Jingrui Zhang

Jingrui Zhang
Beijing Institute of Technology | BIT · School of Aerospace Engineering

Ph.D

About

150
Publications
26,408
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1,594
Citations

Publications

Publications (150)
Article
Full-text available
With the escalating frequency of space activities, particularly the launch of constellation satellites, the amount of space debris experienced gradually increases, posing threats to the safety and sustainability of the space environment. To counteract the growth of debris, active deorbit devices are imperative for spacecrafts. In low Earth orbit (L...
Article
Full-text available
This brief is devoted to the power-constrained low-thrust optimal control problem (OCP). First, a general model for a class of power constraints is proposed by defining a piecewise smooth function, which describes the discontinuities of the control system. Subsequently, a recursive smoothing function is proposed to smooth the generalized discontinu...
Article
Full-text available
Reachability analysis is very useful and of great interest in various space missions. This correspondence proposes a method to compute the 2-D reachable set (RS) of low-thrust spacecraft with bounded control and limited fuel. For a class of smooth nonlinear affine-control systems, a two-step solving procedure is proposed to solve the boundary of 2-...
Article
Full-text available
The libration motion of conductive tether in the electrodynamic tether system has been demonstrated to be inherently unstable. However, the relationship between the instability of libration motion and the tether current, orbital inclination and attitude of libration motion has not been thoroughly investigated. The novelty of this paper lies in the...
Article
To ensure the secure operation of space assets, it is crucial to employ ground and/or space-based surveillance sensors to observe a diverse array of anthropogenic space objects (ASOs). This enables the monitoring of abnormal behavior and facilitates the timely identification of potential risks, thereby enabling the provision of continuous and effec...
Article
Full-text available
In the field of active deorbiting technologies, the electrodynamic tether has garnered attention due to its cost-effectiveness, light weight, and low fuel consumption. In this study, to address the low success rate of the deployment mechanisms used in previous in-orbit experiments, a novel deployment mechanism with a size of 2 U and a weight 2.3 kg...
Article
Full-text available
Low-thrust propulsion systems are widely used in space missions due to their high specific impulse and reduced propellant consumption. However, current research focuses on eliminating drifts in low-thrust maneuvers, resulting in high operational costs for daily station-keeping. This study aims to achieve autonomous station-keeping by exploiting lon...
Preprint
Full-text available
The libration motion of conductive tether in electrodynamic tether system had been demonstrated unstable inherently. This paper conducts a further dynamic analysis of the instability in electrodynamic tether system, specifically investigating the existence of periodic solution and equilibrium point, as well as exploring the condition for rapid inst...
Article
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Increasingly frequent launch activities, as well as the development of mega constellations, would cause a drastic increase in the number of space objects, which will then alter the evolution of outer space. To reveal this long-term change, an accurate space-environment model is required. There are two main approaches to building this model, one of...
Article
The electrodynamic tether (EDT) system is used as one of the end-of-life disposal technologies to deorbit defunct satellites with the benefit of Earth's magnetic field and plasma environment. However, due to the flexibility of the conductive tether, the orbit-attitude coupling effects as well as the influence of Multiphysics fields, this system suf...
Article
Full-text available
With the development of Electric Propulsion (EP) systems in the geostationary region, indirect optimization method shows a great potential in solving the station-keeping control law. Three main challenges, including the strong nonlinearity of the equations of motion for both states and costate, free transfer time, and the Earth-shadow prediction, a...
Article
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The rapid development of Low Earth Orbit (LEO) mega constellations has significantly contributed to several aspects of human scientific progress, such as communication, navigation, and remote sensing. However, unrestrained deployment of constellations has also strained orbital resources and increased spacecraft congestion in LEO, which seriously af...
Article
This paper presents the crucial method for the results found at Beijing Institute of Technology and China Academy of Space Technology in the 11th Global Trajectory Optimization Competition (GTOC-11). To build 12 solar-power stations placed in the "Dyson Ring" orbit around the Sun, GTOC-11 focuses on the flyby trajectory design, low-thrust trajector...
