Research On Impulse Orbital Maneuver Reachable Domain Method

The reachable domain for spacecraft reflects the orbital maneuver capability.It can provide feasibility criterion for orbit interception and on-orbit servicing mission.Based on the background mentioned above,this dissertation studies the computing methods of the interception for orbit interception as well as orbital rendezvous.In addition,it expands the field of application to apply interception reachable domain to deep space exploration mission.The primary research works in this dissertation are as follows:1.The computing methods of the space accessibility and the accessibility to target orbit of spacecraft are studied.First,based on the concept of space envelope,the computing method of the space reachable domain for spacecraft is derived.Then,the computing method of the hit area in the target orbit is further derived in combination with the target orbit.What’s more,the existence of the hit area is analyzed.The simulation results indicate that the computing method suggested is valid.What’s more,the point decided by the intersecting line between the initial orbital plane and the target one is a hit point consuming the least fuel.2.The computing method of the reachable domain for orbit interception mission with impulse thrust is studied.The reachable domain for orbit interception is representative target-oriented reachable domain.First,the definition of the reachable domain for orbit interception is expressed.Eight fundamental interception problems are solved after being put forward from generalized interception problem.At last,based on the scenario of coplanar maneuver and inverse interception,the computing method of the reachable domain for orbit interception is derived considering the energy,time and encounter angle constraints.The simulation results indicate that the computing method suggested is valid and it can be used to analyze the reachable domain for orbit interception in special missions.3.The computing method of the reachable domain for orbital rendezvous mission with impulse thrust is studied.Based on the definition of the reachable domain for orbital rendezvous,the interval of the rendezvous feasible solution under the energy constraint is derived in the coplanar circle orbital rendezvous mission with double impulse.The computing method of the reachable domain for orbital rendezvous is derived considering the energy,time,encounter angle and minimum perigee height constraints.The simulation results indicate that the computing method suggested is valid and it can be used to analyze the reachable domain for orbital rendezvous in special missions.4.The application of the accessibility of orbit interception in deep space exploration is studied.Based on patched conic technique and the computing method of the reachable domain for orbit interception,the projectile area and intercepting area in the near earth asteroid impact mission with a deep space impacter is analyzed.The simulation results indicate that the computing method suggested is valid and it can be used to analyze the reachable domain in the near earth asteroid impact mission.5.The computing method of the accessible probability of orbit interception under random error is studied.Based on the definition of the accessible probability of orbit interception,the accessible probability models of orbit interception under the maximum transfer ability and target orbit altitude error are analyzed.The simulation results indicate that the computing method suggested is valid and it can be used to analyze the accessible probability of orbit interception under the normal distribution random error.