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## Publications

Publications (142)

This paper proposes a trajectory-battery integrated design of the electric pump-fed (EPF) engine and demonstrates its application feasibility to orbital maneuvers in low-Earth orbit (LEO). Based on the mass model that comprises the main components of the engine, the advantages of the electric pump system in terms of the structural mass, addition of...

This paper investigates the nonlinear dynamical behaviors of a time-delayed supercavitating vehicle system varying with the system parameters, and proposes control strategies to stabilize the trajectory. A simplified dynamical model of the supercavitating vehicle is firstly constructed and then analyzed on its local and global stability in terms of...

An integrated strategy is proposed for asteroid orbiting, consisting of stationkeeping, autonomous navigation, and real-time geodetical recovery. It is designed to maintain the spacecraft on its nominal trajectory under some uncertainties from the spacecraft and the asteroid. Furthermore, it performs adaptive estimations on the mass and thruster of...

An integrated simulation system for solar sail spacecraft with individually controllable elements (SSICE) is investigated in this paper, including the modelling of power management, thermal control, attitude control, umbra prediction, and orbit prediction subsystems. Considering the self-control and reactivity subsystems, an agent based method is a...

A surrogate-based optimization method is proposed in this paper to realize the optimization of the entire trajectory from launch to reentry. Different from traditional strategy of multiphase trajectory optimization that directly utilizes the original dynamical model, a surrogate model is substituted for the original time-consuming model to improve...

This study addresses the boundary and fluctuation of invariant relative orbits for spacecraft formation flying in a high-order gravitational field. The invariant relative condition is analyzed to obtain the analytical boundary. To ensure the accuracy of invariant condition, zonal harmonic terms of the gravitational field, from J2 to J15, are consid...

A frozen orbit is beneficial for observation owing to its stationary apsidal line. The traditional gravitational field model of frozen orbits only considers the main zonal harmonic terms J2 and limited high-order terms, which cannot meet the stringent demands of all missions. In this study, the gravitational field is expanded to J15 terms and the H...

The ascending trajectory from the surface of Phobos to a resonance quasi-satellite orbit around Phobos is investigated with a newly proposed dynamical model based on the Elliptic Restricted Three-Body Problem. The proposed model incorporates the non-spherical gravity field and physical libration of Phobos as well. The trajectories from the surface...

In the general 2-satellite formation near Earth, the deputy satellite moves around the chief one, resulting that the relative baseline exhibits the periodical variations in the form of trigonometric functions. In such case, only the certain positions can be employed for interferometric imaging, and the high requirements of Earth observation and rem...

This paper proposes a low-thrust reconfiguration strategy for formation flying based on the Jordan normal form and evaluates its performance based on the required control acceleration and fuel cost. First, the relative dynamics of reconfiguration is disposed by Jordan decomposition to describe the unstable component, i.e., the drift velocity along...

The deflecting asteroid by dusting (DAD) mission addresses the challenges of deflecting a potentially hazardous asteroid (PHA) that has a large probability of impacting Earth. It is an innovative and mass-minimalist approach to exploit PHAs by using the dusting deflection method. This conceptual design is developed based on an asteroid space duster...

In this paper, a genetic programming method for satellite system design is proposed to simultaneously optimize the topology and parameters of a satellite system. Firstly, the representation of satellite system design is defined according to the tree structure. The genetic programming method is designed based on that representation. Secondly, accord...

This paper proposes a novel method for the low-thrust transfer to the triangular libration points in the Earth-Moon system. Horseshoe orbit is explored as the coasting arc in this transfer scenario. By tangential thrust control strategy, the low-thrust transfer from the Earth to the short-period orbit around L4 point is realized. The pseudospectral...

Coulomb thrusting presents attractive prospects in many astronautical missions from the standpoint of close-proximity formation flying. In this study, a dynamical model of Coulomb formation and its Hamiltonian is derived on the basis of the Tschauner–Hempel equation. As a nonautonomous system, it is more complicated than the dynamical model based o...

