MEMS-Based Solid Propellant Rocket Array Thruster
Shuji Tanaka,Ryuichiro Hosokawa,Shin Ichiro Tokudome,Keiichi Hori,Hirobumi Saito,Masashi Watanabe,Masayoshi Esashi +6 more
67
TL;DR: In this paper, the prototype of a solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was completed and tested, and the prototype has 10×10 φ0.8 mm solid-rockets arrayed at a pitch of 1.2 mm on a 20×22 mm substrate.
read more
Abstract: The prototype of a solid propellant rocket array thruster for simple attitude control of a 10 kg class micro-spacecraft was completed and tested. The prototype has 10×10 φ0.8 mm solid propellant micro-rockets arrayed at a pitch of 1.2 mm on a 20×22 mm substrate. To realize such a dense array of micro-rockets, each ignition heater is powered from the backside of the thruster through an electrical feedthrough which passes along a propellant cylinder wall. Boron/potassium nitrate propellant (NAB) is used with/without lead rhodanide/potassium chlorate/nitrocellulose ignition aid (RK). Impulse thrust was measured by a pendulum method in air. Ignition required electric power of at least 3–4 W with RK and 4–6 W without RK. Measured impulse thrusts were from 2×10−5 Ns to 3×10−4 Ns after the calculation of compensation for air dumping.
read more
Chat with Paper
AI Agents for this Paper
Find similar papers on Google Scholar, PubMed and Arxiv
Write a critical review of this paper
Analyze citations of this paper to find unaddressed research gaps
Citations
Nanoenergetic Materials for MEMS: A Review
TL;DR: In this article, the authors provide a comprehensive review of current research activities in nEMs for microenergetics application and propose a strategy to select nEM based on an analysis of the material diffusivity and heat of reaction.
483
Integration of a MEMS based safe arm and fire device
Helene Pezous,Helene Pezous,Carole Rossi,Carole Rossi,Marjorie Sanchez,Marjorie Sanchez,Fabrice Mathieu,Fabrice Mathieu,Xavier Dollat,Xavier Dollat,Samuel Charlot,Samuel Charlot,Ludovic Salvagnac,Ludovic Salvagnac,Véronique Conédéra,Véronique Conédéra +15 more
TL;DR: In this article, the authors describe a new architecture of a Safe Arm and Fire (SAF) device that could constitute a real breakthrough for safe miniature fuzing device, which takes all the functions embodied in a conventional mechanical arm and fire system and integrates them in a single 1.cm 3 package made of assembly of different parts.
131
Micropyrotechnics, a new technology for making energetic microsystems : review and prospective
Carole Rossi,Daniel Esteve +1 more
TL;DR: A review of the micropyrotechnics related works is done in this article, where authors identify obvious difficulties and insufficiencies that may require future work, particularly in terms of the development of new materials, new modelling tools and new processes for integration into micro-systems.
Matrix of 10 × 10 addressed solid propellant microthrusters: Review of the technologies
Carole Rossi,Danick Briand,Maxime Dumonteuil,Thierry Camps,Phuong Quyên Pham,Nicolaas F. de Rooij +5 more
TL;DR: In this article, the EC funded MicroPyros project has permitted the development of technologies to fabricate, assemble and command solid propellant microthrusters arrays for thrusts of a few milli Newtons.
References
A Hybrid Cold Gas Microthruster System for Spacecraft
TL;DR: In this paper, a complete hybrid cold gas microthruster system for spacecraft, designed to deliver maximum thrusts in the range of 0.1 to 10 mN, has been demonstrated.
138
Design, fabrication and modeling of solid propellant microrocket-application to micropropulsion
TL;DR: In this article, the authors present the process of fabrication and the assembling of micro-thrusters as well as the specific equipment developed to load the solid propellant into microcavities.
118
Study of a vaporizing water micro-thruster
X.Y. Ye,Fei Tang,Henggao Ding,Z.Y. Zhou +3 more
- 20 Mar 2001
TL;DR: In this article, a single micro-thruster with a pulse power of 30 W was designed to operate in a high-pressure gas chamber, and the total impulse produced in a second was more than 0.2×10 −6 ǫ n.
60
Vaporizing liquid microthruster
TL;DR: In this paper, a micro-thruster design, fabrication, and test results are presented for a microchamber with anisotropic wet etching of silicon micro-nozzles, where liquid is vaporized by resistive silicon heaters.
Microfabrication of a high pressure bipropellant rocket engine
A. P. London,Arturo A. Ayon,Alan H. Epstein,S.M. Spearing,Todd Harrison,Yoav Peles,J.L. Kerrebrock +6 more
TL;DR: In this article, a high pressure bipropellant rocket engine was successfully micromanufactured by fusion bonding a stack of six individually etched single crystal silicon wafers, achieving a thrust power of 750 W. In order to test the device, an innovative packaging technique was developed to deliver liquid coolant and gaseous propellants to the rocket chip at pressures in excess of 200 atm at temperatures above 300°C.