Abstract: An inflatable bladder is placed between the wall of an aircraft inlet duct nd the liquid fuel to reduce the potential damage caused by hydrodynamic ram effects from a projectile penetrating the fuel tank. The inflatable bladder is inflated by a regulated gas source prior to combat. The inflatable bladder may be formed as a double layered section of a rubber bladder fuel cell type fuel tank, or an inflatable bladder may be bonded to the inner surface of an integral fuel tank wall.
June 6, 1983
Date of Patent:
December 12, 1989
The United States of America as represented by the Secretary of the Navy
Abstract: Greatly reduced cost of extraterrestrial transporation of strong items and materials is obtained through the use of impact into a crash-capturing-containing facility for deceleration. Cargoes from both the Earth and Moon can be cheaply crash-transported to a low earth orbit crash-load-capturing-satellite so that the satellite maintains a somewhat constant low earth orbit. By crash-capturing only lunar materials, the crash-containing satellite can also become a cargo-transporting satellite that travels from low earth orbit and delivers a much greater quantity of materials to a higher earth orbiting station that it started with. By crash-capturing only retrograde highly elliptically orbiting lunar material, that cargo-transporting satellite can be moved from a high earth orbit back to a low earth orbit.
Abstract: A drive mechanism for power boats having an inboard motor and a stern drive propeller mounting. The device includes a gimbaled propeller shaft housing located outboard of the transom. A gear pair mounted within the propeller shaft housing provides a lower propeller shaft relative to the hull of the boat without requiring a greater propeller shaft angle relative to the hull and without requiring a lowered inboard motor position.
Abstract: An aircraft having a rotatively driven blade cooperating with an electrochemical power system for operating an electric drive system. The blade provides cooling heat transfer relative to the lithium/peroxide fuel system effecting desirable separation of the lithium-hydroxide monohydrate in a suitable filter/plenum provided as a portion of the power system. In one form, the cooling is effected by disposing a heat transfer portion of the power system in the path of air flow generated by the propulsion blade of the aircraft. In another form, the cooling is effected by flowing the electrolyte through the propulsion blade. Molarity of the electrolyte is maintained by separating the precipitated lithium-hydroxide monohydrate in solid form in the filter/plenum and addition of replacement hydrogen/peroxide solution from the reservoir thereof.
Abstract: A method of applying and controlling vortex lift to a unique high-lift airfoil (29) is described wherein the planform of the airfoil (29) comprises a swept-forward outer panel (31) and a swept-aft or unswept inboard panel (33). A leading edge vortex (37) is formed on (31) and attached flow is maintained on (33). The attached flow on (33) causes the vortex (37) of the airfoil (29) to turn downstream and also induces axial flow along axis of vortex (37). Both of these results serve to delay vortex burst. A high-lift trailing edge device (45) such as a mechanical flap as the circulation control concept will induce a high leading edge flow angularity and cause the vortex (37) to grow in strength, thereby increasing vortex lift. The vortex (37) replaces the high-weight, high-lift leading device that would otherwise be required.
Abstract: One or more spinning flywheels are adapted to despin or partially despin a rotating mass such as a satellite and to convert the rotational energy into heat or electrical energy. The flywheels have one degree of freedom, parallel to the satellite, spin axis. This one degree of freedom allows the flywheel to precess in the manner of a gyroscope. As the flywheel precesses it turns a shaft which drives an electrical generator which produces electrical power that can be taken out of the despin device to drive external electrical devices that will disperse the rotational energy in the form of heat, light or electrically driven chemical changes. The flywheels exchange rotational energy after the spin vector of the spinning flywheel becomes congruent with the spin vector of the spinning satellite, thereby allowing the energy extraction process to be repeated. Bearing loss makeup energy is restored to the spinning flywheel system by feedback from the extracted satellite rotational energy.
