Skip Entry Trajectory Planning and Guidance

Brunner, Christopher W.; Lu, Ping

doi:10.2514/6.2007-6777

Cited by 16 publications

(18 citation statements)

References 19 publications

(14 reference statements)

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“…During the bank reversal the trajectory is not under effective control. For aerocapture applications, just like in skip entry, 29,30 it is usually desirable that a bank reversal takes the direction (rotating through the zero degree attitude or 180-deg attitude) that requires the shortest time to complete the bank reversal.…”

Section: A a Two-phase Algorithmmentioning

confidence: 99%

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Optimal Aerocapture Guidance

Cerimele

Tigges

et al. 2015

AIAA Guidance, Navigation, and Control Conference

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Aerocapture is the maneuver by an interplanetary spacecraft to fly through the atmosphere of a planet aimed at attaining a specified orbit around the planet. By appropriately controlling the aerodynamic lift and/or drag force vectors, the spacecraft can exit the atmosphere and enter the target orbit without the need for large propellant consumption in post-atmospheric orbital correction burns. The focus of this paper is to develop an algorithm to guide the spacecraft accurately and reliably during the aerocapture maneuver with lift vector control while ensuring the least possible post-atmospheric propellant expenditure for inserting into the target orbit. The analysis of optimal aerocapture flight in this work shows that the optimal aerocapture trajectory in general has a bang-bang control structure in which the spacecraft first flies with the largest possible vertical lift up, then the largest possible vertical lift down. Based on this understanding, a two-phase numerical predictor-corrector guidance algorithm is developed. It is demonstrated that this algorithm not only exhibits the strengths of adaptivity and high accuracy of predictor-corrector guidance algorithms, but also produces an optimal performance in terms of propellant consumption that is significantly better than existing aerocapture numerical predictor-corrector guidance algorithms.

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Section: A a Two-phase Algorithmmentioning

confidence: 99%

“…In practice, the filters have been demonstrated to work satisfactorily even with time-varying uncertainties 29,30. …”

mentioning

confidence: 99%

Optimal Aerocapture Guidance

Cerimele

Tigges

et al. 2015

AIAA Guidance, Navigation, and Control Conference

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“…The purpose of dispersion simulations is to evaluate the performance of the guidance algorithm in the presence of significant deviations in trajectory state, vehicle, and environment modeling uncertainties. The dispersions in the entry conditions and other key parameters used here are the same as those used in a recent work on Orion CEV [16,17], which are listed in Table II. The reference trajectory to be followed is the same to the one used in Reference [18], which is not presented here for the sake of conciseness.…”

Section: Application Of the Feedback Gainsmentioning

confidence: 99%

“…Several candidate design approaches for determining FGs have already proposed, as shown, for example, in References [2][3][4][5][6][7][8][9][10]. Coate et al [3] propose a simple-implemented method to determine the guidance gains, but the method is based on the use of empirically determined weighting functions.…”

Section: Introductionmentioning

confidence: 99%

“…The method, which has been employed in Apollo mission, is relatively typical [4,5], in which the FGs are determined by means of linearized perturbation equations as well as Taylor expansion. This method continues to be used by Orion Crew Exploration Vehicle (CEV), particularly in its second entry phase [5][6][7][8]. Although Apollo's method was applied successfully in practice, from an optimal point of view, the derivation is not sufficiently rigorous.…”

Section: Introductionmentioning

confidence: 99%

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Optimal feedback gains determination method for nominal reentry guidance

Shen

2015

Optim Control Appl Methods

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This paper presents a new method for solving feedback gains in guidance based on optimal control theory. The determination of feedback gains is a critical problem for nominal guidance, because landing precision benefits from appropriate feedback gains. The magnitude of the bank angle is determined by minimizing the total error of final altitude as well as downrange requirement to the landing site. The problem is formulated as an optimal control problem by means of the Pontryagin's maximum principle, and backward integration is used to solve the problem based on homogeneous property. The proposed approach not only can avoid linearizing the nonlinear dynamic equations, but also are applicable to different guidance equations. Validation shows that the proposed approach can provide consistent results with that of Apollo. Despite employment of nominal guidance in the entire reentry of lunar mission, the proposed approach demonstrates good performance in all simulation cases while subject to significant disturbances. Figure 3. The 5000 dispersed cases of simulation results. (a) Latitude versus longitude, (b) histogram of load factor, (c) histogram of maximal heat rate, and (d) histogram of heat load. 221 OPTIMAL FEEDBACK GAINS FOR REENTRY GUIDANCE

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Adaptive sliding‐mode control for Mars entry trajectory tracking with finite‐time convergence

Shen

Xia

et al. 2018

Intl J Robust & Nonlinear

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This paper presents a novel adaptive sliding-mode control (ASMC) method for Mars entry guidance and the finite-time convergence in the presence of large uncertainties can be guaranteed. With the help of gain adaptive law, the nonoverestimating value of control gains can be achieved, and then, the chattering can be attenuated by the proposed ASMC method. Meanwhile, the extended state observer is introduced to estimate and compensate for uncertainties and the nonoverestimating problem is resolved further. In addition, the proposed method does not require any knowledge on the upper bound of uncertainty, which yields to be used in practical systems. Finally, the numerical simulation results are given to demonstrate the effectiveness of the proposed guidance law.

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Skip Entry Trajectory Planning and Guidance

Cited by 16 publications

References 19 publications

Optimal Aerocapture Guidance

Optimal Aerocapture Guidance

Optimal feedback gains determination method for nominal reentry guidance

Adaptive sliding‐mode control for Mars entry trajectory tracking with finite‐time convergence

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