Abstract: Systems (10, 10a) and a methods (40) that employ a spin-stabilized spacecraft (12) in combination with a support and deployment module (14) to carry a plurality of probes (16) containing scientific instruments that are to enter a planet's atmosphere and/or are to be landed on a planet (19) that is to be explored. The spacecraft (12) functions as a probe carrier using the support and deployment module (14), and near the planet (19), it functions as an orbiting communications satellite (12) that relays data and commands between the aerocraft (16) and Earth. The support and deployment module (14) secures the probes (16) and is interposed between the spacecraft (12) and the launch vehicle (11). The support and deployment module (14) passes all structural loads due to the added mass of the aerocraft (16) directly to the launch vehicle (11), which is designed (nominally) for the total launch mass, and does not impose any structural loads on the satellite (12).

Abstract: An aircraft which is capable of safely landing during an emergency landing is disclosed. The aircraft has a safety device which includes a plurality of auxiliary engines. Each auxiliary engine is movable so as to vary the thrust axis in a range between a substantially horizontal direction and a substantially vertical direction. The safety device also includes a plurality of gas bags contracted and disposed at a lower portion of the aircraft body so as to be instantly expandable at a necessary time, such as during an emergency landing.

Abstract: A VTOL/STOL free wing aircraft includes a free wing having wings on opposite sides of a fuselage connected to one another respectively for free rotation about a spanwise access. Improved control upon landing of the aircraft is achieved by utilizing a variable pitch propulsion system, enabling the pitch of the propeller to be varied corresponding to the speed of the aircraft and angle of approach upon descent.

Abstract: A two-piece inflatable kite is made from configured, mirror imaged top and bottom polyester films which are heat sealed about their peripheral edge. Integrally extending from the edges forwardly and rearwardly are string connecting tabs formed from the top and bottom films. The tabs support reinforced apertures for attaching the kite string bridle. The top and bottom film portions also form a valve for adding air into and out of an air tight compartment within the kite. The air tight compartment also forms the wings of the kite.

Abstract: The wing deployment device is a simple mechanical device that resides in hollow of the wing and combines a primary and a secondary rotational motions to translate the wing from its stored position to its deployed position. The primary rotational motion occurs when the initial restraint holding the wing to the missile body is severed and the wing, under the influence of the spring component of the device, rotates to a position normal to the missile body axis. After the lapse of a pre-determined duration of time, the secondary rotational motion is started when the tensile force of the spring is transfered to the swivel component via the kevlar rope coupled between the spring and the swivel. As the kevlar rope that is wrapped around the cylindrical shaft component unwinds, the swivel rotates and transmits the rotational motion to the base component which is rigidly coupled to the wing and, in turn, imparts the motion to the wing, thereby engaging the wing in the secondary rotational motion to be deployed.

Abstract: A vehicle having a ceramic radome includes a vehicle body having an opening therein, a ceramic radome sized to cover the opening of the vehicle body, and an attachment structure joining the radome to the vehicle body to cover the opening. The attachment structure has a substantially cylindrically symmetric compliant metallic transition element disposed structurally between the radome and the body. The radome is joined to a first end of the transition element by a first brazed butt-joint. A primary seal is disposed between the transition element and the vehicle body. A spanner nut overlies the transition element and has a first engagement to the transition element. A threaded engagement between the spanner nut and the vehicle body allows the radome/transition element assembly to be attached and tightened to the vehicle body and to be later removed.

Abstract: It is a problem in conventional aircraft having a fuselage of substantially circular cross-section, that a conventional lower deck would have an insufficient standing height for passengers if the lower deck were to be equipped as a passenger cabin space including seats, sleeping cabins, or other passenger service facilities. In the present aircraft, the lower deck floor (2, 2') is depressed or dropped at least in a certain area (14) that will form an aisle (16), so that the free height of the lower deck in the area of the depressed floor provides at least the normal standing height (HS) for a person. A module (15, 15') containing passenger service facilities is arranged in the lower deck area at least to one side of the depressed floor area. A modular construction provides a great flexibility and convenience in reconfiguring a lower deck from a cargo hold configuration to a passenger cabin configuration and vice versa.

Abstract: Loading apparatus for loading containers into a cargo area in an aircraft are known that comprise, in addition to undriven conveyor rollers, a plurality of roller drive units. Each of the roller drive units includes a controllable drive motor to rotate drive rollers in a predetermined direction. In such loading systems, if the operator is inattentive it can happen that the roller drive units continue to run under containers that have been latched in place, so that the surface of their drive rollers and/or the drive motors are damaged. It is proposed to provide control leads between the roller drive units with control means in the control leads and/or in the roller drive units.

Abstract: A ducted fan 20 provides lift to a flying vehicle 10. The ducted fan includes direction control vanes (1, 2, 3, 4) for controlling torques applied to the vehicle, and also includes lift negation vanes (305, 306, 307, 308), which control the available lift. The lift negation vanes are oriented with their longitudinal axes parallel to the forward-aft axis (9) of the vehicle in order to reduce drag at high forward velocities. The thrust negation vanes include fixed (305) and movable (305M) portions, with the movable portions rotatable so as to extend into the duct airflow to cause turbulence. The direction control vanes are airfoils arranged for rotation about their quarter-chord axes (410), which reduces the amount of torque required for rotation of the direction-control vanes. This, in turn, allows stepper motors (924a) to be used to drive the vanes. The effects of forward velocity on the ducted fan also creates effects which tend to pitch the vehicle nose-down.

