Design and application of solar sailing: A review on key technologies

Solar sail technology has been proposed and developed for space explorations with advantages of low launch cost, no-propellant consumption, and continuous thrust, which has great potentials in earth polar detection, interstellar explorations and etc. The development of solar sail has made significant progress in structural design, manufacturing, materials, orbit transfer, and stability control in the past few decades, which makes meaningful contributions to astronomy, physics, and aerospace science. Technological breakthroughs of Solar Radiation Pressure (SRP) propulsion and interstellar transfer have been achieved in current solar sail missions. However, there are still many challenges and problems need to be solved. This paper attempts to summarize the research schemes and potential applications of solar sailing in space missions from the viewpoint of key technologies, so as to provide an overall perspective for researchers in this field. Analyses of the key technologies of solar sailing system design are provided. Finally, challenges and prospective development of solar sailing are discussed.     

新型高速单粒子翻转自恢复锁存器设计

航天器中芯片工作时钟频率的不断提高使得单粒子翻转(single-event-upset,SEU)效应对时序逻辑的影响更加显著。目前已经提出的辐射加固锁存器存在面积和延时较大、功耗较高且抗单粒子翻转能力有限的问题。针对这些问题，提出了一款基于130nm部分耗尽绝缘体上硅(partially-depleted silicon on insulator,PD SOI)工艺的高速单粒子辐射自恢复锁存器。在对电路设计进行介绍的基础上，与其他已经报道的电路进行了对比，并利用节点翻转分析和仿真波形验证了该锁存器具有抗单粒子翻转自恢复的功能。对比结果表明，与其他的抗单粒子翻转自恢复锁存器相比，在牺牲部分功耗的代价下，大幅减小了锁存器的面积和延时。本方案所提出的辐射加固锁存器的综合开销指标APDP较其他辐射加固锁存器平均节省了71.14%，适用于辐射环境下的对速度和可靠性有较高要求的电路，为国产宇航高可靠自研芯片提供了选择。     

Novel orbit-attitude combination mode for solar power satellites to reduce mass and fuel

Solar power satellite receives great attention because it can release the energy crisis and environmental problems in the future. However, the launch and maintenance costs are tremendous due to the large system mass and large fuel consumption to counteract space perturbations. To reduce mass and fuel, a novel quasi-Sun-pointing attitude in Sun-frozen orbit is proposed. The Sun-frozen orbit has a nonzero eccentricity vector that always points towards the Sun. The quasi-Sun-pointing attitude is a periodic solution of the Sun-pointing attitude angle. Although about 3 % electricity must be given up because of the variation of Sun-pointing attitude angle, little control action is required to deal with the solar radiation pressure and gravity-gradient torque. The algorithm to obtain initial conditions is proposed. The influences of system parameters and structural flexibilities are studied. Simulation results reveal that the quasi-Sun-pointing attitude in Sun-frozen orbit dramatically reduce fuel consumption, the dry mass, and complexity of the control system. In addition, structural vibration is hardly induced by the gravity-gradient torque. Thus, the bending stiffness as well as the mass of the supporting structure can be reduced.     

航空发动机热电偶传感器稳态测温偏差分析

为了满足航空发动机上高温、高压、高来流马赫数的恶劣工作环境下的使用需求，对某型航空发动机上选用的低压涡轮后热电偶传感器开展热风洞校准试验及测温准确性分析,明确热电偶传感器测温偏差的影响因素，并通过一种基于表面传热系数推导公式的测温偏差修正方法对校准结果进行计算验证，结果表明，计算方法合理可行，计算结果与测量结果一致性良好，在全部试验点偏差量均小于0.6%。针对现有校准设备无法完全模拟航空发动机真实工况的问题，对校准结果进行修正计算，修正计算结果与真实气流温度偏差在0.7%以内，传感器的稳态测温偏差能够满足在该型航空发动机上的使用需求。     

深空辐射环境对高吸收率消杂光涂层的性能影响

为了研究深空辐射环境对SCB-1型空间高吸收率消杂光涂层的太阳光谱吸收性能影响。采用5 000 ESH剂量的真空-紫外、2.5×10¹⁵ p/cm²注量的真空-质子和2.5×10¹⁶ e/cm²注量的真空-电子依次对SCB-1消杂光涂层进行串联辐照试验，分析各项辐照试验前后消杂光涂层外观、太阳吸收比α_s及半球发射率ε_H的变化情况。并采用热失重分析（Thermal Gravity Analysis）判断消杂光涂层受辐照试验后的分解情况与热稳定性变化。经串联辐照试验后，SCB-1消杂光涂层全波段太阳吸收比总变化值Δα_s下降了0.011~0.012，400~1 100 nm波段太阳吸收比总变化值Δα_s下降了0.011~0.013，以上三项串联辐照过程中SCB-1消杂光涂层的半球发射率总变化值Δε_H无明显变化。SCB-1消杂光涂层呈现了极佳的深空辐射环境下的消杂光持久性，可对未来深空探测领域的光学技术发展提供有力支持。     

Solar sail attitude control using shape variation of booms

Active attitude control of solar sails is required to control the direction of the force generated by Solar Radiation Pressure (SRP). It is desirable to control the attitude through propellant-free means. This paper proposes a new method for attitude control of solar sails: A boom consisting of “smart” structural material can be deformed by the piezoelectric actuator, and Solar Radiation Pressure torque will be generated due to shape variation of sail membrane caused by boom deformation. The method has the advantages of simple structure, small disturbance and small additional load, and is not limited by the size of the solar sail. The case of rendezvous with the Asteroid 2000 SG344 is used to verify the attitude control around the pitch and yaw axes.     

宽温度范围大口径高精度变温标准黑体辐射源研制

红外成像探测系统的应用环境越来越复杂，工作适应温度范围低温可达到-50 ℃以下，高温可达到70 ℃以上。为满足相应要求，研制宽温度范围大口径高精度变温标准黑体辐射源，采用细分均匀加热、模糊PID自整定控制算法、双路配气保护等技术，满足高低温需求，同时开展腔型设计、超黑高发射率涂层等相应研究，保证了黑体辐射源的整体性能，确保完成相应功能。研制完成后，在高低温环境下进行了验证试验，可达到以下指标：有效发射率≥0.999，空腔开口直径≥60 mm，温度测量不确定度10 mK（k=2）。经验证，可满足宽温度范围条件红外探测系统的计量要求。     

铝锂合金曲面件超低温成形工艺

针对铝锂合金室温成形性差和热成形性能弱化的难题,利用发现的超低温下伸长率与硬化指数同时提高的双增效应,提出铝锂合金曲面件超低温成形新工艺。通过2195铝锂合金板材在不同温度和热处理状态下的超低温变形行为研究,确定发生双增效应的临界温度为低于-140℃,伸长率可提高至40%以上、硬化指数达到0.44;利用建立的超低温成形工艺实验装置,首次试制出直径200 mm的2195铝锂合金球底曲面件,深径比达到0.55、成形极限提高104%;阐明超低温成形试件壁厚分布规律与回弹规律,最大减薄率为10.3%。