171 results about "Nose cone" patented technology

A friction stir additive welding device configured to join a first work-piece and second work-piece is provided. In one aspect, the device includes a nosecone including a channel extending along a central axis and configured to receive a rotating screw. The device also includes a slot including a first opening in an outer sidewall of the nosecone, a second opening in a wall of the channel of the nosecone, and a passageway through the nosecone between the first opening and the second opening. The slot is configured to receive a portion of a structure positioned between the first work-piece and the second work-piece.

A friction stir additive welding device configured to join a first work-piece and second work-piece is provided. In one aspect, the device includes a nosecone having a sidewall extending from a first end to a second end, a channel extending from the first end to the second end along a longitudinal axis of the nosecone, and a screw positioned within the channel. The first end is configured to couple the nosecone to a robotic arm and the second end has a surface configured to be advanced along a weld line between the first and second work-pieces. A central axis of the screw defines an angle that is less than 90 degrees relative to a plane that is perpendicular to surfaces of the first and second work-pieces as the surface of the nosecone advances along the weld line.

The invention discloses an anchoring device and an aerostat anchoring and releasing method. The anchoring device comprises an anchoring tower body, a nose cone, a guide assembly and a winding assembly. The nose cone is arranged at the top of the anchoring tower body through the mounting frame, is located on the mounting frame and can be opened and closed relative to the mounting frame so as to be switched between a release state and a locking state; the guide assembly comprises a rail and a sliding block arranged on the rail in a sliding mode, and the rail inclines downwards from the end, provided with the nose cone, of the installation frame and extends to the bottom of the anchoring tower body to form a triangular structure with the anchoring tower body. The winding assembly comprises a pull rope and a locking block fixed to the pull rope, and the pull rope is connected to the two ends of the sliding block so as to drive the sliding block to reciprocate along the track. A driving channel is formed in the center of the nose cone, the pull rope penetrates through the driving channel, and the locking block can move along the track along with movement of the pull rope and gradually enter the driving channel to push the nose cone to enable the nose cone to be converted into a locking state from a releasing state so as to lock the aerostat.

The present invention discloses a porous material transpiration cooling leading edge structure, which includes multiple layers of porous material layers and a cooling cavity provided on one side of the multiple layers of porous material layers. A coolant supply channel is provided in the cooling cavity, and the coolant supply channel is used to supply coolant to the cooling cavity. The multiple layers of porous material layers include an outer layer, an intermediate layer, and an inner layer, and the material of the inner layer is a shape memory alloy porous material. The present invention can adaptively adjust the porosity of the porous material, automatically adjust the usage amount of the coolant, effectively improve the usage efficiency of the coolant, and further enhance the thermal protection effect in the high-temperature tip region. Moreover, the shape memory alloy material can be reused. The porous material transpiration cooling leading edge structure can be used for structures such as the nose cone of an aircraft, the leading edge of a rudder, and the leading edge of a wing that are subjected to more high-temperature heat fluxes.

The invention discloses an aircraft nose cone. The aircraft nose cone comprises a cone section, a first connecting part, a second connecting part and a movable part. The plurality of cone sections are connected in sequence to form a nose cone; a plurality of first connecting parts and a plurality of second connecting parts are arranged on every two adjacent cone sections at intervals in the circumferential direction of the cone sections, and the first connecting parts and the second connecting parts are in one-to-one correspondence; one end of the movable part is hinged with the first connecting part, and the other end of the movable part is connected with the second connecting part through a universal joint; wherein the movable part is suitable for deforming to drive the two adjacent cone sections to move relatively so as to drive the nose cone to deform. According to the aircraft nose cone, under the condition that the structure is simplified, the deformation stability and flexibility of the nose cone can be guaranteed, and any-angle deformation of the nose cone is achieved.

