patentstorm.us

Guided munition systems including combustive dome covers and methods for equipping guided munitions with the same

Patent Number: 8445823
Publication Date: 2013-05-21
Inventor:

Embodiments of a guided munition system are provided, as are embodiments of a combustive dome cover and methods for equipping a guided munition with a combustive dome cover. In one embodiment, the guided munition system includes a guided munition, which has a munition body and a seeker dome coupled thereto, and a combustive dome cover disposed over the seeker dome. The combustive dome cover is configured to uncover the seeker dome at a predetermined time of deployment and to combust when so ...

One-piece Nano/Nano class Nanocomposite Optical Ceramic (NNOC) extended dome having seamless non-complementary geometries for electro-optic sensors

Patent Number: 8445822
Publication Date: 2013-05-21
Inventor:

A one-piece extended dome having a spanning angle greater than 180 degrees. The dome is integrally formed of a Nano/Nano class Nanocomposite Optical Ceramic (NNOC) material. The extended dome comprises seamless first and second non-complementary geometric shapes, such as a first spherical geometry and a second conical or ogive geometry. The Nano/Nano class NNOC material comprises two or more different chemical phases (nanograins) dispersed in one another, each type having a sub-micron grain ...

High lift system for an aircraft

Patent Number: 8444094
Publication Date: 2013-05-21
Inventor:

A high-lift system for an aircraft includes a main wing, a lift flap arranged on the main wing of the aircraft, which lift flap is adjustable, between a retracted position and several extended positions relative to the main wing of the aircraft, by means of a flap adjustment mechanism for coupling the lift flap to the main wing and by means of a drive device, wherein the flap adjustment mechanism comprises at least two adjustment devices arranged so as to be spaced apart from each other in ...

Airplane leading edge de-icing apparatus

Patent Number: 8444093
Publication Date: 2013-05-21
Inventor:

An airplane leading edge de-icing apparatus having a heat diffuser for heating the leading edges of an airplane is provided. The heat diffuser has a first heat diffuser side having a concave shape and a second heat diffuser side having a convex shape. The heat diffuser is joined to the leading edge of an airplane. A counter current heat exchanger is provided and heats a heat transfer fluid with heat energy absorbed from hot gases. The heat transfer fluid is pumped in and out of a reservoir ...

Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing same

Patent Number: 8444092
Publication Date: 2013-05-21
Inventors: ; ; ;

Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing these metal sheets and plates are disclosed herein. In an embodiment, there is provided a transportation vessel that includes at least one metal product having at least one surface that is substantially grooved, wherein the substantially grooved surface forms a riblet topography, the riblet topography including a multiplicity of adjacent permanently rolled longitudinal riblets running along at ...

Aircraft stabilizer surface trailing edge

Patent Number: 8444091
Publication Date: 2013-05-21
Inventor:

Trailing edge (3) of an aircraft stabilizer surface (1), where this surface (1) is manufactured of a composite material and comprises an outer cladding (40) and an inner cladding (41) that are connected by a connecting clip type element (20) on this trailing edge (3), the connecting clip type element (20) comprising at its ends some recesses (23) used for coupling to the inner zone of the upper and lower claddings (40, ...

Transverse butt connection between two fuselage sections

Patent Number: 8444090
Publication Date: 2013-05-21
Inventors: ; ;

A transverse butt connection between two fuselage sections, more particularly for creating a fuselage cell for an aircraft, can have a number of stringers arranged spaced out uniformly parallel to one another inside on an outer skin. In order to enable a universal tolerance compensation with standardised compensating means within a predetermined tolerance band between two fuselage sections which are to be joined together, both end areas of the fuselage sections can have on the inside ...

Pressure bulkhead and method for subdivision of an aircraft or spacecraft

Patent Number: 8444089
Publication Date: 2013-05-21
Inventors: ;

The present invention provides a pressure bulkhead for subdivision of an aircraft or spacecraft into an internal and an external pressure region. The pressure bulkhead comprises a pressure plate having an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft, a supporting means which tiltably supports the edge on the inner contour, and a seal which seals the edge with the inner contour. A further aspect of the invention provides a method for subdivision of an ...

