198 results about "Launch craft" patented technology

A shooting target launcher, associated components and methods. The launcher spins one or more helicopter-like shooting targets to launch the targets. A target connector receives the targets. The target connector is rotated about an axis of rotation to rotate the targets about the axis of rotation. The targets have fan blades that, when rotated, propel the target through the air.

The claimed invention discloses a catapult launcher for a fixed-wing unmanned aerial vehicle (UAV), the launcher comprises a starting rail having an I-beam cross-section that comprises two sections that are foldable / unfoldable and mounted on adjustable supports, a carriage that is equipped with wheels that are configured to interact with an internal surface and with an external surface of the starting rail and that is equipped with a UAV interaction mechanism that is represented by fasteners and joint elements that interact with adapters that are fixed to a UAV's fuselage and made in a form of two plates, and a lower edge of the plates is produced with grooves so as to enable interaction with the fasteners and with detents in a form of hooks that are tangent to joint elements. The launcher is equipped with elastic cords that are symmetrically arranged along the starting rail and fixed to the carriage and to the starting rail, and with a release device. A beginning of the starting rail is provided with an inclined section, and the release device joins to the carriage on the inclined section and the carriage to the UAV, their reliable fixation and start of the carriage movement upon activation of the release device. This configuration ensures reliability and portability of the launcher as well as a safe UAV launch at a short acceleration distance.

A shooting target launcher, associated components and methods. The launcher spins one or more helicopter-like shooting targets to launch the targets. A target connector receives the targets. The target connector is rotated about an axis of rotation to rotate the targets about the axis of rotation. The targets have fan blades that, when rotated, propel the target through the air.

An unmanned quadcopter aircraft system integrated with a pneumatic paintball projectile launching mechanism for recreational and training applications. The system includes a compressed gas powered single-shot paintball launcher with gravity-fed ammunition hopper, mechanical counterweight recoil compensation, and multiple electronic safety systems. GPS-based geofencing prevents firing in restricted zones, while altitude sensors prevent firing above predetermined heights. The flight control system automatically reduces aircraft speed and altitude limits when the projectile system is armed. A ground control system integrates standard flight controls with firing controls, safety indicators, and emergency stop capability. An alternative embodiment allows a used to adjust the elevation of the firing system while maintaining the orientation of the drone in space and also allowing recoil compensation. The system enables aerial paintball gaming and training scenarios while maintaining safety through redundant control systems and automatic parameter limiting.

A toy projectile launcher able to rapidly and sequentially launch a plurality of projectiles (such as four foam darts, each dart launched every 0.1 second) after being loaded and primed once, creating a machine gun effect. The launcher may be non-electronic, manually operated, and including a fluid compressor comprising a walled chamber holding a launch spring and a piston coupled to a priming actuator having a catch assembly with catch stops. A valve system may be coupled to the fluid compressor and an active barrel group comprising one or more launch barrels able to receive a plurality of projectiles. A trigger assembly may comprise a variable latch engaging the catch assembly, configured to single launch or sequentially launch the plurality of projectiles after the fluid compressor has been primed once by the priming actuator. Such structures also support electronic launchers and various projectiles (e.g., darts, balls, gel beads, etc.).

A launch apparatus, such as a toy gun, is disclosed herein. The launch apparatus includes a launch system for launching an object that has been loaded in the launch apparatus. The launch system has a guide channel extending in a launch direction. The launch system also includes a launcher element. At least part of the launcher element is mounted in the guide channel and is movable through the guide channel along the launch direction. Further, the launch system includes a drive system for driving the at least part of the launcher element through the guide channel in the launch direction. The launcher element is configured to accelerate the loaded object for launching the loaded object from the launch apparatus when the at least part of the launcher element is driven through the guide channel in the launch direction.

