Abstract: A device for braking the fall of a load, the device having a flexible fabric structure with a central hub connected to at least two radial blades adapted to impart rotary motion to the structure, thereby generating lift, and suspension rigging connecting the flexible fabric structure to the load beneath it.

Abstract: An aerial cargo container system for transporting cargo from an aircraft to the ground having a cargo box with a continuous side wall with six rectangular side panels, and rotor blades having stowed positions against alternating box side panels and deployed positions extending outwardly from the box in a generally horizontal plane. Each blade may include a lower panel and an upper panel that has two triangular sections behind the leading edge that forms an aerodynamic camber. The blades are hinged to a rotor hub secured across the top of the box. The upward deployment of the blades is limited by tethers extending from the blades down to a tether attach frame secured across the bottom of the box. The box and blades are preferably formed of corrugated paper or plastic material. The entire unit rotates with the load to create aerodynamic braking and lower cargo to the ground with a minimum of energy being translated to the cargo on impact.

Abstract: A nose assembly and method for controlling the rotation and stabilizing the orientation of a vehicle during landing maneuvers. The vehicle includes a nose assembly that is coupled to an airframe thereof and that has a frame and flap assembly. The flap assembly includes an actuating means and a flap coupled to the frame such that the actuating means moves the flap from and between a fully retracted position and a fully extended position in response to a guidance signal received from a flight control computer. In a preferred embodiment of the present invention, the flap assembly includes a plurality of flaps each coupled to the nose assembly frame and an actuating means that selectively positions the plurality of flaps in response to a signal.

Abstract: A recoverable aerial toy having a gyro-rotating recovery system that includes a main body which extends along a longitudinal axis, a rotor hub element mounted on the main body and rotatable relative thereto about the longitudinal axis, and a plurality of rotor blades. The rotor blades are hingedly coupled to the rotor hub element for rotation therewith about the axis and for hinged movement relative thereto between a closed position and an open position, such that the rotor blades extend along the longitudinal axis when disposed in the closed position and extend radially relative to the axis and outward from the main body when disposed in the open position.

Abstract: An apparatus and method is disclosed for decelerating and absorbing impact of a re-entry vehicle suitable for payloads that are relatively light as well as payloads weighing several tons or more. The apparatus includes four inflatable legs displaced equidistantly from each other around a capsule or housing which contains a payload. The legs are inflated at a designated altitude after entering Earth's atmosphere to slow the descent of the re-entry vehicle. Connected between each of the four legs are drag inducing surfaces that deploy as the legs inflate. The drag inducing surfaces are triangularly shaped with one such surface being connected between each pair of legs for a total of six drag inducing surfaces. The legs have drag inducing outer surfaces which act to slow the descent of the re-entry vehicle.

Abstract: The recoverable airborne instrument module is implemented using an aerodynamic housing which has at least one moveable control surface thereon. In operation, the recoverable instrument module is carried aloft by balloon to enable its instrument package payload to perform a series of meteorological measurements. The exterior housing of the recoverable instrument package has an aerodynamic shape, such as a delta wing airframe with a controllable rudder. A navigation circuit contained within the housing references the radio frequency transmissions of a plurality of beacons to determine the altitude and geographic position of the instrument package. This information, as well as data identifying the location of at least one predetermined landing site is used to dynamically calculate a flight path to controllably descend the instrument module to a selected one of these landing sites.

Abstract: A weapon arranged to travel in a given orientation when in flight, has a body and a ribbon. The body has a payload casing and a spindle rotatably mounted at the rear of the payload casing. The ribbon is formed into a flexible loop for trailing behind the body in flight. This ribbon is attached to the spindle. The ribbon has an impelling surface shaped to apply a torque to the spindle when in flight.

Abstract: An imaging device that automatically rotates upon descent through an atmosphere provides an onboard image detector a sweeping panoramic scan as it descends. No moving parts or propulsion system are required. The location, angle and pitch of the winged structure, together with its inertia properties, passively induces rotation. The angled location of the image detector takes advantage of the resulting rotation. Data generated by the image detector may be transmitted to a remote receiver or, alternatively, stored for subsequent recovery.

Abstract: Two ram air sections are included in a parachute canopy. The sections are arranged on opposite sides of a central axis, and face in opposite directions with respect to translational movement but the same direction with respect to rotational movement about the axis. The lower skins of the sections slope upwards from front to rear whereby the canopy rotates and the ram air sections create aero-dynamic lift slowing descent.

Abstract: An assembly of a payload and container is described whereby a payload supt having a base with a perimeter enclosed by a sidewall forming a cup for receiving a tubular container is provided. A first and second tie are connected to one end of the tubular container, and are terminated in an elastic ring. The first and second ties have a length which will permit the elastic ring to be placed in an annular groove in the exterior sidewall of the cup, thereby fixing the payload support to the container. During free flight of the assembly, air flow moves the first and second ties away from the container freeing the elastic ring from the annular groove in the cup whereby the container separates from the payload support.

Abstract: A brake device for retarding linear and rotative movement of a load carrying unit after ejection from an in-flight projectile, wherein a container encloses the unit and includes a plurality of slits which divide the container into sections. Each section includes a concave end portion which pivots into a position for retarding movement of the unit responsive to movement of the container through the atmosphere.

Abstract: A deployable stowed rotor having a rotor hub to which a pair of telescoping otor blades are connected is foldable into a package suitable for stowage prior to use. When the rotor is deployed, for example, as a lifting device for an ejection seat, positive preconing of the blades is provided by a spreading link arrangement connected to a drogue chute. Further coning during rotor spin-up is synchronized by intermeshed gears provided at respective one ends of the blades attached to the hub by teeter link hinges. Rotor speed is automatically regulated by a governing spring formed in conjunction with a helical spline arrangement between each of the blades and the hub and which varies the pitch of the spinning blades according to rotational velocity.

Abstract: A sonobuoy for launching at high altitudes from present sonobuoy launching tubes. A plurality of spring loaded stabilizing fins are held in place adjacent the body of the sonobuoy by rotovanes in their stored position. Upon launching the sonobuoy from an aircraft, the stabilizing fins assume their stabilizing position substantially perpendicular to the body of the sonobuoy due to the spring action but are held in place by the stored rotovanes. Upon reaching a lower altitude, the rotovanes are released to allow rotochute action to slow the descent of the sonobuoy. Upon deployment of the rotovanes to their operating position, the stabilizing fins previously held in place by the stored rotovanes separate to allow proper rotochute action.