Abstract: An Eyepiece-support arm assembly device on an aircraft. The device comprises flanges formed on the eyepiece-support arm and on a support attached to the aircraft, along with a retention belt (32) liable to be set to a locking status, wherein the arm is immobilised in relation to the support, a setting status, wherein the arm can be moved between a position for use and a retracted position, and a disassembly status allowing the assembly and disassembly of the eyepiece-support arm, without modifying the setting. The status is changed by operating levers (44, 46).

Abstract: A flight lock actuator that can be powered by two sources of stored energy when aircraft power has been switched off. A mechanical energy storage means and an electrical energy storage means provide a fully redundant energy storage system that stores sufficient energy to complete the actuator's extension stroke when aircraft power is removed. The actuator has a motor control system that limits the stroke velocity for both the extension and retraction strokes, including a damper feature capable of effectively braking the actuator during the back-driven extension stroke.

Abstract: A design and installation method are provided to improve access to equipment mountable on aircraft equipment racks, including installing modified equipment rack framework on the aircraft, preassembling the equipment on a separate equipment package, providing separate matable hinge units on both the framework and equipment package, and temporarily supporting the equipment package in a hanging position from the equipment rack by matably joining the separate hinge units. Wiring the equipment from adjacent wireway banks is performed in the hanging position, followed by rotating the equipment package about an axis of rotation formed by the joined hinge units into a fixed stowed position, and fastening the equipment package to the equipment rack framework to complete the installation.

Abstract: A method and system for controlling a movable appendage on an aerospace vehicle independent from the position of the aerospace vehicle. First and second beacons containing actual position information for the movable appendage are tracked and acquired by first and second beacon tracking sites. The beacon tracking sites report the azimuth and elevation data relating to the position of the movable appendage to a processor where a correction command is determined based on an error calculated from the position data and a desired position. The correction command is communicated to the movable appendage so that appropriate correction to the desired position can be made.

Abstract: A sprayed on, semi-rigid, substantially closed cell foam insulation which forms an insulative layer directly on an interior wall or internal structural member associated with a skin of an aircraft fuselage. The foam insulation may comprise a polyurethane, substantially closed cell foam which is sprayed on to the interior wall of the fuselage to form a layer having a thickness of between about 0.25 inch-1.5 inch and a weight of between about 2 lbs. per cubic foot to about 3 lbs per cubic foot. The insulative layer forms a thermal and acoustic barrier and is highly resistant to the absorption of condensation and humidity. The foam insulation, being sprayed on, can be installed much more quickly than conventional blanket-type insulation material and with significantly less cost.

Abstract: A window apparatus for use within an aircraft interior. This window having at least one shade frame, at least one shade attached to the shade frame at its top and a moveable shade rail attached at its bottom, a first and second lens assembly where the first lens assembly has first lens and the second lens assembly has a second lens, the first and second lenses being mountable to the shade frame such that they form a double convex configuration, and means for moving the shade between a substantially open position and a substantially closed position. The first and second lenses may have the same dimensions and/or be rectangular in shape. The first lens may have a length of at least 40 inches, a width of at least 30 inches, and an area of at least 1200 square inches. The shade may be pleated, tubular in shape, and have means for maintaining the horizontal alignment of the shade rail.

Abstract: Apparatus and methods for pointing a non-deployable or deployable appendage disposed on a spacecraft. The appendage is secured to a backup structure comprising a plurality of beams. A plurality of control beams are secured to the backup structure. A plurality of deformation control elements, such as piezoelectric elements, for example, are secured to selected surfaces of the plurality of control beams. The deformation control elements are connected to a control source, such as a voltage control source, for example. Selected deformation control elements are activated to deform the associated control beams to point the deployable appendage in a desired direction.

