Mars Science Laboratory: Entry, Descent, and Landing System Performance

Abstract: Describes the MSL EDL architecture and predicted landing performance, including guided lifting entry and parachute deploy that define the targeting footprint. Establishes the design landing ellipse for the first guided-entry Mars mission.


Mars Science Laboratory: Entry, Descent, and Landing System Overview

Abstract: System-level overview of MSL EDL: guided entry, supersonic parachute, powered descent, sky-crane. Source for the MSL guidance suite and its targeting capability relative to ballistic-entry predecessors.


Entry Guidance Performance for Mars Precision Landing

Journal of Guidance, Control, and Dynamics

Abstract: Evaluates reference-path (Apollo-heritage) versus predictive path-planning guidance for Mars entry via Monte Carlo simulation of an MSL-class vehicle. Core source for the guided-entry technology lever and its effect on landing dispersion.


Entry Guidance for the 2011 Mars Science Laboratory Mission

Abstract: Documents the specific entry-guidance algorithm flown by MSL, the first Mars mission with closed-loop guided lifting entry. Source for coding the guided-entry technology indicator at the MSL mission.


On the use of a range trigger for the Mars Science Laboratory Entry, Descent, and Landing

Abstract: Compares a navigated velocity trigger to a range-to-go (Smart Chute) parachute-deploy trigger, showing the range trigger reduces footprint. Primary quantitative source for the range-trigger technology lever.


Entry, Descent, and Landing Performance of the Mars Phoenix Lander

Abstract: Reports EDL performance of Phoenix, a ballistic-entry modern lander; provides the design ellipse for a late-era unguided mission, a control case distinguishing guided from unguided performance.


Statistical Reconstruction of Mars Entry, Descent, and Landing Trajectories and Atmospheric Profiles

Abstract: Statistical methodology for reconstructing Mars EDL trajectories and atmospheric profiles from flight data; methodological backbone for building a comparable cross-mission landing-accuracy series.


Mars 2020 Lander Vision System Flight Performance

Abstract: Mars 2020 delivered Perseverance to Jezero using TRN, the Lander Vision System, and Safe Target Selection. Primary source for the TRN lever and achieved precision at a hazardous site.


Making an Onboard Reference Map From MRO/CTX Imagery for Mars 2020 Lander Vision System

Abstract: Constructing the onboard georeferenced reference map from MRO Context Camera imagery against which LVS matches descent images. Evidences the maturing propositional base (orbital mapping) underlying TRN.


Real-Time Terrain Relative Navigation Test Results from a Relevant Environment for Mars Landing

Abstract: Real-time TRN performance in a relevant test environment ahead of Mars 2020. Establishes the technology-readiness trajectory of TRN prior to flight insertion.


Implementation of a Map Relative Localization System for Planetary Landing

Abstract: Map-relative localization architecture for planetary landing, generalizing the LVS approach. Supports treating TRN as an extensible, general planetary-landing capability.


Planetary landings with terrain sensing and hazard avoidance: A review

Abstract: Survey of terrain-sensing and hazard-avoidance for planetary landing, including TRN and HDA. Situates the three technology levers within the broader precision-landing field.


Mars Entry, Descent, and Landing Instrumentation 2 Trajectory, Aerodynamics, and Atmosphere Reconstruction

Abstract: MEDLI2 flight-data reconstruction of the Mars 2020 EDL trajectory, aerodynamics, atmosphere. Source for Mars 2020 reconstructed performance and the approach-accuracy control variable.


Reconstruction of Entry, Descent, and Landing Communications for the InSight Mars Lander

Abstract: Reconstructs the InSight EDL from communications data. Supports the InSight control case: a late, ballistic-entry lander targeted to a large flat ellipse.


Selection of the InSight Landing Site

Abstract: Documents InSight landing-site selection and the large, flat Elysium Planitia ellipse acceptable to an unguided lander. Linchpin control case that breaks time-technology collinearity in the identification strategy.


The Tianwen-1 Guidance, Navigation, and Control for Mars Entry, Descent, and Landing

Abstract: GNC for the Tianwen-1 Mars EDL. Out-of-sample, non-U.S. data point for external-validity discussion.


Crater Navigation System for Autonomous Precision Landing on the Moon

Abstract: Crater-based navigation for autonomous lunar precision landing. Establishes terrain-relative precision landing as a general planetary capability beyond Mars.


Forecasting technology costs via the experience curve - Myth or magic?

Technological Forecasting and Social Change

Abstract: Examines reliability and limits of experience-curve forecasting; warns the relationship is empirically powerful but not a law of nature and must be validated. Methodological grounding for the log-linear learning-rate model.


Re-examining rates of lithium-ion battery technology improvement and cost decline

Abstract: Estimates technology-improvement and cost-decline rates for lithium-ion batteries, separating mechanisms and disciplining the experience axis. Methodological template for estimating a learning rate carefully.


Taking the Pulse of the Economy: Measuring GDP

Landefeld, J. S.; Seskin, E. P.; Fraumeni, B. M.

Abstract: Modern restatement of the national-accounts measurement problem Kuznets pioneered. Anchors the Kuznetsian measurement discipline applied to the landing-ellipse series.


Measuring Economic Growth from Outer Space

Henderson, J. V.; Storeygard, A.; Weil, D. N.

Abstract: Uses satellite night-lights to proxy economic growth where national accounts are weak. Marks the lineage of the Kuznetsian satellite-account measurement ethic.


Technological revolutions and techno-economic paradigms

Abstract: Develops the techno-economic paradigm account in which a key enabling capability reorganizes a domain around itself. Published restatement of the Mokyrian point applied to onboard EDL guidance.


Hall of Shoulders dossier: Joel Mokyr - economic history of technology

Abstract: Mokyr distinction between propositional knowledge (knowing why) and prescriptive knowledge (the technique); techniques resting on a deep propositional base are extensible and self-correcting; the line between one-time macro-invention and sustained incremental improvement. Methodological anchor for the causal mechanism of the landing learning curve.


Hall of Shoulders dossier: Simon Kuznets - cliometric measurement

Abstract: Kuznets insistence that an aggregate is meaningless without a stated boundary of coverage, valuation convention, and netting rule; building long, comparable, decomposed series before theorizing; distinction between transient (level-shift) and secular movements with a warning against short-window extrapolation. Methodological anchor for the measurement construction of the ellipse series.