Abstract: An adjustable support assembly for an aircraft leading edge guide track. The support assembly includes an upper portion pivotally connected to the guide track, and a threaded shaft having a rotatable member threadably engaged thereto which extends through the top of a trunnion housing. The rotatable member includes a shoulder portion which is disposed beneath the trunnion housing, and which is engaged by a wedge member therebelow to support the slat track via the shaft. Rotation of the rotatable member along the shaft adjusts the height of the guide track. The wedge member is supported by a horizontal shaft connected to the aircraft wing and to the housing. The wedge member includes opposing side portions which extend downwardly and inwardly, and which are engaged by complementary surfaces of locking tubes disposed about the horizontal shaft.
Abstract: An orbiting satellite system includes an asymmetrically deployed antenna and two deployable solar cell arrays. The solar cell arrays are deployed to a location which compensates for the asymmetry of the antenna so that the resulting station keeping thruster torques balance. Also, the system surfaces may be configured and the arrays so deployed to balance solar pressure torques on the system.
Abstract: An aircraft door having an electrically operated latching device (601) engaged only when electrical power is applied. Latch logic permits release by actuation of a switch (603) on the pilot's panel, by loss of electrical power (602), by a knob on the control cabin side (605) OR by a key from outside the control cabin (604). The aircraft door controlled by the electrically operated latching device (601) further includes a decompression override mechanism (606).
November 28, 1984
Date of Patent:
July 21, 1987
The Boeing Company
Royce F. Church, Donald B. McCaffrey, Leo W. Plude
Abstract: A free fall escape vehicle has surfaces of a deceleration structure that decelerate the vehicle upon entry into the water at a rate no greater than 4 g to 10 g by progressively increasing in area towards an escape vessel of the vehicle. In one form, the deceleration structure is circularly symmetrical normal to its axis, which can be approximated by a series of spaced-apart shells, each shell being a zone of a sphere the center of curvature of which is at or above the center of gravity of the escape vehicle; the condition can also be approximated by truncated sections of right circular cones. An escape vehicle similar to a lifeboat has a wedge-shaped deceleration structure with the sides of the wedge paralleling the fore-and-aft axis of the vessel, the structure can be approximated by a series of right circularly cylindrical shells or flat plates both having an effective center of curvature at or above the center of gravity of the vehicle.
Abstract: The control system includes a schedule (54) which plots airspeed versus stabilizer angle for a trim condition. Following a pilot adjustment of the stabilizer angle to establish trim, the schedule (54) plots the trim airspeed to obtain a stabilizer angle value. A change in airspeed from trim is sensed by a sensor (52) and the schedule (54) plots the new airspeed on the same graph to obtain a new stabilizer angle value. The schedule (54) determines a change in stabilizer angle signal in the form of increments of movement of the stabilizer control actuator (28) to return the stabilizer (18) to a trim condition. A schedule (40) in the system also senses any change in the rate of change of altitude from trim and computes from this change a second signal in the form of increments of actuator movement. There is an algebraic summation of these two signals and a stabilizer angle feedback signal to produce a command signal.
Abstract: A modular structure formed of components which when assembled define the basic chassis of a land, sea, or air vehicle, to which chassis is attachable a body which may be a fuselage or hull in a selected configuration to create the desired vehicle. The structure consists of substantially identical front and rear cradles joined to opposing ends of a floor tray. The use to which the cradles are put depends on the nature of the vehicle, so that in the case of a land vehicle, wheel suspension fixtures are bolted to the cradles to support the wheels depending on the nature of the vehicle. Overlying the floor tray and secured thereto is a safety capsule, the capsule acting as a truss for the chassis and functioning as the cockpit section of a body which, in the case of an automobile, is completed by a front body section secured to the front cradle and a rear body section secured to the rear cradle.
