- The document describes a 3D software wreckage reconstruction system (3D-SWRPS) used to assist in investigating the 2002 crash of China Airlines Flight CI611.
- The 3D-SWRPS utilizes 3D modeling of wreckage recovered from the site, laser scanning, and a reference Boeing 747-200 model to reconstruct wreckage pieces in 3D.
- Over 160 wreckage pieces were scanned and reconstructed in 3D to determine fracture patterns and the aircraft breakup sequence.
In the aftermath of the September 11, 2001 attacks on the World Trade Center Towers, and the inability of First Responders to effect a rescue of any victims above the aircraft impact points, the SKYSCRAPER EMERGENCY RESPONSE TEAM or IN-S.E.R.T., strategy was crafted with colleagues within academia, industry and government. Formulated with input from key members of the Detroit Fire Department, inclusive of the late General Manager Weylin Gildon, and the Chicago Fire Department, IN-S.E.R.T. was designed as a means to effectively rescue disaster victims trapped in historically inaccessible areas. In this case, the upper floors of a burning high-rise, while using off-the-shelf firefighting technology and modified first response rescue methodologies structured to epitomize operational simplicity. Moreover, it is to serve as a global first response template to be utilized by emergency teams in multiple countries benefitting from strict protocols of cooperation/collaboration.
IN-S.E.R.T. teams, strategically based around the world and equipped with Boeing C-17 Globemasters modestly modified for this mission, would be capable of responding to any emergency, anywhere.
This paper was presented to 18 Argonne National Laboratory scientists and 2 FEMA representatives for review on 18 October, 2001.
Copyright GHHLLC 2001-2008
248-695-0009
This document provides a literature review and recommendations for designing flight deck documentation to optimize readability and comprehension. It discusses typographical factors like typefaces, font size, spacing, and line length that affect legibility and readability of printed text in the cockpit environment. The document also addresses environmental conditions like glare and paper quality that influence reading. It aims to bridge the gap between basic typography research and the information needs of flight deck documentation designers.
The document discusses various components of aviation and airport infrastructure management. It covers topics like air traffic management, runway infrastructure, fuel infrastructure, terminal infrastructure, and safety risk management. For runway infrastructure, it describes airport pavement management systems which are used to predict pavement condition and determine maintenance and repair plans. It also provides examples of managing risks from equipment outages at major US airports. For terminal infrastructure, it outlines the key functions of terminals and formulas for calculating passenger loads at security checkpoints.
This document discusses aerodynamic modeling and simulation of aircraft at high angles of attack. It outlines some of the challenges, including developing accurate mathematical models from wind tunnel data and flight tests. Nonlinear effects like separated and unsteady flow require dynamic modeling approaches. Qualitative analysis of the nonlinear dynamics can reveal critical flight conditions like departures and spins. Flight simulations are used alongside flight tests to evaluate control laws and train pilots. Accurate modeling of phenomena like aerodynamic asymmetry is important for understanding spin behavior.
This document summarizes the results of Project MAX GAP, which aimed to correlate pilot-induced oscillation (PIO) tendency ratings with a new preflight calculation called the Gap Criterion. The USAF Test Pilot School conducted flight tests and simulator sessions to collect longitudinal handling qualities data. Overall results confirmed a correlation between Gap Criterion and PIO tendency ratings for most test conditions. The project gathered both new and historical simulator and flight test data to augment the database for predicting PIO using describing function analysis of rate-limited actuators.
Safety Risk Assessment for Aircraft Fuel Management (VU)Viktor Gregor
This master's thesis develops a risk assessment model for aircraft fuel management using dynamically coloured Petri nets and rare event simulation methods, in order to estimate the probabilities of events like landing with less than the required final reserve fuel or fuel starvation based on flight parameters and expected conditions. The model accounts for the roles of pilots, airline operations control, airports and the environment to simulate fuel consumption and the evolution of a flight while considering uncertainties. The purpose is to provide a basis for further research on risk assessment of fuel management.
This document discusses Traffic Alert and Collision Avoidance Systems (TCAS). It provides background on TCAS, including how it works using secondary surveillance radar, its evolution through different generations, and improvements made based on past mid-air collisions. The document also covers TCAS displays, advisories, and pilot actions in response to resolutions. It discusses some human factors considerations regarding TCAS design, implementation, and use as well as incidents where human factors played a role in near mid-air collisions.
Estudio de la física de la teletransportacinMorfeo1
This document summarizes a study on teleportation physics. It proposes two quasi-classical physics concepts for teleportation: 1) Engineering the spacetime metric to induce a traversable wormhole. 2) Treating spacetime metric changes in terms of equivalent changes in the vacuum permittivity and permeability constants using a polarizable vacuum-general relativity approach. It also reviews quantum teleportation and explores extra dimensions, psychokinesis, and anomalous teleportation phenomena as potential teleportation models. The study evaluates various physics theories for their ability to describe teleportation and identifies promising experiments.
In the aftermath of the September 11, 2001 attacks on the World Trade Center Towers, and the inability of First Responders to effect a rescue of any victims above the aircraft impact points, the SKYSCRAPER EMERGENCY RESPONSE TEAM or IN-S.E.R.T., strategy was crafted with colleagues within academia, industry and government. Formulated with input from key members of the Detroit Fire Department, inclusive of the late General Manager Weylin Gildon, and the Chicago Fire Department, IN-S.E.R.T. was designed as a means to effectively rescue disaster victims trapped in historically inaccessible areas. In this case, the upper floors of a burning high-rise, while using off-the-shelf firefighting technology and modified first response rescue methodologies structured to epitomize operational simplicity. Moreover, it is to serve as a global first response template to be utilized by emergency teams in multiple countries benefitting from strict protocols of cooperation/collaboration.
IN-S.E.R.T. teams, strategically based around the world and equipped with Boeing C-17 Globemasters modestly modified for this mission, would be capable of responding to any emergency, anywhere.
This paper was presented to 18 Argonne National Laboratory scientists and 2 FEMA representatives for review on 18 October, 2001.
Copyright GHHLLC 2001-2008
248-695-0009
This document provides a literature review and recommendations for designing flight deck documentation to optimize readability and comprehension. It discusses typographical factors like typefaces, font size, spacing, and line length that affect legibility and readability of printed text in the cockpit environment. The document also addresses environmental conditions like glare and paper quality that influence reading. It aims to bridge the gap between basic typography research and the information needs of flight deck documentation designers.
