Abstract: An aircraft is provided including a fuselage with a drive shaft in the fuselage, in which the drive shaft drives an aerodynamic generator consisting of an aerodynamic rotor which is attached to the shaft and an aerodynamic stator which is attached to the fuselage over the rotor. A control device which is responsive to control commands is attached to the fuselage and has an actuator for controlling the aerodynamic generator. The aerodynamic generator produces an aerodynamic force in response to the commands whose intensity, direction and sense of direction can be controlled through the control device, in which vertical lifting and landing are achieved by orienting the direction and sense of direction of the aerodynamic force vertically with respect to the horizon plane.

Abstract: A device for the attachment of an aircraft engine to a strut comprises a main attachment structure (18, 24) able to transmit normally to the strut forces exerted in two directions (X′, Y′), whereof one is mainly parallel to the longitudinal axis (OX) of the engine and the other mainly perpendicular to said axis and to a median plane common to the engine and the strut. The device also comprises an emergency attachment structure essentially constituted by an element (10) fixed to the strut and also forming part of the main attachment structure. The element (10), preferably implemented in the form of two coupled together parts (10a, 10b), comprises a pin (42) penetrating with clearance a recess formed on the aircraft casing (C).

Abstract: Mach's principle and local Lorentz-invariance together yield the prediction of transient rest mass fluctuations in accelerated objects. These restmass fluctuations, in both principle and practice, can be quite large and, in principle at least, negative. They suggest that exotic space time transport devices may be feasible, the least exotic being “impulse engines”, devices that can produce accelerations without ejecting any material exhaust. Such “impulse engines” rely on inducing transient mass fluctuations in conventional electrical circuit components and combining them with a mechanically coupled pulsed thrust to produce propulsive forces without the ejection of any propellant. The invention comprises a method of producing propellant-less thrust by using force transducers (piezoelectric devices or their magnetic equivalents) attached to resonant mechanical structures.

Abstract: An automatic and sequencing pneumatic actuation assembly is provided for use in an ejection system capable of unlocking and forcibly ejecting stores from racks mounted on an aircraft or similar weapon carrier. The actuation assembly including a primary valve and release ram for reciprocating movement along a common longitudinal axis between closed and open positions. A solenoid control valve initiates movement of the primary valve by creating a pressure imbalance across the primary valve. Pressurized gas is caused to vent to an environment having a pressure lower than the pressurized gas, allowing the primary valve to move the release ram into engagement with a mechanism capable of unlocking the hooks before moving ejector pistons to forcibly eject the unlocked stores. A bias member is provided for automatically returning the primary valve to the closed position after the stores have been released.

Abstract: A composite structure element (14) with built-in damping is formed with a non-metallic matrix (15) reinforced by a plurality of filaments (18) within the matrix. A lightweight metal (19) having a specific damping capability of at least 1% is provided on at least one of the matrix and the filaments of the composite structure element for attenuating vibrations of the element. The lightweight metal is preferably a magnesium alloy or an aluminum alloy which is coated on the filaments (18) and/or the pores (22) of a porous matrix (16). A metal structural member, such as a satellite antennae (27), subject to disturbance when used for its intended purpose can also be provided with built-in damping by providing a lightweight metal (32) having a specific damping capability of at least 1% on the structural member on the wire mesh (29) of the deployable antennae for damping disturbances.

Abstract: A series of parallel riblets extend from a smooth, aerodynamic surface for reducing the skin friction drag of the surface an airstream flows around it. The riblets extend longitudinally along the surface and have a triangular cross-section in the transverse direction. The apex of the cross-section defines a continuous, undulated ridge with peaks and valleys. Measured from the surface, the peaks have a greater height than the valleys. The interaction of the riblets with the structure of the turbulent boundary layer of the airstream reduces the skin friction drag coefficient of the surface by approximately 12% over an identical smooth surface without the riblets. This reduction occurs despite the significant increase in wetted area of the riblet-covered surface over the smooth surface.

