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	Design, integration, and test of the scientific payloads on-board the HERMES constellation and the SpIRIT mission 期刊论文 OAI收割 SPACE TELESCOPES AND INSTRUMENTATION 2022: ULTRAVIOLET TO GAMMA RAY, 2022, 卷号: 12181, 页码: 121811G 作者: HERMES Collaboration \| 收藏 \| 浏览/下载：17/0 \| 提交时间：2023/11/09 High Energy Astrophysics HERMES SpIRIT CubeSat Payload Space 4.0 Silicon Drift Detectors GAGG ASIC Gamma-ray Bursts
	Rotary Joint Design for High Payload Remote Handling System for a Tokamak Reactor 期刊论文 OAI收割 IEEE TRANSACTIONS ON PLASMA SCIENCE, 2020, 卷号: 48 作者: Bai, Xiaowei; Zhou, Zibo; Wang, Yan; Yao, Damao; Choi, Chang-Hwan \| 收藏 \| 浏览/下载：27/0 \| 提交时间：2020/10/29 Gears Payloads Torque Loading Stress Servomotors Inductors China fusion engineering test reactor (CFETR) cycloid gearbox design requirements high payload remote handling (RH) rotary joint three-stage reducers
	Preparation of Microgels with Ultrahigh Payload of Various Hydrophilic and Hydrophobic Inorganic Nanoparticle Composites up to 92 wt % 期刊论文 OAI收割 ACS APPLIED MATERIALS & INTERFACES, 2019, 卷号: 11, 期号: 4, 页码: 4408-4415 作者: Wang, Anhe; Li, Jieling; Dong, Qianqian; Wang, Shengtao; Jian, Honglei \| 收藏 \| 浏览/下载：71/0 \| 提交时间：2019/04/03 microgel encapsulation high payload nanocomposites "casting" strategy
	Far ultraviolet nighttime ionospheric photometer 期刊论文 OAI收割 ASTROPHYSICS AND SPACE SCIENCE, 2015, 卷号: 355, 期号: 1, 页码: 1-7 作者: Fu, Liping; Peng, Ruyi; Shi, Entao; Peng, Jilong; Wang, Tianfang 收藏 \| 浏览/下载：48/0 \| 提交时间：2015/09/28 FUV optical sensing remote Payload Ionosphere F2 electron density distribution High sensitivity
	Bootstrap loader design of aerospace payload controller based on TSC695F (EI CONFERENCE) 会议论文 OAI收割 2010 2nd International Conference on Computational Intelligence and Natural Computing, CINC 2010, September 13, 2010 - September 14, 2010, Wuhan, China Xu W.; Piao Y. 收藏 \| 浏览/下载：37/0 \| 提交时间：2013/03/25 Anti-radiation TSC695F is usually used as aerospace payload controller in tasks to ensure the aerospace payload having extremely high reliability in abominable space environment. The processor bases on SP ARC V7 architecture with parity check and EDAC so it could design out high reliable bootstrap loader to guarantee the operation system of VxWorks and application codes loaded correctly and worked stable and high effective. First this paper put forward the system hardware composition and boot mode which apply for aerospace payload then it makes clear the related contents of register group initialization stack initialization system hardware initialization in bootstrap loader of TSC695F and give out the method to establish TRAP table. That's all through comparing different type of organize mode of program image. After that compiling of target codes have been described and the kernel code of MakeFile had been given at the same time for reference aimed at the realization of engineering. Although this paper is based on TSC695F but it could be extended to other embedded system based on SP ARC for bootstrap loader analysis and design for example the TSC697 which based on SP ARC V8 with higher performance so this paper has extremely high engineering value. 2010 IEEE.
	Design and analysis of large spaceborne light-weighted primary mirror and its support system (EI CONFERENCE) 会议论文 OAI收割 3rd International Symposium on Advanced Optical Manufacturing and Testing Technologies, AOMATT 2007: Large Mirrors and Telescopes, July 8, 2007 - July 12, 2007, Chengdu, China Yan Y.; Jin G.; Yang H.-B. 收藏 \| 浏览/下载：17/0 \| 提交时间：2013/03/25 With the development of the resolution of spaceborne remote sensor the diameter of the primary mirror of spaceborne telescope becomes larger and larger. The distortion of primary mirror which is influenced by the mirror material structure self-weight support system and temperature environment affects optical image quality finally. In this paper an on-axis TMA high-resolution Cassegrain optical payload with a primary mirror whose diameter is 650mm was designed and the effects of the influence factors of the distortion acts on the on-axis TMA optical system primary mirror had been analyzed by means of Finite Element Analysis. During work the technology of the primary mirror design had been summarized and general consideration of the primary mirror design technology also had been described at the same time. Considering the telescope manufacture and work station a reasonable and optimal structure of the primary mirror sub-assembly is taken finally. In the end the distortion of the primary mirror during its fabrication station and work station had been analyzed by integrated Finite Element Analysis Method. The results implicated the synthesis profile error (P-V value) for the primary mirror is less than /10 and all the indexes of the primary mirror satisfy the requirements of the optical system.