Quaternion Error Based Optimal Attitude Control Applied to Pinpoint Landing-Reference-Cited by-同舟云学术

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Quaternion Error Based Optimal Attitude Control Applied to Pinpoint Landing

Published:2015-01-02 Issue: Volume: Page:
ISSN:
Container-title:AIAA Guidance, Navigation, and Control Conference
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Author:

Ghiglino Pablo¹,Lappas Vaios¹

Affiliation:

1. University of Surrey

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2015-1998

Reference22 articles.

1. GN&C Technology Needed to Achieve Pinpoint Landing Accuracy at Mars

2. 2Smith, R. “Closed-Loop Aeromaneuvering for a Mars Precision Landing,” Tech. Rep. CCEC-96-0205, 1996.

3. 3Smith, R., Bayard, D., and Mease, K. “Mars Precision Landing: an Integrated Estimation, Guidance and Control Simulation,” Tech. Rep. CCEC-98-0918, 1998.

4. Desensitizing the Minimum-Fuel Powered Descent For Mars Pinpoint Landing

5. Minimum-Fuel Powered Descent for Mars Pinpoint Landing

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1. Quaternion Error Based Optimal Attitude Control Applied to Pinpoint Landing;AIAA Guidance, Navigation, and Control Conference;2015-01-02

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