An investigation in to an un-powered, return to base platform form high altitudes

Paper number

IAC-06-C1.P.7.04

Author

Mr. Armin Ellis, Dartmouth College / Astro Pioneer Ltd, United Kingdom

Year

2006

Abstract

Automated recovery of scientific payloads from space was first achieved in the early 1960's, for the retrieval of astronauts, space exposed experimental samples and film canisters from remotes sensing satellites. However, with the exception of only a few projects the recovery has been passive, or non-guided, such that the payload acquisition would either be done at lower altitudes by an aircraft, or on land in an area with large margins of error.

The study performed is for the design of a recovery system with no propulsion system capable of an accurate glide return of the return vehicle to a predetermined zone on the ground using a Mamdani type fuzzy logic system which will have the ability to generate the fuzzy rules automatically and to reconfigure its own structure depending on environment under investigation. By reconfiguration one means the level granularity of information it needs to solve the task at hand. Such granularity can vary from 'low' to 'high' depending on the task complexity.

Potential applications for a guided recovery system are numerous, and include the Mars sample recovery missions and delivery of commercial space manufactured products.

The use of a fuzzy logic algorithm is particularly suitable for solving this multi-variable, highly dimensional and uncertain problem. The variables required for successful recovery of the payload include atmospheric density and local wind vector and speeds, both imposing non-linear demands on the control system, however a rigorous testing program is required to ensure that this nonlinear control problem is consistently robust.

The presented results are based on the simulated performance of the designed fuzzy logic system, addressing the many aspects of the design and configuration of the re-entry body, use of actuator technologies and the performance of the different designs. This also includes power consumption, trajectory optimization, limitations in a variety of atmospheric conditions and adequacy of the algorithms and configuration for such applications.

Abstract document

IAC-06-C1.P.7.04.pdf

Manuscript document

IAC-06-C1.P.7.04.pdf (🔒 authorized access only).

To get the manuscript, please contact IAF Secretariat.