Abstract: An aircraft drainmast assembly including a drainmast for ejection of waste water from an aircraft and a grounding plate for protection against lightning strike currents. The grounding plate is made of an electrically conductive material and is attached to the metallic drain tube in such manner (e.g., welding) that a conductive path is established between the grounding plate and the drain tube. The grounding plate is placed in contact with the aircraft fuselage during installation of the drainmast whereby an electrically conductive path is formed thereby allowing lightning strike currents to travel from the drain tube to the grounding plate to the aircraft fuselage. The grounding plate may be pressed against the outside surface of the fuselage by an elastomeric gasket installed between the grounding plate and a flange of the drainmast's fairing thereby allowing for a simple lightning protection installation from the outside of the aircraft.

Abstract: A subfloor structure of an aircraft airframe, particularly of a helicopter, includes longitudinal beams and crossbeams that intersect each other and are interconnected to form a grid that is fixedly attached to the floor and the bottom skin of the aircraft fuselage. Structural elements such as pyramid frustums and reinforcements are arranged on the beams. The longitudinal beam and the crossbeam have a trapezoidal cross-section that is preferably open on the wider base side, closed by a spine web along the narrow side, and bounded laterally by inclined leg webs that extend downwardly from the spine web at an angle outwardly relative to each other. The subfloor structure grid effectively absorbs the energy of a crash impact having both axial or vertical as well as non-axial or lateral impact force components.

Abstract: The present invention includes an instrument panel that is adapted to stand over the lap of a pilot within a cockpit of an aircraft to make more efficient use of the limited space within the cockpit. The panel houses at least a portion of the instruments that are installed in the cockpit to fly the aircraft. More efficiently use of the space within the cockpit reduces the size and weight of the cockpit. Moreover, reducing the weight of the cockpit allows the cockpit with the canopy to be ejected from the aircraft rather than just the pilot seat. The cockpit enclosed by the canopy ejects the pilot faster and protects the pilot during and after the ejection. The ejection is faster because there is no need to remove the canopy before ejecting the seat. The pilot is further protected because the canopy protects the pilot from wind impact and harsh atmospheric conditions at high altitude.

Abstract: The capacity of airliner overhead storage bins is increased by replacing the original door with a curved replacement door. The replacement door has an outwardly curved main panel, and at least one side panel that fills the space between the main panel of the door and the bulkhead of the storage bin.

Abstract: An aircraft drainmast assembly including a drainmast for ejection of waste water from an aircraft and a grounding plate for protection against lightning strike currents. The grounding plate is made of an electrically conductive material and is attached to the metallic drain tube in such manner (e.g., welding) that a conductive path is established between the grounding plate and the drain tube. The grounding plate is placed in contact with the aircraft fuselage during installation of the drainmast whereby an electrically conductive path is formed thereby allowing lightning strike currents to travel from the drain tube to the grounding plate to the aircraft fuselage. The grounding plate may be pressed against the outside surface of the fuselage by an elastomeric gasket installed between the grounding plate and a flange of the drainmast's fairing thereby allowing for a simple lightning protection installation from the outside of the aircraft.

Abstract: A detection apparatus for use with a system having a plurality of moveable surfaces, the apparatus comprising a signal transmission apparatus extending across each surface, a signal generator and a signal receiver. The apparatus further comprises a signal interrupter associated with adjacent ones of the surfaces and arranged to interrupt the transmission of a signal along the signal transmission apparatus upon relative movement of the adjacent ones of the surfaces occurring. The invention also relates to a leading edge high lift system of an aircraft wing having a plurality of moveable leading edge high lift surfaces.

Abstract: The invention provides a quick disconnect mounting system for cabinets and partitions which entails only the removal of one or two bolt fasteners on the bottom of the cabinet and a pair of retractable pin fasteners on the upper portions of the cabinet, with an optional retractable pin fastener in the center rear of the cabinet. Each of these acoustical mounts are insulated, thus preventing vibration in the structural portion of the fuselage from entering the passenger compartment.

Abstract: A bellows body is curved and formed with a plurality of convolutions to allow axial and lateral flexure of both ends of the bellows when connected between the engine exhaust stack and an airframe duct. The upper slotted end of the bellows fits over the stack nipple and is conventionally, fixedly sealingly secured thereto by an O-clamp. The outside diameter of the lower end forms a gas tight slip joint in the bore of the lower cowling heater duct flange. For added reinforcement an optional collar may be permanently fitted exteriorly and/or interiorly of the stack wall adjacent the stack nipple and an optional brace may be welded interiorly between the stack and scupper.

