Selection of a Carrier Aircraft and a Launch Method for Air Launching Space Vehicles

Sarigul-Klijn, Marti; Hudson, Gary; McKinney, Bevin; Llc, AirLaunch; Voss, Jim; Chapman, Phil; Morgan, Bob; Tighe, Jim; Kramb, Jason; Doyle, Ken; Quayle, Michael; Brown, C Jr Q

doi:10.2514/6.2008-7835

Cited by 8 publications

(7 citation statements)

References 1 publication

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“…the NB-52B). Note that other launch configurations have been investigated in Refs (7,8) for launch to orbit applications, such as towed carry and internal carry. Those launch configurations have not been considered in the present context.…”

Section: Consideration Of Hypersonic Programs and Carrier Vehiclesmentioning

confidence: 99%

A sizing-based approach to evaluate hypersonic demonstrators: demonstrator-carrier constraints

et al. 2020

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The objective of this study is to identify, evaluate, and provide recommendations towards the realisation of near-term hypersonic flight hardware through the consideration of carrier vehicle constraints. The current rush of available funds for hypersonic research cannot cause a program to ignore growth potential for future missions. The prior NB-52 carrier vehicles, famous for the X-15 and X-43A missions, are retired. Next generation hypersonic demonstrator requirements will necessitate a substitution of carrier vehicle capability. Flight vehicle configuration, technology requirements, and recommendations are arrived at by constructing and evaluating a hypersonic technology demonstrator design matrix. This multi-disciplinary parametric sizing investigation of hypersonic vehicle demonstrators focuses on the evaluation of the combined carrier platform, booster, and hypersonic cruiser solution space topography. Promising baseline configurations are evaluated against operational requirements by trading fuel type, endurance cruise time, and payload weight. The multi-disciplinary study results are constrained with carrier payload mass and geometry limitations. The multi-disciplinary results provide physical insights into near-term hypersonic demonstrator payload and cruise time requirements that will stretch the capability of existing carrier aircraft. Any growth in hypersonic research aircraft size or capability will require new carrier vehicle investments.

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Section: Consideration Of Hypersonic Programs and Carrier Vehiclesmentioning

confidence: 99%

A sizing-based approach to evaluate hypersonic demonstrators: demonstrator-carrier constraints

et al. 2020

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“…Currently, several airlaunch systems are under development (see [14], [3]). Most current airlaunch projects use standard or lightly modified airplanes as first stage.…”

Section: Introductionmentioning

confidence: 99%

Conditional servo-compensator of an airlaunch system

Nguyễn

Damm

2013

2013 10th IEEE INTERNATIONAL CONFERENCE ON NETWORKING, SENSING AND CONTROL (ICNSC)

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A Multiple Input Multiple Output (MIMO) controller based on the conditional servo-compensator technique is designed for the robust stabilization of a new satellite launching strategy called (unmanned) airlaunch. This strategy consists in using a two-stages launching system. The first stage is composed of an airplane (manned or unmanned) that carries a rocket launcher which constitute the subsequent stages. The control objective is to stabilize the aircraft in the launch phase. It is developed separately for two nonlinear motion modes of the model, the longitudinal and lateral modes, and is applied to the full multi-input multi-output model of the aircraft. The controller is indeed able to assure system stability for rather large disturbances. Performance of the proposed control algorithm is illustrated through simulations.

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“…A more efficient solution in this case is to use the procedure of airlaunch (see ). It consists of using a two‐stage launching system (see Figure ).…”

Section: Introductionmentioning

confidence: 99%

MIMO conditional integrator control for unmanned airlaunch

Nguyễn

Damm

2013

Intl J Robust & Nonlinear

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International audienceA nonlinear MIMO controller based on the conditional integrator technique is designed for the robust stabilization of a new satellite launching strategy called (unmanned) airlaunch. This control technique concerns an integrator performing similar to a sliding mode controller when the system is outside a boundary layer defined by the controller, and performing as a linear controler that provides the integral term when the system enters into the boundary layer. Satellite airlaunch strategy consists in using a two-stage launching system. The first stage is composed of an airplane (manned or unmanned) that carries a rocket launcher, which constitute the subsequent stages. The control objective is to stabilize the aircraft in the launch phase. It is developed separately for the two nonlinear (one MIMO and one SISO) motion modes of the model, the longitudinal mode and lateral mode, and is then applied to the full model of the aircraft. The considered system is highly nonlinear, mostly as a consequence of a possible large angle of attack, sideslip, and roll angle. Finally, the present work illustrates through simulations, the good performance of the proposed control algorithm

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Selection of a Carrier Aircraft and a Launch Method for Air Launching Space Vehicles

Cited by 8 publications

References 1 publication

A sizing-based approach to evaluate hypersonic demonstrators: demonstrator-carrier constraints

A sizing-based approach to evaluate hypersonic demonstrators: demonstrator-carrier constraints

Conditional servo-compensator of an airlaunch system

MIMO conditional integrator control for unmanned airlaunch

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