Abstract: A method and system for use as a modeling tool accurately estimates propellant remaining aboard a spacecraft at the completion of a transfer orbit by iterating mass flowrate in a linear optimized fashion until the difference between a predicted .DELTA.V and observed .DELTA.V is minimized. Actual flight pressure telemetry data is used to calculate a corresponding mass flowrate which must have been produced by a liquid apogee motor (LAM) for the spacecraft to reach the desired position. A thruster specific impulse value (ISP) is derived from ground test data to allow computation of the amount of propellant consumed during transfer orbit. When this value is subtracted from the known initial propellant load, the propellant remaining at the beginning of life (BOL) of a satellite can be calculated.

Abstract: An aircraft engine vibration analysis system is provided with at least one vibration sensor disposed proximate an aircraft engine. The analysis system is further provided with a vibration analysis module for receiving an input from the vibration sensor and generating an output representative of vibration characteristics of the aircraft engine. The analysis module is provided with a multiple pin input port which is connectable to the vibration sensor. The analysis module is further provided with test sequence select circuity which is in electrical communication with the input port for implementing an appropriate vibration analysis sequence in response to measured conductivity between pins of the multiple pin input port. The analysis system is further provided with a sensor connecting cable which is connectable to the vibration sensor and the analysis module input port.

Abstract: A propeller (10a) comprising a plurality of propeller blades (9a) each having a root end (11a) attached to the central propeller disc or hub (12a), an intermediate portion (13a) extending from the root end (11a) and having a generally aerofoil cross section extending chordwise between a leading edge (14a) and a trailing edge (15a), and the blade (9a) having a tip (19) at an end of the intermediate portion (13a) remote from the root end (11a), the tip (19) having a leading edge portion (20) extending forwardly from a junction (21) with the leading edge (14a) of the intermediate portion (13a) thus to provide a discontinuity or notch (25) in the leading edge (14a) of the blade (9a) at the junction (21).

Abstract: A system for fastening aircraft assemblies is disclosed. The system comprises a first wing clip (10) having an anchor plate (12) with at least one ear (20) for affixing to a first assembly (16); a second wing clip (11) having an anchor plate (14) and at least one ear (20) for affixing to a second assembly (18); and a fastener (44) for joining the first wing clip (10) to the second wing clip (11).

Abstract: A golf bag includes a bag body and a base disk mounted onto the bottom of the bag body. The base disk is provided with two wheel seats each receiving a wheel and at least one leg, whereby the golf bag can be stably placed on the ground to be in a standing condition. If required, a handle can be provided at the upper end of the bag body, on a side above the wheels such that the golf bag can be slanted and moved when users grasp the upper end of the bag body or pull the handle in order to move the wheels.

Abstract: A snow board comprising a flexible core element enveloped by a covering of resin impregnated fiberglass wherein the core includes a plurality of parallel grooves running the longitudinal direction of the board such that in conjunction with resin impregnated fiberglass form a series of parallel integral hollow beam members increasing the strength of the board while simultaneously reducing the overall weight

Abstract: An indicator for determining brake stroke condition on a vehicle braking system comprising: a bracket having an elongated member having at one end an attachment portion located generally at a right angle radius to the elongated member, the bracket mounted to a chamber mounting bracket which supports a brake chamber, the bracket chamber having a clevis assembly including a clevis pin which connects the clevis assembly to a brake arm; a continuous slot extending along the length of the elongated member, the elongated member running parallel to the clevis assembly; and a second bracket detachably mounted to the continuous slot along the elongated member the second bracket having a base and two extending members from the base; the position of the extending members being a predetermined distance from the clevis pin thereby indicative of the brake stroke condition on the vehicle braking system.

Abstract: The bleed air requirements for a pressurization and environmental control system for the cabin (10) of an aircraft may be reduced by a system that includes a turbomachine (20) having a rotary compressor (22) driven by a turbine wheel (26). A ram air inlet (16) is connected to the compressor inlet (28) and the aircraft is provided with a cabin air exhaust port (18) which is connected to the outlet (34) of the turbine wheel (26). A heat exchanger (40) has a cabin inlet air flow path (42) and a cabin outlet air flow path (44) in heat exchange with one another. The cabin inlet air flow path (42) is connected to the outlet (30) of the compressor (22) and to the cabin (10) of the aircraft. The cabin outlet air flow path (44) is connected to the cabin (10) as well as to the inlet (32) of the turbine (26).

Abstract: A binding for snowboards has a back plate 2 at the rear of a base plate 1, and the back plate 2 is moved back and forth to vertically move side plates 3 which are provided with an ankle strap 32 and a toe strap 33.

Abstract: An apparatus and method for aerial refueling of an unmanned aerial vehicle (UAV) wherein a laser receiver/transmitter on a target device towed by a host aircraft projects a reticle pattern aft of the host aircraft and a laser receiver/transmitter on a probe of the UAV is activated as the UAV is moved within the projected reticle pattern. Thereafter, a rangefinder guides the UAV towards the host aircraft until the laser transmitter/receiver of the UAV is aligned and boresighted with the laser transmitter/receiver of the host aircraft at which time the mode of the laser transmitter/receiver of the UAV alternates between a rangefinder mode and a modulation data link mode to transmit vital information concerning the UAV to the host aircraft. The probe on the UAV continues to move toward the drogue until the probe establishes contact within a receptacle structure of the drogue and is coupled thereto.

