Journal of Guidance, Control, and Dynamics

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ISSN / EISSN : 0731-5090 / 1533-3884
Total articles ≅ 7,759
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Wei Dong, Chunyan Wang, Jianan Wang,
Journal of Guidance, Control, and Dynamics pp 1-15;

In this paper, a distributed three-dimensional (3D) nonsingular cooperative guidance law is designed for multiple missiles with different seeker’s field-of-view (FOV) constraints to achieve salvo attack against a stationary target. The guidance law is derived from an extended biased proportional navigation guidance (PNG). The PNG is augmented by a cooperative guidance term to ensure that times-to-go of the missile group reach consensus in a fixed time before interception. Two auxiliary functions are included into the biased guidance term to guarantee nonsingularity of the guidance law and meet the FOV constraints. The proposed design does not require guidance law switching that is used in some existing biased or multistage guidance designs, which allows for a smooth guidance command. A feasible impact time set is given for the cooperative mission when applying the proposed guidance law. The nonsingularity, FOV constraint satisfaction, and closed-loop stability of the proposed guidance law are theoretically analyzed and proved. Moreover, the criteria for selecting all guidance parameters are provided to facilitate the guidance design. Finally, numerical simulations with comparative studies are conducted to verify the effectiveness of the proposed guidance law and demonstrate the advantages over existing cooperative guidance laws.
Peng Zhao, Heinz Erzberger, Yongming Liu
Journal of Guidance, Control, and Dynamics pp 1-19;

A new method for efficient trajectory planning to resolve potential conflicts among multiple aircraft is proposed. A brief review of aircraft trajectory planning and conflict resolution methods is given first. Next, a new method is proposed that is based on a probabilistic conflict risk map using the predicted probability of conflict with the intention information of the intruders. The risk-map-based method allows the path planning algorithm to simultaneously account for many uncertainties affecting safety, such as positioning error, wind variability, and human errors. Following this, A* algorithm is used to find the cost-minimized trajectory for a single aircraft by considering all other aircraft as intruders. Search heuristic method is implemented to iterate the A* algorithm for all aircraft to optimize the trajectory planning. Convergence and computation efficiency of the proposed method are investigated in detail. Numerical examples are used to illustrate the effectiveness of the proposed method under several important scenarios for air traffic control, such as wind effects, non-cooperative aircraft, minimum disturbance of pilots, and deconflict with flight intent information. Several conclusions are drawn based on the proposed method.
, Yusuke Oki, Yuichi Tsuda
Journal of Guidance, Control, and Dynamics pp 1-23;

The orbital motion of spacecraft around asteroids is strongly disturbed primarily because of solar radiation pressure (SRP) and higher-order gravitational forces. To achieve stable orbits in such an environment, the implementation of frozen orbits is a promising approach. This research derives semi-analytical solutions of frozen orbits subject to SRP and zonal gravity up to the fourth order based on singly averaged Lagrange planetary equations. Moreover, the stability of frozen orbits is characterized analytically by introducing linearized variational equations, revealing the complex eigenstructures of the proposed frozen orbits. These analytical theories identify several different types of stable frozen orbits, which are further validated via high-fidelity numerical simulations. Consequently, this paper demonstrates the feasibility and intriguing dynamic characteristics of frozen orbits around asteroids.
Hugo Fournier, Paolo Massioni, Minh Tu Pham, Laurent Bako, Robin Vernay, Michele Colombo
Journal of Guidance, Control, and Dynamics pp 1-15;

This work concerns the problem of gust load alleviation of a flexible aircraft by focusing on Airbus’s XRF1 aircraft concept, with a fully actuated wing. The aircraft is equipped with a lidar sensor, which measures the wind velocity ahead of it, together with standard sensors. Based on the available measurements, controllers are then designed by H∞ and μ syntheses, with emphasis put on the multiple-input multiple-output robustness in order to reduce a selected set of loads due to the wind, hence potentially saving mass in the aircraft design. A state-space model of the flexible aircraft is obtained by means of an aeroelastic computation and system identification from frequency data. The controllers’ performance is evaluated through their capability to reduce shear force, bending, and torsion moments on different locations of the aircraft in response to different types of discrete gusts and continuous turbulence; the constraints of the sensors and the actuators are taken into account. The gain in performance due to the use of lidar is assessed, and a tradeoff is discussed concerning the optimal measurement distance. Finally, the closed-loop robustness is assessed by simulations where different types of uncertainties are applied to the system.
Tao Fu, Yue Wang
Journal of Guidance, Control, and Dynamics, Volume 44, pp 1607-1620;

Orbiting the primary of a binary asteroid system is extremely challenging due to the perturbative effects of the primary’s nonspherical gravity and the secondary’s close-proximity third-body gravity. In this work, the stability of perturbed Keplerian orbits around the primary is investigated from the point of view of the long-term eccentricity oscillation. Numerical investigations indicate that the eccentricity undergoes a large-amplitude oscillation, caused by the secular perturbation of the secondary’s gravity and may cause impact. A two-degree-of-freedom dynamic model is established, based on the doubly averaged, semi-analytical orbital dynamics incorporating effects of the primary’s oblateness and the secondary’s nonspherical third-body gravity. The oscillation of eccentricity, including its phase and amplitude, and its dependence on initial orbital geometry, is investigated through the phase space structure. The results can reveal the origin of the instability, predict stable and unstable regions in the space of orbital elements, and determine the initial orbital geometry that can ensure the secular stability. The binary asteroid system 2003 YT1 is used as an example to present our verifications and analyses, and the results can also be applied to other binary asteroid systems and even planetary systems with the central body’s oblateness and the third-body gravity dominating the perturbative environments.
Simon Shuster, David Geller, Matthew Harris
Journal of Guidance, Control, and Dynamics, Volume 44, pp 1593-1606;

This paper presents an analytic solution for a three-impulse maneuver sequence that reconfigures safety ellipses. Safety ellipses are relative motion trajectories that do not require thrusting to ensure a high probability of short-term collision avoidance. Primer vector theory is used to derive analytic expressions that relate the necessary conditions for optimality to properties of the initial and final safety ellipses. The primer vector analysis is validated numerically using convex optimization and Monte Carlo methods. A general passive safety parameter for relative motion trajectories in near-circular orbits is also introduced. It is shown that for practical safety ellipse reconfiguration scenarios, the maneuver sequence generates optimal transfer trajectories that also remain passively safe.
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