honeywell certified Project Manager and Green Belt with publications and trade secrets in his field.
The document summarizes the key discussions and outcomes from a workshop focused on using direct digital manufacturing (DDM) of metallic components to enhance operational readiness and reduce costs for the US Navy. The workshop brought together experts from government, industry and academia. They identified technical challenges and potential approaches to address qualifications and certification; innovative structural design; and maintenance and repair using DDM. Near, mid and long term objectives and approaches were proposed to develop the necessary technologies and reduce barriers to implementing DDM for naval aviation.
Edward Boylan seeks a career in structural engineering. He has a Master's degree in Aerospace Engineering from Embry-Riddle Aeronautical University and a Bachelor's degree in Aeronautical and Mechanical Engineering from Rensselaer Polytechnic Institute. His projects include multidisciplinary design optimization of an impeller blade using HEEDS software and extending the damage tolerance of composite structures. He has experience with stress analysis, unmanned aerial vehicles, and structural health monitoring.
Ia W. Whiteley has over 15 years of experience in engineering, testing, manufacturing, and product development. She has a Secret level federal security clearance and certifications in cost savings methods. Her career includes positions at aerospace companies Skyward and GE Aviation, where she led projects, managed teams, analyzed test data, and implemented cost reduction strategies. She also has experience in reverse engineering, quality control, and website design.
Dorsey T. Rubendall is a Principal Systems Analyst with extensive experience in missile defense operations, systems engineering, modeling and simulation (M&S), and verification and validation. He has over 20 years of experience in the Army and as a contractor supporting the Missile Defense Agency. Currently he is a Principal Systems Analyst supporting M&S for missile defense and coordinates modeling efforts across multiple organizations. He has held various engineering and management roles developing tools and conducting analyses to support missile defense testing and evaluation.
@@ 3+ years of Experience in Aerospace Design (1) (2)darshan kr
Darshan K R is seeking a position that allows him to utilize his 3.6 years of professional experience. He has a B.E. in Industrial and Production Engineering and a diploma in Mechanical Engineering. His experience includes over 2 years working as a Design Engineer at Aeronautical Development Agency, where he has designed structural components for aircraft integration projects. He also has experience as a Project Executive Engineer and Lab Engineer Trainee. His technical skills include CAD modeling in CATIA V5 and structural analysis. He is proficient in design standards and has experience designing aircraft structural parts and assemblies.
This 3-day, classroom and practical instructional program provides individuals or teams entering the unmanned aircraft system (UAS) market with the need to 'hit the ground running'. Delegates will gain a working knowledge of UAS system classification, payloads, sensors, communications and data links. You will learn the UAS weapon design process and UAS system design components. The principles of mission planning systems and human factors design considerations are described. The critical issue of integrating UAS in the NAS is addressed in detail along with major considerations. Multiple roadmaps from all services are used to explain UAS future missions.
The Max Launch Abort System (MLAS) project developed an alternative design for NASA's Orion Launch Abort System to demonstrate during a pad abort test. A broad-based team designed a flight test vehicle using existing hardware when possible. The MLAS concept utilized four center-clustered solid rocket motors on a separable boost skirt and planar fins on a coast skirt. Upcoming milestones included completing integration and testing of the crew module avionics and conducting the pad abort flight test in March 2009.
Digital Signal Processing - Practical Techniques, Tips and Tricks Course SamplerJim Jenkins
This document discusses the technique of dithering, which involves adding noise to signals to improve results. It explains that dithering can reduce distortion and quantization errors for low-amplitude signals. As an example, it shows how adding noise to a constant signal before quantization significantly reduces quantization error. The document also demonstrates a method of injecting noise to detect a very small signal that is below the detection threshold, and finds the optimal amount of noise to add without swamping the signal.
ELINT Interception and Analysis course samplerJim Jenkins
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Space Radiation & It's Effects On Space Systems & Astronauts Technical Traini...Jim Jenkins
This course is designed for technical and management personnel who wish to gain an understanding of the fundamentals and the effects of space radiation on space systems and astronauts. The radiation environment imposes strict design requirements on many space systems and is the primary limitation to human exploration outside of the Earth's magnetosphere. The course specifically addresses issues of relevance and concern for participants who expect to plan, design, build, integrate, test, launch, operate or manage spacecraft and spacecraft subsystems for robotic or crewed missions. The primary goal is to assist attendees in attainment of their professional potential by providing them with a basic understanding of the interaction of radiation with non-biological and biological materials, the radiation environment, and the tools available to simulate and evaluate the effects of radiation on materials, circuits, and humans
Space Systems & Space Subsystems Fundamentals Technical Training Course SamplerJim Jenkins
This four-day course in space systems and space subsystems is for technical and management personnel who wish to gain an understanding of the important technical concepts in the development of space instrumentation, subsystems, and systems. The goal is to assist students to achieve their professional potential by endowing them with an understanding of the subsystems and supporting disciplines important to developing space instrumentation, space subsystems, and space systems. It designed for participants who expect to plan, design, build, integrate, test, launch, operate or manage subsystems, space systems, launch vehicles, spacecraft, payloads, or ground systems. The objective is to expose each participant to the fundamentals of each subsystem and their inter-relations, to not necessarily make each student a systems engineer, but to give aerospace engineers and managers a technically based space systems perspective. The fundamental concepts are introduced and illustrated by state-of-the-art examples. This course differs from the typical space systems course in that the technical aspects of each important subsystem are addressed.
AESA Airborne Radar Theory and Operations Technical Training Course SamplerJim Jenkins
The revolutionary active electronically scanned array (AESA) Radar provides huge gains in performance and all the front line fighters in the world from the Americans (F35, F22, F18, F15, F16) to the Europeans, Russians and Chinese already have one or soon will. This four day seminar, which took 10,000 man hours to produce, is a comprehensive treatment on the latest systems engineering technology required to design the modes for an AESA to capitalize on the systems inherent multi role, wide bandwidth, fast beam switching, and high power capabilities. Steve Jobs once said “You must provide the tools to let people become their best”, and this seminar will include two indispensable tools for the AESA engineer. 1) A newly written 400+ page electronic book with interactive calculations and simulations on the more complicated seminar subjects like STAP and Automatic Target Recognition. 2) A professionally designed spread sheet (with software) for designing, capturing and predicting the detection performance of the AESA modes including the challenging Alert-Confirm waveform.