Abstract: A method for designing a non-waisted fuselage for supersonic wing/fuselage configurations that increases the fuselage volume and improves the supersonic aerodynamic performance compared to a conventional waisted-fuselage configuration. The method entails removing the waisted region of an existing waisted-fuselage configuration by linearly reconstructing cross-sections between the endpoints representing the waisted cross-sectional area portion to create a modified fuselage configuration without waisting. This configuration will have increased fuselage volume and improved supersonic aerodynamic performance. The fuselage camber can then be optimized using non-linear aerodynamic methods to further increase the supersonic aerodynamic performance.

Abstract: A collapsible seat device having a framework that allows the seat to be easily developed and collapsed, having an upper end portion of the front leg 13 connected with a front portion of the armrest member 21 by means of the hinge 23, and an upper end portion of the rear leg 25 connected with a center with respect to the longitudinal direction of the armrest member 21 by means of a hinge. A push rod 9 is connected with a rear portion of the armrest member 21 by means of the hinge 27. A lower end portion of the push rod 9 is connected with an upper end portion of the rotary member 29 by means of the hinge 31. A lower end portion of the rotary member 29 is connected with the rear leg 25 by means of the hinge 33. The other end portion of the connecting member 35 connected with the front leg 13 by means of the hinge 37 is connected with a substantial center of the rotary member 29 by means of the hinge 39. This configuration allows the collapsible seat device to be made compact after it has been collapsed.

Abstract: A mud flap extender for mounting on the rear quarter panel behind each rear wheel or wheels of a truck or other vehicle and suspending a mud flap a sufficient distance rearwardly of the wheel(s) to prevent the wheel(s) from engaging the mud flap and tearing the mud flap from the vehicle frame when the vehicle is operated in reverse. Each mud flap extender is characterized by a fender module that matches the curvature of the vehicle rear quarter panel and typically mounts on the wheel well plate of the rear quarter panel and an angle-iron mount plate having a top flange for engaging the fender module and a bottom flange for mounting a mud flap which is suspended downwardly from the fender module in spaced relationship with respect to the rear wheel or wheels of the vehicle.

Abstract: A method for automatic resetting of a timer according to the exit time when an item starts descending from a flying object. The resetting is based on a number of altitude values, which are continuously measured by performing air pressure measurements or position measurements. Furthermore, a microprocessor based apparatus implementing said method is described. The timer can be used for activating an external mechanical or electrical apparatus e.g. a canopy or an audible warning device.

Abstract: An aircraft for transporting passengers is provided having a raised and rearward positioned cockpit. The aircraft preferably has an elongate main body including a passenger compartment positioned in a forward end of the main body and a passenger window extending across the forward end of the main body for forward viewing by passengers positioned in the passenger compartment. The passenger window preferably extends substantially the entire height of the passenger compartment of the main body, the entire lateral extent of the forward end of the passenger compartment of the main body, and into forward side peripheries of the passenger compartment of the main body to thereby define a panoramic-type viewing window for passengers positioned in the forward end portion of the main body. A plurality of wings are connected to and extend outwardly from the main body. A tail is connected to a rearward end of the main body.

Abstract: In order to be able to install in juxtaposed manner several satellites beneath the nose cone of the same launcher without any collision risk at the time of their separation, between each satellite and the support plate is positioned an adaptor. During launch, the adaptors occupy a size-limiting carriage position. When it is wished to control the separation of a satellite, its adaptor passes into a separation position, in which the satellite is tilted or swung away from the neighbouring satellite or satellites.

Abstract: The balloon basket (1) according to the invention essentially comprises several pneumatic elements: an upper ring (2) and a lower ring (3), both advantageously segmented, are joined by a number of struts (4). The number of these struts (4) preferably corresponds to the number of corners of the polygonally formed rings (2, 3) and the number of their segments. Between the rings (2, 3) and the struts (4) side wall elements (5) are arranged so that they--apart from the holes (7) made in them--tightly seal the balloon basket (1) at the sides. In the lower ring (3) is fitted a floor (6). Side wall elements (5) and floor (6) are made with double walls and comprise at least in part of distance fabric such that the two corresponding walls of the side elements (5) and the floor (6) are held together by a plurality of threads and therefore retain their flat form on inflation with compressed air.

Abstract: This is a hydraulic anti-vibration mount intended to be interposed between a vehicle body and an engine and in particular comprising an armature which can be secured to the body, a head which can be secured to the engine, a thick frustoconical wall linking a circular bearing surface of the armature to the head and defining with the latter a working chamber, and a diaphragm defining with the armature a compensation chamber which communicates with the chamber via a restricted passage. An active attenuation device is also provided, the device comprising a piston immersed in the working chamber, a member for exciting this piston and an electronic circuit for controlling this excitation member. The armature forms on the one hand a double pan constituting the ends, arranged side by side, of the two chambers and on the other hand a housing containing side by side the excitation member and its electronic control circuit.