The present status and prospects in the research of orbital dynamics and control near small celestial bodies

Small celestial body exploration is of great significance to deep space activities. The dynamics and control of orbits around small celestial bodies is of top priority in the exploration research. It includes the modeling of dynamics environment and the orbital dynamics mechanism. This paper introduced state-of-the-art researches, major challenges, and future trends in this field. Three topics are mainly discussed: the gravitational field modeling of irregular-shaped small celestial bodies, natural orbital dynamics and control, and controlled orbital dynamics. Finally, constructive suggestions are made for China's future space exploration missions.     

超大型航天结构动力学与控制的保辛方法

超大型航天器是空间资源探索和利用的重要空间基础设施,也是实现航天强国目标的重大战略性航天装备。由于这类结构的质量和尺寸巨大,将带来在轨运行中的姿-轨-结构耦合和在轨姿态控制问题。同时,结构的超大尺度、构型变化与空间环境相互作用将产生极复杂的结构振动和大型结构特有的波动现象。这些为其动力学建模与数值求解、在轨精确姿态控制、低频结构振动抑制和振动波动耦合的特性调控等提出了新的挑战。本文介绍了本团队近十年基于保辛方法针对上述问题取得的研究进展,包括超大型航天结构在轨耦合动力学与姿态控制、超大型航天结构波动力学行为与控制、可展开结构设计以及变刚度主动控制方法等。     

The optimal control variational principle and finite elements analysis for viscoplastic dynamics

This paper presents the optimal control variational principle for Perzyna model which is one of the main constitutive relation of viscoplasticity in dynamics. And it could also be transformed to solve the parametric quadratic programming problem. The FEM form of this problem and its implementation have also been discussed in the paper.     

空间机械臂捕获卫星过程的碰撞动力学模拟及镇定运动的鲁棒控制

讨论了漂浮基空间机械臂捕获未知运动目标卫星的接触碰撞动力学建模和接触碰撞后系统镇定运动的控制问题。利用第二类拉格朗日方法和牛顿-欧拉法分别建立了接触碰撞前漂浮基空间机械臂和目标卫星两分体系统的动力学模型;以此为基础借助于空间机械臂与目标卫星接触点间的运动几何关系、力传递关系,计算了接触碰撞所产生的影响效应;捕获卫星后,联立空间机械臂与卫星接触碰撞前的动力学模型,建立了接触碰撞后两系统组合体动力学模型;并设计了增广鲁棒控制算法,以对受碰撞冲击后处于不稳定的组合体系统进行镇定运动控制。上述控制方法能应用于空间机械臂载体位置不受控情况,并能使组合体系统控制方程关于卫星不确定参数呈线性化关系。最后,利用数值仿真模拟捕获过程系统运动状态,验证了上述鲁棒控制镇定运动的效果。     

Analytical solutions for dynamics of dual-spin spacecraft and gyrostat-satellites under magnetic attitude control in omega-regimes

The attitude dynamics of a dual-spin spacecraft (a gyrostat with one rotor) with magnetic actuators attitude control is considered in the constant external magnetic field at the presence of the spacecraft’s own magnetic dipole moment, which is created proportionally to the angular velocity components (this motion regime can be called as “the omega-regime” or “the omega-maneuver”). The research of the dual-spin spacecraft angular motion under the action of the magnetic restoring torque is fulfilled in the generalized formulation close to the classical mechanics’ task of the heavy body/gyrostat motion in the Lagrange top. Analytical exact solutions of differential equations of the motion are obtained for all parameters in terms of elliptic integrals and the Jacobi functions. New obtained analytical solutions can be classified as results developing the classical fundamental problem of the rigid body and gyrostat motion around the fixed point. The technical application of the omega-regime to the angular reorientation of the spacecraft longitudinal axis along the angular momentum vector is considered.     

Impact dynamics analysis of free-floating space manipulator capturing satellite on orbit and robust adaptive compound control algorithm design for suppressing motion

The impact dynamics, impact effect, and post-impact unstable motion sup- pression of free-floating space manipulator capturing a satellite on orbit are analyzed. Firstly, the dynamics equation of free-floating space manipulator is derived using the sec- ond Lagrangian equation. Combining the momentum conservation principle, the impact dynamics and effect between the space manipulator end-effector and satellite of the cap- ture process are analyzed with the momentum impulse method. Focusing on the unstable motion of space manipulator due to the above impact effect, a robust adaptive compound control algorithm is designed to suppress the above unstable motion. There is no need to control the free-floating base position to save the jet fuel. Finally, the simulation is proposed to show the impact effect and verify the validity of the control algorithm.     

Predictions and observations of the flow field induced by laminar flow control microperforations

Hybrid laminar flow control (HLFC) aims to reduce aircraft skin friction drag by controlling the boundary-layer characteristics through a combination of surface suction and surface profile shaping. Suction is applied through an array of microperforations in the surface; and, to enable HLFC design criteria to be established with confidence, a full understanding of how these suction perforations affect the boundary layer is required. The objective of this paper is to predict the flow field induced by surface suction through single and multiple rows of microperforations, at transonic cruise conditions. A broad range of cases are studied for a variety of geometric and flow configurations by solving the compressible, laminar, Navier-Stokes equations. The geometric parameters considered are perforation diameter, inclination to the surface, and perforation duct profile. The flow parameters consist of the boundary-layer displacement thickness and suction mass flow rate through the hole. From the predictions and analyses of the results, a wide variety of flow field patterns and features are observed; including longitudinal vortices, streamline curvature, large cross-flow velocities, inherently unstable velocity profiles, and a recirculation region at the perforation entrance. The perforation inlet shape is found to have a minimal effect on the induced flow field, but the level of streamwise vorticity is increased for inclined perforations. The size and shape of the sucked stream tube, which is currently used to predict the critical suction velocity, also is determined. For multiple rows of perforations, the flow field characteristics are shown to be influenced by significant interhole effects. The mass flow rate characteristics of microperforations are found to be insensitive to the ratio of hole diameter to boundary-layer displacement thickness. Also, conical bore holes are shown to provide substantial static pressure recovery due to diffusion effects.     

Stochastic minimax semi-active control for MDOF nonlinear uncertain systems under combined harmonic and wide-band noise excitations using MR dampers

A stochastic minimax semi-active control strategy for multi-degrees-of-freedom (MDOF) strongly nonlinear systems under combined harmonic and wide-band noise excitations is proposed. First, a stochastic averaging procedure is introduced for controlled uncertain strongly nonlinear systems using generalized harmonic functions and the control forces produced by Magneto-rheological (MR) dampers are split into the passive part and the active part. Then, a worst-case optimal control strategy is derived by solving a stochastic differential game problem. The worst-case disturbances and the optimal semi-active controls are obtained by solving the Hamilton–Jacobi–Isaacs (HJI) equations with the constraints of disturbance bounds and MR damper dynamics. Finally, the responses of optimally controlled MDOF nonlinear systems are predicted by solving the Fokker–Planck–Kolmogorov (FPK) equation associated with the fully averaged Itô equations. Two examples are worked out in detail to illustrate the proposed control strategy. The effectiveness of the proposed control strategy is verified by using the results from Monte Carlo simulation.