Computations of Viking Lander Capsule Hypersonic Aerodynamics with Comparisons to Ground and Flight Data

Edquist, Karl T.

doi:10.2514/6.2006-6137

Cited by 18 publications

(18 citation statements)

References 17 publications

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“…The shape also has sufficient stability to minimize control system usage. 6 A scaled variant of the Viking 70-deg sphere cone forebody has been employed on every Mars landing mission to date due to its relatively high hypersonic drag coefficient and the existence of a broad set of aerodynamic performance data on this shape. 7 Therefore this forebody shape has a significant heritage beyond the extensive project Viking heritage.…”

Section: A Design Philosophy and Assumptionsmentioning

confidence: 99%

“…The heatshield OML is geometrically scaled (4.565 scale factor) from the 3.505 m diameter Viking lander 70 degree sphere-cone heatshield. 6 The LM2/LM3 EDL trajectory was initially modeled on a Mars Science Laboratory vehicle EDL parametric analysis, with C B of 63 kg/m 2 and L/D of 0.18. 7 Two degree-offreedom simulations were then performed using the NASA standard Mars atmosphere model and a spherical Mars gravitational potential to size the DGB parachute, descent engines, and vehicle, and optimize the trajectory.…”

Section: A Design Philosophy and Assumptionsmentioning

confidence: 99%

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Crew and Cargo Landers for Human Exploration of Mars-Vehicle System Design

Benton

2008

5th AIAA Theoretical Fluid Mechanics Conference

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This paper describes Mars lander design concepts that were first presented as part of the Spaceship Discovery independent research project. This conceptual space vehicle architecture for human solar system exploration was presented in 2006. The Spaceship Discovery architecture includes two types of Mars exploration landers: A piloted crew lander, designated Lander Module 2 (LM2), and an autonomous cargo lander, designated Lander Module 3 (LM3). The LM2 and LM3 designs were first presented at the AIAA Space 2007 conference. The LM2 and LM3 concepts have recently been extensively redesigned. The objective of this paper is to present these revised designs. The LM2 and LM3 landers are based on a common design that can be configured to carry either crew or cargo. They utilize a combination of aerodynamic reentry, parachutes, and propulsive braking to decelerate from orbital velocity to a soft landing. The LM2 crew lander provides two-way transportation for a nominal three-person crew between Mars orbit and the surface, and provides life support for a 24-day contingency mission. It contains an ascent section to return the crew to orbit after completion of surface operations. The LM3 cargo lander provides one-way, autonomous transportation of cargo from Mars orbit to the surface and can be configured to carry a mix of consumables and equipment, or equipment only. Lander service life and endurance is based on the Spaceship Discovery conjunction-class Design Reference Mission 2. The LM3 is designed to extend the surface stay for three crew members in an LM2 crew lander such that two sets of crew and cargo landers enable human exploration of the surface for the bulk of the 454 day wait time at Mars, in two shifts of three crew members each. Design requirements, mission profiles, mass properties, performance data, and configuration layouts are presented for the LM2 crew and LM3 cargo landers. These lander designs are a proposed solution to the problem of safely transporting a human crew from Mars orbit to the surface, sustaining them for extended periods of time on the surface, and returning them safely to orbit. They are based on reliable and proven technology and build on an extensive heritage of successful unmanned probes. Safety, redundancy, and abort and rescue capabilities are stressed in the design and operations concepts. The designs share many common features, hardware, subsystems, and flight control modes to reduce development cost. The LM2 and LM3 Mars landers presented in this paper are an integral part of the Spaceship Discovery architecture but could be used in any other Mars exploration architecture that utilizes a Mars orbit rendezvous methodology.