Article
Full-text available
The reconfiguration of a constellation with several faulty satellites concerns performance improvements in multiple fields, which can be regarded as a multiobjective optimization (MOO) problem. In the optimization design, it is inevitable to evaluate the constellation performance and providing the reconfiguration strategy thousands of times is time...
Article
Two participants with competing objectives are considered in one-to-one orbital pursuit-evasion problem, one of which attempts to satisfy some certain terminal conditions with a minimum cost through its own control while the other player attempts to maximize the specified payoff and avoids entering this terminal range. This paper treats the problem...
Article
This paper is dedicated to exploring the NASA Langley Challenge on Optimization under Uncertainty by proposing a series of approaches for both forward and inverse treatment of uncertainty propagation and quantification. The primary effort is placed on the categorization of the subproblems as to be forward or inverse procedures, such that dedicated...
Article
This paper presents a flexible modeling framework for multi-target tracking based on the theory of Outer Probability Measures (OPMs). The notion of labeled uncertain finite set is introduced and utilized as the basis to derive a possibilistic analog of the $\delta$ -Generalized Labeled Multi-Bernoulli ( $\delta$ -GLMB) filter, in which the uncertai...
Article
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...
Article
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The Bhattacharyya distance has been developed as a comprehensive uncertainty quantification metric by capturing multiple uncertainty sources from both numerical predictions and experimental measurements. This work pursues a further investigation of the performance of the Bhattacharyya distance in different methodologies for stochastic model updatin...
Conference Paper
Full-text available
In this work, the Earth re-entry by exploiting the lunisolar perturbations with low-thrust maneuvers is studied for the need to investigate alternative end-of-life disposals for satellites in the inclined geosynchronous orbits. A simplified double-averaged semi-analytical propagator is built for long-term orbital propagation, which is accurate enou...
Article
To ensure the safety of operations with a fast-tumbling target, a detumbling strategy implemented by a dual-arm space robot with finger-type end effectors is proposed to attenuate the target rotation. A detumbling system that consists of the robot and the target is established. Through the contact effects between the two parts, the energy of the ta...
Article
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Analytical expressions are obtained for computing the collision probability of a large Composite CubeSats hovering in the close vicinity of another large Composite CubeSats in a Leader-Follower configuration. The composite is constructed from a large number of Unitary CubeSats arranged in a cuboid volume. The study involves the modeling of the grow...
Article
Use of a debris-tether-tug (DTT) system has been recognized as one of the most promising techniques for space debris removal. Attitude motion of the debris may give rise to severe disturbances to the debris removal system. In this case, a conventional DTT system with a single tether may no longer be capable of removing the debris in a stable manner...
Article
This paper presents an electromagnetic vibration isolation system (EVIS) that connects the support module (SM) and the payload module (PM) by electromagnetic interaction, where there is no mechanical connection between the two parts to keep the PM free from disturbances while working on orbit. The configuration and the control method of the EVIS ar...
Article
Mean orbital elements estimation for geostationary (GEO) satellites is important for related studies, including station-keeping, rendezvous and end-of-life disposal. With increasingly limited operational slots in GEO region and the advance of all-electric-propulsion satellites, a fast and accurate mean orbital element estimation tool is necessary....
Conference Paper
Small constellations of satellites in Inclined Geosynchronous Orbits (IGSO) provide an alternative to the increasingly crowded Geostationary Equatorial Orbit (GEO) belt. Satellite platforms equipped with electric propulsion systems increase in popularity since they broaden the mission design opportunities due to the potentially significant propella...
Conference Paper
Full-text available
This paper investigates low-thrust station-keeping strategies for geostationary satellites. On the contratry to traditional low-thrust control methods, which requires ground-station operations in a daily basis, the proposed method maximises the exploitation of natural dynamics and allows for the design of an efficient control within a predefined sl...
Article
Full-text available
This paper focuses on geostationary satellites with an electric propulsion system and develops two efficient station-keeping strategies in full and failure modes. High-precision mean orbital elements are calculated by an estimator and used as the inputs of two control strategies. In the full mode, an optimization-based maneuver planner, which requi...
Article
This paper proposes the Coulomb tether double-pyramid satellite formation, which includes a cluster of charged satellites repelling each other by Debye-shielded Coulomb forces and two counterweights connecting to each satellite via elastic massless tethers. The center of mass of the formation is prescribed to move along the geostationary orbit. The...
