Abstract: An isolator in an exhaust system of a vehicle is provided. The isolator comprises a bracket to be connected with an under body of the vehicle; and a gas filled cushion at least partially embedded in the bracket. The cushion is formed to have a through hole in a middle portion and the through hole is configured to receive a hanger connected to an exhaust system.

Abstract: Apparatus and method for propelling a user wearing paragliding equipment are disclosed The apparatus includes at least one thruster for providing thrust in a predetermined direction; and an attachment element for attaching the at least one thruster to a user's body such that the thruster is secured against the front portion of the user's body.

Abstract: The system includes a keel fitting that can be rigidly attached directly to the keel of the hang glider. It also includes two elongated frame members symmetrically mounted on opposite sides of the keel fitting. At least one electrical motor is mounted on each frame member and there are at least two propellers, each in driving engagement with a corresponding one of the electrical motors. The system further includes an electrical power unit mounted on the back of the pilot. The electrical power unit includes at least one battery and a pilot-actuated control circuit to vary the electrical power supplied to the electrical motors. The system gives the pilot the capability of taking off from a flat terrain. Once airborne, the system is not operated and the hang glider can then be used as an unpowered one.

Abstract: A small unmanned airplane includes; a main wing having a camber airfoil whose under surface is approximately flat, narrowing in the shape of taper to a blade tip, leading edge of which holds sweepback angle, of flying wing type which has an aerodynamic surface of tailless wing type and is low aspect ratio; movable flaps extending approximately extreme breadth in trailing edge part of both left and right sides of the main wing, having a dihedral angle at least in level flight; vertical stabilizers placed at blade tips of left and right of the main wing; and two propellers installed on the top surface of the main wing. This can materialize miniaturization and weight saving of a small unmanned airplane for individual carrying capability and for suitability for such as lift-off by hand throw.

Abstract: A modular automated air transport system comprising an unmanned autonomous aircraft having a selectively detachable control systems portion and a structural air frame portion, wherein the structural air frame portion contains an interior cargo hold, aerodynamic members having control surfaces and at least one propulsion device attached to the structural air frame portion; and wherein the control system portion includes a control computer for autonomously controlling the flight of said air transport system from one known location to a second known location.

Abstract: An aeronautical apparatus, the combination comprising a primary airfoil having at least one panel which is an upper panel, a lower panel, and multiple gas containing tubes associated with the airfoil and extending lengthwise thereof, the tubes including relatively larger cross-section tubes positioned chordwise of the airfoil, and relatively smaller cross-section positioners located to stabilize the relatively larger cross-section tubes.

Abstract: A small radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, the device being capable of short take-off and landing and flying at maximum speed of 35 Km/h. The device includes a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6). The base is a welded one-piece element that includes the engine, the airscrew, a tank and the radio control. The apex is a welded one-piece element. The lower plane and the two lateral planes include spars (11, 12) assembled at the base and as the apex. The lower plane includes at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires.

Abstract: An aeronautical apparatus, the combination comprising a primary airfoil having at least one panel which is an upper panel, a lower panel, and multiple gas containing tubes associated with the airfoil and extending lengthwise thereof, the tubes including relatively larger cross-section tubes positioned chordwise of the airfoil, and relatively smaller cross-section positioners located to stabilize the relatively larger cross-section tubes.

Abstract: An aeronautical apparatus, the combination comprising a primary airfoil having at least one panel which is an upper panel, a lower panel, and multiple gas containing tubes associated with the airfoil and extending lengthwise thereof, the tubes including relatively larger cross-section tubes positioned chordwise of the airfoil, and relatively smaller cross-section positioners located to stabilize the relatively larger cross-section tubes.

Abstract: A motorized paraglider including a wheeled frame with a steerable nose wheel and a pair of casters arranged in a tricycle configuration. Each of the casters has a trailing wheel and a support bracket rotatably carrying the trailing wheel. A swivel mechanism is positioned atop the support bracket for permitting the trailing wheel to swivel about a substantially vertical axis. A stop is coupled with the support bracket for preventing the trailing wheel from swiveling inwardly. A spring is also coupled with the support bracket for normally urging the support bracket against the stop yet, under the influence of a sufficient lateral force, permitting the trailing wheel to swivel outwardly.

