Abstract: A reusable module is affixed atop a reusable orbital vehicle (OV). Various configurations of the reusable module have identical external dimensions in the region of attachment to the OV to permit interchangeability. Different configurations can accommodate a variety of missions of different type and duration. A variety of cargo modules of different configurations allow cargo to be uplifted into orbit. In one embodiment, the cargo module is an unpressurized cargo module in which the cargo is exposed to the environment of space during the unloading process. The cargo module may also be a pressurized cargo module. In an alternative embodiment, the cargo module may include both a pressurized cargo module and unpressurized cargo module.

Abstract: A fin control assembly includes a housing, an arm configured to couple to a fin and to steer the fin relative to the housing, and a locking member disposed within the housing. The locking member is configured to (i) lock the arm in a substantially fixed state to inhibit movement of the arm relative to the housing when the locking member is in an engaged position, and (ii) unlock the arm from the substantially fixed state to allow the arm to steer the fin relative to the housing when the locking member moves from the engaged position to a disengaged position. The locking member has a cylindrical body portion and a cylindrical end portion, which is eccentric with the cylindrical body portion, to enable the locking member to lock the arm in the substantially fixed state while the arm holds the fin in a neutral location.

Abstract: A small, substantially spherical, free-flying utility platform for use in space can be docked, inspected and serviced in an apparatus including a container with a chamber therein mounted on the outside of a space vehicle or space station. A motorized closing mechanism drives a door to selectively open or close an opening of the container into the chamber, and another mechanism automatically latches and locks the door. The door operations can be automatically triggered as the platform breaks the beams of light beam devices arranged in the container. The proper positioning of the platform in the container can be detected by a photoelectric switch. Capture and docking of the platform is facilitated by sloping funnel-shaped interior walls of the container, and properly shaped cushions and/or a docking cradle. When docked, the platform has its batteries recharged, its fuel tank refueled, and its electronics evaluated and diagnosed.

Abstract: A simplified structure for a wing skin and wing box wherein the internal surface (2) of an aircraft wing skin panel (1) in the wing box includes a multiplicity of strips (3), each strip being associated with a stringer. The strips (3) have different gradients in the span-wise direction S, which is the direction in which the strips extend. The surface of each strip is, in the chord-wise direction C, parallel to the external surface (5). At a junction, at which a rib meets a stringer, the interior surface (2) has an area (4a) that is parallel to the exterior surface (5), such that the rib and stringer at that junction may be simply attached to the wing skin panel (1).

Abstract: A method and apparatus is provided relating to the use of fishing accessories attached to a fishing rod or reel. A fishing accessory, such as a fish hook retainer, can be attached to a fishing rod using a device with a shape suitable to be clamped between the mounting flange of a fishing reel and a fishing rod and/or reel clamp of the fishing rod. A fish hook retainer includes a pocket for retaining a fish hook, while protecting the point and barb of the hook from exposure.

Abstract: Methods and systems for controlling fuel tank flammability control systems are disclosed herein. In one embodiment, a system for use with an aircraft or other vehicle includes a flammability control system and a controller operably coupled to the flammability control system. The flammability control system can be configured to control the development of flammable vapors in a fuel tank of the vehicle. The controller can be configured to receive one or more signals relating to a condition of the fuel tank and control operation of the flammability control system at least partially in response to the one or more fuel tank condition signals. In another embodiment, the controller can be configured to receive one or more signals relating to an operational phase of the aircraft and control operation of the flammability control system at least partially in response to the one or more aircraft operation signals.

Abstract: An apparatus (10) for transporting laboratory animals comprises a container (12), a cover piece (14), and a closure piece (16). The container (12) has an open top. The cover piece (14) is connectable with the container (12) for closing the open top of the container (12). The cover piece (14) has a passage (188) through which the at least one laboratory animal passes during insertion into and extraction from a cavity (28). The closure piece (16) includes a portion (234) that is rotatable relative to the cover piece (14) between a first position in which the portion (234) of the closure piece (16) closes the passage (188) in the cover piece (14) and a second position in which the passage (188) in the cover piece (14) is open to permit the insertion and extraction of the at least one laboratory animal through the passage (188).

Abstract: A wild animal feeder is disclosed which is attachedly suspended form a tree or other stabilized element and may be horizontally and vertically suspended from same.

Abstract: The present invention relates to a convertible aircraft provided with first and second tilt fans disposed on either side of the fuselage a little forward of the center of gravity of the convertible aircraft. In addition, the convertible aircraft includes, in remarkable manner, a non-tilting fan that is permanently in a vertical position and that is contained inside the fuselage.

Abstract: A passenger accommodation unit with deployable bed, including a passenger seat and a passenger bed positioned relative to the seat and adapted for movement between a stowed position wherein the bed is upright and adjacent to the seat, and a deployed position wherein the bed is horizontal for use and overlaps and is supported in part by the seat. The unit includes a credenza positioned adjacent the seat and between the seat and the bed that supports the bed when deployed.

Abstract: A float retractable landing gear. The float retractable landing gear incorporates a wheel support, a side gear door, a bottom gear door, and one or more hinges and strut ears attached to a spine. At least one hinge is rotatably attached to a float. The float incorporates a float side cutout communicating with a float bottom cutout. A spring-loaded strut incorporating on over center toggle down lock feature is attached between the float retractable landing gear and the float. A float side wall skin is attached to an upper portion of the float side wall cutout. The side gear door is sized to cover the lower portion of the float side wall cutout, and the bottom gear door is sized to cover the float bottom cutout. The float retractable landing gear may be specified to default into the extended or retracted position depending on the strut spring constant selected.

