Abstract: For use with towable airfoils used to supply lift to a towed rider to assist with jumping in sports and recreation, a handle system having one or more control lines for coupling to the airfoil, and a line for coupling the handle to a tow vehicle, the one or more control lines and line for coupling to the tow vehicle being coupled together by a tension translation mechanism that divides the tension from the line for the tow vehicle to the one or more control lines by a predetermined factor, which typically would be other than 1:1. The handle system may further include an engagement mechanism for engaging the one or more control lines to lock or brake a line.

Abstract: A personal aircraft device (“PAD”) and a powered personal aircraft device (“PPAD”) configured to be ridden and/or releasably connected to a person or user. The personal aircraft device can be configured to provide a large array of maneuvers during sky diving or free fall, and perform somewhat as a lifting device requiring a parachute landing and/or alternatively can be configured to glide to a safe landing. The personal aircraft device and powered personal aircraft device according to the present invention provide for high performance, speed and/or maneuvering of a person or user during free fall, and can provide increased or significantly increased gliding capability versus free falling or deployment of a high performance parachute.

Abstract: A personal aircraft device (“PAD”) and a powered personal aircraft device (“PPAD”) configured to be ridden and/or releasably connected to a person or user. The personal aircraft device can be configured to provide a large array of maneuvers during sky diving or free fall, and perform somewhat as a lifting device requiring a parachute landing and/or alternatively can be configured to glide to a safe landing. The personal aircraft device and powered personal aircraft device according to the present invention provide for high performance, speed and/or maneuvering of a person or user during free fall, and can provide increased or significantly increased gliding capability versus free falling or deployment of a high performance parachute.

Abstract: Aircraft flight data collection is enhanced by changing the data sampling rate as a function of an operational condition of the aircraft, such as its flight phase. An algorithm is used to determine the flight phase. Then, the data is collected at a first sampling rate when the flight phase is one of a first set of flight phases and collected at a second sampling rate when the flight phase is one of a second set of flight phases. The second sampling rate is greater than the first sampling rate to maximize the data storage capacity of the system. Generally, the higher sampling rate is used with transient flight phases such as takeoff and thrust reverse.

Abstract: The present invention related to a universal joint assembly for attaching two missile sections together wherein one section is a recycled rocket motor. The joint assembly includes a plurality of attachment blocks each secured through fasteners to the outer surface of the rocket casing. Separate fasteners are employed between the attachment blocks and the adjacent section. As the fasteners are advanced, the attachment blocks are first secured to the rocket casing and then the attachment blocks are drawn toward the adjacent section until the sections are abutting one another. The attachment blocks do not abut the adjacent section.

Abstract: The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section, a lower section, and fabric ribs disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded and deployed in the air.

Abstract: A method of converting diatomic oxygen to a free-radical version such that the combination of the two can produce ozone. It is widely held that the ozone layer is becoming depleted as ever increasing levels of chloroflourocarbons become present at that altitude. It is believed that even though such ozone-destroying chemicals will be banned by the year two-thousand their effects will be felt long after. A method for combating the depletion of ozone would not only be of tremendous value to the environment but it would also herald the advent of technology serving to function on a world-wide scale. The method for producing free-radical oxygen would simply involve using coherent ultra-violet light produced by a laser mounted on a satellite; the satellite being in geo-synchronous orbit about the location where ozone depletion is evident(i.e. Antarctica). When the ultra-violet light hits available atmospheric oxygen it should act to break the oxygen-oxygen bond to produce ozone.

Abstract: The weight-shift movements of a suspended pilot are transformed into electrical signals representative of the movements. The signals may be used as the pitch and roll input information in an interactive computerized flight simulation system. The signals may also be generated by an actual pilot of a hang glider or ultralight aircraft and used on board to control ailerons, elevators, rudders, or the like, so as to enhance the performance potentials of these types of aircraft.

Abstract: A flight control apparatus for use in an aircraft includes support structure for suspending a pilot beneath a pair of wings while permitting movement of the pilot relative to the aircraft in the forward, rearward and both lateral directions. A control system is connected between the support structure and the wings for altering the geometries of the wings during flight to vary the drag and lift characteristics of the wings and alter the direction of flight and the speed/performance range of the aircraft in response to movement of the pilot relative to the aircraft in any of the forward, rearward, and lateral directions. The geometries of the wings are altered during flight by moving the leading edges between extended and retracted positions relative to the central longitudinal axis of the aircraft in response to movement of the pilot in the forward, rearward and both lateral directions relative to the aircraft.

Abstract: An aircraft comprises a vehicle (1) suspended in flight by a steering control rod (68) pivotally mounted to the body of the vehicle and having outer ends (12, 14) connected to the lower ends of load suspension lines (3, 5, 6) connected at their upper ends to a flexible wing portion (2) of a ram air inflatable type of airfoil canopy. Steering of the aircraft is by pivotal movement of control rod (68) to manipulate the load suspension lines and thereby the canopy surfaces. The aircraft may be radio controlled by a radio receiver (112) in the vehicle body for operating the speed of a drive motor (36) for driving a propeller (38) and a steering drive motor (98) coupled to the control rod (68) by a suitable linkage system. Battery pack (104) is removably mounted in the vehicle body for providing power to the receiver and motors therein. The radio controlled aircraft is controlled by a remote transmitter which controls the steering and speed of the aircraft.

Abstract: A safety apparatus for a hang glider that indicates any failure of a pilot to properly hook in a flight harness. The apparatus includes a circuit having a power source, such as a dry cell battery, connected to an alarm through a harness hook in sensor. When the pilot fails to properly hook in the harness, an alarm sounds. The circuit also includes an on/off switch that activates the circuit only in direct response to erection of the hang glider. Thus, the circuit is deactivated when the hang glider is disassembled for transport to or from a launch site and during storage. Consequently, annoying alarm soundings are avoided and battery life is increased. In addition, the circuit includes a deactivation switch that prevents the alarm from sounding when the hang glider is resting on the ground. Finally, a test switch is provided to allow manual testing to confirm proper activation and operation of the circuit.

Abstract: A safety device to warn the pilot of a hang glider if take-off is attempted without the glider hook-up strap being connected to the pilot's harness includes two sensors arranged in series with an alarm. One of the sensors is arranged to close a circuit when the glider is positioned in a take-off attitude and the other sensor closes a circuit when the free end of the hook-up strap is disconnected from the pilot's harness. The alarm is activated when both circuits are closed.