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本文论述了垂直发射先进拦截导弹(VLAIM)的空气动力设计依据,给出导弹基本外形的设计方法.这个方法可初步确定导弹的性能指标,这些性能指标包括:导弹速度、最小和最大拦截距离、机动性(用平衡过载g和弹体的时间常数来表达)以及发射期间的转弯能力.作为设计例子,考虑导弹在海平面上的续航速度M≈3.0,最大射程为9海里,最小射程为1海里,摧毁目标所需的机动能力超过50g.这些指标通常按预定的威胁范围提出.发射重量、有效载荷(即制导电子设备、战斗部/引信)重量和长度/体积均由导弹装运箱尺寸来确定.假定推进系统的推力足以使导弹获得所要求的射程、速度和过载能力,则导弹基本外形的选择依赖于对以下空气动力因素的综合考虑:需用的控制型式、导弹的物理限制、阻力、制导系统的敏感元件性能、升力面和控制面的最佳选配、垂直发射和转弯的燃气舵控制、弹体的时间常数以及导弹的基本性能等.
This paper discusses the aerodynamic design basis of VLAIM and gives the design method of the missile’s basic shape.This method can initially determine the performance of the missile, including the missile velocity, the minimum and maximum intercept distance, Mobility (expressed in terms of equilibrium over time g and time constant of the projectile), as well as the turning ability during launch As a design example, consider the missile’s cruising speed at sea level M ≈ 3.0, a maximum range of 9 knots and a minimum range of 1 Nautical miles, the maneuverability required to destroy a target is more than 50g. These indicators are usually based on a predetermined range of threats. The launch weight, payload (ie, pilot electronics, warhead / fuse) weight and length / Assuming that the thrust of the propulsion system is sufficient to achieve the desired range, velocity and overload capability of the missile, the choice of missile’s basic shape will depend on a combination of the following aerodynamic considerations: the type of control required, the physical limitations of the missile, the resistance , The performance of the guidance system’s sensitive components, the optimal matching of the lifting surface and control surface, the vertical firing and turning of the combustion Gas rudder control, the time constant of the projectile and the basic performance of the missile.