A Comparative Study of Aerocapture Missions with a Mars Destination

Vaughan, Diane; Miller, Heather C.; Griffin, Brand N.; James, Bonnie; Munk, Michelle M.

doi:10.2514/6.2005-4110

Cited by 10 publications

(8 citation statements)

References 3 publications

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“…Aerocapture has never been implemented to date, but there are numerous studies for it's application to Mars and other interplanetary missions [19]. These studies have illustrated the many advantages of using aerocapture.…”

Section: Figure 40 Summary Of Magnetoshell Results Translating Impulse Into Direct Equivalent Steady Thrust Measurements Orbital Modelingmentioning

confidence: 99%

A Plasma Aerocapture and Entry System for Manned Missions and Planetary Deep Space Orbiters

Kirtley

2014

AIAA Atmospheric Flight Mechanics Conference

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Section: Figure 40 Summary Of Magnetoshell Results Translating Impulse Into Direct Equivalent Steady Thrust Measurements Orbital Modelingmentioning

confidence: 99%

A Plasma Aerocapture and Entry System for Manned Missions and Planetary Deep Space Orbiters

Kirtley

2014

AIAA Atmospheric Flight Mechanics Conference

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“…Numerical results presented throughout this paper use the conditions and parameters displayed in Tables 1 and 2. The range of entry speeds examined at Earth, Mars, Titan, and Neptune are adapted from previous studies 1,2,8,9,16,17 and are displayed in Table 2. We choose an entry flight path angle that targets a circular orbit at exit (assuming the ballute/lander is not released).…”

Section: Numerical Resultsmentioning

confidence: 99%

“…IGNIFIGANT research has been conducted to investigate the benefits and feasibility of aerocapture and ballute aerocapture at multiple destinations. [1][2][3][4][5][6][7][8][9] An inflatable ballute system for aerocapture has the potential of providing performance benefits via its large area-to-mass ratio. During ballute aerocapture simulations, it is customary to release the ballute at the appropriate instant and then ignore it to focus on the trajectory of the orbiter.…”

Section: Introductionmentioning

confidence: 99%

Analytic Solutions for Aerocapture, Descent, and Landing Trajectories for Dual-Use Ballute Systems

Medlock

Ayoubi

Longuski

et al. 2006

AIAA/AAS Astrodynamics Specialist Conference and Exhibit

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In a dual-use ballute system, we use the ballute first, to aerocapture the orbiter, and second, to soft-land the payload. Using Vinh's analytic theory for aerocapture trajectories, we derive expressions for the maximum heating rates, maximum deceleration, and maximum dynamic pressure as functions of the ballistic coefficient and of the capture trajectory, which in turn provides the required size (area/mass ratio) of the ballute. We follow a similar approach in developing an analytic theory for the ballute-lander. We apply our results to Earth (returns), Mars, Titan, and Neptune.

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“…[1][2][3] In these missions, aerocapture is a promising technology for the orbital insertion of spacecraft 4,5) because significant gains in payload mass are possible without the need for spacecraft to carry the chemical propulsion used for deceleration. However, to obtain sufficient deceleration, spacecraft need to enter the Martian atmosphere at low altitude, resulting in severe aerodynamic heating.…”

Section: Introductionmentioning

confidence: 99%

Temperature Measurements of CO2 and CO2 - N2 Plasma Flows around a Blunt Body in an Arc-Heated Wind Tunnel

Yamada

Otsuta

Matsuno

et al. 2013

AEROSPACE TECHNOLOGY JAPAN

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The purpose of this research is to characterize the thermochemical states of CO2 and CO2-N2 arc plasma flows via temperature measurements. To do this, radiation from the stagnation streamline around a disk model is measured using the newly developed multipoint spectroscopic measurement system and temperatures are deduced by applying the spectrum fitting method to the measured spectra. It is found that the vibrational temperature is nearly constant and higher than the rotational temperature along the stagnation streamline, showing the vibrational nonequilibrium process. The rotational temperature is also nearly constant and does not increase in the shock layer. This may be caused by the fact that measured temperatures are averaged temperatures along the line-of-sight (LOS). In conclusion, the thermochemical states of CO2 and CO2-N2 arc plasma flows are vibrational nonequilibrium states in the free stream region. However, the thermochemical state in the shock layer cannot be clarified accurately using LOS averaged temperatures. In the future, LOS effects should be examined using spectroscopic measurements along a radial direction.

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A Comparative Study of Aerocapture Missions with a Mars Destination

Cited by 10 publications

References 3 publications

A Plasma Aerocapture and Entry System for Manned Missions and Planetary Deep Space Orbiters

A Plasma Aerocapture and Entry System for Manned Missions and Planetary Deep Space Orbiters

Analytic Solutions for Aerocapture, Descent, and Landing Trajectories for Dual-Use Ballute Systems

Temperature Measurements of CO2 and CO2 - N2 Plasma Flows around a Blunt Body in an Arc-Heated Wind Tunnel

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