Midcourse correction design is key to space transfers in the cislunar space.Autonomous guidance has garnered significant attention for its promise to decrease the dependence on ground control systems.This study addres...Midcourse correction design is key to space transfers in the cislunar space.Autonomous guidance has garnered significant attention for its promise to decrease the dependence on ground control systems.This study addresses the problem of midcourse corrections for Earth-Moon transfer orbits based on high-order state transition tensors(STTs).The scenarios considered are direct Earth-Moon transfers and low-energy transfers to lunar distant retrograde orbits(DROs),where the latter involve weak stability boundary(WSB)and lunar gravity assist(LGA)techniques.Semi-analytical formulas are provided for computing the trajectory correction maneuvers(TCMs)using high-order STTs derived using the differential algebraic method.Monte Carlo simulations are performed to evaluate the effectiveness of the proposed approach.Compared with existing explicit guidance algorithms,the STT-based approach is much cheaper computationally and features fewer final position errors.These results are promising for fast and efficient orbital autonomous correction guidance approaches in the cislunar space.展开更多
The usage of state transition tensors(STTs)was proved as an effective method for orbital uncertainty propagation.However,orbital maneuvers and their uncertainties are not considered in current STT-based methods.Uncert...The usage of state transition tensors(STTs)was proved as an effective method for orbital uncertainty propagation.However,orbital maneuvers and their uncertainties are not considered in current STT-based methods.Uncertainty propagation of spacecraft trajectory with maneuvers plays an important role in spaceflight missions,e.g.,the rendezvous phasing mission.Under the effects of impulsive maneuvers,the nominal trajectory of a spacecraft will be divided into several segments.If the uncertainty is piecewise propagated using the STTs one after another,large approximation errors will be introduced.To overcome this challenge,a set of modified STTs is derived,which connects the segmented trajectories together and allows for directly propagating uncertainty from the initial time to the final time.These modified STTs are then applied to analytically propagate the statistical moments of navigation and impulsive maneuver uncertainties.The probability density function is obtained by combining STTs with the Gaussian mixture model.The proposed uncertainty propagator is shown to be efficient and affords good agreement with Monte Carlo simulations.It also has no dimensionality problem for high-dimensional uncertainty propagation.展开更多
基金This work was supported by the National Natural Science Foundation of China(Grant No.12003054)National Key R&D Program of China(Grant No.2022YFC2204700)Strategic Priority Program on Space Science of the Chinese Academy of Sciences(Grant No.XDA30010200).
文摘Midcourse correction design is key to space transfers in the cislunar space.Autonomous guidance has garnered significant attention for its promise to decrease the dependence on ground control systems.This study addresses the problem of midcourse corrections for Earth-Moon transfer orbits based on high-order state transition tensors(STTs).The scenarios considered are direct Earth-Moon transfers and low-energy transfers to lunar distant retrograde orbits(DROs),where the latter involve weak stability boundary(WSB)and lunar gravity assist(LGA)techniques.Semi-analytical formulas are provided for computing the trajectory correction maneuvers(TCMs)using high-order STTs derived using the differential algebraic method.Monte Carlo simulations are performed to evaluate the effectiveness of the proposed approach.Compared with existing explicit guidance algorithms,the STT-based approach is much cheaper computationally and features fewer final position errors.These results are promising for fast and efficient orbital autonomous correction guidance approaches in the cislunar space.
基金the National Natural Science Foundation of China(Nos.11222215 and 11572345)the National Basic Research Program of China(973 Program,No.2013CB733100)the Program for New Century Excellent Talents in University(No.NCET-13-0159).
文摘The usage of state transition tensors(STTs)was proved as an effective method for orbital uncertainty propagation.However,orbital maneuvers and their uncertainties are not considered in current STT-based methods.Uncertainty propagation of spacecraft trajectory with maneuvers plays an important role in spaceflight missions,e.g.,the rendezvous phasing mission.Under the effects of impulsive maneuvers,the nominal trajectory of a spacecraft will be divided into several segments.If the uncertainty is piecewise propagated using the STTs one after another,large approximation errors will be introduced.To overcome this challenge,a set of modified STTs is derived,which connects the segmented trajectories together and allows for directly propagating uncertainty from the initial time to the final time.These modified STTs are then applied to analytically propagate the statistical moments of navigation and impulsive maneuver uncertainties.The probability density function is obtained by combining STTs with the Gaussian mixture model.The proposed uncertainty propagator is shown to be efficient and affords good agreement with Monte Carlo simulations.It also has no dimensionality problem for high-dimensional uncertainty propagation.
