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  • 1
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    Propulsive Reaction Control System Model (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: This software models a propulsive reaction control system (RCS) for guidance, navigation, and control simulation purposes. The model includes the drive electronics, the electromechanical valve dynamics, the combustion dynamics, and thrust. This innovation follows the Mars Science Laboratory entry reaction control system design, and has been created to meet the Mars Science Laboratory (MSL) entry, descent, and landing simulation needs. It has been built to be plug-and-play on multiple MSL testbeds [analysis, Monte Carlo, flight software development, hardware-in-the-loop, and ATLO (assembly, test and launch operations) testbeds]. This RCS model is a C language program. It contains two main functions: the RCS electronics model function that models the RCS FPGA (field-programmable-gate-array) processing and commanding of the RCS valve, and the RCS dynamic model function that models the valve and combustion dynamics. In addition, this software provides support functions to initialize the model states, set parameters, access model telemetry, and access calculated thruster forces.
    Keywords: Man/System Technology and Life Support
    Type: NPO-46978 , NASA Tech Briefs, November 2011; 13
    Format: application/pdf
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  • 2
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    The Development of the MSL Guidance, Navigation, and Control System for Entry, Descent, and Landing (2013)
    In:  Other Sources
    Details
    Publication Date: 2019-07-19
    Description: On August 5, 2012, the Mars Science Laboratory (MSL) mission successfully delivered the Curiosity rover to its intended target. It was the most complex and ambitious landing in the history of the red planet. A key component of the landing system, the requirements for which were driven by the mission ambitious science goals, was the Guidance, Navigation, and Control (GN&C) system. This paper will describe the technical challenges of the MSL GN&C system, the resulting architecture and design needed to meet those challenges, and the development process used for its implementation and testing.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking; Spacecraft Instrumentation and Astrionics; Lunar and Planetary Science and Exploration
    Type: Annual AAS Guidance and Control Conference; Feb 01, 2013 - Feb 06, 2013; Breckenridge, CO; United States
    Format: text
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  • 3
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    Mars Science Laboratory Entry, Descent and Landing System Development Challenges and Preliminary Flight Performance (2013)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: 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.
    Keywords: Astronautics (General)
    Type: AAS 13-123 , Space Flight Mechanics Meeting; Feb 10, 2013 - Feb 14, 2013; Kauai, HI; United States
    Format: text
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  • 4
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    Integrated Attitude Control Strategy for the Asteroid Redirect Mission (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Space Sciences (General); Space Transportation and Safety
    Type: JSC-CN-31109 , AIAA SpaceOps 2014; May 05, 2014 - May 09, 2014; Pasadena, CA; United States
    Format: application/pdf
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  • 5
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    System Verification of MSL Skycrane Using an Integrated ADAMS Simulation (2012)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Mars Science Laboratory (MSL) will use the Skycrane architecture to execute final descent and landing maneuvers. The Skycrane phase uses closed-loop feedback control throughout the entire phase, starting with rover separation, through mobility deploy, and through touchdown, ending only when the bridles have completely slacked. The integrated ADAMS simulation described in this paper couples complex dynamical models created by the mechanical subsystem with actual GNC flight software algorithms that have been compiled and linked into ADAMS. These integrated simulations provide the project with the best means to verify key Skycrane requirements which have a tightly coupled GNC-Mechanical aspect to them. It also provides the best opportunity to validate the design of the algorithm that determines when to cut the bridles. The results of the simulations show the excellent performance of the Skycrane system.
    Keywords: Mechanical Engineering
    Type: IEEE Aerospace Conference; Mar 03, 2012 - Mar 10, 2012; Big Sky, MT; United States
    Format: text
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  • 6
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    Powered Flight Design and Reconstructed Performance Summary for the Mars Science Laboratory Mission (2013)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Powered Flight segment of Mars Science Laboratory's (MSL) Entry, Descent, and Landing (EDL) system extends from backshell separation through landing. This segment is responsible for removing the final 0.1% of the kinetic energy dissipated during EDL and culminating with the successful touchdown of the rover on the surface of Mars. Many challenges exist in the Powered Flight segment: extraction of Powered Descent Vehicle from the backshell, performing a 300m divert maneuver to avoid the backshell and parachute, slowing the descent from 85 m/s to 0.75 m/s and successfully lowering the rover on a 7.5m bridle beneath the rocket-powered Descent Stage and gently placing it on the surface using the Sky Crane Maneuver. Finally, the nearly-spent Descent Stage must execute a Flyaway maneuver to ensure surface impact a safe distance from the Rover. This paper provides an overview of the powered flight design, key features, and event timeline. It also summarizes Curiosity's as flown performance on the night of August 5th as reconstructed by the flight team.
