Research On Methods Of Attitude Control For Hypersonic Vehicle

With the potential military use of the near space, its value is increasinglyexcavated, hypersonic aircraft, especially hypersonic missile development, hasbecome the world’s military powers that each country is in desperate need to obtainto capture the high ground. Research about control strategies of the relevant field ofhypersonic control is carried out throughout all the countries around the world, andto varying degrees progress has been made. Currently, China is facing griminternational situation unprecedented in the history of our times, including securitychallenges of territory, airspace, territorial waters. In the foreseeable future, theinformation warfare will be calculated by the unit of second. There will be urgentneed for a country to have a high flight speed, large airspace combat radius, highpenetration rate, all-weather capability, a sharp sword to defend the motherland! Inthis paper, the attitude controller is designed for hypersonic missile flying in thenear space, including angle of attack feedback and overload feedback. Those twoattitude feedback controller are tested to verify their validity.Firstly, hypersonic missiles with conventional missiles were compared inperformance in this paper. Math model of the hypersonic missile in longitudinalchannel was built.Classical PID control method was used to design the overloadtracking controller. Through simulation analysis, it was shown that when using theaerodynamic control method only, steering engines rested in the saturation zone fora very long time and response of missile is show, and cannot meet the indexrequirements.Secondly, the lateral forces were introduced, and a combined control model oflateral thrust/aerodynamics was built for hypersonic missiles in the LongitudinalChannel. A Sliding mode control method was used to design the attitude control lawfor hypersonic missile. Using control method similar to that of the X43in UnitedStates, several control modes for longitudinal are studied: attack angle control andnormal overload control autopilot, two different modes.Finally, feedback tracking controller for angle of attack was designed, it couldachieve precise control of angle, and vivificated in several feature points. Compareswere made with the relevant results in the other papers. Then, aiming at the case ofoverload feedback tracking control, this treatise designed an attitude controller, andtested the controller for a couple of feature points to verify its effectiveness.