45 results about "Catapult" patented technology

Launcher system with apparatus and methods for a toy projectile blaster removably interfaced with shoulder or butt stock receptacle hopper for multiple additional projectiles, user operable providing a hopper receptacle passageway in alignment with a firing projectile launching element to a projectile launching barrel for discharging projectiles. The pre-firing area allows projectile rounds to be received, while coupling the hopper stock projectiles magazine holds projectiles located distally along an upper portion of the pre-firing area for communication to outwardly launch the received projectile rounds. A user operable barrier at the hopper stock projectiles magazine receptacle opens and feeds by gravity into the pre-firing area The hopper stock projectiles magazine receptacle tilts towards the breech for feeding received projectile received into the pre-firing area.

The utility model provides a folding type catapult rack device for assisting takeoff of a flapping-wing unmanned aerial vehicle. The folding type catapult rack device comprises a track bottom plate, a guide rail, a guide rail shaft, a folding supporting and fixing assembly, a lifting table, a tripod supporting assembly, a lock catch fixing assembly, a catapult spring, a catapult baffle and a stop block spring. A guide rail and a guide rail shaft are arranged on the front face of a rail bottom plate, so that an ejection spring drives a lock catch fixing assembly to make contact with an ejection baffle, and kinetic energy is provided for takeoff of the flapping-wing unmanned aerial vehicle; the lifting platform is arranged at one end of the reverse side of the track bottom plate, the tripod supporting assembly is arranged at the other end of the reverse side of the track bottom plate, the mounting groove is formed in the upper portion of the folding supporting and fixing assembly, and the mounting hole matched with the mounting groove is formed in the lifting platform so that the height between the track bottom plate and the ground can be adjusted, and therefore the inclination angle of the track bottom plate can be adjusted. And the inclination angle of the lock catch fixing assembly is adjusted, so that the flapping-wing unmanned aerial vehicle has a proper take-off inclination angle.

To safely remove arching during operation of a combustion plant equipped with a boiler, without damaging the hopper below the boiler. [Solution] The removal system 1 includes a projectile launcher 22 that launches projectiles towards an arching formed by fly ash 21 that has fallen from the flue 5 into the boiler lower hopper 16 through an opening 23 formed in the wall surface of the boiler lower hopper 16, and a temperature sensor 26 that measures the temperature of the outer or inner surface of the boiler lower hopper 16 below the arching and near the hopper outlet 17, or the outer or inner surface of the falling fly ash transfer device 18 near the hopper outlet 17, or the outer or inner surface of the piping 28, and a pressure sensor 25 that measures the air pressure inside the falling fly ash transfer device 18, or either one or both. The control device 29 launches projectiles from the projectile launcher 22 during the operation of the combustion plant 2 based on the temperature information measured by the temperature sensor 26 or the air pressure information measured by the pressure sensor 25.

A catapulting assembly comprises a catapulting guide rail, a first catapulting device and a catapulting carrier, the catapulting guide rail comprises a first end and a second end opposite to the first end, the catapulting carrier is used for loading a machine body to be catapulted, and the catapulting carrier can slide between the first end of the catapulting guide rail and the second end of the catapulting guide rail. The first ejection device is arranged at the first end of the ejection guide rail, the first ejection device can drive the ejection carrier to slide from the first end of the ejection guide rail to the second end of the ejection guide rail through elastic force, and the ejection carrier can release the machine body to be ejected when sliding to the second end of the ejection guide rail.

1. Name of the product in this design: Cat Climbing Frame (Rocket). 2. Purpose of this design: The main purpose of this design is for cats to rest and play with. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

A projectile launcher may comprise a magazine configured to receive one or more cartridges. The magazine may comprise a body comprising a first end opposite a second end. The magazine may comprise a bore defining an opening through the body. The bore may be configured to receive a cartridge. The magazine may comprise an impact absorber positioned within the bore. In response to the bore receiving the cartridge, an axially forward surface of the cartridge may be configured to contact the impact absorber. The impact absorber may be configured to receive a force in response to a deployment of the cartridge.

