Abstract: Side impact airbag system for a vehicle includes a side airbag arranged to deploy along a left or right side of the vehicle and an electronic crash sensor. The electronic crash sensor includes a housing, a mass arranged within the housing to be movable in a lateral direction relative to the housing in response to lateral accelerations of the housing, and a control mechanism for controlling deployment of the side airbag and which is responsive to the motion of the mass only in the lateral direction. The housing is mounted in such a position and a direction as to sense an impact into a side of the vehicle resulting in lateral acceleration of the housing. The electronic crash sensor may generate a signal representative of the movement of the mass.

Abstract: Vehicle including an occupant protection apparatus for protecting an occupant during an impact into a side of the vehicle, and a side impact, electronic crash sensor assembly for detecting impact into the side of the vehicle and controlling the occupant protection apparatus responsive to the detected impact. The sensor assembly includes a sensor housing arranged in a door or between inner and outer side panels along a side of the vehicle, a movable sensing mass arranged within and movable in the lateral direction relative to the sensor housing in response to lateral accelerations thereof, a micro-processor containing an algorithm which generates a time-varying signal representative of lateral movement of the mass, analyzes the signal and generates a deployment signal based thereon, and a control unit for receiving the deployment signal from the micro-processor and controlling deployment of the occupant protection apparatus based thereon.

Abstract: Vehicle including a side impact sensor system having a longitudinally extending outer skin arranged on a side of the vehicle, a system housing arranged inward of the outer skin and having an opening facing a portion of a passenger compartment, an inflatable airbag arranged in the system housing, an inflator arranged in connection with the system housing, and a sensor system for detecting an impact into a side of the vehicle. The sensor system includes a sensor housing and a mass arranged therein and movable relative thereto housing in response to acceleration in excess of a threshold value. Movement of the mass relative to the sensor housing provides an indication of a side impact for which deployment of the airbag is desired. The inflator is actuated in response to a side impact by the sensor system in order to expel the airbag through the opening into the passenger compartment.

Abstract: A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a fixed wing and a fuselage with a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters, preferably integrated into the wing, on each side of the fuselage. The aircraft has a lift to drag ratio equal to or greater than 2. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with at one thruster inoperative on each side of the fuselage. At least one thruster on each side of the fuselage preferably comprises a “levitator” which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.

Abstract: Side airbag system including an airbag arranged to deploy in the event of an impact into a side of the vehicle, a side impact crash sensor arranged to sense an impact into a side of the vehicle, and an inflator for inflating the airbag. The crash sensor is an electrical sensor which includes a movable sensing mass which moves when the side of the vehicle is impacted and a signal generating mechanism for generating a time-varying signal representative of movement of the sensing mass, analyzing the signal representative of the movement of the sensing mass and generating a deployment signal based thereon. The inflator is coupled to the crash sensor and receives the deployment signal therefrom and inflates the airbag upon receipt of the deployment signal.

Abstract: A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a fixed wing and a fuselage with a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters, preferably integrated into the wing, on each side of the fuselage. The aircraft has a lift to drag ratio equal to or greater than 2. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with at one thruster inoperative on each side of the fuselage. At least one thruster on each side of the fuselage preferably comprises a “levitator” which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.

Abstract: A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters attached to the outer periphery of the compartment. At least two thrusters are disposed on each side of the compartment. The thrusters, which are preferably ducted fan units, are capable of providing a vertically upward force to the compartment. The thrusters preferably comprise a “Levitator” which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.

Abstract: An end stop is disclosed for limiting the maximum displacement of a flexible member so as to minimize stress on this member and thus provide an extended surface life. The flexible member is rigidly supported at at least two spaced-apart points such that the flexible member can flex in the region between these points. The end stop includes a support member for clamping the flexible member at the two supporting points and a wall surface arranged in opposed, facing relationship to the flexible member in the region between the two points. The curvature of the wall surface is defined by first and second curves that form a continuous curvature and have first and second derivatives of the local angle .phi. of the tangent to the curve with respect to the distances along the curve which are zero.

Abstract: A ground-air-water craft comprises a fuselage body with a passenger compartment mounted thereon, a box-type main wing connected to the fuselage and extending outwardly on both sides thereof, the main wing comprising an upper wing and a lower wing which are substantially horizontal and which have a total wing span in the range of 5 to 10 feet, as well as a right side member and a left side member, each side member extending substantially vertically and connected between the lateral ends of the upper and lower wings on the respective right and left sides of the craft. The craft also comprises a control or canard wing connected to the fuselage and extending outwardly on both sides of the fuselage with a wing span no greater than 10 feet.