Attitude Tracking Control Reconfiguration for Space Launch Vehicle With Thrust Loss Fault

Abstract

The thrust loss fault of the space launch vehicle is quite different from that of ordinary actuator efficiency loss. Focusing on the attitude tracking control problem of the launch vehicle with thrust loss fault, the special impacts of that fault on the control system are explored, and a two-stage control reconfiguration strategy based on the cascaded pseudo-inverse allocation method and the neuron adaptive gain scheduling method is proposed for faults with different severity. Meanwhile, a practical reconfigurability analysis for the faulty system based on the control state reachability is presented for some representative fault scenarios. Based on the nonlinear dynamical model of the faulty system, lots of numerical simulations under various fault scenarios are finally carried out. The results indicate that the designed control reconfiguration strategy not only can effectively deal with the thrust loss fault with high practicability but also is easy to implement. INDEX TERMS Space launch vehicle, thrust loss fault, control reconfiguration strategy, cascaded pseudo-inverse allocation, neuron adaptive gain scheduling, reconfigurability analysis.

Multistep thrust allocation method based on priority idea for remotely operated underwater vehicle with horizontal thrusters configured as X shape

“…Thrust allocation based on the pseudo-inverse method is really simple, but on the other hand shows some limitations. A well-known problem is that the obtained solution may exceed the maximum thrust of the thrusters, and various measures [13][14][15] have been taken to deal with this problem. Another problem is that the method is designed without considering the actual top-level motion requirements of the ROV.…”

“…Normalization process of inputs is a convenient method to avoid the oversaturation of thrusters, but this method also reduces the utilization rate of the propulsion system. By comparison, redistribution pseudo-inverse method 12,13 and cascade pseudo-inverse method 14 are more superior solutions for dealing with the oversaturation case, which use linear programming to realize the secondary allocation and optimization. Ye et al 15 introduced a weight matrix into the pseudo-inverse method, which can minimize the energy consumption of the propulsion system under many restricted conditions.…”

Online trajectory optimization and guidance algorithm for space interceptors with nonlinear terminal constraints via convex programming

“…A successful space interceptor against these high-speed targets (Yan et al , 2014) such as satellites and ballistic missiles is in great demand. However, the only available way to provide enough thrust and energy for space intercept missions is chemical propulsion and the capacity of strike is seriously limited (Zhang et al , 2019). To achieve the mission with limited consumption and ensure the attack precision, trajectory optimization during the ascent phase is of great importance.…”

Simple Adaptive Control‐Based Reconfiguration Design of Cabin Pressure Control System

“…As a branch of fault-tolerant control, control reconfiguration is widely applied to some safety-critical systems at present, especially in the field of aerospace engineering [12]. e control reconfiguration technology for the control system in the presence of faults is a key way to realize the soft redundancy [13]. It can be divided into active reconfiguration and passive reconfiguration, based on Fault Detection and Identification (FDI) and FDI-free reconfiguration methods [14][15][16].…”