Ati space, satellite,aerospace,engineering technical training courses catalog...Jim Jenkins
This document is a course catalog from Applied Technology Institute (ATI) that provides information about their technical training courses. ATI has been providing engineering and systems training courses since 1984 focusing on areas like cyber security, communications, defense, missiles, space systems, and more. The catalog advertises upcoming open enrollment courses along with the option to host courses on-site at a customer's location to save money with larger class sizes. It encourages readers to contact ATI to discuss hosting a course or bringing training to their organization.
This three day course is intended for practicing systems engineers who want to learn how to apply model-driven systems Successful systems engineering requires a broad understanding of the important principles of modern spacecraft communications. This three-day course covers both theory and practice, with emphasis on the important system engineering principles, tradeoffs, and rules of thumb. The latest technologies are covered. <p>
New catalog of ATI courses on Space, Satellite, Radar, Missile, Defense & Sys...Jim Jenkins
This document provides information about technical training courses offered by Applied Technology Institute (ATI) in various engineering disciplines including space systems, defense systems, communications, and more. It lists over 50 courses covering topics such as satellite communications, radar systems, cyber security, fiber optics, unmanned systems, systems engineering, and acoustics/sonar engineering. The document encourages readers to consider hosting an on-site course at their organization to save money compared to public courses. It details how ATI has been providing technical training since 1984 and can tailor on-site courses to meet organizations' specific training needs and objectives.
Communications Payload Design and Satellite System Architecture: Bent Pipe a...Jim Jenkins
This four-day course, ATI Courses.com's Communications Payload Design and Satellite System Architecture course , provides communications and satellite systems engineers and system architects with a comprehensive and accurate approach for the specification and detailed design of the communications payload and its integration into a satellite system. Both standard bent pipe repeaters and digital processors (on board and ground-based) are studied in depth, and optimized from the standpoint of maximizing throughput and coverage (single footprint and multi-beam). Applications in Fixed Satellite Service (C, X, Ku and Ka bands) and Mobile Satellite Service (L and S bands) are addressed as are the requirements of the associated ground segment for satellite control and the provision of services to end users.
This document is a catalog from Applied Technology Institute, LLC promoting their technical training courses. It provides an overview of ATI, which has been training professionals since 1984 in areas like defense, engineering, communications, space systems, and more. The catalog lists over 50 courses being offered between April and July 2013 on topics such as satellite systems, engineering, communications, systems engineering, and acoustics/sonar. It encourages bringing on-site training to organizations with 8 or more students to save on costs.
Ati courses technical training professional courses catalog development space...Jim Jenkins
The document is a catalog from Applied Technology Institute advertising their technical training courses. It provides an overview of ATI, which has been training professionals since 1984 in areas like defense, engineering, space systems, and more. The catalog highlights the benefits of hosting an on-site course for 8 or more students, which can save money compared to public courses. It provides an index of upcoming courses in areas like satellite communications, radar, missiles, and more.
Software Defined Radio Engineering course samplerJim Jenkins
This 3-day course is designed for digital signal processing engineers, RF system engineers, and managers who wish to enhance their understanding of this rapidly emerging technology. Most topics include carefully described design analysis, alternative approaches, performance analysis, and references to published research results. Many topics are illustrated by Matlab simulation demos. An extensive bibliography is included.
Satellite RF Communications and Onboard Processing Course SamplerJim Jenkins
Successful systems engineering requires a broad understanding of the important principles of modern satellite communications and onboard data processing. This course covers both theory and practice, with emphasis on the important system engineering principles, tradeoffs, and rules of thumb. The latest technologies are covered, including those needed for constellations of satellites.
This course is recommended for engineers and scientists interested in acquiring an understanding of satellite communications, command and telemetry, onboard computing, and tracking. Each participant will receive a complete set of notes.
Fundamentals of Passive and Active Sonar Technical Training Short Course SamplerJim Jenkins
This four-day course is designed for SONAR systems engineers, combat systems engineers, undersea warfare professionals, and managers who wish to enhance their understanding of passive and active SONAR or become familiar with the "big picture" if they work outside of either discipline. Each topic is presented by instructors with substantial experience at sea. Presentations are illustrated by worked numerical examples using simulated or experimental data describing actual undersea acoustic situations and geometries. Visualization of transmitted waveforms, target interactions, and detector responses is emphasized.
Space Environment & It's Effects On Space Systems course samplerJim Jenkins
This class on the space environment and its effects on space systems is for technical and management personnel who wish to gain an understanding of the important issues that must be addressed in the development of space instrumentation, subsystems, and systems. The goal is to assist students to achieve their professional potential by endowing them with an understanding of the fundamentals of the space environment and its effects. The class is designed for participants who expect to either, plan, design, build, integrate, test, launch, operate or manage payloads, subsystems, launch vehicles, spacecraft, or ground systems.
Each participant will receive a copy of the reference textbook: Pisacane, VL. The Space Environment and its Effects on Space Systems. AIAA Education Series, 2008.
Bioastronautics: Space Exploration and its Effects on the Human Body Course S...Jim Jenkins
This three-day course is intended for technical and managerial personnel who wish to be introduced to the effects of the space environment on humans. This course introduces bioastronautics from a fundamental perspective, assuming no prior knowledge of biology, physiology, or chemistry. The objective of the course is to provide the student with basic knowledge that will allow him or her to contribute more effectively to the human space exploration program. The human body, that through evolution is uniquely designed to function on the Earth, adapts to the space environment characterized by weightlessness and enhanced radiation. These alterations can impact the health and performance of astronauts, especially on return to the Earth.
Introduction of Cybersecurity with OSS at Code Europe 2024Hiroshi SHIBATA
I develop the Ruby programming language, RubyGems, and Bundler, which are package managers for Ruby. Today, I will introduce how to enhance the security of your application using open-source software (OSS) examples from Ruby and RubyGems.
The first topic is CVE (Common Vulnerabilities and Exposures). I have published CVEs many times. But what exactly is a CVE? I'll provide a basic understanding of CVEs and explain how to detect and handle vulnerabilities in OSS.
Next, let's discuss package managers. Package managers play a critical role in the OSS ecosystem. I'll explain how to manage library dependencies in your application.
I'll share insights into how the Ruby and RubyGems core team works to keep our ecosystem safe. By the end of this talk, you'll have a better understanding of how to safeguard your code.
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Topics covered:
• The role of a steering committee
• How do the organization’s priorities determine CoE Structure?
Speaker:
Chris Bolin, Senior Intelligent Automation Architect Anika Systems
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Direct losses from downtime in 1 minute = $5-$10 thousand dollars. Reputation is priceless.
As part of the talk, we will consider the architectural strategies necessary for the development of highly loaded fintech solutions. We will focus on using queues and streaming to efficiently work and manage large amounts of data in real-time and to minimize latency.