The contribution of new technology to economic growth: lessons from economic history

Revista de Historia Económica / Journal of Iberian and Latin American Economic History

Abstract: Abstract This paper reviews the analysis of technological change by cliometricians. It focuses on lessons about total factor productivity (TFP) from growth accounting and on aspects of social capability that are conducive to the effective assimilation of new technology. Key messages are that when TFP growth is very rapid this typically involves reductions in inefficiency not just technological advance and that even really important new technologies have small initial effects on aggregate productivity. Incentive structures matter greatly for the adoption of new technology, but social capability


Joel Mokyr's Contribution to the Nobel Prize: The Economic Growth Theory of Knowledge Dissemination and Institutional Innovation

Abstract: Joel Mokyr, the winner of the 2025 Nobel Prize in Economic Sciences, adopts an interdisciplinary perspective spanning economics and history, focusing on the "Great Divergence" issue. He has constructed a unique knowledge-based economic growth theory that profoundly reveals the origin of modern sustained economic growth. His core argument is that sustained growth relies on the accumulation and dissemination of "useful knowledge" (including propositional knowledge and prescriptive knowledge). The 17th-century "Baconian Program," by incentivizing scientific research and enhancing knowledge access


Organizational Differences in Rates of Learning: Evidence from the Adoption of Minimally Invasive Cardiac Surgery

Gary P. Pisano; Richard M.J. Bohmer; Amy C. Edmondson

Abstract: This paper examines learning curves in the health care setting to determine whether organizations achieve performance improvements from cumulative experience at different rates. Although extensive research has shown that cumulative experience leads to performance improvement across numerous contexts, the question of how much of this improvement is due to mere experience and how much is due to collective learning processes has received little attention. We argue that organizational learning processes may allow some organizations to benefit more than others from equivalent levels of experience.


Learning How and Learning What: Effects of Tacit and Codified Knowledge on Performance Improvement Following Technology Adoption

Amy C. Edmondson; Ann B. Winslow; Richard M.J. Bohmer; Gary P. Pisano

Abstract: ABSTRACT This paper examines effects of tacit and codified knowledge on performance improvement as organizations gain experience with a new technology. We draw from knowledge management and learning curve research to predict improvement rate heterogeneity across organizations. We first note that the same technology can present opportunities for improvement along more than one dimension, such as efficiency and breadth of use. We compare improvement for two dimensions: one in which the acquisition of codified knowledge leads to improvement and another in which improvement requires tacit knowledg


Learning Curve/Experience Curve Theory


Next Frontier of Experience Curve Application - Predicting Performance of Large Learning Systems by Kinked Experience Curve


Experience Curve


Aggregate National Accounts, SNA 1993: Gross domestic product (Edition 2019/1)


A concept for the entry, descent, and landing of high-mass payloads at Mars

Ashley M. Korzun; Gregory F. Dubos; Curtis Iwata; Benjamin Stahl


Overview of a Generalized Numerical Predictor-Corrector Targeting Guidance with Application to Human-Scale Mars Entry, Descent, and Landing

Rafael Lugo; Richard W. Powell; Alicia M. Dwyer-Cianciolo

Abstract: Recent advances in planetary entry guidance algorithms are motivated by precision landing criteria for human-scale Mars missions and improved in-space computing capabilities. An NPC targeting guidance algorithm, originally developed for the Mars Surveyor Program 2001 Missions, has been modified and extended to permit a fully generalized, flexible, and robust approach to spacecraft aerocapture and EDL guidance design. This paper describes this generalized targeting NPC guidance (NPCG) and how its modifications enable its use in precision targeting for human missions. System modeling, trajectory


Aerodynamics for Mars Phoenix Entry Capsule

Karl T. Edquist; Prasun N. Desai; Mark Schoenenberger

Abstract: Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.


Entry, Descent, and Landing Operations Analysis for the Mars Phoenix Lander

Jill L. Prince; Prasun N. Desai; Eric M. Queen; Myron R. Grover


Perseverance's Scanning Habitable Environments with Raman and Luminescence for Organics and Chemicals (SHERLOC) Investigation

R. Bhartia; L. W. Beegle; Lauren DeFlores; William Abbey

Abstract: Abstract The Scanning Habitable Environments with Raman and Luminescence for Organics and Chemicals (SHERLOC) is a robotic arm-mounted instrument on NASA's Perseverance rover. SHERLOC has two primary boresights. The Spectroscopy boresight generates spatially resolved chemical maps using fluorescence and Raman spectroscopy coupled to microscopic images (10.1 μm/pixel). The second boresight is a Wide Angle Topographic Sensor for Operations and eNgineering (WATSON); a copy of the Mars Science Laboratory (MSL) Mars Hand Lens Imager (MAHLI) that obtains color images from microscopic scales (∼13 μm/


The Mars 2020 Engineering Cameras and Microphone on the Perseverance Rover: A Next-Generation Imaging System for Mars Exploration

J. N. Maki; David Gruel; Colin McKinney; M. A. Ravine

Abstract: Abstract The Mars 2020 Perseverance rover is equipped with a next-generation engineering camera imaging system that represents an upgrade over previous Mars rover missions. These upgrades will improve the operational capabilities of the rover with an emphasis on drive planning, robotic arm operation, instrument operations, sample caching activities, and documentation of key events during entry, descent, and landing (EDL). There are a total of 16 cameras in the Perseverance engineering imaging system, including 9 cameras for surface operations and 7 cameras for EDL documentation. There are 3 ty


Mars Science Laboratory Mission and Science Investigation

J. P. Grotzinger; J. A. Crisp; A. R. Vasavada; Robert C. Anderson

Abstract: Scheduled to land in August of 2012, the Mars Science Laboratory (MSL) Mission was initiated to explore the habitability of Mars. This includes both modern environments as well as ancient environments recorded by the stratigraphic rock record preserved at the Gale crater landing site. The Curiosity rover has a designed lifetime of at least one Mars year (∼23 months), and drive capability of at least 20 km. Curiosity's science payload was specifically assembled to assess habitability and includes a gas chromatograph-mass spectrometer and gas analyzer that will search for organic carbon in rocks


Advancing Supersonic Retropropulsion Using Mars-Relevant Flight Data: An Overview

Robert D. Braun; Brandon Sforzo; Charles Campbell

AIAA SPACE and Astronautics Forum and Exposition

Abstract: Advanced robotic and human missions to Mars require landed masses well in excess of current capabilities. One approach to safely land these large payloads on the Martian surface is to extend the propulsive capability currently required during subsonic descent to supersonic initiation velocities. However, until recently, no rocket engine had ever been fired into an opposing supersonic freestream. In September 2013, SpaceX performed the first supersonic retropropulsion (SRP) maneuver to decelerate the entry of the first stage of their Falcon 9 rocket. Since that flight, SpaceX has continued to p


Innovative hazard detection and avoidance strategy for autonomous safe planetary landing