The document discusses various components of aviation and airport infrastructure management. It covers topics like air traffic management, runway infrastructure, fuel infrastructure, terminal infrastructure, and safety risk management. For runway infrastructure, it describes airport pavement management systems which are used to predict pavement condition and determine maintenance and repair plans. It also provides examples of managing risks from equipment outages at major US airports. For terminal infrastructure, it outlines the key functions of terminals and formulas for calculating passenger loads at security checkpoints.
This document discusses aerodynamic modeling and simulation of aircraft at high angles of attack. It outlines some of the challenges, including developing accurate mathematical models from wind tunnel data and flight tests. Nonlinear effects like separated and unsteady flow require dynamic modeling approaches. Qualitative analysis of the nonlinear dynamics can reveal critical flight conditions like departures and spins. Flight simulations are used alongside flight tests to evaluate control laws and train pilots. Accurate modeling of phenomena like aerodynamic asymmetry is important for understanding spin behavior.
This document summarizes the results of Project MAX GAP, which aimed to correlate pilot-induced oscillation (PIO) tendency ratings with a new preflight calculation called the Gap Criterion. The USAF Test Pilot School conducted flight tests and simulator sessions to collect longitudinal handling qualities data. Overall results confirmed a correlation between Gap Criterion and PIO tendency ratings for most test conditions. The project gathered both new and historical simulator and flight test data to augment the database for predicting PIO using describing function analysis of rate-limited actuators.
Safety Risk Assessment for Aircraft Fuel Management (VU)Viktor Gregor
This master's thesis develops a risk assessment model for aircraft fuel management using dynamically coloured Petri nets and rare event simulation methods, in order to estimate the probabilities of events like landing with less than the required final reserve fuel or fuel starvation based on flight parameters and expected conditions. The model accounts for the roles of pilots, airline operations control, airports and the environment to simulate fuel consumption and the evolution of a flight while considering uncertainties. The purpose is to provide a basis for further research on risk assessment of fuel management.
This document discusses Traffic Alert and Collision Avoidance Systems (TCAS). It provides background on TCAS, including how it works using secondary surveillance radar, its evolution through different generations, and improvements made based on past mid-air collisions. The document also covers TCAS displays, advisories, and pilot actions in response to resolutions. It discusses some human factors considerations regarding TCAS design, implementation, and use as well as incidents where human factors played a role in near mid-air collisions.
Estudio de la física de la teletransportacinMorfeo1
This document summarizes a study on teleportation physics. It proposes two quasi-classical physics concepts for teleportation: 1) Engineering the spacetime metric to induce a traversable wormhole. 2) Treating spacetime metric changes in terms of equivalent changes in the vacuum permittivity and permeability constants using a polarizable vacuum-general relativity approach. It also reviews quantum teleportation and explores extra dimensions, psychokinesis, and anomalous teleportation phenomena as potential teleportation models. The study evaluates various physics theories for their ability to describe teleportation and identifies promising experiments.
The document contains three unrelated articles:
1) A summary of an Afghan National Army artillery company training with Marines to improve their targeting accuracy with old Russian artillery guns.
2) An overview of gas-free engineering procedures for entering confined spaces aboard Navy ships, including identifying atmospheric hazards and certification requirements.
3) A brief report on Old Dominion University being included in a ranking of top military-friendly schools based on benefits for veteran and military students.
Brief history of autonomous functions from the past 10 years of research. Focus is on V&V considerations and approaches applied for various autonomous functions. New regulatory trends that we can incorporate down into our system demonstrators and flight test procedures.
The document presents a conceptual design study for a medical evacuation (Medevac) air vehicle. It determines key mission requirements including a range of 805 km and cruise speed of 217 knots based on typical distances to trauma centers and the "golden hour" concept. A hybrid electric propulsion system is proposed using a turboshaft engine, electric generator, and 4 ducted fans for vertical takeoff and landing capability while meeting the high-speed cruise requirement. An initial weight estimate of 3,250 lbs is calculated for the conceptual aircraft design. The study explores using hybrid electric propulsion for improved distributed thrust vectoring for takeoff/landing compared to traditional rotorcraft.
Unmanned Low-altitude Air Cargo, Towards Demonstration With A Specific Opera...Florian-Michael Adolf
At DLR (German Aerospace Center) novel concepts and technologies are investigated focusing on automated air cargo delivery for up to 1 t of cargo payload. The DLR project ALAADy (Automated Low Altitude Air Delivery) addresses a large scope of challenges that come along with such an unmanned aircraft for cargo operations. This presentation will provide an update on the project as well as a status on latest developments, i.e. from use cases and towards our demonstration goal. The discussed aspects comprise a blend of use case requirements and a discussion of onboard functional requirements such that a safe operation under the prospective EASA specific category would be admissible and feasible in very low level flight.
This document summarizes the development and testing of a navigation system for precisely navigating an unmanned vertical takeoff and landing (VTOL) aerial system to land on a moving vessel. It describes how Boeing's Unmanned Little Bird program modified a helicopter to integrate and demonstrate a GNSS/inertial navigation system. This navigation system uses relative navigation techniques to autonomously guide the helicopter to a predetermined precision landing on a ship deck, regardless of deck size or ship motion. The document outlines the development history and phases of testing this navigation system, including motion platform testing, manual and automatic landings on a moving trailer rig designed to emulate a ship deck.
Development of Navigation and Automated Flight Control System Solutions for M...Mark Hardesty
1) The document describes flight tests of a navigation system to guide an unmanned helicopter to precision landings on ships.
2) Tests were conducted using a modified trailer rig emulating a ship deck, and showed the navigation system could successfully guide the helicopter to land and secure itself to the deck.
3) In preparation for maritime flight tests, the helicopter's cockpit instrumentation was upgraded to a glass cockpit display for improved visibility in varied environmental conditions expected over water.
A monte carlo simulation for evaluating airborne collision risk in intersecti...MEHenry
The Intersecting Operations (IO) Model was developed to define a set of separation standards for converging and intersecting runway operations which statistically mitigates collision risk for modeled airport geometries and associated parameters. The IO Model incorporates synthetic trajectory models that account for the variation within historical environmental variables and actual flight data informed by NOP and ASDE-X sources. This model provides a simulation by which analysts can statistically determine an area of unacceptable risk and propose a risk mitigation methodology for these areas.
The document discusses Department of Defense weather programs and the organization of the US Air Force weather services. It describes how the Air Force weather agency oversees weather operations and provides global weather analysis and forecasting. It also summarizes the roles of operational weather squadrons in providing regional weather support and weather flights at Air Force bases in supporting local weather needs.
