Research On Omnidistance Maneuvering Guidance Of Space-Based Reentry Vehicle

The space-based reentry vehicle which has characteristics of fast response,large-area maneuver, high-level penetration, precise strike, is able to reenter, returnand land, or strike enemy vital ground establishments precisely. The fly progress ofspace-based reentry vehicle is constituted of transition phase (including the rocketbreak phase and powerless glide phase) and reentry phase (including reentry phase,terminal guidance phase and load striking phase). The omnidistance maneuveringguidance of ground-strike reentry vehicle is studied this dissertation.The space-based reentry vehicle on orbit needs retropack to deorbit and reachan appropriate reentry point. In allusion to the finite thrust deorbit guidanceproblem, a kind of closed-loop real-time guidance method according to the breakingspeed was studied in this paper. Firstly presented the algorithm of the universalvariable problem solving gaussian and the Newton iterative algorithm consumingrequirement velocity to meet reentry conditions by the current state of vehicle,based on the above theory, gets the procedures of deorbiting guidance algorithm,and gives two kinds of correction guidance scheme considering perturbation.Vehicle reenters into atmosphere with a very high speed, with the problem offlinty heat, dynamical pressure and over loading. To make sure the prosperousaccomplishment of mission, the reentry guidance is very important. A newindependent reentry guidance method was designed based on dragacceleration-energy profile, this method can well satisfy all constraint requirements,and has higher precision and adaptability, at the same time, gives a kind of guidancestrategy considering no-fly zones and midway point, which can improve thevehicle’s mobile penetration ability.To maximizing the destroy effects, it is expected to minimize the miss distancewhen hitting the target with a gesture of appropriate perpendicularity. The presssection trajectory planning technology considering angle constrain was studied inthis paper, and presented adaptive terminal guidance law with attack angleconstraint, it is shown that the guidance law not only has higher guidance accuracy,but also can better meet the requirement of ballistic obliquity and scatters the heightby the release separation point. Through the research of the finite thrust deorbit guidance technique, thereentry guidance method based on drag acceleration-energy profile, and theadaptive terminal guidance law with attack angle constraint, this paper gives theomnidistance maneuvering guidance scheme of the space-based reentry vehicle, andhas some certain reference value to determine the overall scheme and to develop thekey technology of the space-based reentry vehicle.