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为保持飞行器在稀薄大气中的机动性,通常采用喷流反控制作用(RCS),但在超声速来流中,这会导致飞行器表面出现复杂的喷流干扰流场,对飞行控制造成了巨大影响。为提高对超声速条件下的侧向喷流控制作用的规律性认识,应用数值模拟方法,研究了超声速条件下的无舵光滑弹体和带尾舵的弹-翼组合体上的声速侧向喷流控制问题。开展了关于喷口布局对侧向喷流控制效果影响规律的研究工作,并通过引入法向干扰力沿程增长系数从定量角度加以分析。计算结果表明:在有尾舵的情况下,喷口位置的后移和马赫数的增加能够显著增强侧向喷流控制效果;当喷口位置位于舵面之前时,喷流干扰力放大系数随迎角增大而增大,随来流静压增大而减小;当喷流位置后移至舵面之后时,规律相反;在某些喷口位置和来流条件下,弹-翼组合体的侧向控制效果与无舵光滑弹体相比并不具备优势。
In order to keep the aircraft maneuverable in a lean atmosphere, jet anti-control (RCS) is usually used, but in the supersonic flow, this will lead to complex jets disturbing the flow field on the surface of the aircraft, which has a great impact on the flight control . In order to improve the regularity of lateral jet control under supersonic velocity, a numerical simulation method was applied to study the effects of supersonic speed on the velocity of unsprung mass Flow control issues. The research work on the influence of nozzle layout on lateral jet control was carried out and analyzed quantitatively by introducing the growth coefficient of normal disturbance along the process. The calculation results show that the backward jetting and Mach number increase can significantly enhance the control effect of lateral jet when there is a tail rudder. When the jet position is before the rudder, the amplification factor of jet interference force increases with the angle of attack Increases and then increases with increasing hydrostatic pressure and decreases; when the jet position after the move to the rudder surface, the opposite; in some jet position and incoming flow conditions, the elastic - wing assembly side To the control effect and non-helm smooth body does not have the advantage.