Article
Full-text available
The control of a tethered satellite system pendular motion is done by application of Hamiltonian equation of motion on a control design method known as planar H tracking. In this case, the reference motion is considered a natural planar motion. The control of the TSS is accomplished by using the inside plane control inputs as well as the outside pl...
Article
Full-text available
From September 1st 2017 to October 15th 2017, the 9th China Trajectory Optimization Competition was jointly hold by the Chinese Society of Theoretical and Applied Mechanics, Beijing Institute of Technology, Beijing Institute of Electronic System Engineering, Tsinghua Space Center. The competition contains two problems, where problem A focuses on th...
Article
Full-text available
From September 1st 2017 to October 15th 2017, the 9th China Trajectory Optimization Competition (CTOC) was jointly held by the Chinese Society of Theoretical and Applied Mechanics, Beijing Institute of Technology, Beijing Institute of Electronic System Engineering, and Tsinghua Space Center. The competition contains two problems, where problem A fo...
Article
The low-thrust version of the fuel-optimal transfers between periodic orbits with different energies in the vicinity of five libration points is exploited deeply in the Circular Restricted Three-Body Problem. Indirect optimization technique incorporated with constraint gradients is employed to further improve the computational efficiency and accura...
Article
This paper presents a trajectory-optimization method for a chaser spacecraft operating in ultra-close proximity to a failed satellite. Based on the combination of active and passive trajectory protection, the constraints in the optimization framework are formulated for collision avoidance and successful docking in the presence of any thruster failu...
Conference Paper
Full-text available
For future human space programs, it is needed to remove thousands of large debris rotating with high speed around the Earth which they have been left behind from the first space launch in Low Earth Orbit. Although different solutions are proposed for debris mitigation, drag augmentation systems have the advantage of no need for thrust generating su...
Article
Full-text available
This paper presents a modified constraint force algorithm (m-CFA) for the dynamics of flexible multibody systems in arbitrary topologies. The m-CFA can efficiently calculate the constraint forces while solving for the motion of the system. The motion equations are based on recursive formulation, whereas a global equation is generated to obtain the...
Article
This paper presents the deployment strategies for planar multi-tethered satellite formation that spins in orbit plane. By using Lagrange principles, the deployment dynamics, which treat the parent satellite as a finite sized rigid body, are established under gravity gradient perturbation. Comparing with the simplified dynamics that take the parent...
Article
Full-text available
The solar power satellites (SPS) are designed to collect the constant solar energy and beam it to Earth. They are traditionally large in scale and flexible in structure. In order to obtain an accurate model of such system, the analytical expressions of the gravitational force, gravity gradient torque and modal force are investigated. They are expan...
Article
A method is proposed to select the target sequence for a J2-perturbed multiple debris rendezvous mission aimed at removing dozens of debris from several thousand debris candidates running on sun-synchronous orbits (SSO). The solving methodology proceeds in two steps: Firstly, the variance of the right ascension of ascending node (RAAN) of the debri...
Article
In this paper, a path planning algorithm for a multi-arm space robot is proposed. The robot is capable of maneuvering on the exterior of a large space station. Based on the maneuver strategy, continuous and smooth trajectories of the manipulator end effectors are first determined via the polynomial interpolation method. Then, the kinematics describ...
Article
Full-text available
Satellite orbits require periodical maintenance due to the presence of perturbations. However, random errors caused by inaccurate orbit determination and thrust implementation may lead to failure of the orbit control strategy. Therefore, it is necessary to analyze the robustness of the orbit control methods. Feasible strategies which are tolerant t...
Conference Paper
Full-text available
The solar wind electric sail (E-sail) have aroused the researchers’ interests as an innovative and feasible scheme in recent years. Yet the theoretical research about E-sail’s dynamics and control remain unsolved. In this work, the dynamic behavior of a single charged wire - the component unit of an E-sail - is studied. According to the features of...
Article
The development of the complex multibody spacecraft raises higher requirement to multi-body dynamics modeling and control technology. The explicit dynamics equations of the system are always needed to analyze system's characteristics and design controllers, but the complexity of system brings difficulty to deriving the equations. In order to solve...
