Autonomous ascent guidance with multiple terminal constraints for all-solid launch vehicles

Zhang, Qian; Xu, Zhi

doi:10.1016/j.ast.2019.105633

Cited by 9 publications

(2 citation statements)

References 18 publications

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“…The conclusion of Eq. (22) proves that there exists a specific ignition time [23,24], which makes the effect of "directional continuous propulsion" on the trajectory equivalent to that of "instantaneous pulse velocity vector" applied at the intersection point P imp .…”

Section: Algorithm For Burn Arcmentioning

confidence: 99%

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Instantaneous Impact Point Guidance with Coast Arcs for Solid Rockets

Jia

Tong

2021

International Journal of Aerospace Engineering

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This paper proposed an analytical iterative guidance method with the desired instantaneous impact point constraint for solid rockets in “burn-coast-burn” trajectory mode. Solid rocket motors expect to remove the thrust termination mechanism to increase the structural strength and launch reliability, which induce new difficulties and challenges to the guidance problems. In terms of the “Hohmann transfer” principle, a pointing algorithm is deduced in depth to establish the theoretical relations among the ignition time, the required velocity vector, and the orbital element constraints and provides the analytical expression of the ignition time. Then, an analytic solution of the required velocity vector is derived based on orthogonal and nonorthogonal velocity vectors, and a complete guidance logic is used to solve the target orbit elements satisfying the desired instantaneous impact point. Finally, the application of the developed theoretical algorithm in this paper is conducted using a two-stage solid rocket. The proposed guidance method is verified by Monte Carlo simulations, and the testing results demonstrate the adaptability, strong robustness, and excellent performance for different desired impact point missions.

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Section: Algorithm For Burn Arcmentioning

confidence: 99%

“…The velocities v sub:x in the suborbital orbit and v orb:x in the target orbit can be calculated by Eqs. (24) and (25). Similarly, the velocity v sub:y and v orb:y can be obtained, according to the true anomaly f at the point P imp .…”

Section: Calculation Of Velocitymentioning

confidence: 99%