A suborbital abort guidance scheme is presented for returning the orbiter vehicle to the launch site in the event of a booster malfunction. The guidance scheme described, referred to as FBGUID, represents a simple closed-form technique to the flyback abort problem. In addition to returning to the launch site, objectives of the formulation are to preclude excessive structural and heating loads. A demonstration of the feasibility of this abort guidance concept is included for a 150-second abort time.
A suborbital abort guidance scheme for orbital returns to the launch site
1971-06-30
Report
No indication
English
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