Aerodynamic Interference Due to MSL Reaction Control System

Dyakonov, Artem A.; Schoenenberger, Mark; Scallion, W. I.; Norman, John Van; Novak, Luke A.; Tang, Chun

doi:10.2514/6.2009-3915

Cited by 43 publications

(32 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Aerodynamic Interactions with RCS A large development effort was undertaken during the MSL EV development to design and quantify the likely interactions of the RCS plumes with the surrounding wake environment [18,19]. The final interaction model used in simulation showed that RCS interactions would be small [20].…”

Section: Interpretation Of Rcs Firing Historymentioning

confidence: 99%

Assessment of the Reconstructed Aerodynamics of the Mars Science Laboratory Entry Vehicle

Schoenenberger

Norman

Karlgaard

et al. 2014

Journal of Spacecraft and Rockets

Self Cite

View full text Add to dashboard Cite

On August 5, 2012, the Mars Science Laboratory entry vehicle successfully entered Mars atmosphere, flying a guided entry until parachute deploy. The Curiosity rover landed safely in Gale crater upon completion of the Entry Descent and Landing sequence. This paper compares the aerodynamics of the entry capsule extracted from onboard flight data, including Inertial Measurement Unit (IMU) accelerometer and rate gyro information, and heatshield surface pressure measurements. From the onboard data, static force and moment data has been extracted. This data is compared to preflight predictions. The information collected by MSL represents the most complete set of information collected during Mars entry to date. It allows the separation of aerodynamic performance from atmospheric conditions. The comparisons show the MSL aerodynamic characteristics have been identified and resolved to an accuracy better than the aerodynamic database uncertainties used in preflight simulations. A number of small anomalies have been identified and are discussed. This data will help revise aerodynamic databases for future missions and will guide computational fluid dynamics (CFD) development to improved prediction codes.

show abstract

Section: Interpretation Of Rcs Firing Historymentioning

confidence: 99%

Assessment of the Reconstructed Aerodynamics of the Mars Science Laboratory Entry Vehicle

Schoenenberger

Norman

Karlgaard

et al. 2014

Journal of Spacecraft and Rockets

Self Cite

View full text Add to dashboard Cite

show abstract

“…31,32 LAURA is also being used 33 to predict MSL's aerodynamic characteristics in the hypersonic and supersonic continuum flow regimes, including RCS interference effects. 34 For MSL, turbulent solutions using the Baldwin-Lomax algebraic model 35 were obtained for the heatshield based on the expectation of turbulent transition in flight. It will be shown that the Baldwin-Lomax model agrees well with fully-turbulent test data.…”

Section: −21mentioning

confidence: 99%

Aerothermodynamic Design of the Mars Science Laboratory Heatshield

Edquist

Dyakonov

Wright

et al. 2009

41st AIAA Thermophysics Conference

Self Cite

102

View full text Add to dashboard Cite

Aerothermodynamic design environments are presented for the Mars Science Laboratory entry capsule heatshield. The design conditions are based on Navier-Stokes flowfield simulations on shallow (maximum total heat load) and steep (maximum heat flux, shear stress, and pressure) entry trajectories from a 2009 launch. Boundary layer transition is expected prior to peak heat flux, a first for Mars entry, and the heatshield environments were defined for a fully-turbulent heat pulse. The effects of distributed surface roughness on turbulent heat flux and shear stress peaks are included using empirical correlations. Additional biases and uncertainties are based on computational model comparisons with experimental data and sensitivity studies. The peak design conditions are 197 W/cm 2 for heat flux, 471 P a for shear stress, 0.371 Earth atm for pressure, and 5477 J/cm 2 for total heat load. Time-varying conditions at fixed heatshield locations were generated for thermal protection system analysis and flight instrumentation development. Finally, the aerothermodynamic effects of delaying launch until 2011 are previewed.

show abstract

“…5 Four RCS jet pairs are distributed and orientated on the aftbody to provide adequate pitch, roll, and yaw moments to the vehicle while minimizing interaction effects. 1 Each nozzle provides approximately 290 N of thrust and operates intermittently in short bursts, lasting several seconds cumulatively in duration. During atmospheric entry the interaction between the hypersonic crossflow and the multiple RCS jets is not well understood.…”

Section: Introductionmentioning

confidence: 99%