Fuselage structure and method for the production of a fuselage structure

Patent Number: 8444088
Publication Date: 2013-05-21
Inventor:

The present invention provides a method for the production of a fuselage structure, and a fuselage structure, in particular of an aircraft or spacecraft, with an inner shell arrangement which has an upper inner shell and a lower inner shell, the upper inner shell being spaced apart at least in some sections from the lower inner shell by a first gap in order to form a window region; and a window band which is arranged at least in the window region and has a pane device which comprises a grid ...

Composite skin and stringer structure and method for forming the same

Patent Number: 8444087
Publication Date: 2013-05-21
Inventor:

Composite stringer and skin structures and methods for forming the same are disclosed. In one embodiment, a composite stringer and skin structure includes a polymer-based elongated stringer portion having reinforcing fibers positioned in a plurality of adjacent plies, a first portion of the reinforcing fibers being oriented at a relatively shallow angle relative to a selected reference direction, and a second portion of the reinforcing fibers being oriented at a relatively broad angle ...

Aircraft wheel-and-brake set fitted with a rotary drive device

Patent Number: 8444086
Publication Date: 2013-05-21
Inventors: ;

The invention provides an aircraft wheel-and-brake set, the wheel including a rim mounted to rotate on an axle of the aircraft about an axis of rotation, and the brake including a stack of disks extending into the rim in service, and a support carrying brake actuators facing the stack of disks in order to selectively press said disks together, wherein the support carries at least one rotary drive member for driving the wheel in rotation, which drive member is carried in such a manner that ...

Support structure

Patent Number: 8444085
Publication Date: 2013-05-21
Inventors: ;

A support structure is provided for attaching a gas turbine engine to a pylon. The gas turbine engine has an engine casing surrounding an engine core, and the pylon has first and second attachment positions, the second attachment position being forward of the first attachment position relative to the working gas flow direction through the engine. The support structure has three elongate members joined to form a triangular frame encircling the engine casing. A first vertex of the triangular ...

Aeroengine mounting

Patent Number: 8444084
Publication Date: 2013-05-21
Inventor:

A mounting arrangement of a gas turbine engine comprising a core engine, surrounded by a nacelle having a bypass duct, the mounting arrangement comprising a front mount, a rear mount and characterized by the mounting arrangement further comprising a fail-safe mount axially spaced from the front and rear mounts. The fail-safe mount comprises a number of A-frames connecting the core engine and the bypass duct. In normal operation the fail-safe mount does not transmit loads between the engine ...

Auxiliary power unit inlet

Patent Number: 8444083
Publication Date: 2013-05-21
Inventor:

An aircraft auxiliary power unit assembly includes an aircraft skin providing a cavity. The aircraft skin is secured to a structure in an assembled condition and provides an opening. An auxiliary power unit is arranged within the cavity and secured to the structure. The aircraft skin substantially covers the auxiliary power unit in the assembled condition. An inlet duct is removably secured within the opening and is selectively connected to the auxiliary power unit between installed and ...

High performance ‘X’-configuration airplane for storage and launch from a tubular container

Patent Number: 8444082
Publication Date: 2013-05-21
Inventor:

An air vehicle can be folded into or unfolded from a compact tubular storage container without assembly or disassembly of the air vehicle. The air vehicle includes a fuselage, two aerodynamic surfaces rotatably mounted on the fuselage along a common axis with at least one pivot mechanism, and at least one spring mechanism configured to deploy the aerodynamic surfaces so they extend outwardly from the body. In a stowed configuration, both aerodynamic surfaces are parallel to the fuselage for ...

High voltage flying apparatus employing multiple motors

Patent Number: 8444081
Publication Date: 2013-05-21
Inventor:

A flying apparatus having a frame configured to couple to a high voltage tether system, and at least one motor module mounted to the frame, the module including a holding structure attached to the frame, a rotating structure, including a rotor shaft, configured to rotate relative to the holding structure, a rotor attached to the rotor shaft and a plurality of motors attached to the holding structure, each including a drive shaft configured to engage with the rotor shaft, wherein the motors ...