An integrated algorithm to design the optimal ascent trajectory of a target Sun-synchronous orbit (SSO) for small-lift launch vehicles is studied in this paper. A general problem description is provided, including the specific pitch law designed for an ascent trajectory to SSO and the definitions of design variables and equality/inequality constrai...

In this research, the linearized solutions of periodic orbits near the Earth-Moon L4 point are introduced, and the multiple-shooting method is used to modify the linearized results to obtain the periodic orbit in CR3BP. Based on these results, the Poincaré map at L4 point is obtained by which the initial states for quasi-periodic orbit are determin...

We perform an analytical study of the Lissajous and halo orbits around collinear points L1 and L2 in a spatial circular restricted three-body problem of an arbitrary value of the mass ratio. Using a canonical transformation procedure, we generate complete and resonant normal forms through reduction to center manifolds. The coefficients in the norma...

The potentially hazardous asteroid is not only the target of planetary defense missions but also an ideal one for scientific exploration of near-Earth objects due to minimal launching budget during its close encounter with Earth. The flyby segment of asteroid shows to be hyperbolic in an Earth-centred inertial frame. To guide the spacecraft capture...

As a unique configuration of satellite formation, the tethered satellite system has the advantage for space observation due to its flexible baseline. This paper addresses the concept of a tethered satellite cluster system (TSCS) that consists of a central satellite and several member satellites connected by rope or chain. Using the Clohessey–Whilts...

The existing atmospheric mass density models (AMDM) would produce considerable errors in orbital prediction for Low Earth Orbit (LEO) satellites. In order to reduce these errors and correct the AMDM, this paper presents methods based on data mining with historical data of two-line element (TLE). Starting from a typical LEO satellite, TIANHUI, two o...

It is clarified that the parabolic/hyperbolic restricted three-body problem (PRTBP/HRTBP) can be adopted to provide a simple description of the dynamics of fly-by asteroids or the close encounters between different galaxies. For these reasons, PRTBP and HRTBP have been investigated for long intervals of time. However, they are quite different from...

Proximate spacecraft formation flying has many applications in high accurate earth observation and astronomy. In comparison to conventional or electronic thrust, Coulomb thrust has obvious advantages in close-formation control, such as fast throttling, nearly propellantless features and no thruster plume impingement. This paper presents the concept...

This paper develops a new asteroid capture mechanism via triangular libration points based on their stable structure and chaotic motion nearby. Different from collinear libration points, the triangular libration points are linearly stable surrounded by long- and short-period orbit families in the planar case. First, their dynamical structure is exp...

Close-proximity Coulomb formation flying offers attractive prospects in multiple astronautical missions. To achieve a deeper understanding of the dynamical structures of Coulomb formations, in this paper, an eight-charge symmetric configuration of Coulomb formation is presented and its dynamics is analyzed by center manifold reduction and Poincaré...

This research systematically presents the feasibility of allocating reusable cargoes in a quasi-periodic p:q resonant cycler orbit to construct a cislunar in-orbit infrastructure. First, p:q resonant cycler orbits are generated by resonance conditions in the context of a planar circular restricted three-body problem through differential correction...

It is presented in this paper that an innovative concept quasi-periodic formation flying, which can hold bounded trajectories without any restriction initialization, compared with the traditional restriction on initial velocity by linear equation for relative dynamics. The improved periodic linear equation associated with J2 perturbation is derived...

In this study, an improved Hamiltonian structure-preserving controller is applied for formation flying in elliptic orbits. The Lyapunov-Floquet theory is applied to the Tschauner-Hempel (TH) equation in order to generate its transformed form with two zero eigenvalues and two pairs of imaginary eigenvalues. Then, an improved Hamiltonian structure-pr...

This paper discusses the linearized relative motion and control of Electric Solar Wind Sails (E-sails) operating in formation flight around a heliocentric displaced orbit. An E-sail is constituted by thin and centrifugally stretched tethers, and generates a propulsion by momentum interaction with the charged particles from the solar wind. Feasible...