The Mars 2020 Perseverance Rover Mast Camera Zoom (Mastcam-Z) Multispectral, Stereoscopic Imaging Investigation

J. F. Bell; J. N. Maki; G. Mehall; M. A. Ravine

Abstract: Abstract Mastcam-Z is a multispectral, stereoscopic imaging investigation on the Mars 2020 mission's Perseverance rover. Mastcam-Z consists of a pair of focusable, 4:1 zoomable cameras that provide broadband red/green/blue and narrowband 400-1000 nm color imaging with fields of view from 25.6° × 19.2° (26 mm focal length at 283 μrad/pixel) to 6.2° × 4.6° (110 mm focal length at 67.4 μrad/pixel). The cameras can resolve (≥ 5 pixels) ∼0.7 mm features at 2 m and ∼3.3 cm features at 100 m distance. Mastcam-Z shares significant heritage with the Mastcam instruments on the Mars Science Laboratory Cu


Application of a Dual-Quaternion Six Degree-of-Freedom Guidance to Human-Scale Mars Entry, Descent, and Landing

Lugo, Rafael A.; Dutta, Soumyo; Manwell, Michael


Validation of Linear Covariance Techniques for Mars Entry, Descent, and Landing Guidance and Navigation Performance Analysis

Williams, James; Brandenburg, William E.; Woffinden, David; Putnam, Zachary R.


A General Approach to Terrain Relative Navigation for Planetary Landing

Johnson, Andrew; Ansar, Adnan; Matthies, Larry; Trawny, Nikolas

AIAA Infotech@Aerospace 2007 Conference and Exhibit


Mars Entry Navigation: Atmospheric Interface Through Parachute Deploy

AIAA Atmospheric Flight Mechanics Conference and Exhibit


Reefing the Mars Science Laboratory parachute


Mars 2007 Scout Phoenix Parachute Decelerator System Program Overview


Passive vs. parachute system architecture for robotic sample return vehicles

Abstract: The Multi-Mission Earth Entry Vehicle (MMEEV) is a flexible vehicle concept based on the Mars Sample Return (MSR) EEV design which can be used in the preliminary sample return mission study phase to parametrically investigate any trade space of interest to determine the best entry vehicle design approach for that particular mission concept. In addition to the trade space dimensions often considered (e.g. entry conditions, payload size and mass, vehicle size, etc.), the MMEEV trade space considers whether it might be more beneficial for the vehicle to utilize a parachute system during descent/l


Development of the Robotic Transfer Assembly System for Mars Sample Return

D. Chavez-Clemente; P. Younse; Corey W. Ballantoni; S. Backus

Abstract: The Robotic Transfer Assembly System (RTAS) is a robotic manipulation system within the Capture, Containment and Return System for Mars Sample Return. RTAS is designed to operate in Mars orbit and would be tasked with the mission-critical role of transferring the orbiting sample container from the capture section of the Earth Return Orbiter into the Earth Entry System, which protects the samples during atmospheric entry and landing on Earth. This paper describes the architecture, concept of operations, preliminary design, and various aspects of the development process for the RTAS system. Prel


Mars atmospheric entry guidance for reference trajectory tracking based on robust nonlinear compound controller


Preliminary assessment of the Mars Science Laboratory entry, descent, and landing simulation

Abstract: On August 5, 2012, the Mars Science Laboratory rover, Curiosity, successfully landed inside Gale Crater. This landing was the seventh successful landing and fourth rover to be delivered to Mars. Weighing nearly one metric ton, Curiosity is the largest and most complex rover ever sent to investigate another planet. Safely landing such a large payload required an innovative Entry, Descent, and Landing system, which included the first guided entry at Mars, the largest supersonic parachute ever flown at Mars, and the novel Sky Crane landing system. A complete, end-to-end, six degree-of-freedom, mu


Vision-Aided Inertial Navigation for Spacecraft Entry, Descent, and Landing

Anastasios I. Mourikis; Nikolas Trawny; Stergios I. Roumeliotis; Andrew Johnson

Abstract: In this paper, we present the vision-aided inertial navigation (VISINAV) algorithm that enables precision planetary landing. The vision front-end of the VISINAV system extracts 2-D-to-3-D correspondences between descent images and a surface map (mapped landmarks), as well as 2-D-to-2-D feature tracks through a sequence of descent images (opportunistic features). An extended Kalman filter (EKF) tightly integrates both types of visual feature observations with measurements from an inertial measurement unit. The filter computes accurate estimates of the lander's terrain-relative position, attitud


Vision-Aided Inertial Navigation for Precise Planetary Landing: Analysis and Experiments

Abstract: In this paper, we present the analysis and experimental validation of a vision-aided inertial navigation algorithm for planetary landing applications. The system employs tight integration of inertial and visual feature measurements to compute accurate estimates of the lander's terrain-relative position, attitude, and velocity in real time. Two types of features are considered: mapped landmarks, i.e., features whose global 3D positions can be determined from a surface map, and opportunistic features, i.e., features that can be tracked in consecutive images, but whose 3D positions are not known.


Terrain Relative Navigation for Planetary Landing Using Stereo Vision Measurements Obtained from Hazard Mapping


ChemCam activities and discoveries during the nominal mission of the Mars Science Laboratory in Gale crater, Mars

S. Maurice; S. M. Clegg; R. C. Wiens; O. Gasnault

Journal of Analytical Atomic Spectrometry

Abstract: At Gale crater, Mars, ChemCam acquired its first laser-induced breakdown spectroscopy (LIBS) target on Sol 13 of the landed portion of the mission (a Sol is a Mars day).


Mars exploration rovers entry, descent, and landing trajectory analysis

The Journal of the Astronautical Sciences


A passive Earth-entry capsule for Mars Sample Return

Robert Mitcheltree; S. Kellas; John T. Dorsey; Prasun N. Desai

Abstract: A combination of aerodynamic analysis and testing, aerothermodynamic analysis, structural analysis and testing, impact analysis and testing, thermal analysis, ground characterization tests, configuration packaging, and trajectory simulation are employed to determine the feasibility of an entirely passive Earth entry capsule for the Mars Sample Return mission. The design circumvents the potential failure modes of a parachute terminal descent system by replacing that system with passive energy absorbing material to cushion the Mars samples during ground impact. The suggested design utilizes a sp


Mars Exploration Rover mission

J. A. Crisp; Mark Adler; J. Matijevic; S. W. Squyres

Journal of Geophysical Research Atmospheres

Abstract: In January 2004 the Mars Exploration Rover mission will land two rovers at two different landing sites that show possible evidence for past liquid‐water activity. The spacecraft design is based on the Mars Pathfinder configuration for cruise and entry, descent, and landing. Each of the identical rovers is equipped with a science payload of two remote‐sensing instruments that will view the surrounding terrain from the top of a mast, a robotic arm that can place three instruments and a rock abrasion tool on selected rock and soil samples, and several onboard magnets and calibration targets. Engi