The steam ejection device applied to the glider comprises a flying runway, a steam tank and an ejection system, two sliding grooves are formed in the flying runway, the ejection system is arranged below the flying runway, the ejection system comprises a sliding shuttle and two guide steel pipes arranged in parallel, and the sliding shuttle is connected with the steam tank. A guide groove is formed in the guide steel pipe, an open groove is formed in the pipe wall of the guide steel pipe, one end of the guide steel pipe is connected with the steam tank through an air pipe, a hydraulic buffer groove is formed in the other end of the guide steel pipe, a steam valve is arranged on the air pipe, and a piston is arranged at the lower end of the sliding shuttle. The piston is in sliding fit with the guide groove, a connecting plate is arranged at the upper end of the sliding shuttle, and the connecting plate penetrates through the sliding groove and is connected with a front wheel of the glider through a connecting rod. The utility model relates to the technical field of space flight and aviation.

This invention discloses a fire-fighting drone, comprising a fuselage and multiple aircraft mounted on the fuselage, including a probe head disposed on the fuselage; a magazine located on the fuselage for storing fire extinguishing bombs, with a bomb-dropping hole at the bottom of the magazine; a mounting slot located at the bottom of the fuselage; and a bomb-dropping mechanism disposed within the mounting slot. This fire-fighting drone provides high bomb-dropping accuracy and excellent fire-fighting effect. It employs a partially engaged gear and rack drive system combined with a spring energy storage mechanism to achieve catapult-style deployment of fire extinguishing bombs. The moment the partially engaged gear and rack disengage, the bomb-dropping tube rapidly resets under the elastic potential energy of the spring, using inertia to project the fire extinguishing bomb. This catapult method imparts a certain initial velocity to the fire extinguishing bomb, enabling it to fly along a specific trajectory towards the target fire point, effectively shortening the flight time of the fire extinguishing bomb.

This invention relates to the field of unmanned aerial vehicle (UAV) technology, and provides a self-locking device and method for a pneumatically launched foldable UAV. The device includes a locking baffle, a locking connector, a locking support, a button connector, a button support, and a locking button. The locking baffle is used for limiting the movement of the UAV arm. The locking connector connects the locking baffle and the button connector, and also connects to the locking support to form a rotating joint. The button connector passes through the button support and connects to the two locking connectors. The button support is coaxially assembled with the locking button, the fuselage connector, and the locking column, and is connected to the fuselage connector by bolts. The fuselage connector has a threaded hole in the middle, which is threadedly connected to the locking column. This invention achieves two working modes of the self-locking mechanism by adjusting the position of the locking button: when the locking button is in the relaxed state, the arm can be folded to achieve the self-locking function; when the locking button is in the locked state, the arm can automatically unfold under the action of a spring.

The invention provides a miniature unmanned aerial vehicle catapult canister and a control method thereof. The miniature unmanned aerial vehicle catapult canister comprises a catapult canister body; the spring is arranged in the ejection cylinder body; the unmanned aerial vehicle bottom support is connected with the spring; the stay wire is connected with the unmanned aerial vehicle bottom support; the ratchet wheel is matched with the pull wire, the bobbin is connected with the ratchet wheel, and the electric push rod is used for locking the ratchet wheel. The unmanned aerial vehicle bottom support can move in the ejection cylinder body in the axial direction, one end of the spring is fixed to the ejection cylinder body, the other end of the spring is connected with the unmanned aerial vehicle bottom support, one end of the pull wire is fixed to the unmanned aerial vehicle bottom support, the other end of the pull wire is wound around the wire shaft, a clamping block is arranged at the output end of the electric push rod, and the clamping block is connected with the ejection cylinder body. And the clamping block can be meshed with the ratchet wheel to lock the ratchet wheel. According to the invention, enough ejection energy can be provided for the miniature folding wing unmanned aerial vehicle under the condition of low space occupation.

