基于固态功率控制器的器载配电器的BIT设计技术研究[BT)]

航空航天飞行器发展迅速,用电设备数量增多,飞行任务复杂性增大,对飞行器配电系统的智能程度以及可靠性提出更高要求。配电器是配电系统的核心设备,为飞行器所有用电负载设备分配电能,其性能的优劣直接影响到飞行任务的成败,BIT（Built-In Test）技术是一种能够显著改善系统或设备测试性能和诊断能力的重要手段。研究了以固态功率控制器为核心器件的配电系统总体方案,对固态功率控制器的故障模式与测试方法进行了分析,给出了测试点设计和优选方法,通过故障诊断能力计算结果表明BIT设计技术可提高配电系统的可靠性和智能化程度。     

Variations of the flux and the energy spectrum of neutrons born in the galactic cosmic ray proton interactions with the matter of Earth''s satellites and orbital stations

This paper presents the energy spectra of secondary neutrons obtained from Monte Carlo simulations of the interactions of protons of galactic cosmic rays with the material of a spacecraft, and also the variation of the fluxes of these particles as a function of latitude. The variations of the secondary neutron flux with changing geometry and orientation of the craft, and detector position were evaluated as well. The simulations were conducted over a wide range of masses of spacecraft, from 300 kg (Earth Probe Total Ozone Mapping Spectrometer) to 420,000 kg (International Space Station in its full configuration), with calculations for the ISS also being carried out for its first development stage (mass of approx. 20,400 kg) and its configuration with a mass of approx. 81,000 kg. The calculations were carried out for circular orbits at altitudes of 500 km and for the energy intervals 0.001–10 MeV and 10–10,000 MeV, for both maximum and minimum solar activity. The results obtained agree reasonably well with results from previous calculations and do not contradict experimental data.     

Singularly perturbed feedback linearization with linear attitude deviation dynamics realization

A new approach for feedback linearization of attitude dynamics for rigid gas jet-actuated spacecraft control is introduced. The approach is aimed at providing global feedback linearization of the spacecraft dynamics while realizing a prescribed linear attitude deviation dynamics. The methodology is based on nonuniqueness representation of underdetermined linear algebraic equations solution via nullspace parametrization using generalized inversion. The procedure is to prespecify a stable second-order linear time-invariant differential equation in a norm measure of the spacecraft attitude variables deviations from their desired values. The evaluation of this equation along the trajectories defined by the spacecraft equations of motion yields a linear relation in the control variables. These control variables can be solved by utilizing the Moore–Penrose generalized inverse of the involved controls coefficient row vector. The resulting control law consists of auxiliary and particular parts, residing in the nullspace of the controls coefficient and the range space of its generalized inverse, respectively. The free null-control vector in the auxiliary part is projected onto the controls coefficient nullspace by a nullprojection matrix, and is designed to yield exponentially stable spacecraft internal dynamics, and singularly perturbed feedback linearization of the spacecraft attitude dynamics. The feedback control design utilizes the concept of damped generalized inverse to limit the growth of the Moore–Penrose generalized inverse, in addition to the concepts of singularly perturbed controls coefficient nullprojection and damped controls coefficient nullprojection to disencumber the nullprojection matrix from its rank deficiency, and to enhance the closed loop control system performance. The methodology yields desired linear attitude deviation dynamics realization with globally uniformly ultimately bounded trajectory tracking errors, and reveals a tradeoff between trajectory tracking accuracy and damped generalized inverse stability. The paper bridges a gap between the nonlinear control problem applied to spacecraft dynamics and some of the basic generalized inversion-related analytical dynamics principles.     

De-wrinkling of pre-tensioned membranes

Thin membranes are used in the spacecraft industry as extremely lightweight structural components. They need to be stiffened, usually by applying discrete forces, and this increases their susceptibility to wrinkling in regions where high tensile stresses develop. We consider a regular polygonal membrane uniformly loaded at its corners by equal forces and we prevent wrinkle formation by trimming the edges of the polygon into very gentle curves. We confirm this performance through simple physical experiments using Kapton, a typical membrane material and, using computational analysis, we show how the distribution of compressive stresses, responsible for causing wrinkles, dissipates following trimming. Finally, we accurately predict the required level of trimming for any number of sides of polygon using a simple, linear model, which invokes a plate-bending analogy.     

