Binfeng Pan

Binfeng Pan
Northwestern Polytechnical University | NWPU · School of Astronautics

PhD

About

50
Publications
14,308
Reads
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763
Citations
Citations since 2016
36 Research Items
708 Citations
2016201720182019202020212022050100150
2016201720182019202020212022050100150
2016201720182019202020212022050100150
2016201720182019202020212022050100150
Introduction
Binfeng Pan currently works at the School of Astronautics, Northwestern Polytechnical University. Binfeng does research in orbital dynamics, trajectory optimization, computational guidance and control, and machine learning.
Additional affiliations
January 2011 - present
Northwestern Polytechnical University
Position
  • Professor (Full)

Publications

Publications (50)
Article
Full-text available
The main contribution of this Note is to show that within the context of computational guidance, a recent approach dubbed Model Predictive Static Programming (MPSP) heavily promoted by its authors is at the fundamental level just the application of the classical Newton method for solving an under-determined algebraic system. Therefore the MPSP appr...
Article
Full-text available
The homotopy method has long served as a useful tool in solving optimal control problems, particularly highly nonlinear and sensitive ones for which good initial guesses are difficult to obtain, such as some of the well-known problems in aerospace trajectory optimization. However, the traditional homotopy method often fails midway: a fact that occa...
Article
Full-text available
Although homotopy methods have been widely utilized to find the extremals of low-thrust trajectory optimization problems to circumvent the high sensitivity with respect to the unknowns, there has been little discussion in the literature on how to design the homotopy to find not just any extremal, but one with the least value of performance index. I...
Article
Full-text available
Solving fuel-optimal low-thrust trajectory problems is a long-standing challenging topic, mainly due to the existence of discontinuous bang–bang controls and small convergence domain. Homotopy methods, the principle of which is to embed a given problem into a family of problems parameterized by a homotopic parameter, have been widely applied to add...
Article
Full-text available
Convex optimization is a class of mathematical programming problems with polynomial complexity for which state-of-the-art, highly efficient numerical algorithms with pre-determinable computational bounds exist. Computational efficiency and tractability in aerospace engineering, especially in guidance, navigation, and control (GN&C), are of paramoun...
Article
Full-text available
In this study, the problem of the stabilisation of a class of nonautonomous nonlinear systems was studied. First, a fractional stability theorem based on a fractional-order Lyapunov inequality was formulated. Then, a novel fractional-order sliding surface, which was a generalisation of integral, first-order, and second-order sliding surfaces with v...
Chapter
Full-text available
This paper presents an analytical zero-effort-miss(ZEM) /zero-effort-velocity(ZEV) feedback guidance algorithm using the Levi-Civita transformation, where the ZEM and ZEV vectors can be determined explicitly instead of numerical integration or any propagators. Ineach guidance cycle, the states of the spacecraft and targetare first trans-formed into...
Article
This paper presents a feasible sequential convex programming method to solve the multistage ascent trajectory optimization problem. The proposed method is based on the inexact restoration technique, in which a more feasible intermediate iterate is first produced by solving a constrained least-squares problem, and then a more optimal iterate is gene...
Article
Full-text available
When launch vehicles encounter thrust drop faults during endoatmospheric flight, conventional nominal trajectory-based guidance methods may fail to compensate adequately, and the launch mission may culminate in failure. In this paper, we present an improved parallel-structured Newton-type guidance (PSNG) algorithm to address the above challenge. Co...
Article
Full-text available
This paper presents an improved sequential convex programming (SCP) algorithm for ascent trajectory optimization of launch vehicles, by exploiting the state-of-the-art modified Chebyshev–Picard iteration (MCPI) technique. In the proposed algorithm, the MCPI technique is first utilized to transcribe the continuous-time optimization problem into a se...
Article
This paper presents a parallel-structured Newton-type guidance law for the missile guidance problems. In the proposed approach, the modified Chebyshev–Picard iteration is used to approximate the dynamic equations, by which the continuous-time guidance problem is transcribed into a sequence of discrete-time subproblems, and both serial and parallel...
Article
Solving minimum-time low-thrust orbital transfer problems in the three-body problem by indirect methods is an extremely difficult task, which is mainly due to the small convergence domain of the optimal solution and the highly nonlinear nature associated with the three-body problem. Homotopy methods, the principle of which is to embed a given probl...
Article
Full-text available
Finding a solution to a low-thrust minimum-fuel transfer trajectory optimization problem in the circular restricted three-body problem (CRTBP) is already known to be extremely difficult due to the strong nonlinearity and the discontinuous bang-bang control structure. What is less commonly known is that such a problem can have many local solutions t...
Article
The rapid developments of artificial intelligence in the last decade are influencing aerospace engineering to a great extent and research in this context is proliferating. We share our observations on the recent developments in the area of spacecraft guidance dynamics and control, giving selected examples on success stories that have been motivated...
Article
Full-text available
