Ballistic Range Testing of the Mars Exploration Rover Entry Capsule

Schoenenberger, Mark; Hathaway, Wayne; Yates, Leslie A.; Desai, Prasun N.

doi:10.2514/6.2005-55

Cited by 25 publications

(24 citation statements)

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“…Newtonian aerodynamics were used in the MER database to predict stable hypersonic pitch damping (C mq = -0.338). 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.…”

Section: B Dynamic Pitch Damping Databasementioning

confidence: 99%

“…Blunt bodies such as the Phoenix capsule are known to be dynamically unstable at supersonic Mach numbers. 17 This instability is characterized by pitch amplitude growth at supersonic Mach numbers. The MER program conducted ballistic range testing to determine pitch damping characteristics at supersonic Mach numbers.…”

Section: Dynamic Pitch Dampingmentioning

confidence: 99%

“…The MER program conducted ballistic range testing to determine pitch damping characteristics at supersonic Mach numbers. 17 Given the similarity in capsule geometries, the MER dynamic damping data were used in the Phoenix database. Dynamic stability is generally predicted when C mq (= C nr ) is negative.…”

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: B Dynamic Pitch Damping Databasementioning

confidence: 99%

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

Self Cite

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show abstract

“…Reference 16 provides a detailed analysis of the use of the VL1 pressure and on-board accelerometer measurements to estimate aerodynamic coefficients in the free-molecular, transitional, and hypersonic continuum flight regimes. The analysis differed from the initial post-flight work in Reference 1 in that the pressure data were used in lieu of having a direct density measurement for Equation 5. The pressure and accelerometer data allowed the use of an iterative scheme to extract aerodynamic force coefficients in the body-reference frame 16 .…”

Section: B Vl1 Flight Datamentioning

confidence: 99%

“…The aerodynamics for MPF and MER were based almost completely on computational fluid dynamics flowfield solutions [2][3][4] . Consequently, no ground-based aerodynamics test programs were conducted for those vehicles, other than ballistic range testing for dynamic stability characterization 5 . Both MPF and MER were spin-stabilized, so the aerodynamics prediction at zero L/D was not as critical as it would be for an entry that depended on lift for target accuracy and altitude performance.…”

Section: Introductionmentioning

confidence: 99%