The invention belongs to the field of embedded atmosphere data system fault identification and elimination calculation, and particularly relates to a flying wing aircraft seven-pressure-measuring-point embedded atmosphere data system fault identification and calculation method, which comprises the following steps: step 1, pressure measuring points are grouped: each group of pressure measuring points comprises nose cone lower surface pressure measuring points, left and right symmetrical pressure measuring points and upper and lower symmetrical pressure measuring points, the pressure measuring points are used for solving the attack angle alpha and the sideslip angle beta, one pressure measuring point is reused, the pressure measuring points are divided into four groups under different attack angles, and each group of pressure measuring points is composed of four pressure measuring points; step 2, identifying the fault type of the pressure measuring point and the fault point: according to the attack angles alpha 1, alpha 2, alpha 3 and alpha 4, the sideslip angles beta 1, beta 2, beta 3 and beta 4 obtained by resolving the four groups of pressure measuring points under different attack angles, and the pressure measuring point used for resolving the attack angle alpha and the sideslip angle beta, identifying the fault type of the pressure measuring point, and further identifying the fault point; and step 3, removing fault points, and calculating and outputting atmospheric parameters including an attack angle alpha and a sideslip angle beta.

A method of directing particles entrained within an airflow disposed to enter a gas turbine engine of an aircraft is provided. The gas turbine engine includes a nose cone, a fan section, a compressor inlet, a compressor section, and a turbine section. The nose cone is fixed for rotation with the fan section. The method includes: providing an entrained particle removal (EPR) system configured to inject a fluid outward from the nose cone from a plurality of nozzles engaged with the nose cone, wherein the nozzles are spaced apart from one another around a circumference of the nose cone; and controlling the EPR system to inject the fluid from the plurality of nozzles into the airflow. The particles wetted by the injected fluid are subject to centrifugal force in and aft of the fan section and are directed radially outward of the compressor inlet.

An assembly for an aircraft propulsion system includes a propulsor and an imaging assembly. The propulsor includes a propulsor disk, a plurality of propulsor blades, and a nose cone. The plurality of propulsor blades are circumferentially distributed about the propulsor disk. Each propulsor blade of the plurality of propulsor blades extends radially between and to a root end and a tip end. The root end is disposed at the propulsor disk. The propulsor disk and the plurality of propulsor blades are configured to rotate about the rotational axis. The nose cone is disposed axially adjacent the propulsor disk. The imaging assembly includes an imaging device disposed on the nose cone. The imaging device includes a camera. The camera is configured to capture image data of each propulsor blade of the plurality of propulsor blades as the plurality of propulsor blades rotate about the rotational axis.

According to the active thermal protection and thermal power generation integrated system based on the supercritical Brayton cycle, the two active cooling modes of convection cooling and sweating cooling are combined, and the energy utilization rate is increased; according to the gradient cooling structure of the nose cone front edge of the high-speed aircraft, the nose cone front edge is divided into a top end section, a middle section and a low end section, heat flows of the three sections are sequentially decreased, and porous metal matrix layers are arranged on the three sections of the nose cone front edge in a gradient mode according to the porosity; a two-stage regenerative-shunt recompression closed Brayton cycle power configuration obtained through calculation and optimization is adopted, and the characteristics of high energy recovery efficiency and compact system structure of the closed Brayton cycle are achieved; and a wing rib array is arranged in the heat exchange channel, so that a larger heat exchange surface area is provided.

A payload container includes a nose cone electronics hub assembly, a collar assembly, a canister assembly, and a grid fin system. The nose cone electronics hub assembly has a nose cone housing electronic components in support of flight and detonator systems. The collar assembly includes a collar coupling the nose cone electronics hub and canister together. A canister of the canister assembly houses separate parts when in a shipping configuration that can be attached to an exterior of the payload container in a deployment configuration. A fin assembly facilitates vertical descent of the payload container when dropped from an unmanned aircraft.