57th International Astronautical Congress

Abstract: ESA is planning a series of robotic missions to Mars, the safe delivery of which will be greatly assisted by landing systems capable of autonomous navigation and hazard detection and avoidance. Vision-based navigation is a promising technique which is currently being developed by ESA. The testing of vision-based navigation systems can benefit from computer-based planet surface simulations representative of the target planetary body. PANGU (Planet and Asteroid Natural Scene Generation Utility) is a software tool for simulating and visualising the surface of various planetary bodies. PANGU build


Samples Collected From the Floor of Jezero Crater With the Mars 2020 Perseverance Rover

Justin I. Simon; Keyron Hickman‐Lewis; B. A. Cohen; L. E. Mayhew

Abstract: Abstract The first samples collected by the Mars 2020 mission represent units exposed on the Jezero Crater floor, from the potentially oldest Séítah formation outcrops to the potentially youngest rocks of the heavily cratered Máaz formation. Surface investigations reveal landscape‐to‐microscopic textural, mineralogical, and geochemical evidence for igneous lithologies, some possibly emplaced as lava flows. The samples contain major rock‐forming minerals such as pyroxene, olivine, and feldspar, accessory minerals including oxides and phosphates, and evidence for various degrees of aqueous activ


Single Image Super-Resolution Restoration of TGO CaSSIS Colour Images: Demonstration with Perseverance Rover Landing Site and Mars Science Targets

Yu Tao; Susan J. Conway; Jan‐Peter Müller; Alfiah Rizky Diana Putri

Abstract: The ExoMars Trace Gas Orbiter (TGO)'s Colour and Stereo Surface Imaging System (CaSSIS) provides multi-spectral optical imagery at 4-5 m/pixel spatial resolution. Improving the spatial resolution of CaSSIS images would allow greater amounts of scientific information to be extracted. In this work, we propose a novel Multi-scale Adaptive weighted Residual Super-resolution Generative Adversarial Network (MARSGAN) for single-image super-resolution restoration of TGO CaSSIS images, and demonstrate how this provides an effective resolution enhancement factor of about 3 times. We demonstrate with qua


Vision System for the Mars Sample Return Capture Containment and Return System (CCRS)

Brent J. Bos; David L. Donovan; J. Capone; Chen Wang

Abstract: The successful 2020 launch and 2021 landing of the National Aeronautics and Space Administration's (NASA) Perseverance Mars rover initiated the first phase of the NASA and European Space Agency (ESA) Mars Sample Return (MSR) campaign. The goal of the MSR campaign is to collect scientifically interesting samples from the Martian surface and return them to Earth for further study in terrestrial laboratories. The MSR campaign consists of three major spacecraft components to accomplish this objective: the Perseverance Mars rover, the Sample Retrieval Lander (SRL) and the Earth Return Orbiter (ERO)


Mars Entry, Descent, and Landing guidance under dynamic uncertainty


Mars Atmospheric Entry, Descent, and Landing: An Atmospheric Perspective

Oxford Research Encyclopedia of Planetary Science


Vision-based Terrain Relative Navigation for Planetary Landing


A Review of Vision-Based Terrain Relative Navigation for Planetary Descent and Landing of Space Vehicles

Abdhul Rahuman, Mohomad Aqeel; Lee, Kyuman

International Journal of Aeronautical and Space Sciences


GEOMORPHIC MAPPING OF THE BASEMENT UNIT WITHIN THE NORTHEAST SYRTIS MARS 2020 LANDING ELLIPSE

Geological Society of America Abstracts with Programs


Entry, Descent, and Landing with Propulsive Deceleration: Supersonic Retropropulsion Wind Tunnel Testing

50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition

Abstract: The future exploration of the Solar System will require innovations in transportation and the use of entry, descent, and landing (EDL) systems at many planetary landing sites. The cost of space missions has always been prohibitive, and using the natural planetary and planet s moons atmosphere for entry, descent, and landing can reduce the cost, mass, and complexity of these missions. This paper will describe some of the EDL ideas for planetary entry and survey the overall technologies for EDL that may be attractive for future Solar System missions. Future EDL systems may include an inflatable


Performance evaluation of hazard detection and avoidance algorithms for safe Lunar landings

A. Huertas; Andrew Johnson; Robert A. Werner; Robert A. Maddock

Abstract: Unmanned planetary landers to date have landed ¿blind¿; that is, without the benefit of onboard landing hazard detection and avoidance systems. This constrains landing site selection to very benign terrain, which in turn constrains the scientific agenda of missions. Systems for automatic surface reconstruction and for hazard detection, mapping, and assessment are becoming mature. Before they can be put to practical use, it is essential to be able to characterize their performance for the purposes of scientific evaluation and their utility to engineers planning and designing landed missions. It


Mars Pathfinder Atmospheric Entry Reconstruction

Kallemeyn, P. H.; Peng, C. Y.; Braun, R. D.; Thurman, S. W.

Abstract: The primary objective of the Mars Pathfinder mission was to demonstrate an innovative, low-cost and reliable method for placing a science payload on the surface of Mars. This paper describes the results of an effort to access the spacecraft performance during Entry, Descent and Landing.


Mars Science Laboratory Entry, Descent, and Landing Trajectory and Atmosphere Reconstruction

Karlgaard, Christopher D.; Kutty, Prasad; Schoenenberer, Mark; Shidner, Jeremy D.

Abstract: On August 5th 2012, The Mars Science Laboratory entry vehicle successfully entered Mars atmosphere and landed the Curiosity rover on its surface. A Kalman filter approach has been implemented to reconstruct the entry, descent, and landing trajectory based on all available data. The data sources considered in the Kalman filtering approach include the inertial measurement unit accelerations and angular rates, the terrain descent sensor, the measured landing site, orbit determination solutions for the initial conditions, and a new set of instrumentation for planetary entry reconstruction consisti


Mars 2020 Entry, Descent and Landing Instrumentation 2 (MEDLI2)

Hwang, Helen H.; Bose, Deepak; White, Todd R.; Wright, Henry S.

