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本文论述了垂直发射拦截导弹的气动力外形设计问題。采用的设计方法是用于初步确定导弹的性能,包括导弹速度,最小和最大拦截距离。机动性(或者说平衡过载和弹体时间常数)和发射段的拐弯能力。作为一个例子,所分析的导弹的速度在海平面为M≈3马赫,最小和最大拦截距离分别为1海里和9海里。同时为了能对付入侵目标,它的机动能力应该大于50g。这些要求通常可以根据要对付的威胁范围来确定。导弹的发射重量,有效载荷(即制导设备,战斗部和引信)的重量,长度和体积应考虑发射筒的限制。假设推进系统提供的推力能够把有效载荷送到要求的射程并达到足够的速度和机动能力。通过对下列一些问題的气动力分析来确定导弹的气动外形,它们是:控制类型,对导弹的物理限制,阻力和制导传感器的性能,升力和控制面的优化,用于垂直发射和拐弯的燃气舵控制,弹体时间常数和导弹的性能。
This article discusses the design of the aerodynamic shape of a vertical launch interceptor missile. The design methodology used was to initially determine the missile’s capabilities, including missile speed, minimum and maximum intercept distances. Maneuverability (or balance of overload and projectile time constants) and launch segment turnability. As an example, the missile analyzed has a M 3 3 Mach speed at sea level and a minimum and maximum interception distance of 1 nm and 9 nm respectively. At the same time in order to deal with the invasion of the target, its mobility should be greater than 50g. These requirements are usually determined by the scope of the threat to be dealt with. The launch weight, the payload, ie the weight, length and volume of payloads (ie, guidance equipment, warhead and fuze), should take into account the limits of the launch tube. Suppose the propulsion provided by the propulsion system can deliver the payload to the required range and achieve sufficient speed and maneuverability. The aerodynamic profile of the missile is determined by aerodynamic analysis of the following issues: control type, physical limitations on the missile, resistance and performance of the guidance sensor, optimization of lift and control surfaces, gas for vertical launch and turn Rudder control, missile body time constant and missile performance.