The invention relates to a cross-medium aircraft variant nose cone with dynamically adjustable surface wettability, and belongs to the field of cross-medium aircrafts. Comprising a variant skeleton and a flexible skin. Under the heating condition, the variant framework can drive the flexible skin to deform, the flexible skin keeps the deformed state after normal temperature is recovered, and therefore curvature distribution and section characteristics of the nose cone structure are changed. The surface of the flexible skin is covered with a wettability intelligent response coating. After the wettability intelligent response coating is irradiated by ultraviolet rays, the surface wettability can be converted into a super-hydrophilic state, and the wettability intelligent response coating can be recovered into a super-hydrophobic state after being heated. The head configuration and the surface wettability layout of the cross-medium aircraft are adjusted according to the specific water entry working condition, the hydrodynamic force and the hydrodynamic moment borne by the aircraft in the water entry process are changed through the influence effect of the configuration and the surface wettability on water entry cavitation evolution, the impact load is reduced as needed, and the attitude and trajectory stability is improved; the purposes of being compatible with various launching platforms and guaranteeing the water entry efficiency and safety are achieved.

The invention discloses a tungsten-containing ultrahigh-temperature high-entropy rare earth boride ceramic material as well as a preparation method and application thereof. The preparation method of the tungsten-containing ultrahigh-temperature high-entropy rare earth boride ceramic material comprises the following steps: 1) preparing a green body from metal oxide powder and boron carbide powder; 2) performing electric field sintering, crushing and screening on the green body to prepare tungsten-containing ultrahigh-temperature high-entropy rare earth boride ceramic powder; and 3) pressing the tungsten-containing ultrahigh-temperature high-entropy rare earth boride ceramic powder into a green body, and then carrying out spark plasma sintering. The tungsten-containing ultra-high-temperature high-entropy rare earth boride ceramic material has excellent ultra-high-temperature oxidation resistance, is wide in component space range and low in cost, has a very wide application prospect in ultra-high-temperature thermal protection components such as the leading edge, the nose cone and the control surface of a hypersonic aircraft, and has a wide application prospect. And the preparation method has the advantages of simple operation and process flow, short reaction time, low synthesis cost and the like, and is suitable for large-scale industrial production.

An assembly for an aircraft propulsion system includes a propulsor and an imaging assembly. The propulsor includes a propulsor disk, a plurality of propulsor blades, and a nose cone. The plurality of propulsor blades are circumferentially distributed about the propulsor disk. Each propulsor blade of the plurality of propulsor blades extends radially between and to a root end and a tip end. The root end is disposed at the propulsor disk. The propulsor disk and the plurality of propulsor blades are configured to rotate about the rotational axis. The nose cone is disposed axially adjacent the propulsor disk. The imaging assembly includes an imaging device disposed on the nose cone. The imaging device includes a camera. The camera is configured to capture image data of each propulsor blade of the plurality of propulsor blades as the plurality of propulsor blades rotate about the rotational axis.

The invention discloses a cylindrical ejection folding multi-rotor unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. Comprising a machine head, a machine body, a machine arm folding assembly and a folding foot stool, and the machine head comprises a nose cone and an upper-layer bottom plate connected to the lower portion of the nose cone; the fuselage is a shell connected to the lower portion of the upper-layer bottom plate, the arm folding assembly comprises multiple arms and arm mounting assemblies, the tail ends of the arms are rotationally connected with the fuselage in a folded mode through the arm mounting assemblies, and the folding foot stools are rotationally connected with the fuselage in a folded mode through foot stool mounting assemblies. In a non-operation state, the vehicle arms can be folded and put into the launch canister, the space occupancy rate of storage and transportation is reduced, after the unmanned aerial vehicle is launched through the launch canister, the vehicle arms are rapidly and automatically unfolded under the action of the torsional springs and are limited, the attitude of the unmanned aerial vehicle is adjusted, stable flight, rapid response and specific task execution are achieved, and the unmanned aerial vehicle is convenient to use. The method has the advantages that the low-altitude field can be quickly deployed to preempt the low-altitude air control right; and the requirements of ejection launching in a specific environment are met.

