Mission Plan Of Active Debris Removal And Design Of Guidance And Control Techniques Applying Space Maneuver Vehicle

Active Debris Removal（ADR）is an essential technology to stabilize the space environment,to improve the capability of on-orbit service and to insure the space security.With the challenge of large size debris,increasing quantity uncertain motion and tumbling motion,the application of Space Maneuver Vehicle（SMV）in multi debris removal and disposal is investigated in this thesis,then the guidance and control system is designed for autonomous rendezvous.1.The mission plan of multi debris removal is studied in the thesis.Mission plan of multi debris removal includes mission parameter configuration and orbit plan.This thesis proposed the model of two-level mixed interger scheme to solve the programming problem of multi debris removal.The upper level solves the ADR sequence problem including the order,transfer time and operation time.The lower level solves the orbit maneuvering time which is actually the orbit optimization problem considering the J₂ pertubation.In the simulation part,besides the single objective optimization problem,the multi objective optimization problem is also conducted which give the pareto front of fuel consumption and mission time,which demonstrates the effectiveness of proposed algorithm.Finally,an example with four real CZ debris is given,and the feasibility of proposed scheme is verified.2.Augmented proportional navigation（APN）is proposed for autonomous rendezvous guidance.A three-dimensional kinematic equation set is constructed in a rotating coordinate system.Input for APN is the relative distance and LOS information without further knowledge of debris orbit.Feedback control is applied in the direction of line of sight（LOS）,which transfers the traditional proportional navigation into augmented proportional navigation.Furthermore,the performance of proximity to uncooperative target is verified by assuming the spacecraft is malfunctioning with an unknown acceleration to the chaser.Simulation result demonstrates the feasibility and robustness of APN.By the comparison with exponential deceleration and sliding mode control along LOS,it is proved that the control of constant deceleration is more time saving and fuel saving.Under the scheme of APN,the finite time convergence sliding mode control and terminal sliding mode control is applied in LOS to insure that the proximity time can be limited.3.Performance analysis methods are proposed to evaluate the guidance system.（1）Error propagation of LOS rate is investigated considering uncertainty such as initial state,LOS rate measurement noise and measurement frequency through deriving explicit propagation equation of mean and covariance.Covariance analysis presents a straightforward and analytical solution to evaluating the stability of discrete/continuous control system.Compared with Monte Carlo shooting method,it is more acceptable for remarkable computation saving.（2）The non-gaussian nature of guidance system is explored.Through statistical analysis of nonlinear system we find that,the state variable disobeys the Gaussian distribution under the circumstance of strong nonlinearity and larger uncertainty sources.（3）This thesis explores the potential application of Polynomial Chaos（PC）in performance analysis of terminal guidance system,which transfers the random differential equation into multi-dimentions deterministic differtial equation.Furthermore,the adaptive PC is investigated in the case that there are a large number of uncertainty sources.PC shows a tremendous performance in computation cost and precision.4.The complex relative motion model and control strategy for close range operation is established.Forced fly-around of tumbling spacecraft is a key phase in ADR mission for sake of characterization or surveillance.Whereas the tumbling feature poses a significant challenge for GNC design.Different from past study which focus on the controller design,this paper focuses on astrodynamical model and proposed a new guidance and control scheme based on thorough description of target motion.The scheme is established based on the differential geometry,through which the three dimensional motion is decoupled into the translational motion in instantial rotation plane（IRPL）and the rotating motion of IRPL.Furthermore,the nutational closing operation is presented for sake of the safety when approaching tumbling target with large appdenages.5.The disposal mission is designed based on skip reentry of SMV.This thesis investigates the potential applications of skip SMV and one of the most promising applications is active debris removal.The key feature of skip trajectory is to descend from LEO into atmosphere and then exit.Thesis established the dynamic and control equations for skip SMV with thrust capability.Space shuttle is adopted as the SMV model because the parameter settings are available from open source literatures.Trajectory optimization is the key issue for skip SMV and it is in detail discussed in our paper with different scenarios.Simulation results demonstrate feasibility of skip SMV in active debris removal satisfying constraints.