We will focus special attention on the architectural patterns used in the design of the fintech system, microservices and event-driven architecture, which ensure scalability, fault tolerance, and consistency of the entire system.
For the full video of this presentation, please visit: https://www.edge-ai-vision.com/2024/06/temporal-event-neural-networks-a-more-efficient-alternative-to-the-transformer-a-presentation-from-brainchip/
Chris Jones, Director of Product Management at BrainChip , presents the “Temporal Event Neural Networks: A More Efficient Alternative to the Transformer” tutorial at the May 2024 Embedded Vision Summit.
The expansion of AI services necessitates enhanced computational capabilities on edge devices. Temporal Event Neural Networks (TENNs), developed by BrainChip, represent a novel and highly efficient state-space network. TENNs demonstrate exceptional proficiency in handling multi-dimensional streaming data, facilitating advancements in object detection, action recognition, speech enhancement and language model/sequence generation. Through the utilization of polynomial-based continuous convolutions, TENNs streamline models, expedite training processes and significantly diminish memory requirements, achieving notable reductions of up to 50x in parameters and 5,000x in energy consumption compared to prevailing methodologies like transformers.
Integration with BrainChip’s Akida neuromorphic hardware IP further enhances TENNs’ capabilities, enabling the realization of highly capable, portable and passively cooled edge devices. This presentation delves into the technical innovations underlying TENNs, presents real-world benchmarks, and elucidates how this cutting-edge approach is positioned to revolutionize edge AI across diverse applications.
Skybuffer SAM4U tool for SAP license adoptionTatiana Kojar
Manage and optimize your license adoption and consumption with SAM4U, an SAP free customer software asset management tool.
SAM4U, an SAP complimentary software asset management tool for customers, delivers a detailed and well-structured overview of license inventory and usage with a user-friendly interface. We offer a hosted, cost-effective, and performance-optimized SAM4U setup in the Skybuffer Cloud environment. You retain ownership of the system and data, while we manage the ABAP 7.58 infrastructure, ensuring fixed Total Cost of Ownership (TCO) and exceptional services through the SAP Fiori interface.
Session 1 - Intro to Robotic Process Automation.pdfUiPathCommunity
👉 Check out our full 'Africa Series - Automation Student Developers (EN)' page to register for the full program:
https://bit.ly/Automation_Student_Kickstart
In this session, we shall introduce you to the world of automation, the UiPath Platform, and guide you on how to install and setup UiPath Studio on your Windows PC.
📕 Detailed agenda:
What is RPA? Benefits of RPA?
RPA Applications
The UiPath End-to-End Automation Platform
UiPath Studio CE Installation and Setup
💻 Extra training through UiPath Academy:
Introduction to Automation
UiPath Business Automation Platform
Explore automation development with UiPath Studio
👉 Register here for our upcoming Session 2 on June 20: Introduction to UiPath Studio Fundamentals: https://community.uipath.com/events/details/uipath-lagos-presents-session-2-introduction-to-uipath-studio-fundamentals/
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How information systems are built or acquired puts information, which is what they should be about, in a secondary place. Our language adapted accordingly, and we no longer talk about information systems but applications. Applications evolved in a way to break data into diverse fragments, tightly coupled with applications and expensive to integrate. The result is technical debt, which is re-paid by taking even bigger "loans", resulting in an ever-increasing technical debt. Software engineering and procurement practices work in sync with market forces to maintain this trend. This talk demonstrates how natural this situation is. The question is: can something be done to reverse the trend?
Connector Corner: Seamlessly power UiPath Apps, GenAI with prebuilt connectorsDianaGray10
Join us to learn how UiPath Apps can directly and easily interact with prebuilt connectors via Integration Service--including Salesforce, ServiceNow, Open GenAI, and more.
The best part is you can achieve this without building a custom workflow! Say goodbye to the hassle of using separate automations to call APIs. By seamlessly integrating within App Studio, you can now easily streamline your workflow, while gaining direct access to our Connector Catalog of popular applications.
We’ll discuss and demo the benefits of UiPath Apps and connectors including:
Creating a compelling user experience for any software, without the limitations of APIs.
Accelerating the app creation process, saving time and effort
Enjoying high-performance CRUD (create, read, update, delete) operations, for
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Russell Alfeche, Technology Leader, RPA at qBotic and UiPath MVP
Charlie Greenberg, host
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Tactical Missile Design
1. Professional Development Short Course On:
Tactical Missile Design - Integration
Instructor:
Eugene L. Fleeman
http://www.ATIcourses.com/schedule.htm
ATI Course Schedule:
http://www.aticourses.com/tactical_missile_design.htm
ATI's Tactical Missile Design:
All rights reserved. No part of this publication may be reproduced, distributed, or transmitted in any form or by any
means, or stored in a database or retrieval system, without the prior written permission of the Publisher and / or Author.
349 Berkshire Drive • Riva, Maryland 21140
888-501-2100 • 410-956-8805
Website: www.ATIcourses.com • Email: ATI@ATIcourses.com
2. Tactical Missile Design
January 12-14, 2009
Laurel, Maryland
April 13-15, 2009
Beltsville, Maryland
$1590
Summary (8:30am - 4:00pm)
This three-day short course covers the fundamentals quot;Register 3 or More & Receive $10000 each
of tactical missile design. The course provides a Off The Course Tuition.quot;
system-level, integrated method for missile
aerodynamic configuration/propulsion design and
analysis. It addresses the broad
range of alternatives in meeting
cost and performance
requirements. The methods
presented are generally simple
closed-form analytical
expressions that are physics-
based, to provide insight into the
primary driving parameters.
Configuration sizing examples are
Course Outline
presented for rocket-powered,
ramjet-powered, and turbo-jet
1. Introduction/Key Drivers in the Design Process.
powered baseline missiles.
Overview of missile design process. Unique characteristics of
Typical values of missile tactical missiles. Key aerodynamic configuration sizing
parameters and the characteristics of current parameters. Missile conceptual design synthesis process.
operational missiles are discussed as well as the Projected capability in C4ISR.
enabling subsystems and technologies for tactical
2. Aerodynamic Considerations in Tactical Missile
missiles and the current/projected state-of-the-art.
Design. Optimizing missile aerodynamics. Missile
Videos illustrate missile development activities and configuration layout (body, wing, tail) options. Selecting flight
missile performance. Finally, each attendee will design, control alternatives. Wing and tail sizing. Predicting normal
build, and fly a small air powered rocket. Attendees will force, drag, pitching moment, and hinge moment.
vote on the relative emphasis of the material to be
3. Propulsion Considerations. Turbojet, ramjet,
presented. Attendees receive course notes as well as
scramjet, ducted rocket, and rocket propulsion comparisons.
the textbook, Tactical Missile Design, 2nd edition. Turbojet engine design considerations. Selecting ramjet
engine, booster, and inlet alternatives. High density fuels.
