Guidance and navigation for solar electric interplanetary missions

Jordan, J. F.; Rourke, K. H.

doi:10.2514/6.1970-1152

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Spectral Factorization For Periodically Time-varying Systems1

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“…Specifically, Eq. (5) reduces in this case to P = _ PH'(HPH' + + GQG' (7) Let a matrix A(2n x 2n) be constructed by the coefficient matrices of Eq. (7) such that…”

Section: Spectral Factorization For Periodically Time-varying Systemsmentioning

confidence: 99%

Spectral Factorization in Periodically Time-Varying Systems and Application to Navigation Problems

NlSHIMURA

1972

Journal of Spacecraft and Rockets

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Spectral factorization is a powerful tool in deriving the steady-state solution of Kalman filtering equations. It is an algebraic, nortrecursive method, thus economical in terms of computing cost, when compared with the conventional iterative algorithm. In this paper the technique is extended to time-varying systems having periodic coefficient matrices for both discrete and continuous systems. The tracking of low-thrust spacecraft from an Earth-based station is used as an example and a sensitivity study is performed using a computer program incorporating the algorithm.

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“…Specifically, Eq. (5) reduces in this case to P = _ PH'(HPH' + + GQG' (7) Let a matrix A(2n x 2n) be constructed by the coefficient matrices of Eq. (7) such that…”

Section: Spectral Factorization For Periodically Time-varying Systemsmentioning

confidence: 99%

Spectral Factorization in Periodically Time-Varying Systems and Application to Navigation Problems

NlSHIMURA

1972

Journal of Spacecraft and Rockets

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The Role of Automatic Control in Future Interplanetary Spaceflight

Scull

Moore

1976

IFAC Proceedings Volumes

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Iterative explicit guidance for low thrust spacecraft

Jacobson

Powers²

1972

Astrodynamics Conference

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A retargeting procedure is developed for use as a nonlinear low thrust guidance scheme. The selection of a control program composed of a sequence of inertially fixed thrust-acceleration vectors permits all trajectory computations to be made with closed form expressions, and allows the controls to be represented by constant parameters, thrust-acceleration vectors and thrusting times. By requiring each trajectory to be time optimal, the guidance problem is transformed into a parameter optimization problem which is solved by the conjugate gradient method. The scheme is applied to a low thrust capture mission, and the results of computer simulations are presented.

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Guidance and navigation for solar electric interplanetary missions

Cited by 4 publications

References 1 publication

Spectral Factorization in Periodically Time-Varying Systems and Application to Navigation Problems

Spectral Factorization in Periodically Time-Varying Systems and Application to Navigation Problems

The Role of Automatic Control in Future Interplanetary Spaceflight

Iterative explicit guidance for low thrust spacecraft

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