Disaster Risk Reduction: A Case Study on Missing Aircrafts and Damage of Brid...IRJET Journal
This document discusses two case studies: 1) The missing Indian Air Force aircraft AN-32 and fighter jet Sukhoi SU-30. It details the search efforts and provides theories for what may have caused them to go missing. 2) The collapse of the Mahad bridge in India due to flooding, which resulted in buses falling into the river. The response efforts including search and rescue are described. Countermeasures are proposed, such as using hyperspectral imaging instead of radar to detect missing aircraft.
Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)Designage Solutions
Next part of "A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)" with case studies.
Find previous presentation here- http://www.slideshare.net/HarshadaGurav/a-review-of-flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
The document analyzes the stability and control of the Zivko Edge 540T aerobatic aircraft. It estimates key physical properties and determines equilibrium flight conditions. Non-dimensional stability derivatives are then calculated, showing the aircraft is longitudinally stable. Lateral stability is also analyzed, with the aircraft found to be laterally stable except for an unstable spiral mode. Dimensional derivatives are used to examine specific stability modes, with most modes stable except the spiral mode.
This document discusses the conceptual design, structural analysis, and flow analysis of an unmanned aerial vehicle (UAV) wing. It begins by providing background on UAVs and listing the design requirements and parameters for the wing. It then describes selecting a rectangular wing planform and NACA 2415 airfoil based on the design criteria. Aerodynamic analysis is conducted to determine performance parameters like lift coefficient and drag. Structural analysis of the wing is performed using two spar designs - a tubular spar with and without a strut. Maximum stresses and bending moments are calculated and compared for straight and tapered wing configurations. Flow simulation will also be conducted on the finalized wing design.
This document provides a summary of an individual's military experience and training. It details their occupations in the Navy from 2007 to 2015 as an Aviation Ordnanceman (AO) and Airman Recruit/Airman (AR/AN) as well as course histories. Their duties included maintaining and inspecting airborne weapons and aviation ordnance equipment. They completed various Navy courses in intermediate armament maintenance, aircraft weapons systems, ordnance, and aviation fundamentals.
This document is the foreword and preface for a manual on planning, designing, and drilling wells for the US Army, Navy, and Air Force. It states that the manual provides guidance for engineer personnel on techniques for installing wells, including expedient methods for digging shallow wells. The manual focuses on common experiences well drillers encounter in the field and well installation in NATO countries. It is intended to help engineer personnel successfully install wells by understanding groundwater principles, well drilling mechanics, and hydraulics.
A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehi...Designage Solutions
A brief study of flight dynamics and different types of simulation and analysis are presented here.
Find case studies in my next PPT.- http://www.slideshare.net/HarshadaGurav/flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
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 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.
The document discusses the history and development of artificial intelligence over the past 70 years. It outlines some of the key milestones in AI research including the creation of logic theories, machine learning algorithms, and neural networks. Recent advances in deep learning now allow AI systems to perform complex tasks like image recognition and natural language processing.
This document summarizes the final report on the April 10, 2010 accident of the Tu-154M aircraft with tail number 101 of the Republic of Poland. The 3-sentence summary is as follows:
The aircraft crashed during approach to Smolensk "Severny" airdrome in Russia, descending below the minimum safe altitude in weather conditions below the established minima. All 96 people on board were killed in the accident. An investigation was conducted in accordance with ICAO standards to determine the causes and make safety recommendations to prevent future accidents.
Ceph is an open-source distributed storage system that provides object, block, and file storage. The document discusses optimizing Ceph for an all-flash configuration and analyzing performance issues when using Ceph on all-flash storage. It describes SK Telecom's testing of Ceph performance on VMs using all-flash SSDs and compares the results to a community Ceph version. SK Telecom also proposes their all-flash Ceph solution with custom hardware configurations and monitoring software.
The document contains three unrelated articles:
1) A summary of an Afghan National Army artillery company training with Marines to improve their targeting accuracy with old Russian artillery guns.
2) An overview of gas-free engineering procedures for entering confined spaces aboard Navy ships, including identifying atmospheric hazards and certification requirements.
3) A brief report on Old Dominion University being included in a ranking of top military-friendly schools based on benefits for veteran and military students.
Brief history of autonomous functions from the past 10 years of research. Focus is on V&V considerations and approaches applied for various autonomous functions. New regulatory trends that we can incorporate down into our system demonstrators and flight test procedures.
The document presents a conceptual design study for a medical evacuation (Medevac) air vehicle. It determines key mission requirements including a range of 805 km and cruise speed of 217 knots based on typical distances to trauma centers and the "golden hour" concept. A hybrid electric propulsion system is proposed using a turboshaft engine, electric generator, and 4 ducted fans for vertical takeoff and landing capability while meeting the high-speed cruise requirement. An initial weight estimate of 3,250 lbs is calculated for the conceptual aircraft design. The study explores using hybrid electric propulsion for improved distributed thrust vectoring for takeoff/landing compared to traditional rotorcraft.
Unmanned Low-altitude Air Cargo, Towards Demonstration With A Specific Opera...Florian-Michael Adolf
At DLR (German Aerospace Center) novel concepts and technologies are investigated focusing on automated air cargo delivery for up to 1 t of cargo payload. The DLR project ALAADy (Automated Low Altitude Air Delivery) addresses a large scope of challenges that come along with such an unmanned aircraft for cargo operations. This presentation will provide an update on the project as well as a status on latest developments, i.e. from use cases and towards our demonstration goal. The discussed aspects comprise a blend of use case requirements and a discussion of onboard functional requirements such that a safe operation under the prospective EASA specific category would be admissible and feasible in very low level flight.
This document summarizes the development and testing of a navigation system for precisely navigating an unmanned vertical takeoff and landing (VTOL) aerial system to land on a moving vessel. It describes how Boeing's Unmanned Little Bird program modified a helicopter to integrate and demonstrate a GNSS/inertial navigation system. This navigation system uses relative navigation techniques to autonomously guide the helicopter to a predetermined precision landing on a ship deck, regardless of deck size or ship motion. The document outlines the development history and phases of testing this navigation system, including motion platform testing, manual and automatic landings on a moving trailer rig designed to emulate a ship deck.
Development of Navigation and Automated Flight Control System Solutions for M...Mark Hardesty
1) The document describes flight tests of a navigation system to guide an unmanned helicopter to precision landings on ships.
2) Tests were conducted using a modified trailer rig emulating a ship deck, and showed the navigation system could successfully guide the helicopter to land and secure itself to the deck.
3) In preparation for maritime flight tests, the helicopter's cockpit instrumentation was upgraded to a glass cockpit display for improved visibility in varied environmental conditions expected over water.