The utility model belongs to the technical field of anchor rod testing devices, and discloses an anchor rod dynamic bearing capacity testing device based on a Hopkinson pressure bar. According to the anchor rod dynamic bearing capacity testing device based on the Hopkinson pressure bar, the telescopic end of the hydraulic jack extends out relative to the fixed end to apply pre-tightening force to the to-be-tested anchor rod, the pre-tightening force of the to-be-tested anchor rod is monitored through the anchor rod pre-tightening force measuring device, the pre-tightening force is accurately applied to the to-be-tested anchor rod, and operation is convenient; a bullet is launched to the end face of the incident rod through the launcher, the dynamic load impact of the bullet on the incident rod is transmitted to the to-be-tested anchor rod through the force transmission frame, the dynamic load impact is applied to the to-be-tested anchor rod, and the dynamic bearing capacity of the anchor rod is tested; in the process, the actual working condition of the anchor rod support is accurately simulated, the speed of the bullet is monitored through the speed acquisition instrument, and the strain data of the anchor rod to be tested are acquired through the strain acquisition instrument, so that the dynamic bearing capacity parameters of the anchor rod are accurately tested.

The invention relates to the technical field of spacecraft propulsion system measurement, in particular to a device and a method for measuring response time and thrust of a microminiature thruster. A thrust frame of the device is arranged in a vacuum chamber, a to-be-tested thruster and a laser transmitter are installed on the thrust frame, and a gas source provides gas for the to-be-tested thruster. The laser receiver and the laser transmitter are arranged at an interval, and the laser receiver is used for receiving laser transmitted by the laser transmitter. Computer calculates thruster opening response time and thruster closing response time through transmission light intensity change time and control signal emission time difference and calculates thrust according to thrust data acquired by force sensor in time period from thruster starting control signal fluctuation first tending to stabilize to thruster starting control signal termination and the force device stabilizes the thrust. According to the device, laser is used for irradiating plume of the miniature thruster, the body structure of the thruster is not damaged, rapid non-contact measurement of the response time of the thruster is achieved, and steady-state thrust measurement of the thruster can also be achieved.

To provide ion thruster systems for spacecraft, and more particularly, to an integrated ion thruster unit that may be configured to accommodate payload envelope dimensions associated with a spacecraft.SOLUTION: An integrated ion thruster unit for a spacecraft can include a unit housing including a thrust face, and a plurality of tiles arranged in an array on the thrust face. Each of the tiles can include an emitter and an extractor configured to provide a reference voltage with respect to the emitter. The emitter can include a plurality of tips configured to emit ions in a thrust direction from an ionic liquid propellant in response to an applied voltage.SELECTED DRAWING: Figure 5

This invention belongs to the field of measurement technology, specifically a measurement and positioning device applied to keel construction, including a positioning instrument. A laser emitter is fixedly connected to the top surface of the positioning instrument, used to emit laser light for measuring and positioning the keel. A connecting shell protecting the laser emitter is fixedly connected to the top surface of the positioning instrument, and a sliding rod is fixedly connected to the top surface of the connecting shell. A connecting rod is slidably connected to the surface of the sliding rod. A suction cup is attached to the wall or steel frame to complete the installation of the positioning instrument. Through the above structural improvements, this device can more accurately measure the distance, level, or dimensions of the keel during use, allowing for more precise keel construction and improving construction accuracy and efficiency.

A remote launcher includes a base frame, a cradle, a cradle actuator, and a launch control system. The cradle is pivotably coupled to the base frame and includes one or more skids that are configured to receive and support an unmanned water-based deployable. The cradle actuator is coupled to the base frame and to the cradle. The launch control system includes a communication interface, a processor, and memory having instructions. The instructions direct the launch control system to receive, via the communication interface, one or more wireless launch signals and then, in response thereto, generate at least one cradle control signal to enable the cradle actuator to incline the cradle to a launch angle.

The invention discloses an integrated electrospray thruster transmitting module based on a 3D printing technology, and belongs to the technical field of spaceflight. The integrated electrospray thruster transmitting module is an integrated component which is integrally formed through a micro three-dimensional photoetching 3D printing technology, and a continuous fluid transmission channel from a liquid supply connector at the bottom end to a transmitting nozzle at the top end is arranged in the integrated electrospray thruster transmitting module; in the fluid flowing direction, the integrated electrospray thruster transmitting module sequentially comprises a liquid supply interface layer, a multi-layer flow channel structure and a transmitting layer from bottom to top. Integrated forming and high integration of the complex micro-channel structure are achieved, the array liquid supply uniformity is improved through the forked micro-channel structure, the size of sprayed liquid drops and the single-hole flow are reduced, and therefore emitter miniaturization is achieved, and the overall emission performance and working stability of the electrospray thruster are improved.

