A survey of aeroassisted orbit transfer

Walberg, Gerald D.

doi:10.2514/3.25704

Cited by 226 publications

(40 citation statements)

References 53 publications

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“…However, an aerocapture mission involves a lot of complicated technical difficulties. For example, the corridor width for the entry path angle is quite narrow and it strongly depends on the vehicle's aerodynamic characteristic and the entry velocity 1,2) . During the atmospheric flight, the aerodynamic lift must be adequately controlled to obtain an optimized descending and ascending rate without losing necessary deceleration so that the vehicle can avoid the crash onto the ground even when the uncertainties in the atmospheric properties exist.…”

Section: K M Wmentioning

confidence: 99%

“…Aerocapture technique 1) has the potential for providing substantial weight savings, because aerodynamic drag is used to remove enough kinetic energy instead of conventional fuel-costly chemical propulsion. It also enables us to complete orbital maneuvering in smaller time than aerobraking, which takes several weeks or several months to insert the vehicle into the target orbit.…”

Section: Introductionmentioning

confidence: 99%

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Simultaneous Optimization of Flight Control and Aerodynamic Shape for Aerocapture Vehicle

Honma

Suzuki

2010

AEROSPACE TECHNOLOGY JAPAN

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Aerocapture is expected to reduce the cost of the interplanetary exploration in the future because it utilizes aerodynamic drag to decelerate the vehicle rather than fuel-costly chemical propulsion. However, aerocapture mission involves lots of complicated difficulties such as quite narrow entry path angle, excess aerodynamic heating, aerodynamic load, and various uncertainties. It requires high levels of control technique and aerodynamic characteristics prediction. In this paper, the results of the simultaneous optimization of the flight control and aerodynamic shape for Mars aerocapture vehicle are presented. To maximize the payload mass, fuel mass for orbital transfer and TPS mass must be minimized. For this purpose, objective functions are set as follows: 1) minimize the delta-V for orbit insertion, 2) minimize the total heat load, 3) minimize both the delta-V and total heat load. Firstly, optimization was conducted only for the flight control, assuming the fixed aerodynamic shape and entry path angle. Secondary, simultaneous optimization was conducted. As a result, trade-off between delta-V and total heat load was clarified. Moreover, by executing simultaneous optimization, the guideline of designing aerocapture, which can minimize the objective function in each case 1)-3), was obtained.

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Section: K M Wmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Simultaneous Optimization of Flight Control and Aerodynamic Shape for Aerocapture Vehicle

Honma

Suzuki

2010

AEROSPACE TECHNOLOGY JAPAN

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“…This method requires that the satellite be packaged into a vehicle with aerodynamic qualities. Moreover, it has been suggested by Walberg 3 that the lift to drag ratio must be greater than one and that the required plane change be greater than 15 degrees before a synergetic plane change becomes more efficient than a conventional propulsive burn alone.…”

Section: B Orbit Modificationmentioning

confidence: 99%

Aerodynamic and Propulsion Assisted Maneuvering for Orbital Transfer Vehicles

Jolley

2007

45th AIAA Aerospace Sciences Meeting and Exhibit

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The ability to perform rapid orbital transfers will provide the ability for unpredictable reconnaissance or timely rescue missions. This paper examines the means and ways of enabling responsive space through propulsive and aero-assisted maneuvers. A conical hypersonic waverider was designed and its aerodynamic database was generated using hypersonic incidence angle analysis tools with a viscous skin-drag correction. Sample trajectories were analyzed for heating levels. Transpirational cooling along the leading edge or the use of ultra-high temperature ceramics are needed to control heating. A throttled engine regulator control was built to provide sufficient energy to maintain the orbit. The regulator control law is derived and analyzed for performance ability. The orbital transfer trajectories were analyzed using an interactive simulation tool. Results have confirmed previous research that aero-assisted maneuvers are more efficient than purely propulsive maneuvers alone for executing synergetic plane changes.

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“…Driving applications for external, continuum, hypersonic aeow simulation in the period 1980 to 1990 in the United States included generic studies for aeromaneuvering and aeroassisted orbital transfer vehicles, 2 Space Transportation System घSTSङ support, 3 defense interceptors design, 4 Pegasus, 5 and the National AeroSpace Plane घNASPङ. 6 In Europe, programs of note during this same period include HER-MES, 7 Sí anger, 8 and HOTOL 9 and early work on Huygen 10 probe.…”

Section: Historical Perspective and Technology Driversmentioning

confidence: 99%

Computational aerothermodynamic design issues for hypersonic vehicles

Olynick

Venkatapathy

1997

32nd Thermophysics Conference

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A brief review of the evolutionary progress in computational aerothermodynamics is presented. The current status of computational aerothermodynamics is then discussed, with emphasis on its capabilities and limitations for contributions to the design process of hypersonic vehicles. Some topics to be highlighted include: घ1ङ aerodynamic coeaecient predictions with emphasis on high temperature gas eaeects; घ2ङ surface heating and temperature predictions for thermal protection system घTPSङ design in a high temperature, thermochemical nonequilibrium environment; घ3ङ methods for extracting and extending computational aeuid dynamic घCFDङ solutions for eaecient utilization by all members of a multidisciplinary design team; घ4ङ physical models; घ5ङ validation process and error estimation; and घ6ङ gridding and solution generation strategies. Recent experiences in the design of X-33 will be featured. Computational aerothermodynamic contributions to Mars Pathaender, METEOR, and Stardust घComet Sample returnङ will also provide context for this discussion. Some of the barriers that currently limit computational aerothermodynamics to a predominantly reactive mode in the design process will also be discussed, with the goal of providing focus for future research.

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A survey of aeroassisted orbit transfer

Cited by 226 publications

References 53 publications

Simultaneous Optimization of Flight Control and Aerodynamic Shape for Aerocapture Vehicle

Simultaneous Optimization of Flight Control and Aerodynamic Shape for Aerocapture Vehicle

Aerodynamic and Propulsion Assisted Maneuvering for Orbital Transfer Vehicles

Computational aerothermodynamic design issues for hypersonic vehicles

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