The document discusses the evolution of electrical systems engineering for missiles and space vehicles. Early missile programs involved parallel subsystem design with minimal coordination, but the V2 program established the need for overall systems engineering. The Mercury program applied this approach and introduced additional safety systems to protect astronauts, including redundant abort systems. Electrical systems play a key role in integrating complex functions like engine control, flight sequencing, telemetry and more across multiple stages in large modern rockets like Saturn.
The document summarizes a flight test campaign conducted by Boeing in November 2007 using an Unmanned Little Bird (ULB) helicopter to demonstrate sensor and avionics technologies relevant for future lunar and planetary landers. Over 13 flight test hours were performed across 14 flights. Experiments included emulating lunar lander descent trajectories, testing a 3D imaging LADAR system, evaluating a passive imaging system for crater navigation, and demonstrating a precision radio beacon navigation system. All experiments were successfully completed and yielded satisfactory results, validating the technologies for real-time testing in environments simulating the moon or Mars.
The document outlines a proposed mission, called Program INCEP, to investigate the composition and structure of comet 209P/LINEAR using a 6U cubesat. The mission objectives include performing a flyby of the comet with optical and infrared imaging and spectroscopy to analyze the comet's composition and estimate its mass. The cubesat design includes an ion thruster, cameras, spectrometers, an X-band radio for communications, and deployable solar panels. Trajectory analysis shows the cubesat can perform a flyby with the required instruments using its propulsion budget.
This document is a project report submitted by three students for their Bachelor of Technology degree. It outlines the design and implementation of an unmanned aerial vehicle (UAV) in the form of a quadcopter for campus surveillance. The quadcopter will house a camera and use a wireless transmission system to provide live video feed from the camera to a ground station. Sensors such as an IMU and GPS will be used to help stabilize and navigate the quadcopter. An onboard processor and flight controller using Arduino will control the quadcopter. The project aims to develop a low-cost and lightweight surveillance drone.
The document discusses lessons learned from developing the Solar Dynamics Observatory (SDO) satellite. It notes that 484 problem reports were filed during development and testing, with 19 resulting in serious project issues or risks at launch. Many issues were due to design errors or interactive complexity between subsystems that were only discovered after system integration testing. The two instruments with the most complexity, HMI and AIA, accounted for many problem reports. On-orbit, SDO has exceeded science requirements with only two minor issues occurring after launch.
Design and Structural Analysis for an Autonomous UAV System Consisting of Sla...IOSR Journals
An Unmanned Aerial Vehicle (UAV) is an aircraft without a human pilot. It can either be controlled manually by a pilot on the ground using a trans-receiver or it can be programmed to operate autonomously. In this proposed control system, multiple slave Micro Aerial Vehicles(MAV) are dispatched from a master UAV for surveillance. All the MAVs are synchronized with each other through the master UAV which highlights their purpose and position. The master UAV acts as a mobile base for the surveillance, it stores the data collected by the MAVs and transmits them to a remote base. A design of the UAV-MAV system and its performance analysis is presented.
This document summarizes research on autonomous attitude control for quadcopter unmanned aerial vehicles. It provides background on quadcopters and their components. It then describes various control system designs for quadcopters, including automatic landing, take-off, navigation, and attitude control systems. It specifically discusses the use of proportional-integral-derivative (PID) control algorithms for attitude control and references previous research applying PID control that demonstrated stable flight and attitude stabilization.
The SAGAN mission proposes using a constellation of four microsatellites in a tetrahedral formation to study the impact of atmospheric waves, neutral forcing, and ionospheric currents on low and mid-latitude plasma structuring. The satellites would carry instruments to measure electric and magnetic fields, electron density, and ion composition. Maintaining the tetrahedral formation over multiple orbital planes would allow for spatial correlation measurements to understand plasma dynamics in the ionosphere. The proposed one to two year mission aims to advance understanding of ionospheric coupling processes.
The telemetry, tracking, and command (TT&C) subsystem allows ground stations to monitor and control satellites. It performs functions like controlling the satellite's orbit and attitude, realigning antennas, receiving and executing commands, tracking the satellite's position, and modulating and transmitting telemetry data about things like voltage, temperature, and tank pressures to ground stations. The subsystem consists of separate telemetry, tracking, and command subsystems that work together to monitor the satellite's conditions and control it from the ground.
The document summarizes a flight test campaign conducted by Boeing in November 2007 using an Unmanned Little Bird (ULB) helicopter to demonstrate sensor and avionics technologies relevant for future lunar and planetary landers. Over 13 flight test hours were performed across 14 flights. Experiments included emulating lunar lander descent trajectories, testing a 3D imaging LADAR system, evaluating a passive imaging system for crater navigation, and demonstrating a precision radio beacon navigation system. All experiments were successfully completed and yielded satisfactory results, validating the technologies for real-time testing in environments simulating the moon or Mars.
The document outlines a proposed mission, called Program INCEP, to investigate the composition and structure of comet 209P/LINEAR using a 6U cubesat. The mission objectives include performing a flyby of the comet with optical and infrared imaging and spectroscopy to analyze the comet's composition and estimate its mass. The cubesat design includes an ion thruster, cameras, spectrometers, an X-band radio for communications, and deployable solar panels. Trajectory analysis shows the cubesat can perform a flyby with the required instruments using its propulsion budget.
This document is a project report submitted by three students for their Bachelor of Technology degree. It outlines the design and implementation of an unmanned aerial vehicle (UAV) in the form of a quadcopter for campus surveillance. The quadcopter will house a camera and use a wireless transmission system to provide live video feed from the camera to a ground station. Sensors such as an IMU and GPS will be used to help stabilize and navigate the quadcopter. An onboard processor and flight controller using Arduino will control the quadcopter. The project aims to develop a low-cost and lightweight surveillance drone.
The document discusses lessons learned from developing the Solar Dynamics Observatory (SDO) satellite. It notes that 484 problem reports were filed during development and testing, with 19 resulting in serious project issues or risks at launch. Many issues were due to design errors or interactive complexity between subsystems that were only discovered after system integration testing. The two instruments with the most complexity, HMI and AIA, accounted for many problem reports. On-orbit, SDO has exceeded science requirements with only two minor issues occurring after launch.
Design and Structural Analysis for an Autonomous UAV System Consisting of Sla...IOSR Journals
An Unmanned Aerial Vehicle (UAV) is an aircraft without a human pilot. It can either be controlled manually by a pilot on the ground using a trans-receiver or it can be programmed to operate autonomously. In this proposed control system, multiple slave Micro Aerial Vehicles(MAV) are dispatched from a master UAV for surveillance. All the MAVs are synchronized with each other through the master UAV which highlights their purpose and position. The master UAV acts as a mobile base for the surveillance, it stores the data collected by the MAVs and transmits them to a remote base. A design of the UAV-MAV system and its performance analysis is presented.
This document summarizes research on autonomous attitude control for quadcopter unmanned aerial vehicles. It provides background on quadcopters and their components. It then describes various control system designs for quadcopters, including automatic landing, take-off, navigation, and attitude control systems. It specifically discusses the use of proportional-integral-derivative (PID) control algorithms for attitude control and references previous research applying PID control that demonstrated stable flight and attitude stabilization.
The SAGAN mission proposes using a constellation of four microsatellites in a tetrahedral formation to study the impact of atmospheric waves, neutral forcing, and ionospheric currents on low and mid-latitude plasma structuring. The satellites would carry instruments to measure electric and magnetic fields, electron density, and ion composition. Maintaining the tetrahedral formation over multiple orbital planes would allow for spatial correlation measurements to understand plasma dynamics in the ionosphere. The proposed one to two year mission aims to advance understanding of ionospheric coupling processes.
The telemetry, tracking, and command (TT&C) subsystem allows ground stations to monitor and control satellites. It performs functions like controlling the satellite's orbit and attitude, realigning antennas, receiving and executing commands, tracking the satellite's position, and modulating and transmitting telemetry data about things like voltage, temperature, and tank pressures to ground stations. The subsystem consists of separate telemetry, tracking, and command subsystems that work together to monitor the satellite's conditions and control it from the ground.
The document discusses the telemetry, tracking and control (TT&C) subsystem for spacecraft. It describes how TT&C provides communication between the spacecraft and ground stations through functions like carrier tracking, command reception, and telemetry transmission. It outlines the key components of TT&C including command systems, telemetry systems, and considerations for antenna size, transmitter power, and interfaces with other spacecraft subsystems.
