Testing method for unmanned plane flight-control structure modal coupling

A technology of structural mode and test method, which is applied in the field of flight control structural mode coupling test, can solve the problems that the aircraft state cannot be effectively determined, and the excitation signal cannot be injected, so as to avoid signal amplitude failure, reduce test items, and save manpower Effect

Inactive Publication Date: 2012-07-11
CHENGDU AIRCRAFT INDUSTRY GROUP
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Problems solved by technology

[0005] The task of the present invention is to propose a flight control structure modal coupling test method that can reduce test equipment and test items and save resources, and solve the problem that the excitation signal cannot be injected and the aircraft state cannot Effective determination, reasonable division of control loops, etc.

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  • Testing method for unmanned plane flight-control structure modal coupling
  • Testing method for unmanned plane flight-control structure modal coupling
  • Testing method for unmanned plane flight-control structure modal coupling

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Embodiment Construction

[0018] Refer to figure 1 . The following describes the specific implementation plan in conjunction with the modal coupling test of a certain type of UAV flight control structure. According to the results of the aircraft vibration test, through aero-servoelastic calculations, a reasonable aircraft three-channel (aircraft longitudinal, lateral, heading) structure notch filter is designed to prevent damage to the aircraft when the flight control structure is seriously coupled during the aircraft test.

[0019] According to the design of the flight control law and the longitudinal and lateral coupling of the aircraft, the aircraft longitudinal, lateral, and heading control channels are combined and divided to determine the specific test items; the flight control law should be clearly defined

[0020] Table 1 Test channel and test signal division

[0021]

[0022]

[0023] Compile special flight control and management software and comprehensive inspection vehicle software for flight cont...

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Abstract

The invention discloses a testing method for unmanned plane flight-control structure modal coupling, and aims at providing a flight-control structure modal coupling testing method which can save resources, so as to solve the problems that stimulation signals are not injected, states of a plane cannot be effectively confirmed, a control loop cannot be divided reasonably in a unmanned plane flight-control structure modal coupling test. The method is realized by following measures that: a flight-control computer is adopted to compile software which can automatically generate stimulation signals, the flight-control computer uses received comprehensive inspection vehicle signals to generate agreement stimulation signals and plane control surface stimulation signals which are used as input of the test, ground states and air states are divided according to flight configuration conditions, vibration sensors used for monitoring plane vibration conditions are arranged on the head of the plane, the wing tip ends of swings and the wing tip end of a V-shaped tail wing, and parameters of the vibration sensors can be directly monitored by an oscilloscope.

Description

Technical field [0001] The invention relates to a method for completing a modal coupling test of a flight control structure based on a flight control computer automatically generating an excitation signal, and is suitable for a UAV flight control structure modal coupling test. Background technique [0002] In the process of aircraft design, aero-servo elasticity may occur, including the coupling of aircraft structural dynamics, unsteady aerodynamic forces, and servo control systems containing sensors, stability enhancement control laws, and steering gears. This coupling is particularly serious for aircraft with superior performance such as low structural weight coefficient, large flight control system authority, and high relative flight speed. Aero-servo-elastic instability is different from flutter. It is closely related to the parameters of flight dynamic pressure and flight control law. This instability can occur in any state within the flight envelope, including the ground ro...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02
Inventor 余长贵张瞿辉王毅
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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