DYNAMIC RESPONSE OF AIRCRAFT TO PAVEMENT UNEVENNESS
1978; The MIT Press; Issue: 175 Linguagem: Inglês
ISSN
0360-859X
Autores Tópico(s)Simulation and Modeling Applications
ResumoA computer program was developed to simulate aircraft dynamic response to runway roughness during taxiing and takeoff. The mathematical model has rigid-body degrees of freedom of pitch, roll, and vertical and horizontal translation and up to 30 flexible modes of vibration. Runway profile data measured at approximately 0.61-m (2-ft) intervals is input into the program and used as the model forcing function. A different profile is encountered by each landing gear. All the necessary landing-gear and airplane data were collected for the following aircraft: Boeing--KC-135; B-52C,G,H; T-43 (737); AMST Comp (YC-14); 727-100; 727-200; 707-320; and 747; McDonnell Douglas--AMST Comp (YC-15); C-9A,B;DC-8-63; DC-9-40; DC-10-10; and RF-4C; Lockheed--C-130E; C-5A; C-141; and L-1011; and other--F-111A; A-37; and CT-39. Each of these aircraft was simulated; a comparison of the responses of several different military aircraft showed that the simulated accelerations at the pilot stations were within 5 to 10 percent of the measured values. Typical computer run times were less than 60 s on a CDC 6600. The intended purpose of the program was to locate the rough areas of a runway by using plus or minus 0.4g as a limiting vertical acceleration. Additional useful applications of the program are (a) analysis of pavement dynamic loading; (b) runway repair evalution; (c) evaluation of the dynamic response of new aircraft, such as the Concorde and supersonic transport, on a given runway profile; and (d) the performance of aircraft parametric studies, such as that of the high preload-pressure, nose landing-gear strut, to determine methods for reducing aircraft ground loads. /Author/
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