Analytical solution of attitude motion for spacecraft with a slewing appendage

This paper investigates pitch motion and in orbital plane elastic vibration of a spacecraft with a flexible beam type appendage undergoing prescribed slew maneuver. The governing equations are transformed into a standard quasi-linear form, and then solved by Butenin's variation of parameters approach. Validity of the analytical solutions is assessed over a range of system parameters and initial conditions by comparing them with the results of numerical integration. The results show that they are very good approximations and provide extensive insight into the dynamical response of the system.     

An improved nonlinear control strategy for deep space formation flying spacecraft

This paper aims to provide further study on the nonlinear modeling and controller design of formation flying spacecraft in deep space missions. First, in the Sun-Earth system, the nonlinear formation dynamics for the circular restricted three-body problem （CRTBP） and elliptic restricted three-body problem （ERTBP） are presented. Then, with the Floquet mode method, an impulsive controller is developed to keep the Chief on the desired Halo orbit. Finally, a nonlinear adaptive control scheme based on Nonzero set- point LQR and neural network is proposed to achieve high precision formation maneuver and keeping. The simulation results indicate that the proposed nonlinear control strategy is reasonable as it considers not only the orbit keeping of the Chief, but also the formation modeling inaccuracy. Moreover, the nonlinear adaptive control scheme is effective to improve the control accuracy of the formation keeping.     

航天器多层绝热材料的非稳态传热分析

根据反射屏能量平衡建立了多层绝热材料的非稳态传热方程。以双面镀铝涤纶薄膜为研究对象,在不进行预处理、表面印花处理两种实验条件下,得到了绝热材料中各反射屏温度随航天器飞行过程中的具体数值变化规律。最后,在特定的两个时刻分析了绝热材料的当量热导率及其分量,发现残留气体导热约占70%。     

Chaotic attitude motion of a magnetic rigid spacecraft and its control

This paper deals with chaotic attitude motion of a magnetic rigid spacecraft with internal damping in a circular orbit near the equatorial plane of the earth. The dynamical model of the problem is established. The Melnikov analysis is carried out to prove the existence of a complicated non-wandering Cantor set. The dynamical behaviors are numerically investigated by means of time history. Poincare map, power spectrum and Lyapunov exponents. Numerical simulations indicate that the onset of chaos is characterized by the intermittency as the increase of the torque of the magnetic forces and decrease of the damping. The input-output feedback linearization method is applied to control chaotic attitude motions to the given fixed point and periodic motion.     

Evolution of morphologic properties on the preparation of Ir/Al2O3 catalysts with high metallic contents

Ir/Al₂O₃ catalysts with high metallic contents are applied on satellite thruster to decompose hydrazine. The present work has as principal aim the study of the morphologic evolution of Ir/Al₂O₃ catalysts with metallic contents from 12 to 30 wt.%. The catalysts were prepared through consecutive impregnations from the H₂IrCl₆ precursor, using three different types of aluminas. The specific surface area, volume and distribution of pore size, specific metallic area and metallic particles average diameter, as well as the mechanical resistance were determined. Results show that the Ir addition leads to a decrease of the specific surface area and the pores volumes, while increases the mechanical resistance. Values for average diameter of metallic particles are comprised between 1.4 and 2.4 nm when the metallic content increases from 12 to 30 wt.%. Catalysts containing 30 wt.% of Ir presents specific metallic areas around 30 m²/g, although pores volumes and distributions of pore size were considerably different for the three supports. Their metallic particles dispersion and size values are very close to those of a commercial catalyst Shell 405, even though the preparation methods were different. These results show that there is a strong interaction between the alumina and the iridium precursor.     

The Method of Averaging for Euler's Equations of Rigid Body Motion

We formulate the method of averaging for perturbations of Euler's equations of rotational motion. Euler's equations are three strongly nonlinear coupled differential equations that can be viewed as a three dimensional oscillator. The method of averaging is used to determine the long-term influence of perturbation terms on the motion by averaging about the nominal rigid body motion. The treatment is applicable to a large class of motions including precession with large nutation – it is not restricted to small motions about simple spins or nearly axi-symmetric bodies. Three examples are shown that demonstrate the accuracy of the method's predictions.