- The document describes the intern's work testing and integrating sounding rocket payloads at Orbital Sciences Corporation under NASA's Sounding Rocket Operations Contract.
- Key tasks included aiding the testing of payloads through procedures like vibration, bend, and balance testing to ensure durability and mission success.
- The intern also helped design hardware components and gained an understanding of manufacturing processes.
- Overall the internship met the goals of learning about payload integration timelines and systems, and developing mechanical engineering skills.
The document discusses the telemetry, tracking, command and monitoring (TTC&M) system for satellites. The TTC&M system provides essential communication between the spacecraft and ground stations. It includes subsystems for telemetry, tracking, command, and monitoring. Telemetry transmits sensor data from the satellite. Tracking determines the satellite's position and orbit. Command controls satellite functions. Monitoring collects and analyzes sensor data to check satellite health. The TTC&M system enables ground stations to observe and control the satellite.
The document summarizes the key functions of the telemetry, tracking and command (TT&C) subsystem of a satellite. It discusses how TT&C provides vital communication between the satellite and ground stations by (1) monitoring the satellite's status and measurements through telemetry, (2) sending commands from the ground to control satellite functions, and (3) tracking the satellite's location through antenna positioning and Doppler effect measurements. The TT&C subsystem receives commands from and provides data to the satellite's command and data handling system and performs autonomous operations like antenna pointing and fault recovery.
The document outlines plans for the AREND aircraft's critical design review. It discusses the project objectives of finding poachers in the Kruger National Park before they kill. The concept of operations involves the aircraft searching sectors within the park from launch stations. Subsystems that will be reviewed include embedded systems/control/communication, on-board sensors, power/propulsion, fuselage, wings/tail, and testing integration. Risks like schedule delays and budget issues will also be addressed.
1. The Mobile Radiological Laboratory (MRL) is a compact environmental survey laboratory built on a bus chassis to enable rapid deployment in the event of a radiation emergency or accident.
2. The MRL is equipped with instrumentation for environmental monitoring including systems for measuring radiation levels, identifying radionuclides, and assessing internal contamination.
3. Special equipment on the MRL includes a shielded chair for whole body counting and in-situ gamma spectrometry systems for soil analysis. Computers network the data collection and portable generators power the instruments during field operations.
The objective of the project was to integrate the HyTES system and its supporting components securely into the ER-2 aircraft to meet flight requirements. HyTES is an imaging spectrometer currently flown on a NASA twin otter airplane to measure thermal emissions and the spectral content of light. It will be installed using a modular system in the ER-2's wing pods, with components distributed between the aft, mid, and forward pods based on interconnectivity. The design and validation process was challenging due to the modular nature of the system and many separate validation processes required.
The document provides an overview of the ROCKY CubeSat project. The goal is to design and develop a 3U CubeSat to measure lift, drag, magnetic fields, radiation, and GPS performance in low Earth orbit (LEO) and actively control its descent into the atmosphere to maximize time spent in LEO. Key requirements include measuring various phenomena, actively controlling descent from LEO, and including at least one additional science enhancement option. The document outlines subsystem requirements and details partner communications between various universities collaborating on the project. It also discusses relevant past research and technology that could inform project components.
This document describes the design, fabrication, and testing of a small VTOL UAV. Various design configurations were considered including fixed wing, rotating wing, quadcopter, and tiltrotor designs. A quadcopter design was selected. Materials and components were chosen and structural, flow, and vibration analyses were performed in ANSYS and CATIA. The frame was fabricated from aluminum and electronic components like motors and a control board were integrated. Testing showed the design was stable but improvements could be made to strength, payload capacity, and autonomous control.
Galileo concept of operations, first iov leop and initial operationsMarco Lisi
Presentation at the SpaceOps conference in Stockolm, June 2012, about the first launch of Galileo satellites.
Galileo is the European global navigation satellite system (GNSS), funded by the European Commission and developed by the European Space Agency.
This report summarizes the design, analysis, and testing of a hydraulic landing gear actuator and system for a Cessna Citation Jet aircraft. The group used programs like Multisim, Simulink, and Solidworks to model and simulate the hydraulic system and actuator design. They analyzed requirements from EASA and modeled the hydraulic system architecture in Simulink. The group then designed the actuator in Solidworks, calculating necessary specifications like stroke length from aircraft specifications and force requirements. Tests of the simulated actuator model showed it overcompensates, with ripples in response, indicating needed response time improvements.
The document summarizes the process of preparing the Space Shuttle Orbiter for its next flight after landing. It begins with the orbiter landing and initial safety checks on the runway. Then it is towed to the Orbiter Processing Facility where it undergoes maintenance, repairs, upgrades, and processing over several months to prepare it for its next mission. This includes removing payloads, inspecting and repairing the thermal protection system, troubleshooting any issues, and installing equipment for the upcoming flight before it is cleared for rollout to the launch pad.
Common Cause Analysis - Zonal Safety AnalysisTom Jacyszyn
This document provides a common cause analysis and zonal safety analysis for the main landing gear bay of an S18 aircraft. It describes the systems installed in the main landing gear bay, including hydraulic systems, braking components, landing gear components, and an auxiliary power unit bleed duct. Guidelines for equipment installation and separation of redundant systems are discussed. Failure modes are analyzed to determine their effects on other systems. The analysis provides evidence that failures assumed to be independent are truly independent and that hazards from the systems in this zone will not cause a catastrophic failure condition.
Thermal vacuum testing subjects the Space Based Infrared System (SBIRS) satellite to extreme hot and cold temperatures in a vacuum chamber to simulate the space environment. During the 66-day test, the satellite underwent three thermal cycles and five thermal balance runs while key components and functions were verified, including payload operations, power distribution, and thermal control. The successful test provides confidence in the satellite's ability to withstand the space environment and perform its mission.
The document describes the optical performance verification methodology for the James Webb Space Telescope (JWST). The methodology involves (1) testing the optical performance of each component, (2) measuring the alignment between components, (3) verifying the adjustability of movable mirrors, and (4) validating wavefront sensing and control algorithms. This data is used in an integrated telescope model to predict final optical performance on-orbit after wavefront correction. The verification program uses a combination of component tests, subsystem tests, and system-level tests to build confidence while addressing the technical challenges of JWST's large size and cryogenic operation.
Rahul Venkatraman gave a presentation about high altitude balloon flights conducted by the High Altitude Balloon Club at Texas A&M University. He discussed the motivation and goals of the club's projects, which include studying the atmosphere and testing engineering systems. The presentation described past projects such as the Aurora Alaska expedition and the development of a Remote Launch System for hydrogen balloons. It also outlined the club's stratospheric glider project and Rahul's role in the aerodynamic design and leadership of that project.
Thermal batteries provide electrical power through chemical reactions that are activated by applying an external heat source. They have long storage lives but short active lives. Thermal batteries are used in missiles and other military applications due to their ruggedness and ability to operate reliably in harsh environments. They have also been used to power components of Mars rovers during critical entry, descent, and landing phases. Thermal batteries offer advantages such as long storage, maintenance-free operation, and high power density, but have disadvantages like a one-time use and requiring an external heat source for activation.
2013.10.18 alfred piggott gentherm nrel sae thermoelectric battery thermal ma...ap3slidshare
This document discusses using thermoelectric devices (TEDs) for distributed battery thermal management. It proposes integrating TEDs directly into battery bus bars to provide localized and individually controlled cooling of battery cells. Modeling shows TED-only cooling of 5 watts per cell can maintain a 10-year battery life. Future development testing will evaluate air-cooled TED concepts for battery thermal management and utilize a simplified drive cycle generating 3.5-5 watts of heat per cell. Thermoelectric battery thermal management could enable active cooling solutions for mild hybrid applications without liquid cooling loops.
___CV of Senior ELV%2c Special & Electrical Systems Engineer (Amr Gamal) (1) (2)amr gamal
This document provides a summary of an individual's qualifications and experience as a senior engineering and project management professional with over 30 years of experience. The individual has extensive experience managing electrical, IT/telecom, and building management systems on large construction projects in Egypt, Saudi Arabia, Qatar, and Kuwait. Some of the key projects summarized include serving as the Lead Testing & Commissioning Engineer on a $2 billion project in Qatar and as a Senior Special & Electrical Systems Engineer on a $15 billion airport project in Qatar.
