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Advanced Rocket Trajectory Propagation Techniques

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: HQ0147-18-C-7405
Agency Tracking Number: B17C-002-0080
Amount: $100,000.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: MDA17-T002
Solicitation Number: 2017.0
Solicitation Year: 2017
Award Year: 2018
Award Start Date (Proposal Award Date): 2018-03-28
Award End Date (Contract End Date): 2018-09-27
Small Business Information
6201 East Oltorf St.
Austin, TX 78741
United States
DUNS: 100651798
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Sebastian Liska, Ph.D
 (512) 389-9990
Business Contact
 Michael Mayo
Phone: (512) 389-9990
Research Institution
 Jet Propulsion Laboratory (JPL)
 Jason Rabinovitch
4800 Oak Grove Drive
Pasadena, CA 91109
United States

 (818) 354-4713
 Federally Funded R&D Center (FFRDC)

High-fidelity trajectory propagators are fundamental to the simulation and analysis of launch vehicles, missiles, and satellites. Applications in fields ranging from missile threat analysis to flightpath optimization seek fast and accurate solutions to large numbers of trajectories in federated simulation environments. Due to their robustness, well-known properties, and straightforward implementation, most trajectory simulators use standard numerical integrators. However, the low computational and memory efficiency of standard integrators often limits the scope and complexity of the problems they consider. Recently developed multi-stage, multi-derivative Hermite-Birkhoff-Taylor methods couple Taylor Series and Runge-Kutta methods and achieve superior computational efficiencies compared to standard integrators. A straightforward extension of these methods based on Hermite interpolation yields smooth, piecewise polynomial expressions for the solution with tunable accuracies and storage requirements. Nanohmics proposes to collaborate with the Jet Propulsion Laboratory managed by the California Institute of Technology to investigate extensions of Hermite-Birkhoff-Taylor methods to efficiently solve and store vehicle trajectories in high-throughput, federated simulation environments. Numerical experiments on simple 3-DoF space launches will compare the computational performance of prototype implementations with those of standard propagators. Experimental results will be extrapolated using numerical analysis to identify computationally efficient extensions suitable for 6-DoF trajectories based on high-fidelity models.Approved for Public Release | 18-MDA-9522 (23 Feb 18)

* Information listed above is at the time of submission. *

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