The utility model relates to an integrally-formed water rocket launcher base which is provided with a base main plate, a first connecting table protruding upwards is formed on the base main plate, a pair of pivot joint seats opposite to each other in a spaced mode is formed at the upper end of the first connecting table, a pair of coaxial pivot joint holes are formed in the pivot joint seats, and the pivot joint holes are communicated with the first connecting table. The water rocket launcher is assembled through screw and nut connection; second connecting tables protruding upwards are formed at the edges of a set of opposite sides of the base main board respectively, and U-shaped clamping grooves are formed in the two ends of each second connecting table respectively; three hollowed-out parts are further formed in the base main plate, and an assembling accessory of the water rocket launcher is formed in each hollowed-out part. By means of the structure, when the emitter base is integrally formed, another three emitter spare and accessory parts can be formed at the same time, and therefore the number of molds needed by production of the whole emitter is reduced, and production cost is greatly reduced; spare and accessory parts of the emitter and the base can be stacked, so that the occupied space is reduced, and the packaging and transportation cost is reduced.

The application discloses an environment-friendly bird repelling bomb device with an electromagnetic conductive electric ignition head structure, which is mainly used for bird repelling in an airport flight area. The device comprises a launching shell body (1), an electromagnetic conductive electric ignition head combination unit (2) arranged on the bottom of the inner cavity of the launching shell body, an electric ignition head inner sleeve unit (3), a bird repelling bomb body unit (6), at least one flame jet hole (4) arranged on the center of the top end surface of the electric ignition head inner sleeve unit, and a propellant layer (5) attached to the top end surface of the electric ignition head inner sleeve unit. The launching port end of the launching shell body is sealed by a sealing end cover (7). The bird repelling bomb device with the integrated structure which is combined by the above components is matched with an aviation special bird repelling launcher to realize electromagnetic induction conductive ignition launching. The bird repelling bomb device with the above structure has the advantages of vertical fixed connection between the electric ignition head and the two electrode ends in the center of the electromagnetic induction magnetic plate surface, realization of rapid ignition of the explosive body, no continuous ignition, no residue, environmental protection safety and the like.

Launching devices, kits, systems and methods. Embodiments may include devices for launching submergible vehicles from the top surface of the hull of ships. A launcher may retain vehicles at varying angles prior to launch. A bottom member may receive the vehicle and may have legs welded to the ship. The launcher may be tilted at varying angles, including a horizontal orientation for loading the vehicle and a raised orientation for launching the vehicle. The position of the loaded vehicle may be aligned by rotating the vehicle within the bottom member. An alignment fixture may engage alignment protrusions or slots on the exterior surface of the loaded vehicle. A top member may be attached to secure the aligned vehicle within the launcher. Upon command, the secured vehicle may be launched from the ship by releasing and enabling the vehicle to slide off of the bottom member into the water below.

A method of identifying a vessel as well as a vessel identifying device and a floating object and land installation including such a vessel identifying device. The vessel identifying device includes a processor operative to obtain a position of a vessel being sensed by a sensor, assign an identity to the vessel, which identity is assigned according to an identity assignment scheme of at least a part of a maritime tracking system, which maritime tracking system is an Automated Identification System (AIS), and provide an identification of the vessel according to the maritime tracking system, the identification including the assigned identity and the position of the vessel, and order a transmitter to transmit the identification of the vessel.

A wireless model rocket launcher and rocket which provide for safety checking and advanced functionality to be performed wirelessly using a mobile communication device such as a cell phone. A set of safety checks can be performed before the rocket is armed and triggered for launch. In addition, a location of the rocket can be tracked wirelessly on the mobile communication device.

1. Name of the product in this design: Toy (Runway Launcher). 2. Intended use of this design: for toys. 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.