Abstract: A method and apparatus is disclosed for providing a propulsive force to a dynamic body without having to interact with an external mass. The technique is based on an internal exchange of kinetic energy working in concert with the influence of an ancillary force such as gravity to produce a net momentum change in the body. In one embodiment a body may be rotated through space without having to expel propellant or otherwise resort to an interaction with an external mass. In another embodiment, the invention can be used to dampen a swaying motion or vibration of a body such as a tall, earth-bound tower or a beam in a space station when there is no convenient external mass to which the body may be anchored.

Abstract: A subsonic aircraft having backswept lifting wings is equipped with individually rotatable winglets at the wing tips thereof, in order to reduce drag during cruise flight, to minimize the dangers posed by wing tip vortices to following aircraft during take-off and landing, and to minimize the total wingspan during ground operations, with respective different positions of the winglets. A streamline-shaped rotation body made up of at least two individually rotatably supported rotation segments is mounted on the wing tip of each lifting wing. A respective winglet is mounted on each respective rotation segment. Each rotation segment with its associated winglet is individually rotatable about a rotation axis of the rotation body extending substantially parallel to the aircraft lengthwise axis. Thereby, each winglet is individually pivotable to any selected pivot angle relative to a horizontal plane extending through the rotation axis.

Abstract: A deployment inhibiting arrangement for a jet engine thrust reverser system, the system including one or more actuators for operating a thrust reverser of the system and first locking means for the or each actuator normally serving to hold the system in a condition in which the thrust reverser is undeployed, the inhibiting arrangement including additional locking means normally held in an inactive condition, but operable by means independent of said one or more actuators and said first locking means to provide an additional mechanical lock serving to prevent deployment of the thrust reverser irrespective of the condition of the first locking means and/or actuator(s). The invention also relates to a jet engine thrust reverser system, the system including such a deployment inhibiting arrangement.

Abstract: The present invention is a nanocomposite layer applied to the leading edge of an airfoil. The nanocomposite is an elastomeric matrix reinforced with nanosized reinforcing particles ranging in size from about 0.5 to 1000 nanometers and preferably ranging in size from about 5 to 100 nanometers. These nanosized reinforcing particles improve the mechanical properties of a pure elastomer. Improving such properties assists the nanocomposite layer in absorbing and dissipating the impact energy caused by the repeated impact of particulate matter, such as sand and rain. Adding the nanosized reinforcing particles to an elastomer allows the nanocomposite to absorb the impact energy over a larger volume in comparison to a pure elastomeric material. The nanocomposite layer is, therefore, capable of withstanding the repeated impact caused by the particulate matter for a greater length of time compared to a pure elastomer.

Abstract: A method for estimating motion of a dual-spin spacecraft having a gimballed momentum wheel. The method disengages the gimbal from its drive train in anticipation of a short disturbance. Then, the gimbal slip resulting from the disturbance is measured. The method may be used to stabilize any dual-spin spacecraft that uses a gimballed momentum wheel. To stabilize the dual-spin spacecraft, the gimbal angle and gimbal rate are measured during and after the disturbance to provide an indication of the inertial spacecraft motion along gimbal axes. The magnitude and direction of the disturbance are determined by comparing motion of the gimbal before and after the disturbance. Then, torques are applied to the gimbal to counteract the spacecraft motion resulting from the disturbance.

Abstract: An arrangement for an aircraft propulsion system to determinably reduce or eliminate inlet cowl induced bending of a turbofan aircraft jet engine case during certain flight conditions. The arrangement includes a turbofan aircraft jet engine having an engine case with a fan case portion, a nacelle structure housing the engine and having a forward nacelle portion and a rearward nacelle portion, and a pylon structure to support the engine and the nacelle structure while permitting the forward nacelle structure to be translated forwardly from an operational position to a servicing position to permit access to the engine and its components. The forward nacelle portion is independently supported from the pylon and has an inner skin portion that sealingly engages the fan case portion of the engine case and an outer skin portion that is determinably locked to the rearward nacelle portion.