The utility model relates to the technical field of steel rolling equipment, in particular to a wire coil collecting and collecting device capable of reducing head scratches of wire coils, which comprises a coil collecting drum, a nose cone, a temporary coil supporting arm, a lifting coil supporting plate and a core rod, and is characterized in that a lifting support for lifting the wire coils is arranged on the lifting coil supporting plate; a winding drum notch for preventing the winding drum from interfering with the lifting support is formed in the lower part of the winding drum; a heightening support corresponding to the lifting support in height is arranged at the lower part of the core rod; the lifting support is fixedly connected with the lifting coil supporting plate through a plate inserting pin; the heightening support is fixedly connected with the core rod through the inserting plate pin; and a pin opening for the insertion plate to pass through is formed in the insertion plate pin. According to the utility model, by introducing the lifting support, the wire coil is lifted up after reaching a preset height, so that the bottom of the wire coil is prevented from being contacted with the temporary coil supporting arm, and the problems of falling impact and head scratch possibly occurring when the wire coil is separated from the temporary coil supporting arm in the prior art are solved.

A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and / or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

The present invention discloses a nose cone mooring structure for an airship without a rigid frame, comprising a base, a bottom ring, straight beams, and arc beams. The base is provided with several straight beams, and the ends of the straight beams away from the base are connected to the arc beams via a four-way structural member. The arc beams are provided with through slots that cooperate with fixing loops on the airship capsule. The bottom ring is provided between the four-way structural members. The nose cone mooring structure for an airship without a rigid frame of the present invention provides a simple nose cone fixing and mooring method for mooring an airship without a rigid frame. This solution can evenly distribute the tension during the mooring of the airship, does not require special reinforcement of the airship capsule material, and does not significantly increase the amount of capsule material used. At the same time, the nose cone can also ensure that the head portion, which is subject to greater air resistance, does not deform during the flight of the airship, thereby increasing the flight resistance.

The present invention provides a deformable heat exchange pipeline for a variable nose cone of an aircraft, comprising a main contraction heat exchange pipeline and a main extension heat exchange pipeline fixedly installed on the surface of the variable nose cone; both the main contraction heat exchange pipeline and the main extension heat exchange pipeline include a non-deformable unit, a telescopic deformation unit and a bending deformation unit, and each unit is connected by a plug-in transition pipe with a bending angle, and its deformation follows the follow-up deformation of the variable nose cone; the non-deformable unit is a pipeline with a hexagonal cross-section; the telescopic deformation unit is composed of a multi-stage sleeve structure; the bending deformation unit adopts a flexible Yoshimura origami structure; the bending deformation unit of the main contraction heat exchange pipeline is in the extended limit state; the bending deformation unit of the main extension heat exchange pipeline is in the contracted limit state. The present invention actively reduces heat by arranging a heat exchange pipeline on the surface of the aircraft, and uses the waste heat on the surface of the aircraft to preheat the fuel working medium, realizing the reuse of heat energy while protecting the safety of the internal equipment of the aircraft.

A cryogenic insulated pipe having a conformally-bonded aerogel paper layer on an outer surface of the pipe. The conformally-bonded aerogel paper layer is conformally-bonded to the pipe outer surface in a pre-applied resin layer. An insulative blanket is applied over the aerogel paper, and a breathable protective layer is applied over the insulative blanket. Also disclosed is a cryogenic fuel tank for retrofitting a conventional fossil fuel-powered aircraft, or for a purposely built aircraft to run on hydrogen has an aerodynamically shaped outer surface including an ogive shaped nose cone, and a tapered tail cone, wherein the tapered tail cone includes actively adjustable elements for adjusting aerodynamic characteristics of the cryogenic fuel tank. The cryogenic fuel tank is configured to be attached below wings of the aircraft, through support pylons, which include sensors configured to measure forces applied by the cryogenic fuel tank to the airframe. The cryogenic fuel tank includes a nozzle and valve configured to vent gas from the cryogenic fuel tank by expansion through the nozzle in the event that the cryogenic fuel tank is j ettisoned from the aircraft.