Abstract: A cat litter box includes a first litter box half with a first recess and a first lip. The litter box includes a second litter box half with a second recess and a second lip which engages with the first litter box half to create an enclosure. The first recess and the second recess align to form an entrance to the enclosure through the which the cat can enter or exit the enclosure. Each recess sloped to act as a pour spout. Each half has a sliding gate that moves up and down over the recess. The gate in a down and stored position while in use for the cat and in an up position for sifting the litter. A method for cleaning a cat litter box.

Abstract: Aerospace vehicle yaw generating systems and associated methods are disclosed herein. One aspect of the invention is directed toward a yaw generating system that can include an aerospace vehicle having a fuselage with a first portion and a second portion. The system can further include a movable control surface coupled to the fuselage and extending generally in a horizontal plane. The control surface can be movable to a deflected position in which the control surface can be positioned to create a flow pattern proximate to the fuselage when the aerospace vehicle is located in a flow field. The flow pattern can be positioned to create a pressure differential between the first portion of the fuselage and the second portion of the fuselage. The first and second portions can be located so that the pressure differential produces a yawing moment on the aerospace vehicle.

Abstract: The present invention provides a method for the attitude control of satellites in elliptic orbits or satellites initially placed in circular orbits perturbed to elliptic orbits due to environmental disturbances. The method relies on the application of solar radiation pressure to provide the desired torque for the satellite attitude control. The satellite is equipped with two-oppositely placed light-weight solar panels extending away from the satellite along a predetermined direction (satellite body fixed Y-axis). By rotating one of these solar panels or both of them through desired angles about their axis using the respective driver motors as per the simple open-loop control law, the torque about the satellite axis is developed to achieve the desired attitude performance.

Abstract: The invention relates to a mechanism to control the pitch and/or roll and/or center of gravity of a vehicle. The first embodiment is a track-based mass transfer system in which pathways are positioned along or radially terminate at a central horizontal plane of the vehicle to move one or more mass transfer devices to a desired location to control the pitch and/or roll and/or center of gravity of the vehicle. A second embodiment is a fluid mass distribution system in which one or more conduits selectively distribute a fluid to one or more tanks positioned near a central horizontal plane of the vehicle to control the pitch and/or roll and/or center of gravity of the vehicle.

Abstract: An air discharge valve for an aircraft has an inner valve flap (1) and an outer valve flap (3) which partially overlap each other to form a nozzle of the Laval type with a nozzle inlet (6) converging toward a nozzle neck (S) and with a nozzle outlet (7) diverging away from the nozzle neck (S). The inner valve flap (1) has a trailing edge (8A) hinged to the aircraft body and a first leading edge (8) facing in the flight direction and having a curved sectional configuration. The outer valve flap (3) has a second leading edge (9) hinged to the aircraft body and a trailing edge (9A). Both flaps (1, 3) have a wedge shape. An outwardly facing surface portion (11B) of the inner flap (1) forms an air flow guide for air flowing out of the nozzle outlet (7). An inwardly facing surface portion (15B) of the outer flap (3) forms an air flow guide into the nozzle inlet (6) formed by the curved sectional configuration of the first leading edge (8) and by the inwardly facing surface portion (15B).

Abstract: A method of ornamenting conduits, cylindrical or otherwise, as well as other tubes, filters, narrow and cylindrical surfaces which can be found in an aquarium or terrarium whereby the tubes, conduits, and cylinders are provided with attachment members on their exteriors and ornaments are provided with attachment members so that the ornaments can be placed on the exteriors of the tubes, conduits, and cylinders enabling the texture or appearance of the exterior to be changed to produce a pleasing and aesthetic effect. The conduits and other aquarium equipment with attachment members on their narrow or cylindrical surfaces, as well as the ornaments with corresponding attachment members or regions are also described.

Abstract: Asymmetrical Control Surface System for Tube-Launched Air Vehicles places one control surface, such as a wing or a horizontal tail, above horizontal midplane axis of an air vehicle, such as a tube-launched missile, and the opposing control surface below the midplane axis. Such asymmetrical arrangement of the control surfaces increases the lift and maneuverability of the air vehicle during flight. For stowage inside the tube prior to launch, each control surface slides into its corresponding slot in the body of the vehicle, making the entire control system compact.

Abstract: An apparatus for controlling movement of a flying device, such as a kite. In controlling such movement, the apparatus comprises a series of force transmitting members associated with a control bar to be grasped by an operator. Such association minimizes interference of the force transmitting members with the control bar surface so as to heighten the level of control that the operator may exert over the kite. Such association also permits the operator to achieve, through movement of the control bar, selective adjustments in both the velocity and acceleration at which the kite and the operator are able to move in a single direction.

Abstract: The door comprises a panel (14) formed from two rigid parts (14a, 14b) hinged to each other edge to edge. A first part (14a) of these two parts is connected to the aircraft structure through a pivot pin (20) and a control means (22) is inserted between this first part (14a) and the structure. A kinematic control mechanism (16) connects the two parts (14a, 14b) to the aircraft structure, so as to enable progressive and controlled folding of these parts when opening the door. Thus the landing gear door can be opened and closed without any risk of it coming into contact with the wheels when the landing gear is extended.