Abstract: A jet aircraft has a generally cylindrical fuselage section defining a passenger compartment and a generally conical aft fuselage section having a maximum lateral dimension substantially smaller than the lateral dimension of the fuselage section. A propulsion engine is mounted on the vertical stabilizer of the fuselage and has an air inlet disposed entirely within a rearward projection of the fuselage passenger compartment to preclude the ingestion of foreign objects into the engine.

Abstract: A solar power system for orbiting spacecraft includes a collector surface and attached mirror which is retained in a coiled position around the outer surface of the spacecraft in its launch mode. The system is deployed from the orbiting spacecraft by releasing restraining straps and permitting the mirror and attached collector surface to automatically uncoil as a result of the resilient spring characteristics of the mirror. During orbit, the deployed system extends from one side or both sides of the spacecraft such that the mirrored surface faces the sun. Heating pipes are pivotably disposed between the mirror and the collector surface to also function as spacing struts. The collector surface covered with photovoltaic solar cells made of silicon or Gallium Arsenide-Phosphide (GaAsP) in a first embodiment of the invention, can be replaced by a flat heat pipe for conducting heat energy to the input of an external heat engine electric generator in a second embodiment of the invention.

Abstract: A service system is arranged for at least one docking position for a craft, which requires the supply of various utilities and the discharge of waste. The system comprises a plurality of service boxes (3) lowered into the ground in the docking position. The service boxes each comprise a casing (9) and a cover (10) forming the top of the service box. The service boxes each accommodate a connecting device (22-26) for connecting an underground supply or discharge conduit (5) opening into the service box and connected to a utility source and a waste receiver, respectively, to a corresponding inlet and outlet, respectively, of the craft. At least one of the service boxes (3) comprises a cassette (15) accommodated in the casing (9), said cassette being liftable up from said casing when the cover (10) is removed, the connecting device (22-26) of the service box and the associated equipment, if any, being mounted in the cassette.

Abstract: A cargo pod for light aircraft forming a sealed enclosure with an access door therein, the pod being attached to the aircraft through the use of over center latches. The cargo pod is made of a fiberglass laminate and has skids for sliding the pod when detached from the aircraft.

Abstract: A modular spacecraft and fabrication method for producing a spacecraft of the kind that forms an enclosure and framework for installation of the external and internal subsystems of the spacecraft. The primary structure of the spacecraft is formed as a split shell enclosure including composite formed upper and lower shell portions. The spacecraft, with the shells open, provides an extremely high degree of access during the assembly, installation and test of the spacecraft. A self-aligning tapered joint is formed at respective contacting lip surfaces of at least one set of common end walls of the upper and lower shell portions. Heat pipes are formed integral within the composite structure of selected walls of the shell portion to provide thermal regulation to the spacecraft and the subsystems contained therein. Removable battery modules are incorporated into the end wall structure of the upper shell portion.

Abstract: A number of resistive elements are incorporated into the aerofoil in the vicinity of its leading edge. Each of the resistive elements is electrically connected to the other resistive elements at its distal end and is fitted at its proximal end with means of connection to an electrical power supply. The resistive elements are split between a first set that includes at least two resistive elements and a second set that includes at least one resistive element. In service, the resistive of the first set are powered in turn, while each resistive element of the second set acts as a return path for the electricity and is powered continuously or almost continuously.

Abstract: Articulating overhead luggage bin assemblies including a luggage bin that it is adapted for mounting to a support structure in a mass transit vehicle, such as an aircraft. The bins have an upper shroud portion, and a lower bucket portion, with cooperating means for interconnecting these two bin portions so that the bucket portion is guided downward and forward relative to the shroud, when the bin is opened. The cooperating means are "rigid" so that each end of the bucket moves in concert with the other, without need for a torque tube or other motion control device linking the bucket ends. The assembly also includes a downlock mechanism for holding the bin in a fully opened position. To close the bin, the downlock mechanism is disengaged by application of backward force to the bucket portion.

Abstract: A remote-control maintains the angle-of-attack of a tethered aircraft in fluxuating wind velocity. The tether is attached to the towing-point that is on a motor-driven tether-transporter. The transporter is secured to the structure of the aircraft. The angle-of-attack is modulated when actuating signals from a remote station cause the motor to propel the transporter, which carries the towing-point, to or fro, across the windward face of the aircraft.

Abstract: Security apparatus and a method for preventing theft or unauthorized removal of instruments from the cockpit instrument panel of an aircraft and for preventing theft or unauthorized use of the aircraft. The apparatus includes a rigid plate substantially covering the instrument panel and two rigid arms pivotally secured to the plate inwardly of the columns respectively and laterally pivotable rearwardly away from and forwardly toward the plate. Each of the arms include an end portion for restrainably engaging the aircraft flight control yokes against rotation when the arms are pivoted to extend rearwardly away from the plate while the columns are fully rearwardly extended and the yokes are fully rotated to one side. A locking device is engageable with the end portions of the arms for locking the arms rearwardly extended and for cooperating with the yokes to prevent forward displacement of the columns while securing the plate against the instrument panel.

Abstract: One of the routines required for maintaining the air worthiness of an aircraft is the frequent inspection of rudder and elevator cables. Given traditional aircraft design, for example the Cessna "335" and "340" aircraft, access to these cables has been achievable only by removing the tail-cone from the body of the aircraft. Composed as they have been of aluminum or ABS plastic, these tail-cones have been prone to breakage. Their replacements, also of ABS plastic, have consisted of two large halves bolted together, one of which must still be removed from the aircraft to allow cable inspection and for which breakage is still a concern. The invented generally one-piece tail-cone molded of fiberglass constitutes a durable replacement for a broken cone. Equipping the new fiberglass cone with relatively small doors to be used for cable inspection allows the tail-cone to remain in place on the aircraft during its conceivable considerably lengthened life span.