Abstract: An apparatus and method are provided for reducing the drag of an aircraft wing. Many modern high speed aircraft have a low aspect ratio wing generating significant induced drag. The invention provides a drag reduction system, which is made up of a high aspect ratio supplementary wing connected to the fuselage by a streamlined fuselage connection, and at least two struts connecting the supplementary wing to the main wing. The drag reduction system is capable of reducing the total drag of a modern high speed, high altitude aircraft with a low aspect ratio cantilevered wing, by at least 29.1%. At least 65% of the total lift of the aircraft can be provided by the supplementary wing. The main wing then provides structural strength to transfer lifting loads to the fuselage of the aircraft, and for this purpose, the main wing and interconnections for the supplementary wing can be designed with this structural function in mind.

Abstract: The development of polymer composite liquid oxygen (LOX) tanks is a critical step in creating the next generation of launch vehicles. A composite LOX tank will weigh significantly less than conventional metal tanks. This benefit of reduced weight is critical to enable future launch vehicles to meet required mass fractions. The high strength and low weight of a composite tank allows for a lighter weight craft and/or higher payload capacity which results in lower costs per pound to place an object in orbit. The unique, nontraditional idea described here is to use resin-based composite materials to make such a composite tank or other oxygen carrying component such as a feedline. Polymer composites have traditionally been regarded as being more flammable than metals and therefore deemed not oxygen compatible. However, several cyanate ester composites have been tested for their ability to withstand ignition in the presence of oxygen, and have shown to be resistant to ignition.

Abstract: A charging sensor that uses photoemission to directly measure the electrical potential of a spacecraft in orbit relative to the space environment. The photoemission based charging sensor uses photoemission from a photoemitting conductive plate of a charge probe as a reference point for voltage readings and provides direct measurements of spacecraft charging.

Abstract: During a thermal equilibrium test, the heating of components of a spacecraft such as a satellite by albedo, terrestrial infrared and solar thermal fluxes is simulated by placing the craft directly in a vacuum chamber whose walls are cooled to a low temperature to represent the space environment. The simulation is effected by heating devices integrated between the panels forming the external structure of the spacecraft and external radiating components opposite the equipment units which dissipate heat. The heating devices, which are preferably electrical devices, remain in place on the spacecraft in flight.

Abstract: A link for use in an aircraft engine mounting system includes a span section having a first connector formed (at one end thereof and a second connector formed at another end thereof. A lumped mass is disposed on the span section for placing the resonant frequency of the link away from engine excitation frequencies.

Abstract: A submersible water toy comprises a buoyant streamlined body and a pair of wings attached thereto. While the body encourages the vehicle to rise in water, the wings, being formed from thin flat members resist vertical movement while providing little resistance to forward motion. The centerline of the wings is positioned behind the center of gravity of the bode so that the vehicle will rise in a forward direction while the wings resist vertical movement. Upon release, the submerged water toy will glide at relatively high speeds in a forward direction while slowly rising to the surface.

Abstract: A bias correction system for use in a neutrally-stable aircraft having a control column and a pitch control system is provided. The position of the control column is generally represented by a control column position signal. The bias correction system is for removing control column bias when the control column is in a neutral position. The bias correction system includes a first combining unit for combining the control column position signal and a correction signal, and a switch. The switch includes activated and deactivated states. The switch is set to the deactivated state when the control column is physically displaced from its neutral position. The deactivated state allows the correction signal to remain at its last value, the activated state allows the correction signal to equal approximately the control column position signal.

Abstract: The invention utilizes a moving band, typically on an airplane, to increase the apparent speed and therefore the lift of any body moving through a fluid. The invention will allow take-offs and landings at reduced speeds and allow a greater load. It will also reduce drag due to turbulence thereby allowing a flatter design of the wing, and reducing boundary later separation.