Aircraft having offset telescopic wings

Patent Number: 8439314
Publication Date: 2013-05-14
Inventor:

An aircraft includes a fuselage, a first wing, and a second wing. The first wing and the second wing each have at least two wing panels, where the at least two wing panels of each wing are telescopically related to one another for movement between an extended position and a retracted position. The first wing and the second wing are both connected to the fuselage and are positioned with respect to the fuselage such that the first wing is offset with respect to the second ...

Forward swept winglet

Patent Number: 8439313
Publication Date: 2013-05-14
Inventors: ;

An aircraft may include a pair of wings. A forward swept winglet may be attached proximate to a wing tip of each wing. The forward swept winglet may include a leading edge and a trailing edge. The leading edge of each winglet may extend from the wing at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the ...

System and methods for simultaneous momentum dumping and orbit control

Patent Number: 8439312
Publication Date: 2013-05-14
Inventors: ;

The present system and methods enable simultaneous momentum dumping and orbit control of a spacecraft, such as a geostationary satellite. Control equations according to the present system and methods generate accurate station-keeping commands quickly and efficiently, reducing the number of maneuvers needed to maintain station and allowing station-keeping maneuvers to be performed with a single burn. Additional benefits include increased efficiency in propellant usage, and extension of the ...

Aerial refueling boom and boom pivot

Patent Number: 8439311
Publication Date: 2013-05-14
Inventor:

An aerial refueling boom may include a refueling boom assembly and a pivot assembly for attaching the aerial refueling boom to a tanker aircraft. The refueling boom assembly may include a main boom section and a hollow telescoping boom section. The hollow telescoping boom section is adapted to be moved between a retracted position within the main boom section and an extended position extending from the main boom section for in-flight refueling of an aircraft. The pivot assembly may include ...

Aircraft presenting two pairs of wings and fuel tanks in fluid communication

Patent Number: 8439310
Publication Date: 2013-05-14
Inventors: ;

An aircraft comprises: a fuselage; a front pair of wings; a rear pair of wings; and a pair of bodies, each body interconnecting, at a distance from the fuselage, the front and rear wings that are situated on the same side of the ...

De-icer, a fixture and a method of adjusting the position of a de-icer

Patent Number: 8439309
Publication Date: 2013-05-14
Inventor:

A de-icer including a bracket arranged on a structural member and a de-icer module mounted on the bracket. The de-icer module is adjustable arranged on the bracket such that a position of the de-icer module is adjustable in relation to the bracket. Also a fixture and a method of adjusting a position of a ...

Spring loaded pressure relief door

Patent Number: 8439308
Publication Date: 2013-05-14
Inventors: ; ;

A pressure relief apparatus for an engine compartment having a wall and an opening in the wall is provided. The pressure relief apparatus includes a door panel arranged in blocking relationship to the opening in the wall of the engine compartment, a plurality of hinges coupling the door panel to an inner surface of the wall of the engine compartment, a spring assembly coupled between each hinge and the inner surface of the wall, wherein the spring assembly includes a canister having an open ...

Structural component with rib and cross member element

Patent Number: 8439307
Publication Date: 2013-05-14
Inventors: ; ; ; ; ;

The present invention provides a fuselage structure for an aircraft or spacecraft with an outer skin. The fuselage structure comprises a rib element for stiffening the outer skin and ad cross member element. Here the rib element is bent in the shape of an arc to correspond to an inner contour of the outer skin. The cross member element connects two arc sections of the rib element transversely to each other. The cross member element has a higher strength than the rib element. From another ...

Thermal management system with staged cooling

Patent Number: 8439306
Publication Date: 2013-05-14
Inventors: ; ;

A thermal management system comprises a first heat exchanger having an inlet and an outlet, a second heat exchanger having an inlet and an outlet, a fluid loop, a first heat pump, and a second heat pump. The fluid loop circulates a fluid, and forms a continuous path between the first and second heat exchangers. The first heat pump is connected to the fluid loop and is disposed between the outlet of the second heat exchanger and the inlet of the first heat exchanger. The second heat pump is ...

