Key Technologies Of Long-range Hypersonic Air-to-ship Missiles

Aiming at the medium-range and long-distance high supersonic missile's key technology, this dissertation emphasizes particularly on a high supersonic air-ship missile's guidance and control problems, including the quotation and improvement of a singular perturbation midcourse guidance law, the analysis about the combination of inertia navigation and double star orientation and the compound guidance system of SINS/active and passive guidance head, which solve some sixty-four-dollar questions, and receive good result. The major contributions of the dissertation are as follows.1. Taking the advantage of the conclusion on the most excellent problem of two restrains in the nonlinear singular perturbed systems, through analyzing the two-time-scale behavior of point-mass equation for missiles, the paper introduce a closed loop's design method of singular perturbed optimum midcourse guidance and control law, Finally this method is applied to a high supersonic cruise missile to imitate the three dimension trajectory, which receives a good result.2. A midcourse guidance law is presented based on the other method of dividing time-scale of point-mass equation for missiles. After the guidance law is revised, the paper puts forward a new singular perturbed optimum midcourse guidance and control law that ascents and descends more quickly. The imitation shows that the improved midcourse guidance law is more fit for high supersonic cruise missile.3. This paper discusses the indispensability and the feasibility of the combination of inertia navigation and double star orientation, then it puts forward some major problems and some possible solutions in this combinatioa The research shows that the combination system has expansive development space.4. The dissertation puts forward a compound guidance and control technology adopting SINS and guidance head, midcourse guidance method adopts compound guidance of SINS and passive guidance, passive guidance head measures angle between missile and target to rectify missile's deviation, terminal control method is compound guidance of SINS and active guidance, active guidance head measures angle and velocity between missile and target, missiles have control instructions in the whole flight process. A feasible compound method is presented for high supersonic cruise missiles and requirement of original precision is reduced.