飞机飞行载荷校准试验约束补偿技术

doi:10.7527/S1000-6893.2023.27500

Abstract

Abstract:

To solve the problem that the loads on the aircraft restraint device go beyond its limit of the landing gear under the serious load conditions in a particular aircraft loads calibration test， the design theory of constraint compensation is studied. A longitudinal and lateral-directional balance engineering model for aircraft is established based on mechanical analysis， and the relationship function between the constraint compensation and the calibration loads is derived. According to the structural characteristics of the aircraft， a constraint compensation scheme which can realize the dynamic balance of the whole aircraft during the test， and implementation control techniques are proposed， which can effectively correct the nonlinear errors in dynamic loading， component deformation and loading equipment installation deviation during loads calibration tests. By the implementation of aircraft loads calibration test， the scientific nature of the constraint compensation is verified. The results show that the constraint compensation can be used to realize the dynamic balance of the aircraft during loads calibration test and keep the variations of the 3-way loads on the passive restraint device of the landing gear within 5%， thus effectively reducing the risks of the calibration test.

Key words: flight loads, load calibration test, aircraft constraint, constraint compensation, aircraft balance

CLC Number:

V217⁺.32

Jianhu YU. Constraint compensation technology on aircraft loads calibration test[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(19): 227500-227500.

Figures/Tables 8

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References 21

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部件	加载方式	作用点	方向	大小/%DLL
平尾	两侧对称	16点组合	向下	41
垂尾	单侧加载	8点组合	向左	37

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Constraint compensation technology on aircraft loads calibration test

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