Revised Algorithm for Analytic Predictor-Corrector Aerocapture Guidance: Exit Phase

Hanak, Chad; Crain, Timothy; Masciarelli, James

doi:10.2514/6.2003-5746

Cited by 8 publications

(4 citation statements)

References 1 publication

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“…Crater estimation techniques have received significant renewed interest in the context of lunar exploration [47,48]. This technique has been especially considered for the case of lunar descent, where decimetre performances are usually targeted [16,49].…”

Section: Crater Navigationmentioning

confidence: 99%

Autonomous and Earth-Independent Orbit Determination for a Lunar Navigation Satellite System

Critchley-Marrows,

Wu,

Kawabata

et al. 2024

Aerospace

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In recent years, the number of expected missions to the Moon has increased significantly. With limited terrestrial-based infrastructure to support this number of missions, as well as restricted visibility over intended mission areas, there is a need for space navigation system autonomy. Autonomous on-board navigation systems in the lunar environment have been the subject of study by a number of authors. Suggested systems include optical navigation, high-sensitivity Global Navigation Satellite System (GNSS) receivers, and navigation-linked formation flying. This paper studies the interoperable nature and fusion of proposed autonomous navigation systems that are independent of Earth infrastructure, given challenges in distance and visibility. This capability is critically important for safe and resilient mission architectures. The proposed elliptical frozen orbits of lunar navigation satellite systems will be of special interest, investigating the derivation of orbit determination by non-terrestrial sources utilizing celestial observations and inter-satellite links. Potential orbit determination performances around 100 m are demonstrated, highlighting the potential of the approach for future lunar navigation infrastructure.

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Section: Crater Navigationmentioning

confidence: 99%

Autonomous and Earth-Independent Orbit Determination for a Lunar Navigation Satellite System

Critchley-Marrows,

Wu,

Kawabata

et al. 2024

Aerospace

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“…In each guidance cycle, after the determination of t mid , the complete bank angle magnitude profile can be defined by the above equation. Under the control of this profile, the state at atmospheric exit is obtained by numerical integration of the differential equations of motion, and then the post-aerocapture orbit and the velocity increment required for orbital insertion are determined by Equations ( 13)- (18). After that, we can correct t mid according to the deviation between the prediction and the target.…”

Section: Longitudinal Guidance Lawmentioning

confidence: 99%

“…Both algorithms are derived from the algorithm in the aerocapture flight test (AFE) [17]. Based on HYPAS, Chad Hanak et al [18] proposed an improved bank angle control law for the exit phase in Mars and Titan aerocapture. Through feedback linearization, the gain that is difficult to solve analytically and needs to change with mission parameters is eliminated.…”

Section: Introductionmentioning

confidence: 99%

Robust Near-Optimal Aerocapture Guidance Method Based on Saturation Function

et al. 2022

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Aerocapture maneuvers refer to a single atmospheric crossing to deplete orbital energy and establish a closed orbit. During the atmospheric flight, adjusting the spacecraft’s vertical lift component in an optimal manner, bang-bang bank control, will minimize the propulsion fuel consumption required to establish the target orbit. However, such methods have been suffering from the performance’s oversensitivity to the control’s instantaneous switching time and poor robustness. To address these problems, we propose a new numerical predictor-corrector guidance algorithm based on the saturation function profile in this paper. The saturation function is used to basically simulate the bang-bang control structure, which enhances the algorithm’s robustness by reducing its dependence on the relevant parameters without losing too much optimality. Monte Carlo simulations in both Earth and Mars scenarios demonstrate the robustness, accuracy, and near-optimal performance of the proposed guidance method.

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“…An alternate calculation for the bank angle control law of an aerocapture predictorcorrector guidance algorithm is proposed by Ref. [13]. This control law eliminates reference derived gains in an attempt to save time in configuring the guidance for new applications and make the guidance more adaptive to unpredicted changes in an aerocapture mission's environment.…”

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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Revised Algorithm for Analytic Predictor-Corrector Aerocapture Guidance: Exit Phase

Cited by 8 publications

References 1 publication

Autonomous and Earth-Independent Orbit Determination for a Lunar Navigation Satellite System

Autonomous and Earth-Independent Orbit Determination for a Lunar Navigation Satellite System

Robust Near-Optimal Aerocapture Guidance Method Based on Saturation Function

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

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