Blended control, predictor–corrector guidance algorithm: an enabling technology for Mars aerocapture

Jits, Roman; Walberg, Gerald D.

doi:10.1016/s0094-5765(03)00159-0

Cited by 27 publications

(15 citation statements)

References 5 publications

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“…In the paper, we will analyse first a simplest, one-parametric predictive guidance with only one control variable, namely, an AoA a=const. That is, only one terminal condition- (13) or (14)-may be taken into account. The fulfilment of velocity condition (14) is crucial, otherwise the soft landing is impossible.…”

Section: Mathematical Formulationmentioning

confidence: 99%

“…and relief elevation uncertainties. However, in order to solve the given eigenvalue problem we choose the condition of precision landing (13), checking the accomplishment of the constraint (14) on a solution and discarding the latter if final velocities were too high.…”

Section: Mathematical Formulationmentioning

confidence: 99%

“…From the mathematical point of view, a solution to the guidance problem formulated in Section 3 should be sought in a class of two-parametric control functions, because the corresponding eigenvalue problem involving four initial conditions (12) and two terminal ones (13) and (14) must have two eigenvalues to be found. The twoparametric control function may be chosen from various classes (algebraic, transcendental), but we will take the function being linear within a rangea 2 ½a min ,a max , i.e.…”

Section: Two-parametric Planning Predictive Algorithm and Its Adaptivmentioning

confidence: 99%

“…Powell [12] investigated the performance of the numerical predictor-corrector technique to guide a Mars lander to both the aerocapture objective and precision landing one, namely, to deploy a parachute within 10 km of a target. A more complex predictor-corrector technique having decoupled angle-of-attack (AoA) and bank angle control was also considered by Jits and Walberg [13] for the aerocapture case with the focus on guidance under multiple off-nominal conditions, including significant atmospheric and aerodynamic dispersions. Kluever [1] carried out the comparative performance analysis of pre-planned reference-path and predictive path-planning entry guidance methods for a lander modelled on the Mars Science Laboratory mission.…”

Section: Introductionmentioning

confidence: 99%

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Analysis of predictive entry guidance for a Mars lander under high model uncertainties

Kozynchenko¹

2011

Acta Astronautica

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a b s t r a c tThe problem of precision landing on Mars is now considered to be an essential challenge in the planned Mars missions. The paper focused on the guided atmospheric entry as a predominant phase in achieving a desired target state, as compared with the following parachute and powered descent. The predictive algorithms for the longitudinal guidance of a low-lift entry vehicle are treated. The purpose is to investigate applicability of the predictive strategy under possible high discrepancies between the on-board dynamic model and real environment while in entry trajectory. The comparative performance analysis based on computer simulation has been made between the standard one-parametric ''shooting'' predictive algorithm and a more complex two-parametric algorithm providing lower final velocity and, thus, expanding the interval of admissible downrange. However, both algorithms display considerable degradation of downrange accuracy in the cases when the actual drag force is larger than the modelled one. An acceptable solution has been found by including to both predictive guidance schemes an identification algorithm that repeatedly adapts the on-board model to varied environment in real time scale.

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Section: Mathematical Formulationmentioning

confidence: 99%

Section: Mathematical Formulationmentioning

confidence: 99%

Section: Two-parametric Planning Predictive Algorithm and Its Adaptivmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Analysis of predictive entry guidance for a Mars lander under high model uncertainties

Kozynchenko¹

2011

Acta Astronautica

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“…16 Due to their high accuracy and flexibility, numerical predictor-corrector guidance algorithms have become popular in recent years. [17][18][19][20] While open-loop aerocapture trajectory optimization has been extensively investigated, 8,21 performance optimization in terms of post-exit propellant consumption has not been explicitly addressed in most aerocapture (closed-loop) guidance algorithms, because of the challenges involved in directly solving the nonlinear optimal control problem on-board. Still, a few guidance schemes have taken performance into design considerations in various degrees.…”

Section: Introductionmentioning

confidence: 99%

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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Solving complex optimal control problems with nonlinear controls using trigonometric functions

Mall

Grant

Taheri

2020

Optim Control Appl Methods

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This study investigates the use of trigonometric functions to resolve two major issues encountered when solving practical optimal control problems (OCPs) that are characterized by nonlinear controls. First, OCPs with constraints on nonlinear controls require the solution to a multipoint boundary value problem, which poses additional computational difficulties. Second, in certain unconstrained OCPs with nonlinear controls, the extremum found from the necessary conditions can be opposite than expected (e.g., a maximum instead of a minimum) due to the absence of control options. The aforementioned issues and their effective resolution by using trigonometric functions are explained through two examples including a second‐order system problem and an aerocapture problem of a slender entry vehicle in the Martian atmosphere.

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Blended control, predictor–corrector guidance algorithm: an enabling technology for Mars aerocapture

Cited by 27 publications

References 5 publications

Analysis of predictive entry guidance for a Mars lander under high model uncertainties

Analysis of predictive entry guidance for a Mars lander under high model uncertainties

Optimal Aerocapture Guidance

Solving complex optimal control problems with nonlinear controls using trigonometric functions

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