Abstract: A reconnaissance pod for viewing a scene has a structural backbone extending generally parallel to a pod axis, a forward housing affixed to the backbone, and an aft housing affixed to the backbone. The aft housing is separated from the forward housing along the pod axis. A central housing is mounted between the forward housing and the aft housing along the pod axis. The central housing includes a central body, a window through the central body, and at least a portion of a sensor assembly supported within the central housing from the forward housing and/or the aft housing. A rotational drive assembly has a forward support rotationally supporting the central body from the forward housing, with a forward bearing oriented to permit rotation of the central housing about the pod axis. The rotational drive assembly also includes an aft support rotationally supporting the central body from the aft housing, with an aft bearing oriented to permit rotation of the central housing about the pod axis.

Abstract: Rotary wing aircraft with electric pitch control. According to the invention, each blade (5.i) of the wing comprises a plurality of flaps (6.i) which are able to control the pitch of said blade and are aligned along the span of the latter, said flaps being individually controlled in orientation from a flight control device (17). Elimination of mechanical and hydromechanical members for controlling the rotor of such an aircraft, without loss of reliability.

Abstract: A device (22) fitted with ribs is placed on a cylindrical rod (20) so that it is fixed to it in bending. The device (22) is formed of at least three ribs connected to each other at their ends, and at least one pair of elements in the form of a star connecting the ribs together, at least close to its central region. This device enables the rod (20) to apply an approximately radial force to the center of the rod through an actuator onto webs (24) bearing on its ends, minimizing the mass for a given spacing of the webs (24). The device is particularly applicable to the control of aircraft control surfaces.

Abstract: A remotely controlled movably powered shuttle frame has foundation pads attached thereto at all four corner portions for separating skid pads of a helicopter from the flight deck of a marine vessel, wherein both the skid pads and the fight deck are outfitted with hook and loop fabrics. Skid blades displaced from retracted positions underlying the foundation pads are extended from the shuttle frame underlying a landed aircraft whose weight has been lifted off the flight deck by lifting arms pivotally mounted on the foundation pads. The aircraft carried by the lifting arms on the shuttle frame after the skid blades are retracted is shuttled by wheeled movement of the shuttle frame to a desired location on the flight deck.

Abstract: An apparatus for determining the attitude of an artificial satellite by narrowing attitude candidates to a correct one in a short time. The apparatus has star sensors, a star catalog data base, star identification sections in each of which star images output from the star sensors are collated with a star catalog with respect to each star sensor to output a group of corresponding candidates, attitude computation sections for computing a value of an attitude candidate of the artificial satellite with respect to each corresponding candidate, an attitude updating section for updating the value of the attitude candidate on the basis of the star images output from the star sensor and the star catalog, and an attitude propagation section for computing the value of the attitude candidate at the present sampling time from the value of the attitude candidate at the preceding sampling time and the artificial satellite's angular velocity.

Abstract: A system for the dissemination of pheromone bearing carrier substrates which includes an airplane/helicopter mountable carrier substrate dispenser, the actuation for release of the carrier substrates loaded into the dispenser being controlled from the cockpit of the plane/helicopter. Each carrier substrate has one A member card and at least one B member card released upon actuation of the dispenser, for disposition of the carrier substrates within treetops, where the pheromone will be released automatically from the substrate of the card to dissipate into the ambient air. The released pheromone acts to confuse male members of a particular pest insect, such that the males are impeded in their efforts to locate females of that specie who would also be disseminating pheromone, to thereby interfere with the mating cycle of such pest insects.

Abstract: A novel means of stability for a lifting platform utilizing toroidal vortex airflow through air guide means. A toroidal vortex created by the airflow means efficiently maintains a raised air pressure zone beneath the lifting platform or body. Airflow is directed downwards by means of air guides, which serve to produce lift and control rotational motion of the lifting platform to achieve stability of the body during operation. The system can also be easily modified to function as an attractor device. Overall, the present invention explores the uses of vortex airflow towards maintaining rotational stability.

Abstract: The aircraft crew rest station for a long distance airline flight includes an overhead crew rest portion contoured to occupy the space between the curved top portion of the hull of the aircraft and the lowered ceiling of the aircraft, and an entry vestibule providing access to the overhead crew rest portion. The overhead crew rest portion includes contains one or more forward, aft, and side bunk portions. The crew rest station can be located approximately in the aircraft midsection. In one presently preferred embodiment, the overhead crew rest portion comprises forward, aft, and side bunk portions configured in cross-wise fashion. The vestibule also provides a lavatory area, as well as a closet space.

Abstract: A loading system for loading a cargo deck in a cargo space of an aircraft with cargo holders is proposed, in which there are provided two pairs of mounting tracks with support rollers and transverse cargo latches, a middle mounting rail for the attachment of transverse cargo latches, and rows of side-mounted transverse cargo latches. The distance between the outer mounting track of each pair of mounting, tracks and the middle mounting rail corresponds to a first, lesser fixation distance of relatively smaller cargo holders (LD2). The distance between the outer mounting track of one pair and the inner mounting track of the opposite pair corresponds to a second, greater transverse fixation distance of relatively larger cargo holders (LD3). As a result it is possible to load a cargo space optimally even if the construction of the aircraft produces constrictions of the cargo space.