Abstract: A storage compartment is combined with an air flow channel (5) between a passenger seat and an aircraft side wall in an aircraft cabin. The storage compartment is constructed of five walls forming a box (3) inserted into the air channel that extends longitudinally along the aircraft side wall and along the cabin floor. The box (3) is upwardly closed by a hinged cover (16) forming a tray (17). The aircraft side wall (2) has at least one air filter element (10) facing into the channel. One or more dado panels (7) with air flow passages (6) enclose the channel toward the cabin. A cabin floor (4) closes the channel (5) downwardly. One or more decompression flaps (15) in the floor (4) normally close the channel (5). Under normal operating conditions air flow into and out of the cabin passes around the box through the channel (5) and the filter element (10).

Abstract: Disclosed is a first miniature digital video camera in a streamlined configuration mounted on or in proximity to the vertical stabilizer of an aircraft and in communication preferably with both remote digital video recording apparatus and at least one cockpit video monitor. The video recording apparatus is preferably one or more channels on the flight data recorder for postcrash investigation. The preferred embodiment would employ two video cameras, one on anterior or front of the tail assembly, and one of the posterior or rear of it. One alternative embodiment would consist of only one video camera, fastened to an extension of the tail assembly. The second preferred embodiment would include two video cameras, one of which would be mounted on the posterior end of the tail assembly, the other on the under side of the plane, just behind the wings.

Abstract: A fitting for anchoring an aircraft seat to a track mounted to the floor of the aircraft is provided. The fitting is removably mounted to the seat and includes a generally rectangular elongate base having flange-like extensions running longitudinally thereof. The base has symmetric slide bearings affixed thereto, one at each end thereof, and overlaying the base, dimensioned so that the base with attached bearings is slidably insertable into the slot of the track. When the seat is mounted to the track, the symmetric bearings are in contact with the upper inside surfaces of the slot within the track, providing relative ease of slidable movement thereof when required.

Abstract: Blue icing can be prevented by an apparatus inside an aircraft. A sump is provided which has a removable screen cover disposed over an open-top container. The sump is placed underneath the aircraft's service valve, between the service valve and service door, to collect leaked aircraft lavatory fluid. A level sensor switch placed on an interior wall of the container senses the level of the fluid in the sump and activates a pump inside the sump when the fluid reaches a predetermined level. A recirculation loop has a recirculation hose in circuit with a one-way valve. The activated pump pumps the fluid through the recirculation loop. The recirculation loop leads to a three-port fluid return fitting, allowing the pumped fluid to return to the lavatory fluid reservoir. The fluid return fitting connects to the recirculation hose, lavatory fluid reservoir and to a vent hose equilibrating the pressure within the reservoir with the ambient pressure of the aircraft's interior.

Abstract: A drainmast including an electronic temperature detecting and control circuit contained in a fairing detects the temperature of a drain tube and the electronic temperature detecting and control circuit selectively applies voltage to one or more heating elements in accordance with the detected temperature. The applied voltage may be unequally applied to the heating elements. The electronic temperature detecting and control circuit only requires two leads, one for ground and one for the supplied voltage. The drainmast is reliable, has a long life span and rapidly responds to temperature changes.

Abstract: A missile includes a fuselage with a roll axis and a nod axis perpendicular to the roll axis, and a conformal window mounted to a forward-facing end of the fuselage. There is a sensor system with a field of regard through the window and a line of sight, and a sensor system pointing mechanism affixed to the airframe and upon which the sensor system is supported. The sensor system pointing mechanism includes a gimbal structure having a first degree of rotational freedom about the roll axis and a second degree of rotational freedom about the nod axis, and a linear translational mechanism connected to the sensor system. The linear translational mechanism is operable to translate the sensor system away from the window with increasing angular deviation of the line of sight of the sensor system from the roll axis. Preferably, the translational mechanism is a slider-crank mechanism.