This paper is devoted to the bifurcation of periodic orbits and libration points in the linked restricted three-body problem (LR3BP). Inherited from the classic circular restricted three-body problem (CR3BP), it retains most of the dynamical structure of CR3BP, while its dynamical flow is dominated by angular velocity ω and Jacobi energy C. Thus, f...

Data clustering analysis is proposed to detect the orbital maneuvers of satellites at different scales. In this study, the unsupervised classification methods of K-means, hierarchical, and fuzzy C-means clustering are used to handle the two-line element (TLE) historical data. The K-means-based contour map method is applied to the characteristic var...

This paper analytically describes the nonlinear motion of displaced orbits obtained by low-thrust propulsion, and focuses on the first-order analytical derivation of perturbation solutions of osculating Keplerian element (OKE) time histories. A virtual Earth (VE) model is developed to transform non-Keplerian orbits above the Earth into Keplerian or...

The lifetime of the existing attitude and orbit control systems (AOCS) generally depends on the amount of the fuel carried on a spacecraft. This paper proposes a novel design concept for a low Earth orbit (LEO) spacecraft named In-Drag Sail with Individually Controllable Elements (IDSICE), which can release the fuel's limitation to its attitude con...

This paper investigates the velocity-free spacecraft pose tracking control in terms of dual quaternions, and its application to six-degrees-of-freedom (six-DOF) asteroid-hovering operation. First, a coupled linear velocity and angular velocity observer, driven by the spacecraft position and attitude measurements, is designed via the immersion and i...

A semi-analytical technique for both the design and control of repeat ground-track (RGT) orbits in a high fidelity dynamical model, including non-conservative forces and accurate Earth orientation parameters, is introduced. The method is based on the use of high-order expansion of Poincaré maps to propagate forward in time regions of the phase spac...

This paper employs a parallelized genetic algorithm in generating long-term bounded halo orbit and optimizing transfer trajectory from earth to it in the full ephemeris model. While the conventional gradient methods are lacking in precision as well as time-consuming, the parallel genetic algorithm (PGA) offers an access to large-scale computing bas...

This Paper proposes a control strategy and optimization of low-thrust reconfiguration for formation flying by Jordan norm form to overcome the drawback of eigenvalue decomposition in describing the unstable term of the relative motion. In this Paper, the initial values of general solution from simplified dynamics are regarded as the invariants of f...

Searching for naturally bounded relative orbits in a zonal gravitational field is a crucial and challenging task in astrodynamics. In this work, a semi-analytical approach based on high-order Taylor expansions of Poincaré maps is developed. Entire families of periodic orbits, parameterized by the energy and the polar component of the angular moment...

We design a distributed situational observer using formation flying in a displaced orbit. The main focus of our investigation is the relative dynamics and control of displaced orbits obtained by low-thrust propulsion. The spatial dynamics in Newtonian form are used to derive the numerical relative motions, and their natural frequencies discovered b...

The local invariant (stable, unstable, and center) manifolds of a saddle \(\times \) center \(\times \) center equilibrium point can be used to construct a three-dimensional Hamiltonian structure-preserving (HSP) controller. The linear stability of the controlled Hamiltonian system is verified when one of the proposed criteria is satisfied. The non...

By patching the invariant manifolds of collinear libration points Lyapunov orbits of two restricted three body problem (CR3BP), Koon (2001) successfully constructed low-energy Earth-Moon transfers in the Sun-Earth-Moon system. It reveals the essential mechanism of low-energy cislunar transfers, i.e., weak stability boundary (WSB), from the viewpoin...

This paper deals with the man-machine interaction of robotic arm teleoperation by the developed Kinect and first-person-perspective follow-up technologies. Kinect is used to collect and preprocess the depth information to determine the hand position vector. With the help of the virtual robotic arm set up by Processing, the relationship between the...