The invention relates to the technical field of target projectiles, in particular to a multipurpose high-speed target projectile modified based on retired equipment, which comprises a retired rocket projectile shell, a simulated infrared characteristic module, a connecting screw and an RCS characteristic simulation module, the retired rocket projectile shell comprises a simulated combat cabin, a front engine, a rear engine, a projectile tail stabilizing mechanism and a spray pipe, the simulated warhead cabin is located at the front end of the retired rocket projectile shell, the end of the simulated warhead cabin is arranged to be a wave-transparent head cover, the connecting screw piece is located at the middle end of the simulated warhead cabin, the wave-transparent head cover is connected to the connecting screw piece, and the simulated infrared characteristic module and the RCS characteristic simulation module are both in threaded connection with the connecting screw piece. The infrared characteristic simulation module and the RCS characteristic simulation module are located at the two ends of the connecting screw piece respectively, the infrared characteristic simulation module comprises an illumination torch located in the simulated combat cabin, and the RCS characteristic simulation module comprises a Luneberg ball base and a Luneberg ball. The method has the advantage of being convenient for troop training.

A multifunctional integrated Mars reentry detector relates to the technical field of Mars detection and mainly comprises a detector body, a rotor wing, a nose cone cover, a rotating device, a heat shield and the like. During launching, the rotor wings are in a compressed and folded state, and the detector body, the nose cone cover and the heat-proof cover serve as a whole device fairing. In the initial stage of reentry, the heat shield is used for protecting the rotor blade from pneumatic heating, can be further unfolded to a certain angle after descending at a certain speed, and serves as a speed brake for further speed reduction. And when the speed is reduced to subsonic speed, the rotor blades are unlocked and released, the blades are unfolded through an internal telescopic mechanism, the blades are driven to rotate by utilizing relative incoming flow, and rotation kinetic energy is converted into electric energy to be stored while lift force is provided for deceleration. In the landing stage, the rotor wings are switched to an active working mode, stored electric energy is used for providing rotating power for the rotating device, and autonomous hovering and obstacle avoidance are achieved; and the heat shield is completely unfolded to provide stable support and buffer for the detector body.

The present invention provides a fully automatic gluing and pressing device for the nose cone of an active touch pen, comprising a body, a gluing module, a pressing module, and a curing module; the pen tip clamping assembly of the pressing module comprises a movable bracket seat, a clamping bracket rotatably connected to the bracket seat, and a three-claw cylinder provided on the clamping bracket. When the clamping bracket rotates, the gluing needle of the gluing module can evenly apply the glue on the pen tip clamped by the three-claw cylinder along the circumferential direction. The operation is convenient, the gluing effect is good, and the safety is good. The pen tip loading assembly of the pressing module comprises a pen tip seat with a locating pin on the side and a floating pressure head for correcting and pressing the pen tip. When loading the pen tip, the locating pin and the locating hole can cooperate to ensure that the pen tip is inserted in a set posture and the alignment is accurate; the axis of the nose cone placement groove on the nose cone seat of the nose cone clamping assembly coincides with the axis of the three-claw cylinder. After the gluing is completed, the support seat can be moved to squeeze the pen tip into the nose cone. The pressing consistency is good and the yield rate is high.

A treatment device includes a housing having a longitudinal axis extending between a proximal end and a distal end, a striking element disposed within the housing and moveable along the longitudinal axis, a tip disposed adjacent the distal end, and a nose cone disposed about at least a portion of the tip, the tip being moveable within the nose cone.

