The Experts below are selected from a list of 228 Experts worldwide ranked by ideXlab platform
R. Schroer - One of the best experts on this subject based on the ideXlab platform.
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electronic warfare a century of Powered Flight 1903 2003
IEEE Aerospace and Electronic Systems Magazine, 2003Co-Authors: R. SchroerAbstract:Electronic warfare (EW) is a term that includes a number of different electronic technologies for intelligence gathering and/or interfering with enemy operations. Electronic intelligence (ELINT), or eavesdropping, has been going on since the invention of the telephone and telegraph. Electronic countermeasures (ECM) deprive an enemy of the electronic spectrum by creating interference (jamming) that obscures their information or generates false information (spoofing). Electronic counter countermeasures (ECCM) is an effort designed to mitigate and overcome enemy ECM operations. ECM objectives include: search for signals in frequency, azimuth, and elevation; detect and identify radar signals via characteristics; and establish signal importance; commence appropriate countermeasures. It is only recently that these technologies have traditionally been categorized as EW, and are also referred to as electronic combat (EC). This section will focus on EW as it relates only to aviation.
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Aviation Radio [A century of Powered Flight 1903-2003]
IEEE Aerospace and Electronic Systems Magazine, 2003Co-Authors: R. SchroerAbstract:The following topics are dealt with: electron tubes; World War I efforts; post WWI radio advances; airmail; antenna developments; weather; and WWII and after.
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Cockpit Instruments [A century of Powered Flight:1903-2003]
IEEE Aerospace and Electronic Systems Magazine, 2003Co-Authors: R. SchroerAbstract:Since nearly the beginning airplanes were flown using only the stick or control column, rudder pedals, dials, and switches. There were as many control arrangements (sticks, wheels, and levers) as there were pioneer airmen. The 1903 Wright Flyer was far from conventional in many ways. Their only instruments were a stopwatch and prop revolution counter. Instruments were of little interest for about a decade after the Wright Brother's Flight. Just getting off and back onto the ground safely was the primary concern. Controls have evolved, but not changed as much as instrument displays. The stick/control column is beginning to be replaced by hand controllers in some fly-by-wire (FBW) aircraft (e.g., Airbus A-320 and up). Servo feedback provides the necessary hand controller "feel" as a function of the aerodynamic pressure expected on the control surface.
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Introduction [A century of Powered Flight:1903-2003]
IEEE Aerospace and Electronic Systems Magazine, 2003Co-Authors: R. SchroerAbstract:The term Avionics is used loosely to identify that electronic equipment necessary to fly an aircraft. The term is nearly 50 years old with origins in military electronics. With the increasing dependence of aviation on electronics the amount of equipment that falls into this category has skyrocketed. This issue is intended to commemorate the Wright Brothers' Centennial of Powered Flight. It emphasizes aviation-related electrical/electronic advances for the years 1903 to 1953. The following paragraphs highlight some of the major topics discussed in this special issue.
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Electric power. [A century of Powered Flight: 1903-2003]
IEEE Aerospace and Electronic Systems Magazine, 2003Co-Authors: R. SchroerAbstract:The following topics are dealt with: magnetos; batteries; starting and powering electric loads; WW II aircraft; distributed power; and tomorrow's airplanes.
Xinzhe Yin - One of the best experts on this subject based on the ideXlab platform.
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Dynamic modeling and stability analysis of a flexible spinning missile under thrust
International Journal of Mechanical Sciences, 2016Co-Authors: Ji-li Rong, Da-lin Xiang, Cheng-long Pan, Xinzhe YinAbstract:Abstract The general equations of motion of a flexible spinning missile under thrust in the Powered Flight phase are established and the stability of the motion of the missile is analyzed. The spinning missile is approximated to the unconstrained flexible rotor. Moreover, the thrust in the Powered Flight phase is deemed as a follower load when the factors of gyroscopic effect, aeroelastic effect, and axial force are considered under the mean axis condition. The equations of motion and stability of the flexible spinning missile in the Powered Flight phase are then deduced. The stability and dynamic response of the flexible spinning missile under thrust is analyzed through numerical calculation. Calculation results show that thrust, spinning speed, and dynamic pressure exert different influences on the stability of the spinning missile. These factors should be considered and analyzed comprehensively.
Frederick Serricchio - One of the best experts on this subject based on the ideXlab platform.
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Powered Flight Design and Performance Summary for the Mars Science Laboratory Mission
Journal of Spacecraft and Rockets, 2014Co-Authors: Steven W. Sell, Jody L. Davis, A. Miguel San Martin, Frederick SerricchioAbstract:The Powered Flight segment of Mars Science Laboratory’s Entry, Descent, and Landing system extends from backshell separation through landing. This segment is responsible for removing the final 0.1% of the kinetic energy dissipated during entry, descent, and landing and culminates with the successful touchdown of the rover on the surface of Mars. Powered descent overcame the many challenges that exist in the Powered Flight segment: extracting the Powered descent vehicle from the backshell, performing a 300 m divert maneuver to avoid collision with the backshell and parachute, slowing the descent from 85 m/s to 0.75 m/s successfully lowering the rover on a 7.5 m bridle beneath the rocket-Powered descent stage, and gently placing it on the surface using the sky crane maneuver. Finally, the nearly spent descent stage executed a flyaway maneuver to ensure surface impact at a safe distance from the rover. The Powered Flight segment’s execution resulted in Mars Science Laboratory’s successful touchdown on the ...
