Anomalistic disturbance torques during the entry phase of the mars exploration rover missions—a telemetry and mars-surface investigation

Tolson, R. H.; Willcockson, William H.; Desai, Prasun N.; Thomas, P.

doi:10.1007/bf03256543

Cited by 2 publications

(4 citation statements)

References 7 publications

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“…23 During these instabilities, the pressure distribution does not produce a restoring moment when the angle-of-attack deviates from zero. This instability was also predicted 10 and observed 19 for the MER capsules since the same physics applied for those entries.…”

Section: Static Pitch Stabilitysupporting

confidence: 63%

“…There are regions in the rarefied (Kn > 0.2) and hypersonic continuum regimes (3.6 km/s) where C m,cg is positive at positive angles-of-attack. This behavior was observed for Phoenix 7 , Pathfinder, 18 and MER, 19 and will be discussed in a later section. …”

Section: Resultsmentioning

confidence: 52%

“…The MER supersonic ballistic range data 17 predicted dynamically unstable behavior (C mq > 0) at the nominal trim α = 0 for Mach numbers less than 3.5. This capsule characteristic causes attitude oscillation growth prior to parachute deployment, which has been observed in Pathfinder 18 and MER 19 flight data. Phoenix reconstruction analysis 7 also showed this oscillation growth.…”

Section: B Dynamic Pitch Damping Databasementioning

confidence: 69%

“…Entry trajectory reconstruction of the Pathfinder 18 and MER 19 capsules showed dynamic oscillation growth at supersonic Mach numbers prior to parachute deployment. The requirement for Phoenix was that the total angle-of-attack at parachute deployment was less than 10 deg.…”

Section: Dynamic Pitch Dampingmentioning

confidence: 99%

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Aerodynamics for the Mars Phoenix Entry Capsule

Edquist

Desai

Schoenenberger

2008

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

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Pre-flight aerodynamics data for the Mars Phoenix entry capsule are presented. The aerodynamic coefficients were generated as a function of total angle-of-attack and either Knudsen number, velocity, or Mach number, depending on the flight regime. The database was constructed using continuum flowfield computations and data from the Mars Exploration Rover and Viking programs. Hypersonic and supersonic static coefficients were derived from Navier-Stokes solutions on a pre-flight design trajectory. High-altitude data (free-molecular and transitional regimes) and dynamic pitch damping characteristics were taken from Mars Exploration Rover analysis and testing. Transonic static coefficients from Viking wind tunnel tests were used for capsule aerodynamics under the parachute. Static instabilities were predicted at two points along the reference trajectory and were verified by reconstructed flight data. During the hypersonic instability, the capsule was predicted to trim at angles as high as 2.5 deg with an on-axis center-of-gravity. Trim angles were predicted for off-nominal pitching moment (4.2 deg peak) and a 5 mm off-axis center-ofgravity (4.8 deg peak). Finally, hypersonic static coefficient sensitivities to atmospheric density were predicted to be within uncertainty bounds.

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Section: Static Pitch Stabilitysupporting

confidence: 63%