重力梯度稳定小卫星的最优主动磁控和动量轮控制

为了提高小卫星定点精度,姿态控制系统采用俯仰轴动量轮控制和三轴磁力矩控制。用四元数方法建立起卫星动力学方程和运动学方程。以响应时间和响应时间内欧拉角误差和角速率误差的平方和这两个单目标作为目标函数,以三轴的位置增益、速率增益和卸载增益为设计变量,以三轴欧极子矩不超过要求值,俯仰轴的轮动量矩不超过要求值,以及末尾响应时间内应保证欧拉角和角速率逼近控制值为约束条件,建立起卫星最优控制模型。最后,作为例子应用到小卫星姿态控制中,结果证实最优控制算法是可行有效的。与传统PD控制相比,优化后的姿态控制性能也大大提高。     

Optimal motion cueing algorithm for accelerating phase of manned spacecraft in human centrifuge

This paper presents a novel optimal Motion Cueing Algorithm (MCA) to control the rotations of a Human Centrifuge (HC) and achieve the best simulation of a SpaceCraft (SC) motion. Relations of the specific forces sensed by astronauts of the SC and the HC have been derived and linearized. A Linear Quadratic Regulator (LQR) controller is implemented for the problem which tends to minimize the error between the two sensed specific forces as well as control input in a cost function. It results in control inputs of the HC to generate its sensed specific force as close as possible to the one in the SC. The algorithm is implemented for both linearized and nonlinear portions of a US space shuttle mission trajectory as a verification using MATLAB. In longitudinal direction, the proposed MCA, works well when the acceleration is less than 2g in which the tracking error does not exceed 12%. In lateral direction the tracking is much better even in nonlinear region since the error remains less than 7% for tilting up to 50°. Finally, the effect of weight matrixes in the LQR cost function on overall weight and power of the HC motion system is discussed.     

Robust control for constant thrust rendezvous under thrust failure

A robust constant thrust rendezvous approach under thrust failure is proposed based on the relative motion dynamic model. Firstly, the design problem is cast into a convex optimization problem by introducing a Lyapunov function subject to linear matrix inequalities. Secondly, the robust controllers satisfying the requirements can be designed by solving this optimization problem.Then, a new algorithm of constant thrust fitting is proposed through the impulse compensation and the fuel consumption under the theoretical continuous thrust and the actual constant thrust is calculated and compared by using the method proposed in this paper. Finally, the proposed method having the advantage of saving fuel is proved and the actual constant thrust switch control laws are obtained through the isochronous interpolation method, meanwhile, an illustrative example is provided to show the effectiveness of the proposed control design method.     

脉冲爆震火箭发动机同轴喷注器实验研究

为了使液态燃料在脉冲爆震火箭发动机爆震室内形成雾化均匀的小液滴,并且与气态氧化剂掺混后形成空间分布均匀的混合气,设计了适用于脉冲爆震火箭发动机的气液同轴剪切式喷注器。实验研究了三种喷注器结构对脉冲爆震发动机工作过程的影响,结果表明,采用同轴剪切式喷注器的脉冲爆震发动机在20Hz能够产生稳定、连续和充分发展的爆震波。实验中发现,在同时满足雾化良好以及爆震室填充均匀的条件下,喷注器的出气口存在一个最佳面积,实验研究中喷注器出气口的最佳直径在12mm左右。     

Survey of orbital dynamics and control of space rendezvous

Rendezvous orbital dynamics and control （RODC） is a key technology for operating space rendezvous and docking missions. This paper surveys the studies on RODC. Firstly, the basic relative dynamics equation set is introduced and its improved versions are evaluated. Secondly, studies on rendezvous trajectory optimization are commented from three aspects： the linear rendez- vous, the nonlinear two-body rendezvous, and the perturbed and constrained rendezvous. Thirdly, studies on relative navigation are briefly reviewed, and then close-range control methods including automated control, manual control, and telecontrol are analyzed. Fourthly, advances in rendezvous trajectory safety and robust analysis are surveyed, and their applications in trajectory optimization are discussed. Finally, conclusions are drawn and prospects of studies on RODC are presented.     