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.
Sr Electrical Designer Engineer_wiring harness (EWIS) _Chandram NarayanaChandram Narayana
This document contains the resume of Chandram Narayana, who has 9+ years of experience as a senior electrical design engineer working on electrical wiring systems and motors for the aerospace and defense industries. He holds a Bachelor's degree in Electrical Engineering and has worked at several companies designing, developing and testing electrical systems and components. His skills include design of wiring harnesses, motors, and actuators as well as experience with various design software and standards.
1. The document discusses the history and components of missile technology, including guidance systems, propulsion, and classifications of missiles like ballistic and cruise.
2. It provides details on India's integrated guided missile development program and key missiles developed, including Prithvi, Agni, Dhanush, and the supersonic Brahmos cruise missile jointly produced with Russia.
3. The document concludes that while missiles are generally harmful, they may be necessary in today's world for protection against threats like terrorism from other countries.
The document discusses the telemetry, tracking and control (TT&C) subsystem for spacecraft. It describes how TT&C provides communication between the spacecraft and ground stations through functions like carrier tracking, command reception, and telemetry transmission. It outlines the key components of TT&C including command systems, telemetry systems, and considerations for antenna size, transmitter power, and interfaces with other spacecraft subsystems.
- The document describes the intern's work testing and integrating sounding rocket payloads at Orbital Sciences Corporation under NASA's Sounding Rocket Operations Contract.
- Key tasks included aiding the testing of payloads through procedures like vibration, bend, and balance testing to ensure durability and mission success.
- The intern also helped design hardware components and gained an understanding of manufacturing processes.
- Overall the internship met the goals of learning about payload integration timelines and systems, and developing mechanical engineering skills.
The document discusses the telemetry, tracking, command and monitoring (TTC&M) system for satellites. The TTC&M system provides essential communication between the spacecraft and ground stations. It includes subsystems for telemetry, tracking, command, and monitoring. Telemetry transmits sensor data from the satellite. Tracking determines the satellite's position and orbit. Command controls satellite functions. Monitoring collects and analyzes sensor data to check satellite health. The TTC&M system enables ground stations to observe and control the satellite.
The document summarizes the key functions of the telemetry, tracking and command (TT&C) subsystem of a satellite. It discusses how TT&C provides vital communication between the satellite and ground stations by (1) monitoring the satellite's status and measurements through telemetry, (2) sending commands from the ground to control satellite functions, and (3) tracking the satellite's location through antenna positioning and Doppler effect measurements. The TT&C subsystem receives commands from and provides data to the satellite's command and data handling system and performs autonomous operations like antenna pointing and fault recovery.
The document outlines plans for the AREND aircraft's critical design review. It discusses the project objectives of finding poachers in the Kruger National Park before they kill. The concept of operations involves the aircraft searching sectors within the park from launch stations. Subsystems that will be reviewed include embedded systems/control/communication, on-board sensors, power/propulsion, fuselage, wings/tail, and testing integration. Risks like schedule delays and budget issues will also be addressed.
1. The Mobile Radiological Laboratory (MRL) is a compact environmental survey laboratory built on a bus chassis to enable rapid deployment in the event of a radiation emergency or accident.
2. The MRL is equipped with instrumentation for environmental monitoring including systems for measuring radiation levels, identifying radionuclides, and assessing internal contamination.
3. Special equipment on the MRL includes a shielded chair for whole body counting and in-situ gamma spectrometry systems for soil analysis. Computers network the data collection and portable generators power the instruments during field operations.
The objective of the project was to integrate the HyTES system and its supporting components securely into the ER-2 aircraft to meet flight requirements. HyTES is an imaging spectrometer currently flown on a NASA twin otter airplane to measure thermal emissions and the spectral content of light. It will be installed using a modular system in the ER-2's wing pods, with components distributed between the aft, mid, and forward pods based on interconnectivity. The design and validation process was challenging due to the modular nature of the system and many separate validation processes required.
The document provides an overview of the ROCKY CubeSat project. The goal is to design and develop a 3U CubeSat to measure lift, drag, magnetic fields, radiation, and GPS performance in low Earth orbit (LEO) and actively control its descent into the atmosphere to maximize time spent in LEO. Key requirements include measuring various phenomena, actively controlling descent from LEO, and including at least one additional science enhancement option. The document outlines subsystem requirements and details partner communications between various universities collaborating on the project. It also discusses relevant past research and technology that could inform project components.
This document describes the design, fabrication, and testing of a small VTOL UAV. Various design configurations were considered including fixed wing, rotating wing, quadcopter, and tiltrotor designs. A quadcopter design was selected. Materials and components were chosen and structural, flow, and vibration analyses were performed in ANSYS and CATIA. The frame was fabricated from aluminum and electronic components like motors and a control board were integrated. Testing showed the design was stable but improvements could be made to strength, payload capacity, and autonomous control.
Galileo concept of operations, first iov leop and initial operationsMarco Lisi
Presentation at the SpaceOps conference in Stockolm, June 2012, about the first launch of Galileo satellites.
Galileo is the European global navigation satellite system (GNSS), funded by the European Commission and developed by the European Space Agency.
This report summarizes the design, analysis, and testing of a hydraulic landing gear actuator and system for a Cessna Citation Jet aircraft. The group used programs like Multisim, Simulink, and Solidworks to model and simulate the hydraulic system and actuator design. They analyzed requirements from EASA and modeled the hydraulic system architecture in Simulink. The group then designed the actuator in Solidworks, calculating necessary specifications like stroke length from aircraft specifications and force requirements. Tests of the simulated actuator model showed it overcompensates, with ripples in response, indicating needed response time improvements.
The document summarizes the process of preparing the Space Shuttle Orbiter for its next flight after landing. It begins with the orbiter landing and initial safety checks on the runway. Then it is towed to the Orbiter Processing Facility where it undergoes maintenance, repairs, upgrades, and processing over several months to prepare it for its next mission. This includes removing payloads, inspecting and repairing the thermal protection system, troubleshooting any issues, and installing equipment for the upcoming flight before it is cleared for rollout to the launch pad.
Common Cause Analysis - Zonal Safety AnalysisTom Jacyszyn
This document provides a common cause analysis and zonal safety analysis for the main landing gear bay of an S18 aircraft. It describes the systems installed in the main landing gear bay, including hydraulic systems, braking components, landing gear components, and an auxiliary power unit bleed duct. Guidelines for equipment installation and separation of redundant systems are discussed. Failure modes are analyzed to determine their effects on other systems. The analysis provides evidence that failures assumed to be independent are truly independent and that hazards from the systems in this zone will not cause a catastrophic failure condition.
Thermal vacuum testing subjects the Space Based Infrared System (SBIRS) satellite to extreme hot and cold temperatures in a vacuum chamber to simulate the space environment. During the 66-day test, the satellite underwent three thermal cycles and five thermal balance runs while key components and functions were verified, including payload operations, power distribution, and thermal control. The successful test provides confidence in the satellite's ability to withstand the space environment and perform its mission.
The document describes the optical performance verification methodology for the James Webb Space Telescope (JWST). The methodology involves (1) testing the optical performance of each component, (2) measuring the alignment between components, (3) verifying the adjustability of movable mirrors, and (4) validating wavefront sensing and control algorithms. This data is used in an integrated telescope model to predict final optical performance on-orbit after wavefront correction. The verification program uses a combination of component tests, subsystem tests, and system-level tests to build confidence while addressing the technical challenges of JWST's large size and cryogenic operation.
Rahul Venkatraman gave a presentation about high altitude balloon flights conducted by the High Altitude Balloon Club at Texas A&M University. He discussed the motivation and goals of the club's projects, which include studying the atmosphere and testing engineering systems. The presentation described past projects such as the Aurora Alaska expedition and the development of a Remote Launch System for hydrogen balloons. It also outlined the club's stratospheric glider project and Rahul's role in the aerodynamic design and leadership of that project.
Thermal batteries provide electrical power through chemical reactions that are activated by applying an external heat source. They have long storage lives but short active lives. Thermal batteries are used in missiles and other military applications due to their ruggedness and ability to operate reliably in harsh environments. They have also been used to power components of Mars rovers during critical entry, descent, and landing phases. Thermal batteries offer advantages such as long storage, maintenance-free operation, and high power density, but have disadvantages like a one-time use and requiring an external heat source for activation.
