Study On Smart Morphing Missile Aerodynamic Configuration Conceptual Design

In the traditional mission of tactical cruise missile may be comprised of three distinct sections: long-range high-altitude cruise to maximize specific range outside of a threat environment, low-speed low-altitude loiter while remaining in threat area and attack the target. With the development of science,technology and anti-missile system, the cruise missile system is required to improve greatly as the modern fighting environment deteriorates increasingly. It requires cruise missile to fight with larger speed-range and full-space flight ability and it must be able to destroy the target before anti-missile system working. To satisfy such requests, an advanced cruised missile which is able to long-range high-altitude high-speed cruise to dangerous region and low-speed low-altitude loiter while remaining in threat area is needed to design.It is a challenge for conceptual design as the shape fixed missile is hardly to achieve the large speed-range and full-space flight ability. Compare with smart morphing missile which could morph configuration to adapt to different environment. This thesis study of the conceptual design of the smart morphing missile, and stability and maneuverability of the missile with different shape have been analyzed. The work is performed as follows:1. To design an excellent cruise missile configuration, built the missile body after aerodynamics, radar cross section, and cubage have been synthetically considered at first. Then, a morphing wing that used moving wing-box structure has been designed to adapt to obtain better flight performance. After that, finished the missile configuration design since the horizontal tail and vertical tail designed based on stability and overload demanded.2. In order to make sure that missile configurations could satisfy the mission requests, obtained the missile aerodynamics with different shape through the computational simulation, and established the aerodynamic mathematical model.3. Derived transfer functions in the pitch yaw and roll channel respectively and dynamic characteristics of missile have been analyzed.4. In the end of this thesis, a digital adaptive autopilot has been built and a six-degree of freedom mathematic simulation model has been established. A...