Optimal guidance of extended trajectory shaping

To control missile＇s miss distance as well as terminal impact angle, by involving the timeto-go-nth power in the cost function, an extended optimal guidance law against a constant maneuvering target or a stationary target is proposed using the linear quadratic optimal control theory.An extended trajectory shaping guidance（ETSG） law is then proposed under the assumption that the missile-target relative velocity is constant and the line of sight angle is small. For a lag-free ETSG system, closed-form solutions for the missile＇s acceleration command are derived by the method of Schwartz inequality and linear simulations are performed to verify the closed-form results. Normalized adjoint systems for miss distance and terminal impact angle error are presented independently for stationary targets and constant maneuvering targets, respectively. Detailed discussions about the terminal misses and impact angle errors induced by terminal impact angle constraint, initial heading error, seeker zero position errors and target maneuvering, are performed.     

交会对接组合体热管理研究

组合体热管理是实现目标飞行器和载人飞船交会对接组合体载人热环境控制的重要手段。文章提出了以舱段间通风为技术途径的交会对接组合体热管理方案。在组合体热特性分析和热平衡试验基础上,获得了组合体热管理系统分析模型。分析结果表明,组合体密封舱空气温度在19～26℃范围内可调,验证了交会对接组合体热管理设计的正确性。最后,对空间...     

Comparison of computational and experimental results in vibroacoustic active control using piezoelectric film technology

The present investigation concerns control of far-field acoustic radiation generated by a thin plate in a broad frequency band using piezoelectric films. System dynamics is of modal nature.This paper describes a comparison of numerical and experimental results for a closed loop type control. This comes from Optimal Control Theory via radiation filter causal transformation based on a dissipative criterion.     

Optimal multi-site selection for a PV-based lunar settlement based on a novel method to estimate sun illumination profiles

Recently, space organizations have considered the Moon to host lunar bases. Such bases require power and energy to function. However, the efficient and safe use of the energy resources on the Moon is a huge challenge. Space photovoltaic (PV) power systems are appealing technologies due to their maturity and high solar energy availability at some locations on the Moon. The effectiveness of these PV systems depends on their selenographic location, which might necessitate the deployment of energy storage technologies to cover the base’s energy demand. Some analysts have proposed the installation of PV modules on kilometers-tall towers near the lunar poles to harvest more solar energy and limit the need for energy storage systems (ESSs). Alternatively, this paper proposes to harvest the energy from multiple sites in the lunar South Pole region using a novel technique to compute the Sun illumination profile and the LOLA topographic databases to compute the terrain elevations. The proposed algorithm seeks the most optimal configuration of sites and tower heights to minimize the longest night period and total distance between the sites. This study assesses groups of 1 to 6 sites assuming the use of towers having heights of 10, 100, and 500 [m]. The time horizon for the analysis is one Axial Precession Cycle, which is approximately 18.6 years. According to the results, a system of two sites with a separation of 42.05 [km] and towers of 500 [m] height has a maximum darkness period of only 3 [h] while another solution proposes a system of three sites with towers of 10 [m] that removes the need of EES (solar eclipse periods by the Earth are not considered). The proposed technique is suitable for engineering applications, such as base planning and operation management.     

交会对接任务故障与应急仿真系统设计与实现简

为了模拟交会对接任务多目标情况下的航天测控故障与应急过程,建立系统级的故障仿真和综合性的应急处置效能评估环境,采用分布式、支持互操作的高层体系结构,研究了故障SPR柔性描述技术,设计了基于脚本引擎驱动的故障协同演练控制方法,实现了故障建模、存储、提取和组装全过程的规范化,实现了故障的操作控制、效果监视和处置评估的一体化.解决了我国重大空间工程地面故障仿真、应急过程演练和人员训练的技术难题,经受了3次交会对接任务的重大工程应用考验.