A kind of control method of side slip and turn of aircraft
A technology of sideslip turning and control method, which is applied in the direction of control start method, adaptive control, general control system, etc. It can solve the problems of excessive risk and too conservative, and achieve the effect of improving accuracy and safety and reducing risk
Active Publication Date: 2015-12-23
CHINA ACAD OF LAUNCH VEHICLE TECH
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Correspondingly, using the side-slip angle command calculated without considering the coupling to constrain the side-slip turn control also deviates from reality, and the correspondingly designed side-slip turn control command tends to be either too risky or too conservative
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[0064] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:
[0065] The realization principle of the present invention is: firstly, in a given flight state, consider the control coupling of the three channels of pitch, roll and yaw, and the aerodynamic coupling of the aerodynamic rudder to the pitch channel to calculate the aerodynamic coupling stability ratio, and then calculate the aerodynamic coupling stability ratio according to the available rudder deviation of the aerodynamic rudder. Design the allowable range of the side slip angle command with the aerodynamic coupling control ratio, and finally generate the maneuver control command of the sideslip turn under the optimized allowable range of the side slip command. The specific implementation steps are as follows: figure 1 Shown:
[0066] (1) According to the aircraft roll aerodynamic moment coefficient C mx , Yaw aerodynamic moment coefficient C ...
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The invention discloses a sideslip turning control method for an aircraft. Aiming at the aircraft which is severe in manipulative coupling or aerodynamic coupling of pitching caused by a sideslip angle, the method comprises the following steps: firstly, calculating the controllability-stability ratio of the aerodynamic coupling by considering three-channel manipulative coupling and aerodynamic coupling of the pitching caused by an aerodynamic rudder to in a given flight state; secondly, designing an optimal sideslip angle instruction tolerance range according to the available rudder bias size of the aerodynamic rudder and the controllability-stability ratio of the aerodynamic coupling; finally, generating a sideslip turning maneuvering control instruction in the optimal sideslip angle instruction tolerance range. Compared with a conventional method, the sideslip turning control method has the advantage that the risk of the obtained sideslip turning maneuvering control instruction is small. Under the condition that the sideslip angle instruction tolerance range obtained through the conventional method is smaller than the sideslip angle instruction tolerance range obtained through the sideslip turning control method, the sideslip turning maneuvering control instruction obtained through the sideslip turning control method can fully utilize the controllability of the aircraft. Therefore, compared with the conventional method, the sideslip turning control method has the advantage that the accuracy and the safety of the sideslip turning control of the aircraft are improved.
Description
technical field [0001] The invention relates to an aircraft sideslip and turn control method, in particular to an aircraft sideslip and turn control method under the conditions of three-channel manipulation coupling and sideslip angle-to-pitch channel aerodynamic coupling, and belongs to the technical field of aircraft guidance and control. Background technique [0002] There are two basic methods for an aircraft in the atmosphere to perform turning maneuvers by relying on aerodynamic forces: one is banked turns, and the other is sideslip turns. The banked turn is to turn by turning the projectile (or airframe) relying on the lift force component, and its sideslip angle command is zero; while the sideslip turn is to turn by relying on the side force by generating a certain sideslip angle, and its sideslip angle command is not to zero. When performing a sideslip turn, how large the sideslip angle command can be is directly related to the control capability of the aircraft's ...
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IPC IPC(8): B64C13/16G05B13/04
Inventor 李争学黄世勇张振兴李杰奇解海鸥张永张旭辉
Owner CHINA ACAD OF LAUNCH VEHICLE TECH