Analytic Development of a Reference Trajectory for Skip Entry

Garcia-Llama, Eduardo

doi:10.2514/1.50798

Cited by 7 publications

(2 citation statements)

References 13 publications

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“…Kluever presented an analytical method using a matched asymptotic expansion for skip entry guidance; however, the algorithm relies on a fixed density model (Kluever, 2008). D'Souza and García-Llama extended the strategy of tracking a drag profile from the Space Shuttle to the reentry capsules, but certain coefficients that are used in the profile fitting depend on empirical analyses or a priori information (D'Souza, 2008;García-Llama, 2011). A numerical predictor-corrector guidance method has successfully demonstrated its performance in terms of enhancing the range capability of a low-lifting vehicle during lunar returns (Bairstow, 2006;Tigges et al, 2007;Rea and Putnam, 2007;Miller, 2007;Brunner and Lu, 2008).…”

Section: Introductionmentioning

confidence: 99%

Skip entry guidance using numerical predictor–corrector and patched corridor

2015

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Section: Introductionmentioning

confidence: 99%

Skip entry guidance using numerical predictor–corrector and patched corridor

2015

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“…In a more recent work, a reference drag profile as a polynomial of velocity is used to define the reference trajectory. The required bank angle magnitude is solved from the drag profile (much like the Shuttle entry guidance) [11]. Extending these numerical algorithms to a complete prediction of an entire skip entry at every guidance cycle is a particular feature of this and other recent work [2,5,21].…”

Section: Introductionmentioning

confidence: 99%

Comparison of Fully Numerical Predictor-Corrector and Apollo Skip Entry Guidance Algorithms

Brunner

2012

J of Astronaut Sci

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The dramatic increase in computational power since the Apollo program has enabled the development of numerical predictor-corrector (NPC) entry guidance algorithms that allow on-board accurate determination of a vehicle's trajectory. These algorithms are sufficiently mature to be flown. They are highly adaptive, especially in the face of extreme dispersion and off-nominal situations compared with reference-trajectory following algorithms. The performance and reliability of entry guidance are critical to mission success. This paper compares the performance of a recently developed fully numerical predictor-corrector entry guidance (FNPEG) algorithm with that of the Apollo skip entry guidance. Through extensive dispersion testing, it is clearly demonstrated that the Apollo skip entry guidance algorithm would be inadequate in meeting the landing precision requirement for missions with medium (4000-7000 km) and long (>7000 km) downrange capability requirements under moderate dispersions chiefly due to poor modeling of atmospheric drag. In the presence of large dispersions, a significant number of failures occur even for shortrange missions due to the deviation from planned reference trajectories. The FNPEG algorithm, on the other hand, is able to ensure high landing precision in all cases tested. All factors considered, a strong case is made for adopting fully numerical algorithms for future skip entry missions.

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Reliability-based trajectory optimization using nonintrusive polynomial chaos for Mars entry mission

Huang

2018

Advances in Space Research

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Analytic Development of a Reference Trajectory for Skip Entry

Cited by 7 publications

References 13 publications

Skip entry guidance using numerical predictor–corrector and patched corridor

Skip entry guidance using numerical predictor–corrector and patched corridor

Comparison of Fully Numerical Predictor-Corrector and Apollo Skip Entry Guidance Algorithms

Reliability-based trajectory optimization using nonintrusive polynomial chaos for Mars entry mission

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