Start control moment online extraction method based on attitude angular velocity discrimination
An extraction method, attitude angle technology, applied in vehicle position/route/height control, non-electric variable control, control/regulation system and other directions, can solve complex flow field, interference and other problems
Pending Publication Date: 2020-11-17
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology
[0005] The technical problem to be solved by the present invention is how to reasonably determine the start-up time of the pitch-yaw circuit and the roll-off circuit when the aircraft is separated from the launcher or carrier, and how to start the control as soon as possible for the circuit with greater interference, and at the same time Reasonable allocation of rudder deviation resources to avoid aircraft instability
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[0043] A method for online extraction of control start time based on attitude angular velocity discrimination of the present invention will be further described in detail below in conjunction with the accompanying drawings.
[0044] Taking a roll-stabilized axisymmetric three-channel control aircraft as an example to illustrate this method, the control schematic diagrams of the three channels can be shown as follows: Figure 1-Figure 3 As shown, where ksf is the damping loop control parameter, km is the attitude control loop control parameter, g 2 is the damping loop control parameter of the rolling loop, g 3 is the control parameter of the roll loop attitude control loop.
[0045]The following describes the specific steps of online extraction of control start time. After control start, calculate the rudder deflection command online, drive the rudder surface deflection, apply control force and control torque, and stabilize the attitude of the missile.
[0046] 1. Initialize ...
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The invention discloses a start control moment online extraction method based on attitude angular velocity discrimination. The method comprises the following steps: (1) initializing start control moments of a pitching deviation loop and a rolling loop to be maximum values of allowable start control time; (2) filtering pitch, yaw and rolling loop attitude angular velocity signals measured by a gyroscope when the flight time is between the minimum value and the maximum value of the allowable start control time; (3) resolving the start control moment of the rolling loop in real time according tothe filtered rolling loop attitude angular velocity and a rolling loop damping loop control parameter g2; (4) calculating the start control moment of the pitching deviation loop in real time accordingto the filtered attitude angular velocity of the pitching and yawing loop, a control parameter ksf of the damping loop of the pitching deviation loop and the start control moment of the rolling loop;and (5) when the flight time reaches the maximum value of the allowable start control time, if the pitching deviation loop or the rolling loop is still not started, taking the maximum value of the allowable start control time as the start control moment of the pitching deviation loop or the rolling loop.
Description
technical field [0001] The invention belongs to the field of aircraft stability control, and in particular relates to an online extraction method for the start-up control time of a pitching circuit and a rolling circuit after the aircraft is separated in the air. The method is applicable to the online extraction method of the start-up control time after the aircraft is separated from the carrier or the launcher, or after the aircraft is separated from the booster. Background technique [0002] The stability control system is an important part of the aircraft. During the aircraft separation process, its function is to effectively suppress the initial attitude angular velocity interference and aerodynamic interference, stabilize the aircraft attitude, and ensure safe separation. [0003] During the separation process of the aircraft, due to the force of the separation mechanism, there is a disturbance in the initial attitude angular velocity; and the distance between the aircr...
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IPC IPC(8): G05D1/10
CPCG05D1/107Y02T90/00
Inventor 叶赛仙陈光山王蕾霍红梅彭一洋田野郑子元
Owner SHANGHAI AEROSPACE CONTROL TECH INST