Non-handed thrust reverser for installation on handed aircraft gas turbine propulsion engines

Patent Number: 8439305
Publication Date: 2013-05-14
Inventor:

An assembly for an aircraft gas turbine propulsion engine includes an engine nacelle and a thrust reverser. The engine nacelle is configured to have at least a portion of an aircraft gas turbine propulsion engine mounted therein, and includes an intake end, an exhaust end, and an outer surface that extends between the intake end and the exhaust end. At least the engine nacelle outer surface proximate the exhaust end has a semicircular section and a noncircular section. The thrust reverser ...

Energy absorber system for an undercarriage, and an aircraft provided with said energy absorber system

Patent Number: 8439304
Publication Date: 2013-05-14
Inventors: ; ; ;

An energy absorber system (10) provided with a shock absorber (11) extending from a first end (12) suitable for being connected to a rocker arm (5) of an undercarriage (3) housed in a wheel bay (4), towards a second end (13). In addition, the system includes a fitting (20) connected to said second end (13), and guide means (30) for guiding said fitting (20) in translation that is suitable for being fastened to a ...

Retractable undercarriage for an aircraft

Patent Number: 8439303
Publication Date: 2013-05-14
Inventor:

An undercarriage for a rotary wing aircraft, includes a tubular structure (7) with skids, the tubular structure (7) being designed to be mounted under or in a bottom portion (4) of the aircraft, the undercarriage being characterized in that the tubular structure (7) includes left and right longitudinal portions that are retractable, each of which portions is suitable for moving between a retracted position in a cruising flight configuration and a deployed ...

Aircraft with at least two rudder units in a non central arrangement

Patent Number: 8439302
Publication Date: 2013-05-14
Inventors: ;

An aircraft has at least two rudder units in a non-central arrangement. The rudder units have a profile and are rigidly secured to the aircraft. The profile is adjusted in such a way as to yield an inflow at a positive geometric angle of incidence, so that the profile generates a lift force having a component pointing in the flight direction. This makes it possible to offset a portion of the aircraft ...

Systems and methods for deployment and operation of unmanned aerial vehicles

Patent Number: 8439301
Publication Date: 2013-05-14
Inventors: ; ;

An unmanned aerial vehicle (UAV) system provides for UAV deployment and remote, unattended operation with reduced logistics requirements. The system includes a launcher that can include one or more launch tubes, each launch tube configured to house a UAV in a canister and one or more gas generators operatively connected to each canister and configured to push the UAV out of the launch tube by releasing gas into the canister. A controller for activating the gas generators can sequentially, ...

Rear part of an aircraft comprising a structure for supporting engines, extending through the fuselage and connected thereto by at least one connecting rod

Patent Number: 8439300
Publication Date: 2013-05-14
Inventor:

A rear part of an aircraft, including a support structure for supporting engines, extending through the fuselage, through two openings distributed on either side of a vertical median plane of the aircraft. The support structure includes a first half-structure and a second half-structure respectively extending through the first and second fuselage openings, the first and second half-structures being joined to each other so that they can be disassembled in an inside space defined by the ...

Active cancellation and vibration isolation with feedback and feedforward control for an aircraft engine mount

Patent Number: 8439299
Publication Date: 2013-05-14
Inventor:

An engine mount structure is provided with active vibration mechanisms which are attached in the vicinity of the engine mount to prevent engine vibrations from propagating into the engine mounting structure, for example, the wing or fuselage structure of an aircraft. Additionally, sensors are provided on the engine and/or wing/fuselage structure to provide control signals to the active vibration mechanisms so that the active vibration mechanism react to the sensed data to minimize the ...

Device for shrouding an aircraft nacelle

Patent Number: 8439298
Publication Date: 2013-05-14
Inventors: ; ;

An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes:

a flexible element that follows the curved profile of the door between two remote anchoring points,

at least one safety index including a latch pivotable around an axis of ...