This paper discusses a numerical searching approach for the relative motion of formation flying in displaced orbits by spacecraft with low-thrust propulsion. The nonlinear dynamical model of spacecraft is established in a two-body rotating reference frame with arbitrary polar component of momentum and thrust-induced acceleration. Motions near the s...

This paper discusses the stability, transition and control of displaced non-Keplerian orbits by the spacecraft using low-thrust propulsion. The two-body dynamical model developed in the polar coordinates is parameterized by the thrust pitch angle, and then two of the hyperbolic and elliptic equilibria are solved from it. The bounded motions near tw...

Formation flying near a libration point is an effective method of the multi-point in-situ detection of deep-space environment and the high resolution observation of astronomy etc. This paper proposes a novel numerical searching method based on ergodic Poincaré mappings to seek natural formation flying on quasi-halo orbits in a photogravitational ci...

Two types of new orbital transfer strategies that use only-accelerating maneuvers are proposed for a simple spacecraft with only one engine. Based on the requirement of only-accelerating maneuvers, the constraints on the orbital parameters in the entire transfer process are derived from Gauss variational equations. The explanation of these constrai...

Due to their lack of fuel consumption, solar sails have potential applications for deep space exploration. However, due to the optical degradation and deformation of such a sail, a nonideal model is preferable for investigating their dynamics and control when moving around an artificial Lagrangian point. An improved imperfectly reflecting sail mode...

In this paper, a new methodology is proposed to derive the high-order approximations of motions near them in three cases, i.e., the mass ratio is greater than, smaller than and equal to Gascheau and Routh critical value. A preliminary analysis on the phase space structure of triangular libration points in the first case is accomplished from the poi...

In this paper, the orbit acquisition and maintenance strategies for the repeat-groundtrack orbit are investigated to maintain the ground track of the satellite within a certain range. Two kinds of orbital dynamics models are introduced to calculate the on-orbit state of satellite. One is the orbital propagation model which is of high fidelity and c...

This paper studies the dynamics and control of a spacecraft, whose area-to-mass ratio is increased by deploying a reflective orientable surface such as a solar sail or a solar panel. The dynamical system describing the motion of a non-zero attitude angle high area-to-mass ratio spacecraft under the effects of the Earth's oblateness and solar radiat...

For the requirements from some missions, the spacecraft is placed near the unstable region around the hyperbolic equilibrium. To stabilize the motion, a novel concept of the weak Hamiltonian-Structure-Preserving (HSP) control parameterized by the Coriolis acceleration is introduced. Based on the dynamical model of low-thrust displaced orbits, this...

High-precision, temperature control technology is currently an important research field in spacecraft thermal control. High-precision temperature control based on grading-structure and PID-feedback strategies determine by theoretical analysis and grading a thermal control experiment is proposed in this paper. A sensitivity analysis of the key param...

This paper is devoted to stabilizing motions near a special type of equilibrium point of contact binary asteroids by Hamiltonian structure-preserving control. Aiming at noncollinear equilibrium points of the asteroid 1996 HW1, a Hamiltonian structure-preserving controller is built up using stable and unstable manifolds. Compared with traditional Ha...

In view of the limitations of the existing libration-point satellite navigation systems in cislunar space, this paper replaces satellites with solar sails to construct a cislunar navigation constellation and is devoted to the trajectory optimization of solar sails to minimize the lightness number control. The Artificial Lagrangian Points (ALPs) yie...

In this paper, a novel approach for high-accuracy attitude control in a flexible spacecraft is developed by compensating and damping the vibration of the flexible appendage. A vibration suppression-based attitude controller (VSAC) that addresses the coupling disturbance in attitude dynamics that is generated by the vibration of the flexible appenda...

Earth-orbiting satellites experience a partial or full eclipse when they pass through the night side of the Earth. These eclipse events can have significant impacts on the satellite due to the dramatic change of the solar radiation incident. It is therefore essential to propose a high-precision eclipse prediction algorithm or even a spaceborne algo...