关键词: 角动量管理, 环境力矩, 参数辨识, 深空探测

Abstract: To reduce the jet propulsion system fuel consumption of deep-space micro-nano satellites, extend the intervals between momentum unloadings, and minimize ground management requirements, an online angular momentum identification and autonomous management method for deep-space micro-nano satellites is proposed. This method calculates the optimal attitude bias angle and solar panel rotation angle on orbit in real-time, reasonably manipulates environmental torques, achieving angular momentum accumulation suppression and residual angular momentum unloading. First, the primary environmental torques acting on micro-nano satellites orbiting around deep-space celestial bodies are modeled. The independent environmental parameters within the expressions are extracted and organized, and their integrals over one orbital period are computed to derive the angular momentum accumulation function of the satellite under orbit stable conditions. The trust-region reflective least squares parameter identification method is employed to independently identify the unknown parameters of the angular momentum accumulation function using rotation wheel speed data over a certain orbital period, without relying on the navigation system. Based on this, optimization of the angular momentum accumulation function is performed using barrier function interior-point method, with objectives of minimizing the magnitude of angular momentum accumulation over a single orbital period and optimizing the spatial orientation of angular momentum accumulation. This yields the attitude bias angle and solar panel rotation angle that either minimize angular momentum accumulation or enable environmental torques to unload residual angular momentum, thereby achieving effective utilization of environmental torques. Simulation experiments demonstrate that lunar micro-nano satellites can fully unload angular momentum using this management method without consuming jet propulsion fuel. For Mars small satellites, jet propulsion fuel consumption for angular momentum unloading is reduced to 0.5% of the pre-management level, and the angular momentum accumulation speed is 51% lower than that with traditional management methods. Large-scale targeting simulations indicate that Mars satellites with low orbital altitudes (500~2000 km) and high solar radiation pressure area-to-mass ratios (0.06–0.08 m2/kg) exhibit minimal unresolvable angular momentum and achieve better management outcomes when using the autonomous angular momentum management method.

Key words: angular momentum management, environmental torque, parameter estimation, deep space exploration