Predictor-Corrector Reentry Guidance Algorithm with Path Constraints for Atmospheric Entry Vehicles

Joshi, Ashok; Sivan, K.; Amma, S. Savithri

doi:10.2514/1.26306

Cited by 76 publications

(33 citation statements)

References 10 publications

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“…These constraints given in (31)-(33) can be defined as the maximum allowable drag at any instant in the flight [8]. Because the reentry trials considered in this paper have not violated any of these maximums, these constraints are not considered explicitly.…”

Section: Reentry Constraintsmentioning

confidence: 99%

“…Because the reentry trials considered in this paper have not violated any of these maximums, these constraints are not considered explicitly. In certain cases, when some of these path constraints are activated, the bank angle modulation algorithms presented in subsection 3.1 is changed by a maximum allowable drag profile tracking method as in [8], until the constraints remain inactivated again.…”

Section: Reentry Constraintsmentioning

confidence: 99%

“…The drag and lift accelerations used in the predictor are updated online using the vehicle and environmental characteristics that are estimated during flight. The compensation algorithm given in [8,15] is used for this purpose, and is summarized here. The accelerometers, mounted on the vehicle, measure the aerodynamic accelerations in the body frame, as (a x , a y , a z ).…”

Section: Predictor Model Correctionmentioning

confidence: 99%

“…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%

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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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Section: Reentry Constraintsmentioning

confidence: 99%

Section: Reentry Constraintsmentioning

confidence: 99%

Section: Predictor Model Correctionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Prediction-based guidance algorithm for high-lift reentry vehicles

Zhang

Hu²

2011

Sci. China Inf. Sci.

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“…Analytic approaches using asymptotic expansions and optimal control techniques have been attempted for skip entry and aeroassist maneuvers [6,8,19,20]. With the advent of flight computers, onboard calculation of a trajectory has become viable through the use of numerical predictorcorrector methods [9,10,11,20,21,22,23,24,25,26]. These methods are not limited by the validity of the simplifications, approximations and empirical assumptions necessary for any analytical treatment, thus they hold greater potential to be more accurate and adaptive.…”

Section: Introductionmentioning

confidence: 99%

Skip Entry Trajectory Planning and Guidance

Brunner

2007

AIAA Guidance, Navigation and Control Conference and Exhibit

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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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Predictor-Corrector Reentry Guidance Algorithm with Path Constraints for Atmospheric Entry Vehicles

Cited by 76 publications

References 10 publications

Prediction-based guidance algorithm for high-lift reentry vehicles

Prediction-based guidance algorithm for high-lift reentry vehicles

Skip Entry Trajectory Planning and Guidance

Optimal feedback gains determination method for nominal reentry guidance

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