Abstract: A supplemental thrust system for an airplane comprising a submerged inlet duct, a diffuser section in communication with the inlet duct, and a duct outlet in communication with the diffuser section, an outlet nozzle in communication with the duct outlet, a turbocharger unit comprising one or more turbocharges in communication with each other to provide compressed air to the engine and the cabin, a heat exchanger unit comprising a plurality of heat exchangers in the diffuser section to provide cooling liquid to cool pressurized air in the cabin, engine intake air and the engine jacket, where each turbocharger is coupled to the intake manifold of an engine to increase the power of the engine by introducing compressed air into the manifold.

Abstract: A fuselage for an airplane including a frame comprising an upper truss and a lower truss extending from a front end of the fuselage towards the rear end of the fuselage, wherein the lower truss comprises one or more forward box beams, a plurality of support rings attached to the upper truss and lower truss, a front bulkhead connected to a first end of the upper truss and lower truss, a main bulkhead connected to the upper truss and lower truss, a pressure vessel adapted to fit within the frame between the front bulkhead and main bulkhead, and a skin adapted to fit over the frame.

Abstract: A wing including a spar, a box shaped sleeve in the spar running substantially the entire length of the wing, a skin affixed to spar and to the corners of the sleeve and shaped to from a leading edge and trailing edge of the wing, a spoiler affixed to an upper surface of the trailing edge of the spar, a vent affixed to the lower surface of the trailing edge of the spar below the spoiler.

Abstract: A front landing gear system for an aircraft including a swing arm rotatively coupled to a wheel, a forward link arm rotatively coupled to the swing arm, a oleopneumatic cylinder rotatively coupled to the swing arm, second extension arm and a bulkhead, a plate rotatively coupled to the bulkhead, an actuation device rotatively coupled to the bulkhead and to the plate, where refraction of the linear actuation device causes the plate and extension arms to move upward towards the bulkhead.

Abstract: A main landing gear system for an aircraft including a truss element, a first support unit and second support unit affixed to the truss on opposing sides of the truss, a first actuator and a second actuator rotatively affixed to respective first support unit and second support unit and to a respective first wheel and second wheel, a first trailing link and second trailing link each coupled to the respective first wheel and second wheel, a first extension plate and second extension plate each rotatively coupled to the respective first trailing link and second trailing link and to a side of the truss, a first plate locking unit and second plate locking unit rotatively affixed to an end of the respective first extension plate or second extension plate and to a side of the truss.

Abstract: A wing flap control system on a wing comprising at least two control plates having an opening sized to accommodate a drive shaft, a drive shaft that engages each of the openings in each of the plurality of plates, a sprocket rotatively affixed the drive shaft with the drive shaft penetrating the other control plate, at least two idler sprockets between the control plates, a chain wrapped around the sprocket and idler sprockets, a support arm rotatively coupled to the chain by a chain shoe and to a foreflap, a link arm rotatively coupled to the support arm and to a flap, where movement of the drive shaft causes the foreflap and flap to extend and retract to increase or decrease the surface area of the wing.

Abstract: A support unit for a structure within a pressure vessel that includes an external load distribution plate, an internal load distribution plate, a standoff unit between the external load distribution plate and the internal load distribution plate that extends through an opening in a pressure vessel.

Abstract: A wing including a spar, a box shaped sleeve in the spar running substantially the entire length of the wing, a skin affixed to spar and to the corners of the sleeve and shaped to from a leading edge and trailing edge of the wing, a spoiler affixed to an upper surface of the trailing edge of the spar, a vent affixed to the lower surface of the trailing edge of the spar below the spoiler.

Abstract: A supplemental thrust system for an airplane comprising a submerged inlet duct, a diffuser section in communication with the inlet duct, and a duct outlet in communication with the diffuser section, an outlet nozzle in communication with the duct outlet, a turbocharger unit comprising one or more turbocharges in communication with each other to provide compressed air to the engine and the cabin, a heat exchanger unit comprising a plurality of heat exchangers in the diffuser section to provide cooling liquid to cool pressurized air in the cabin, engine intake air and the engine jacket, where each turbocharger is coupled to the intake manifold of an engine to increase the power of the engine by introducing compressed air into the manifold.

