Abstract: A slip control system for a motor vehicle controls slippage of driving wheels and includes, a sensor for detecting a slip ratio of each driving wheel, a device for detecting a reduction in speed of each wheel, and a traction control system for decreasing a slip of each driving wheel by controlling brake fluid pressure in each driving wheel so that the slip ratio of each driving wheel is at least equal to a predetermined desired slip ratio when the slip ratio of each driving wheel becomes equal to the desired slip ratio. The system further includes an antiskid brake system for controlling brake fluid pressure, based on the reduction speed of each wheel, so as to cancel a lock condition of the wheel.

Abstract: A four wheel drive system for a vehicle comprises a transverse power unit, a first (front) differential unit, an angular drive unit for changing the direction of torque path, a propeller shaft, and a second (rear) differential assembly between left and right permanent drive (rear) wheels which are always connected with the power unit through the differential case of the first differential unit, the angular drive unit, the propeller shaft and the second differential assembly. The first differential unit is provided between left and right nonpermanent drive (front) wheels. One of the nonpermanent drive wheels is simply connected with one side gear of the first differential unit by an axle shaft. The other nonpermanent drive wheel is connected with the other side gear of the first differential unit through a coupling unit, such as an orifice coupling, which can vary a driving torque distribution between the front and rear wheels by varying a transmission torque therebetween.

Abstract: In the event of sudden depressurization caused by an explosion in an aircraft cargo compartment, a blast attenuation valve is provided in the aircraft's air channels to form a barrier to the passage of air between the cargo compartment and passenger cabin. The valve contains a mixture of compressible bodies through which air can normally permeate. After an explosion, the bodies block and blast wave by compressing together due to the substantial increase in pressure.

Abstract: An apparatus for securing elements to the wall of composite components has a holder which passes through an aperture of the composite component. The holder consists of a coupling part which is disposed on the side of the composite component to which access is difficult and also of an operating part which is disposed at the readily accessible side of the composite component. The actuating part and the coupling part are engagable with one another for the application of a rotary movement from the actuating part to the coupling part. The coupling part is couplable with a coupling counterpart of the element to be mounted which passes through the actuating part through mutual rotation and axial clamping of the coupling part, the wall, the actuating part and the element.

Abstract: A retractable lifeline safety device usable by workers performing tasks at great heights above the ground. The mechanical components of the safety device are contained within a sealed housing that is filled with a viscous fluid. The sealed housing prevents the introduction of dirt, moisture and other foreign matter into the mechanical mechanism of the safety device, reducing the likelihood that those components may be fouled by dirt and corrosion, which in turn could greatly reduce the effectiveness of the safety device. The safety device is attached to the structure on which the worker is performing the task, and a lifeline such as a cable is withdrawn from the housing thereof, the end of which is attached to a belt or harness worn by the worker. The cable may be easily drawn out of the housing in response to the worker moving about normally in the appropriate work space, and the cable is automatically drawn back into the housing of the safety device as the worker draws closer thereto.

Abstract: A wind driven craft comprising a body and a pair of wings extending therefrom. The wings are pivotally connected to the body of the craft. The wings provide lift and thrust to the craft such that it is able to move under influence of the wind.

Abstract: A cam actuator (12) for rapidly opening an aircraft door (14) that is attached to an aircraft fuselage (18) by a hinge assembly (26). The actuator includes a piston (40), a piston rod (42) that is secured to the piston and rotating sleeve (44) that is fitted over the piston rod that functions as the hinge pin between a hinge clevis (26) on the aircraft and a hinge arm lug (54) on the hinge assembly. The piston is contained within a housing (38) adapted to receive a pressurized pneumatic gas. An annular cam (50) through which the piston rod travels and that is formed with an outer surface (104) having a helical profile is attached to the hinge clevis. A cam follower (46) is attached for the sleeve so as to rotate in unison therewith. The hinge arm lug (54) is also secured to the sleeve (44) for rotation. When the actuator of this invention is triggered, the piston rod (42) urges the cam follower (46 ) against the cam (50) so as to cause the cam follower to rotate.

Abstract: An improved fighter aircraft has three primary lifting surfaces acting as wings on the airframe. The lifting surfaces are attached 120 degrees apart on the airframe so the fighter may turn in any direction without prior movements. The pilot has means to position himself to feel only positive g's in these maneuvers. A rotatable cockpit section, for example, moves independent of the airframe with the canard wings thereon. The pilot flies the cockpit section and the airframe with wings thereon responds accordingly.

Abstract: A method for controlling reorientation of a spacecraft's spin from a minor axis spin bias to a desired major axis spin after spin transition. A control system monitors rotational rates about the principal axes to detect a separatrix crossing of a polhode path therein. Controlled thruster firings resulting from spin rate information successively decrease and increase a characteristic parameter and capture the spacecraft during a spin transition to a desired major axis bias orientation. It is possible to monitor only .omega..sub.1 and .omega..sub.3 in an alternate embodiment.

