Vacuum test of a micro-solid propellant rocket array thruster
Kazuyuki Kondo,Shuji Tanaka,Hiroto Habu,Shinichiro Tokudome,Keiichi Hori,Hirobumi Saito,Akihito Itoh,Masashi Watanabe,Masayoshi Esashi +8 more
TL;DR: RK has no benefit for the ignition of NAB, and other kinds of ignition aid should be found, according to results of a micro-thruster tested in vacuum.
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Abstract: A φ0.8mm micro-solid propellant rocket array thruster for simple attitude control of a 10kg class micro-spacecraft was tested in vacuum. The micro-thruster uses boron/potassium nitrate propellant (NAB), because NAB has ignition temperature as low as 500°C, and easily start to burn in vacuum. For a half of the rockets, an ignition aid (RK) was also loaded. Ignition was succeeded in vacuum with NAB + RK and NAB. The maximum impulse thrust of 4.6 × 10-4 Ns, which is approximately a half of our requirement, was obtained with NAB. Compared to NAB, NAB + RK generated lower impulse thrust. The success rate of ignition was as low as 30%, although RK was used. These results suggest that RK has no benefit for the ignition of NAB, and other kinds of ignition aid should be found.
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Citations
Test of B/Ti multilayer reactive igniters for a micro solid rocket array thruster☆
Shuji Tanaka,Kazuyuki Kondo,Hiroto Habu,Akihito Itoh,Masashi Watanabe,Keiichi Hori,Masayoshi Esashi +6 more
TL;DR: In this article, reactive B/Ti multilayer igniters were investigated for the noncontact ignition of a micro solid rocket array thruster in vacuum, and three sizes of three sizes were fabricated and tested in six configurations of solid propellant.
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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.
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Development of a solid propellant microthruster with chamber and nozzle etched on a wafer surface
TL;DR: In this paper, the development of a novel solid propellant micro-thruster is presented, which is an excellent micropropulsion system for high-accuracy station keeping, attitude control, speed adjustment, gravitation compensation and orbit adjustment of microspacecraft.
70
MEMS-Based Solid Propellant Rocket Array Thruster
Shuji Tanaka,Ryuichiro Hosokawa,Shin Ichiro Tokudome,Keiichi Hori,Hirobumi Saito,Masashi Watanabe,Masayoshi Esashi +6 more
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.
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