First Results from a Hardware-in-the-Loop Demonstration of Closed-Loop Autonomous Formation Flying
Gill, E. and Naasz, B. and Ebinuma, T. (2003) First Results from a Hardware-in-the-Loop Demonstration of Closed-Loop Autonomous Formation Flying. American Astronautical Society. 26th Annual AAS Guidance and Control Conference, Breckenridge, Co., Feb. 5-9 2003.
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A closed-loop system for the demonstration of autonomous satellite formation flying technologies using hardware-in-the-loop has been developed. Making use of a GPS signal simulator with a dual radio frequency outlet, the system includes two GPS space receivers as well as a powerful onboard navigation processor dedicated to the GPS-based guidance, navigation, and control of a satellite formation in real-time. The closed-loop system allows realistic simulations of autonomous formation flying scenarios, enabling research in the fields of tracking and orbit control strategies for a wide range of applications. The autonomous closed-loop formation acquisition and keeping strategy is based on Lyapunovs direct control method as applied to the standard set of Keplerian elements. This approach not only assures global and asymptotic stability of the control but also maintains valuable physical insight into the applied control vectors. Furthermore, the approach can account for system uncertainties and effectively avoids a computationally expensive solution of the two point boundary problem, which renders the concept particularly attractive for implementation in onboard processors. A guidance law has been developed which strictly separates the relative from the absolute motion, thus avoiding the numerical integration of a target trajectory in the onboard processor. Moreover, upon using precise kinematic relative GPS solutions, a dynamical modeling or filtering is avoided which provides for an efficient implementation of the process on an onboard processor. A sample formation flying scenario has been created aiming at the autonomous transition of a Low Earth Orbit satellite formation from an initial along-track separation of 800 m to a target distance of 100 m. Assuming a low-thrust actuator which may be accommodated on a small satellite, a typical control accuracy of less than 5 m has been achieved which proves the applicability of autonomous formation flying techniques to formations of satellites as close as 50 m.
|Document Type:||Conference or Workshop Item (Paper)|
|Additional Information:||LIDO-Berichtsjahr=2003, monograph_id=AAS 03-040,|
|Title:||First Results from a Hardware-in-the-Loop Demonstration of Closed-Loop Autonomous Formation Flying|
|Page Range:||pp. 1-16|
|Publisher:||American Astronautical Society|
|Keywords:||Formation Flying; GPS|
|Event Title:||26th Annual AAS Guidance and Control Conference, Breckenridge, Co., Feb. 5-9 2003|
|HGF - Research field:||Aeronautics, Space and Transport (old)|
|HGF - Program:||Space (old)|
|HGF - Program Themes:||W EO - Erdbeobachtung|
|DLR - Research area:||Space|
|DLR - Program:||W EO - Erdbeobachtung|
|DLR - Research theme (Project):||UNSPECIFIED|
|Institutes and Institutions:||Space Operations and Astronaut Training > Hauptabteilung Raumflugbetrieb und Astronautenausbildung|
|Deposited By:||Karin Klier|
|Deposited On:||16 Sep 2005|
|Last Modified:||14 Jan 2010 17:25|
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