This paper deals with the study and comparison of the dynamic response of aircraft with passive and active landing gears due to runway irregularities while the aircraft is taxying. This paper develops a detailed full aircraft mathematical vibration model to describe an active landing gear system. The derived dynamic equations are used to analyze the active landing gear system using proportional integral derivative (PID) controllers. The performance of this system is compared with the passive landing gear system by numerical simulations. The active landing gear system is able to increase the ride comfort and good track holding by reducing the fuselage acceleration, vertical fuselage displacement caused by landing and runway excitations.
BenderEKBeiberM (1971) A feasibility study of active landing gear. AFFDL Technical Report-70-126, U.S.. Airforce (available as AD 887451L).
2.
Catt T, Cowling D and Shepard A (1993) Active landing gear control for improved ride quality during ground roll, AGARD Smart structures for aircraft and spacecraft, Conference Proceedings-531, Stirling Dynamics Ltd, Bristol.
Freymann R and Johnson W (1985) Simulation of aircraft taxi testing on the AGILE Shaker Test Facility, Second International Symposium on Aero elasticity and Structural Dynamics sponsored by Deutsche Gesellschaft fur Lufund Raumfahrt e.V.in Aachen, W.Germany, April 1–3.
9.
GiuaAMelasMSeatzuC (2004) Design of predictive semi active suspension system. Vehicle Systems Dynamics41(4): 277–300.
10.
GoodallRM (1983) Active controls in ground transportation – a review of the state-of-the-art and future potential. Vehicle Systems Dynamics12(4): 225–257.
11.
Griffin MJ, McLeod RW, Maseley MJ, et al. (1986) Whole body vibration and aircrew performance. Institute of Sound and Vibration Research, Technical Report-132, University of Southampton, Southampton, England.
12.
HacA (1985) Suspension optimation of a 2-dof vehicle model using a stochastic optimal control technique. Journal of Sound and Vibration100(3): 347–357.
13.
HaitaoWangXingJTPriceWG (2008) An investigation of an active landing gear system to reduce aircraft vibrations caused by landing impacts and runway excitations. Journal of Sound and Vibration317: 50–66.
14.
HortaLGDaughertyRHMartinsonVJ (1999) Modeling and validation of an A6-Intruder actively controlled landing gear system. NASA TP-1999-209124.
15.
Howell WE, McGehee JR, Daugherty RH, et al (1991) F-106B airplane active control landing drop test performance, Landing Gear Design Loads Conference No. 21, AGARD Conference Proceedings-484, Povoa dc Varzim, Portugal, October 8–12.
16.
ISO 2631-1 (1997) Mechanical Vibration and Shock – Evaluation of Human Exposure to Whole Body Vibration. Part 1: General Requirements. Geneva: International Standards Organization.
17.
KarnoppD (1983) Active damping in road vehicle suspension system. Vehicle Systems Dynamics12(6): 291–316.
18.
McGeheeJRGardenHD (1979) Analytical investigation of the landing dynamics of a large airplane with a load-control system in the main landing gear. NASA Technical Paper 1555.
19.
RossIEdsonR (1982) Application of active control landing gear technology to the A-10 aircraft. NASA CR-166104.
Sheperd A, Catt T and Cowling D (1992) The simulation of aircraft landing gear dynamics, 18th Congress of the International Council of the Aeronautical Sciences, Beijing, China, September 20–25, ICAS-92-1.7.1.
22.
ShinnersSM (1964) Control System Design, NewYork: Wiley.
23.
Simulink (1997) Dynamic system simulation for MATLAB, version 2- using Simulink, The Math Works Inc.
24.
Wignot Jack E, Durup Paul C, Gamon et al. (1971) Design formulation and analysis of an active landing gear. AFFDL-Technical report 1: 71–80.
25.
ZhangLJLeeCMWangYS (2002) A study on non stationary random vibration of a vehicle in time. International Journal of Automotive Technology3(3): 101–109.
