Mars Science Laboratory Rover System Thermal Test

Novak, Keith; Kempenaar, Joshua; Liu, Yuanming; Bhandari, Pradeep; Dudik, Brenda

doi:10.2514/6.2012-3516

Cited by 9 publications

(5 citation statements)

References 5 publications

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“…Furthermore, a comprehensive system-level environmental verification program was conducted to ensure the reliability of the flight system when exposed to the various environments over the course of its mission. To this end, a suite of environmental tests and analyses were conducted, including system thermal-vacuum tests [40][41][42], acoustic noise, random vibration, and pyro-shock tests, as well as electromagnetic compatibility (EMC) tests. To ensure complete coverage, all applicable test results of these domains were reviewed and audited by the EDL team.…”

Section: Flight System Testingmentioning

confidence: 99%

Verification and Validation of the Mars Science Laboratory/Curiosity Rover Entry, Descent, and Landing System

Kornfeld

Prakash

Devereaux

et al. 2014

Journal of Spacecraft and Rockets

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the Curiosity rover successfully touched down on the Martian surface setting off the most ambitious surface exploration of this planetary body. Preceding this significant step were years of design, development, and testing of the Curiosity Entry, Descent, and Landing system to prepare for the most complex landing endeavor ever attempted at Mars. To address the numerous challenges, the approach and implementation of the overall Entry, Descent, and Landing verification and validation program relied on its decomposition into three distinct domains: flight dynamics, flight system and subsystem verification and validation. The test and analysis scope, the venues, and the processes utilized were tailored to each of these domains, and are discussed in greater detail. The overall lessons learned and conclusions described herein can serve as a pathfinder for the Entry, Descent, and Landing system testing approach and implementation of future Mars landed missions.

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Section: Flight System Testingmentioning

confidence: 99%

Verification and Validation of the Mars Science Laboratory/Curiosity Rover Entry, Descent, and Landing System

Kornfeld

Prakash

Devereaux

et al. 2014

Journal of Spacecraft and Rockets

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“…Working in partnership with MSSS engineers, ATLO tests involving use of the Mastcams and MARDI aboard Curiosity were conducted thereafter in JPL facilities and, starting in July 2011, at NASA's Kennedy Space Center (KSC) in Florida. Major tests involving the cameras included integrated camera geometric calibration in December 2010 [ Maki et al ., ; Bell et al ., ] and rover system thermal/vacuum testing in a large environment chamber at JPL in March 2011 [ Novak et al ., ]. Final inspection and cleaning of the camera head optics by the MSSS team occurred in August 2011 at KSC.…”

Section: Roles and Responsibilitiesmentioning

confidence: 99%

“…Earth and Space Science [Maki et al, 2012;Bell et al, 2017] and rover system thermal/vacuum testing in a large environment chamber at JPL in March 2011 [Novak et al, 2012].…”

Section: Mardimentioning

confidence: 99%

The Mars Science Laboratory (MSL) Mast cameras and Descent imager: Investigation and instrument descriptions

Malin

Ravine

Caplinger

et al. 2017

Earth and Space Science

142

166

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The Mars Science Laboratory Mast camera and Descent Imager investigations were designed, built, and operated by Malin Space Science Systems of San Diego, CA. They share common electronics and focal plane designs but have different optics. There are two Mastcams of dissimilar focal length. The Mastcam‐34 has an f/8, 34 mm focal length lens, and the M‐100 an f/10, 100 mm focal length lens. The M‐34 field of view is about 20° × 15° with an instantaneous field of view (IFOV) of 218 μrad; the M‐100 field of view (FOV) is 6.8° × 5.1° with an IFOV of 74 μrad. The M‐34 can focus from 0.5 m to infinity, and the M‐100 from ~1.6 m to infinity. All three cameras can acquire color images through a Bayer color filter array, and the Mastcams can also acquire images through seven science filters. Images are ≤1600 pixels wide by 1200 pixels tall. The Mastcams, mounted on the ~2 m tall Remote Sensing Mast, have a 360° azimuth and ~180° elevation field of regard. Mars Descent Imager is fixed‐mounted to the bottom left front side of the rover at ~66 cm above the surface. Its fixed focus lens is in focus from ~2 m to infinity, but out of focus at 66 cm. The f/3 lens has a FOV of ~70° by 52° across and along the direction of motion, with an IFOV of 0.76 mrad. All cameras can acquire video at 4 frames/second for full frames or 720p HD at 6 fps. Images can be processed using lossy Joint Photographic Experts Group and predictive lossless compression.

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“…During this test, fluid and gas pressures of the fluid loop are monitored and show no degradation or sign of leak. 13 Prior to loading the MPFLs for the final time, leak tests of the entire loop are performed to verify that the loop is leak tight. System pressure is monitored during fill and for extended time periods before disconnecting the GSE required to load the system (Fig.…”

Section: System Verificationmentioning

confidence: 99%

Leak Mitigation in Mechanically Pumped Fluid Loops for Long Duration Space Missions

Miller

Birur

Bame

et al. 2013

43rd International Conference on Environmental Systems

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Mechanically pumped fluid loops (MPFLs) are increasingly considered for spacecraft thermal control. A concern for long duration space missions is the leak of fluid leading to performance degradation or potential loop failure. An understanding of leak rate through analysis, as well as destructive and non-destructive testing, provides a verifiable means to quantify leak rates. The system can be appropriately designed to maintain safe operating pressures and temperatures throughout the mission. Two MPFLs on the Mars Science Laboratory Spacecraft, launched November 26, 2011, maintain the temperature of sensitive electronics and science instruments within a -40°C to 50°C range during launch, cruise, and Mars surface operations. With over 100 meters of complex tubing, fittings, joints, flex lines, and pumps, the system must maintain a minimum pressure through all phases of the mission to provide appropriate performance. This paper describes the process of design, qualification, test, verification, and validation of the components and assemblies employed to minimize risks associated with excessive fluid leaks from pumped fluid loop systems. NomenclatureCFC = Chlorofluorocarbon CHRS = Cruise Heat Rejection System CIPAS = Cruise Integrated Pump Assembly System FEM = Finite Element Model GHe = Gaseous Helium HRS = Heat Rejection System JPL = Jet Propulsion Laboratory MMPDS = Metallic Materials Properties Development and Standardization MMRTG = Multi-Mission Radioisotope Thermoelectric Generator MPFL = Mechanically Pumped Fluid Loop MSL = Mars Science Laboratory RAMP = Rover Avionics Mounting Plate RHRS = Rover Heat Rejection System RIPAS = Rover Integrated Pump Assembly System SCC = Standard Cubic Centimeter

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Mars Science Laboratory Rover System Thermal Test

Cited by 9 publications

References 5 publications

Verification and Validation of the Mars Science Laboratory/Curiosity Rover Entry, Descent, and Landing System

Verification and Validation of the Mars Science Laboratory/Curiosity Rover Entry, Descent, and Landing System

The Mars Science Laboratory (MSL) Mast cameras and Descent imager: Investigation and instrument descriptions

Leak Mitigation in Mechanically Pumped Fluid Loops for Long Duration Space Missions

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