2013.10.18 alfred piggott gentherm nrel sae thermoelectric battery thermal ma...ap3slidshare
This document discusses using thermoelectric devices (TEDs) for distributed battery thermal management. It proposes integrating TEDs directly into battery bus bars to provide localized and individually controlled cooling of battery cells. Modeling shows TED-only cooling of 5 watts per cell can maintain a 10-year battery life. Future development testing will evaluate air-cooled TED concepts for battery thermal management and utilize a simplified drive cycle generating 3.5-5 watts of heat per cell. Thermoelectric battery thermal management could enable active cooling solutions for mild hybrid applications without liquid cooling loops.
___CV of Senior ELV%2c Special & Electrical Systems Engineer (Amr Gamal) (1) (2)amr gamal
This document provides a summary of an individual's qualifications and experience as a senior engineering and project management professional with over 30 years of experience. The individual has extensive experience managing electrical, IT/telecom, and building management systems on large construction projects in Egypt, Saudi Arabia, Qatar, and Kuwait. Some of the key projects summarized include serving as the Lead Testing & Commissioning Engineer on a $2 billion project in Qatar and as a Senior Special & Electrical Systems Engineer on a $15 billion airport project in Qatar.
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.
Sr Electrical Designer Engineer_wiring harness (EWIS) _Chandram NarayanaChandram Narayana
This document contains the resume of Chandram Narayana, who has 9+ years of experience as a senior electrical design engineer working on electrical wiring systems and motors for the aerospace and defense industries. He holds a Bachelor's degree in Electrical Engineering and has worked at several companies designing, developing and testing electrical systems and components. His skills include design of wiring harnesses, motors, and actuators as well as experience with various design software and standards.
1. The document discusses the history and components of missile technology, including guidance systems, propulsion, and classifications of missiles like ballistic and cruise.
2. It provides details on India's integrated guided missile development program and key missiles developed, including Prithvi, Agni, Dhanush, and the supersonic Brahmos cruise missile jointly produced with Russia.
3. The document concludes that while missiles are generally harmful, they may be necessary in today's world for protection against threats like terrorism from other countries.
Presentation given to the AEROSPACE Electrical Systems Expo on April 2, 2014. A short, 17 slide, presentation that looks at several aspects of EWIS (Electrical Wiring Interconnection System).
Aerospace structure and engineering unitsVera414786
Aerospace structure and engineering units encompass disciplines vital to aircraft and spacecraft design, ensuring structural integrity, performance, and safety. These units specialize in materials science, aerodynamics, propulsion, and systems engineering. Engineers collaborate to create lightweight yet robust structures capable of withstanding extreme environments, while optimizing fuel efficiency and maneuverability. Their innovations drive advancements in aviation and space exploration.
The document summarizes the process of constructing a spacecraft. It involves building individual units and testing them, then assembling the units into subsystems which are further tested. The subsystems are mounted on the spacecraft structure which consists of a service module and communications module. After integration, the complete satellite undergoes testing to ensure the systems can operate as intended in the expected launch and in-space environments. This qualification process demonstrates the satellite's readiness for launch.
1. The document presents a simulation software developed to evaluate the control system for an autonomous unmanned helicopter.
2. The simulation models the helicopter dynamics, sensors, and an extended Kalman filter. It accounts for forces like gravity, rotors, wind, and allows tuning the helicopter servos.
3. The goal is to design the guidance system without risking damage to real equipment by testing in simulation first.
This document discusses control approaches for cooperative unmanned aerial vehicles (UAVs). It first presents the modeling of a quadrotor's dynamics using piecewise affine systems to capture nonlinearities. It then describes the design of an experimental quadrotor platform called UPATcopter that can estimate its state autonomously. Finally, it proposes three control strategies for quadrotors: 1) a constrained finite time optimal controller for attitude control, 2) a switching model predictive controller for trajectory/attitude control, and 3) a PID-2nd derivative controller for attitude and translation control. Experimental results demonstrate the effectiveness of these control approaches.
The document proposes an architecture for a satellite ground station emulator to train operators. The emulator would simulate telemetry from a satellite and transmit it to a physical ground station. This allows trainees to use real equipment while practicing receiving telemetry and responding to injected anomalies. The emulator aims to guide trainees through normal operations and special scenarios to prepare them for communicating with an actual satellite. It seeks to minimize human errors and maximize mission success by providing realistic training in a safe simulated environment.
Trajectory estimation studies for long coasting phase of mars missioneSAT Journals
Abstract At Sriharikota range, configuration of down range tracking network, Real-time tracking and trajectory estimation play a critical role during a satellite launch for flight safety as well as mission monitoring. Criticality is more when the mission parameters vary during the launch window to meet the mission requirements. PSLV-C25, the 320 T XL version is intended to inject the 1337.24 Kg MARS Orbiter into 250 Km * 23500 Km * 19.2 deg Sub-GTO orbit. MARS Orbiter Mission [MOM] is the first Indian interplanetary mission to orbit a spacecraft around MARS in an elliptical orbit of 360km * 80000 km. This paper deals with the trajectory estimation and prediction methodologies studied and established at Sriharikota Range for this launch. The major challenge in the Mars orbiter mission is to configure the Down range network of Telemetry stations in view of large variation in the Argument of Perigee (AOP) requirement ranging from 2760 to 2890 during injection over the period of launch window. Requisite AOP facilitates transit of the Spacecraft from Earth to Mars using minimum energy Hohmann transfer. The change in the requirement of AOP each day in turn demanded a new trajectory with its characteristic changes in long coasting duration, fourth stage ignition time and subsequent MARS Orbiter injection time into sub-GTO. It is mandatory to capture the Telemetry data during those critical events to assess the success of the mission. The flight duration was around 3000s and the coasting duration was 1600s before the ignition of the PS4 stage. Study of configuration of mobile Telemetry stations on Ship-borne terminals is carried out to cater to visibility requirements of critical events such as fourth stage ignition time and subsequent MARS Orbiter injection. State vector accuracy studies are carried out for the Ship-borne radar data of the vehicle during long coasting using Linear Kalman filter. Also a trajectory extrapolation algorithm is designed and studied to provide extrapolated trajectory during the long coasting period after 3rd stage burn out which in turn is used to compute and display trajectory parameters to mission executives and provide antenna-pointing information to the ship-borne terminals. This paper presents the trajectory estimation methodology proposed, extrapolation techniques adopted and accuracies achieved for the long coast duration. Keywords: Mars Orbiter Mission (MOM), Flight Safety, Trajectory estimation, Network simulations, Argument of Perigee (AOP).
The document summarizes projects conducted by NASA Ames Research Center's Aeromechanics Branch, including the development of the Tiltrotor Test Rig (TTR) since 2008. The TTR is being developed in collaboration with other organizations to evaluate full-scale tiltrotors and provide insight into technological requirements for future civilian tiltrotors. In Fall 2014, the TTR was moved onto a calibration rig using a complex lifting procedure to ensure safety. The calibration rig will be used to calibrate the TTR's internal balance system to accurately measure forces during testing.
Flight testing is important for developing human-rated spacecraft as ground testing cannot fully replicate integrated systems operating together. The PA-1 and Ares I-X tests provided valuable data for validating models and designs. Key challenges for flight testing included committing to readiness despite pressure to simplify processes, determining appropriate rigor for non-human flights, ensuring consistency across organizations, and managing certification timelines. Both tests were successful and provided data to refine designs without any major issues occurring.
A Review on Longitudinal Control Law Design for a Small Fixed-Wing UAVIRJET Journal
This document reviews various techniques for designing longitudinal control laws for small fixed-wing unmanned aerial vehicles (UAVs). It discusses techniques such as integral sliding mode control, linear quadratic regulator (LQR), Apriltags recognition algorithm with PID control, observer Kalman identification with PID control, root locus method, nonlinear model simulation, and multi-model techniques. These techniques have been applied to problems such as longitudinal guidance, stability augmentation, autonomous landing, and modeling fixed-wing UAV dynamics. The document analyzes the effectiveness and robustness of different proposed control schemes through simulations and comparisons of various techniques.
alat penentu lokasi pada saat emergency (Emergency locator transmitter)Lalu Giat Putra
ELT merupakan alat yang berada di pesawat yang berfungsi untuk mencari letak pesawat pada saat kecelakaan, alat ini berfungsi apabila terkena benturan dan terendam air.