A monte carlo simulation for evaluating airborne collision risk in intersecti...MEHenry
The Intersecting Operations (IO) Model was developed to define a set of separation standards for converging and intersecting runway operations which statistically mitigates collision risk for modeled airport geometries and associated parameters. The IO Model incorporates synthetic trajectory models that account for the variation within historical environmental variables and actual flight data informed by NOP and ASDE-X sources. This model provides a simulation by which analysts can statistically determine an area of unacceptable risk and propose a risk mitigation methodology for these areas.
The document discusses Department of Defense weather programs and the organization of the US Air Force weather services. It describes how the Air Force weather agency oversees weather operations and provides global weather analysis and forecasting. It also summarizes the roles of operational weather squadrons in providing regional weather support and weather flights at Air Force bases in supporting local weather needs.
Disaster Risk Reduction: A Case Study on Missing Aircrafts and Damage of Brid...IRJET Journal
This document discusses two case studies: 1) The missing Indian Air Force aircraft AN-32 and fighter jet Sukhoi SU-30. It details the search efforts and provides theories for what may have caused them to go missing. 2) The collapse of the Mahad bridge in India due to flooding, which resulted in buses falling into the river. The response efforts including search and rescue are described. Countermeasures are proposed, such as using hyperspectral imaging instead of radar to detect missing aircraft.
Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)Designage Solutions
Next part of "A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehicle (UAV)" with case studies.
Find previous presentation here- http://www.slideshare.net/HarshadaGurav/a-review-of-flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
The document analyzes the stability and control of the Zivko Edge 540T aerobatic aircraft. It estimates key physical properties and determines equilibrium flight conditions. Non-dimensional stability derivatives are then calculated, showing the aircraft is longitudinally stable. Lateral stability is also analyzed, with the aircraft found to be laterally stable except for an unstable spiral mode. Dimensional derivatives are used to examine specific stability modes, with most modes stable except the spiral mode.
This document discusses the conceptual design, structural analysis, and flow analysis of an unmanned aerial vehicle (UAV) wing. It begins by providing background on UAVs and listing the design requirements and parameters for the wing. It then describes selecting a rectangular wing planform and NACA 2415 airfoil based on the design criteria. Aerodynamic analysis is conducted to determine performance parameters like lift coefficient and drag. Structural analysis of the wing is performed using two spar designs - a tubular spar with and without a strut. Maximum stresses and bending moments are calculated and compared for straight and tapered wing configurations. Flow simulation will also be conducted on the finalized wing design.
This document provides a summary of an individual's military experience and training. It details their occupations in the Navy from 2007 to 2015 as an Aviation Ordnanceman (AO) and Airman Recruit/Airman (AR/AN) as well as course histories. Their duties included maintaining and inspecting airborne weapons and aviation ordnance equipment. They completed various Navy courses in intermediate armament maintenance, aircraft weapons systems, ordnance, and aviation fundamentals.
This document is the foreword and preface for a manual on planning, designing, and drilling wells for the US Army, Navy, and Air Force. It states that the manual provides guidance for engineer personnel on techniques for installing wells, including expedient methods for digging shallow wells. The manual focuses on common experiences well drillers encounter in the field and well installation in NATO countries. It is intended to help engineer personnel successfully install wells by understanding groundwater principles, well drilling mechanics, and hydraulics.
A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehi...Designage Solutions
A brief study of flight dynamics and different types of simulation and analysis are presented here.
Find case studies in my next PPT.- http://www.slideshare.net/HarshadaGurav/flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
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 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.
The document discusses the history and development of artificial intelligence over the past 70 years. It outlines some of the key milestones in AI research including the creation of logic theories, machine learning algorithms, and neural networks. Recent advances in deep learning now allow AI systems to perform complex tasks like image recognition and natural language processing.
This document summarizes the final report on the April 10, 2010 accident of the Tu-154M aircraft with tail number 101 of the Republic of Poland. The 3-sentence summary is as follows:
The aircraft crashed during approach to Smolensk "Severny" airdrome in Russia, descending below the minimum safe altitude in weather conditions below the established minima. All 96 people on board were killed in the accident. An investigation was conducted in accordance with ICAO standards to determine the causes and make safety recommendations to prevent future accidents.
Ceph is an open-source distributed storage system that provides object, block, and file storage. The document discusses optimizing Ceph for an all-flash configuration and analyzing performance issues when using Ceph on all-flash storage. It describes SK Telecom's testing of Ceph performance on VMs using all-flash SSDs and compares the results to a community Ceph version. SK Telecom also proposes their all-flash Ceph solution with custom hardware configurations and monitoring software.
This is seminar report of ageing of aircraft.this useful for those student who want to give seminar on designing area of aircraft.In this report you will find brief introduction of ageing of aircraft.
Improvements to Situational Awareness During Approach and Landing Through Enh...Justin Stephen Brown
Pilot workload varies greatly during a typical flight. Technological advances are designed to reduce pilot workload and improve safety by eliminating pilot tasks during the busiest phases of flight - approach and landing. But do these new systems actually increase pilot workload? How do we measure the workload on the pilot? How do we measure safety?
Justin Stephen Brown
The Problem:
September 11, 2001 proved the High-rise rescue operational inadequacies of municipally based fire/rescue services. It is imperative that this problem is quickly addressed using both existing and proposed technologies and methods.
A Solution:
IN-S.E.R.T. is a dedicated emergency response unit operated as an extension of The United States Coast Guard (USCG) F.E.M.A. and existing fire/rescue departments in any major city. Team members will have at their disposal a range of fire/rescue and fire suppression technologies designed to facilitate High-rise rescue operations. The potential flexibility of IN-S.E.R.T makes it a template for a broad spectrum of emergency responses not limited to High-rise rescue. Therefore, it has value beyond that immediately observable.
Technology, Equipment, Methods:
Specially trained personnel will benefit from the decades old expertise of the acclaimed “Smoke Jumpers” of the Western/Pacific Northwestern United States and Red Adair’s legendary pyro-containment methodologies. Additionally, they will benefit from newly developed Victim Extraction At Altitude (VEAA)techniques.
An Interactive Approach For Hierarchical Analysis Of Helicopter Logistics In ...Allison Thompson
This document summarizes a study that develops mathematical models to aid in planning helicopter missions for disaster relief operations. The planning problem is broken down into two hierarchical sub-problems - a top-level problem that determines tactical decisions like fleet composition and crew assignment, and a base-level problem that handles operational routing and loading. An iterative procedure coordinates the two levels to transfer information and improve solutions. Multiple objectives require a multi-criteria analysis and interactive process to evaluate alternative solutions.
