A predictor-corrector guidance algorithm for use in high-energy aerobraking system studies

Braun, Robert D.; Powell, Richard W.

doi:10.2514/6.1991-58

Cited by 11 publications

(7 citation statements)

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“…(7) with Eq. (9). When the vehicle flies in the down phase, the factors K ρ and K LD are fixed during the trajectory prediction.…”

Section: Trajectory Predictionmentioning

confidence: 99%

“…[7,12]. Generally, the desired bank magnitude profile is obtained through an iteration technique, such as Newton-Raphson method [9,13], bisection method [10], secant method [7,14], and false position method [5,15]. It is remarked that improper lateral state in the first entry will result in a stressful crossrange or crossrange rate for the second entry.…”

mentioning

confidence: 99%

“…For simplicity, the bank magnitude profile is parameterized by one or more variables, such as single-variable profiles used in Refs. [4][5][6][9][10][11] and piecewise profiles used in Refs. [7,12].…”

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confidence: 99%

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Blended skip entry guidance for low-lifting lunar return vehicles

2014

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A skip entry guidance algorithm blending numerical predictor-corrector and nominal trajectory tracking is presented for lunar return vehicles. The guidance is decoupled into longitudinal and lateral channels. A piecewise bank-vs-energy magnitude profile and a sign profile are adopted in the skip phase. A magnitude parameter is used to adjust the predicted downrange, and a pseudo-crossrange at the beginning of the final phase is selected as the lateral control variable. Prediction biases of both channels are nullified by a false position iteration algorithm. An on-line estimation and modeling method is introduced to compensate for aerodynamic and atmospheric uncertainties. A nominal trajectory for the final phase is generated based on actual reenter conditions, and the obtained nominal trajectory is tracked by a linear feedback law. A lateral corridor is used to manage the lateral state. The proposed guidance algorithm is assessed using three-degree-of-freedom Monte Carlo analyses, and the results show a satisfactory and robust performance under highly stressful dispersions.

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“…(7) with Eq. (9). When the vehicle flies in the down phase, the factors K ρ and K LD are fixed during the trajectory prediction.…”

Section: Trajectory Predictionmentioning

confidence: 99%

mentioning

confidence: 99%

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Blended skip entry guidance for low-lifting lunar return vehicles

2014

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“…Bank angle modulation has been employed in all five of these schemes, which have been demonstrated on simulated AFE flights. Braun and Powell 13 have developed a three-phase, three-degree-of-freedom, predictorcorrector, guidance algorithm. The first phase uses a constant commanded bank angle calculated to yield the proper exit energy.…”

Section: Robust Roll Modulation Guidance For Aeroassisted Mars Missionmentioning

confidence: 99%

Robust roll modulation guidance for aeroassisted Mars mission

Thorp

Pierson

1995

Journal of Guidance, Control, and Dynamics

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The utility of using an aggregate measure of a vehicle's performance in determining the gains in a fixed-structure guidance scheme for an aeromaneuvering spacecraft so as to increase the "robustness" of the vehicle's performance is examined. The gains in the guidance scheme are determined by minimizing an "averaged" performance measure based upon the vehicle's flight through several different atmosphere models. This technique is applied to a Martian aeromaneuvering problem. Simulation results using gains determined by this method show a significant increase in off-nominal performance. A C D C L actual "target m n R r r a,exit; a, target r p,t\\ti Fp, target s V trigger w Y 8 f 9 V P /^nominal

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“…Consequently, these types of guidance algorithms have long been analyzed and simulated in various entry vehicles [7][8][9][10] and aero-assisted orbital transfer missions [11,12] for their feasibility and robustness. A standard PC algorithm uses numerical or analytical methods to integrate the translational equations of motion for the prediction of the final conditions and then a correctional step follows to nullify the final errors.…”

Section: Introductionmentioning

confidence: 99%

Prediction-based guidance algorithm for high-lift reentry vehicles

Zhang

Hu²

2011

Sci. China Inf. Sci.

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In this work, we propose a pseudo four-degrees-of-freedom (DOF) prediction based guidance algorithm specifically for high-lift reentry vehicles. The algorithm is composed mainly of three parts. First, at the beginning of each guidance cycle, the 4-DOF predictor is called upon to predict the final downrange, crossrange, and heading errors. Then, the magnitude of the bank angle is determined from the downrange error, using the proportional-integral (PI) control method. Finally, two bank angle reversal time points are determined to minimize the crossrange and heading errors. Compared with traditional predictor-corrector guidance, the algorithm proposed does not require iterative procedures which significantly decreases the computational burden for the on-board computer and makes the implementation practical. Simulation results for dispersion tests demonstrated that our algorithm is computationally efficient and robust against uncertainties and disturbances.

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A predictor-corrector guidance algorithm for use in high-energy aerobraking system studies

Cited by 11 publications

References 0 publications

Blended skip entry guidance for low-lifting lunar return vehicles

Blended skip entry guidance for low-lifting lunar return vehicles

Robust roll modulation guidance for aeroassisted Mars mission

Prediction-based guidance algorithm for high-lift reentry vehicles

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