Abstract: A stabilizer suitable for stabilizing a shock formed during transonic velocity is presented. The stabilizer comprises an inboard end, an outboard end that forms an airfoil, which is positioned opposite the inboard end and, an upper surface that extends between the inboard end and the outboard end. A lower surface also extends between the inboard end and the outboard end and is positioned to oppose the upper surface. A leading edge between the upper surface and lower surface forms the stabilizer nose. A trailing edge positioned opposite the leading edge forms a generally concave surface. The outboard end of the stabilizer forms a predetermined angle omega with the trailing edge for positioning the outboard end relative to the trailing edge. The outboard end of the stabilizer forms a predetermined angle tau with the leading edge for providing a forward sweep angle.

Abstract: A spin-stabilised artillery projectile (11) can be easily subsequently fitted with an axially symmetrical aerodynamic braking device for reducing the ballistic trajectory if the tip (14) which is equipped with the fuse (13) and which is easily removable from the projectile body (12) is equipped at approximately half its height with flap-shaped sectors (24) which are pivotably mounted in such a way that they can be pivotably extended and which in their launch position fit snugly into the conical peripheral surface of the tip (14) and in the operative position are pivotably extended to form a radial ring which is closed or which has gaps.

Abstract: A protective panel for a reusable launch vehicle provides enhanced moisture protection, simplified maintenance, and increased temperature resistance. The protective panel includes an outer ceramic matrix composite (CMC) panel, and an insulative bag assembly coupled to the outer CMC panel for isolating the launch vehicle from elevated temperatures and moisture. A standoff attachment system attaches the outer CMC panel and the bag assembly to the primary structure of the launch vehicle. The insulative bag assembly includes a foil bag having a first opening shrink fitted to the outer CMC panel such that the first opening and the outer CMC panel form a water tight seal at temperatures below a desired temperature threshold. Fibrous insulation is contained within the foil bag for protecting the launch vehicle from elevated temperatures.

Abstract: A satellite attitude control system includes a programmed processor system which includes a gyroscopic actuator first control stage for changing the attitude of the satellite and a reaction wheel second control stage for assuring that pointing of the satellite is accurate and stable. The method is intended to be used for a satellite including the two control stages indicated above, which it uses selectively for the operations indicated above.

Abstract: The deployable flexible airlock and method for space vehicles, modules, and other structures has a flexible conduit attached between a vehicle frame member and a distal frame member. The airlock may be integrated into the hatch of a space vehicle. In the stowed configuration the airlock occupies a small volume to minimize the usable space impact to the space vehicle. The airlock is deployed by introducing vehicle cabin air into a number of support columns or tubes, which thereby inflate and cause the distal frame member to be pushed away from the vehicle frame member. When deployed, a chamber is formed for a user to transition through the airlock. The airlock is pressurized using cabin air and depressurized by evacuating the cabin air. Retraction of the airlock for stowage is accomplished by use of cables attached to the distal frame member, and controlled by actuator assemblies attached to the vehicle frame member.

Abstract: A common flight deck module for use with a plurality of aircraft platforms. The common flight deck module includes a discrete structure that is independent of the structure of the aircraft fuselage and may includes an avionics system and other hardware, controls and equipment. The common flight deck module is configured to “plug into” the fuselage from each of the aircraft platforms. The “plug in” modularity of the common flight deck module permits the standardization of various components and procedures to thereby make possible efficiency-based cost reductions for both aircraft manufacturers and aircraft consumers.

Abstract: A box for storage of passenger oxygen masks in an aircraft has a housing which contains a network for distributing oxygen from a general pipe or from a chemical generator and a door arranged to be beneath the box when it is in position in an aircraft. An inside face of the door or of the housing carries cradles defining a retaining position for each of the oxygen masks and latches that are displaceable responsive to closing the door from a position in which they define mask-retaining sockets to a position in which the latches release the masks.

Abstract: A microthruster having an inverted exhaust system traps burst diaphragm fragments providing a clean exhaust while an exhaust port provides increased back pressure for efficient combustion of a propellant charge in a fuel cell. A converging diverging micronozzle provides a predictable exhaust vector for improved microthrusting well suited for propulsion system on small spacecraft.

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, PEAR (polyether amide resin) composites, due to their low flammability and high toughness, could be made into liquid oxygen tanks.

Abstract: Compliant mechanisms are arranged to enable airfoil and other structures to adapt their shapes to different flight conditions and thereby achieve optimum lift:drag ratios in plural flight conditions. The compliant mechanisms can be formed integrally whereby a compliant frame thereof, or the skin of the airfoil, undergo elastic or other deformation to produce the desired displacements in direct response to applied forces. In an airfoil context, shape changes can be effected by the leading and trailing edges of the entire airfoil system. In addition, the driver arrangements of the compliant mechanisms can be controlled individually to effect a desired surface contour throughout the length of the wing, illustratively a twist therein.

Abstract: An environment control system for a body of an aircraft that provides controlled ventilation of the interior space of an aircraft body, facilitating reduction of volatile organic compounds (VOCs) within cabin air, dehumidifying and reducing moisture condensation and thus corrosion and other moisture related problems within the envelope, allowing increased humidification of cabin air, and allowing suppression of fires within the envelope. The environment control system includes at least a cabin and an envelope. It includes supply means for supplying a flow of dry ventilation air to the aircraft body. An airflow control device is capable of dividing the flow of ventilation air onto an envelope ventilation air stream and a cabin ventilation air stream. An envelope ventilation duct system directs the envelope ventilation air stream into the envelope, and a cabin duct system directs the cabin ventilation air stream into the cabin.