Aircraft attitude control method, aircraft attitude control system and aircraft
An attitude control and aircraft technology, applied in the field of aircraft, can solve the problem that the anti-shock requirement and the minimum working time requirement cannot be fully considered.
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Embodiment 1
[0089] In this embodiment, an aircraft attitude control method is provided, such as figure 1 As shown, the method includes:
[0090] Step 101, sampling switch control quantities corresponding to multiple target channels of the aircraft at preset intervals, wherein the switch control quantities are determined based on the angle deviation correction value of the target channel of the aircraft;
[0091] Step 102, obtaining the control quantity correction strategy of each target channel respectively, wherein the control quantity correction strategy includes the shortest working time strategy and the anti-shock strategy;
[0092] Step 103, according to the control amount correction strategy, calculate the control value of each target channel at the current sampling time through the target switch control amount at the current sampling time and multiple historical correction values of the switch control amount before the current sampling time Quantity correction value;
[0093] S...
example 1
[0139] Set the pitch, yaw and roll channel initial switch control value p y0 ,p z0 and p x0 ,See image 3 , the output value p calculated by the minimum working time of the attitude control engine and the coupling design method of the anti-shock strategy y ,p z ,p x See Figure 4 .
example 2
[0141] Set the pitch, yaw and roll channel initial switch control value p y0 ,p z0 and p x0 ,See Figure 5 , the output value p calculated by the minimum working time of the attitude control engine and the coupling design method of the anti-shock strategy y ,p z ,p x See Image 6 .
[0142] According to the minimum working time of the attitude control engine and the anti-shock coupling design algorithm input p in verification example 1 and verification example 2 y0 ,p z0 ,p x0 and calculate the output p y ,p z ,p x As can be seen from the analysis results, based on the minimum working time of the attitude control engine proposed by the present invention and the anti-shock coupling design method, the p y ,p z ,p x Fully meet the minimum working time requirements of the attitude control engine and anti-shock requirements, and the algorithm logic is easy to implement without algebraic loops, and has the conditions for engineering applications.
[0143] Further, the...
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