The utility model provides a novel ejection toy which comprises a shell, a bullet capable of being contained in the shell and a control assembly used for locking and releasing the bullet, and the control assembly comprises a triggering piece and a locking piece. The triggering piece comprises a first rotating shaft rotationally connected to the shell, a triggering end and a pushing end, the triggering end and the pushing end are fixed to the first rotating shaft, and the triggering end is exposed on the shell; the locking piece comprises a second rotating shaft, a buckling end and a follow-up end, the second rotating shaft is rotationally connected to the shell, the buckling end and the follow-up end are fixed to the second rotating shaft, the buckling end is kept in buckling fit with the bullet through an elastic piece, the follow-up end is located on the rotating path of the pushing end, and when the follow-up end is pushed by the pushing end to rotate, the follow-up end is located on the rotating path of the bullet. And the buckle end rotates to be separated from the bullet. The ejection toy is more stable in structure, not prone to losing working capacity due to the influence of external force and higher in structural reliability and practicability.

This invention provides an artificial weather jamming device, including a launching body and a cluster cabin disposed on the launching body; the cluster cabin is provided with an installation and adjustment mechanism, and a plurality of sub-launchers are disposed on the installation and adjustment mechanism; wherein, the installation and adjustment mechanism includes: a main shaft disposed in the cluster cabin; a first adjustment group and a second adjustment group respectively disposed at both ends of the main shaft, and the plurality of sub-launchers are disposed on the first adjustment group and the second adjustment group; and a catapult device disposed on the main shaft and positioned between the first adjustment group and the second adjustment group; the artificial weather jamming device proposed in this invention can launch multiple sub-launchers simultaneously after a single launch, ensuring that a sufficient area can be reached after a single launch; avoiding multiple launches in the prior art, thereby reducing the launch difficulty and risk factor while saving manpower and time costs.

The utility model discloses an unmanned aerial vehicle ejection device, and relates to the technical field of unmanned aerial vehicles. The ejection frame comprises a supporting base, at least two supporting rods arranged in the width direction of the supporting base at intervals, and at least one cross beam arranged in the height direction of the supporting rods at intervals. Wherein the two ends of the cross beam are connected to the two supporting rods. At least one group of track assemblies are obliquely arranged on the two supporting rods in the launching direction of the unmanned aerial vehicle at a preset elevation angle, and each group of track assemblies comprises at least two guide rails which are arranged in parallel. The two ends of at least one elastic piece are connected to the sides, away from the supporting rods, of the two corresponding guide rails, and the middle of the elastic piece forms a traction section for hooking a hook of the abdomen of the unmanned aerial vehicle. And at least one executing mechanism is mounted at the top of the corresponding cross beam. One end of at least one locking piece is connected to a hanging ring of the abdomen of the unmanned aerial vehicle, and the other end is detachably connected to the output end of the corresponding executing mechanism. Through the collaborative design of the built-in elastic piece and the track assembly, an external anchor point is not needed, and the device can flexibly adapt to complex terrains.

A launch system and method for a launch vehicle that can save initial launch fuel includes a support structure, characterized in that: the support structure consists of a horizontal support frame (3) and an ascending section support frame (4), a horizontal track section (5) is installed on the horizontal support frame (3), an inclined track section (6) connected to the horizontal track section (5) is installed on the ascending section support frame (4), a launch acceleration pipe (10) is fixedly installed on the horizontal support frame (3) and the ascending section support frame (4), an electromagnetic catapult (14) is installed on the electromagnetic catapult slide rail (13), a rocket trolley (8) is installed on the horizontal track section (5) and the arc track section (6), and a rocket bracket (9) is provided on the rocket trolley (8). The present invention has a reasonable structure, can obtain sufficient initial velocity before launch ignition, can save launch fuel, can increase the effective payload, and is conducive to saving launch costs.

