Feasibility of Guided Entry for a Crewed Lifting Body Without Angle-of-Attack Control

Putnam, Zachary R.; Grant, Michael J.; Kelly, Jenny R.; Braun, Robert D.; Krevor, Zachary C.

doi:10.2514/1.62214

Cited by 16 publications

(4 citation statements)

References 27 publications

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“…where uref = [αref, σref] is the reference control variable. Note that to improve the accuracy of the predictor, the onboard estimation and correction method in [32] is employed in calculating the lift and drag accelerations.…”

Section: B Closed-loop Predictor For Terminal Timementioning

confidence: 99%

Lateral Entry Guidance With Terminal Time Constraint

Liang

Chang

Zhu

2023

IEEE Trans. Aerosp. Electron. Syst.

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A simultaneous attack mission requires the entry vehicle to be capable of controlling the terminal time. To satisfy the terminal time constraint and meanwhile to cooperate with the previous longitudinal guidance algorithms, a lateral entry guidance method is developed using a closed-loop trajectory predictor for the terminal time, a bank reversal logic based on a double-corridor strategy, and a terminal time determination approach. The double-corridor contains a time error corridor used to activate the modification of the terminal time, and an adjustable heading corridor, when activated, used to reduce the terminal time error. The desired terminal time is calculated according to a feasibility index which describes the tolerance of aerodynamic dispersions. The simulations of a time constrained entry flight show that the lateral guidance method can achieve a high accuracy of the terminal time control while satisfying the conventional entry constraints. The advantage of the desired terminal time given by the feasibility index is also demonstrated.

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Section: B Closed-loop Predictor For Terminal Timementioning

confidence: 99%

Lateral Entry Guidance With Terminal Time Constraint

Liang

Chang

Zhu

2023

IEEE Trans. Aerosp. Electron. Syst.

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“…If we want uncertainties in additional parameters, other than reentry states, to be considered, it is necessary to include them in the equations of motion and add their contribution to the evolution of the density in Eq. (5). For example, in the case under examination, we want to consider an uncertainty over the ballistic coefficient β and include the possibility of taking into account uncertainty in the atmospheric density (through an atmospheric correction coefficient ξ).…”

Section: Uncertainty Propagationmentioning

confidence: 99%

“…This type of statistical analysis can be applied to several aspects of the re-entry problem. The design of crewed vehicles and their navigation algorithms can strongly benefit from an uncertainty analysis given the strict requirements on the sustainable loads and on the landing location [1][2][3][4][5]. The design of exploration probes and Presented as paper AAS 19-409 at the 29th AAS/AIAA Space Flight Mechanics Meeting, Ka'anapali, HI, 13 sample return missions can also gain from uncertainty quantification to improve the robustness of the mission [6][7][8] with the aim to increase the landing mass and precision and to provide more robust designs for the thermal protection and parachute deployment systems.…”

Section: Introductionmentioning

confidence: 99%

Propagation and Reconstruction of Reentry Uncertainties Using Continuity Equation and Simplicial Interpolation

Trisolini

Colombo

2021

Journal of Guidance, Control, and Dynamics

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This Paper proposes a continuum-based approach for the propagation of uncertainties in the initial conditions and parameters for the analysis and prediction of spacecraft reentries. Using the continuity equation together with the reentry dynamics, the joint probability distribution of the uncertainties is propagated in time for specific sampled points. At each time instant, the joint probability distribution function is then reconstructed from the scattered data using a gradient-enhanced linear interpolation based on a simplicial representation of the state space. Uncertainties in the initial conditions at reentry and in the ballistic coefficient for three representative test cases are considered: a three-state and a six-state steep Earth reentry and a six-state unguided lifting entry at Mars. The Paper shows the comparison of the proposed method with Monte Carlo-based techniques in terms of quality of the obtained marginal distributions and runtime as a function of the number of samples used.

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“…Because of their adaptive ability, flexibility, and wide applicability, numerical predictor-corrector entry guidance algorithms have in recent years become a primary choice for entry guidance. They have been extensively examined for skip entry missions [2][3][4][5][6] as well as direct entry for capsule vehicles [1,7] and lifting-body vehicles [1,[8][9][10][11][12]. Their potential applications in aerobraking and aerocapture missions have also shown great promise [13][14][15].…”

Section: Introductionmentioning

confidence: 99%

Entry Guidance Using Time-Scale Separation in Gliding Dynamics

2015

Journal of Spacecraft and Rockets

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Feasibility of Guided Entry for a Crewed Lifting Body Without Angle-of-Attack Control

Cited by 16 publications

References 27 publications

Lateral Entry Guidance With Terminal Time Constraint

Lateral Entry Guidance With Terminal Time Constraint

Propagation and Reconstruction of Reentry Uncertainties Using Continuity Equation and Simplicial Interpolation

Entry Guidance Using Time-Scale Separation in Gliding Dynamics

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