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本文讨论气动力设计方面的考虑,以确定垂直发射的先进拦阻导弹的基本外形。所采用的设计方法是,先明确导弹的性能要求,其中包括导弹的速度、最小和最大拦截距离、机动性(平衡过载和弹体时间常数)及发射期间的转弯能力。作为设计考虑的例子,我们假定导弹以马赫数≈3.0的巡航速度在海面上空飞行,其最大和最小拦截距离分别为9.0和1.0海里,并要求导弹对付目标有超过50g的机动能力。这些要求一般是根据所对付的目标性能提出的。导弹的发射重量、有效负载(即导引电子设备、战斗部/引信))的重量及长度/体积,由弹箱的限制所确定。我们假设发动机系统的推力,足够用以按所要求的速度和过载,把有效负载送到所要求的距离上。基本弹体的选择基于空气动力上的综合考虑,需要的控制形式,加给导弹的物理约束、阻力和传感器的性能、升力面和控制面的优化、垂直发射及转弯的燃气舵控制、弹体的时间常数和导弹的基本性能等。
This article discusses aerodynamic design considerations to determine the basic profile of an advanced blocking missile that is vertically launched. The design approach adopted is to first define the missile’s performance requirements, including missile speed, minimum and maximum intercept distances, maneuverability (balance overload and projectile time constants), and cornering capability during launch. As an example of design considerations, we assume that a missile will fly above the sea at a cruise speed of Mach ≈3.0 with a maximum and minimum intercept distance of 9.0 and 1.0 nautical miles, respectively, and requires that the missile have a maneuver capability of over 50 g against the target. These requirements are generally based on the target performance to be addressed. The weight and length / volume of the missile’s launch weight, payload (ie, lead electronics, warhead / fuse)) are determined by the limitations of the tank. We assume that the thrust of the engine system is sufficient to deliver the payload to the required distance at the required speed and overload. The selection of the basic projectile is based on aerodynamic considerations, the type of control required, the physical constraints imposed on the missile, the performance of the drag and sensor, the optimization of the lift surface and control surface, the control of the vertical launching and turning of the gas rudder, The time constant and the basic performance of the missile.