Article
A new vibration control strategy is presented to realize rapid attitude maneuvers and stabilization for a spacecraft with flexible appendages. This control strategy combines the command input shaping and the technique of passive vibration isolation for vibration sources. The analytical dynamic model of the spacecraft with CMGs, passive vibration is...
Article
The initial orbital state of a space object cannot be determined using atracklet as the tracklet only contains angular and angular rate observations without any ranging information. One approach to determine confident initial orbits is to constructan admissible region, which restricts the range/range-rate to a compact subset by considering physical...
Article
The objective of this paper is to find the minimum-fuel orbit transfer between sun-synchronous orbits with low-thrust while considering the J2 perturbation. A quasi-circular orbit model with the effect of the J2 perturbation is established. The minimum fuel problem is solved by the indirect optimization method. Several effective techniques are empl...
Article
The Ultrasail, a novel solar sail design development at the University of Illinois at Urbana-Champaign, relies in small-tip satellites to provide tension in rectangular sails. With the present rate of growth of orbital space debris, this paper analysis the influence of the Ultrasail dynamics on space debris. The main work is given the study of the...
Article
A nonlinear output feedback control law based on passivity is proposed to reduce the vibration of large space structures. The considered system is assumed to be equipped with collocated actuators and sensors. The concept of practically finite-time stability is first developed to describe the finite-time convergence of a passive system. Then, an out...
Conference Paper
Full-text available
The magnitudes of the constraint forces at the joints in a multibody spacecraft are critical parameters in designing the joints structure. Therefore, it is desirable to efficiently calculate the constraint forces in the dynamics simulation. In this work, a constraint force algorithm for flexible multibody system (CFA-F) is developed. The proposed m...
Article
Full-text available
Techniques associated with stable manifold and lunar flyby have been applied to the construction of optimal transfers to Earth-Moon \(L_{1} /L_{2}\) libration point orbits. Compared with traditional design methods and to reduce maneuver cost, the design process presents a detailed analysis on the effect of lunar proximity with multiple constraints....
Article
This paper presents a trajectory planning algorithm to optimise the collision avoidance of a chasing spacecraft operating in an ultra-close proximity to a failed satellite. The complex configuration and the tumbling motion of the failed satellite are considered. The two-spacecraft rendezvous dynamics are formulated based on the target body frame, a...
Article
The objective of this paper is to minimize fuel consumption needed for geostationary Earth orbit station keeping by Xenon Ion Propulsion System (XIPS) thrusters in failure mode under eclipse constraints. Two diagonal XIPS thruster pairs, each pair consisting of one north thruster and one south thruster, are mounted on the antinadir face of the sate...
Article
The objective of this paper is to find the minimum-fuel station change for geostationary satellites with low-thrust while considering significant perturbation forces for geostationary Earth orbit (GEO). The effect of Earth's triaxiality, lunisolar perturbations, and solar radiation pressure on the terminal conditions of a long duration GEO transfer...
Article
Full-text available
Gyroelastic body refers to a flexible structure with a distribution of stored angular momentum (called gyricity). In previous studies, it was assumed that each volume element of the structure possesses an infinitesimal spinning rotor so that the distribution of the gyricity is continuous. However, the momentum devices must be discretely distributed...
Article
This paper discusses the dynamic characteristics of the impacts and corresponding frictions generated by the clearances of joints of vibration isolation platforms for control moment gyroscopes (CMGs) on spacecraft. A contact force model is applied using a nonlinear contact force model, and the frictions in the joints are considered in the dynamic a...
Conference Paper
Full-text available
The magnitudes of the constraint forces at the joints in a multibody spacecraft are critical parameters in designing the joints structure. Therefore, it is desirable to efficiently calculate the constraint forces in the dynamics simulation. In this work, a modified constraint force algorithm (MCFA) for dynamics of arbitrary multibody spacecraft is...
Article
Full-text available
The efficient dynamics algorithm for multibody system has always been a research hotspot. In recent years, many efficient dynamics algorithms made progresses in improving the computational efficiency, but most of them cannot provide an explicit expression of the system's dynamics or resolve the constraint forces. Based on the above issue, a constra...