Abstract: The Mars Entry Descent and Landing Instrumentation 2 (MEDLI2) sensor suite will measure aerodynamic, aerothermodynamic, and TPS performance during the atmospheric entry, descent, and landing phases of the Mars 2020 mission. The key objectives are to reduce design margin and prediction uncertainties for the aerothermal environments and aerodynamic database. For MEDLI2, the sensors are installed on both the heatshield and backshell, and include 7 pressure transducers, 17 thermal plugs, and 3 heat flux sensors (including a radiometer). These sensors will expand the set of measurements collected b


Mars InSight Entry, Descent, and Landing Trajectory and Atmosphere Reconstruction

Christopher D Karlgaard; Ashley M Korzun; Mark Schoenenberger; Eugene P Bonfiglio

Abstract: The InSight mission landed on the surface of Mars on November 26th, 2018. The InSight system performance met all design requirements, although several performance metrics fell near the boundaries of the predictions. The peak deceleration was high, the overall timeline was short, and the landing site was uprange and crossrange from the target.  This paper describes the reconstruction of the entry, descent, and landing trajectory and atmosphere. The approach utilizes a Kalman filter to blend sensor data to obtain the vehicle trajectory. The aerodynamic database is used in combination with the se


Mars Science Laboratory Entry, Descent and Landing System Development Challenges and Preliminary Flight Performance

Steltzner, Adam D.; San Martin, A. Miguel; Rivellini, Tommaso P.

Abstract: The Mars Science Laboratory project recently landed the Curiosity rover on the surface of Mars. With the success of the landing system, the performance envelope of entry, descent, and landing capabilities has been extended over the previous state of the art. This paper will present an overview of the MSL entry, descent, and landing system, a discussion of a subset of its development challenges, and include a discussion of preliminary results of the flight reconstruction effort.


Mars 2020 Entry, Descent and Landing Instrumentation (MEDLI2)

Bose, Deepak; Wright, Henry; White, Todd; Schoenenberger, Mark

Abstract: This paper will introduce Mars Entry Descent and Landing Instrumentation (MEDLI2) on NASA's Mars2020 mission. Mars2020 is a flagship NASA mission with science and technology objectives to help answer questions about possibility of life on Mars as well as to demonstrate technologies for future human expedition. Mars2020 is scheduled for launch in 2020. MEDLI2 is a suite of instruments embedded in the heatshield and backshell thermal protection systems of Mars2020 entry vehicle. The objectives of MEDLI2 are to gather critical aerodynamics, aerothermodynamics and TPS performance data during EDL p


Mars Science Laboratory Navigation Results

Martin-Mur, Tomas J.; Kruizingas, Gerhard L.; Burkhart, P. Daniel; Wong, Mau C.

Abstract: The Mars Science Laboratory (MSL), carrying the Curiosity rover to Mars, was launched on November 26, 2011, from Cape Canaveral, Florida. The target for MSL was selected to be Gale Crater, near the equator of Mars, with an arrival date in early August 2012. The two main interplanetary navigation tasks for the mission were to deliver the spacecraft to an entry interface point that would allow the rover to safely reach the landing area, and to tell the spacecraft where it entered the atmosphere of Mars, so it could guide itself accurately to close proximity of the landing target. MSL used entry


Mars 2020 Perseverance Edl Gnc Safe Target Selection Reconstruction

Dutta, Soumyo; Way, David W.; Casoliva, Jordi; Brugarolas, Paul

Abstract: On February 18th, 2021, NASA landed Perseverance on the Jezero crater (on Mars) using a new Terrain Relative Navigation (TRN) capability. TRN is com-prised of a new sensor, the Lander Vision System (LVS), and a new GNC algo-rithm, the Safe Target Selection (STS). LVS localized the descent vehicle with respect to a map. STS selected the safe landing target within a reachable region from the on-board Safe Targets Map (STM). The landing target was then handed to the Mars Science Laboratory (MSL) heritage powered descent GNC system to execute the landing. This paper describes the design and the as


Deep visual odometry and pose reconstruction through single image depth map and triangulation for terrain relative navigation


Towards sustainable horizons: A comprehensive blueprint for Mars colonization

Abstract: This paper thoroughly explores the feasibility, challenges, and proposed solutions for establishing a sustainable human colony on Mars. We quantitatively and qualitatively analyze the Martian environment, highlighting key challenges such as radiation exposure, which astronauts could experience at minimum levels of 0.66 sieverts during a round trip, and the complications arising from Mars' thin atmosphere and extreme temperature variations. Technological advancements are examined, including developing Martian concrete, which utilizes sulfur as a binding agent, and innovative life support strate


Mars Exploration Rovers Landing Dispersion Analysis

Knocke, Philip; Wawrzyniak, Geoffrey; Kennedy, Brian; Desai, Prasun

AIAA/AAS Astrodynamics Specialist Conference and Exhibit


Probabilistic regression for autonomous terrain relative navigation via multi-modal feature learning

Abstract: The extension of human spaceflight across an ever-expanding domain, in conjunction with intricate mission architectures demands a paradigm shift in autonomous navigation algorithms, especially for the powered descent phase of planetary landing. Deep learning architectures have previously been explored to perform low-dimensional localization with limited success. Due to the expectations regarding novel algorithms in the context of real missions, the proposed approaches must be rigorously evaluated in extraneous scenarios and demonstrate sufficient robustness. In the current work, a novel formul


Landing Site Dispersion Analysis and Statistical Assessment for the Mars Phoenix Lander

E. Bonfiglio; D. Adams; Lynn E. Craig; D. Spencer


Mars Pathfinder atmospheric entry - Trajectory design and dispersion analysis


Synopsis of Precision Landing and Hazard Avoidance (PL&HA) Capabilities for Space Exploration

Abstract: Until recently, robotic exploration missions to the Moon, Mars, and other solar system bodies relied upon controlled blind landings. Because terrestrial techniques for terrain relative navigation (TRN) had not yet been evolved to support space exploration, landing dispersions were driven by the capabilities of inertial navigation systems combined with surface relative altimetry and velocimetry. Lacking tight control over the actual landing location, mission success depended on the statistical vetting of candidate landing areas within the predicted landing dispersion ellipse based on orbital re


Integrated Precision Landing Performance and Technology Assessments of a Human-Scale Mars Lander Using a Generalized Simulation Framework

Rafael A Lugo; Alicia Dwyer Cianciolo; R Anthony Williams; Soumyo Dutta

Abstract: Human-scale missions to Mars will likely require multiple landers delivered precisely to designated locations. The current NASA human Mars reference architecture assumes delivery of three 25 t payloads from a 1- or 5-Sol orbit to the surface with a landing precision of 50 m to ensure logistics are located near the habitat. While initial navigation estimates improve with on-orbit ground tracking, errors increase during post-deorbit coast. Likewise, Mars atmospheric variability and forecasting uncertainty means that the entry vehicle guidance, navigation, and control systems must be robust to ac


Mars Entry Guidance for High Elevation Landing with Uncertainty Quantification and Reduction

