AIAA Guidance, Navigation, and Control Conference and Exhibit 2002
DOI: 10.2514/6.2002-4559
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Atmospheric Ascent Guidance for Rocket-Powered Launch Vehicles

Abstract: An advanced ascent guidance algorithm for rocketpowered launch vehicles is developed. The algorithm cyclically solves the calculus-of-variations two-point boundary-value problem starting at vertical rise completion through main engine cutoff, taking into account atmospheric effects. This is different from traditional ascent guidance algorithms which operate in a simple open-loop mode until the high dynamic pressure portion of the trajectory is over, at which time guidance operates under the assumption of negli… Show more

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Cited by 50 publications
(27 citation statements)
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“…The derivation of the expressions of the costate equations (21) and (22) is quite involved. The detailed equations are provided in Appendix A.…”
Section: B Optimal Control Problemmentioning
confidence: 99%
“…The derivation of the expressions of the costate equations (21) and (22) is quite involved. The detailed equations are provided in Appendix A.…”
Section: B Optimal Control Problemmentioning
confidence: 99%
“…There has been much research and development work in recent years on endo-atmospheric ascent guidance (Bradt et al 1987, Kelly 1992, Hanson et al 1994, Calise et al 1998, Leung and Calise 1994, Gath and Calise 2001, Dukeman 2002, Dukeman and Calise 2003, Lu et al 2003, 2005. Relevant to the current work, Lu et al 2003 presented a treatment of the optimal atmospheric ascent problem.…”
Section: Introductionmentioning
confidence: 92%
“…In brief, the guidance uses an open-loop phase (pitch, yaw, and roll versus altitude) followed by a closed-loop design. An optimization procedure 4 and linear tangent steering were evaluated for the closed-loop design. The current baseline is the Shuttle version of linear tangent steering, Powered Explicit Guidance 5 (PEG).…”
Section: Simulation and Modeling Of Ares Imentioning
confidence: 99%