Abstract: A wing flap control system on a wing comprising at least two control plates having an opening sized to accommodate a drive shaft, a drive shaft that engages each of the openings in each of the plurality of plates, a sprocket rotatively affixed the drive shaft with the drive shaft penetrating the other control plate, at least two idler sprockets between the control plates, a chain wrapped around the sprocket and idler sprockets, a support arm rotatively coupled to the chain by a chain shoe and to a foreflap, a link arm rotatively coupled to the support arm and to a flap, where movement of the drive shaft causes the foreflap and flap to extend and retract to increase or decrease the surface area of the wing.

Abstract: A support unit for a structure within a pressure vessel that includes an external load distribution plate, an internal load distribution plate, a standoff unit between the external load distribution plate and the internal load distribution plate that extends through an opening in a pressure vessel.

Abstract: A main landing gear system for an aircraft including a truss element including a front portion joined to a rear portion, a first support unit and second support unit affixed to the truss at the junction of the first portion and the second portion on opposing sides of the truss, a first actuator and a second actuator rotatively affixed to respective first support unit and second support unit and to a respective first wheel and second wheel, a first trailing link and second trailing link each coupled to the respective first wheel and second wheel, a first extension plate and second extension plate each rotatively coupled to the respective first trailing link and second trailing link and to a side of the truss, a first plate locking unit and second plate locking unit rotatively affixed to an end of the respective first extension plate or second extension plate and to a side of the truss, where actuation of the actuator causes the extension plates to move up or down with respect to the truss raising and lowering

Abstract: A fuselage for an airplane including a frame comprising an upper truss and a lower truss extending from a front end of the fuselage towards the rear end of the fuselage, wherein the lower truss comprises one or more forward box beams, a plurality of support rings attached to the upper truss and lower truss, a front bulkhead connected to a first end of the upper truss and lower truss, a main bulkhead connected to the upper truss and lower truss, a pressure vessel adapted to fit within the frame between the front bulkhead and main bulkhead, and a skin adapted to fit over the frame.

Abstract: A front landing gear system for an aircraft including a swing arm rotatively coupled to a wheel, a forward link arm rotatively coupled to the swing arm, a oleopneumatic cylinder rotatively coupled to the swing arm, second extension arm and a bulkhead, a plate rotatively coupled to the bulkhead, an actuation device rotatively coupled to the bulkhead and to the plate, where refraction of the linear actuation device causes the plate and extension arms to move upward towards the bulkhead.

Abstract: A deployable crew quarters incorporates folding panels and acoustic panels to provide a lightweight on-orbit crew quarter. The deployable crew quarters preferably includes a frame and a plurality of panels mounted to the frame. At least one of the panels is hinged to the frame to allow movement between a stowed position and a deployed position. More specifically, the panels include a front panel coupled to the frame and two side panels moveable coupled to the frame. The two side panels are moveable between a stowed position and a deployed position. Still further, a top panel is also preferably moveable coupled to the frame, wherein the top panel is moveable between a stowed position and a pop-up deployed position. The front panel includes a sliding door panel to allow crew access to the deployable crew quarters. The front panel also preferably extends outward from the frame, which provides space in which a ventilation mechanism can be mounted.

Abstract: An electronic torque wrench including a strain measuring bridge circuit disposed to measure the bending strain of the handle thereof, a NAND gate circuit connected to alternately excite the bridge according to the switching state thereof, a differential circuit connected to receive the bridge balance signal, an integrator connected to integrate a selected polarity output signal from said differential circuit, a clock-driven counter connected to be inhibited for a predetermined time interval following each time the integrating circuit output signal changes polarity providing selected binary level output signals to switch the NAND gate circuit according to the state thereof and a logical switching circuit connected to the selected binary level output signals of said counter for alternatively connecting either the output signal from the differential circuit or a fixed reference signal to the integrator.