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Investigation into nitrous oxide pro...

Zakirov, V.A.,

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Investigation into nitrous oxide propulsion option for small satellite applications /

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Investigation into nitrous oxide propulsion option for small satellite applications // V.A Zakirov.
作者:	Zakirov, V.A.,
面頁冊數:	1 electronic resource (312 pages)
附註:	Source: Dissertations Abstracts International, Volume: 79-02, Section: C.
Contained By:	Dissertations Abstracts International79-02C.
標題:	Aerospace engineering. -
電子資源:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=U533017
ISBN:	9781073928910

Investigation into nitrous oxide propulsion option for small satellite applications /
Zakirov, V.A.,

Investigation into nitrous oxide propulsion option for small satellite applications /V.A Zakirov. - 1 electronic resource (312 pages)

Source: Dissertations Abstracts International, Volume: 79-02, Section: C.

Nitrous oxide has been considered as a propellant for space applications. Its application offers multiple advantages (higher ΔV manoeuvres, system multi-functionality and flexibility, and low-cost) over existing propulsion systems for a small satellite. In 1998, a Ph.D. research programme was started at Surrey Space Centre to investigate N2O propulsion option for small satellite applications. The primary objective of this research is to identify the advantages & disadvantages and quantify the performance of the use of this propellant for spacecraft propulsion. To achieve this two subsequent research goals have been set: investigate the potential of N2O as a spacecraft propellant; assess the feasibility of suggested N2O decomposition technique. During the course of the research both of the goals were achieved. Analysis of the specifics of small satellite propulsion suggested that liquefied gases were the preferred propellants. Extensive background information regarding its properties, storage, handling, and applications has shown that N2O is safe, low cost, suitable, and may be catalytically, exothermically decomposed. N2O multi-mode propulsion system concept was proposed for a small satellite. A novel monopropellant thruster concept employing N2O catalytic decomposition technique was developed. Test apparatus, set-up, procedure, and data acquisition were developed for the testing. More than 250 tests were performed to gain experience on the subject. The following are the main contributions to the state-of-the-art in this field by this research: The decomposition technique suggested was proven feasible for the restartable N2O monopropellant; The input power for N2O decomposition initiation was determined, and found suitable for micro-satellite platforms; The method involving loading factors and axial temperature profile for N2O decomposition is developed, and found useful for the catalyst pack sizing; The pressure drop through N2O catalyst pack was predicted, and found to be within feed system operational limits; N2O decomposition was found to be flow-controlled, and is proposed for the monopropellant thruster control; A model was developed for designing of N2O monopropellant thrusters; The challenges of N2O decomposition were identified, and are associated with high process temperature.

English

ISBN: 9781073928910Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Catalytic decomposition

Investigation into nitrous oxide propulsion option for small satellite applications /
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520 $a Nitrous oxide has been considered as a propellant for space applications. Its application offers multiple advantages (higher ΔV manoeuvres, system multi-functionality and flexibility, and low-cost) over existing propulsion systems for a small satellite. In 1998, a Ph.D. research programme was started at Surrey Space Centre to investigate N2O propulsion option for small satellite applications. The primary objective of this research is to identify the advantages & disadvantages and quantify the performance of the use of this propellant for spacecraft propulsion. To achieve this two subsequent research goals have been set: investigate the potential of N2O as a spacecraft propellant; assess the feasibility of suggested N2O decomposition technique. During the course of the research both of the goals were achieved. Analysis of the specifics of small satellite propulsion suggested that liquefied gases were the preferred propellants. Extensive background information regarding its properties, storage, handling, and applications has shown that N2O is safe, low cost, suitable, and may be catalytically, exothermically decomposed. N2O multi-mode propulsion system concept was proposed for a small satellite. A novel monopropellant thruster concept employing N2O catalytic decomposition technique was developed. Test apparatus, set-up, procedure, and data acquisition were developed for the testing. More than 250 tests were performed to gain experience on the subject. The following are the main contributions to the state-of-the-art in this field by this research: The decomposition technique suggested was proven feasible for the restartable N2O monopropellant; The input power for N2O decomposition initiation was determined, and found suitable for micro-satellite platforms; The method involving loading factors and axial temperature profile for N2O decomposition is developed, and found useful for the catalyst pack sizing; The pressure drop through N2O catalyst pack was predicted, and found to be within feed system operational limits; N2O decomposition was found to be flow-controlled, and is proposed for the monopropellant thruster control; A model was developed for designing of N2O monopropellant thrusters; The challenges of N2O decomposition were identified, and are associated with high process temperature.
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590 $a School code: 0597
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Software. $2 gtt. $3 619355
650 4 $a Cold. $3 560283
650 4 $a Electricity distribution. $3 3562889
650 4 $a Pressure vessels. $3 3592797
650 4 $a Systems design. $3 3433840
650 4 $a Chemical reactions. $3 519248
650 4 $a Orbits. $3 534192
650 4 $a Decomposition. $3 3561186
650 4 $a Heat. $3 573595
650 4 $a Stress analysis. $3 3681390
650 4 $a Gas flow. $3 3487726
650 4 $a Nitrogen. $3 1314426
650 4 $a Space exploration. $3 3696172
650 4 $a Gases. $3 559387
650 4 $a Thermocouples. $3 726758
650 4 $a Spacecraft. $3 3682976
650 4 $a Electric power. $3 2143306
650 4 $a Nitrous oxide. $3 1567394
650 4 $a Steel pipes. $3 3686413
650 4 $a Kerosene. $3 3295855
650 4 $a Satellites. $3 924316
650 4 $a Reynolds number. $3 3681436
650 4 $a Ground stations. $3 3683603
653 $a Catalytic decomposition
690 $a 0538
710 2 $a University of Surrey (United Kingdom). $b School of Electronic Engineering, Information Technology and Mathematics. $e degree granting institution. $3 3815769
773 0 $t Dissertations Abstracts International $g 79-02C.
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791 $a Ph.D.
792 $a 2001
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