The document discusses the flight testing of a flight management computer system (FMCS) for the Boeing 747-400 aircraft. It describes the development and certification testing of the FMCS, which featured unique system and hardware changes for the 747-400 as well as improvements over previous generation systems. Testing of the FMCS was a multi-faceted effort involving ground testing, laboratory testing, flight testing, and flights simulating typical airline operations to test navigation, flight planning, map display, and performance-related functions. A variety of data collection techniques were used including real-time monitoring with special test equipment.
I will give you a choice of two topics to write about. Choose one .docxsheronlewthwaite
I will give you a choice of two topics to write about. Choose one of the following:
1. Forensic Readiness
· What does this mean for a company?
· What are some of the benefits for a company? Explain each one.
· As an Security Manager of the company how would you present this to the CEO?
2. Computer Forensics Methodologies
· List them and explain each one.
· Pick one of the methodologies and describe
·
· What tools could you use for what situations.
· Procedures that you would follow.
· Types of documentation you would need to keep.
· Would it need to be done in a mobile lab or not? Why?
New York Times
July 13, 2009
http://www.nytimes.com/2009/07/14/business/14blackbox.html?_r=1&scp=1&sq=black%20boxes&st=cse
Airlines Study Alternatives to Jets’ Black Boxes
By CHRISTINE NEGRONI
Modern communication technology allows even those with little important to say to transmit real-time information about where they are and what they are doing. But last month, when Airbus jets from Air France and Yemenia Airways crashed into the ocean, taking their black boxes into the deep with them, neither aircraft could send its data and cockpit voice recordings to a secure place on the ground.
On July 2, the day that the missing recorders from Air France Flight 447 were presumed to have exhausted their 30-day battery and stopped emitting the pinging noise of the locator beacon, Airbus announced that it would look for new ways to reduce the chance of losing critical data.
“This is a worldwide industry issue, albeit a rare one,” said Mary Anne Greczyn, manager of communications for Airbus Americas. In an e-mail message, Ms. Greczyn said, “Recent accidents certainly made this a front-burner topic of discussion.”
What is known so far about the crash of Flight 447, in which 228 people died, comes from automatic messages sent from the airplane to Air France. Those messages are not intended to provide information for accident investigators but are routinely used by airlines for maintenance. When an airplane is crossing an ocean and out of radio range, only the most important information is sent, since communication must be by satellite and transmission is expensive. Airlines can select what kind of flight data is worth the price of satellite time.
According to a statement from Airbus, even using the normal radio signal to send all the information about a flight would require enormous bandwidth.
But Krishna Kavi, a professor of computer science and engineering at the University of North Texas, said that might not be the case. In 2001, Mr. Kavi proposed transmitting in real time just the information from the flight data recorder. “The amount of data is very small compared to video photos that you receive on smartphones,” he said. Mr. Kavi said his plan was even more achievable today.
Mike Poole, an air crash investigator with CAE Flightscape, an aviation safety company in Canada, said that transmitting all that data in real time “sounds really attractive” but ...
As the Manager of Accident Prevention at Westinghouse Electric, Lewis Barbe, a safety engineer, received the National Safety Council Award for establishing a world safety record.
FE Based Crash Simulation of Belly Landing of a Light Transport AircraftRSIS International
Crash survivability is one of the key features to be
attended during the design of an airworthy aircraft. Belly/crash
landing is the most common phenomenon to be considered in
developing a crashworthy product. That makes it essential to
have redundant structure to enhance the safety of occupants and
also limit the damage to easily repairable state in case of such
event. Even from the certification point of view, it is necessary to
investigate this event by test/analysis. Recent development of
advance computing and their capability to simulate such
phenomenon to acceptable accuracy under given conditions
conveniently replace the need for test which is otherwise costly.
At the same time, one has to be cautious while selecting the
modeling parameters to simulate the condition near to reality.
Taking advantage of this feature an effort is made to simulate the
belly landing and its consequences on the structure complying to
the guidelines of the federal aviation regulations. This paper
presents the methodology adopted to successfully simulate the
belly landing phenomenon for a light transport aircraft flying
prototype.
Control of aircraft from the base station using eog siganl transmissiontheijes
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
The papers for publication in The International Journal of Engineering& Science are selected through rigorous peer reviews to ensure originality, timeliness, relevance, and readability.
Control of aircraft from the base station using eog siganl transmissiontheijes
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
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1. Application of the 3D Software Wreckage Reconstruction Technology at the
Aircraft Accident Investigation
Wen-Lin, Guan*1, Victor Liang *2, Phil Tai *3, Kay Yong**
Aviation Safety Council
16th Floor, 99 Fu-Hsing North Road, Taipei 105, Taiwan, R.O.C.
Tel:+886-2-25475200; Fax: +886-2-25474975
Abstract
The purpose of this paper is to present a methodology and application of a
Three-Dimensional-Software-Reconstruction and Presentation System (3D-SWRPS).
This system was developed to support the investigation of China Airlines flight CI611
in flight breakup accident that occurred on May 25, 2002. The accident aircraft was a
B747-200 carrying 19 crewmembers and 206 passengers. The accident occurred near
Penghu Island in the Taiwan Strait. All 225 people onboard the aircraft perished in
this accident. The Aviation Safety Council, an independent government organization
responsible for all civil aircraft accident and serious incident investigation, has been
investigating the accident. At the moment of this writing, this investigation is still
ongoing and probable causes of this accident have not yet been determined.
The 3D-SWRPS utilizes a combination of the computer 3D-graphic techniques,
laser scanning of wreckages recovered, structure frame of a Boeing 747-200 cargo
aircraft, and a generic CATIA engineering model of the same type of aircraft. It can
provide sub-centimeter accuracy in the reconstruction process, and can be used to
determine fracture behavior and propagation of stress of break up. In addition, the
3D-SWRPS can combine radar return signal, wreckage salvage data, and ballistic
simulation program to assist in the analysis of breakup sequence. It is believed that
this technology would play an important role in supporting future accident
investigation.
I. Introduction
When an aircraft accident happens, investigation begins on-scene: searching for
and subsequent readout of the flight recorders, gathering relevant factual data,
drafting analytical topics, finding out probable causes and proposing safety
*1
Investigation Lab / Deputy Chief
*2
Investigation Lab / Engineer
*3
Investigator
**
Managing Director
1
2. recommendations, etc.
The above work process is familiar to everyone in this field; however, for an
in-flight breakup accident such as Pan-American flight 103 (PA103, 747-100) [1];
Trans World Airlines flight 800 (TW800, 747-141) [2], or Swissair flight 111 (SR111,
MD-11) [3], wreckage reconstruction becomes an important method to help factual
evidence collection and the following task of analysis.
