Abstract: A non-lethal projectile includes a projectile body; a fuze disposed in a rear of the projectile body; an expelling charge disposed adjacent the fuze; a wad disposed adjacent the expelling charge; a dense powder ballast disposed adjacent the wad; a non-lethal payload disposed adjacent the dense powder ballast; and an end cap disposed on a front end of the projectile body; wherein the expelling charge expels the dense powder ballast and non-lethal payload and reduces the forward kinetic energy of the projectile body and the fuze to one of a near non-lethal or non-lethal level such that as the projectile body and the fuze travel from a burst point to a target impact a residual kinetic energy of the projectile body and the fuze is non-lethal.

Abstract: The present invention is structured such that lift control apparatus such as flaps and flaperons operate in association with elevator operation performed by a pilot. Lift control conforming to elevator operation by the pilot is performed.

Abstract: An ejection escape system for passenger airplane that there is a locking mechanism at the connection of the left top cabin cover, the right top cabin cover with the airplane body, there is also a locking mechanism at the connection of the left top cabin cover and the right top cabin cover, the passenger seat is an ejection escape seat, the switches for the locking mechanism and the ejection escape seat are installed in the cockpit, where the pilot can turn on the locking mechanism switch to open the left and right top cabin covers and turn on the ejection escape switch to eject the seat out of the airplane through the opening of the left and right top cabin covers.

Abstract: A pivoting power transmission unit is provided for transmitting rotational drive from a power source to a rotor configured to revolve about a first axis and configured to swivel about a second axis perpendicular thereto. The transmission unit comprises: input pinion driven in rotation by the power source; two contra-rotating gearwheels which mesh with the input pinion and are co-axially mounted along the second axis; two cylindrical intermediate pinions, each joined to rotate co-axially with a respective one of the two gearwheels; and a further gearwheel in meshing engagement with the intermediate pinions. The further gearwheel drives in rotation an output shaft linked to the rotor.

Abstract: A drag damper for use on a rotary wing aircraft rotor comprises a body defining two variable volume chambers linked by a piston. The chambers are filled with fluid and are connected by a restriction port (35) and by a channel (32) of larger cross-section than the restriction port. A secondary piston slidable and pressure-tight piston is fitted in the channel and loaded by an elastic bias (34). The equivalent mass of this secondary piston (33) and of the fluid which it displaces, and the stiffness of the elastic bias (34) are such that the secondary piston is resonant in the channel (32) at the rotation frequency of the rotor, to filter the dynamic component at this frequency of stresses applied to the damper (20).

Abstract: Guidance of a gliding vehicle is disclosed. A method of the invention allows the range of the glide phase of a gliding vehicle to be maximized, while satisfying final flight path angle and aimpoint requirements. The method controls the time-of-flight of the gliding value to a desired value. The time-of-flight control can correct for winds, off-nominal launch conditions, and rocket motor variations, among other factors. Both time-of-flight control and range and cross-range maximization can be achieved by the inventive method, utilizing a compact closed-loop approach.

Abstract: There is provided a store ejection system, store, and method for mounting a jettisonable store on an aircraft. The system uses a pressurized non-pyrotechnic fluid from a pressure vessel integral to the store and sealed by a releasable seal as the source of energy and the transfer mechanism. An actuation system includes an accumulator for receiving and storing the fluid from the pressure vessel, a dump valve for controlling a flow of the fluid from the accumulator, and a controller for actuating the dump valve to an open position in response to a control signal to jettison the store. The seal is configured to hermetically seal the pressure vessel before the actuation system is connected to the pressure vessel, and the actuation system is configured to be fluidly connected to the pressure vessel upon release of the releasable seal.

Abstract: A kite in the shape of an aircraft having one or more wings. The number of wings can vary due to novel V-shaped connection members employed together with strut rod members cut to predetermined lengths. The connection members are preformed V-shaped connectors slidably mounted to spar members disposed in open-ended sleeves in the leading and trailing edges of a wing and may be oriented to receive strut members form either above or below the wing, for efficiency manufacturing, ease in assembly, and minimum exposure to breakage during operation, storage and transport. Additional connection members may be added to the spar members to receive strut members connected to additional wings thereby allowing for an airplane kite having one wing, two wings, three wings, or more. Multiple-V connectors may be combined to create hubs for propellers or wheels that rotate when they encounter a front wind. Ram air openings are utilized in the fuselage of the kite to maintain the shape of the fuselage and the angles of wings.

Abstract: An aircraft including a fuselage, a compound tilting wing (CTW) and aircraft engines mounted on the aircraft. The CTW includes a leading edge wing portion and a tilting main wing portion. The leading edge wing portion and the tilting main wing portion each include a leading edge, a trailing edge, a chord, a lower surface and an upper surface. The tilting main wing portion is pivotally mounted on the fuselage for rotation from a cruise flight position to various low flight speed positions. In the cruise flight position, the tilting main wing portion fits conformably with the leading edge wing portion forming an aerodynamically single wing. In one embodiment, two aircraft engines are mounted on a fixed leading edge wing portion and two aircraft engines are mounted on the tilting main wing portion.

Abstract: A deorbiting spacecraft includes a grabber for grabbing an orbiting debris object in space and a deorbitor for deorbiting the debris object. The grabber includes inflatable fingers with loop eyes for bending inflated fingers around and to grab the space debris object using controlled motors and tension lines. The deorbitor is a dragsphere for deorbiting low earth orbit debris objects into the atmosphere for burn up, or is a surface for collecting solar wind for pushing the debris into an outer disposal orbit, or is a thruster for transorbiting a high earth orbit debris object to an outer waste orbit.