Effective thrust magnitude control. Reducing propellant and
Instructor turbojet observables. Rocket motor prediction and sizing.
Ramjet engine prediction and sizing. Motor case and nozzle
Eugene L. Fleeman has more than 40 years of
materials.
government, industry, and academia
experience in missile system and 4. Weight Considerations. Structural design criteria
factor of safety. Structure concepts and manufacturing
technology development. Formerly a
processes. Selecting airframe materials. Loads prediction.
manager of missile programs at Georgia
Weight prediction. Motor case design. Aerodynamic heating
Tech, Boeing, Rockwell International,
prediction and insulation trades. Dome material alternatives.
and Air Force Research Laboratory, he Power supply and actuator alternatives.
is an internationally known lecturer on
5. Flight Trajectory Considerations. Aerodynamic
missiles and the author of over seventy publications
sizing-equations of motion. Maximizing flight performance.
including the AIAA textbook Tactical Missile Design. Benefits of flight trajectory shaping. Flight performance
prediction of boost, climb, cruise, coast, ballistic, maneuvering,
and homing flight.
What You Will Learn
6. Measures of Merit and Launch Platform Integration.
• Key drivers in the missile design process.
Achieving robustness in adverse weather. Seeker, data link,
• Critical tradeoffs, methods and technologies in and sensor alternatives. Counter-countermeasures. Warhead
subsystems, aerodynamic, propulsion, and structure alternatives and lethality prediction. Alternative guidance laws.
sizing. Proportional guidance accuracy prediction. Time constant
contributors and prediction. Maneuverability design criteria.
• Launch platform-missile integration.
Radar cross section and infrared signature prediction.
• Robustness, lethality, accuracy, observables,
Survivability considerations. Cost drivers of schedule, weight,
survivability, reliability, and cost considerations.
learning curve, and parts count. Designing within launch
• Missile sizing examples. platform constraints. Storage, carriage, launch, and separation
• Missile development process. environment. Internal vs. external carriage.
7. Sizing Examples and Sizing Tools. Trade-offs for
extended range rocket. Sizing for enhanced maneuverability.
Who Should Attend Ramjet missile sizing for range robustness. Turbojet missile
The course is oriented toward the needs of missile sizing for maximum range. Computer aided sizing tools for
engineers, analysts, marketing personnel, program conceptual design. Soda straw rocket design, build, and fly.
managers, university professors, and others working in House of quality process. Design of experiment process.
the area of missile analysts, marketing personnel and 8. Development Process. Design validation/technology
technology development. Attendees will gain an development process. New missile follow-on projections.
understanding of missile design, missile technologies, Examples of development facilities. New technologies for
launch platform integration, missile system measures tactical missiles.
of merit, and the missile system development process.
9. Summary and Lessons Learned.
Register online at www.ATIcourses.com or call ATI at 888.501.2100 or 410.956.8805
30 – Vol. 95
3. www.ATIcourses.com
Boost Your Skills 349 Berkshire Drive
Riva, Maryland 21140
with On-Site Courses Telephone 1-888-501-2100 / (410) 965-8805
Tailored to Your Needs
Fax (410) 956-5785
Email: ATI@ATIcourses.com
The Applied Technology Institute specializes in training programs for technical professionals. Our courses keep you
current in the state-of-the-art technology that is essential to keep your company on the cutting edge in today’s highly
competitive marketplace. Since 1984, ATI has earned the trust of training departments nationwide, and has presented
on-site training at the major Navy, Air Force and NASA centers, and for a large number of contractors. Our training
increases effectiveness and productivity. Learn from the proven best.
For a Free On-Site Quote Visit Us At: http://www.ATIcourses.com/free_onsite_quote.asp
For Our Current Public Course Schedule Go To: http://www.ATIcourses.com/schedule.htm
4. Outline
Introduction / Key Drivers in the Missile Design - Integration Process
Aerodynamic Considerations in Missile Design - Integration
Propulsion Considerations in Missile Design - Integration
Weight Considerations in Missile Design - Integration
Flight Performance Considerations in Missile Design - Integration
Measures of Merit and Launch Platform Integration
Sizing Examples
Missile Development Process
Summary and Lessons Learned
References and Communication
Appendices ( Homework Problems / Classroom Exercises, Example of
Request for Proposal, Nomenclature, Acronyms, Conversion Factors,
Syllabus )
3/3/2009 ELF 2
5. Missile Design Should Be Conducted in a
System-of-Systems Context
Example: Typical US Carrier Strike Group Complementary Missile Launch Platforms / Load-out
JASSM, SLAM, Harpoon, JSOW, JDAM, Maverick, HARM, GBU-10, GBU-5, Penguin, Hellfire
Air-to-Surface:
AMRAAM, Sparrow, Sidewinder
Air-to-Air:
SM-3, SM-2, Sea Sparrow, RAM
Surface-to-Air:
Tomahawk, Harpoon
Surface-to-Surface:
3/3/2009 ELF 3
6. Pareto Effect: Only a Few Parameters
Drive the Design
Example: Rocket Baseline Missile ( Sparrow ) Maximum Flight Range
Example:
•Rocket Baseline: Launch @ Altitude = 20k ft, Mach Number = 0.7;
Terminate @ Flight Range = 9.5 nm ( Mach Number = 1.5 )
•Top Four Parameters Drive 85% of Maximum Flight Range Sensitivity
3/3/2009 ELF 4
7. Missile Synthesis Is a Creative Process That
Requires Evaluation of Alternatives and Iteration
Define Mission Requirements
Alt Mission
Establish Baseline
Alt Baseline
Aerodynamics
Propulsion
Resize / Alt Config / Subsystems / Tech
Weight
Trajectory
Meet No
Performance?