There are several relevant applications associated with wreckage reconstruction:
finite element analysis (FEA), for the research of structure stress and metal fatigue;
computational fluid dynamics (CFD), for verification of flow fields; evaluation of
human-mechanics interface and flight controls by engineering flight simulators. For
example, in hard landing investigations for a MD-11 and EMB-145, FEA was used to
examine the stress of landing gears and support structures [4][5].
After the Air France Concorde accident in year 2000, academic researches in
University of Leeds applied CFD to analyze the Concorde’s phenomenon of
combustible stabilization [6].
Thanks to the advanced technology, the application of 3D surveying technology
provides an even better way to promote the efficiency and cost saving of wreckage
reconstruction. This so-called 3D surveying technology is by aiming the precise 3D
laser scanner at an object to measure its tangent planes, then align these planes with
selected reference points of alignment to assemble them into complete 3D model.
The methodology and application of 3D-SWRPS presented here can also be
used for future accident investigation in the area of three-dimensional site survey, in
secluded mountain area, or inside an airport, to determine the distributional
relationship of wreckage and terrain.
II. Aviation Accident Investigation and Wreckage Reconstruction
2.1 Characteristics of Aviation Accident Investigation
Aviation accident investigation integrates the technologies of aerospace, avionics,
human factor, flight operation, weather, underwater recovery, spatial remote sensing
(Global Position System, Geographic Information System, Remote Sensing), etc.
ICAO Annex 13 generally dictates the investigation procedures for the determination
of causal factors, and for proposing safety recommendations for the prevention of
similar occurrence from happening again.
The investigation of aviation accident as a whole contains six phases: on-scene
investigation, factual data collection, factual verification, analysis, findings, and
safety recommendations.
2
3. Size of the investigation team depends on the nature and severity of the
occurrence. A typical investigation team should include groups of flight operations,
flight recorders, air traffic control, weather, airport, maintenance, survival factor,
human factor, system, and logistics.
The most difficult accident investigation in terms of budget and logistic is when
it happens over the water that requires underwater recovery of the recorders and
wreckages. For an in-flight breakup accident, wreckage reconstruction becomes very
informational helpful in the determination of causal factors. In the past decade, the
aviation accident investigation agencies were aggressively seeking for an efficient
method of wreckage reconstruction but without significant development. In the last
fifteen years there were six in-flight breakup accidents: PA 103, AA811, TW800,
SR111, Air France’s Concorde, and China Airlines’ CI611. As summarized in Table 1,
wreckage reconstructions were conducted for the determination of their probable
causes.
2.2 Methods of Wreckage Reconstruction
Irrespective of whether an aircraft crashed on land or into the sea, after
salvaging the wreckage, investigators need to identify and examine the wreckage
pieces one by one. When the source of force and destructive direction of structure
could not be determined, then reconstruction using the wreckage collected is a viable
method. In general, to evaluate probable causes, determination of the failure sequence
is required. However, not all accidents need wreckage reconstruction. For example,
the case of Singapore Airlines flight 006 (SQ006) crashed on the runway at Chiang
Kai-Shek International Airport in Taiwan on October 31, 2000, its structure failure
sequence could be determined by ground collision marks and wreckage distribution,
and hence did not require reconstruction of the wreckages.
Wreckage reconstruction serves three purposes: first, to find out source of
structure failure; second, to judge the endurance of condition of forces; and third, to
study the propagation of stress or force between main structures.
Several preparation considerations are required prior to the wreckage
reconstruction: 1) Evaluation of the reconstruction site; 2) Identification and tagging
of wreckages; 3) Partial or whole wreckage reconstruction; 4) 2D wreckage layout or
3D wreckage reconstruction; 5) Design of frame or mock-up; 6) Wreckage cut up and
crane operation; 7) Accessibility to the mock-up; and 8) Safety concerns of personnel
at work. etc.
The determination of whether to proceed a partial or whole wreckage
3
4. reconstruction is an important issue. Decision should be made according to clues and
factual information collected during the on-scene investigation phase. These clues can
usually be radar tracks, flight recorder data, related testimonies, and characteristics of
salvaged wreckages. Those characteristics include failure conditions at different
sections of the fuselage, burning conditions, and fracture surfaces, etc.
For example, after the in-flight break up of TW800, primary radar data display
indicated that wreckages followed the flight path spread along down-wind side. In
interviews, testimonies such as "fireball and descending" appeared. There was
abnormality and high-energy sound wave recorded in the cockpit voice recorder.
Therefore, wreckage reconstruction of TW800 emphasized on finding out the source
of explosion; hence, the reconstruction was focused on fuselage and central fuel tanks
sections.
Furthermore, after the in-flight break up of SR111, primary radar data indicated
that wreckages followed the flight path and spread along down-wind side. Before the
cockpit voice recorder stopped recording, flight crews were discussing “cabin smoke
problem.” Therefore, wreckage reconstruction of SR111 emphasized on the source of
spark and smoke, reconstruction sections were then focused on fuselage, flight deck
and electrical wiring. In contrast to past aircraft wreckage hardware reconstruction,
TSB of Canada was the first to produce panoramic images of the flight deck, which
provides wreckage inspection technology similar to “virtual reality.” In conjunction
with wreckage sketches, 3D CAD models, and relevant power wiring diagrams, TSB
was able to demonstrate evidence of wire burning during the breakup sequence. The
3D CAD model used to establish SR111 wreckage reconstruction is an improved
method from the traditional hardware reconstruction.
From the experience of using 3D CAD model developed by TSB in SR111
investigation, ASC went on developing the 3D Software Wreckage Reconstruction
and Presentation System (3D-SWRPS).
2.3 Architectures of 3D-SWRPS
The 3D-SWRPS utilizes a combination of computer 3D-graphic techniques,
laser scanning of wreckages recovered, the structure frame of an identical B747-200
aircraft, and a generic CATIA engineering model of the same type of aircraft. It
provides sub-centimeter accuracy in the reconstruction process. It can also be used to
determine fracture behavior and propagation of stress of the break up. In addition, the
3D-SWRPS can combine radar return signal, wreckage salvage data, and ballistic
simulation program to assist analyzing the breakup sequence.
4
5. 3D-SWRPS project uses long range and precise 3D laser scanner. Table 2
summarizes the functions of 3D laser scanners- OPTECH (model ILRIS) and RIEGL
(model LMS Z420). Based on reliable operational safety of laser, it can achieve
precision to 3 mm with maximum range of 2 km. In order to align the 3D wreckage
model onto the “reference model”, two models were collected, a Boeing 747-200
CATIA model, and a scanned model of a China Airlines’ B747-200 cargo aircraft,
ASC selected the ILRIS to do the job. The 3D scanning was done to the whole
aircraft’s inner and outer body.
