Trajectory & maneuver design of the NEA Scout solar sail mission

被引：6

作者：

Lantoine, Gregory ^{[1
]}

Cox, Andrew ^{[1
]}

Sweetser, Theodore ^{[1
]}

Grebow, Dan ^{[1
]}

Whiffen, Gregory ^{[1
]}

Garza, David ^{[1
]}

Petropoulos, Anastassios ^{[1
]}

Oguri, Kenshiro ^{[1
]}

Kangas, Julie ^{[1
]}

Kruizinga, Gerhard ^{[1
]}

Castillo-Rogez, Julie ^{[1
]}

机构：

[1] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA

来源：

ACTA ASTRONAUTICA | 2024年 / 225卷

基金：

美国国家航空航天局;

关键词：

Solar sail; Secondary payload; Near-Earth asteroid; Trajectory design; Optimization; Automation; OPTIMIZATION;

D O I：

10.1016/j.actaastro.2024.08.039

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The Near-Earth Asteroid Scout (NEA Scout) mission aimed to deliver a 6U CubeSat to a slow flyby of a Near Earth Asteroid using a solar sail as the primary propulsion system. NEA Scout was launched as a secondary payload aboard Artemis I, on November 16, 2022, but communication with the spacecraft was not achieved. This paper describes the target asteroid selection and the innovative trajectory and maneuver design for the NEA Scout mission, including cold gas maneuvers, multiple lunar flybys, solar sail thrusting, and design margins for solar sailing. The resulting trajectory design tools, solutions, and analyses are potentially applicable to future solar sail missions.

引用

页码：77 / 98

页数：22

共 67 条

[1]

[Anonymous], 1976, ASTR C, DOI DOI 10.2514/6.1976-792

[2]

[Anonymous], 2012, GLOBAL SPACE EXPLORA

[3]

Barbee B.W., 2010, AIAAGUIDANCE NAV CON, V2010

[4] Sliding mode control for attitude maneuvers of Helianthus solar sail [J].