When designing the door mechanism of a civil aircraft, in order to meet the availability clauses and operating requirements, the handle force of the aircraft door during opening or closing process is an important indi...
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ISBN:
(数字)9798350352252
ISBN:
(纸本)9798350352269
When designing the door mechanism of a civil aircraft, in order to meet the availability clauses and operating requirements, the handle force of the aircraft door during opening or closing process is an important indicator that needs to be considered. Taking a typical door as an example, a skeleton model of the door mechanism is introduced in this paper. A dynamics model of the door mechanism is proposed based on multi-body dynamics software ADAMS, and the analytic algorithm of handle force is given. The accuracy of the ADAMS model is verified through comparing with the analytic algorithm. Based on the ADAMS dynamic model, the handle forces of the door mechanism in the process of opening and closing are calculated, and the contribution of the door gravity, the torque rod of the booster mechanism, the seals and the friction of the mechanism to the handle force is analyzed. Besides, the influence of torsion bar and seal parameters on the opening and closing handle forces is studied. The results can provide reference for the design of the door mechanism and the analysis of the handle force.
Resurrecting the legacy Inner Loop Thrust Vectoring research flight controller to investigate the tail shock region brought unique challenges. This report documents these challenges and lessons learned from a stabilit...
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ISBN:
(纸本)9781600867392
Resurrecting the legacy Inner Loop Thrust Vectoring research flight controller to investigate the tail shock region brought unique challenges. This report documents these challenges and lessons learned from a stability and controls perspective. The flight test approach for flight envelope expansion and probing tests, as well as limited flight test results, are presented. Recent advances in sonic boom reduction technology have contributed to a resurgent interest in civilian supersonic cruise flight. These advances have focused only on fore body shaping, however, and little, if any, experimental flight data are available to develop and validate design tools for the tail shock region. In January of 2009, the NASA Dryden flight Research Center completed research flights to investigate the tail shock region of a highly modified F-15 aircraft by probing the shock waves around it, using another F-15 aircraft. To adjust the lift distribution and plume shape, a decade-old research flight controller from the Inner Loop Thrust Vectoring project was required. To investigate the tail shock region, the lift distribution was changed by adjusting the canard position, and the plume shape was changed by adjusting the nozzle area and thrust vectoring.
A value-centric system design tool has been developed as part of the DARPA F6 (Future Fast, Flexible, Fractionated, Free-Flying Spacecraft united by Information eXchange) Phase 1 architecture studies. This System Valu...
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As computer computational power has increased, the level of fidelity of flight simulators has increased along with it. This increased fidelity has provided for better flight test rehearsals for the test pilot but has ...
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A novel method for designing notch filters to attenuate structural responses that show significant cross-coupling (between axes) is presented. This approach differs from the conventional methods in that it is a single...
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McDonnell Douglas Helicopter Company recently undertook a study to determine the actual simulator hardware time delay in all the simulators. It also investigated the effect of time delay on pilot performance and his a...
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