Sections 44, 46 and 48 of the CI611 wreckage were 3D scanned and modeled at
Hangar II of Tao Yuan Air Force Base (TAFB), Taiwan. In total, 161 pieces of
wreckage were digitized and modeled into 3D-SWRPS, among them, fifty wreckage
pieces needed crane handling to be scanned. Wreckages less than 1m in size or
smaller cargo floor beam pieces were ignored. The 3D scanning and modeling process
took nearly one month.
3D-SWRPS represents a different processing method for the aircraft wreckage
reconstruction through following:
3D object digitizing: Once the laser scanner scanned each individual piece,
the piece was then digitized. It processes organized point clouds, as produced
by most plane-of-light laser scanner and optical systems.
Aligning Multiple Datasets: During digitizing process, investigators need
either to rotate the wreckage or move the 3D laser scanner in order to
measure all wreckage surfaces. As a result, the digitizing process produced
several 3D scans expressed in different 3-dimensional coordinate system.
This step consists of bringing these scans into the same coordinate.
Merging Multiple Datasets: A 3D-graphic virtual reconstruction allows
investigators to automatically merge a set of aligned 3D scans of wreckage
into a reference model, which was obtained from the same type of aircraft
and Boeing’s CATIA model. This procedure reduces the noise in the original
3D data by averaging overlapped measurements.
Polygon Editing and Reduction: In order to control the computer’s memory
allocation, this step uses the polygon reduction tool to reduce 3D model’s
size.
Manually edit surfaces: Especially with uneven surfaces that may cause data
loss.
Texture Mapping: Investigators can create texture-mapped models from the
digitized color 3D data.
Break Up Animation: Major function of this module is to simulate the
5
6. in-flight breakup sequence, by combining radar data, ballistic trajectory, wind
profile data, and wreckage 3D model data in time history.
The 3D-SWRPS consists of six stand-alone programs: Ballistic Trajectory,
Polywork, Multigen Creator, Polytrans, Rational Reduction, and the Recovery
Analysis and Presentation System (RAPS). NTSB of USA developed the Ballistic
Trajectory Program. TSB of Canada developed RAPS. The Investigation Laboratory
of ASC Taiwan developed other programs and integrated the whole as 3D-SWRPS.
Figure 1 shows the detailed architectures of 3D-SWRPS.
After all 161 pieces of wreckage were scanned and modeled, ASC investigators
spent three months to align and attach 62 pieces onto the reference model, based upon
their frame station and stringer number of the original aircraft.
The result gives the investigators capability to interact with the 3D-SWRPS to
view the inner and outer side of the fuselage in different angles; to further examine the
fracture conditions of neighboring wreckage pieces, metal fatigue and stress
propagation of structures. In Addition, the 3D wreckage model also links to the
database of the Systems Group, where investigators could access wreckage attributes
through secured intranet. These attributes include size, station, section, damage photos,
3D model, etc.
III. Results and Discussion
3.1 Results of Cargo Aircraft 3D Model
The reference model of 747-200 cargo aircraft includes nose, fuselage, horizontal
and vertical tails, inner frame, duct, aft pressure bulkhead and door frames.
During D-check of the cargo aircraft, the heat insulation blanket was removed.
ASC spent thirty hours scanning the inner portion of the model. Figure 2 illustrates
the 3D model of 747-200 cargo aircraft’s inner left aft fuselage, including frame
segments of section 46, floor, duct, and installation platform for flight recorders.
Right side of Figure 2 indicates the outer portion of the fuselage model, including
registration number, nose wheel, flight deck and L1-door frame, etc.
3.2 Results of CI611 Wreckage 3D Model
ASC spent two months for the scanning and modeling of 161 pieces of wreckage.
Each piece requires three to eight scans depend on its shape. The basic element of a
3D model is composed of polygons. According to the conditions of the crooked and
6
7. fractured wreckage, each 3D model consists of polygons ranging from thirty to
seventy thousand in numbers, and from 3 MB to 120 MB in file size. The data
processing platform is PC-based hi-level graphics workstation, equipped with 1024
MB memory, AGP 4x graphics card, and 80 GB hard drive.
Figure 3 shows the crane operation and side-view of item 640. Fig. 3(A) is an
inner view of the 3D model of item 640; Fig. 3(B) is the outer view of the 3D model
of item 640. The size of item 640 is 260”x 200”, station number between 1920 and
2180; stringer number between S-24L and S-50R. Figure 4 illustrates the crane
operation and side-view of item 2136. The reference number of stations and stringers
are between 1960 and 2100, and between S-07L and S-11R, respectively.
3.3 Results of 3D Software Reconstruction
The entire 3D wreckage model is aligned with reference coordinates of stations
and stringers. Wreckages with the least deformed fracture surfaces were selected first
as reference point of alignment and aligning surfaces. The greatest difficulty in 3D
software reconstruction is the computer’s memory allocation and the appropriate
selection of reference point of alignment. An uneven selection of reference point of
alignment could cause gaps in the connecting surfaces of wreckages, or alignment
could not be done just like in actual hardware reconstruction.
By using the reference coordinates of item 640, when manually align this piece
onto the reference model of 747-200, it shows that the item is belongs to section 46 of
the right aft fuselage structure. Figure 5 indicates that the severe damage of outer
blend is located at stations 2060 and 2180, and a large “V” shaped fracture existed at
station 2180. Figure 5 also shows the inner view of item 640; the aft cargo-door frame
is slightly deformed but intact with relevant frames of fuselage. Fig. 5 also illustrates
significant fracture conditions between stations 1920 and 1980. Besides, the lower left
of figure 5 with a rectangular cut, is a sample of metal fatigue examination, detail
shown on Figure 6.
Upper Figure 6 shows the repair doubler of item 640. Lower Figure 6 shows the
3D models of fuselage and doubler. The blue dotted line is the area where SEM
examination was conducted. In fact, it is very useful to adopt the 3D-SWRPS to
evaluate or measure fracture behaviors. It could easily measure the arc-distance,
including curve angles on the surface of wreckages, then to mark or compare the
differences between the wreckage and reference model. Figure 7(a) indicates the “N”
shaped 12.5 cm crack at station 2160. Figure 7(b) shows the electron microscopic
examination of item 640, which shows metal fatigue crack around station 2100.
7
8. Totally, 1442 pieces of wreckage had been salvaged from the Taiwan Strait,
which were then identified and placed at the Air Force base hangar for hardware
reconstruction. After finish tagging, sketching, and initial examination, all wreckages
were arranged on the hangar floor according to their respective fuselage station and
stringer numbers. For the time being, there are 62 pieces of wreckage aligned on the
reference CATIA model. Fig. 8 shows the 2D layout and 3D software reconstruction
at section 46 and aft pressure bulkhead, view from the outer right side.
