Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: An oblique wing aircraft (1) designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment (27) on one side of the wing and an aft swept wing segment (29) on the opposite side of the wing. A center oblique airfoil section (25) connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. The center oblique airfoil section is not shaped solely to function as a circular fairing to fill the gap between an oblique wing and a fuselage at different oblique wing angles, nor is it a second wing in an X wing configuration. Preferably, the aircraft is an all-wing aircraft.

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: An oblique wing aircraft (1) designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment (27) on one side of the wing and an aft swept wing segment (29) on the opposite side of the wing. A center oblique airfoil section (25) connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. The center oblique airfoil section is not shaped solely to function as a circular fairing to fill the gap between an oblique wing and a fuselage at different oblique wing angles, nor is it a second wing in an X wing configuration. Preferably, the aircraft is an all-wing aircraft.

Abstract: The current invention relates primarily to the control of rotary wing and fixed wing aircraft where a small electric actuator (7, 104) changes the pitch on a small aerodynamic surface (5, 66) and the resulting airloads on said small aerodynamic surface are used to change the pitch on a significantly larger aerodynamic surface (3, 60). In the preferred embodiment the resulting airloads on said larger aerodynamic surface is then used to change the pitch on a still larger aerodynamic surface (1, 62). As a result small electric actuators are capable of moving and controlling large aircraft control surfaces with an effective two step amplification of power utilizing the energy in the airstream. The current invention also discloses means to control and prevent undesirable motion of said aerodynamic surfaces.

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: Passenger accommodations are easily and rapidly convertible from conventional seats to bunk beds and back. A support structure (9) supports a seat pad (13) and a seat pad extension (15) and also rotatably supports a seat back (5). The seat pad extension (15) and seat back (5) are partially supported by the support structure (9) of a row of seats ahead of the convertible seats when the convertible seats are converted to bunk beds. A third bunk bed (21,23) may be unfolded under the lower bunk bed formed by the seat pad (13, 15).

Abstract: A method of launching and retrieving a UAV (Unmanned Aerial Vehicle) (10). The preferred method of launch involves carrying the UAV (10) up to altitude using a parasail (8) similar to that used to carry tourists aloft. The UAV is dropped and picks up enough airspeed in the dive to perform a pull-up into level controlled flight. The preferred method of recovery is for the UAV to fly into and latch onto the parasail tow line (4) or cables hanging off the tow line and then be winched back down to the boat (2).

Abstract: The current invention relates primarily to the control of rotary wing and fixed wing aircraft where a small electric actuator (7, 104) changes the pitch on a small aerodynamic surface (5, 66) and the resulting airloads on said small aerodynamic surface are used to change the pitch on a significantly larger aerodynamic surface (3, 60). In the preferred embodiment the resulting airloads on said larger aerodynamic surface is then used to change the pitch on a still larger aerodynamic surface (1, 62). As a result small electric actuators are capable of moving and controlling large aircraft control surfaces with an effective two step amplification of power utilizing the energy in the airstream. The current invention also discloses means to control and prevent undesirable motion of said aerodynamic surfaces.

Abstract: A pod (34) containing sensors and/or targeting systems such as laser designators or range finders are hung on a cable (30) below an aircraft (12). The line (30) can be reeled in or out similar to towed decoys. This allows the aircraft (12) to operate above or in the cloud cover while the sensors/targeting equipment (34) are operating below the cloud cover to find the enemy forces.

Abstract: Passenger accommodations are easily and rapidly convertible from conventional seats to bunk beds and back. A support structure (9) supports a seat pad (13) and a seat pad extension (15) and also rotatably supports a seat back (5). The seat pad extension (15) and seat back (5) are partially supported by the support structure (9) of a row of seats ahead of the convertible seats when the convertible seats are converted to bunk beds. A third bunk bed (21,23) may be unfolded under the lower bunk bed formed by the seat pad (13, 15).

Abstract: A pod (34) containing sensors and/or targeting systems such as laser designators or range finders are hung on a cable (30) below an aircraft (12). The line (30) can be reeled in or out similar to towed decoys. This allows the aircraft (12) to operate above or in the cloud cover while the sensors/targeting equipment (34) are operating below the cloud cover to find the enemy forces.

Abstract: An aircraft adapted for flight in helicopter mode with its longitudinal axis oriented generally vertically and in airplane mode with its longitudinal axis oriented generally horizontally is provided with the capability of launching and landing with the tail end directed skyward. The invention also includes improvements to the controllability and efficiency of aircraft in helicopter mode provided by the stabilizer wings and relative rotation of the fuselage section about the aircraft's longitudinal axis. The aircraft has an elongate boom positioned between the rear fuselage and the stabilizer wings for engagement with a base structure. The base structure may be attached to a building, a trailer transporter, a ship or some other structure. The base may be a beam having latching arms that swing inward when pressure from the boom is applied, then trap the boom in a recess between the latching arm and beam, thereby suspending the aircraft.

Abstract: The present invention pertains to an aircraft that is capable of converting between vertical flight or helicopter mode flight, and horizontal flight or airplane mode flight where a two-bladed rotor is employed as both helicopter rotor blades in vertical flight and as a fixed wing in horizontal flight. In vertical flight, a bearing connection between two fuselage sections enables a forward section supporting the rotor blades to rotate relative to an aft section of the aircraft fuselage about the longitudinal axis of the aircraft. The exhaust or thrust force created by the mode of power (either a propeller engine or a turbine jet engine) is partially routed over the exterior of the aircraft to provide both vertical and horizontal thrust force, and in one embodiment a portion of the exhaust is routed through the interiors of the rotor blades and out exhaust ports at the blades' distal ends to rotate the blades in vertical flight and to provide a thrust force for the blades in horizontal flight.