Abstract: A carriage and ejection assembly for retaining different types of stores to an aircraft and selectively ejecting a carried one of the stores away from the aircraft is disclosed. The assembly can include a sway brace having at least one contact location for each type of store, wherein during ejection of the carried store by actuation of the sway brace, the at least one contact location corresponding to the carried store applies a pitch downward moment to the carried store. Another feature of the assembly can include a direct connection of the sway brace to a moveable part of an ejection actuator. Another feature of the assembly can include independent latching and unlatching of plural store retaining hooks of the assembly. Another feature can include a compressor for pressurizing a piston of the assembly that is carried by the aircraft. Yet another feature can include a hook release actuator placed in series with and upstream of an ejector actuator.

Abstract: A crew rest module for use in a mobile platform, particularly on commercial aircraft. The crew rest module in one implementation forms a pair of laterally adjacent crew rest compartments that each include a reclinable seat and a dedicated stairway for ingress and egress. The crew rest compartments are further elevated above a main floor of the cabin of a mobile platform to provide a degree of storage space underneath the crew rest compartments. Another embodiment provides a crew rest module having upper and lower crew rest compartments, with each compartment including a berth and a seat disposed laterally adjacent its associated berth. A stairway allows access to the upper crew rest compartment. Each of the modules provide a highly space efficient area that can accommodate a pair of crew members simultaneously and provide a degree of privacy for each crew member for rest and relaxation. The module further makes efficient use of the crown area of a commercial aircraft.

Abstract: A window assembly incorporating a window frame and seal and a method of forming the same are provided. The window assembly includes a window transparency first ply coupled to a first window structure. A window transparency second ply is coupled to the first ply and is spaced apart from the first structure defining a gap there between. A portion of the first structure, or a second window structure coupled to the first structure, extends over the second ply. A seal is placed, fitted or formed within the gap and between the second ply and the portion of the first structure or the second structure extending over the second ply.

Abstract: Stiffened structures and associated methods are disclosed. In one embodiment, an elongated metallic stiffening member can be attached to a composite sheet and positioned to resist bending of the composite sheet. In another embodiment, a structural system can include an elongated composite element attached between a composite sheet and a metallic stiffening member. In still another embodiment, the structural system is formed without attaching a honeycomb stiffening arrangement.

Abstract: An overhead area access staircase stowage system (7) includes a servicing unit (10) having a stowage unit and a staircase (12) proximate to the stowage unit. The staircase (12) has a stowed state (18) and a deployed state (20). The staircase (12) includes multiple stair elements (40) and a state actuating system (60). The state actuating system (60) transitions the stair elements (40) between the stowed state (18) and the deployed state (20).

Abstract: A fuel transfer apparatus for an aircraft comprises: two or more fuel tanks (2,3,4,5,6) arranged in an inboard to outboard alignment, at least one being situated in the wing (1) of the aircraft, means for transferring fuel between the tanks (8, 9), and a fuel management system (10) for controlling and monitoring the transfer of fuel between tanks the fuel management system comprises; means for receiving a first input signal that the aircraft has left the ground, means for receiving a second input signal that the aircraft is approaching its destination, means for initiating the transfer of the fuel from a relatively inboard tank location to a relatively outboard tank location in response to the first input signal, and means for initiating the transfer of the fuel from a relatively outboard tank location to a relatively inboard tank location in response to the second input signal.

Abstract: An improved structure and method for powering the flight of a model airplane by positioning the motors and propellers on the back side of the top wings of an airplane using a single or double-deck wing design so that the propellers and motors of the airplane are better protected from damage in the event of a crash. The fuselage of the airplane is formed of a deformable material such as a foam to aid in crash resistance.

Abstract: An electronic automatic reserve or primary parachute activation device incorporates partial or complete capture of freefaller or tethered parachute jumper kinematics to rapidly and reliable determine when to automatically activate deployment of the primary or reserve chute. This device uses means for directly measuring acceleration, velocity and/or position in addition to air pressure change to enable reliable detection of chute deployment conditions earlier than is possible with conventional pressure change activated automated activations devices. This is important when the activation decision must be made within 5–10 seconds of the initiation of the jump as is the case for military low altitude parachuting.

Abstract: An airship deployment system comprises an airship of unique shape having laminar flow over this shape to enable low power propulsion, capable remote control, comprising an inflatable body; a propeller assembly for station keeping and repositioning said airship and capable of being folded into a compacted position and unfolded into an operational position; and a payload, comprising gas for inflating said inflatable body; and means for transferring data between said airship and a remote location; and a missile for carrying said airship in a compacted state to a predetermined location and altitude, and releasing said airship at said predetermined location and altitude. When said airship is released from said missile said inflatable body is inflated and said propeller assembly is unfolded into said operational position.

