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Showing 1 to 14 of 14 for “"Mars entry"”.
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Navigation analysis and design for Mars entry
… system design for a lander module during entry at Mars. The system estimates the state vector with an extended Kalman filter, which utilizes update information provided by the following measurement types: two-way range with orbiting satellites, two-way Doppler with orbiting satellites, …
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Mars entry navigation performance analysis using Monte Carlo techniques
An atmospheric entry and descent full-state navigation filter is developed and presented. Using this filter a navigation performance analysis is performed to examine the effects of various instrument packages and differing sensor scenarios for the entry and descent phase of the Mars Aerial …
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Performance assessment of Mars entry systems with flap-based trajectory control
Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2022-11-14 without embargo terms
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An Iterative LQR Method for Addressing Model Uncertainty in the Mars Entry Problem
… as the future destinations beyond Earth orbit, Mars presents significant challenges to the entry, landing and descent sequence. Missions including sample return and human exploration require precise landing accuracy. Additionally, entry vehicle dynamics and atmospheric parameters at time of …
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Flight test of a supersonic decelerator on Earth to simulate a Mars entry
… of a decelerator (parachute) and spacecraft for entry through the atmosphere of the planet Mars by a flight test in the Earth's atmosphere. Engineering atmosphere models for Mars are defined and based on these models requirements for parachutes to be used for Mars entry are developed. Appropriate …
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A systems and cost analysis of human rated Mars entry, descent, and landing vehicles
… of the biggest obstacles to sending humans to Mars. However, spacecraft costs are typically not taken into consideration until after the preliminary vehicle and mission concepts have been designed. Once costs have been estimated, managers and project teams often lack confidence that the final …
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Uncertainty quantification applied to the analysis and design of a hypersonic inflatable aerodynamic decelerator for spacecraft reentry
… Aerodynamic Decelerator configuration for Mars entry, subject to uncertainty sources in the high-fidelity computational models and the operating conditions. Efficient uncertainty quantification methods based on stochastic expansions are applied to the analysis of the hypersonic flowfield, …
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Collocation Method and Model Predictive Control for Accurate Landing of a Mars EDL vehicle
… through which the accuracy in landing of a Mars entry-descent-landing (EDL) vehicle can be improved. The methods investigated include the collocation method and model predictive control (MPC). The primary control variable utilized in this study is the bank angle of the spacecraft, which is …
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Optimal lift and drag modulation hypersonic control options for high ballistic coefficient entry vehicles at Mars
Future Mars entry, descent, and landing (EDL) missions will require larger mass vehicles and payloads, especially if humans are to land on the surface. Current Mars EDL technology relies heavily on Viking-era supersonic parachutes that are approaching their landed mass limits; however, supersonic …
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Morphing Hypersonic Inflatable Aerodynamic Decelerator (HIAD) Mechanisms and Controls
To enable a crewed mission to Mars, precision landing capabilities of Entry, Descent, and Landing (EDL) systems must be improved. The need for larger payloads, higher landing sites, and controllability has motivated the National Aeronautics and Space Administration (NASA) to invest in new …
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Mars Precision Entry Vehicle Guidance Using Internal Moving Mass Actuators
Many landing sites of scientific interest on Mars including most of the Southern Hemisphere at elevations above 2km Mars Orbiter Laser Altimeter reference are inaccessible due to current limitations in precision entry guidance and payload deceleration. Precision guidance and large payload …
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Assessment of aerocapture-entry trajectories for human Mars exploration
… insert into an elliptic parking orbit prior to entry, descent, and landing is being explored for human Mars missions. These aerocapture-entry trajectories have advantages over a direct entry, but the advantages come at the cost of additional entry system mass. The goal of this research is to …
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Assessment of aerosurface-based hypersonic control of blunt bodies for planetary entry
Submission original under an indefinite embargo labeled 'Open Access'. The submission was exported from vireo on 2025-10-19 without embargo terms
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Hypersonic flight strategies for supersonic retropropulsion at Mars
Future large-scale Mars surface exploration missions require landed masses beyond the capability of current entry, descent, and landing technology. High-mass missions will likely use supersonic retropropulsion to increase landed mass, a paradigm shift from current supersonic parachute systems. This …