Sky Launch Corporation

Other

United States of America As Represented by the Administrator of Nasa

Gerald D Budd

Thomas McNicholas

Angela Monheim

Charles E Rogers

A system and method for carrying an aeronautical or launch vehicle to altitude for release to flight may involve a multiplicity of mounting elements affixed to a carrier aircraft in distributed fashion along a mounting axis. Each mounting element may include a cradle and a retention strap. Each retention strap may be suspendedly attached to a respective cradle, and actuatable from a retention configuration to a release configuration. The retention configuration allows the retention straps to clampingly secure the vehicle to the respective cradles. The actuation of the retention straps from the retention configuration to the release configuration may disable the clamping securement and thereby release the vehicle to drop away from the cradles. For one or more of the retention straps, the actuation may be by way of detonating at least one corresponding pyrotechnic fastener.

System and method for carrying an aeronautical or launch vehicle to altitude for release to flight

Disclosed are systems and methods for reconnectably coupling an aft vehicle to a forward vehicle in flight. A docking structure is affixed to the forward vehicle. A coupler has a line connection portion, a probe receiver port, and a plurality of aerodynamic controls. The probe receiving port receives and releasably retains a probe portion of the aft vehicle. A tow line has a proximal end, a distal end, and a line extension length. The proximal end may be attached to the tow actuation element. The distal end is connectable to the coupler. The tow actuation element is configured to adjust the line extension length. The aerodynamic control elements are configured to adjust lateral and vertical positioning of the coupler with respect to the probe portion when the system is in flight. Movement of the coupler is restrained with respect to the docking structure when docked thereto.

System and method for reconnectably coupling an AFT vehicle to a forward vehicle in flight

Disclosed are systems and methods for carrying an aeronautical or launch vehicle to altitude for release to independent flight. The system may comprise one or more mounting elements affixed to a carrier aircraft along a mounting axis and actuatable from a retention configuration to a release configuration. The retention configuration enables the mounting elements to secure the vehicle to the carrier aircraft. Actuation from retention configuration to release configuration releases the vehicle from the carrier aircraft. A detent element is configured to restrict movement of the vehicle rotationally about, and axially along, a roll axis of the vehicle with respect to the carrier aircraft when the vehicle is secured to the carrier aircraft. The system may include an adaptor beam to which each mounting element is fastened, and by which the affixing is achieved. The retention configuration may enable the mounting elements to secure the vehicle beneath the carrier aircraft.

The invention is a system and method of air launching a powered launch vehicle into space or high altitude. More specifically, the invention is a tow aircraft which tows an unpowered glider, with the powered launch vehicle attached thereto, to launch altitude. The powered launch vehicle is released from the unpowered glider and powered on for launch.

System and method for air launch from a towed aircraft

The model airplane control surface position measurement system and method uses an adjustable ruler scale attached to a support stand in combination with a laser device attached to the trailing edge of a control surface of the model airplane. The laser device may be adjusted to orient the light beam axis to be approximately perpendicular to the control surface hinge axis. The ruler scale may be positioned behind the control surface at a distance from the hinge axis using a positioning rod. The support stand is adjusted to orient the positioning rod perpendicular to the ruler scale at a zero angle deflection mark. The ruler scale is also adjusted such that the laser device light beam is incident at the zero angle deflection mark. The model airplane control surface may then be deflected by the control mechanism and the deflection angle observed on the ruler scale at the point of incidence of the laser device light beam.

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Lancaster, CA, United States of America

Gerald D Budd