22nd AIAA International Space Planes and Hypersonics Systems and Technologies Conference


Fast Monte Carlo Analysis For 6-DoF Powered-Descent Guidance via GPU-Accelerated Sequential Convex Programming

G. M. Chari; Abhinav G. Kamath; Purnanand Elango; Behçet Açikmese

Abstract: We introduce a GPU-accelerated Monte Carlo framework for nonconvex, free-final-time trajectory optimization problems. This framework makes use of the prox-linear method, which belongs to the larger family of sequential convex programming (SCP) algorithms, in conjunction with a constraint reformulation that guarantees inter-sample constraint satisfaction. Key features of this framework are: (1) continuous-time constraint satisfaction; (2) a matrix-inverse-free solution method; (3) the use of the proportional-integral projected gradient (PIPG) method, a first-order convex optimization solver, cu


Entry Dispersion Analysis for the Stardust Comet Sample Return Capsule

Prasun N. Desai; Robert Mitcheltree; F. McNeil Cheatwood

Abstract: Covers advancements in spacecraft and tactical and strategic missile systems, including subsystem design and application, mission design and analysis, materials and structures, developments in space sciences, space processing and manufacturing, space operations, and applications of space technologies to other fields.


Heuristic Decision Making

Abstract: As reflected in the amount of controversy, few areas in psychology have undergone such dramatic conceptual changes in the past decade as the emerging science of heuristics. Heuristics are efficient cognitive processes, conscious or unconscious, that ignore part of the information. Because using heuristics saves effort, the classical view has been that heuristic decisions imply greater errors than do "rational" decisions as defined by logic or statistical models. However, for many decisions, the assumptions of rational models are not met, and it is an empirical rather than an a priori issue how


Flight testing of terrain-relative navigation and large-divert guidance on a VTVL rocket

Nikolas Trawny; Joel Benito; Brent Tweddle; Charles Bergh

AIAA SPACE 2015 Conference and Exposition

Abstract: Since 2011, the Autonomous Descent and Ascent Powered-Flight Testbed (ADAPT) has been used to demonstrate advanced descent and landing technologies onboard the Masten Space Systems (MSS) Xombie vertical-takeoff, vertical-landing suborbital rocket. The current instantiation of ADAPT is a stand-alone payload comprising sensing and avionics for terrain-relative navigation and fuel-optimal onboard planning of large divert trajectories, thus providing complete pin-point landing capabilities needed for planetary landers. To this end, ADAPT combines two technologies developed at JPL, the Lander Visio


Convex Programming Approach to Powered Descent Guidance for Mars Landing

Journal of Guidance Control and Dynamics

Abstract: We present a convex programming algorithm for the numerical solution of the minimum fuel powered descent guidance problem associated with Mars pinpoint landing. Our main contribution is the formulation of the trajectory optimization problem, which has nonconvex control constraints, as a finite-dimensional convex optimization problem, specifically as a second-order cone programming problem. Second-order cone programming is a subclass of convex programming, and there are efficient second-order cone programming solvers with deterministic convergence properties. Consequently, the resulting guidanc


Adaptive powered descent guidance based on multi-phase pseudospectral convex optimization


Enhancements on the Convex Programming Based Powered Descent Guidance Algorithm for Mars Landing

Behçet Açıkmeşe; Daniel P. Scharf; Lars Blackmore; Aron A. Wolf

Abstract: In this paper, we present enhancements on the powered descent guidance algorithm developed for Mars pinpoint landing. The guidance algorithm solves the powered descent minimum fuel trajectory optimization problem via a direct numerical method. Our main contribution is to formulate the trajectory optimization problem, which has nonconvex control constraints, as a finite dimensional convex optimization problem, specifically as a finite dimensional second order cone programming (SOCP) problem. SOCP is a subclass of convex programming, and there are efficient SOCP solvers with deterministic conver


A Powered Descent Guidance Algorithm for Mars Pinpoint Landing

AIAA Guidance, Navigation, and Control Conference and Exhibit

Abstract: We present a powered descent guidance algorithm for Mars pinpoint landing that solves the minimum fuel trajectory optimization problem via a direct numerical method. Our main contribution is the formulation of the trajectory optimization problem, which has nonconvex control constraints, as a finite dimensional convex optimization problem, specifically as a finite dimensional semidefinite program (SDP). Since efficient SDP solvers with deterministic convergence properties exist, the resulting guidance algorithm can potentially be implemented onboard. In this paper, we present a powered descent


Guidance of Reusable Launchers: Improving Descent and Landing Performance

Pedro Simplício; Andrés Marcos; Samir Bennani

Abstract: The sizing and capability definitions of reusable launchers during high-speed recovery are very challenging problems. In this paper, a convex optimization guidance algorithm for this type of system is proposed, based on performance improvements arising from the study of the coupled flight mechanics, guidance, and control problem. To appreciate the obtained improvements, tradeoff analyses of powered descent and landing scenarios are presented first using traditional guidance techniques. Subsequently, these results are refined by using the proposed online successive convex optimization-based gui


Constrained Reachability and Controllability Sets for Planetary Precision Landing via Convex Optimization

Utku Eren; Daniel Dueri; Behçet Açıkmeşe

Abstract: This paper presents a convex optimizations-based method to compute the set of initial conditions from which a given landing accuracy to a target can be achieved (constrained controllability set) and the set of states that can be reached from a given set of initial states (constrained reachability set) for a planetary landing vehicle with all the relevant control and mission constraints. The proposed method is based on the lossless convexification of the powered-descent landing guidance problem and methods of convex optimization and computational geometry. These techniques are used to generate


Mid Lift-to-Drag Rigid Vehicle 6-DoF Performance for Human Mars Entry, Descent, and Landing: A Fractional Polynomial Powered Descent Guidance Approach

Johnson, Breanna J.; Lu, Ping; Sostaric, Ronald R.


