Ballute Entry Systems for Lunar Return and Low-Earth-Orbit Return Missions

Clark, Ian G.; Braun, Robert D.

doi:10.2514/1.31612

Cited by 6 publications

(4 citation statements)

References 19 publications

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“…2,4 The system of interest is a ballute, which is a parachute braking device manufactured as a cone with a toroid around its widest point. In supersonic to subsonic speeds, this toroid is to ensure flow separation and stabilize the ballute as it decelerates.…”

Section: Introductionmentioning

confidence: 99%

Analysis of a Free-Fall Ballute Vehicle

Erford¹,

Henry²,

Nay³

et al. 2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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Section: Introductionmentioning
confidence: 99%

Analysis of a Free-Fall Ballute Vehicle
Erford¹,
Henry²,
Nay³
et al. 2012
53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
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0
0
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“…On a blunt body, such as shown in figure 1.1, the 'shock layer' is the high temperature chemically reacting gas which forms between the shock wave and the vehicle. The immediate thermochemical effects of the shock wave are well known [7,[17][18][19], but the effects caused by the expansion of the gas as it flows around the vehicle are less well understood.…”

Section: Flow-fieldmentioning
confidence: 99%

“…Data was recorded from high-altitude, high velocity nonequilibrium flows down to low-altitude low-velocity equilibrium flows [54]. 6 3 Calorimeters 0.56 7 3 Calorimeters and 1 pressure sensor 0. 70 8 Theoretical cone apex 1.0 Adapted from [20].…”

Section: Fire IImentioning
confidence: 99%

“…Whether the entry mission is to Mars, to the gas giants, or return to Earth, the atmospheric entry phase will be the most demanding on spacecraft design. Due to this, extensive further research is needed into improving our fundamental understanding of all aspects of atmospheric entry to allow design of efficient spacecraft which can survive the entry [7,8]. In the near future, more and more interplanetary missions will be conducted, with a requirement of planetary entry.…”

Section: Introductionmentioning
confidence: 99%

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Spectral analysis of atomic argon radiation in an expanding hypersonic flow
Kelly¹
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Entering the atmosphere of a planet is one of the key phases of many space missions, being significant for both interplanetary travel and for returning home to Earth, and remains one of the major challenges of interplanetary missions. Convective and radiative heat loads pose a significant threat to equipment and personnel during this process. Thermal protection systems are employed to mitigate the thermal loads, but are expensive in both cost and mass of the vehicle. Knowledge of these thermal heat loads requires accurate understanding of the flow-field that will develop around the vehicle. Experimental measurements are needed due to significant uncertainty in current aerothermodynamic models. Measurements in actual flight tests are difficult, due to the massive cost and the complexity of the flight tests themselves. This makes ground tests, conducted in hypersonic wind tunnel facilities, an essential practical alternative. Aerodynamic data for interplanetary flight can be generated in specialised wind tunnel facilities. Impulse facilities, specifically, have the ability to replicate planetary entry conditions. Due to the hostile nature of hypersonic test flows, sensors on the body of the test model may suffer damage from repeated use. Instrumentation attached to the test model can also influence the flow-field, impacting on the accuracy of measurements. Spectroscopic measurements are a non-intrusive method of extracting properties of the hot gas during testing, by measuring the radiation emitted by the gas, which have the advantage of not interfering with the gas flow during measurement. This thesis reports on the use of spectroscopic techniques to probe a radiating hypersonic flow-field, extracting population densities of excited states, and then determining the thermochemical state of the gas. A simplified two-dimensional wedge geometry was used to generate an oblique shock wave followed by an expansion. The aim of the project was to investigate the potential non-equilibrium flow effects during the expansion, an afterbody effect which remains poorly understood. Argon was chosen for the test gas as it is a monatomic gas with chemistry limited to ionisation and only two thermal modes. Such a simplified gas potentially allows for more direct and quantifiable determination of equilibrium or non-equilibrium of the gas as it expands, serving as a good basis for development of fundamental understanding and model development. Two experimental campaigns were conducted using the X2 expansion tube at The University of Queensland. The first campaign examined a relatively low-density argon flow which was expected to contain thermochemical non-equilibrium regions, due to the low gas density. The second campaign examined a higher density argon flow which was expected to be closer to thermochemical equilibrium. A structured analytical framework was developed to analyse the spectral data, which was coded into the application SELA. The populations of excited electronic energy levels were determined by examining the spectral emi...
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A historical review of Inflatable Aerodynamic Decelerator technology development
Smith
¹
,
Tanner
²
,
Mahzari
³

et al. 2010
2010 IEEE Aerospace Conference
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Ballute Entry Systems for Lunar Return and Low-Earth-Orbit Return Missions

Cited by 6 publications

References 19 publications

Analysis of a Free-Fall Ballute Vehicle

Analysis of a Free-Fall Ballute Vehicle

Spectral analysis of atomic argon radiation in an expanding hypersonic flow

A historical review of Inflatable Aerodynamic Decelerator technology development

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