Sinha, SK and Shrivastava, SK (1990) Optimal explicit guidance of multistage launch vehicle along three-dimensional trajectory. In: Journal of Guidance, Control, and Dynamics, 13 (3). pp. 394-403.
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Details of an efficient optimal closed-loop guidance algorithm for a three-dimensional launch are presented with simulation results. Two types of orbital injections, with either true anomaly or argument of perigee being free at injection, are considered. The resulting steering-angle profile under the assumption of uniform gravity lies in a canted plane which transforms a three-dimensional problem into an equivalent two-dimensional one. Effects of thrust are estimated using a series in a recursive way. Encke's method is used to predict the trajectory during powered flight and then to compute the changes due to actual gravity using two gravity-related vectors. Guidance parameters are evaluated using the linear differential correction method. Optimality of the algorithm is tested against a standard ground-based trajectory optimization package. The performance of the algorithm is tested for accuracy, robustness, and efficiency for a sun-synchronous mission involving guidance for a multistage vehicle that requires large pitch and yaw maneuver. To demonstrate applicability of the algorithm to a range of missions, injection into a geostationary transfer orbit is also considered. The performance of the present algorithm is found to be much better than others.
| Item Type: | Journal Article |
|---|---|
| Publication: | Journal of Guidance, Control, and Dynamics |
| Publisher: | American Institute of Aeronautics and Astronautics |
| Additional Information: | Copyright of this article belongs to American Institute of Aeronautics and Astronautics. |
| Department/Centre: | Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering) |
| Date Deposited: | 25 Feb 2011 07:00 |
| Last Modified: | 25 Feb 2011 07:02 |
| URI: | http://eprints.iisc.ac.in/id/eprint/34994 |
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