Pseudospectral Convex Optimization for Powered Descent and Landing

Journal of Guidance, Control, and Dynamics


Generalized hp Pseudospectral Convex Programming for Powered Descent and Landing

2018 AIAA Guidance, Navigation, and Control Conference


Obstacle avoidance guidance for Mars powered descent using convex optimization and elevation angle


Convex programming based method for stochastic optimal powered descent guidance with Wasserstein terminal cost


Olfactory-based powered descent guidance for Mars methane plume exploration in long-time-average wind environment


Transformer-Based Tight Constraint Prediction for Efficient Powered Descent Guidance


Tight Constraint Prediction of Six-Degree-of-Freedom Transformer-based Powered Descent Guidance

AIAA Science and Technology Forum and Exposition AIAA Scitech Forum 2025


Sequential Convex Programming for 6-DoF Powered Descent Guidance with Continuous-Time Compound State-Triggered Constraints

Samet Uzun; Behçet Açikmese; John M. Carson

Abstract: This paper presents a sequential convex programming (SCP) framework for ensuring the continuous-time satisfaction of compound state-triggered constraints, a subset of logical specifications, in the powered descent guidance (PDG) problem. The proposed framework combines the generalized mean-based smooth robustness measure (D-GMSR), a parameterization technique tailored for expressing discrete-time temporal and logical specifications through smooth functions, with the continuous-time successive convexification (CT-SCvx) method, a real-time solution for constrained trajectory optimization that gu


Fuel-optimal powered descent guidance with free final-time and path constraints


Survey of autonomous guidance methods for powered planetary landing

Zhengyu Song; Cong Wang; Stephan Theil; David Seelbinder

Frontiers of Information Technology & Electronic Engineering

Abstract: This paper summarizes the autonomous guidance methods (AGMs) for pinpoint soft landing on celestial surfaces. We first review the development of powered descent guidance methods, focusing on their contributions for dealing with constraints and enhancing computational efficiency. With the increasing demand for reusable launchers and more scientific returns from space exploration, pinpoint soft landing has become a basic requirement. Unlike the kilometer-level precision for previous activities, the position accuracy of future planetary landers is within tens of meters of a target respecting all


Innovative hazard detection and avoidance guidance for safe lunar landing

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering

Abstract: Safe planetary landing is considered a key technology for future robotic and manned planetary landing missions. The relay hazard detection and proportion-integration-differentiation avoidance guidance algorithms were used in Chang'e-3 mission, which not only increased the complexity of the guidance system, but also resulted in non-fuel-optimal avoidance guidance from the viewpoint of fuel consumption. To further develop and improve the hazard detection and avoidance scheme of Chang'e-3, novel autonomous hazard avoidance methodologies should be investigated. This paper addresses an innovative h


P63-64 Powered Descent Guidance


Development of Supersonic Retropropulsion for Future Mars Entry, Descent, and Landing Systems

Karl T. Edquist; Ashley M. Korzun; Artem Dyakonov; Joseph W. Studak

Abstract: Recent studies have concluded that Viking-era entry system deceleration technologies are extremely difficult to scale for progressively larger payloads (tens of metric tons) required for human Mars exploration. Supersonic retropropulsion is one of a few developing technologies that may enable future human-scale Mars entry systems. However, in order to be considered as a viable technology for future missions, supersonic retropropulsion will require significant maturation beyond its current state. This paper proposes major milestones for advancing the component technologies of supersonic retropr


Human Mars Entry, Descent and Landing Architecture Study Overview

Tara Polsgrove; Alicia M. Dwyer-Cianciolo

Abstract: The Entry, Descent, and Landing (EDL) Architecture Study is a multi-NASA center activity to analyze candidate EDL systems as they apply to human Mars landing in the context of the Evolvable Mars Campaign. The study, led by the Space Technology Mission Directorate (STMD), is performed in conjunction with the NASA's Science Mission Directorate and the Human Architecture Team, sponsored by NASA's Human Exploration and Operations Mission Directorate. The primary objective is to prioritize future STMD EDL technology investments by (1) generating Phase A-level designs for selected concepts to delive


Human Mars Entry, Descent, and Landing Architecture Study: Rigid Decelerators

Tara Polsgrove; Alicia M. Dwyer-Cianciolo; Edward A. Robertson; Thomas K. Percy

2018 AIAA SPACE and Astronautics Forum and Exposition

Abstract: Several technology investments are required to develop Mars human scale Entry, Descent, and Landing (EDL) systems. Studies play the critical role of identifying the most feasible technical paths and high payoff investments. The goal of NASA's Entry, Descent and Landing Architecture Study is to inform those technology investments. In Phase 1 of the study, a point design for one lifting-body-like rigid decelerator vehicle, was developed. In Phase 2, a capsule concept was also considered to determine how it accommodated the human mission requirements. This paper summarizes the concept of operatio


Autonomous Landing and Hazard Avoidance Technology (ALHAT)

Chirold Epp; Edward A. Robertson; Tye Brady

Abstract: The ALHAT project is funded by NASA to develop an integrated AGNC (autonomous guidance, navigation and control) hardware and software system capable of detecting and avoiding surface hazards and guiding humans and cargo safely, precisely and repeatedly to designated lunar landing sites. There are important interdependencies driving the design of a lunar landing system including such things as lander hazard robustness, landing site conditions (terrain and natural lighting), trajectories, sensors, crew involvement, and others. The ALHAT system must be capable of operating in a wide range of luna


Probabilistic Hazard Detection for Autonomous Safe Landing

Tonislav Ivanov; A. Huertas; John M. Carson

AIAA Guidance, Navigation, and Control (GNC) Conference

Abstract: Future generation of landing craft will autonomously look at the surface during the terminal phase of powered descent and then, in real-time, choose and divert to a safe landing site in order to avoid hazards. Enabling technologies for such capability have been under development in recent years in the Autonomous Landing Hazard Avoidance Technology (ALHAT) project funded by NASA's Exploration Technology Development Program. ALHAT is a comprehensive system that spans the approach and landing events - from de-orbit coasting to touchdown. In this paper, we focus on ALHAT's perception task of detec


Real-Time Hazard Detection and Avoidance Demonstration for a Planetary Lander

Chirold Epp; Ed Robertson; John M. Carson

AIAA SPACE 2014 Conference and Exposition

Abstract: The Autonomous Landing Hazard Avoidance Technology (ALHAT) Project is chartered to develop and mature to a Technology Readiness Level (TRL) of six an autonomous system combining guidance, navigation and control with terrain sensing and recognition functions for crewed, cargo, and robotic planetary landing vehicles. In addition to precision landing close to a pre-mission defined landing location, the ALHAT System must be capable of autonomously identifying and avoiding surface hazards in real-time to enable a safe landing under any lighting conditions. This paper provides an overview of the rec


Overview of Terrain Relative Navigation Approaches for Precise Lunar Landing

Johnson, Andrew E.; Montgomery, James F.