A projectile launcher may comprise a magazine configured to receive one or more cartridges. The magazine may comprise a body comprising a first end opposite a second end. The magazine may comprise a bore defining an opening through the body. The bore may be configured to receive a cartridge. The magazine may comprise an impact absorber positioned within the bore. In response to the bore receiving the cartridge, an axially forward surface of the cartridge may be configured to contact the impact absorber. The impact absorber may be configured to receive a force in response to a deployment of the cartridge.

The application discloses a catapult vehicle, a hydraulic system and a recoil force transmission control method, and adopts a sliding block, a storage and transportation ammunition box, a sliding frame, a sliding oil cylinder, an erecting frame, a pitching oil cylinder, a rotary table, a base and a sliding guide rail, the storage and transportation ammunition box is installed on the sliding frame, the sliding guide rail is connected on the upper surface of the erecting frame through bolts, the sliding block is connected on the lower surface of the sliding frame through bolts, and the sliding guide rail and the sliding block form a sliding pair through mutual cooperation; the piston cylinder end hinge base of the sliding oil cylinder is connected on the erecting frame, the piston rod end of the sliding oil cylinder is connected with the sliding frame, and the sliding frame is driven to slide relative to the erecting frame through the extension and contraction of the sliding oil cylinder; the two ends of the pitching oil cylinder are connected with the rotary table and the erecting frame respectively; the rotary table is installed on the base, and the erecting frame is hinged with the rotary table. The whole vehicle has high lightweight degree, and has strong recoil force buffering capacity.

The application discloses a locking device for the tail end of an energy accumulator of a UAV (unmanned aerial vehicle) pneumatic catapult system, which realizes reliable locking and unlocking of the tail end of the energy accumulator by optimizing the structural design of the locking device, and ensures the stability and safety of the catapult process. The device adopts a wedge-shaped self-locking matching structure between the tail end of a locking tongue and a locking link groove, and forms double limiting in combination with a safety pin, and has the characteristics of anti-vibration and anti-loosening, rapid unlocking response and high safety coefficient. The application can effectively improve the reliability and efficiency of the UAV catapult system, is suitable for the locking of the energy accumulator in the UAV pneumatic catapult system, and provides important technical support for the efficient deployment of the UAV.

This application discloses a projectile toy, comprising: a central plate, multiple control plates, and an actuating element. The central plate has a central groove and multiple passageways, each passageway being arranged sequentially at intervals around the circumference of the central plate and connecting to the central groove. Each control plate is arranged sequentially around the circumference of the central plate, and each control plate includes a plate body and a projectile element. The plate body has an operating groove and a side opening connecting to the operating groove. The projectile element is disposed on the plate body, and the plate body is detachably connected to the central plate. The projectile element can launch the actuating element, propelling the actuating element into the central groove. This projectile toy, by arranging multiple detachably connected control plates sequentially at intervals around the circumference of the central plate, breaks the limitations of existing products in terms of the number of participants, meeting the needs of simultaneous multi-person interaction. It also allows for flexible adjustment of the number of control plates based on the actual number of participants, adapting to different usage scenarios. Furthermore, it facilitates storage and transportation, and allows for independent repair and replacement of individual faulty control plates, reducing usage costs and significantly improving the product's practicality, flexibility, and fun.

The utility model discloses a rockfill dam compaction quality detection device based on compressed air ejection, including air compressor, support frame, pneumatic catapult and drop hammer, and air compressor provides high pressure air to pneumatic catapult through high pressure gas pipeline, makes drop hammer obtain greater ejection initial velocity, does not need too high device and too heavy drop hammer, can make drop hammer reach predetermined kinetic energy, has reduced the height and drop hammer's quality of device, has reduced the cost, the volume and weight of device, in addition device can dismantle, the carrying and shift of convenient device have been improved work efficiency.

