Evaluation method for rapidity index of aircraft control system with strong aerodynamic nonlinear characteristics
A control system and aircraft technology, applied in general control systems, control/regulation systems, instruments, etc., can solve problems such as inaccurate rapidity assessment of control systems
Active Publication Date: 2021-10-15
SHANGHAI AEROSPACE CONTROL TECH INST
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[0004] In order to solve the problem that the small-disturbance linearized fixed-point simulation model is difficult to accurately evaluate the inaccurate evaluation of the rapidity of the control system under the strong nonlinear aerodynamic characteristics, the present invention provides a rapidity index evaluation method based on the full-parameter dynamic model of the aircraft, which can accurately evaluate Rapidity index of aircraft with strong nonlinear aerodynamic characteristics
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[0016] Hereinafter, the present invention will be further described in conjunction with the drawings and embodiments.
[0017] The steps to evaluate the rapidity index of the flight control system based on the three-channel full-parameter simulation model are as follows:
[0018] Based on CFD calculation data or wind tunnel test data, an unsteady mathematical model describing the six-degree-of-freedom motion of the aircraft can be established, which can reflect the change law of aerodynamic characteristics with the angle of attack, Mach number, and dynamic pressure, such as figure 1 shown.
[0019] Select the characteristic quantities that are strongly related to the aerodynamic characteristics of the aircraft, in this case, Mach number and altitude, as the basis for the division of characteristic states, and form a two-dimensional table as shown in Table 1, so that the strong nonlinear characteristics of the aircraft can be comprehensively and effectively assessed. In the di...
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The invention discloses a rapidity index evaluation method of an aircraft control system with strong aerodynamic nonlinear characteristics. The method provided by the present invention comprises: step 1, establishing the full parameter dynamics model of aircraft; Step 2, selecting several characteristic states; Step 3, setting the initial condition of simulation; Step 4, applying certain step instruction, assessing the performance of the control system Rapidity. The invention evaluates the rapidity index of the control system based on the full-parameter dynamic model of the aircraft, and solves the problem that the non-linear aerodynamic characteristics of the aircraft cannot be accurately described by the conventional small-disturbance linearization model, resulting in inaccurate evaluation of the rapidity of the control system.
Description
technical field [0001] The invention relates to an evaluation method of a rapidity index of an aircraft control system, which solves the problem that the conventional small-disturbance linearization model cannot accurately describe the non-linear aerodynamic characteristics of the aircraft. Background technique [0002] The rapidity of the domestic aircraft control system is designed and evaluated based on the small disturbance linearized fixed-point model. With the increase of the available angle of attack of the aircraft, the influence of aerodynamic nonlinearity becomes more and more obvious, which is reflected in the dynamic model describing the aircraft. is the static stability coefficient a 2 , Rudder efficiency coefficient a 3 , lift coefficient a 4 As the angle of attack changes significantly, even with a difference of more than 1 times under the large and small angles of attack, the small-disturbance linearized fixed-point simulation model cannot accurately reflec...
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IPC IPC(8): G05B17/02G06F30/20
CPCG05B17/02G06F30/367Y02T90/00
Inventor 奚勇冯昊廖幻年孙逊余帅先王璐朱成成
Owner SHANGHAI AEROSPACE CONTROL TECH INST