Analysis and Testing of a LIDAR-Based Approach to Terrain Relative Navigation for Precise Lunar Landing

AIAA Guidance, Navigation, and Control Conference


Optical Terrain Relative Navigation Approaches to Lunar Orbit, Descent and Landing

Steffes, Stephen R.; Monterroza, Fredy; Benhacine, Lylia; Mario, Courtney


Autonomous Precision Landing and Hazard Detection and Avoidance Technology (ALHAT)

Abstract: As NASA plans to send humans back to the Moon and develop a lunar outpost, technologies must be developed to place humans and cargo safely, precisely, repeatedly, on the lunar surface with the capability to avoid surface hazards. Exploration Space Architecture Study requirements include the need for global lunar surface access with safe, precise landing without lighting constraints on terrain that may have landing hazards for human scale landing vehicles. Landing accuracies of perhaps 100's of meters for sortie crew missions to 10's of meters for Outpost class missions are required. The Autono


Mars 2020 Entry, Descent, and Landing System Overview

Adam Nelessen; Chloe Sackier; Ian G. Clark; Paul Brugarolas

Abstract: Building upon the success of the Mars Science Laboratory (MSL) landing and surface mission, the Mars 2020 project is a flagship-class science mission intended to address key questions about the potential for life on Mars and collect samples for possible Earth return by a future mission. [1] Mars 2020 will also demonstrate technologies needed to enable future human expeditions to Mars. Utilizing the groundbreaking entry, descent, and landing (EDL) architecture pioneered by the MSL, [2] [3] Mars 2020 will launch in July 2020 and land on Mars in February 2021. Like its predecessor, Mars 2020 will


Human Mars EDL pathfinder study: Assessment of technology development gaps and mitigations

Abstract: This paper presents the results of a NASA initiated Agency-wide assessment to better characterize the risks and potential mitigation approaches associated with landing human class payloads on Mars. Due to the criticality and long-lead nature of advancing Entry, Descent, and Landing (EDL) techniques, it is necessary to determine an appropriate strategy to improve the capability to land large payloads. A key focus of this study was to understand the key EDL risks with a focus on determining what "must" be tested at Mars. This process identified the various risks and potential risk mitigation str


Free-Flight Terrestrial Rocket Lander Demonstration for NASA's Autonomous Landing and Hazard Avoidance Technology (ALHAT) System

David Rutishauser; Chirold Epp; Edward A. Robertson

Abstract: The Autonomous Landing Hazard Avoidance Technology (ALHAT) Project is chartered to develop and mature to a Technology Readiness Level (TRL) of six an autonomous system combining guidance, navigation and control with terrain sensing and recognition functions for crewed, cargo, and robotic planetary landing vehicles. The ALHAT System must be capable of identifying and avoiding surface hazards to enable a safe and accurate landing to within tens of meters of designated and certified landing sites anywhere on a planetary surface under any lighting conditions. Since its inception in 2006, the ALHAT


Powered-descent landing GNC system design and flight results for Tianwen-1 mission

Xiangyu Huang; Chao Xu; Jinchang Hu; Maodeng Li

Abstract: Abstract The powered-descent landing (PDL) phase of the Tianwen-1 mission began with composite backshell-parachute (CBP) separation and ended with landing-rover touchdown. The main tasks of this phase were to reduce the velocity of the lander, perform the avoidance maneuver, and guarantee a soft touchdown. The PDL phase overcame many challenges: performing the divert maneuver to avoid collision with the CBP while simultaneously avoiding large-scale hazards; slowing the descent from approximately 95 to 0 m/s; performing the precise hazard-avoidance maneuver; and placing the lander gently and sa


Integrated Optical Terrain Relative Navigation for Autonomous Lunar Landing

Parracino, Giovanni Pio; Ceresoli, Michele; Silvestrini, Stefano; Lavagna, Michèle


Guidance with Supersonic Retropropulsion for Mars Pinpoint Landing

J. Sreelekshmi; M. S. Navin; P. S. Shenil

International Conference on Computational Collective Intelligence

Abstract: Future human and robotic missions to Mars require the landing of heavier payloads with greater precision. The present entry, descent and landing (EDL) technology is that of the Viking mission with necessary modifications. But this will be challenged by the larger payload mass of the future missions. The high ballistic coefficient of such missions makes parachute deployment impractical. The spacecraft will reach the parachute deployment conditions only at a low altitude with insufficient time for the rest of the EDL events. Also the diameter of the parachute has to be increased and materials wh


Mars Sample Return Campaign Concept Architecture

B. Muirhead; A. Nicholas; C. Edwards; J. Umland

Abstract: MSR is currently envisioned to be a campaign of three flight elements and one ground element. The Mars 2020 mission with its Perserverance caching rover is the first element and is on schedule to launch this July. This paper describes the other two flight elements envisioned for MSR, namely a Sample Return Lander and Earth Return Orbiter, that are being jointly studied by NASA and the European Space Agency (ESA). Overall objectives and mission options will be described, including the campaign architecture's constraints and notional timelines. The paper will highlight architecture-level trade s


Long-Distance Altimetry and Terrain Relative Navigation Capabilities of a Multi-Functional Imaging Lidar for Precision Safe Landing

Farzin Amzajerdian; Aram Gragossian; Paul F Brewster; Jacob M Heppler

Abstract:
A linear-mode flash lidar sensor employing a resolution enhancement algorithm is being developed at NASA Langley Research Center for enabling precise and safe landing on the Moon, Mars, and other destinations in the solar system. This lidar, referred to as Terrain Sensing Lidar (TSL), is a multi-mode sensor capable of hazard detection and avoidance, terrain relative navigation, and long-distance altimetry. TSL offers a solution for future missions that require landing in rough terrain and/or poor lighting conditions. The viability
of TSL for terrain hazard detection and avoidance has already


High Resolution Terrain Sensing Lidar for Precision Navigation and Safe Landing of Space and Aerial Vehicles

Farzin Amzajerdian; Aram Gragossian; Alexander Bulyshev; Paul F Brewster

Abstract: A 3-D imaging flash lidar sensor employing a resolution enhancement algorithm is being developed at NASA Langley Research Center for providing Terrain Relative Navigation and Hazard Avoidance capabilities onboard spacecraft landing on the Moon, Mars, and other planetary bodies. This lidar sensor, we refer to as Terrain Sensing Lidar (TSL), is a solution for future missions that require landing at pre-designated sites near high value resources or at areas of high scientific value, while avoiding hazardous terrain features, such as escarpments, craters, slopes, and rocks, or pre-deployed assets.


Development of a SURF-Based Lunar Terrain Relative Navigation Algorithm

Abstract:
The upcoming NASA Artemis missions face the unique challenge of landing on the rugged and poorly-lit lunar south pole. Unlike the equatorial regions of the moon, the poles see very little sunlight. As a result, mountains often cast kilometer-long shadows across the lunar terrain.

With the south pole being largely out of view of Earth, the HLS spacecraft cannot rely on Earth-based navigation and localization. Modern spacecraft employ a combination of star trackers, altimeters, Inertial Measurement Units (IMUs), and Terrain Relative Navigation (TRN) to maintain a self-contained, Earth-independe