Hypersonic waveriders for planetary atmospheres

Anderson, J. D.; Lewis, Mark J.; Kothari, Ajay P.; Corda, Stephen

doi:10.2514/3.26259

Cited by 47 publications

(13 citation statements)

References 13 publications

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“…A Delta IVor Atlas V launch vehicle is more than capable of delivering such launch energies, assuming the vehicle has a reasonably small mass [22]. The values of the vehicle's maximum E considered were 3, 5, 7, and 10 [6]. The lower values are considered feasible for the near future, and the higher values may be achievable in the long term.…”

Section: Interplanetary Trajectory Selection Using Stourmentioning

confidence: 99%

“…However, according to Anderson et al [6], if the vehicles are designed specifically to fly at Mars or Venus, the aerodynamic characteristics would be different. For optimally shaped vehicles at Venus and Mars, lift coefficients of approximately 0.015 and 0.034, respectively, are to be expected.…”

Section: Approximate Calculation For Aga Boundary Conditionsmentioning

confidence: 99%

“…In addition, Mars has some of the tallest mountains in the solar system, with Olympus Mons reaching nearly 22 km above the mean radius of Mars. Assuming the lift coefficients given by Anderson et al [6], a vehicle mass-to-area ratio of approximately 100 kg∕m 2 would keep the vehicle around 25 to 30 km during cruise at the reference altitude, which clears the Martian mountains. At Venus, the same vehicle would cruise in a range of about 85 to 90 km, depending on the velocity.…”

Section: Approximate Calculation For Aga Boundary Conditionsmentioning

confidence: 99%

“…To perform an AGA maneuver, a vehicle with a high L∕D ratio is desirable so that the energy lost to drag is minimized for an arbitrary turn angle. It was found that waveriders may be among the best candidate vehicles to perform or test AGA missions due to their potential for high L∕D ratios [5][6][7][8].…”

mentioning

confidence: 99%

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Design and Optimization of Interplanetary Aerogravity-Assist Tours

Henning

Edelman

Longuski

2014

Journal of Spacecraft and Rockets

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Aerogravity-assist maneuvers have the potential to deliver spacecraft to a wide range of destinations within the solar system. The ultimate goal is to minimize the maximum lift-to-drag ratio that a vehicle must provide for a given mission. First, assuming an arbitrary maximum lift-to-drag ratio during the aerogravity assist as an initial guess (e.g., maximum L∕D 3), a patched-conic solution is obtained for the interplanetary trajectory, yielding boundary conditions at the flyby planets. Second, the flythrough departure velocity at a given planet is maximized while meeting the required atmospheric turn angle to get to the next planet. Depending on whether the departure velocity at each planet is greater (or less) than required, the vehicle's maximum L∕D is determined such that the aerogravity-assist maneuver matches the required departure velocity and turn angle. Then, the overall mission minimum value representing the vehicle's maximum L∕D to complete a given tour is determined by taking the highest value (or limiting case) found from all of the aerogravity-assist flybys. As an example (and as a possible technology demonstrator) an Earth departure and return mission with flybys at Mars and Venus with a total flight time of 375 days and a maximum lift-to-drag ratio of 3.015 is constructed, enabling atmospheric sample returns from Earth's nearest neighbors.

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Section: Interplanetary Trajectory Selection Using Stourmentioning

confidence: 99%

Section: Approximate Calculation For Aga Boundary Conditionsmentioning

confidence: 99%

Section: Approximate Calculation For Aga Boundary Conditionsmentioning

confidence: 99%

mentioning

confidence: 99%

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Design and Optimization of Interplanetary Aerogravity-Assist Tours

Henning

Edelman

Longuski

2014

Journal of Spacecraft and Rockets

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“…In fact, the cross range ability of reentry vehicles is tied directly to their ratio of lift-to-drag 4 . When performing a plane change, however, the spacecraft desires to maintain its orbital energy.…”

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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Aero-gravity assist maneuvers: controlled dynamics modeling and optimization

Armellín

Lavagna

Ercoli-Finzi

Periodic, Quasi-Periodic and Chaotic Motions in Celestial Mechanics: Theory and Applications

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Hypersonic waveriders for planetary atmospheres

Cited by 47 publications

References 13 publications

Design and Optimization of Interplanetary Aerogravity-Assist Tours

Design and Optimization of Interplanetary Aerogravity-Assist Tours

Aerodynamic and Propulsion Assisted Maneuvering for Orbital Transfer Vehicles

Aero-gravity assist maneuvers: controlled dynamics modeling and optimization

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