Abstract: A boat and propulsion system especially useful for shallow water operation. A boat, such as a flat bottom fishing boat, is provided with a lowered transom and a platform attached to the transom which extends upwardly at an angle along the sides of the boat to define a well area which receives and drains any backwash. An air cooled internal combustion engine is provided with a straight propeller shaft and propeller attached thereto. A motor plate rigidly attached to the engine may be removably mounted on a swivel-hinge assembly mounted on the platform to allow double axis movement of the engine and propeller in relation to the platform. This provides for a thrusting position with the propeller in the water and a neutral position with the propeller held above the water. A control handle may be removably connected to the motor plate to provide one handed steering and throttle control by the operator.
Abstract: A motor-driven marine propeller is disclosed for propelling a marine vessel. The propeller includes a hub member driven by the motor and a can member disposed coaxially relative to the hub member the can member having a fore and an aft end. The hub member and the can member define therebetween an annular port for the passage therethrough of a portion of the exhaust generated by the motor. Supports extend between the hub member and the can member for supporting the can member coaxially relative to the hub member and a plurality of blades are secured to and extend from the can member with each of the blades being equidistantly spaced relative to each other. Each of the blades defines a leading and a trailing surface such that the propeller rotates in a direction from the trailing towards the leading surface in normal forward motion.
Abstract: A supercritical movable airfoil over which is blown air to obtain a Coanda affect. A sealing strip is provided on a stationary airfoil portion which seals against the movable airfoil portion during blowing to prevent flow of air therebetween.
Abstract: An earth orbiting satellite (10) having an interior portion (22) supporting heat generating elements (26) and an exterior portion (12) having a thermal radiator (20) for heat radiated by these elements, is provided with reflectors (34s, 34c) in the annulus between the interior and exterior portions, the reflectors being configured to reflect radiation from the axially extending side surfaces of the heat generating elements to the thermal radiator and to conduct heat from the heat generating elements and radiate the conducted heat to the thermal radiator.
Abstract: A replaceable tip for an aircraft leading edge and which has a metallic abrasion shield glove removably mounted to the leading edge of the aircraft, fasteners for securing the abrasion shield glove to the leading edge of the aircraft, and a non-metallic resilient cushion insert fixedly attached to the abrasion shield glove so that the resilient cushion insert forms a dampening arrangement which reduces the amount of damage to the aircraft leading edge when the replaceable leading edge tip is hit.
Abstract: A method is disclosed for exchanging a payload module on a satellite comprising a control module and a detachable payload for a new payload module in the STS or space shuttle orbiter using one RMS or remote manipulator system. In the method after the space shuttle orbiter is placed near the satellite the RMS rotates the new payload in a position to present the control module attachment end away from the cargo bay. The RMS then captures the satellite and positions it in the cargo bay of the orbiter adjacent the new module with the control module facing away from the cargo bay. The control module is moved to the new payload module and the assembly deployed in space away from the space shuttle orbiter.
Abstract: A minimum weight horizontal and vertical stabilizer (188) which a primary torque box is formed within the skins (202, 204) and extends transversely from the most forwardly spars (190, 212) to the most rearwardly spar (196) to occupy spaces between all of the spars (190, 212, 192, 194, 196).
Abstract: Apparatus for adjustably mounting an ejection seat (16) in an aircraft in which outer catapult cylinders (58, 60) support inner catapult cylinders (62, 64) and supply force to the inner cylinders to eject the inner cylinders and the seat from the aircraft, the inner cylinders being connected to an upper rear end of the seat (66, 68). The seat (16) is supported in the aircraft by the inner and outer catapult cylinders (62, 64, 58, 60), by adjusting actuators (40) to raise and lower and to tilt the seat forwardly and rearwardly, by lower anchor links (30) pivotally connected to the aircraft and to lower end (26, 28) of the outer catapult cylinders and to the actuators (40), and by upper links (50). The seat is connected to the catapult cylinders (58, 60) by slipper blocks 82. The slipper blocks (82) are pivotally connected to the seat by pins (84) and are slidably engaged with the outer catapult cylinders.