Abstract: A control system for a vehicle such as an automobile comprises a device for storing data for determining a driver's age, a group of various sensors for sensing driver's operations and a controlling system which estimates a driver's characteristic from information supplied from the sensors, and which modifies a response characteristic of any one or more of steering system, brake system and accelerating system of the vehicle in accordance with the driver's age and the estimated driver's characteristic in order to make the vehicle easier for aged or unskilled drivers to control. When the driver is aged or unskilled, the controlling system advances the phase of the response characteristic.

Abstract: A space launcher and method for launching satellites and other payloads into space, comprising multi-stage rockets with payload wherein the ratio of the weight of any lower stage rocket to the weight of the rocket stage directly above it is less than two and a half, and wherein the weight of each rocket stage can be defined as that weight of the space launcher, at the start of firing of this stage, minus the weight of the rocket and payload of the stage directly above it at the time when the latter stage rocket begins firing.

Abstract: A STOL aircraft includes propfan engines which are each connected to a lower surface of one of the wings by a pylon. The propfan engine is located directly below the wing and are each equipped with fans at a rear portion thereof. A slat is connected to a leading edge of the wing and not divided by any object, including the pylon and the propfan engine.

Abstract: The present invention is drawn to an improvement in the configuration of an inner lining plate of an aircraft fuselage wall, which will result in the sound transmission loss (TL) of the inner lining plate to occur in a frequency range covering the frequencies of external noises such as propeller sound, such that external noises transmitted from the inside of the aircraft fuselage can be reduced. The improvement resides in that a tensile rigidity in the circumferential direction of a substantially cylindrical fuselage wall inner lining plate is less than the tensile rigidity in the axial direction thereof. In this respect, the inner lining plate is provided with a large number of parallel crests extending in the axial direction.

Abstract: The invention relates to friction pairs of machine parts.A friction element of a friction pair comprises a three-dimensional framework (1) embedded in a matrix (2) in the zone of the friction surface (4).The framework (1) is made from a wear-resistant material and the matrix (2) from a material with high heat conductivity coefficient. The framework (1) has a cellular shape formed by a honeycomb structure, a corrugated strip and the like. The framework rises partially above the surface of the matrix forming, together with the latter, a friction surface (4) possessing a regular microrelief. The area of the framework (1) rising above the matrix (2) diminishes proportionally in the direction from the maximum load zone towards the minimum load zone.The invention can be used in braking mechanisms, in particular in brake disks and drums of passenger cars, in disks of friction clutches and the like.

Abstract: According to the present invention, a rotation preventive portion for preventing the rotation of bead portion, such as a stepped projection, is provided on the bead portion of diaphragm, which is squeezed between a front shell and a rear shell. When the front shell and the rear shell are assembled with such a diaphragm, the rotation of the bead portion is prevented by this rotation preventive portion (stepped bead). As the result, outer lip of the bead portion of diaphragm or the rolling portion of diaphragm are not squeezed between the front shell and the rear shell, and the front shell and the rear shell can be assembled without damaging or breaking the diaphragm.

Abstract: A life parachute including a canopy formed of pieces of fabric sewed together, sheaths extending from the center of the canopy in a spoke-wise manner, and an inflatable envelope connected to a compressed gas container by way of a conduit. The inflatable envelope has a main body in the center thereof and legs extending spoke-wisely from the periphery of the main body; the legs and the main body are interconnected and inflatable. The number of legs is equal to that of the sheaths. The free ends of the legs are inserted into the corresponding sheaths and then secured onto the canopy so that the main body of the inflatable envelope can be maintained at the central portion of the canopy.

Abstract: A safety device for an aircraft inflatable escape slide which functions to prevent inadvertent inflation of the slide during shipping. The safety device incorporates a rotatable hook means which retains the firing lanyard in a fixed position and is adapted to release the firing lanyard when the slide pack covers are leased. A pair of swaged ball elements are provided on the lanyard, one on either side of the hook means.

Abstract: A jet engine fan nacelle which maintains attached flow during engine windmilling. The nacelle includes a cylindrical airfoil body having an inner surface. A plurality of vortex generators are positioned on the inner surface between the nacelle body's leading edge and its throat within ninety degrees of rotation from the crown line hilite about the nacelle's longitudinal axis. The vortex generators energize the airflow to maintain an attached flow around the leading edge and along the outer surface of the nacelle's body without separating from the outer surface which would produce an undesirable increase in drag.

Abstract: A shock absorber for damping the movement of the body of an automobile. The shock absorber includes a pressure cylinder forming a working chamber with a piston disposed therein. The piston has a plurality of flow passages extending therethrough. A first valve disk is located on one surface of the piston, while the second valve disk is located on the second surface of the piston. Finally, an electromechanical transducer is disposed adjacent to the first valve disk so as to permit control of flow of damping fluid through the piston.

Abstract: A reclining ejection seat (1) for an aircraft which includes an arm support (7) composed of two parts (8,10) which are moveable fore and aft. A first part (8) carries flying controls (9) and is adjustable for reach. A second part (10) which is adjustable for comfort, locates the elbow of a pilot (11) and supports his forearm. The arm support (7) permits the pilot (11) to maintain adequate control over his arm movements even when the aircraft is carrying out very high speed maneuvers.