Near-earth solar sail navigation: Preliminary results

被引：0

作者：

Christensen, EJ ^{[1
]}

Williams, BG ^{[1
]}

Ionasescu, R ^{[1
]}

机构：

[1] CALTECH, Jet Prop Lab, Navigat & Miss Design Sect, Pasadena, CA 91109 USA

来源：

ASTRODYNAMICS 2001, PTS I-III | 2001年 / 109卷

关键词：

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Preliminary analyses have been conducted to assess the accuracy of the measured acceleration acting on a solar sail in a low-Earth orbit. The studies focused on a sun-synchronous Earth orbiter in a nearly circular, similar to1000 km altitude orbit. Perturbations to this orbit were simulated using a 40mx40m square solar sail to propel a 157 kg spacecraft into a slowly expanding spiral orbit. Although the forces exerted by the sail are relatively small, it was found that they could be estimated to within similar to6x10(-4) mm/s(2), in similar to3 days with only one pass of Deep Space Network (DSN) tracking per day.

引用

页码：755 / 764

页数：10

共 8 条

[1] Propulsion trades for space science missions [J].

Gershman, R ;

Seybold, C .

ACTA ASTRONAUTICA, 1999, 45 (4-9) :541-548

[2] Technology needs of future planetary missions [J].

Gershman, R ;

Wallace, RA .

ACTA ASTRONAUTICA, 1999, 45 (4-9) :329-335

[3]

KAKUDA R, 1994, IAA INT C LOW COST P

[4] Heteroclinic connections between periodic orbits and resonance transitions in celestial mechanics [J].

Koon, WS ;

Lo, MW ;

Marsden, JE ;

Ross, SD .

CHAOS, 2000, 10 (02) :427-469

[5]

McInnes C.R., 1999, Solar Sailing-Technology, Dynamics and Mission Applications, P247, DOI [10.1007/978-1-4471-3992-8, DOI 10.1007/978-1-4471-3992-8]

[6]

MULLIGAN P, 2001, SPACEVIEWS 0618

[7]

Sims J.A., 1999, AAS 99-338

[8]

WOLFF PJ, 1998, AAS AIAA SPAC FLIGHT

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