The invention discloses a nose cone-shaped fluid director and a manufacturing method thereof. The fluid director comprises a fluid guiding cone used for bearing impact of fuel gas flow, a non-metal protective cover used for resisting ablation of high-temperature fuel gas flow is attached to the surface of a groove of the fluid guiding cone, the fluid guiding cone comprises a shield with a nose conical surface, the nose head end of the shield is located on the upstream of the fuel gas flow, and the nose tail end of the shield is located on the downstream of the fuel gas flow. The edge of the nose conical surface of the shield extends towards the left side, the right side and the downstream to form a base surface, and the shield and the base surface are integrally in a state of inclining from the upstream of a gas flow to the downstream of the gas flow; a framework is welded on the shield and the lower surface of the base surface; second supporting plates which are vertically arranged and used for preventing fuel gas flow from rushing out of the side edges are welded to the left side and the right side of the base face respectively, a front baffle which extends in the left-right direction and is vertically arranged is welded to the end face of the shield nose head, and the front baffle completely covers the end face of the shield nose head and is in a smooth inverted-V shape. The device is small in occupied area, few in parts and easy to maintain.

A snap fit nose cone comprising a body having a tapered nose and an edge with a snap fit lip configured such that the nose cone can be snapped into place on an inlet housing and such that the edge of the inlet housing abuts the edge of the inlet housing body.

An integrated unit for de-icing the propeller blades and the nose of a turbomachine including: a rotary transformer including a static part and a rotary part; a DC-to-AC voltage converter connected at its output to the static part of the rotary transformer and intended to be connected at its input to a DC electrical power supply, and a power switch connected to the rotary transformer and configured to transmit electrical power to at least one pair of propeller blades and to the nose cone of the turbomachine.

This invention discloses an integrated heat dissipation and power generation device for high-speed aircraft, comprising: a heat dissipation pulsating heat pipe arranged in the nose cone of the high-speed aircraft; the heat dissipation pulsating heat pipe includes an annular pulsating heat pipe condensation section, several U-shaped pulsating heat pipe evaporation sections, and two intermediate sections connecting each U-shaped pulsating heat pipe evaporation section to the annular pulsating heat pipe condensation section; at least one branch pipe communicating with the intermediate section is arranged at intervals between the two intermediate sections; a heat extraction pipe for heat exchange with the annular pulsating heat pipe condensation section of the heat dissipation pulsating heat pipe; and a power generation module for converting the heat energy acquired by the heat extraction pipe into electrical energy. This integrated device provides thermal protection for the aircraft while converting high-temperature aerodynamic heat into electricity, alleviating the aircraft's demand for onboard battery power, reducing the need for carrying cooling fluid, and improving energy utilization efficiency. It is of great significance for aircraft operating in harsh thermal environments for extended periods.

A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and / or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

A fluid purification system for purifying a fluid, such as air, within a fluid flow system, such as a heating, ventilation, and air conditioning system. The fluid purification system has a housing with a specular interior surface. An aerodynamic ultra-violet light module is retained by a framework within the housing to be surrounded by the specular interior surface. The light module has an aerodynamic intake nose cone adjacent to the first end of the housing and an aerodynamic exhaust tail cone adjacent to the second end of the housing. The nose and tail cones are eye-shaped, taper distally, and cooperate to retain a plurality of ultra-violet bulbs in an eye-shaped array that communicates longitudinally within the housing. The housing can be rectangular in cross section with upper and lower walls and opposed sidewalls. Each wall can have a concave inwardly-facing surface operative to focus ultra-violet light within the housing.

The utility model relates to a delivery device and assembly. A delivery device comprises: a handle comprising a body and a nose cone positioned distally of the body, wherein the nose cone comprises at least one axial flow channel extending from an inner surface of the nose cone; a spine positioned within the body of the handle, the spine including a lumen; a shaft positioned within the lumen of the spine, the shaft extending distally from the handle; and a ridge extension positioned within the nose cone and coupled to the ridge, the ridge extension at least partially surrounding the shaft, the ridge extension including a radial protrusion, wherein each of the radial projections includes one or more mating features defining at least one slot corresponding to the at least one axial flow passage of the nose cone.