Abstract: A deployable wing that is folded so as to fit into a carrier such as an airplane that is released and automatically with the aid of parachutes to deploy and fly a given distance without assistance other than steering to reach a given destination and a propeller driven by a gas powered engine is actuated to propel the wing an extended distance. A guard is disposed adjacent to the propeller to assure that the lines of the parachutes do not get tangled into the propeller blades.

Abstract: A powered parachute or pendulum flying machine which includes a mechanism for shortening the chord length of the parachute wing, a mechanism for shortening the distance between the upper and lower airflow surfaces of the parachute wing, and a mechanism for adjusting position of the pilot module relative to the wing so as to adjust the center of gravity of the powered parachute. The mechanism for shortening chord length includes a tube running along the trailing edge of the parachute wing and control lines running from the tube to the pilot module. Pulling in the lines draws the tube forwardly and shortens the chord length. Preferably at the same time as the chord length is decreased, wing height is decreased by the mechanism for shortening the distance between the upper and lower airflow surfaces. Such is accomplished by collapsing a wall disposed between the upper and lower airflow surfaces to the pilot module.

Abstract: A para-plane (parachute or parafoil airplane), ultralight, or the like is provided with a ducted propeller or fan to increase efficiency of the powerplant, thus reducing the size of the powerplant required. In addition, the duct may reduce propeller and/or engine noise and enhance safety for pilot, passengers and bystanders. Axial vanes may be provided upstream or downstream of the propeller within the duct to counteract the torque effect of the propeller. In another embodiment, a novel inflatable parafoil may be provided to reduce the effort required to initially inflate a prior art parafoil and reduce the incidence of ground strikes of the parafoil. The inflatable parafoil may be inflated with a buoyant gas such as helium or hot air to further reduce ground contacts and provide limited buoyancy to the aircraft.

Abstract: An ultralight helicopter has a pair of counter-rotating rotor assemblies which in combination yield zero net angular momentum when rotating at equal speeds. A single motor drives both rotors through a counter-rotating bevel gear set coupled to a pair of concentrically nested output shafts. In an alternative embodiment, the motor is coupled to the rotors through a hydraulic drive system which includes a hydraulic pump and at least one hydraulic motor driving each of the rotor assemblies. The pilot is advantageously suspended in a "hang-glider" type harness from a single hang point positioned proximate the center of lift of the helicopter. A control bar is fixedly mounted to the frame and is grasped by the pilot suspended in the harness. The pilot maneuvers the helicopter in both the pitch and roll directions by manipulating the control bar. The pilot shifts his own center of gravity relative to the center of gravity of the helicopter while grasping the control bar to thereby maneuver the helicopter.

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: The device comprises an arch-like structure (3), shaped similar to a cage, which can be fixed to the motorcycle (1), essentially to its frame and sides; a parafoil sail (5), which can be mounted at the top of the cage, the sail ends being lowerable by a pedal or handle control; a propeller propulsion system (8) mounted at the rear of the motorcycle on the arch-like structure; and a clutching and declutching mechanism which, on control, drives either the driving wheel or the propeller.

Abstract: A vertical takeoff ultralight aircraft having an operator controlled high volume vane axial fan in communication with a conduit configured to direct an air stream produced by the fan to a spanwise air duct disposed forwardly of a wing including an air foil. High velocity air is discharged from the air duct and directed over the upper surface of the air foil. An induced air stream flows upwardly and rearwardly through an air flow path defined by the spanwise air duct and the air foil. The wing and air duct are configured such that the induced air stream joins the air stream discharged from the air duct to create reduced static pressure zone on the upper surface of the wing of sufficient magnitude to effect vertical lift. Fan discharge may be partially deflected rearwardly to provide horizontal thrust.