The application discloses a kind of air bag type phase change cold catapult device and method, air bag type phase change cold catapult device includes catapult frame, guide rail, adapter, catapult carrier, air bag, pressure relief valve and base, guide rail is installed in the inside of catapult frame, adapter is arranged on the inner wall of guide rail, catapult carrier and adapter are mutually fixed and can be linear motion along guide rail together, air bag lower side is installed on base, one side of air bag is equipped with pressure relief valve, when catapult operation, air bag is under the action of phase change high pressure gas and rapidly expands and pushes catapult carrier and makes linear motion along guide rail;After catapult is completed, phase change high pressure gas in air bag is discharged through pressure relief valve and is discharged to surrounding environment.The application discloses a kind of air bag type phase change cold catapult device and method, maintenance and use cost is low, and catapult concealment is good;It can be adapted to a variety of catapult carriers, and reliability is high.

A propulsion system for a projectile launcher may comprise a propulsion source, the propulsion source having a first end, a second end opposite the first end, and a propulsion source wall. A puncture structure having a fluid channel may be located proximate to the first end. A puncher may be located proximate to the second end and configured to translate the propulsion source from a first position to a second position. Translation of the propulsions source from the first position to the second position may fluidly connect the fluid channel and the propulsion source. The projectile launcher may be activated upon the propulsion source being fluidly connected to the fluid channel.

The utility model relates to the technical field of industrial processing, in particular to a polishing structure for ejection rod production, which comprises a bottom plate. The device further comprises a clamping assembly, supporting frames are connected to the left side and the right side of the bottom of the bottom plate, the clamping assembly is arranged on the rear side of the top of the bottom plate, and the clamping assembly comprises a sliding groove, a fixing block, a spring, a sliding block, a motor, an anti-skid wheel and an auxiliary wheel. A sliding groove is formed in the right side of the top of the bottom plate, a fixing block is connected to the left side of the bottom of the bottom plate close to the sliding groove, a spring is connected to the fixing block close to the sliding groove, and a sliding block is connected to the end, away from the fixing block, of the spring and slidably connected with the sliding groove. The clamping assembly is arranged, the ejection rod body is placed between the auxiliary wheel and the anti-skid wheel, the auxiliary wheel is extruded according to the size of the rod body, the auxiliary wheel drives the sliding block to slide in the sliding groove, the sliding block drives the spring to stretch, self-adaptive clamping can be carried out according to ejection rods of different sizes, and the problem that frequent adjustment is needed is solved; and the polishing efficiency is improved.

The utility model discloses a vacuum chamber positioning calibration structure for a rocket electromagnetic ejection track, which comprises a vacuum chamber and a fixed seat, the vacuum chamber comprises a plurality of vacuum pipelines which are sequentially spliced in a sealing way along the axial direction of the vacuum chamber, and any two adjacent vacuum pipelines are connected through a flexible pipe; the two ends, in the axial direction, of the flexible pipe are fixedly connected with the corresponding ends of the adjacent vacuum pipelines in a sealed mode respectively, and an axial supporting part and a radial supporting part are arranged on the outer wall face of each vacuum pipeline at intervals. The fixing base comprises a plurality of fixing frames which are sequentially and fixedly spliced in the height direction of the fixing base, and each fixing frame is fixedly arranged on the periphery of the corresponding vacuum pipeline in a sleeving mode and provided with an axial installation part and a radial installation part. An axial adjusting piece is arranged on each axial mounting part, and a radial adjusting piece is arranged on each radial mounting part, so that the fixing position of the vacuum pipeline relative to the fixing frame is adjusted in the axial direction and the radial direction. The device has the advantages of being simple in structure, convenient to install and adjust and good in sealing performance.

1. The name of the design product: three pulley bow. 2. The use of the design product: three pulley bow. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view.

This invention relates to a model buffer and capture device for land-based vertical catapult tests. The device, used to capture a model, includes a damping system and a capture system. The damping system absorbs energy and buffers during the capture process. The capture system, mounted on the damping system, includes a capture support with a buffer net at its top and a gripper system below the net for clamping and securing the model. A photoelectric proximity switch is also mounted on the capture support; when the switch detects an object passing through, it sends an electrical signal to control the gripper system. A launch tube, vertically positioned below the capture system, launches the model. This invention enables capture in vertical land-based catapult tests, allowing for safe, damage-free, and efficient model recovery after launch, thus improving test efficiency. The buffer system significantly reduces the load on the grippers during model capture, enhancing the overall system reliability.

