METHOD OF CONTROL OVER FLIGHT SPEED OF ROCKET OF NORMAL AERODYNAMIC CONFIGURATION WITH X-CONFIGURATION OF FINS Russian patent published in 2014 - IPC F42B15/01 

FIELD: aircraft engineering.

SUBSTANCE: proposed method consists in measurement of current magnitudes of the path inclination angles θ, path angle ψ, bank angle γ, definition of said angles θ _pres, ψ_pres, γ_pres required for rocket guidance to target, definition of deviation of the path inclination angle Δθ _pres, path angle Δψ_pres, bank angle Δγ_pres from preset magnitudes and generation of speeds of fin deviation in rudder altitude channel $${\dot{\delta }}_a,$$ heading channel $${\dot{\delta }}_n,$$ and that of flaps $${\dot{\delta }}_f.$$ Control signal in channels $${\dot{\delta }}_a,$$ $${\dot{\delta }}_n,$$ $${\dot{\delta }}_f,$$ are summed to generate control signals for each of four X-configured fins $${\delta }_1^{sum},$$ $${\delta }_2^{sum},$$ $${\delta }_3^{sum},$$ $${\delta }_4^{sum}.$$ Rocket air speed V_a is measured and having air speed required for guidance V_{a pres}, departure from preset speed ΔV_{a pres}=V_a-V_{a pres}, is defined to generate extra signal of fins deflection in lengthwise speed channel $${\dot{\delta }}_{ls}.$$ Control signals for each of four X-configured fins $${\delta }_1^{sum},$$ $${\delta }_2^{sum},$$ $${\delta }_3^{sum},$$ $${\delta }_4^{sum}$$ are generated: at angle of attack larger than angle of slip, adjacent fins are synchronously displace on every side in pairs towards each other; at slip angle larger than angle of attack, adjacent fins are synchronously displace synchronously from above and from below towards each other to allow control of rocker air speed V_a.

EFFECT: higher efficiency.

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