Air inlet for an aircraft turbine engine, an aircraft provided with such an air inlet, and a method of optimizing the operation of an aircraft turbine engine with the help of an air inlet

Patent Number: 8439297
Publication Date: 2013-05-14
Inventors: ;

The present invention relates to an air inlet (10) for a turbine engine (2) of an aircraft (1), the air inlet comprising an air delivery duct (20) defined by a side wall (21) and extended by a dynamic inlet duct (30), said dynamic inlet duct (30) extending along a dynamic axis (AX1) towards a front flow section (31), said dynamic inlet duct (30) being provided with a grid (40) for protection against ingesting ...

Aircraft huffer coupling adapter and methods of use

Patent Number: 8439296
Publication Date: 2013-05-14
Inventor:

An aircraft huffer coupling adapter comprises a flange assembly having one or more attachment members in communication with a flange ring via one or more strut members. The flange assembly is attached with a port end of an inner coupling of a huffer coupling via the one or more attachment members. The flange ring defines an inner diameter larger than an outer diameter of the huffer coupling, with at least one space between an inner wall of the flange ring and the outer diameter of the air ...

Aircraft engine inlet pivotable barrier filter

Patent Number: 8439295
Publication Date: 2013-05-14
Inventor:

An inlet barrier filter system for an aircraft engine includes a filter panel (35) including filter media for filtering air prior to intake (15) into the engine. The filter panel has a forward edge (F). The system further includes an actuator for selectively pivoting the panel to form an opening around the panel for allowing air to bypass the filter. The opening is rearward of the forward edge of the filter ...

High speed airship structure

Patent Number: 8439294
Publication Date: 2013-05-14
Inventor:

The structure provided multi-Levels of the center fuselage, two front wings, Extended mid-two wings and two rear wings with two vertical winglets.

The fuselage has a cross section of half circle shaped fuselage.

The first level comprises multi-fuel tanks, water tanks, Helium gas tanks, hydraulic, Pneumatic systems and plurality of the multi-landing gear bays and multi-cargo Compartments.

The first level comprises a top cockpit and the plurality of the multi-passenger ...

Projectile that includes a fin adjustment mechanism with changing backlash

Patent Number: 8436285
Publication Date: 2013-05-07
Inventor:

Some embodiments pertain to a projectile that includes a casing and at least one fin that extends from the casing. The projectile further includes a drive inside the casing and an adjustment mechanism inside the casing. The adjustment mechanism includes a first gear that engages the drive and a second gear that engages the fin and the first gear. The second gear includes teeth that are different distances from an axis of rotation of the second gear. The teeth of the second gear that engage ...

Cavity flow shock oscillation damping mechanism

Patent Number: 8436284
Publication Date: 2013-05-07
Inventors: ;

A pressure oscillation damping mechanism comprises a cavity having an entrance exposed to fluid flowing on an exterior of the cavity. The damping mechanism may include a constriction positioned adjacent to the entrance and being sized to dampen an amplitude of the pressure oscillations occurring within the ...

System and method for guiding and controlling a missile using high order sliding mode control

Patent Number: 8436283
Publication Date: 2013-05-07
Inventors: ;

Higher Order Sliding Mode (HOSM) control techniques are applied to the Guidance Control (G&C) of interceptor missile in which velocity may be steered by combination of main thrust, aerodynamic lift and lateral on-off divert thrusters, and attitude may be steered by continuous or on-off actuators. Methods include the pointing of the seeker, its associated estimation processes, a guidance law that uses concurrent divert mechanisms, and an attitude autopilot. The insensitivity of the ...

Air outlet system for aircraft leading edge

Patent Number: 8434724
Publication Date: 2013-05-07
Inventors: ; ;

An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges are arranged in at least two rows essentially parallel to the leading edge and in an offset manner for at least two consecutive rows. At least one block is inserted between two walls that form the aerodynamic surface. The block includes, on the one hand, an outside surface extending the ...