The document summarizes the design of L.A.S.E.R. 5, a solar-powered unmanned aerial vehicle (UAV) being constructed by students. The goals are to break the world record for longest straight-line distance by a solar-powered UAV and to safely charge the onboard battery using solar panels and hydrogen fuel cells. The design process involves conceptual optimization under FAI regulations, aerodynamic and structural analysis using software, and selection of an efficient airfoil for long-range gliding performance at low speeds. The composite sailplane design incorporates lessons from previous L.A.S.E.R. iterations to advance renewable energy applications for aircraft.
This short Course provides to University Aerospace Engineering students with a Panoramic Instruction on the Project Management (PM), System Engineering (SE) and Integrated Logistic Support (ILS) Processes which are Fundamental to the Success of Aerospace Projects together with some hints for Professional Development in these Fields.
The Cource also introduces the PM, SE and ILS Basic Activities, Organizational Aspects, Main Processes, Methods, and Procedures.
This document outlines the key phases in the design and development of a sounding rocket project. It discusses:
1. Defining the mission objectives and requirements for experiments to be carried out by the rocket.
2. Developing the preliminary design which includes selecting the rocket size, recovery system, and avionics based on the mission objectives.
3. Finalizing the rocket design with consideration given to the structural, aerodynamic, and control systems design. Testing of components and simulations are used to validate the design.
4. Verifying the rocket's performance through simulations, testing of individual components, a full-scale launch, and analysis of flight data. This ensures the rocket meets expected specifications.
The document summarizes the system architecture of the Global Hawk unmanned aerial vehicle. It describes Global Hawk as a high-altitude, long-endurance aircraft system used for intelligence, surveillance, and reconnaissance missions. The key components of the Global Hawk system are the unmanned air vehicle, a common ground segment for command and control, and support systems. The air vehicle carries sensor payloads and has autonomous flight and navigation capabilities. The common ground segment includes a mission control element and launch/recovery element to monitor the vehicle and payload data and control missions.
Triton UAS Technical Design Paper 2020-2021KennyPham19
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The document describes the INSpIRe initiative, which aims to establish a remotely operable observatory to study geocoronal hydrogen and other near-space phenomena. The observatory will integrate two Fabry-Perot spectrometers and one spatial heterodyne spectrometer. Researchers from Embry-Riddle Aeronautical University, NASA Goddard Space Flight Center, and the University of Wisconsin-Madison are collaborating on the project. The observatory is currently under development at ERAU and will allow remote observations to investigate important questions about the distribution and variability of atomic hydrogen in the upper atmosphere and exosphere.
IRJET- Improving Network Life Time using High Populated Harmony Search Al...IRJET Journal
This document discusses improving network lifetime in underwater acoustic sensor networks using a multi-population harmony search algorithm. It proposes using the algorithm to elect leader nodes which can efficiently route data from sensor nodes to a base station, avoiding collisions. The document describes the network architecture, implementation of AODV routing combined with a round robin scheduling method, and analyzing results showing reduced delay when using the multi-population search algorithm. Improving underwater sensor network lifetime, reliability and efficiency through optimized routing techniques is the overall goal.
This document summarizes a proposed crash avoidance system for drones. When one of a drone's motors fails, the system would allow the pilot to manually switch the drone from a quadcopter to a tricopter configuration using a signal sent to the flight controller. This would maintain pilot control and allow the drone to safely land. The system would involve connecting an Arduino board to the flight controller to receive the pilot's signal and cut power to the failed motor while keeping the other three motors operational during the transition, ensuring stable controlled landing. A literature review found that existing methods focus on software solutions while this approach addresses the problem from both a software and hardware perspective.
This document proposes algorithms using geometric functions like spirals and Lissajous curves to generate smoother trajectories for UAVs performing area coverage compared to the traditional lawnmower approach. The smoother trajectories are expected to reduce the time and energy required for area coverage by 22% and 30% respectively while still achieving at least 98% coverage. The algorithms will be implemented using ROS and experiments conducted in Gazebo simulation to evaluate the performance of the proposed methods versus the lawnmower approach.
This document summarizes new challenges brought to the Standard Missile program by the development of the SM-3 variant for exo-atmospheric intercepts of ballistic missiles. Key points:
1) SM-3 will intercept targets at higher speeds and altitudes than previous SM variants, outside of the earth's atmosphere. This requires new technologies for attitude control, thermal protection, and precision guidance/navigation.
2) Additional ground tests are conducted on SM-3 to verify design changes, including separation tests to validate stage separation and a hover test to demonstrate kinetic warhead target acquisition without rocket motors.
3) The Aegis LEAP Intercept demonstration aims to show that SM-3 can intercept
Similar to Electrical systems in missiles and space vehicles (20)
The document is an introduction to electrical engineering that covers basics of electric circuits, AC power, and power generation and transmission. It defines current and voltage, explains Ohm's law, and discusses Kirchhoff's laws. It also describes the advantages of using AC power over DC for power transmission, including the ability to use transformers to change voltage levels. The document concludes by explaining power factors in AC circuits.
Rajasthan Rajya Vidyut Prasaran Nigam Limited (RVPNL) is a company of the Rajasthan State Electricity Board that aims to provide reliable power transmission services to customers. A 132 KV sub-station in Bhadra, Hanumangarh receives power from a thermal power station and contains various components like overhead power lines, transformers, disconnect switches, circuit breakers, current and potential transformers, lightning arresters, and a control building surrounded by a security fence. Key components of the sub-station include lightning arresters, capacitive voltage transformers, wave traps, power line carrier communication systems, isolators, circuit breakers, bus bars, power transformers, and protective rel
Frequency is defined as the number of cycles per unit time and is usually denoted by f. In electrical engineering, frequency is important because it determines how fast alternating current and voltage change direction. The frequency of generated power from a synchronous alternator depends on the speed of its rotor. As electrical load increases, frequency decreases due to opposing electromagnetic forces. Higher frequencies allow for more compact transformers with reduced weight. Resonant circuits have maximum or minimum impedance at specific resonant frequencies, making them important for radio, TV receivers and transmitters.
A power station or power plant generates electric power by converting other forms of energy into electrical energy. The most common types are thermal power plants, which burn fossil fuels to power steam turbines, and nuclear power plants, which use nuclear reactions to power steam turbines. Power plants are also classified by their prime mover, such as steam turbines, gas turbines, or hydroelectric turbines. When an imbalance occurs between power generation and load, it can cause power outages or failures across an electrical grid. Utilities take measures to protect against outages and restore power through monitoring, analytics of power usage and generation, and preventative maintenance of infrastructure.
Resistors restrict electric current and are identified by color-coded bands. Capacitors store electric charge and come in polarized or unpolarized varieties. Resistor and capacitor values use standard prefixes like kilo and micro to indicate multiples of basic units. Circuit diagrams use symbols and shorthand to represent these components concisely.
SF6 is a colorless, odorless, non-toxic gas that is 5 times heavier than air and has excellent dielectric properties. It was first synthesized in 1900 and has been used since the 1930s as an insulating gas for high voltage equipment due to its high dielectric strength. When electric arcs occur, SF6 decomposes into various other gases, some of which can be irritants in high quantities, though dangerous thresholds are rarely reached in equipment. Proper ventilation and safety precautions are required when working with SF6 gas and decomposition products.
Diesel locomotives use a diesel engine to power an alternator that generates electricity to power traction motors on the axles, replacing overhead electric wires. Key components include the diesel engine, alternator, rectifiers or inverters to convert AC to DC for older DC traction motors or back to AC for newer AC traction motors, electronic controls, batteries, a cab, traction motors on each axle via reduction gears, a fuel tank, air compressor, drive shaft, radiator and fans. Diesel locomotives can operate on any route without needing electrification but carry their own power source of a diesel engine and generator.
The document describes an experiment to study the transient response of a second-order RLC circuit for different cases of damping. A series RLC network is considered with input voltage V1(s) and output voltage V2(s). The transfer function of the network is derived. In the program, different RLC circuits are modeled with varying damping ratios (z). Their step responses are plotted to show underdamped, critically damped, and overdamped cases.