Abstract: A mounting for connecting a turbofan gas turbine engine to an aircraft structure comprises three mounting points at the vertices of a triangle on the aircraft structure and three mounting points on the fan casing of the turbofan gas turbine engine. The first mounting point on the aircraft structure is connected to all of the three mounting points on the fan casing by three links. The second mounting point on the aircraft structure is connected to the second mounting point and the third mounting point on the fan casing by two links. The third mounting point on the aircraft structure is connected to the second mounting point and the third mounting point by two links. The links provide an open spaceframe which defines the structure of a pylon. The mounting has reduced weight compared to conventional mountings and is cheaper to manufacture.

Abstract: An underspeed protection system for an aircraft under autopilot control selects a target speed based upon the greater of a minimum maneuver speed and a stick shaker speed. The system then compares a monitored speed to the target speed to produce an error signal. The system also monitors vertical speed to determine if the aircraft begins to descend. If the error signal due to the underspeed condition causes the aircraft to descend, the system provides a hold zero vertical speed signal in place of the error signal such that the aircraft seeks to maintain its altitude. The hold zero vertical speed signal overrides the underspeed error signal such that the aircraft does not pitch forward to seek an increased speed.

Abstract: A launch vehicle payload housing and assembly joint for a launch vehicle, the housing comprising a shroud having first and second shell sections, and a frusto-conical payload adapter mounted in the shroud. The shell sections are connected together to form a housing. A peripherally extending explosive seam and a pair of longitudinally extending explosive seams hold the shell sections together. Each seam comprises a plurality of seam elements which include a pair of brackets attached to opposed ends of those parts of the shell abutting the longitudinally and peripherally extending seams. The brackets are spaced from one another to define a cavity. The cavity accommodates a deformable tube which houses explosive material in the form of an explosive cord. Detonation of the explosive material causes the shell sections to separate from one another.

Abstract: Very large aircraft landing gear using single mounted eight wheel bogie on dual shock struts. A primary or main two-stage shock absorber and a semi-articulating secondary or auxiliary single-stage shock absorber, each of which are mounted using the second and third axles as pivot joints in a four axle, eight wheel truck beam.

Abstract: An improved ice protection apparatus 8 includes a top polyurethane layer 10, an active layer 12, and a base layer 14 cured together into a unitary matrix, wherein the base layer is either polyurethane or chloroprene. The active layer may be either a thermal ice protector, a pneumatic ice protector, or an electro magnetic protection apparatus.

Abstract: The present invention is directed toward a unique lift-generated noise reduction apparatus. This apparatus includes a plurality of tip fences that are secured to the trailing and leading assemblies of the high-lift system, as close as possible to the discontinuities where the vortices are most likely to form. In one embodiment, these tip fences are secured to some or all of the outboard and inboard tips of the wing slats and flaps. The tip fence includes a generally flat, or an aerodynamically shaped plate or device that could be formed of almost any rigid material, such as metal, wood, plastic, fiber glass, aluminum, etc. In a preferred embodiment, the tip fences extend below and perpendicularly to flaps and the slats to which they are attached, such that these tip fences are aligned with the nominal free stream velocity of the aircraft.In addition to reducing airframe noise, the tip fence tends to decrease drag and to increase lift, thus improving the overall aerodynamic performance of the aircraft.

Abstract: The present invention relates to a control system for an aircraft to compensate for crosswinds on landings. In one embodiment, the control system includes two mutually identical control surfaces having common end points, respectively; and an actuator to move completely the two mutually identical control surfaces, as needed to compensate for the crosswinds on landing.

Abstract: A method and system of orienting a payload of an orbiting spacecraft (14) to maintain a desired pointing profile in the presence of orbit inclination. A cone (12) is determined which is traced in inertial space by a pitch axis of the payload to maintain the desired pointing profile throughout an orbit. A bias momentum vector of the spacecraft (14) is oriented at an attitude which lies along the cone (12). The attitude has a nonzero angle with respect to a plane spanned by an orbit normal vector and an equatorial normal vector. The payload is rotated about a single body-fixed axis perpendicular to the pitch axis to align the pitch axis along the cone (12). As a result, the desired pointing profile is maintained throughout the inclined orbit.

Abstract: A selectively tiltable patient loading system and transport device adapted for use in aircraft is disclosed. The device generally comprises a base assembly interconnected to the floor of an aircraft, a platform assembly capable of receiving and supporting a litter with a patient thereon, and an interconnecting assembly interposed between the base assembly and platform assembly for supportably interconnecting the platform assembly to the base assembly and for selectively tilting the platform assembly relative to the base assembly.

Abstract: An expandable metal product for use in extinguishing fires and in the prevention of or protection against explosions. The product is a continuous sheet of magnesium alloy foil having discontinuous slits in spaced apart lines parallel to each other but transverse to the longitudinal dimension of the sheet. The invention is also directed to the expanded form of the product, either in sheets which may be used for preventing fires or explosion or in the form of shaped ellipsoids for use in a passive inerting system for fuel tanks.

Abstract: A helicopter skid having a wall defining an elongated generally cylindrical tubular cross section, and a web extending vertically along the longitudinal axis of the skid between a bottom portion and a top portion of the wall. The top and the bottom portions of the wall have a tapering thickness with maxima where the web meets the top and bottom portions. The web is preferably formed integrally with the wall. A horizontal member formed integrally with the side portions of the wall of the tube extends horizontally through an aperture in the web.