New analytical solutions for proportional navigation

Rao, Meng

doi:10.2514/3.21051

Cited by 11 publications

(1 citation statement)

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“…The optimal guidance law in the radial direction is obtained as a solution to minimizing the performance index 7 r , where Y a 2 Mri dt (7) In Eq. (7), y if is the value of the relative range (miss distance) at the final time tf, S^f is the weight on the miss distance, and y is the weight on the pseudocontrol effort.…”

Section: Line-of-sight (Radial) Commanded Accelerationmentioning

confidence: 99%

Analytical missile guidance laws with a time-varying transformation

Balakrishnan

1996

Journal of Guidance, Control, and Dynamics

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ConclusionsAn approximate method for computing near-optimal, minimumfuel, planar lunar trajectories for low-thrust spacecraft has been developed. Our method approximates the long-duration powered Earth-escape and moon-capture spirals with curve fits from universal low-thrust trajectory solutions and numerically computes the translunar coasting trajectory between the curve-fit boundaries using the restricted three-body problem dynamics. The approximate method requires only four optimization variables, and solutions are readily obtained by using sequential quadratic programming. Nearoptimal solutions for a wide range of initial thrust-to-weight ratios and initial and terminal circular orbit altitudes are obtained both quickly and with little computational load. The performance and orbit transfer characteristics of the near-optimal solutions exhibit a very close match with published optimal lunar trajectory solutions. This method would be a useful preliminary design tool for spacecraft and mission designers.

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Section: Line-of-sight (Radial) Commanded Accelerationmentioning

confidence: 99%