Laser Fine-Adjustment Thruster For Space Vehicles

Rezunkov, Yu. A.; Egorov, M. S.; Rebrov, S. G.; Repina, E. V.; Safronov, A. L.

doi:10.1063/1.3435446

Cited by 4 publications

(5 citation statements)

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“…Combustion effects, especially at higher Àuences, may enhance c m sig-ni¿cantly, as reported in [7]. The boost of c m under ambient atmosphere compared to vacuum conditions can be estimated according to [21] from the propellant's speci¿c combustion heat.…”

Section: Impulse Coupling Of àAt Pom Targets In Ambient Air (Nagoya -Stuttgart)mentioning

confidence: 86%

Review on Japanese-German-U.S. Cooperation on Laser-Ablation Propulsion

Sinko¹,

Karg²,

Röser³

et al. 2011

AIP Conference Proceedings

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We report on an international cooperation between Nagoya University (NU), Japan and DLR Stuttgart, Germany on scaling issues in laser ablative propulsion. Lessons learned from collaborative work in the laboratory will be summarized with respect to the comparability of experimental methods and corresponding standardization issues. With the background of previous experimental research at the University of Alabama in Huntsville (UAH), experimental work with CO 2 lasers in a moderate (NU) and high (DLR) pulse energy range on laser ablation of POM is presented. Pro¿lometry results of target surfaces are compared with Àuence distributions from beam propagation modeling. Ablation from Àat targets is reported with respect to energy and area scaling and compared with results from ablative propulsion employing parabolic nozzles.

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Section: Impulse Coupling Of àAt Pom Targets In Ambient Air (Nagoya -Stuttgart)mentioning

confidence: 86%

Review on Japanese-German-U.S. Cooperation on Laser-Ablation Propulsion

Sinko¹,

Karg²,

Röser³

et al. 2011

AIP Conference Proceedings

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“…Where Q=18.787kJ/g [3] is the released heat. The average experimental results in both atmosphere and nitrogen environments are listed in Table 1, where Δm is the ablated mass, η nom is the nominal laser energy efficiency defined as…”

Section: Figure 1 Experimental Setupmentioning

confidence: 99%

“…The previous studies (Phipps et al [1] , Lippert et al [2] , Rezunkov et al [3] ) found some materials can release chemical energy in the process of laser propulsion and significantly improve the propulsion performance. It could be defined as "Chemical Laser Propulsion (CLP)", which means "laser propulsion with chemical energy release").…”

Section: Introductionmentioning

confidence: 97%

Investigation of performance and mechanism for chemical laser propulsion

Zhi-ping

2013

SPIE Proceedings

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Chemical laser propulsion (CLP) is accompanied by the release of chemical energy in the process of laser propulsion, which can improve laser propulsion performance. In this article the propulsion performance of POM propellant under the constraint of a cylindrical tube-type thruster in atmospheric and nitrogen environments, respectively, has been conducted experimentally. The results indicate that the ablation masses of a single pulse under two gas environments are close, but the momentum coupling coefficient C m and specific impulse I sp in atmospheric environment are higher than that in nitrogen environment, which demonstrates an exothermic reaction occurred between the ablation product and the environment oxygen. To learn the mechanism of CLP the molecular spectra for ablation products of POM propellant in atmospheric and vacuum environments are measured and analyzed, respectively, and it reveals that the final product in a vacuum is CH 2 O, while the final products are CO 2 and H 2 O in the atmosphere. Then the chemical reaction, composition and chemical energy release have been confirmed in the atmospheric environment. By using Arrhenius finite rate chemical reaction model with the code Fluent the flow field evolution of ablation product was simulated numerically. The results show the intensity of chemical energy release is related to the contact and mixing degree of the ablation product and the oxygen in the atmosphere, mixing more fully, the chemical energy released more intensively.

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“…In this case, the satellite is considered as a point mass being under the in §uence of various disturbing forces [18]. The results of the estimations are presented in Table 3, where the following parameters are listed: m pl /M is the payload fraction of the total satellite mass after a single orbit adjustment maneuver; and C e is the speci¦c energy consumption of the satellite correction maneuver.…”

Section: Mitigation and Removal Of Space Debrismentioning

confidence: 99%

“…This operational requirement is caused by the vibration of a satellite construction and by the in §uence of its motion on the high-power laser radiation delivery to the thruster. To control the optical part of the thruster and operating laser beam, Figure 5 Principal schematic diagram of the laser thruster designed on a basis of ASLPE [18] the adjustment system is supplied with a laser illumination system by using auxiliary adjusting lasers and retrore §ectors arranged on the top of the optical rhomb.…”

Section: Laser Propulsion Engine For Space Missions and Laser Thrustementioning

confidence: 99%