The invention relates to an impact test device which comprises a fixing frame and a launcher, the fixing frame is used for fixing a test sample at different angles, the launcher is movably connected to the fixing frame, the launcher comprises a barrel part, an elastic part, a pre-pressing part, a bullet support and a traction assembly, the barrel part is provided with a cavity, the elastic part is provided with a first end and a second end, the elastic part is arranged in the cavity, and the pre-pressing part is arranged in the cavity. The pre-pressing piece is connected with the first end, the sabot is connected with the second end, the pre-pressing piece is used for pre-pressing the first end to a preset position relative to the barrel piece, and the traction assembly is connected with the sabot and used for pulling the sabot to move in the direction close to the first end. According to the impact test device, the stability of the launching speed of the projectile body is improved in an elastic piece launching mode, the launching speed can be adjusted under the prepressing action of the prepressing piece, and the adjustment simplicity and adjustment stability are improved. Besides, the impact test device is also provided with a fixing frame, so that incident impact tests at different positions and angles can be realized, and the test effect is improved.

The invention relates to the technical field of launchers, in particular to a handheld bird repelling bomb launcher which comprises a launch cavity body and a launch tube arranged at the front end of the launch cavity body. The transmitting tube is connected with the bearing guide tube body, and silencing groove bodies are arranged on the side wall of the bearing guide tube body at equal intervals; the outer side wall of the bearing guide pipe body is further sleeved with a loading pipe fitting. An auxiliary mechanism for absorbing and purifying noise and smoke is mainly formed by a bearing guide pipe body, a sound absorption pipe body and a loading pipe fitting. The sound absorption pipe body and the loading pipe fitting are supported by the bearing guide pipe body; in other words, generated noise and smoke are absorbed and purified through cooperative use of the sound absorption pipe body and the auxiliary assembly; on the basis, the sound absorption pipe body absorbs generated noise for the first time, and smoke and leaked noise penetrate through the smoke circulation holes in the sound absorption pipe body and then pass through the smoke absorption purification cotton balls arranged on the inner side of the loading strip to absorb the noise for the second time and purify the smoke.

A shooting target launcher, associated components and methods. The launcher spins one or more helicopter-like shooting targets to launch the targets. A target connector receives the targets. The target connector is rotated about an axis of rotation to rotate the targets about the axis of rotation. The targets have fan blades that, when rotated, propel the target through the air.

The present invention relates to an ion source (1), in particular an ion propellant for propelling a spacecraft, comprising a reservoir (2) for a propellant (3) having a solid state and being liquefiable to a liquid state, a heater (4) for liquefying the propellant (3) in the reservoir (2), an emitter (5) in fluid communication with the reservoir (2) for receiving a stream (S) of liquefied propellant (3) from the reservoir (2), an extractor (7) in front of the emitter (5) for extracting ions (3') from the liquefied propellant (3) of the emitter (5) and accelerating the extracted ions (3') away from the emitter (5), wherein at least one deflector (11) is disposed upstream of the emitter (3) in the stream (S) of the propellant (3) towards the emitter (5).

The utility model provides a cleaning device for a launching tube of a rocket launcher, which belongs to the technical field of military equipment maintenance and comprises a rod body which is of a hollow structure, an air blowing assembly is arranged in the rod body, a plurality of air inlet holes corresponding to the air blowing assembly are further formed in the rod body, and the air inlet holes are communicated with the hollow structure of the rod body. The cleaning cylinder is fixed to the end of the rod body, an air guide cavity is formed in the cleaning cylinder, the hollow structure of the rod body communicates with the air guide cavity, a plurality of air outlets are further formed in the cleaning cylinder, and the two ends of the air outlets communicate with the air guide cavity and the outer wall face of the cleaning cylinder correspondingly; high-pressure airflow can be input into the launching tube through the cleaning cylinder, so that sundries in the launching tube can be cleaned, and the inner side wall of the launching tube cannot be abraded.

An unmanned aerial vehicle (UAV) launch tube (100) that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about the right parallelepiped aperture (305), and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot (700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot (700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).

A five-wheel toy car launching system comprises a toy launcher and a five-wheel toy car. The toy launcher comprises a shell frame, the shell frame comprises a front rail part and a rear control part, the five-wheel toy car can be placed on the rail part, an acceleration mechanism, a locking mechanism and a launching mechanism are integrated in the control part, the locking mechanism can limit the position of the five-wheel toy car on the rail part, and in the limiting state, the launching mechanism can launch the five-wheel toy car on the rail part. Power wheels of the five-wheel toy car are suspended and can be accelerated by the accelerating mechanism, the launching mechanism can drive the locking mechanism to release the limiting state of the five-wheel toy car and push the five-wheel toy car out of the rail part, the accelerating mechanism and the launching mechanism are provided with an accelerating handle and a launching handle respectively, and the two handles extend to the outside of the shell frame. The five-wheel toy car launching system can be specially used for playing the five-wheel toy car, so that the five-wheel toy car can quickly pass along various rails, and the playing interestingness of the toy car is enhanced.