3.4 Comparison of 3D Hardware and Software Reconstruction
The utilization of 3D-SWRPS is generally better than 3D hardware
reconstruction. In fact, man power, budget, and space required for 3D-SWRPS is
much less than 3D hardware reconstruction. 3D-SWRPS has great advantages in
re-usability, ballistic trajectory analysis and simulation, and in conjunction with finite
element analysis.
The cost of 3D hardware reconstruction for CI611 was US$143,000, only for
section 46. The cost of 3D-SWRPS for CI611 was US$91,500, including crane
operation, rental of 3D scanner and labor cost of two engineers. Use of 2D wreckage
layout together with 3D software reconstruction might be the best choice if 3D
hardware reconstruction is not really that necessary from the investigation point of
view.
Table 3 summarizes and makes the comparison between 3D hardware and
software reconstruction of CI611.
IV. Conclusions
3D-SWRPS was developed by utilizing a combination of computer 3D-graphic
techniques, laser scanning of wreckage pieces plus generic engineering model of the
same type of aircraft. It can provide sub-centimeter accuracy scan quality, and can be
used to determine fracture behavior and aircraft breakup propagation.
Advantages of the 3D SWRPS are: a) No wreckage disposal problem; b)
Re-usability, once developed, the methodology can be used for other accident
investigation; c) Only one-half of the cost as compared to hardware reconstruction; d)
Flexibility in combining with simulation program for better analysis support.
References
[1] Aviation Accident Report, “Boeing 747-121, N739PA at Lockerbie, Dumfriesshire,
Scotland on 21 December 1988.” AAIB Report Number: 2/90 (EW/C1094), 1990.
8
9. [2] Aviation Accident Report, “In-flight Breakup Over the Atlantic Ocean Trans
World Airlines Flight 800 Boeing 747-141, N93119 near East Moriches, New
York July 17, 1996.” NTSB Report Number: AAR-00-03, 2000.
[3] “Aviation Safety Recommendations Material Flammability Standards
Investigation Into the Swissair Flight 111 Accident.” TSB Occurrence Number:
A98H0003, 2001.
[4] Har, J., “MD-11 Composite Spoiler Analysis Using MSC/NASTRAN & PATRAN
PLUS,” Korea Institute of Aeronautical Technology (KIAT), KIAT-RR-90-011,
1990.
[5] Francisco K. Arakaki, etl. “EMB-145 Nose Landing Gear Door Stress Analysis,”
Empresa Brasileira de Aeronautica, Structural Analysis Department, 12227-901
Sao Jose dos Campos - SP – Brazil, 1996.
[6] J. T., QinetiQ, “Fatal Concorde Fire Explained,” Leeds University (CFD Center),
Leeds, Yorkshire, Hampshire, UK., 2001.
[7] Vittorio Casella, “Accuracy Assessment Of Laser Scanning Data: A Case Study,”
University Of Pavia, Department of Building and Territorial Engineering, Via
Ferrata, Pavia, Italy, 2001.
[8] Aviation Accident Report, “Explosive Decompression—Loss of Cargo Door in
Flight United Airlines Flight 811 Boeing 747-122, N4713U HONOLULU,
HAWAII February 24, 1989.” NTSB Report Number: AAR-92-02.
9
10. Table 1 Aircraft Wreckage Reconstruction for In-Flight Break-Up Investigations in Recent 15
Years.
PA103 UAL811 TW800 SR111 F-BTSC CAL611
Accident Date 1988.12.21 1989.02.24 1996.07.17 1998.09.02 2000.07.25 2002.05.25
NTSB/AAR-92/0 NTSB/AAR-00/0
Report No. AAIB/2/90 2 3
In-Flight In-Flight In-Flight during takeoff In-Flight
Possible Cause Breakup Breakup Breakup In-Flight Fire In-Flight Fire Breakup
High explosive Explosive Center Tank fire in the ceiling Debris throw the
Device Decompression Explosion area lower wing tank
Foreword Foreword Cockpit and
Reconstruction Full Fuselage and Fuselage with Fuselage and Foreword Wing Structure AFT Fuselage
Area Tail plane Cargo Door Center Wing Tank Fuselage and Tanks Sect 44, 46 and 48
3D Mockup Yes Yes Yes Yes 2D Layout Yes
3D SWRPS No No No No No Yes
Finite Element
Analysis Yes Yes ? Yes Yes
Table 2 Comparison of Long-Range and Precision 3D Laser Scanners
Manufacturer OPTECH (ILRIS-3D) RIEGL (LMS Z420)
Range 30 m ~ 2000 m ~ 800 m
Accuracy 3 mm 5 mm
Speed 2000 points/sec 3000 points/sec
Spot spacing At 100 m < 2.6 mm ?
Controller PDA (serial, IR) PC / Laptop
Weight 12.0 KG 14.5 kg
Eye Safety Class I Laser Class IIIR
10
11. Table 3 Functional comparison between 3D Hardware- and Software- Reconstruction
Hardware Reconstruction Software Reconstruction
2D Layout Limited XY/YZ/XZ
3D Inspection Limited Good
Wreckage
Fracture Good Limited
Determination
Metallurgical
Good No
Inspection
On-scene
5~10 2~4
manpower
Construction
1-2 Hangers None
Area
Time (month) ~5 <3
break-up
Sequence Constrainted Portable
Demostration
Re-use No Yes
Ballistic
Trajectory No Coherent
Analysis
Break-up
No Coherent
Simulation
Finite Element
Limited Good (real model)
Analysis
CI611 Cost US$166,000 US$91,000
11
12. Fig. 1 Architecture of 3D software wreckage reconstruction and
presentation system
Fig. 2 3D scan model of 747-200 cargo aircraft, (a) inner model of rear area,
(b) outer model of front fuselage.
12
13. Fig. 3 Crane operational photo of item 640 and side-view of 3D model. Marks
of (A) and (B) are present as inner- and outer- side-view of 3D model.
Fig. 4 Crane operation photo of item 2136 and side-view of 3D model
13
14. Fig. 5 3D model of item 640 and reference frame model
Fatigue crack region
Fig. 6 Wreckage photo of item 640 and relevant station numbers
14
15. Fig 7 (a) “N” shape crack of item 640 located at station of 2160 (12.5 cm); (b)
SEM results of metal fatigue located at station 2100.
Fig. 8 Comparison of 2D layout and 3D software reconstruction at section 46
and aft pressure bulkhead (upside down, view from the right )
15