Yes
No
Measures of Merit and Constraints
Yes
3/3/2009 ELF 5
9. Subsonic Cruise Missiles Have
Relatively Large Wings
JASSM Apache Taurus
CALCM Naval Strike Missile Tomahawk
Harpoon ANAM / Gabriel 5
Permission of Missile Index. 7
3/3/2009 ELF
10. Wing, Tail, and Canard Panel Geometry Trade-off
ctip
cMAC b/2
yCP
croot
Double
Triangle Aft Swept LE
Rectangle
Swept LE
( Delta ) Bow Tie
Parameter Trapezoid
Variation xAC –
yCP ( Bending / Friction ) – –
Supersonic Drag –
RCS –
Span Constraint –
Stability & Control
Aeroelastic Stab. –
Note: Superior Good Average Poor
= Taper ratio = ctip / croot
A = Aspect ratio = b2 / S = 2 b / [( 1 + ) croot ] –
yCP = Outboard center-of-pressure = ( b / 6 ) ( 1 + 2 ) / ( 1 + )
Based on equal surface area and equal span.
cMAC = Mean aerodynamic chord = ( 2 / 3 ) croot ( 1 + + ) / ( 1 + )
2
Surface area often has more impact than geometry.
3/3/2009 ELF 8
11. Examples of Inlets for
Current Supersonic Air-Breathing Missiles
United Kingdom
Sea Dart GWS-30 Meteor
France
ASMP ANS
Russia
AS-17 / Kh-31 Kh-41 SS-N-22 / 3M80
SA-6 SS-N-19 SS-N-26
China
C-101 C-301
Taiwan
Hsiung Feng III
India
BrahMos
• Aft inlets have lower inlet volume and do not degrade lethality of forward located warhead.
• Nose Inlet may have higher flow capture, pressure recovery, smaller carriage envelope, and lower drag.
3/3/2009 ELF 9
12. Conventional Solid Rocket Thrust-Time Design
Alternatives - Propellant Cross Section Geometry
Example Mission Thrust Profile Example Web Cross Section Geometry / Volumetric Loading
• Cruise
Thrust ( lb ) Thrust ( lb )
Constant ~ 82% ~95% ~90%
Thrust
Burning Time ( s ) End Burner Radial Slotted Tube
•Dive at
~ 79%
constant Regressive
dynamic Thrust
pressure
Burning Time ( s )
•Climb at
Thrust ( lb ) Thrust ( lb )
~ 87%
constant
Progressive
dynamic
Thrust
pressure
Burning Time ( s )
•Fast launch – Extrusion Production of Star Web
cruise ~ 85% Propellant. Photo Courtesy of BAE.
Boost-Sustain
Burning Time ( s )
•Fast launch –
Thrust ( lb )
Boost-Sustain-Boost
cruise – high
~ 85%
speed terminal
Medium Burn Rate Propellant
Burning Time ( s )
Note: High thrust and chamber pressure require large surface burn area. High Burn Rate Propellant
3/3/2009 ELF 10
13. Missile Weight Is Driven by Body Volume
( i.e., Diameter and Length )
WL = 0.04 l d2
10000
Units: WL( lb ), l ( in ), d ( in )
WL, Missile Launch Weight, lb
1000
Example for Rocket Baseline:
100 l = 144 in
d = 8 in
WL = 0.04 ( 144 ) ( 8 )2 = 0.04 ( 9216 ) = 369 lb
10
100 1000 10000 100000 1000000
ld2, Missile Length x Diameter2, in3
FIM-92 SA-14 Javelin RBS-70 Starstreak Mistral HOT Trigat LR
LOCAAS AGM-114 Roland RIM-116 Crotale AIM-132 AIM-9M Magic 2
Mica AA-11 Python 3 AIM-120C AA-12 Skyflash Aspide AIM-9P
Super 530F Super 530D AGM-65G PAC-3 AS-12 AGM-88 Penguin III AIM-54C
Armat Sea Dart Sea Eagle Kormoran II AS34 AGM-84H MIM-23F ANS
MM40 AGM-142 AGM-86C SA-10 BGM-109C MGM-140 SSN-22 Kh-41
3/3/2009 ELF 11
14. Strength – Elasticity of
Airframe Material Alternatives
t = P / A = E
Kevlar Fiber S-Glass Fiber Note:
w / o Matrix w / o Matrix • High strength fibers are:
400 – Very small diameter
Carbon Fiber
– Unidirectional
w / o Matrix
– High modulus of
( 400 – 800 Kpsi )
elasticity
300 – Very elastic
– No yield before failure
Very High Strength Stainless Steel
t, Tensile Stress, – Non forgiving failure
( PH 15-7 Mo, CH 900 )
103 psi • Metals:
High Strength Stainless Steel
200 – More ductile, yield s
( PH 15-7 Mo, TH 1050 )
before failure
– Allow adjacent structure
Titanium Alloy ( Ti-6Al-4V )
to absorb load
– Resist crack formation
100 – Resist impact loads
Aluminum Alloy ( 2219-T81 ) – More forgiving failure
E, Young’s modulus of elasticity, psi
0 P, Load, lb
0 1 2 3 4 5 , Strain, in / in
A, Area, in2
, Strain, 10-2 in / in Room temperature
3/3/2009 ELF 12
15. Composites Are Good Insulators for High
Temperature Structure and Propulsion ( cont )
Graphites
6,000 • Burn
Medium Density Phenolic
• ~ 0.08 lbm / in3
Composites
• Carbon / Carbon
• Char
5,000 • ~ 0.06 lbm / in3
Bulk Ceramics
• Nylon Phenolic, Silica
• Melt
• ~ 0.20 lbm / in Phenolic, Glass
3
4,000 • Zirconium Ceramic, Phenolic, Carbon
Hafnium Ceramic Phenolic, Graphite
Tmax, Max Phenolic
Porous Ceramics
Low Density
• Melt
Temperature 3,000 Composites
• Resin Impregnated
Capability, • ~ 0.12 lbm / in3
• Char
• ~ 0.03 lbm / in3
• Carbon-Silicon
R Carbide • Micro-Quartz
2,000 Paint, Glass-
Cork-Epoxy,
Plastics
Carbon -
• Sublime Silicone Rubber,
• Depolymerizing
1,000 Kevlar-EDPM
• ~ 0.06 lbm / in3
• Teflon
0
0 1 2 3 4
Insulation Efficiency, Minutes To Reach 300 °F at Back Wall
Assumed Weight Per Unit Area of Insulator / Ablator = 1 lb / ft2
Note:
3/3/2009 ELF 13
16. Examples of Aerodynamic Hot Spots
Nose Tip
Leading Edge
Flare
Notional Missile Aero Heating
Video of Radiometric Imagery – SM-3 Flight
3/3/2009 ELF 14
17. 3-DOF Simplified Equations of Motion Show
Drivers for Configuration Sizing
+ Normal Force + Thrust
<< 1 rad
V
+ Moment
W
+ Axial Force
Configuration Sizing Implication
.. ..
High Control Effectiveness Cm > Cm, Iy small
y y α q SRef d Cm + q SRef d Cm
( W small ), q large
.
