Acta Astronautica
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2.83
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#1Xiangyang Ye (Beihang University)
#2Xueping Xu (Beihang University)
Last. Bangcheng Han (Beihang University)
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Abstract Due to the air gap between stator and rotor, magnetically suspended control moment gyro (MSCMG) should be equipped with locking/unlocking device (LUD) to sustain launch vibration and impact. Current LUDs are not repeatable, reliable and compact enough for gyro applications. In this paper, a repeatable locking/unlocking device (RLUD) with several elastic brackets as clamping/releasing mechanism is proposed. Based on the equivalent beam model, static and dynamic analyses of the brackets a...
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#1Jin YushuH-Index: 2
Last. Lun Pan
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#1Steven G. Tragesser (UCCS: University of Colorado Colorado Springs)H-Index: 4
#2Lluis Umbert (UCCS: University of Colorado Colorado Springs)
Abstract An aerobraking maneuver performed with a tethered system has the benefit of increasing the drag for a given center of mass orbit by dropping the lower subsatellite into the denser atmosphere. While this concept has received significant attention in the literature, the exact means of controlling the attitude prior to the aerobraking fly-through has not been adequately treated. In particular, a scheme for repeated passes in elliptical orbits has not been developed, which would be required...
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#1Haotian Fan (HIT: Harbin Institute of Technology)H-Index: 2
#2Zhiguo Chen (HIT: Harbin Institute of Technology)
Last. Daren Yu (HIT: Harbin Institute of Technology)H-Index: 24
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Abstract Using a permanent magnet to realize a design with a large height-radius ratio can effectively reduce the radial size of the thruster. The experimental results show that a Hall thruster with a large height-radius ratio also has significant advantages in its discharge performance. Taking the 1.35 kW Hall thruster HEP-1350PM, which has a large height-radius ratio, as an example, the thrust, specific impulse, and efficiency of HEP-1350PM are increased by up to 4.3%, 10.4%, and 7%, respectiv...
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#1T. V. Krishna (BIT Mesra: Birla Institute of Technology, Mesra)
#2P. Kumar (BIT Mesra: Birla Institute of Technology, Mesra)H-Index: 3
Last. S.L.N. Desikan (VSSC: Vikram Sarabhai Space Centre)
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Abstract Experiments were carried out to assess the effect of rear face geometrical modifications of a wall mounted rectangular cavity on pressure fluctuations at supersonic speed. Initially, tests were conducted on a base cavity of length to depth ratio of 3.6, in a 50 × 100 mm at a Mach number of 2, and a Reynolds number of 2 × 106 based on cavity length. Geometrical modifications to the rear face of the base cavity in the form of single ramp, double ramp and partial ramp circle were done to s...
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#1Taiki OkinoH-Index: 1
#2Yoshiki YamagiwaH-Index: 7
Last. Kiyotoshi OtsukaH-Index: 3
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Abstract Space elevators studied thus far have been mainly the climber type, in which a cable connects the ground to a space station and the payload is transported by climbers ascending and descending along the cable. However, this type of system has problems, such as the difficulty of supplying energy to climbers and a short lifespan owing to the abrasion of the cable and climber wheels during operation. To avoid these problems, in this study, we investigate a novel counterweight-type space ele...
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#1Fei Sun (NUAA: Nanjing University of Aeronautics and Astronautics)
#2Wei-Yi Su (NUAA: Nanjing University of Aeronautics and Astronautics)H-Index: 2
Last. Ren-Jie Wang (NUAA: Nanjing University of Aeronautics and Astronautics)
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Abstract The ramjet/scramjet engines require the control-oriented model to predict the inlet flow field in less than a few seconds. However, it is challenging for these kinds of inlets which utilize curved shock waves to compress the air flow. In this paper, a reduced-order model based on the computational fluid dynamics, the proper orthogonal decomposition theory, and the radial basis function interpolation method is developed. After that, the curved shock waves dominated flow fields of a ramje...
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#1Yusuke Yamashita (UTokyo: University of Tokyo)H-Index: 1
#2Ryudo Tsukizaki (JAXA: Japan Aerospace Exploration Agency)H-Index: 7
Last. Kazutaka Nishiyama (JAXA: Japan Aerospace Exploration Agency)H-Index: 15
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Abstract A cluster of gridded microwave discharge ion thrusters μ10 contributed to the success of the deep space exploration missions of the Japanese asteroid explorers Hayabusa and Hayabusa2. To meet the demands of the next mission DESTINY+, the maximum ion beam current was increased to 200 mA from the 170 mA used in Hayabusa2 by redesigning the magnetic field and grid configuration. However, this thruster exhibited the plasma hysteresis caused by a high-voltage breakdown. Specifically, the ion...
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#1Todd D. Lillian (USA: University of South Alabama)
Abstract The electric solar wind sail (E-sail) has been proposed as a novel propulsion system that, if successful, promises to facilitate missions that would be inconvenient or impractical with traditional chemical propellants. The most common E-sail concept includes a central hub with several long positively charged tethers extending radially outward that harvest momentum from protons in the solar wind. Before the technology is ready for a demonstration mission, we must prove E-sail dynamics ca...
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#1Zhao Di (NPU: Northwestern Polytechnical University)
#2Chong Sun (NPU: Northwestern Polytechnical University)H-Index: 1
Last. Jianping Yuan (NPU: Northwestern Polytechnical University)H-Index: 8
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Abstract The precise attitude determination of a tumbling non-cooperative space target is challenging. This paper proposed an attitude determination approach based on multi-spacecraft collaborative observation. The three-dimensional (3-D) point cloud data of the target is constructed in terms of the collaborative observation data. By virtue of the target features and point cloud matching between two adjacent frames, the attitude change information of the target is derived, and based on this, the...
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