Rajneesh Budania presented on electrical fundamentals and ripple fundamentals. The document discusses different types of ripple including time domain ripple and how it is measured. It also discusses effects of ripple like audible noise and reduced life of capacitors. The document then discusses different types of distortion including amplitude, harmonic, frequency response, phase, and group delay distortion. It provides examples of sources and effects of each type of distortion. Harmonic fundamentals are also covered including causes from non-linear loads and effects like increased heating in electric motors.
This document provides an overview of electrical fundamentals including ripple and harmonic fundamentals. It discusses:
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The document summarizes information about Diesel Shed Ratlam, located in Madhya Pradesh, India. It was established in 1967 and maintains diesel locomotives. It discusses the types of locomotives - steam, diesel-electric, and electric. Diesel-electric locomotives became widely used because they don't produce smoke and have higher efficiency than steam. Traction motors, the main components of locomotives, are also described in terms of their construction, ratings, and operating principle.
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Explore more about Albumentations and join the community at:
GitHub: https://github.com/albumentations-team/albumentations
Website: https://albumentations.ai/
LinkedIn: https://www.linkedin.com/company/100504475
Twitter: https://x.com/albumentations
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1. Electrical Systems in
Missiles and space
vehicles
Now that space operations have become a reality, it is appropriate to review the
accomplishments of the past and to discuss what must be done in the future to
insure the operational readiness of our large carrier vehicle systems. Well-planned
overall systems engineering is the key to this task, with electrical systems
engineering playing a major subsidiary role.
When missiles were introduced on a relatively large scale some 25 years ago
overall electrical systems engineering did not exist as such, although with theV2
missile the systems approach was being utilized for the first time. In those days
the designers of the propulsion system provided for the system's electrical needs
by maintaining the required start and cutoff sequence. The designers of the
guidance and control system worked their own electrical system and took care of
the electrical equipment needed for the checkout and launch operations.
Missiles resulting from this parallel design effort were operational; but to. build,
checkout, and prepare them for Launching was very expensive and time
consuming. Relatively early in the research and development phase of the V2
program the entire system was evaluated for large-scale production. This
evaluation showed that it was impossible to supply all the electrical components
needed to achieve the requested production rates. For the first time, this created
the need for a coordinated overall systems approach which considered checkout
equipment and the missile as one system. Duplication of functional components,
signals, power sources, etc., was avoided to simplify the system as much as
possible. The requirements placed on the overall system created the need for a
systems engineer who was required to have a thorough knowledge of the various
subsystems, their operation, and functions. A philosophy was established which
has been followed since: "Keep the missile system simple; wherever possible,
keep components out of the missile, especially if they only function during pre-
flight checkouts." Under these conditions, the entire V2 system was redesigned.
1
2. Aside from production considerations,
operational simplicity was of major concern. Checkout and launch operations
during the research and development phase were carried out by the designers
themselves or by high-caliber, technically trained personnel. In combat
application, the system being operated by troops had to be self-checking and
automated in its launch sequence. The V2 system at the end of World War II was
a classical example of functional simplicity with a minimum amount of
components. The actual launch operation was simplified to only two pushbuttons:
one to start the launch sequence, and one to start the full flow of propellants. The
entire launch sequence was self-checking and returned the system to a safe
condition if a malfunction was sensed during this time before launch. All
operational missile systems today essentially follow this pattern of operational
sequence.
In-flight instrumentation systems were refined more and more after World war II,
and missile behavior as well as environmental conditions during the entire flight
phase were observed through radio links. This possibility of telemetry coverage
opened a new area for missile" design engineers to obtain valuable data for further
study programs. Theoretical data could be hardened by actual data, and values
could be obtained for the anticipated new missile programs. Within the last 15
years, the measuring program expanded from between 30 and 40 measurements to
between 500 and 600 measurements per test flight. All these measuring programs
had to be incorporated into the overall system in such a way as to not interfere
with the standard system necessary for proper flight performance. A malfunction
in the instrumentation system should not influence in any way the behavior of the
standard system. However, the instrumentation system was required to function as
long as possible to record catastrophic failures, such as fire in the engine area,
control failures, etc., that would eventually lead to a flight failure. This systems-
approach worked very satisfactorily in programs like Redstone, Jupiter, and
Pershing. There were few failures which could not be explained. The telemetry
records gave perfect coverage and usually a quick explanation.
As the missile systems expanded in size and complexity, the checkout time and
the time required for launch readiness also increased. The" constant changes from
one missile to a more advanced missile demanded exacting checkout, test, and
firing procedures. Event sequencing had to be dictated that could be achieved only
by designing all tests and sequence events into the system. Whenever possible, the
human element was eliminated in all critical phases of checkout and launch. This
effort was well spent, judging from the results of the various missile programs of
the last 5 years. It is not a major problem today to prepare a satellite on a certain
day, or even hour of the day, for firing and injection into orbit. It- is taken for
2
3. granted that the entire. system is reliable enough to meet a specified countdown
time. It cannot always be assumed, however, that a missile takes off from its
launch pad and stays on its prescribed trajectory. Special precautions are
necessary as directed by the safety officer of the missile range.
An entirely independent and redundant system has been designed over the years as
a tool for the safety officer to maintain full control over the missile. He must be
able at any time during the propelled flight phase to cutoff thrust or to destroy the
entire missile if he decides that this is necessary for safety reasons. This system
must work under any condition possible in the flying missile such as power
failure, structure breakup, or other failures. The various requirements in the
known missile program, such as 15-min readiness, automation to any degree, and
self-checking of subsystems and components, lead to standardization and
refinement of the entire system to achieve reliability. Only after the achievement
of this reliability was it possible to plan for the placing of man into space.
Project Mercury was established and funded based on reliable missile systems.
The primary missions of Project Mercury are the orbiting of manned capsules
around the Earth, the study of man's capabilities in space flight, and the safe return
of the capsules and their occupants to the surface. The program was divided into
two main phases: (1) to use the modified Redstone carrier for suborbital
unmanned and manned capsule flights to help qualify the Mercury capsule in a
space environment, and (2) to carry out unmanned and manned orbital flights with
the qualified Mercury capsule being boosted by an Atlas ICBM.
It was necessary to analyze the entire flight history of the two systems to establish
a malfunction study that showed where systems improvements were desirable and
possible. Parallel to this study, an abort-sensing philosophy was established to
provide, during the total countdown and flight, the utmost in safe abort for the
man in the capsule and for the launch crew at the pad.
A new design aspect entered the overall systems design; this was the concern
about the man. Electrical checkout and functional circuits, well established in
previous flights, had to be reanalyzed and redesigned because the safety of a
human life was involved. Automatic abort sensing during the countdown and
carrier vehicle flight was to be incorporated into an existing system. Since two
independent systems were involved, carrier vehicle and capsule, close technical
coordination was essential. In the preflight condition, up to liftoff, any
malfunction had to result in the "safing" of the entire system or ,ejection of the
capsule from the carrier rocket. It was necessary to make all abort systems
redundant and operational under all possible conditions. After liftoff, the range
3
4. safety officer's requirements added to the complexity of the system.
Abort had to be possible over radio link at all times from the ground; the astronaut
also had the ability to abort the mission. It was necessary to develop automatic
abort sensing devices for the space carrier vehicle such as:
1. Attitude error sensors for pitch, roll, and yaw axes.
2. Angular velocity sensors for pitch, roll, and yaw.
3. Control voltage detectors to sense voltage failure.
4. Combustion chamber pressure switches to sense engine performance.
All these sensing devices could activate a common abort bus for both carrier '
vehicle and capsule. Elaborate tests were performed with the system to qualify all
components and circuits for the stringent requirements.
The Mercury-Redstone's three, successful, unmanned, test flights and two,
successfu1, manned, suborbital flights indicate that the systems approach is sound
and that the concepts in systems design are advanced enough to be applied to
larger space vehicles.
The experience gained in many missile systems over the past years was carefully
applied to the present systems such as Saturn. The Saturn, a large multistage,
space carrier vehicle, demands an extremely well-coordinated engineering and
design effort to fit all stages into one workable system. Overall systems design
direction and standardization, within stages, are absolutely necessary. The first
block of Saturn vehicle wi1l show what this effort means.