Large / Fast Heading Change CN large, W
( W / gc ) SRef V CN / 2 + SRef V CN / 2 +
small, large ( low alt ), V large, T / V large
( T sin ) / V – ( W / V ) cos
.
High Speed / Long Range Total Impulse large,
( W / gc ) V T - CA SRef q - CN 2 SRef q - W sin
CA small, q small
Note: Based on aerodynamic control
3/3/2009 ELF 15
18. High Missile Velocity and Target Lead Required
to Intercept High Speed Crossing Target
VM sin L = VT sin A, Constant Bearing ( L = const ) Trajectory
4
VM VT
LA
Note:
3 Constant Bearing
VM = Missile Velocity
VM / VT VT = Target Velocity
A = Target Aspect
L = Missile Lead Angle
2 Seeker Gimbal
A = 90°
Example:
A = 45°
1 L = 30 deg
A = 45 deg
VM / VT = sin ( 45 ) / sin ( 30 ) =
1.42
0
0 10 20 30 40 50
L, Lead Angle, Deg
3/3/2009 ELF 16
19. A Radar Seeker / Sensor Is More Robust in
Adverse Weather
O2, H2O
1000 Note:
EO attenuation through
cloud @ 0.1 g / m3 and 100
m visibility
100
H2O H2O EO attenuation through
ATTENUATION (dB / km)
CO2
O2 rain @ 4 mm / h
Humidity @ 7.5 g / m3
10
Millimeter wave and
H2O
O3 microwave attenuation
H2O, CO2
O2 through cloud @ 0.1
CO2
gm / m3 or rain @ 4 mm / h
1 H2O
20° C Attenuation by absorption,
H2O 1 ATM scattering, and reflection
EO sensors are ineffective
0.1
through cloud cover
X Ku K Ka Q V W Very Long Long Mid Short Clouds have greater effect
RADAR on attenuation than
VISIBLE
INFRARED
SUBMILLIMETER
MILLIMETER
0.01
“greenhouse gases”, such
10 GHz 100 1 THz 10 100 1000
3 cm 3 mm 0.3 mm 30 µm 3.0 µm 0.3 µm as H2O and CO2
Radar sensors have good to
Increasing Frequency
superior performance
Increasing Wavelength
through cloud cover and
rain
Source: Klein, L.A., Millimeter-Wave and Infrared Multisensor Design and Signal Processing, Artech House, Boston, 1997
3/3/2009 ELF 17
20. An Imaging Sensor Enhances
Target Acquisition / Discrimination
Imaging LADAR Imaging Infrared SAR
Passive Imaging mmW Video of Imaging Infrared Video of SAR Physics
3/3/2009 ELF 18
21. GPS / INS Allows Robust Seeker Lock-on in
Adverse Weather and Clutter
Target Image
480 Pixels
640 Pixels ( 300 m ) 175 m
Seeker Lock-on @ 500 m to go ( 1 pixel = 0.27 m )
Seeker Lock-on @ 850 m to go ( 1 pixel = 0.47 m )
3 m GPS / INS error nM = 0.44 g, < 0.1 m
3 m GPS / INS error nM = 0.15 g, < 0.1 m req
req
88 m 44 m
Seeker Lock-on @ 250 m to go ( 1 pixel = 0.14 m ) Seeker Lock-on @ 125 m to go ( 1 pixel = 0.07 m )
3 m GPS / INS error nM = 1.76 g, < 0.1 m 3 m GPS / INS error nM = 7.04 g, = 0.2 m
req req
Note: = Target Aim Point and Seeker Tracking Gate, GPS / INS Accuracy = 3 m, Seeker 640 x 480 Image, Seeker
FOV = 20 deg, Proportional Guidance Navigation Ratio = 4, Velocity = 300 m / s, G&C Time Constant = 0.2 s.
3/3/2009 ELF 19
22. A Target Set Varies in Size and Hardness
Lethality
Example of Precision Strike Target Set
Air Defense ( SAMs,
Launch Platform
Robustness
Integration /
Firepower
Lethality
Cost
AAA ) Miss Distance
Reliability
Carriage and
Other
Launch
Survivability
Observables
Considerations
Armor
TBM / TELs
Artillery
C3II
Naval
Counter Air
Oil
Transportation Choke
Aircraft
Refineries
Points ( Bridges,
Railroad Yards, Truck
Parks )
Examples of Targets where Size and Hardness Drive Warhead Design
/ Technology
•Small Size, Hard Target: Tank Small Shaped Charge, EFP, or KE
Warhead
•Deeply Buried Hard Target: Bunker Long KE / Blast Frag Warhead
•Large Size Target: Building Large Blast Frag Warhead
Video Examples of Precision Strike
Targets / Missiles
3/3/2009 ELF 20
23. Accurate Guidance Enhances Lethality
AIM-7 Sparrow 77.7 lb blast / frag
warhead
Typical Aircraft Target
Vulnerability
PK > 0.5 if < 5 ft ( p > 330 psi,
fragments impact energy > 130k ft-
lb / ft2 )
PK > 0.1 if < 25 ft ( p > 24 psi,
fragments impact energy > 5k ft-lb
/ ft2 )
Rocket Baseline Warhead ( 77.7 lb, C / M = 1 ),
Spherical Blast / Fragment Pattern, h = 20k ft,
Typical Aircraft Target
Video of AIM-7 Sparrow Warhead ( Aircraft Targets )
3/3/2009 ELF 21
24. Accurate Guidance Enhances Lethality ( cont )
BILL- Two 1.5 kg EFP warheads ….
Roland 9 kg warhead: multi-projectiles from preformed case………………
2.4 m
Hellfire 24 lb shaped charge witness
warhead ………………………….. plate
Guided MLRS 180 lb blast
fragmentation warhead Video: BILL, Roland, Hellfire, and Guided
MLRS warheads
3/3/2009 ELF 22
25. Examples of Terminal Guidance Laws
Active Seeker Transmitted Energy Miss Distance
1. Homing Active /
Launch Platform
Integration / Robustness
Firepower
Lethality
Cost
Seeker
Passive Seeker
Miss Distance
Reliability
Observables
Survivability
Target Reflected / Emitted Energy
Guidance
Launch / Midcourse Guidance
Semi-Active Seeker
2. Homing Semi-
Active Seeker
Guidance
Target Reflected Energy
Fire Control System Tracks Target
3. Command
Guidance
Rear-looking Sensor Detects
Fire Control System Energy
Fire Control System Tracks Target, Tracks Missile, and Command Guides Missile
3/3/2009 ELF 23
26. A Collision Intercept Has Constant Bearing for a
Constant Velocity, Non-maneuvering Target
Example of Collision Intercept
Example of Miss
( Line-of-Sight Angle Constant )
( Line-of-Sight Angle Diverging ) .
