Reanalysis method for angular motion of rotary aircraft controlled by a pair of canard rudders
A complex analysis, aircraft technology, applied in the control/regulation system, non-electric variable control, 3D position/channel control and other directions, can solve the problem that it is difficult to obtain the analytical solution of the aircraft angular motion model, the complex analysis method cannot, and the single-channel control rotation Research on the stability of the conical motion of the aircraft, etc., to achieve the effect of accurate aerodynamic force and aerodynamic torque
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experiment example 1
[0081] When the rotary aircraft with a pair of canard rudders has no deflection on the rudder surface, its rotational speed is set to 60rad / s, and the analytical expression in formula (1) given in this application is used for simulation.
[0082]
[0083] where, ξ=β * +iα* ,
[0084]
[0085]
[0086]
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[0088]
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[0090] m=18.5051 kg, Δxc=0.3790 m, Δyc=0.1859 m,
[0091] ρ=1.2266 kg·m -3 , V=170.0784 m s -1 , C MQ =-151.91, C NPA =-12.8,
[0092] C NAC = 0.4875, C NA =5.815, μ=2.07, L=0.1047, J 1 =0.0332,J 2 = 0.6992.
[0093] The curve of the angle of attack versus time is obtained as figure 2 As shown in , the curve of sideslip angle changing with time is as follows Figure 4 Correspondingly, through the wind tunnel experiment, the real angle change curve of the same rotating aircraft is given when the rudder surface is not deflected and the speed is 60rad / s. The change curve of the angle of attack with time is as follows ...
experiment example 2
[0096] Select the same aircraft as in Experimental Example 1, control its upper steering surface deflection angle δ=5°, set its speed to 60rad / s, and use the analytical expression in formula (2) given in this application to perform simulation.
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[0098] in,
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[0100]
[0101]
[0102] The curve of the angle of attack versus time is obtained as Figure 6 As shown in , the curve of sideslip angle changing with time is as follows Figure 8 Correspondingly, through the wind tunnel experiment, the real angle change curve of the same rotating aircraft is given when the rudder surface is deflected by 5° and the speed is 60rad / s. The time change curve of the attack angle is as follows Figure 7 As shown in , the curve of sideslip angle changing with time is as follows Figure 9 shown in .
[0103] according to Figure 6 to Figure 9 It can be seen that when the rudder surface is deflected by a fixed angle, the analysis given in this application can acc...
experiment example 3
[0105] Select the same aircraft as in Experimental Example 1, and control the maximum deflection angle δ of the sinusoidal deflection of the upper rudder surface max =10°, control frequency k=p, set its rotational speed as 60rad / s, and use the analytical expression in formula (3) given in this application for simulation.
[0106]
[0107] in,
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[0110]
[0111] The curve of the angle of attack versus time is obtained as Figure 10 As shown in , the curve of sideslip angle changing with time is as follows Figure 12 Correspondingly, through the wind tunnel experiment, given the sinusoidal deflection of the same rotating aircraft, the maximum deflection angle δ max =10°, the control frequency k=p, and the real angle variation curve when the speed is 60rad / s, the variation curve of the angle of attack with time is as follows Figure 11 As shown in , the curve of sideslip angle changing with time is as follows Figure 13 shown in .
[0112] acco...
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