Abstract: An apparatus for releasably attaching all stands or risers of a parachute canopy to a parachutist includes two interlocking plates. The plates incorporate a fulcrum, lever, and alignment tabs, which decrease the amount of force required by the parachutist to release the canopy and hold the plates in position.

Abstract: A system for deployment of a vacuum-packed inflatable structure includes a primary cylinder with a primary valve that can be opened under a primary applied force for discharging a primary pressurized fluid into the inflatable structure. A first connecting arrangement extends between the primary valve and an inflatable actuator bag. A secondary cylinder has a secondary valve movable under a secondary applied force for discharging a secondary pressurized fluid into the inflatable actuator bag. With this arrangement, application of the secondary force to the secondary valve causes the secondary cylinder to inflate the inflatable actuator bag. This in turn causes the first connecting arrangement to open the primary value with the primary applied force and inflate the inflatable structure.

Abstract: A fireset for a low energy exploding foil initiator (LEEFI) comprises a first capacitor for storing a level of electrical energy sufficient to fire the LEEFI, the first capacitor being in electrical communication with the LEEFI, second and third capacitors in electrical communication with the first capacitor for storing lesser levels of energy than is stored by the first capacitor, a diode in electrical communication with the capacitors for limiting charging of the second and third capacitors, and first and second resistors providing isolation among the capacitors. A trigger directs a pulse of electrical energy to a high speed switching transistor adapted to receive the pulse from the trigger and, in response there to, to dump the third capacitor. The third capacitor dumps through a silicone controlled rectifier to short the second capacitor to ground, to decrease the level of energy stored by the second capacitor.

Abstract: The invention relates to a detent for a handgun, comprising at least one sensor for determining the identity of the user on the basis of at least one finger. According to the invention, a sensor determines the capacitance between a sensor surface and a section of the finger, an image of the finger section is generated from the voltage differences and said image is compared with memorized finger sections.

Abstract: Apparatus for separating aerodynamic objects from an aerodynamic vehicle includes a first element, aerodynamically configured to create nose-down pitching moment, mounted to the object surface, a second element mounted to the first element and projecting into an oncoming airstream such that when enabled, the passing air tears the apparatus from the surface which otherwise supports it. The first element is a body designed to be conformal with the object surface to which it is mounted, and includes a forward end projecting into the oncoming airstream and a rearward end, and is secured to said object surface at the rearward end thereof. A flexible gasket is interposed between the first element and the object surface. The second element comprises a forward end directed toward the oncoming airstream and a rearward end, with the second element being mounted to the first element at the rearward end of the second element.

Abstract: A forebody 10 for an aeronautical vehicle 12 is provided. The forebody 10 includes an exterior wall 14 having a first half 16 and a second half 18. The first half 16 has a first porous section 20 and the second half 18 has a second porous section 24. The first half 16 and the second half 18 also have a first exterior side 22 experiencing a first fluidic pressure and a second exterior side 26 experiencing a second fluidic pressure, respectively. A hollow inner cavity 28 is fluidically coupled to the first exterior side 22 and the second exterior side 26 and allows fluid passage between the first exterior side 22 and the second exterior side 26 through the first porous section 20, the inner cavity 28, and the second porous section 24. The exterior wall 14 equalizes the first fluidic pressure with the second fluidic pressure. Additional forebodies and methods for performing the same are also provided.

Abstract: A locking hinge especially used in a folding shoulder rest for paintball guns. The locking hinge comprises a first hinge plate and a second hinge plate in relative rotation. The first hinge plate has a hinge joint axis, a plurality of symmetric mounting holes, and a counter bore for receiving the locking mechanism. The counter bore in the first hinge plate contains a spring and a locking cylinder. The locking cylinder has a taper on the end directed toward the second hinge plate. The second hinge plate has a relative hinge joint axis, a plurality of tapered circular cavities or notches, and a means for symmetric mounting. The locking mechanism sufficiently aligns with the tapered circular cavities or notches at plurality of predetermined positions thereby preventing rotation of the hinge plates. A minor misalignment between the locking mechanism and tapered circular cavities further provide rigid locking of the hinge plates.

Abstract: The present invention relates to a method and a device for handling artillery shells (14-16) when loading artillery guns (1) that have an integral shell magazine (9) fixed in the traverse system but independent from the elevating mass, which magazine on command feeds out shells (14-16) one by one with a specific linear velocity in the longitudinal axis of each shell. Each shell is subsequently transferred to the loading position for the gun by a loading pendulum (13) and cradle (6). The basic idea behind the present invention is that the outfeed velocity of the shells (14-16) from the magazine (9) shall be braked to zero in a brake module (12) mounted on the gun while they lie in a shell carrier (17, 18) mounted on the loading pendulum (13).

Abstract: A mushrooming bullet having a highly improved performance in the retention of the lead core within the bullet jacket subsequent to impact, and in performing effectively over a substantially wider velocity range, the bullet retaining its lead core within its jacket substantially 98-100% of its firings at high velocities, and mushrooming more effectively at lower velocities than conventionally manufactured bullets. The jacket is characterized by a base portion which has a substantially larger interior diameter than its shank portion, and a mouth portion which is substantially softer than its shank portion. The mushrooming of the nose portion of the core and the mouth portion of the jacket is effectively arrested by the harder thick shank portion when the bullet strikes a target, and thereby minimizes the loss of lead from the core.