In this paper, a novel fractional order proportional-integral-differential navigation guidance law utilizing finite time stability approach is presented in order to achieve robust performance for intercepting incoming targets. The proposed guidance law is designed following three-loop guidance and control scheme, considering the interceptor’s nonli...
Article
Full-text available
The homotopy methods have long served as powerful tools in solving nonlinear optimal control problems, particularly for which the solutions are highly sensitive to the unknown initial conditions. The principle of homotopy methods is that a homotopic parameter is embedded into the formulations of the optimal control problems, and the original proble...
Preprint
Full-text available
The rapid developments of Artificial Intelligence in the last decade are influencing Aerospace Engineering to a great extent and research in this context is proliferating. We share our observations on the recent developments in the area of Spacecraft Guidance Dynamics and Control, giving selected examples on success stories that have been motivated...
Article
In this paper, a new hybrid method based on invariant manifold and chaos control is presented to design Earth-Moon low-energy transfer trajectory in the planar circular restricted three-body problem. In the proposed method, one segment trajectory emanates from the period orbit around the Earth to Lyapunov orbit associated with the Lagrange points L...
Article
Full-text available
Homotopy methods have been widely utilized to solve low-thrust orbital transfer problems, however, it is not guaranteed that the optimal solution can be obtained by the existing homotopy methods. In this paper, a new homotopy method is presented, by which the optimal solution can be found with probability one. Generalized sufficient conditions, whi...
Preprint
Full-text available
Homotopy methods have been widely utilized to solve low-thrust orbital transfer problems, however, it is not guaranteed that the optimal solution can be obtained by the existing homotopy methods. In this paper, a new homotopy method is presented, by which the optimal solution can be found with probability one. Generalized sufficient conditions, whi...
Article
Full-text available
Solving hypersensitive optimal control problems is a long-standing challenge for decades in optimization engineering, mainly due to the possible nonexistence of the optimal solution to meet the required error tolerance under double-precision arithmetic and the hypersensitivity of the optimal solution with respect to the initial conditions. In this...
Article
Full-text available
A reentry guidance method for low lift-to-drag (L/D) ratio vehicles in a lunar return mission is presented. Different from the reference drag tracking scheme, method in this paper tracks a weighted profile of altitude and downrange using a command filtered backstepping approach. First, the dynamics of the tracking error are established with dispers...
Article
Full-text available
A multi-step control of chaos method is proposed in this paper to reduce the flight time in the chaotic region of Earth-Moon low-energy orbit transfer. According to the motion regularity and the fact that the chaos orbit is highly sensitive to the initial conditions in the circular restricted three-body system, the optimal perturbation of chaos con...
Article
Full-text available
The chaotic transport in Earth-Moon three-body system has been demonstrated to be a novel approach to explore the Moon at a low energy cost. However, existing targeting methods require sufficient experience to construct Earth-Moon chaotic transfer orbits, which is not an easy task to the untrained eye. In this paper, the elitist teaching-learning-b...
Article
A multiple homotopy method is proposed to optimize the very low thrust fuel-optimal transfer trajectory under the effects of J2 perturbation. A simple problem of high thrust,energy-optimal transfers in the linear gravity without J2 perturbation is constructed as the homotopy initial problem. Three homotopic parameters are embedded in the kinetic eq...
Conference Paper
Full-text available
Low thrust trajectory optimization for the multi-target removal mission of sun-synchronous orbit space debris is studied in this paper. The space debris removal mission is that a 1000 kg spacecraft with the electrical propulsion system is launched to removal the space debris as many as possible among the potential 3629 debris, by releasing a 1 kg d...
Article
The satellite on Earth-Moon L2 periodic orbit will provide communication relay for CE-4,China’s first Lunar landing exploration mission on the moon’s far side. The transfer orbit design plays an important role in the implementation of the relay mission. Considering the constrains on transfer time,flyby altitude and amplitude of the halo orbits,this...
Conference Paper
Full-text available
This paper presents the methods proposed by team 13-NPU in the 9th Global Trajectory Optimization Competition (GTOC9). The debris removal sequence in single submission and the reasonable allocation of all debris in submissions are designed by branch and bound algorithm and image method. Then a three-impulse transfer method involving a deep space ma...
Article
To decrease the bank angle reversal frequency in the skip phase and suppress the aerodynamic load effectively in the final phase of the numerical predictor-corrector guidance for lunar return capsule, an improved guidance scheme is proposed by searching for the energy point of the only one bank reversal in the skip phase and compensating the guidan...
Article
Current methods of the periodic orbit computation have the disadvantages of requiring large amount of computation, varying the Jacobi energy, and the limitation to calculate the specific periodic orbits, a novel method of the periodic orbit computation is proposed in this paper. Firstly, a modified Poincaré section map is created, on which the proj...
Article
A new homotopy method is proposed to solve the fuel-optimal transfer trajectory with flyby of other celestial bodies in the deep space exploration, overcoming the difficulty due to the interior point constraints and discontinuous structure of the Bang-Bang control. The homotopic parameter is embedded in both the performance index and interior point...