Low drag asymmetric tetrahedral vortex generators

Patent Number: 8434723
Publication Date: 2013-05-07
Inventor:

An asymmetric tetrahedral vortex generator that provides for control of three-dimensional flow separation over an underlying surface by bringing high momentum outer region flow to the wall of the structure using the generated vortex. The energized near-wall flow remains attached to the structure surface significantly further downstream. The device produces a swirling flow with one stream-wise rotation direction which migrates span-wise. When optimized, the device produces very low base drag ...

Skydiving equipment to distribute the tension forces of a drogue parachute

Patent Number: 8434722
Publication Date: 2013-05-07
Inventor:

A skydiving equipment with a drogue parachute to capture the deployment bag until the opening, and to suspend the parachutist(s) in a horizontal position during the free fall, while distributing the tension forces of the drogue parachute such that the ripcord operation is effortless, includes a first fastening strap bearing a lower tab and a second fastening strap bearing an upper tab to fasten the drogue parachute drogue bridle to the parachute pack at the desired level of the main ...

Aircraft tank system and method for refueling an aircraft using an eration/deaeration device with a shut-off valve

Patent Number: 8434721
Publication Date: 2013-05-07
Inventors: ; ; ;

An aircraft tank system includes a tank cell for receiving fuel, a fuel line that connects the tank cell to a fuel inlet connection, and an aeration/deaeration device that for aeration/deaeration of the tank cell connects the tank cell to the environment. A shut-off valve of the aeration/deaeration device is adapted in an open position to open a connection between the tank cell and the environment and in a closed position to interrupt the connection between the tank cell and the ...

Pressurised aircraft door equipped with a vent flap

Patent Number: 8434720
Publication Date: 2013-05-07
Inventor:

The invention relates to a pressurized aircraft door that minimizes risk of ingress of precipitation inside the aircraft, while maintaining venting of the aircraft before unlocking the door. The purpose of the invention is achieved using a vent flap controlled by a door control member and designed such that the flap successively occupies the following positions during the opening movement of the control member: a closed position when the control member occupies a first end position putting ...

Leading edge element of aircraft, method for manufacturing one, wing and stabilizer

Patent Number: 8434719
Publication Date: 2013-05-07
Inventor:

A leading edge element, a method for manufacturing one, and an aircraft wing and stabilizer furnished with the leading edge element. The leading edge element is an elongate piece that comprises a skin plate and at least one longitudinal stiffener. The shape of the front edge of the skin plate is closed and the tail edge is open. The stiffener is fastened between the inner surfaces of the skin plate. Between the inner surface of the skin plate of the outermost longitudinal stiffener, there ...

Reusable rotorcraft bumper, and a rotorcraft having such a bumper

Patent Number: 8434718
Publication Date: 2013-05-07
Inventor:

A reusable bumper (10) for a rotorcraft (1) suitable for protecting a rear end (3) of said rotorcraft (1). The bumper (10) comprises a resilient outer shell (20) forming a first chamber (11) having a resilient inner shell (30) placed therein and forming a second chamber (12), said outer shell (20) having at least one main orifice (21), said inner shell (30) being provided with management means (50) ...

Aircraft front portion including a concave bulkhead separating a non-pressurized radome area and a pressurized area

Patent Number: 8434717
Publication Date: 2013-05-07
Inventors: ;

An aircraft front portion includes a sealed bulkhead separating a non pressurized radome area from a pressurized area. The sealed bulkhead is delimited by two surfaces opposite to each other, one being substantially concave when seen from the radome area and the other being substantially convex when seen from the pressurized ...

Compliant crown panel for an aircraft

Patent Number: 8434716
Publication Date: 2013-05-07
Inventors: ;

An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the ...

Nested fairing thrust reverser

Patent Number: 8434715
Publication Date: 2013-05-07
Inventors: ;

A thrust reverser nozzle for a gas turbine engine nacelle includes opposite and asymmetrically pivoting first and second doors defining a nacelle aft section, first and second trailing edges of the first and second doors adjacent to a propulsive jet nozzle outlet of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge is positioned behind the second trailing edge when the doors are in the deployed position, ...