Statistical Entry, Descent, and Landing Performance Reconstruction of the Mars Science Laboratory

Dutta, Soumyo; Braun, Robert D.

doi:10.2514/1.a32937

Cited by 28 publications

(4 citation statements)

References 30 publications

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“…Generally, the orbit determination is operated using the dynamic statistical orbit determination method. This dynamic method is also used in Mars EDL (entry, descent and landing) trajectory reconstruction [11][12][13]. During the process of power landing and lunar surface launching, the spacecraft performs a large number of orbital maneuvers in a short time, leading to a complex trajectory.…”

Section: Introductionmentioning

confidence: 99%

Trajectory Determination of Chang’E-5 during Landing and Ascending

Yang

Huang

et al. 2021

Remote Sensing

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Chang’E-5 (CE-5) is China’s first lunar sample return mission. This paper focuses on the trajectory determination of the CE-5 lander and ascender during the landing and ascending phases, and the positioning of the CE-5 lander on the Moon. Based on the kinematic statistical orbit determination method using B-spline and polynomial functions, the descent and ascent trajectories of the lander and ascender are determined by using ground-based radiometric ranging, Doppler and interferometry data. The results show that a B-spline function is suitable for a trajectory with complex maneuvers. For a smooth trajectory, B-spline and polynomial functions can reach almost the same solutions. The positioning of the CE-5 lander on the Moon is also investigated here. Using the kinematic statistical positioning method, the landing site of the lander is 43.0590°N, 51.9208°W with an elevation of −2480.26 m, which is less than 200 m different from the LRO (Lunar Reconnaissance Orbiter) image data.

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Section: Introductionmentioning

confidence: 99%

Trajectory Determination of Chang’E-5 during Landing and Ascending

Yang

Huang

et al. 2021

Remote Sensing

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“…The GNC design is always a challenging task for various kinds of spacecraft with the descent and landing mission [2][3][4]. In previous Chang'E landing missions, Chang'E-3 and Chang'E-4 [5,6], landing guidance navigation and control (GNC) methods have been developed and successfully applied.…”

Section: Introductionmentioning

confidence: 99%

Guidance Navigation and Control for Chang’E-5 Powered Descent

Zhang¹,

Li²,

Wang³

et al. 2021

Space Sci Technol

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To achieve the goal of collecting lunar samples and return to the Earth for the Chang’E-5 spacecraft, the lander and ascender module (LAM) of the Chang’E-5 spacecraft successfully landed on the lunar surface on 1 Dec., 2020. The guidance, navigation, and control (GNC) system is one of the critical systems to perform this task. The GNC system of previous missions, Chang’E-3 and Chang’E-4, provides the baseline design for the Chang’E-5 LAM, and the new characteristics of the LAM, like larger mass and liquid sloshing, also bring new challenges for the GNC design. The GNC design for the descent and landing is presented in this paper. The guidance methods implemented in the powered descent are presented in detail for each phase. Propellant consumption and hazard avoidance should be particularly considered in the design. A reconfigurable attitude control is adopted which consists of the quaternion partition control, phase and gain stabilization filter, and dual observer. This controller could provide fast attitude maneuver and better system robustness. For the navigation, an intelligent heterogeneous sensor data fusion method is presented, and it is applied for the inertial measurement unit and velocimeter data. Finally, the flight results of the LAM are shown. Navigation sensors were able to provide valid measurement data during descent, and the thrusters and the main engine operated well as expected. Therefore, a successful soft lunar landing was achieved by the LAM.

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“…However, these quantities are of relevant importance in both post-flight analysis, to get accurate values of the actual flight trajectory and atmospheric conditions, and during the flight to be able to make adequate real-time corrections in case of manned flights. Different techniques for freestream characterization in post-flight analysis have been discussed in literature and applied to real flight Inria data [6,7,8]. They usually rely on Inertial Measurement Unit (IMU) and wall pressure data for the characterization of the freestream.…”

Section: Introductionmentioning

confidence: 99%

Forward and backward uncertainty quantification with active subspaces: Application to hypersonic flows around a cylinder

Cortesi

Constantine

Magin

et al. 2020

Journal of Computational Physics

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We perform a Bayesian calibration of the freestream velocity and density starting from measurements of the pressure and heat flux at the stagnation point of a hypersonic highenthalpy flow around a cylinder. The objective is to explore the possibility of using stagnation heat flux measurements, together with pressure measurements, to rebuild freestream conditions since such measurements are available for recent space missions but not exploited for freestream characterization. First, we formulate an algorithm of mesh adaptation, enabling accurate numerical solutions in an automatic way for a given set of inputs. Secondly, active subspaces are used to find a low-dimensional dependence structures in the input-to-output map of the forward numerical solver. Then, surrogate models on the active variables are used to accelerate the forward uncertainty propagation by Monte Carlo sampling and the Markov Chain Monte Carlo sampling of the posterior distribution for Bayesian inversion. A preliminary sensitivity analysis with sparse Polynomial Dimensional Decomposition is performed on the chemical model of the air mixture, to determine the most influential uncertain chemical parameters in the forward problem. Then, the forward and backward methodologies are applied to the simulation of a hypersonic flow around a cylinder, in conditions for which experimental data are available, revealing new insights towards the potential exploitation of heat flux data for freestream rebuilding.

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Statistical Entry, Descent, and Landing Performance Reconstruction of the Mars Science Laboratory

Cited by 28 publications

References 30 publications

Trajectory Determination of Chang’E-5 during Landing and Ascending

Trajectory Determination of Chang’E-5 during Landing and Ascending

Guidance Navigation and Control for Chang’E-5 Powered Descent

Forward and backward uncertainty quantification with active subspaces: Application to hypersonic flows around a cylinder

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