    Keywords: Spacecraft Design, Testing and Performance; Lunar and Planetary Science and Exploration
    Type: AAS 13-424 , AAS/AIAA Spaceflight Mechanics Meeting; Feb 10, 2013 - Feb 14, 2013; Kauai, HI; United States
    Format: text
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  • 7
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    Integrated Attitude Control Strategy for the Asteroid Redirect Mission (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A deep-space mission has been proposed to redirect an asteroid to a distant retrograde orbit around the moon using a robotic vehicle, the Asteroid Redirect Vehicle (ARV). In this orbit, astronauts will rendezvous with the ARV using the Orion spacecraft. The integrated attitude control concept that Orion will use for approach and docking and for mated operations will be described. Details of the ARV's attitude control system and its associated constraints for redirecting the asteroid to the distant retrograde orbit around the moon will be provided. Once Orion is docked to the ARV, an overall description of the mated stack attitude during all phases of the mission will be presented using a coordinate system that was developed for this mission. Next, the thermal and power constraints of both the ARV and Orion will be discussed as well as how they are used to define the optimal integrated stack attitude. Lastly, the lighting and communications constraints necessary for the crew's extravehicular activity planned to retrieve samples from the asteroid will be examined. Similarly, the joint attitude control strategy that employs both the Orion and the ARV attitude control assets prior, during, and after each extravehicular activity will also be thoroughly discussed.
    Keywords: Space Sciences (General); Space Transportation and Safety
    Type: JSC-CN-30896 , SpaceOps 2014; May 05, 2014 - May 09, 2014; Pasadena, CA; United States
    Format: application/pdf
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  • 8
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    Mars Science Laboratory Entry, Descent, and Landing System Overview (2010)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In 2012, the Mars Science Laboratory (MSL) mission will pioneer the next generation of robotic Entry, Descent, and Landing (EDL) systems by delivering the largest and most capable rover to date to the surface of Mars. In addition to landing more mass than prior missions to Mars, MSL will offer access to regions of Mars that have been previously unreachable. The MSL EDL sequence is a result of a more stringent requirement set than any of its predecessors. Notable among these requirements is landing a 900 kg rover in a landing ellipse much smaller than that of any previous Mars lander. In meeting these requirements, MSL is extending the limits of the EDL technologies qualified by the Mars Viking, Mars Pathfinder, and Mars Exploration Rover missions. Thus, there are many design challenges that must be solved for the mission to be successful. Several pieces of the EDL design are technological firsts, such as guided entry and precision landing on another planet, as well as the entire Sky Crane maneuver. This paper discusses the MSL EDL architecture and discusses some of the challenges faced in delivering an unprecedented rover payload to the surface of Mars.
    Keywords: Spacecraft Design, Testing and Performance
    Type: International Planetary Probe Workshop; Jun 12, 2010; Barcelona; Spain
    Format: text
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  • 9
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    The Development of the MSL Guidance, Navigation, and Control System for Entry, Descent, and Landing (2013)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: On August 5, 2012, the Mars Science Laboratory (MSL) mission successfully delivered the Curiosity rover to its intended target. It was the most complex and ambitious landing in the history of the red planet. A key component of the landing system, the requirements for which were driven by the mission ambitious science goals, was the Guidance, Navigation, and Control (GN&C) system. This paper will describe the technical challenges of the MSL GN&C system, the resulting architecture and design needed to meet those challenges, and the development process used for its implementation and testing.
    Keywords: Lunar and Planetary Science and Exploration; Spacecraft Instrumentation and Astrionics
    Type: AAS/AIAA Spaceflight Mechanics Meeting; Feb 10, 2013 - Feb 14, 2013; Kauai, HI; United States
    Format: text
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  • 10
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    The Mars Science Laboratory EDL Mode Commander (2011)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance
    Type: International Planetary Probe (IPPW-8) Workshop; Jun 06, 2011 - Jun 10, 2011; Norfolk, VA; United States
    Format: text
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