This paper focuses on the impulsive orbital pursuit–evasion game (OPEG) with limited action sets for pursuer and evader. Initially, a mathematical model is developed by combining theory dynamics, forming finite-round OPEG problem. The problem then formulated as bilateral optimization problem, employing minimum-maximum index based terminal distance. To tackle this an algorithm tree search designed, enabling determination of optimal strategy sets. Additionally, we explore influence initial...

This study investigates the orbital Target-Attacker-Defender (TAD) game problem in context of space missions. In this game, Attacker and Defender compete for a Target that is unable to maneuver due its original mission constraints. paper establishes three TAD models based on thrust output capabilities: unconstrained output, constrained by an upper bound, fixed magnitude. These are then solved using differential theory obtain Nash equilibrium solutions problems, correctness effectiveness...

This paper conducts a comprehensive study on the nonlinear dynamic modeling of two test masses Drag-Free and Attitude Control System (DFACS) for heliocentric gravitational wave detection missions. First, composition DFACS assumptions are clarified, key reference frames their transformation relationships defined, an innovative approach based formation frame is proposed to characterize geometric constraints among multiple DFACSs. Subsequently, systemic model established, encompassing...

This paper presents a real-time health assessment model for inertial sensors in drag-free satellites, utilizing Bayesian networks. Initially, working of the sensor system satellites is developed. Typical faults across various subsystems are identified and used to construct fault-specific network. Subsequently, fault classification isolation method applied, allowing rapid identification subsystem by comparing actual system's inputs outputs with those predicted physical model. Finally, expert...

This paper deals with the spacecraft relative hovering control problem, which is an important problem of space flight dynamics and one critical aspects satellite motion control. Initially, precise analytic models for active respect to a target both in circular and/or elliptical reference orbit influence perturbation are established. According models, maximum- minimum-force positions under given range determined by well-known optimization technique Lagrange multipliers. In view long-term...

This paper discusses the modeling and solving of orbital pursuit–evasion games (OPEGs) under J 2 perturbation. The optimal long-range maneuver method perturbation is designed, it proved that effect eccentricity can be ignored when transfer times Δ V budgets are fixed. It discovered inclination between initial target orbit equal 10° 25°, whole process simplified to a fixed-inclination transfer. Subsequently, long-term OPEG model provided assumption fixed inclination, zero eccentricity,...

Modeling of the dynamics and disturbances designing precise formation controller are two major problems for inner-formation flying system (IFFS). This paper introduces a nonlinear, nonautonomous model IFFS in general elliptic orbit. integrates newly developed detailed disturbance models, including atmospheric drag, solar radiation pressure, J2 effects. Furthermore, this establishes coupled self-gravitational attraction IFFS. After considering such comprehensive model, control problem is...

This paper proposes an efficient design method for nano satellites formation flying near a large space target to perform ultra-close inspection missions. A parametric model periodic relative motion between two is firstly proposed through detailed analysis of the orbital dynamics. It proved that existing solutions satellite such as in-plane 2:1 elliptic and circular orbits both belong ellipsoid family orbits. The planes their locations orientations general are then determined analytic...

The precise analytic bounds of periodical satellite relative motion are obtained in this paper. To explore the easily, a set algebraic equations applied. In these newly developed equations, tangent value half true anomaly is regarded as restated independent variable. upper and lower coordinates leader local-vertical/local-horizontal frame found by solving partial derivatives with respect to These expressed functions leader's orbital elements element differences follower leader. bounds'...