.
( Line-of-Sight Angle Rate L 0 ) ( Line-of-Sight Angle Rate L = 0 )
Overshoot Miss
t2
t1
( LOS t1
)1 > (
LO S
)0 ( LOS )1 = ( LOS )0
t0 t0
L
L
Seeker Line-of-Sight Seeker Line-of-Sight A
A
Missile Target Missile Target
Note: L = Missile Lead
A = Target Aspect
3/3/2009 ELF 24
27. Examples of Weapon Bay Internal Carriage and
Load-out
Center Weapon Bay Best for Ejection Launchers
F-22 Semi-Bay Load-out: 2 SDB, 1 AIM-120C F-117 Bay Load-out: 1 GBU-27, 1 GBU-10 B-1 Single Bay Load-out: 8 GBU-31
Video Side Weapon Bay Best for Rail Launchers
F-22 Carriage ( AMRAAM / JDAM / AIM-9 ) F-22 Side Bay: 1 AIM-9 in Each Side Bay RAH-66 Side Bay: 1 AGM-114, 2 FIM-
92, 4 Hydra 70 in Each Side Bay 25
3/3/2009 ELF
28. Minimum Smoke Propellant Has
Low Launch Plume Observables
Reduced Smoke Example: AIM-120 Minimum Smoke Example: Javelin
High Smoke Example: AIM-7
Contrail ( HCl from AP oxidizer ) at T < Contrail ( H2O ) at T < -35º F
Particles ( e.g., metal fuel oxide )
-10° F atmospheric temperature. atmospheric temperature.
at all atmosphere temperature.
High Smoke Motor
Reduced Smoke Motor
Minimum Smoke Motor
3/3/2009 ELF 26
29. Examples of Alternative Approaches for
Precision Strike Missile Survivability Launch Platform
Robustness
Integration /
Firepower
Lethality
Cost
1. Low Other Survivability
Miss Distance
Reliability
Observables
Survivability
Observables, Considerations
High Altitude
2. Mission Planning /
Cruise, High
Threat Avoidance /
Speed 4. High g Terminal
Lateral Offset Flight Maneuvering
3. Low Altitude Terrain Masking / Clutter
Video of Tomahawk Using Terrain Following
3/3/2009 ELF 27
30. Examples of Survivability Configured Missiles
High Speed
SS-N-27 Sizzler ( Supersonic Rocket
SS-N-22 Sunburn ( Ramjet Propulsion )
Penetrator after Subsonic Turbojet Flyout )
Low RCS
NSM ( Faceted Dome, Roll Dome with Inlet Top or Bottom, JASSM ( Flush Inlet, Window Dome, Swept
Swept Surfaces, Body Chines, Composite Structure ) Surfaces, Trapezoidal Body, Composite Structure
)
3/3/2009 ELF 28
31. High System Reliability Provided by Few Events,
High Subsystem Reliability and Low Parts Count Launch Platform
Robustness
Integration /
Firepower
Lethality
Cost
Miss Distance
Reliability
Observables
Survivability
Reliability
Rsystem .RSubsystem1 X RSubsystem2 X …
Example: Rsystem RArm X RLaunch X
RStruct X RAuto X RAct X RSeeker X RIn Guid
X RPS X RProp X RFuze X RW/H 0.94
Example Video of Weapon System with
Many Events: Sensor Fuzed Weapon ( SFW )
Note: Typical max reliability
Typical min reliability
3/3/2009 ELF 29
32. EMD Cost Is Driven by Schedule Duration and
Risk
CEMD = $20,000,000 tEMD1.90, ( tEMD in years )
Example:
5 year ( medium risk ) EMD program
CEMD = $20,000,000 tEMD1.90
High
Low Moderate = ( 20,000,000 ) ( 5 )1.90
Risk
Risk Risk = $426,000,000
EMD
EMD EMD
D
Note: EMD required schedule duration depends upon risk. Should not ignore risk in shorter schedule.
-- Source of data: Nicholas, T. and Rossi, R., “U.S. Missile Data Book, 1999,” Data Search Associates, 1999
– EMD cost based on 1999 US$
3/3/2009 ELF 30
33. Learning Curve and Large Production Reduce
Unit Production Cost
Cx = C1st Llog2x, C2x = L Cx , where C in U.S. 99$
1 L = 1.0
Cx / C1st, Cost of Unit x / Cost of First Unit
Javelin ( L = 0.764, C1st = $3.15M,
Y1 = 1994 )
Longbow HF ( L = 0.761, C1st =
L = 0.9
$4.31M, Y1 = 1996 )
AMRAAM ( L = 0.738, C1st =
$30.5M, Y1 = 1987 )
0.1
Example: MLRS ( L = 0.811, C1st = $0.139M,
Y1 = 1980 )
For a learning
curve coefficient HARM ( L = 0.786, C1st = $9.73M,
L = 0.8
of L = 80%, cost of Y1 = 1981 )
unit #1000 is 11% JSOW ( L = 0.812, C1st = $2.98M,
the cost of the first Y1 = 1997 )
L = 0.7
unit Tomahawk ( L = 0.817, C1st =
0.01
$13.0M, Y1 = 1980 )
1 10 100 1000 10000 100000 1E+06
Labor intensive learning curve: L < 0.8
Machine intensive learning curve: L > 0.8 )
x, Number of Units Produced
Contributors to the learning curve include:
• More efficient labor
• Reduced scrap
Source of data: Nicholas, T. and Rossi, R., “U.S. Missile Data Book,
• Improved processes
1999,” Data Search Associates, 1999
• New missile components fraction
3/3/2009 ELF 31
35. Store Compatibility Wind Tunnel Tests Are
Required for Aircraft Launch Platforms
F-18 Store Compatibility Test in AEDC 16T AV-8 Store Compatibility Test in AEDC 4T
Types of Wind Tunnel Testing for Store Compatibility
- Flow field mapping with probe
- Flow field mapping with store
- Captive trajectory simulation
- Drop testing
- Carriage Loads
Example Stores with Flow Field Interaction: Kh-41 + AA-10
3/3/2009 ELF 33
36. Compressed Carriage Missiles Provide Higher
Firepower
Baseline AIM-120B AMRAAM
Compressed Carriage AIM-120C AMRAAM ( Reduced Span Wing / Tail )
Baseline AMRAAM: Load-out
of 2 AIM-120B per F-22 Semi-
Bay
17.5 in 17.5 in
Compressed Carriage
AMRAAM: Load-out of 3
AIM-120C per F-22 Semi-Bay
12.5 in 12.5 in 12.5 in
Video of Longshot Kit on CBU-87 / CEB
Note: Alternative approaches to compressed carriage include surfaces with small span, folded surfaces, wrap
around surfaces, and planar surfaces that extend ( e.g., switch blade, Diamond Back, Longshot ).
