用于推进的驻定斜爆轰的基本特征

基于驻定斜爆轰的基本守恒方程、多组元状态方程和考虑化学平衡移动的组元守恒方程，根据本文推导的迭代公式，计算了不同强度的驻定爆轰波后的平衡组分、反应热和绝热指数，讨论了驻定斜爆轰的基本特点、驻定条件和影响驻定的各种因素。     

姿控发动机内流场及高空羽流流场的DSMC一体化数值模拟

通过引入“平衡抽样方法”有效解决了DSMC求解近连续流区所遇到的碰撞顶计算效率问题;对于过渡流及自由分子流区,构造了适合于DSM仿真的分子碰撞传能模型并配置了一种光滑过渡以减少误差的权函数。在此基础上首次实现了对姿控发动机喷管内流场及包括倒流区在内的高空弱流流场的DSMC方法一体化数值模拟。     

Io’s Atmosphere and Surface-Atmosphere Interactions

Our knowledge of Io’s atmosphere has improved dramatically in the last fifteen years, with a wealth of new observational data at millimeter, UV and IR wavelengths, and the development of numerous models describing its horizontal and vertical structure, composition, photochemistry and plasma interaction. Io’s atmosphere is dominantly composed of SO2, present mostly at low-tomid latitudes with column densities of a few 1016 cm⁻² and important (factors of 5-10) longitudinal variations. Minor compounds include SO, S₂, and NaCl. Sublimation equilibrium with SO₂ frost and direct volcanic output coexist to maintain Io’s atmosphere against condensation, photolytic and escape losses.     

火星进入气体辐射加热研究进展

针对飞行器进入火星大气时气体辐射加热对防热设计带来不确定性,在简述火星探测和气体辐射研究的发展历程的基础上,对火星进入气体辐射加热研究的进展进行综述。首先,针对火星大气环境描述了气体辐射加热的概念和问题由来。其次,重点综述了近年来火星进入气体辐射加热基础模型的数值和试验研究进展,其中包括：热化学非平衡气体动力学、气体辐射特性和辐射传输的计算模型与方法等数值研究;地面测试设备、试验技术和模拟火星大气环境的气体辐射测量与验证等试验研究。再次,综述了流动辐射耦合和后体气体辐射加热等火星进入器设计方面开展的研究。最后,对未来火星进入气体辐射加热研究进行了展望,提出了研究建议。     

一般均衡模型下的税负归宿研究

税负归宿问题因其复杂的传导机制影响着人们对最终税收负担的判断，在局部均衡分析失效的情况下，一般均衡模型是研究税负归宿的更佳方案。基于经典的Harberger模型，运用线性化和逼近技术，讨论了一般均衡框架下的数量求解算法，得到了特定部门资本和劳动用量以及资本价格的微分值，并以此分析了局部要素税的税负归宿以及最终的税收负担。     

Formation flying for magnetic sails around artificial equilibrium points

This paper investigates the problem of magnetic sail-based spacecraft formation control around the artificial equilibrium points (AEPs), which can eliminate the requirement of the propellant. The thrusts are achieved by utilizing the interaction between the solar wind and the artificial magnetosphere generated by superconducting current coil onboard. The circular restricted three-body problem (CRTBP) of magnetic sail is discussed including the allowed regions and linear stability of AEPs, the locations of collinear AEPs and the possibility of existence of periodic orbits around the collinear AEPs. Next, the dynamical models of magnetic sail formation around the collinear AEPs are established. A novel fast fixed-time nonsingular terminal sliding mode controller (FFNTSM) based on fixed-time disturbance observer (FTDO) is developed to account for external disturbances. Several numerical simulations are conducted to substantiate that spacecraft formation can be precisely controlled by the proposed propellantless propulsion method in the presence of external disturbances.     

Stability and shape analysis of relative equilibrium for three-spacecraft electromagnetic formation

The invariant shapes for close formation flying with inter-craft electromagnetic force ensure several potential space applications. However, the 6-DOF relative equilibrium problem has not been systematically investigated. This paper mainly analyzes the invariant shapes of relative equilibrium for the three-spacecraft electromagnetic formation, and studies the families of invariant shape solutions with real and constant magnetic moments as well as their linear stability. The problem is examined based on the full nonlinear coupled dynamic models for collinear and general triangular configurations. The relative equilibrium conditions are analyzed to determine whether an invariant shape do exist, and the corresponding families of invariant shape solutions are identified for static and spinning configurations respectively. Finally, the linear stability of such invariant shapes is numerically discussed, which have shown that most invariant shapes are unstable and controllable.     

基于计算博弈的脉冲作用下航天器追逃策略

本文研究了地球高阶引力模型中,基于脉冲作用的航天器轨道追逃问题。针对该问题,将航天器轨道追逃问题定义为两选手计算博弈,其中以博弈双方的距离和燃料消耗设计了性能指标函数,并以速度增量大小和方向构建容许控制集。此外,为了保证纳什均衡解的求解效率,引入了快速搜索(ARS)算法,并设计了一种数据剪枝方法用于优化搜索空间,最终实现了基于计算博弈的控制策略的快速求解。仿真结果表明:该方法能够有效解决脉冲作用下航天器的追逃难题,与传统方法相比,该方法能同时满足脱靶量精度和燃料消耗要求,具有一定的可行性和有效性。     

带座舱飞船高超声速再入非平衡流场的数值研究

本文针对带座舱飞船高超声速再入大气层过程中存在的严重气动加热现象 ,利用简单隐式TVD差分格式和激波捕捉法 ,数值求解三维化学非平衡Navier Stokes方程 ,其中化学模型是 7组分 1 5个化学反应的空气化学模型 ,对带座舱飞船再入高度为 70km和速度为6 7km/s的化学非平衡流场进行了数值模拟 ,给出了带座舱飞船再入迎角为 0°,1 0°和 2 0°情况下的壁面热流、表面压力和电子数密度等参数分布     

Boundary of nighttime ozone chemical equilibrium in the mesopause region: Improved criterion of determining the boundary from satellite data

A modified derivation of the criterion of nighttime ozone chemical equilibrium (NOCE) in the mesopause region is presented. According to 3D model calculations, the improved criterion reproduces the lower boundary of the equilibrium much better than its earlier version. Processing of the SABER/TIMED data of 2021 has shown that the modified criterion elevates the NOCE boundary by ～ 0.1–1.7 km, depending on latitude and season. The proposed method of determining the condition of chemical equilibrium can be used to analyse the equilibrium of many trace gases in the stratosphere and troposphere important for different practical applications.