The invention discloses an electromagnetic ejection system based on a rotating motor, and the system comprises a power source which is used for providing ejection energy; the ejection device comprises a pulley and is used for applying acceleration to a load; the dragging device is used for converting rotary driving force into linear traction force so as to drag the tackle; and the reset braking mechanism is used for decelerating / braking the dragging device after ejection and driving the tackle to return. The catapulting device, the dragging device and the reset braking mechanism are combined into an integrated mechanical link, and efficient energy conversion-stable driving force transmission-catapulting and reset integrated control is achieved. The structure not only technically overcomes the problems of long stator, high energy consumption, complex control and the like of an existing linear motor ejection system, but also has the advantages of light weight, maintainability and low cost in engineering, and the practical value and expandability of the system are remarkably improved.

The invention relates to the technical field of emergency lifesaving equipment, in particular to an ejection type window breaking device which comprises a columnar shell, a head cover capable of axially stretching and retracting relative to the shell is installed at one end of the shell, a percussion hammer capable of axially moving along the shell is arranged in the shell, a firing pin is installed at the end, close to the head cover, of the percussion hammer, and the end, close to the head cover, of the firing hammer is provided with an ejection rod. The end of the head cover is provided with a needle opening allowing at least part of the firing pin to pass through, an ejection device matched with the firing hammer is arranged in the shell, and after the ejection device is triggered, the firing hammer moves towards the needle opening. The head cover abuts against a head cover return spring which enables the head cover to have a reset trend after the head cover retracts into the shell, and the head cover return spring is arranged in the shell or arranged in the head cover. The invention at least provides an ejection type window breaking device which is easy to operate and rapid in window breaking.

This invention discloses a discrete pulse timing fitting control method for a complex power source series catapult launch, capable of controlling the mass flow rate of multiple small pulse engines. The method achieves consistency between the fitted mass flow rate curve and the theoretical fitting result, maintaining constant overload and stable operation of the missile during launch. The method includes the following steps: Step 1: Solve for the ideal overload using internal ballistics knowledge based on the required missile parameters. Step 2: Obtain the ideal pressure according to the dynamic equations. Step 3: Substitute the ideal pressure into the control equations to obtain the ideal engine mass flow rate. Step 4: Determine whether the interpolation between the ideal engine mass flow rate and the actual mass flow rate meets the requirements. If yes, return to Step 2; otherwise, proceed to Step 5. Step 5: Open a new release point; calculate the actual mass flow rate, and return to Step 2.

The invention relates to a disposable anchoring device for an offshore unmanned monitoring ship. The disposable anchoring device comprises an ejection anchoring device, a remote control winch and a positioning installation device. The ejection anchoring device comprises an anchorage device, a lead cylinder, a light anchor cable, an ejection mechanism, a locking mechanism and a throwing control cabin, the rear section of the anchorage device is inserted into the lead cylinder, the rear end of the lead cylinder is connected with the throwing control cabin, the front section of the ejection mechanism is located in the lead cylinder, the rear section of the ejection mechanism is located in the throwing control cabin, and the light anchor cable is wound on the remote control winch; the free end of the light anchor cable is connected with the anchorage device; the locking mechanism comprises an electromagnet assembly, a cover plate, a buckle hinge and a buckle, the buckle is installed on the throwing control cabin through the buckle hinge, one end of the buckle is fixedly connected with the cover plate, and the other end of the buckle is a lock hook which is separated from or hooked with the ejection mechanism. The invention further relates to an offshore unmanned monitoring ship. According to the automatic anchoring device, the functions of remote quick unlocking of the anchorage device, low-power-consumption instantaneous casting, remote control of recovery and anchor abandoning can be achieved, and the automatic anchoring device belongs to the technical field of automatic anchoring devices.