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Section: A Design Philosophy and Assumptionsmentioning

confidence: 99%

Section: A Design Philosophy and Assumptionsmentioning

confidence: 99%

Crew and Cargo Landers for Human Exploration of Mars-Vehicle System Design

Benton

2008

5th AIAA Theoretical Fluid Mechanics Conference

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“…In order to minimize risk and development cost, the lander design extensively draws on the Viking lander design database. The heatshield OML is geometrically scaled (4.565 scale factor) from the 3.505 m diameter Viking lander 70 degree sphere-cone heatshield (Edquist, 2006). The descent trajectory is based on analysis for the MSL spacecraft (Braun and Marming, 2007) and utilizes Apollo-type guidance, with center of gravity offset and lifting (a up to 20 degrees) to enable precision landings.…”

Section: Design Philosophy and Assumptionsmentioning

confidence: 99%

Spaceship Discovery's Crew and Cargo Lander Module Designs for Human Exploration of Mars

Benton¹

2008

AIP Conference Proceedings

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The Spaceship Discovery design was first presented at STAIF 2006. This conceptual design space vehicle architecture for human solar system exploration includes two types of Mars exploration lander modules: A piloted crew lander, designated Lander Module 2 (LM2), and an autonomous cargo lander, designated Lander Module 3 (LM3). The LM2 and LM3 designs were first presented at AIAA Space 2007. The LM2 and LM3 concepts have recently been extensively redesigned. The specific objective of this paper is to present these revised designs. The LM2 and LM3 landers are based on a common design that can be configured to carry either crew or cargo. They utilize a combination of aerodynamic reentry, parachutes, and propulsive braking to decelerate from orbital velocity to a soft landing. The LM2 crew lander provides two-way transportation for a nominal three-person crew between Mars orbit and the surface, and provides life support for a 30-day contingency mission. It contains an ascent section to return the crew to orbit after completion of surface operations. The LM3 cargo lander provides one-way, autonomous transportation of cargo from Mars orbit to the surface and can be configured to carry a mix of consumables and equipment, or equipment only. Lander service life and endurance is based on the Spaceship Discovery conjunction-class Design Reference Mission 2. The LM3 is designed to extend the surface stay for three crew members in an LM2 crew lander such that two sets of crew and cargo landers enable human exploration of the surface for the bulk of the 454 day wait time at Mars, in two shifts of three crew members each. Design requirements, mission profiles, mass properties, performance data, and configuration layouts are presented for the LM2 crew and LM3 cargo landers. These lander designs are a proposed solution to the problem of safely transporting a human crew from Mars orbit to the surface, sustaining them for extended periods of time on the surface, and returning them safely to orbit. They are based on reliable and proven technology and build on an extensive heritage of successful unmanned probes. Safety, redundancy, and abort and rescue capabilities are stressed in the design and operations concepts. The designs share many common features, hardware, subsystems, and flight control modes to reduce development cost.

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“…The aerodynamic code has been validated on the Viking lander capsule hypersonic aerodynamics data from onground and on-board measurements, which have been recently used by Edquist for comparison to the LAURA NavierStokes code [21]. A high accuracy, average errors lower than 6%, is achieved for both drag and lift-to-drag coefficients.…”

Section: Newtonian Flowmentioning

confidence: 99%

Multidisciplinary Optimization of Aerocapture Maneuvers

Armellín

Lavagna

2008

Journal of Artificial Evolution and Applications

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A multidisciplinary-multiobjective optimization of aerocapture maneuvers is presented. The proposed approach allows a detailed analysis of the coupling among vehicle's shape, trajectory control, and thermal protection system design. A set of simplified models are developed to address this analysis and a multiobjective particle swarm optimizer is adopted to obtain the set of Pareto optimal solutions. In order to deal with an unconstrained multiobjective optimization, a two-point boundary value problem is formulated to implicitly satisfy the constraints on the atmospheric exit conditions. The trajectories of the most promising solutions are further optimized in a more refined dynamical system by solving an optimal control problem using a direct multiple shooting transcription method. Furthermore, a more complete vehicle control is considered. All the simulations presented consider an aerocapture at Mars with a polar orbit of 200 km of altitude as target orbit.

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Computations of Viking Lander Capsule Hypersonic Aerodynamics with Comparisons to Ground and Flight Data

Cited by 18 publications

References 17 publications

Crew and Cargo Landers for Human Exploration of Mars-Vehicle System Design

Crew and Cargo Landers for Human Exploration of Mars-Vehicle System Design

Spaceship Discovery's Crew and Cargo Lander Module Designs for Human Exploration of Mars

Multidisciplinary Optimization of Aerocapture Maneuvers

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