基于超静定配平的机动载荷控制风洞试验

doi:10.7527/S1000-6893.2016.0282

Abstract

Abstract:

Pitching maneuver load alleviation (MLA) is demonstrated on the scale-down wind-tunnel test model of a generic transport aircraft. The objective of the research is to develop an approach for maneuver load control based on overdetermined trim theory via wind-tunnel test. The longitudinal overdetermined trim method for the test model is studied and the fundamental of alleviating the maneuver load by this method is revealed theoretically. The MLA control law is then designed based on the overdetermined trim theory, which utilizes equivalent normal acceleration feedback to deflect aileron and elevator to alleviate wing load and maintain pitch maneuver performance of the test model respectively. The overdetermined trim experiment, aeroservoelastic stability experiment as well as the maneuver load alleviation experiment are implemented in sequence to determine the MLA control law parameters, check the stability of the control system and obtain the system response during pitching maneuver, respectively. The experiment results indicate:when MLA control law functions, the incremental wing root bending moment decreases by more than 10%, compared with that without MLA control law; while the pitch maneuver performance remains almost unchanged; introduction of the MLA control law results in slight decrease of stability of the control augmentation system; the approach of determining MLA control parameters by overdetermined trim experiment effectively improves the reliability of MLA control design, making the amount of reduced wing root bending moment close to the target value. This investigation can provide a feasible approach for MLA control design and test of generic transport aircrafts.

Key words: maneuver load alleviation, generic transport aircraft, wind-tunnel test, overdetermined trim, pitch maneuver performance, wing root bending moment, control law design

CLC Number:

V215.3

ZENG Xian'ang, PU Lidong, LI Junjie, TAN Shen'gang, XIE Huaiqiang. Wind-tunnel test of maneuver load control based overdetermined trim[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(5): 120596-120596.

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Wind-tunnel test of maneuver load control based overdetermined trim

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