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Powered Flight Design and Reconstructed Performance Summary for the Mars Science Laboratory Mission
2013Co-Authors: Steven W. Sell, Jody L. Davis, Frederick Serricchio, Allen Y.k. Chen, Miguel San Martin, Gurkirpal SinghAbstract:The Powered Flight segment of Mars Science Laboratory's (MSL) Entry, Descent, and Landing (EDL) system extends from backshell separation through landing. This segment is responsible for removing the final 0.1% of the kinetic energy dissipated during EDL and culminating with the successful touchdown of the rover on the surface of Mars. Many challenges exist in the Powered Flight segment: extraction of Powered Descent Vehicle from the backshell, performing a 300m divert maneuver to avoid the backshell and parachute, slowing the descent from 85 m/s to 0.75 m/s and successfully lowering the rover on a 7.5m bridle beneath the rocket-Powered Descent Stage and gently placing it on the surface using the Sky Crane Maneuver. Finally, the nearly-spent Descent Stage must execute a Flyaway maneuver to ensure surface impact a safe distance from the Rover. This paper provides an overview of the Powered Flight design, key features, and event timeline. It also summarizes Curiosity's as flown performance on the night of August 5th as reconstructed by the Flight team.
Steven W. Sell - One of the best experts on this subject based on the ideXlab platform.
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Powered Flight Design and Performance Summary for the Mars Science Laboratory Mission
Journal of Spacecraft and Rockets, 2014Co-Authors: Steven W. Sell, Jody L. Davis, A. Miguel San Martin, Frederick SerricchioAbstract:The Powered Flight segment of Mars Science Laboratory’s Entry, Descent, and Landing system extends from backshell separation through landing. This segment is responsible for removing the final 0.1% of the kinetic energy dissipated during entry, descent, and landing and culminates with the successful touchdown of the rover on the surface of Mars. Powered descent overcame the many challenges that exist in the Powered Flight segment: extracting the Powered descent vehicle from the backshell, performing a 300 m divert maneuver to avoid collision with the backshell and parachute, slowing the descent from 85 m/s to 0.75 m/s successfully lowering the rover on a 7.5 m bridle beneath the rocket-Powered descent stage, and gently placing it on the surface using the sky crane maneuver. Finally, the nearly spent descent stage executed a flyaway maneuver to ensure surface impact at a safe distance from the rover. The Powered Flight segment’s execution resulted in Mars Science Laboratory’s successful touchdown on the ...
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Powered Flight Design and Reconstructed Performance Summary for the Mars Science Laboratory Mission
2013Co-Authors: Steven W. Sell, Jody L. Davis, Frederick Serricchio, Allen Y.k. Chen, Miguel San Martin, Gurkirpal SinghAbstract:The Powered Flight segment of Mars Science Laboratory's (MSL) Entry, Descent, and Landing (EDL) system extends from backshell separation through landing. This segment is responsible for removing the final 0.1% of the kinetic energy dissipated during EDL and culminating with the successful touchdown of the rover on the surface of Mars. Many challenges exist in the Powered Flight segment: extraction of Powered Descent Vehicle from the backshell, performing a 300m divert maneuver to avoid the backshell and parachute, slowing the descent from 85 m/s to 0.75 m/s and successfully lowering the rover on a 7.5m bridle beneath the rocket-Powered Descent Stage and gently placing it on the surface using the Sky Crane Maneuver. Finally, the nearly-spent Descent Stage must execute a Flyaway maneuver to ensure surface impact a safe distance from the Rover. This paper provides an overview of the Powered Flight design, key features, and event timeline. It also summarizes Curiosity's as flown performance on the night of August 5th as reconstructed by the Flight team.
Ji-li Rong - One of the best experts on this subject based on the ideXlab platform.
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Dynamic modeling and stability analysis of a flexible spinning missile under thrust
International Journal of Mechanical Sciences, 2016Co-Authors: Ji-li Rong, Da-lin Xiang, Cheng-long Pan, Xinzhe YinAbstract:Abstract The general equations of motion of a flexible spinning missile under thrust in the Powered Flight phase are established and the stability of the motion of the missile is analyzed. The spinning missile is approximated to the unconstrained flexible rotor. Moreover, the thrust in the Powered Flight phase is deemed as a follower load when the factors of gyroscopic effect, aeroelastic effect, and axial force are considered under the mean axis condition. The equations of motion and stability of the flexible spinning missile in the Powered Flight phase are then deduced. The stability and dynamic response of the flexible spinning missile under thrust is analyzed through numerical calculation. Calculation results show that thrust, spinning speed, and dynamic pressure exert different influences on the stability of the spinning missile. These factors should be considered and analyzed comprehensively.