Conference Paper
Full-text available
The time-optimal interplanetary transfer trajectories for solar sailcraft are examined under the Kustaanheimo-Stiefel (KS) transformation. Through transforming both the state and time coordinates to a new model, the KS transformation can changes the unperturbed Kepler equation into a simple linear harmonic oscillator, offering a promising way to in...
Article
Solving Lambert’s problem is one of the fundamental problems in astrodynamics. In this paper, it is first shown in a systematic fashion how Lambert’s problem can be expressed as a univariate equation of one of the orbital elements or various variables related to the orbital elements. Some of the choices of independent variables reported in the lite...
Article
A multi-constrained suboptimal guidance method based on an improved zero-effort-miss/zero-effort-velocity (ZEM/ZEV) algorithm and the recently developed model predictive static programming (MPSP) is presented in this paper for lunar pinpoint soft landing. Firstly, the ZEM/ZEV algorithm is improved so that the trajectories generated by the algorithm...
Article
A method was presented for designing the transfer trajectories to the Sun-Earth L3 periodic orbits based on the pseudo manifolds in the circular restricted three body problem. The dynamics of the pseudo manifolds, constructed by giving a large perturbation to L1 or L2 orbits, were used to construct the transfers. Three deterministic maneuvers were...
Article
An approach for low-thrust and gravity-assist trajectory optimization is presented in this paper based on automatic differentiation and pseudospectral method. The B-plane model is used to increase robustness of the trajectory optimization problem. A Gauss pseudospectral method is applied to the parameterization of the entire trajectory, which inclu...
Article
The poor maneuverability of low lift-to-drag ratio (L/D) vehicles results in low precision of reference-trajectory guidance and difficulty in meeting load constraints. This paper presents an automatic load relief numerical predictor-corrector method for the guidance of low L/D vehicles return from low Erath orbit. By elaborately designing a bank-an...
Article
Full-text available
A long-standing challenge in optimal guidance for orbital insertion of launch vehicles and orbital transfers of spacecraft is how to reduce the transversality conditions in the optimal control problem. The reduction seeks to eliminate the unknown multipliers in the transversality conditions for much improved robustness of convergence and computatio...
Article
The costate along a coast arc on an optimal space trajectory contains critically important information about the trajectory. For free-time fuel-optimal flight, the costate at the start of the coast determines completely the optimal length of the coast. Yet most closed-form solutions for costate under various coordinate systems available in the lite...
Article
Full-text available
The determination of the durations of the coast arcs in optimal finite-thrust, multiple-burn orbital transfer problems is investigated in detail in this paper. The structure of the zeros of the switching function which dictates when to switch from a coast to the next burn is thoroughly analyzed under 3 different ways of treating the gravity in the...
Article
This paper presents numerical enhancements for optimal closed-loop ascent guidance through atmospheric. For 3-dimensional ascent formulation, optimal endo-atmospheric ascent trajectory is numerically obtained by the relaxation approach, and the exo-atmospheric ascent trajectory is generated by an analytical multiple-shooting method. A new root-find...
Conference Paper
This paper presents enhancements for optimal endo- and exo-atmospheric ascent guidance. For 3-dimensional endo-atmospheric ascent, based on analysis of the necessary conditions for the optimal solution, the costate equations are formulated differently as compared to previous work. This change considerably simplifies the vector costate equations, an...
Article
Full-text available
This paper is concerned with theoretical and algorithmic development for fast generation of optimal launch ascent trajectories through the atmosphere and guidance, particularly in highly constrained missions. The theoretical investigation offers an insight into what may be called atmospheric primer vector theory, in which the critical roles of the...
Conference Paper
This work presents a preliminary study on autonomous guidance of deorbit maneuvers. The problem is for a vehicle to autonomously execute a minimum-fuel, finite-time deorbit maneuver that achieves desired entry interface conditions. Many issues, such as impulse versus finite-time burn, single versus multiple-burn deorbit, apogee and non-apogee deorb...
Conference Paper
This paper revisits the challenging problem of optimal rocket powered trajectory consisting of many burn and coast arcs in space. The problem is formulated as a series of N pairs of coast and finite-time burn arcs. The numerical solution to this problem is obtained by an analytical multiple shooting method. A major focus of this work is the treatme...
Conference Paper
This paper describes rapid prototyping of a guidance and control system for missiles to improve its overall design process eectiveness. A rapid prototyping design process is developed based on MATLAB/Simulink/RTW and Skyfly. An air-to-surface missile is used as a design example. A high fidelity 6-DOF missile simulation model is built for rapid prot...
Article
The designing ideas of the flight simulation system were analyzed to meet the practical needs of the flight simulation, which presents designing method of assembling, takes the XML (extensible markup language) to store, operate and show the data, takes in the technology of distributed simulation, provides a good user interface, constructs complex s...

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Projects (5)
Project
To develop on-board guidance and control laws with both robustness and real-time ability.