A ballistic-pendulum test stand to characterize small cold-gas thruster nozzles |
| |
| Authors: | Claudio Lugini Marcello Romano |
| |
| Institution: | 1. SupAéro, 10 Avenue Eduard Belin, Toulouse 31055, France;2. Sapienza Università di Roma, Via Eudossiana 18, Rome 00161, Italy;3. Naval Postgraduate School, Mechanical and Astronautical Engineering Department and Space Systems Academic Group, 700 Dyer Road, Monterey, CA 93940, USA;1. Department of Atmospheric, Oceanic and Space Sciences, University of Michigan, Ann Arbor, MI 48109, USA;2. NASA/Goddard Space Flight Center, Greenbelt, MD 20771, USA;1. Institute of Astronautics, Technische Universität München, 85748 Garching, Germany;2. Mechanical and Aerospace Engineering Department, Naval Postgraduate School, 700 Dyer Road, Monterey, CA, USA;1. University of Padova, Department of Industrial Engineering, Via Venezia 1, Padova 35131, Italy;2. Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 77 Massachusetts Avenue, Cambridge 02139, MA, United States;3. Airbus DS Space Systems, Inc., 555 Forge River Rd Suite 115 Webster, TX 77586;1. Institute of Astronautics, Technische Universität München, Boltzmannstr. 15, 85748 Garching, Germany;2. Department of Mechanical and Aerospace Engineering, Naval Postgraduate School, Monterey, 93943-5107 CA, United States;1. Korea Aerospace Research Institute, Daejeon 305-806, Republic of Korea;2. Astrodynamics & Control Lab., Dept. of Astronomy, Yonsei Univ., Seoul 120-749, Republic of Korea;3. Yonsei Univ. Observatory, Yonsei Univ., Seoul 120-749, Republic of Korea |
| |
| Abstract: | This paper deals with the design, development and experimentation of a new test stand for the accurate and precise characterization of small cold-gas nozzles having thrust of the order of 0.1 N and specific impulse of the order of 10 s. As part of the presented research, a new cold-gas supersonic nozzle was designed and developed based on the quasi one-dimensional theory. The test stand is based on the ballistic-pendulum principle: in particular, it consists of a suspended gondola hosting the propulsion system and the sample nozzle. The propulsion system consists of an air tank, pressure regulator, solenoid valve, battery and digital timer to command the valve. The gondola is equipped with a fin, immersed in water, to provide torsional and lateral oscillation damping. A laser sensor measures the displacement of the gondola. The developed test stand was calibrated by using a mathematical model based on the inelastic collision theory. The obtained accuracy was of ～1%. Sample experimental results are reported regarding the comparison of the new supersonic nozzle with a commercially available subsonic nozzle. The obtained measurements of thrust, mass flow rate and specific impulse are precise to a level of ～3%. The broad goal of the presented research was to contribute to an upgraded design of a spacecraft simulator used for laboratory validation of guidance, navigation and control algorithms for autonomous docking manoeuvres. |
| |
| Keywords: | |
| 本文献已被 ScienceDirect 等数据库收录！ |
|