Abstract: Disclosed is a parawing with an automatic canopy withdrawing mechanism having a canopy, a frame to which the canopy is fastened and on which a pilot can be carried, a propeller mounted on the frame, and a plurality rows of suspension lines interconnecting the canopy and the frame. Also mounted on the frame is an automatic canopy withdrawing mechanism including a reel which may be operated to pull back the suspension lines for withdrawing the canopy. Further, a front pulling rope interconnecting the reel and two rows of suspension lines near the leading edge of the canopy, a rear pulling rope interconnecting the reel and the trailing edge of the canopy, and a plurality of guide rollers for guiding the movement of the front pulling rope and the rear pulling rope are provided so that the suspension lines and the canopy may be withdrawn by the automatic canopy withdrawing mechanism. With the canopy and the suspension lines being withdrawn.

Abstract: Load lines connect chordwise spaced portions of a ram air inflated, airfoil canopy to spaced anchors connected to a pilot supporting vehicle frame on which a forward thrust producing unit is removably mounted. The geometry of the assembled aircraft enhances take-off inflation of the canopy, establishes a stable flight frame when airborne, and enables simple engine throttle control of the thrust producing unit to regulate climb, descent and level flight. Common control is applied for both ground steering of the vehicle frame and air-borne steering of the canopy.

Abstract: Load lines connect chordwise spaced portions of a ram air inflated, airfoil canopy to spaced anchors connected to a pilot supporting vehicle frame on which a forward thrust producing unit is removably mounted. The geometry of the assembled aircraft enhances take-off inflation of the canopy, establishes a stable flight frame when airborne, and enables simple engine throttle control of the thrust producing unit to regulate climb, descent and level flight. Common control is applied for both ground steering of the vehicle frame and airborne steering of the canopy.

Abstract: A light aircraft having a parachute-wing, a single propeller, and means for controlling the direction and speed of the aircraft by simple control lines to the canopy. The carriage is supported by at least two support lines which are secured at attachment points spaced apart laterally with respect to the fore and aft direction of the craft. By ensuring that the support lines are of different lengths a side-to-side suspension bias is created which compensates for the propeller torque reaction. This is a permanent adjustment which allows the aircraft to be balanced so that control of flight may be effected without difficulty. Preferably, the carriage is constructed to use a longitudinal base strut on which a foldable tricycle under carriage is mounted. An upright strut is pivotally mounted to the base strut. The frame of the pilot's seat is used as an integral structural member which rigidly links the base strut to the upright strut in the running condition. The two struts and the sear frame form a triangle.

Abstract: A lightweight, low cost, powered launch vehicle for carrying a hang glider aloft and releasing the glider for free flight provides an integral glider support frame for positioning the glider in flight-ready configuration and a selectively actuatable release device accessible to the glider operator for separation from the vehicle at a desired altitude. The support frame positions the glider so that the wing of the glider provides added lift to the launch vehicle during combined flight.

Abstract: An ultralight aircraft having a generally rectangular, swept-back, single-surface wing. The wing, which is formed by fabric mounted on exposed spars and ribs, has a reflex profile to provide pitch stability which is further augmented by horizontal stabilizers projecting rearwardly from the wing adjacent the tips. Roll and yaw control are provided by a pair of rudders pivotally mounted at each wing tip. The forward ends of the rudders pivot inwardly to alter the magnitude of the wing's lift. The rudders pivoted simultaneously act as spoilers and speed brakes controlling the rate of descent. Pivoting one of the rudders individually moves the center of lift for one wing inwardly and increases the drag of that wing to roll the aircraft into that wing. The rudders tilt upwardly and outwardly in a dihedral configuration to provide roll stability. Stationary end plates mounted at each wing tip adjacent the rudders provide yaw stability.

Abstract: An ornithopter which is propelled upwardly and forwardly by means of flapping wings, similar to the flight of a bird or bat. The power is supplied by a small engine that is mechanically-connected to a hydraulic pump which drives a single hydraulic cylinder and utilizes only the retraction stroke to power both wings simultaneously downwardly. The wings are brought back to the normal position by an elastic device, which in addition will not permit the wings to go beyond optimum positions. A double-acting hydralic cylinder is also provided to move the horizontal tail in an up and down motion. The operation of the wings can be automatic or manually-operated by the pilot. The rear legs and front support are constructed in such a manner that allows the ornithopter to rise and land vertically which permits takeoff and landing from most any type of terrain. The ornithopter can be assembled and disassembled quickly.