The invention relates to a transport system (1) intended to be installed on a space launcher (100) comprising:an aircraft (2) which comprises propulsion means configured to propel the aircraft (2) in a direction of flight, and at least one seat (4) intended to receive a passenger which is movable in rotation about an axis (0) perpendicular to the direction of flight of the aircraft (2), an acceleration sensor being installed on each at least one seat (4) to measure the acceleration of each at least one seat (4);a passenger interface for each at least one seat (4) which comprises a screen intended to display images to the passenger installed on said at least one seat (4), the screen being coupled to said at least one seat (4) so to remain fixed relative to said at least one seat (4);a control unit (6) which is connected to the acceleration sensor and to said at least one seat (4), the control unit (6) being configured to calculate a load factor experienced by the passenger installed on the at least one seat (4) from the acceleration of said at least one seat (4), the control unit (6) being configured to monitor the rotation of the at least one seat (4) during the operation of the transport system (1) in order to maintain the position of the seat (4) fixed relative to the load factor experienced by the passenger throughout the flight.

The utility model belongs to the technical field of flying toy articles, and particularly relates to a toy rocket bomb which comprises a rocket bomb body and side wings, and the rocket bomb body is composed of a rocket body, a launching hole and an arrow; the side wings are connected with the rocket body and are composed of connecting parts, extending parts, twisting parts and wing faces. The connecting part is parallel to the rocket body, the extension part reinforces connection between the rocket body and the side wings, the twisting part enables the side wings to twist by a specific angle relative to the central axis of the rocket body, and the twisting angles of the side wings in one set of rocket projectile are different. When the rocket projectile flies, due to the torsion design of the side wings, the rocket projectile rotates around the axis of the rocket projectile, airflow interference is effectively resisted under the gyroscopic effect, flight stability is remarkably improved, shaking and deviation are reduced, aerodynamic performance is optimized, and the rocket projectile is assisted to fly farther; rich and diversified flight paths are generated, the playing interestingness and novelty are greatly enhanced, the exploration desire of players is stimulated, and the competitive entertainment value of the toy is improved.

The application discloses a floating device for underwater experiment of an aircraft, which comprises a shell, a connecting plug arranged at the bottom of the shell and connected with a projectile body of a launcher, a core body installed in the shell, a top cover arranged at the top of the shell, a locking device arranged between the core body and the bottom of the shell, a spring release assembly connecting the core body and the shell, an electronic control system installed in the core body, an antenna arranged in the core body, and a communication quick plug arranged in the cavity of the core body. The shell bottom quick connector obtains the data in the projectile body, the shell is internally provided with the core body for obtaining the data in the projectile body through the communication quick connector and internal cable, and the core body realizes autonomous floating through the cooperation of the locking device and the spring release assembly. Only the core body needs to be salvaged, and the problems of difficult positioning and salvaging of the projectile body and difficult recovery of the projectile body data in the underwater experiment of the aircraft are solved.

The application discloses a kind of negative pressure environment air cannon launcher systems, cross medium launcher includes cannon barrel and gas holder, cannon barrel rear end passes through gas holder, cannon barrel is equipped with shell support, shell support is equipped with guide belt and multiple sliding seals, cannon barrel in gas holder is opened with air hole, the end of cannon barrel rear end is fixed with bottom plate, bottom plate and shell support are equipped with launch chamber, bottom plate is opened with the air guide hole of communication gas holder and launch chamber, gas holder is inflated to guide belt by air hole before launching and is communicated launch chamber by air hole after launching, the inner wall of cannon barrel is equipped with guide groove.Compared with prior art, the guide function of the anti-rotation mechanism of the present application is only activated after launching, and is not activated at other times, causing less damage to the cannon barrel. Furthermore, due to the flexible contact, the damage to the cannon barrel can be further reduced. The gas holder can complete energy storage for the guide belt through the air hole before launching, and can also communicate with the launch chamber through the air hole after launching, which can significantly improve the launching speed of the projectile.