Aerodynamic Decelerators for Planetary Exploration:  Past, Present, and Future

Cruz, Juna R.; Lingard, J. Stephen

doi:10.2514/6.2006-6792

Cited by 58 publications

(24 citation statements)

References 70 publications

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“…A 19.7 m diameter DGB parachute was flight tested as part of the Viking qualification program (Cruz and Lingard, 2006). Analysis shows this to be adequate to decelerate the 19.4 T lander (deorbit propellant expended) in the supersonic deceleration phase, from M = 2.7 to M = 0.8 (Braun and Maiming, 2007).…”

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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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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“…Inflatable aerodynamic decelerator (IAD) [1][2][3] is a device for deceleration process in Entry, Descent and Landing (EDL) process 4) of planetary exploration mission. For instance, in Mars exploration mission, supersonic parachute which is a kind of IAD is used to achieve adequate deceleration for the landing.…”

Section: Introductionmentioning

confidence: 99%

Measurements by Temperature Sensitive Paint on Flexible and Deforming Model in Hypersonic Flow

Taguchi

Maruyama

Sato

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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Temperature measurement on deforming aeroshell model was performed in hypersonic test flow. Temperature Sensitive Paint (TSP) was used to measure surface temperature on the model. Generally, TSP is not available on flexible surface due to a problem in normalization procedure of images. Present paper describes the improved methodology of TSP which is able to apply to flexible and deforming model surface. For the improved TSP, two different kinds of luminophore, namely Ruphen and Fluorescein, are employed to observe reference image and test image simultaneously. An optical system is produced to detect the luminescence from Ruphen and Fluorescein separately. Results indicate that temperature rise caused by aerodynamic heating is observed, and the temperature distribution measured by the improved TSP method on flexible model shows qualitative agreement with the one obtained by conventional TSP measurement on rigid model which simulates deformed model configuration. Furthermore, the temperature measurement by this method shows good capability to follow model deformation.

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“…For example, Gillis [5] has proposed an upper bound of Mach 2 for parachute aerodynamic decelerators at Mars. However, Cruz [3] places the upper Mach number range somewhere between two and three.…”

Section: Parachute Decelerators For Marsmentioning

confidence: 99%

On the use of a range trigger for the Mars Science Laboratory Entry, Descent, and Landing

Way

2011

2011 Aerospace Conference

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Abstract-In 2012, during the Entry, Descent, and Landing (EDL) of the Mars Science Laboratory (MSL) entry vehicle, a 21.5 m Viking-heritage, Disk-Gap-Band, supersonic parachute will be deployed at approximately Mach 2. The baseline algorithm for commanding this parachute deployment is a navigated planet-relative velocity trigger. This paper compares the performance of an alternative range-to-go trigger (sometimes referred to as "Smart Chute"), which can significantly reduce the landing footprint size. Numerical Monte Carlo results, predicted by the POST2 MSL POST End-to-End EDL simulation, are corroborated and explained by applying propagation of uncertainty methods to develop an analytic estimate for the standard deviation of Mach number. A negative correlation is shown to exist between the standard deviations of wind velocity and the planet-relative velocity at parachute deploy, which mitigates the Mach number rise in the case of the range trigger.

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Aerodynamic Decelerators for Planetary Exploration: Past, Present, and Future

Cited by 58 publications

References 70 publications

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

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

Measurements by Temperature Sensitive Paint on Flexible and Deforming Model in Hypersonic Flow

On the use of a range trigger for the Mars Science Laboratory Entry, Descent, and Landing

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