The electrical interconnect diagram of the Saturn first stage shows the breakdown
into 16 major areas. This breakdown was selected as a logical division into
subassemblies and, in some cases, into subsystems. The interconnection diagram
depicts the vehicle integration scheme and illustrates to some degree the
complexity of the present Saturn electrical network; it is shown in Fig. 29.1.
The electrical system used in Block One Saturn vehicles serves to supply power
for the operating and switching functions needed by the various vehicle
subsystems. Primary vehicle power is provided by the main batteries, which in
many cases furnish the necessary power directly through the distributors to the
electrically operated components. In other cases, battery power is converted into
other voltages and frequencies by power supplies and routed to the subsystems
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5. through the distributors.
The entire integrating electrical network consists of cables and distributor boxes.
Integration of the subsystems requires approximately 500 cable assemblies and
nine distributors, since almost all components are served through distributors. This
system guarantees a high degree of flexibility to incorporate design changes. The
entire system can be built and checked out on the bench prior to assembly into the
vehicle. This means a high assurance of quality and reliability, since accessi- bility
prior to vehicle assembly is provided.
The Block One Saturn subsystems are established as follows:
1. Electrical power. The electrical power system consists of two 28-v batteries
supplying two independent busses; one bus handles all
Fig. 29.1 Electrical interconnect diagram for first stage of Saturn.
steady loads, the other bus all variable loads. The steady loads are mainly the
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6. secondary power supplies, such as 5-v supplies for measuring voltage and the 60-v
power supply for control components. The variable loads are heaters, relays,
valves and cooling equipment. Each battery will carry its total load during flight
after power switch-over from ground supply shortly before ignition of the engines.
2. Pressurization. The propellant tanks are pressurized by two pressurizing
systems. Fuel tank pressurization is controlled by valves in the manifold system
which regulate the nitrogen gas supply with pressure switches. The fuel tanks are
initially pressurized by the ground system prior to ignition. Pressure level is
maintained during powered flight by pressure switch sensing, which activates
required valves in a controlled sequence as fuel is consumed.
The liquid oxygen tanks are initially pressurized by a ground pressure supply.
After ignition, liquid oxygen is gasified by running it through a heat exchanger.
The gas then maintains the desired pressure within the liquid oxygen tanks.
Mechanical vent valves relieve excess pressure through the preset valve. These
tanks may be electrically vented from the blockhouse at any time prior to liftoff.
3.. Engine start and cutoff. The fuel and oxidizer are fed to the engine by turbine-
powered pumps. Initial turbine momentum is given by the turbine spinner, which
is started by squibs ignited by an electrical signal from the ground equipment. The
turbine spinner is sustained by fuel and oxidizer burning in the gas generator.
After initial startup, fuel pressure maintains engine operation. The eight Saturn
engines are started with the ground equipment in a staggered sequence pattern.
Only two engines are ignited simultaneously. The four groups of two engines are
ignited 100 msec apart. All engines are nonitored for combustion and proper build
up of hydraulic fluid pressure needed for engine gimbaling. These criteria are
monitored for 3.3 sec to ensure that all eight engines are running properly and that
hydraulic pressure is maintained.
Only if these indications are satisfactory does the ground support equipment
(GSE) continue the launch sequence with the thrust-commit signal. This signal
deenergizes a relay in the vehicle to energize the one-engine out bus. Energizing
this bus enables the: vehicle to give cutoff automatically to one engine if the thrust
falls below the specified limits. When one engine is cut off prior to liftoff, the
remaining engines are also cut off in a given, patterned sequence. Should the
thrust of any engine drop below the specified limits during the first 10 sec of
flight, that engine will be cut off, and the engine out circuits will be deactivated to
prevent the other engines from being cut off because of low thrust. This circuit is
reactivated at 1iftoff-p1us-10-sec so that the other engines with low thrust may be
cut off. Emergency cutoff may be given from the ground by radio link, through
the destruct command receivers, any time after liftoff. This signal will switch all
engines
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7. off at once. Normal cutoff sequence is provided by liquid level sensors in the fuel
and oxidizer tanks. When fuel and oxidizer consumption reaches a preset low
level, the cutoff for the four inboard engines is triggered. Derived from this signal
6 sec later, the outboard engines are also cut off. In the engine cutoff sequence,
circuitry is provided to insure that there are more than two outboard engines
running at one time.
4. Flight sequencing. The program device is the source of all inflight sequence
events. It provides accurate time pulses to initiate' and execute guidance, control,
and sequenced functions. The program device is a precise, six-channel, magnetic
tape recorder, of which three channels are presently used:
a. One channel provides the tilt program.
b. One channel initiates telemeter inflight calibration.
c. One channel stimulates the overall vehicle sequencing.
The program device is started from zero at liftoff, relating all sequence events of
the channels to liftoff as the time base. Shortly before calculated inboard engine
cutoff, the program device is stopped and restarted at the actual, inboard engine
cutoff signal. This provides a new time base for the upper-stage operational
sequence based on inboard engine cutoff. This has the advantage of eliminating
the tolerances of carrier vehicle performance; cutoff predictions are theoretical
values only. All overall vehicle sequencing stimulated by the program device is
executed by the flight sequencer; a chain of relays respond to pulses from the
program device.
5. Control. The heart of the control system is the stabilized platform and its
executing equipment. The stabilized platform serves as inflight reference for
signals to the control system. The control system senses and corrects vehicle
inflight inaccuracies through null- seeking devices that continuously compare
actual flight information with the programmed flight path. The signals and values
derived from the stabilized platform are transmitted to the control computer. The
control computer in turn translates these signals into control signals. The output
signals are executed by hydraulic servo actuators, which gimbal the four control
engines accordingly.
6. Inflight cooling. To assure proper operation of some inflight equipment within
the given tolerances, an inflight cooling system regulates the temperature within
the pressurized canisters where this equipment is housed.
7. Heating. The air required by the air-bearing gyros is heated to maintain the
stringent tolerances of the platform. A temperature sensing device monitors and
maintains this temperature within the preset limits as the stabilized platform is in
operation. The angle-of-attack meters used with the control system are also heated
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8. to prevent icing during flight.
8. Tracking. The Saturn tracking equipment consists of two radar units, Udop,
Azusa, and their associated antennas. The equipment is powered and operated
through vehicle circuitry. There are four continuously burning lights tracked by
CZR cameras for a period after liftoff. The flight sequencer turns the lights off
after the vehicle is out of camera reach.
9. Telemetering. The Saturn vehicle carries eight telemeter links which are used to
transmit about 600 measurements back to ground rf receiving stations. These
measurements are routed and signal-conditioned from all areas of the vehicle to
the proper telemetry channel for transmission.
These short descriptions of the major areas to be combined into one overall system
indicate the necessity of well-defined technical system coordination. A thorough
knowledge of the system's functional operation is essential for the systems
designer. The design must provide not only reliable, and in some areas redundant,
operation during the flight application, but also the means of complete functional
checkout after completion of assembly, preflight, and launch operations.
Before entering the area of ground checkout equipment, a few words, should be
said about some features in the vehicle system. Since eight engines have to be
operated during the propelled flight phase, the probability of one engine failure
cannot be overlooked. The engine start and cutoff sequences have been described
before. If one engine is lost due to some malfunction, a hazardous condition may
be created for the overall system. Since combustion chamber pressure is sensed as
the criterion for proper engine behavior, this indication is utilized to cut a.
particular engine off. The eight engines are in individual compartments, and a fire
in one compartment should be localized to that area. All propellant supply will be
shut off properly by sequence; however, a fire or minor explosion may destroy all
electrical lines in this engine compartment. The design provides short circuit
protection; one short of any operational electrical line to another or to the vehicle
structure below the fire wall will not affect the rest of the system. All measuring
pickups in each engine area are also fed by its own measuring power supply.
These pickups are protected by line resistors to maintain operation in this troubled
area as long as possible while not affecting the measurements in other areas of the
vehicle.
All circuits for vehicle destruction are completely redundant, from power source
to explosive train. For future application, an exploding bridgewire system will be
introduced for all ordnance items as substitutes for the present sensitive squibs in
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9. which elaborate protective circuitry complicates the system unnecessarily.
The function of the ground checkout system for the Saturn is not a new concept.
