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符号说明α导弹攻角β导弹侧滑角ψ偏航角φ航向角γ滚动角δ_y沿偏航方向的舵偏角δ_x沿滚动方向的舵偏角V导弹的飞行速度m导弹的质量a_z横向加速度I_x(I_y)弹体沿x(y)轴方向的转动惯量F_k由k引起的侧向力系数k=β,δ_x,δ_yM_i~j 由i引起的沿j方向的力矩系数i=β,ψ,δ_x,δ_y,γj= x,ya,b,c,d气动系数A,B,D系数矩阵K反馈矩阵e误差量一、大攻角飞行的气动交链随着飞行目标速度的增加,要求地空导弹显著地增加机动性能和提高制导精度。对于用气动力控制的导弹,为了提高在高空低动压飞行的机动过载,需要增加导弹飞行的攻角;而在大攻角飞行时,导弹将产生明显的气动交链影响,因而给自动驾驶仪的设计造成困难。
REFERENCE SIGNS LIST α missile attack angle β missile side slip angle ψ yaw angle φ heading angle γ rolling angle δ_y rudder deflection angle in yaw direction δ_x rudder deflection angle in rolling direction V missile flight speed m missile mass a_z lateral acceleration I_x (I_y) Moment of inertia along the x (y) axis of the projectile F_k Lateral force coefficient due to k k = β, δ_x, δ_yM_i ~ j Torque coefficient in j direction caused by i i = β, δ_x, δ_y, γj = x, ya, b, c, d Pneumatic coefficient A, B, D Coefficient matrix K Feedback matrix e Error amount a. Air linkage at a high angle of attack As the target speed of flight increases, Air missiles significantly increase maneuverability and improve guidance accuracy. For aerodynamically-controlled missiles, in order to increase the maneuvering overload at high altitude and low-pressure flight, it is necessary to increase the attack angle of the missile; at the high-angle of attack, the missile will have obvious aerodynamic interlinkage effects, thus giving automatic driving Instrument design caused difficulties.