Abstract: The present invention relates to an afterbody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one activatable flow effector on the missile or aircraft afterbody; at least one sensor each having a signal, the at least one sensor being positioned to detect forces or flow conditions on the missile or aircraft afterbody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one activatable flow effector based on at least in part the signal of the at least one sensor.

Abstract: A multimodal vehicle includes a ground based vehicle with an attached high-capacity airfoil parachute for deployment. The ground based vehicle includes a drive system for use on either land, water or both. Furthermore, the ground based vehicle is sized and dimensioned for transport of multiple vehicles in a cargo plane. The high-capacity airfoil parachute allows high-altitude deployment of the multimodal vehicle. The risers to the parachute may be adjusted for powered parachute flight rather than free fall flight. The ground based vehicle may include a propeller for powered flight.

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. The boom can be retracted when not in use to reduce the volume it occupies. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft and the recovery line.

Abstract: An apparatus and method including a deployable spacecraft mount for electric propulsion is disclosed. A typical apparatus includes a spacecraft body, a deployable element having at least two basic positions including a compact stowed position and a deployed position of the element and an electric thruster disposed on the deployable element where the electric thruster is disposed to mitigate negative plume effects in the deployed position that would be present in stowed position. The deployable element can be a radiator and can optionally be disposed on a second deployable payload module. Further, deployable elements can be selective deployed such that some electric thrusters can be used to assist in transfer orbit while undeployed elements help retain heat.

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured by a recovery line in flight, a process that can be aided by a line capture device having a retainer with two portions spaced apart by a distance great enough to receive the recovery line, e.g., to capture the recovery line with increased security. The line capture device can be operatively mounted on a lifting surface of the aircraft.

Abstract: A deployment device for a fin of a projectile incorporating a hinge fixed to the projectile body which allows said fin to make a pivoting movement along at least one axis, wherein said hinge comprises a support for said fin mounted able to tilt over with respect to an axis substantially perpendicular to the projectile axis, said fin being linked to said support by a rod whose axis is substantially parallel to said projectile axis when said fin is in the folded position and substantially perpendicular to said projectile axis when said fin is in the deployed position, said rod itself being able to pivot with respect to said fin support when such said support tilts over, this pivoting of said rod being controlled by driving means.

Abstract: Aircraft frames having multiple bracket mounting holes, corresponding brackets, and associated methods are disclosed. An aircraft frame member in accordance with one embodiment of the invention includes multiple sets of mounting holes, each set having one or more mounting holes. Brackets in accordance with an embodiment of the invention can be attached to either of at least two of the sets of mounting holes, for example, using snap fit attachment devices or other attachment devices. Each bracket can support one or more components (e.g., insulation, wiring, ECS ducting) relative to the aircraft frame member. The bracket can also span between two or more aircraft frame members. Each bracket can be installed in any of a variety of positions without the use of tools and can support any of a variety of devices. Accordingly, the time and cost associated with manufacturing, inventorying, installing and repositioning the brackets and the devices they support can be reduced.

Abstract: A disclosed vertical lift flying craft includes a lift unit that, during operation, develops a force including an upward component. A payload unit suspends from the lift unit. The payload unit suspends from the lift unit in such a way as to impart lateral stability while remaining capable of horizontal flight, without incurring the adverse effects of a downward pitching moment. In addition to a lift unit and a payload unit, the vertical lift flying craft includes a pair of bearings and a suspension structure, which cooperate to suspend the payload unit from the lift unit. Other systems and methods are also disclosed.

Abstract: A cellular actuator device suitable for a control surface of an aircraft or space craft has a number of elementary cells which are combined to a common arrangement and are formed by pressure-tight chambers. The elementary cells can be acted upon by a pressure medium and, when acted upon by the pressure medium, can be deformed in at least one work direction while changing their length. The elementary cells are coupled for combining their length changes in the at least one working direction to an overall movement of the elementary cell arrangement. The actuator device is particularly suitable for actuating a control surface of an aircraft or spacecraft.

Abstract: A wheel-through ski for the landing gear of an aircraft is disclosed. The ski has an airfoil shape, and the ski and its attachments are aerodynamically clean. The ski is provided with a three sided recess that permits the mounting of the ski on the aircraft without lifting the landing gear off the ground. The members of the articulated attachment between the ski and the aircraft are joined by a removable pin and are fixedly attached to the ski and landing gear. The ski is of aircraft construction. It has a thin skin, air frame-like internal structures, foam material internal cores that provide stiffness to the ski and wear strips on the bottom of the ski.

Abstract: Process for improving the maneuverability of an aircraft during a resource. According to the invention, prior to the resource, the adjustable horizontal tailplane (2) is nose-up deflected and the elevators (4) are nose-down deflected.