As in previous projects, it is still designed to checkout
all vehicle circuits in various Subsystem tests. All subsystems are checked out and
qualified, then the overall system is operated with the same equipment, bypassing
all inapplicable subsystems test circuits. The overall systems test, if fully
automated in itself, creates signals in the ground checkout equipment and returns
the resultant stimulus for the next step in the automated process. This method will
consider all critical functions during the countdown, and a failure at any point of
the sequence will stop the countdown and return the system to a safe condition.
Since the complexity of the entire system is considerably increased compared with
other known systems, new methods of manufacturing are being established. The
rack and panel concept was introduced to build up the entire system by use of
modules. Distribution racks were designed on which standardized connectors are
wired to an IBM patchboard. This results in standardization and a high degree of
flexibility. The connectors will receive either an incoming or an outgoing cable.
They will also receive standardized relay modules, diode modules, resistor
modules, transistor modules, etc. Standardized modules and the racks with the
connectors can be fabricated in quantity long before circuit definition. After the
system circuits are established and detailed design is finished, the IBM patchwork
will interconnect all modules. This patchboard can be defined late in the schedule
to incorporate all design refinements or changes. In the area of control panels this
system cannot be adapted readily; however, standardization of panels and
components has been maintained throughout the program and stages involved so
far. This has considerably shortened the design and manufacturing time, as well as
lowering the cost.
For the present, the same equipment used for checkout will be used for stage static
firings as well as for final checkout at the manufacturing site and launch site. The
concept, as described, will serve the overall Saturn system as long as it stays with
the present scheme of operation. The system proved itself to be extremely
satisfactory at the first Saturn firing; no technical difficulties arose during the
countdown and inflight operation. .
The problem of increased distance between launch pad and blockhouse will
dictate a different overall scheme for several reasons. The main reason is the
safety distance in the case of a mishap. This and other considerations, such as
increased firing density, quicker checkout, and better data retrieval, lead into a
new scheme of vehicle electrical systems for the single stage as well as for the
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10. assembled configuration. A scheme will be chosen to standardize stage checkout
at the manufacturer's site for all stages of the system, and to continue to launch
operations. The scheme will make use of a digital method and the automation of
all system checks.
The question may arise as to the necessity of automating to this degree, since the
present automated countdown has worked satisfactorily. Before going into this
major effort of generating a sophisticated automatic system, the advantages and
disadvantages should be discussed. If a properly operating system is assumed, the
biggest advantage to be gained will be improvement of the overall systems
reliability, and an overall time saving for various phases of testing and launch
preparation. The human error can be eliminated in the checkout procedure.
Standardized testing will occur throughout the vehicle test program and complete
test results will be printed out and available for design improvement studies. Since
running time utilized for the testing procedure will be cut to a minimum, the
effective mean time-to-failure ratio for the vehicle will be increased.
Once a system is correctly automated, more thorough testing can be achieved in
much less time than in the manual case. Therefore, the confidence of firing
personnel in the flight hardware can be increased. When a system failure has been
noted, the exact condition under which the failure occurred can be easily
duplicated. More complete data can be gathered at the instant of failure to aid in
trouble-shooting and fault isolation. The anticipated schedules for Saturn flights
will require automation of the checkout procedures to save time and to make the
best use of personnel.
Since the advantages have been reviewed, we can now look at the disadvantages
and the reasons of failure of some known automated systems. The first
disadvantage is the complexity introduced in an overall system by adding
automated features. The complexity in many cases has been generated, not
because it was required, but rather because of conditions under which the design
occurred. Lack of confidence in the system on part of the user in many cases has
been another disadvantage for automated systems. Inadequate learning time for
the user has resulted because of poor planning and crash program conditions. One
of the major reasons for automatic checkout system failures has been inadequate
planning in the area of checkout program generation -- those instructions in
machine language that tell each component exactly what to do. More than one
program has resulted in capable, but ignorant, checkout hardware.
Another item that should not be overlooked is the degeneration of operator
knowledge about the total system in the presence of working automation. A
system may work so well that the operators lose touch with the actual process
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11. being carried out; when there is trouble, panic and lost time occur. Any well
thought-out automation program must consider and overcome these
disadvantages.
The state of the art in various types of checkout equipment, both analog and
digital, has greatly improved over the last few years. It is possible to obtain
reliable conversion and processing equipment to work
.
with digital intelligence equipment of greater reliability than ever before. It is now
possible to foresee a checkout system made up of existing equipment that is
reliable and accurate. In the Saturn program it will be possible to have checkout
equipment operating in an air conditioned environment. It can be operated by
engineering personnel and subjected to preventive maintenance, and it can achieve
the reliability currently expected of industrial automation. Once a system is
working, it can be expected to continue to do so. An automatic checkout system
tailored specifically to the needs of the Saturn and Nova programs can be
generated with a high degree of confidence that the system will work properly.
The following automation requirements should be followed for overall system:
1. The development must cover all foreseeable programs from Saturn C-1.
through Nova.
2. The same technologies, in fact the same hardware wherever possible,
should be used throughout the Saturn-Nova developments, just as vehicle
technologies in hardware are being utilized from one vehicle configuration
to another.
3. The hardware and techniques developed must fit into the plans and
facilities of both the contractor and the launch site.
4. The system must provide for both manual and automatic operation in an
either/or fashion until user confidence and training are adequate.
5. Maximum time should be provided for personnel training and systems
design proofing.
6. The test programming of delivered hardware will be adequate and proven.
7. A systematic method of data processing must be developed to handle the
large flow of test results and performance history generated by the
automatic process.
Before discussing the various checkout configurations and plans, it is necessary to
clarify and define certain operations and test conditions. The vehicle
measurements and controls are separated into: (1) operational measurements and
controls used to prepare and launch the vehice; and (2) telemetry measurements
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12. used to evaluate flight performance.
Measurements of the state of the vehicle are needed for both vehicle operation and
for measuring programs. Such measurements go both to the operational equipment
and to the telemetry system. Prior to assembly, the stage also has operational and
measuring and telemetry checkout requirements. Separate stage interface GSE is
generated as an integral part of the stage design. The equipment may be no more
than a standard electrical distribution system or, in some cases, it may contain
controls and manual monitoring equipment. Some versions may have such items
as analog to digital conversion equipment to allow proper mating with digital
ground support equipment.
Stage interface GSE is broken into two main categories: circuitry concerned with
the operational task, and circuitry utilized to manipulate and evaluate the
measuring and telemetry hardware. Here the stage and its interface GSE are
connected to the facility test equipment. Non-electrical stimuli, such as pressures,
are fed directly from the facility test equipment to the vehicle. To properly
simulate upper and lower interfaces, stage substitutes are provided so that the
entire operation can be evaluated. In the case of liquid propulsion stages, most of
this operation would be concerned with evaluating and calibrating the outputs of
the various measuring adapters contained within the stage. The future
development of an rf link can reduce the number of hard wires which travel
through the stage interface GSE. Interface GSE for measuring and telemetry
systems will consist of electrical measurement stimulation circuitry and a set of
digital acquisitional equipment.
At the launch site all measuring and telemetry information can be received
through an rf link from each stage or up to launch day through a coaxial cable to
avoid radiation. All of the operational portions of the stage interface GSE are
connected to the operational and launch equipment, thus completing the circuitry
required to prepare and launch the vehicle. The intelligence and comparison units
to handle the operational measurements and controls of the vehicle system will be
the computer complex. The heart of this complex will be a medium-size general-
purpose digital computer, which will handle the digital guidance equipment. The
computer will be expanded to handle the various types of analog and digital
equipment in operational checkout. It also will generate commands and data to
preset and launch the vehicle.
As soon as the digital guidance system is introduced in the present Saturn C-l
configuration, automatic checkout equipment will be installed at the stage
contractor site as well as at the launch site. For a number of vehicles, the dual
capability of manual and automatic checkout possibilities will be available until
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13. the new digital checkout system can be proven. By the time the Saturn C-4
configuration is ready to be launched, it will be mandatory that the new automatic
checkout scheme with the digital mode be operational because the distances
between launch site and control room are so great that no other method will be
possible.
Te new automatic system will demand an extreme amount of engineering
discipline and enforcement of standardization at the stage contractor's plant as
well as at the launch site, to make the system reliable and to achieve our goal.
Rajneesh Budania (ELECTRICAL ENG.)
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