3/3/2009 ELF 34
37. Robustness Is Required for Storage, Shipping,
and Launch Platform Carriage Environment
Environmental Parameter Typical Requirement Video: Ground / Sea Environment
Surface Temperature -60° F* to 160° F
Surface Humidity 5% to 100%
Rain Rate 120 mm / h**
Surface Wind 100 km / h steady***
150 km / h gusts****
Salt fog 3 g / mm2 deposited per year
10 g rms at 1,000 Hz: MIL STD 810, 648, 1670A
Vibration
Drop height 0.5 m, half sine wave 100 g / 10 ms: MIL STD 810, 1670A
Shock
160 dB
Acoustic
Note: MIL-HDBK-310 and earlier MIL-STD-210B suggest 1% world-wide climatic extreme typical requirement.
* Lowest recorded temperature = -90° F. 20% probability temperature lower than -60° F during worst month /
location.
** Highest recorded rain rate = 436 mm / h. 0.5% probability greater than 120 mm / h during worst month / location.
*** Highest recorded steady wind = 342 km / h. 1% probability greater than 100 km / h during worst month / location.
**** Highest recorded gust = 378 km / h. 1% probability greater than 150 km / h during worst month of worst location.
3/3/2009 ELF 35
Typical external air carriage maximum hours less for aircraft ( 100 h ) than for helicopter ( 1000 h ).
38. House of Quality Translates Customer
Requirements into Engineering Emphasis
0
- -
Body ( Material, Tail ( Material, Number, Nose Plug ( Material,
Chamber Length ) Area, Geometry ) Length )
7 2 1
5
Flight Range
4 1 5
2
Weight
1 2 7
3
Cost
46 = 5 x 7 + 2 x 4 + 3 x 1 18 = 5 x 2 + 2 x 1 + 3 x 2 36 = 5 x 1 + 2 x 5 + 3 x 7
1 3 2
Note: Based on House of Quality, inside chamber length most important design parameter.
Note on Design Characteristics Sensitivity 1 - Customer Requirements
Matrix: ( Room 5 ):
2 – Customer Importance Rating ( Total = 10 )
++ Strong Synergy 3 – Design Characteristics
+ Synergy 4 – Design Characteristics Importance Rating ( Total = 10 )
0 Near Neutral Synergy 5 – Design Characteristics Sensitivity Matrix
6 – Design Characteristics Weighted Importance
- Anti-Synergy
7 – Design Characteristics Relative Importance
- - Strong Anti-Synergy
3/3/2009 ELF 36
39. Relationship of Design Maturity to the US
Research, Technology, and Acquisition Process
Research Technology Acquisition
6.1 6.2 6.3 6.4 6.5
Engineering
Basic Exploratory Advanced Demonstration System
and Production
Research Development Development & Validation Upgrades
Manufacturing
Development
~ $0.1B ~ $0.3B ~ $0.9B ~ $0.5B ~ $1.0B ~ $6.1B ~ $1.2B
Maturity Level Conceptual Design Preliminary Design Detail Design Production Design
Drawings ( type ) < 10 ( subsystems ) < 100 ( components ) > 100 ( parts ) > 1000 ( parts )
First
Technology Prototype Full Scale 1-3 Block
Technology
Limited Block
Development Demonstration Development Upgrades
Demonstration
~ 2 Years ~ 5
~ 10 Years ~ 4 Years ~ 5 Years ~ 5-15 Years
~ 8 Years
Years
Production
Note:
Total US DoD Research and Technology for Tactical Missiles $1.8 Billion per year
Total US DoD Acquisition ( EMD + Production + Upgrades ) for Tactical Missiles $8.3 Billion per year
Tactical Missiles 11% of U.S. DoD RT&A budget
US Industry IR&D typically similar to US DoD 6.2 and 6.3A
3/3/2009 ELF 37
40. US Tactical Missile Follow-On Programs Occur
about Every 24 Years
Short Range ATA, AIM-9, 1949 - Raytheon AIM-9X ( maneuverability ), 1996 - Hughes
AIM-120 ( autonomous, speed,
Medium Range ATA, AIM-7,1951 - Raytheon Hypersonic Missile, > 2009
range, weight ), 1981 - Hughes
Anti-radar ATS, AGM-45, 1961 - TI AGM-88 ( speed, range ), 1983 - TI Hypersonic Missile > 2009
PAC-3 (accuracy), 1992 - Lockheed Martin
Long Range STA, MIM-104, 1966 - Raytheon
Man-portable STS, M-47, 1970 - McDonnell Douglas Javelin ( gunner survivability,
lethality, weight ), 1989 - TI
Long Range STS, BGM-109, 1972 - General Dynamics Hypersonic Missile > 2009
Long Range ATS, AGM-86, 1973 - Boeing AGM-129 ( RCS ), 1983 - General Dynamics
Medium Range ATS, AGM-130, 1983 - Rockwell JASSM ( cost, range,
observables ), 1999 - LM
1950 1965 1970 1975 1980 1985 1990 1995 > 2000
Year Entering EMD
3/3/2009 ELF 38
41. Missile Design Validation / Technology
Development Is an Integrated Process
•Rocket Static
•Turbojet Static IM Tests
Propulsion
•Ramjet Tests
–Direct Connect
Propulsion Model
Structure Tests
–Freejet
•Static
Airframe
•Vibration
Wind Tunnel
Aero Model
Tests Hardware Flight Test Progression
In-Loop
Guidance ( Captive Carry, Jettison,
Simulation Separation, Guided
and Control Model Digital Simulation
Unpowered Flights, Guided
Powered Flights, Guided
Tower
Seeker Live Warhead Flights )
Lab Tests Tests
Actuators / Initiators
Sensors Lab Tests
Environment
Autopilot / Electronics Tests
•Vibration
Power
•Temperature
Supply
Sled Tests
Ballistic Tests
Warhead Witness / Arena Tests IM Tests
3/3/2009 ELF 39
42. Conduct Balanced, Unbiased Trade-offs
Propulsion
Aerodynamics
Production
Structures
Seeker
Guidance and
Control
Warhead – Fuze
3/3/2009 ELF 40