306 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.

The invention belongs to but not limited to the technical field of interception nets, and particularly relates to a multi-point traction type interception net launching device which comprises a base, a power device, a launcher and an interception net. The base can be adjusted and positioned at multiple angles, the borne impact force is at least not less than 15 KN, the base is designed into a folding structure, the packaging size is reduced, and transportation and storage are facilitated; the power device adopts compressed air as a power source, an air storage chamber is filled with high-pressure air, when a switch is turned on, energy of the high-pressure air is released instantly, and huge aerodynamic force acts on the pressed area of an object, so that the object moves in an accelerated mode from a static state and is thrown out. The power device body is composed of a launching tube, an air chamber, a valve element assembly, a firing device, a trigger, a carbon fiber air cylinder, a shell and the like, the launching tube, the carbon fiber air cylinder and the shell are distributed on the two sides of the air chamber, the firing device is arranged above the air chamber, and the trigger is pressed on the firing device; the launcher is in a horn shape, and four cylindrical storage bins connected with the launching tube are arranged on the edge of the launcher.

The invention discloses a device and method for testing the cross-medium water entry of a navigation body under the wave condition, and relates to the technical field of missile body water entry testing equipment.The device for testing the cross-medium water entry of the navigation body under the wave condition comprises an experimental water tank, and a wave maker is arranged in the experimental water tank; the adjusting module comprises a launching platform capable of adjusting the inclination angle; the emission module comprises an emitter and a driving source, the emitter is arranged on the emission platform, the driving source is in butt joint with one end of the emitter, the other end of the emitter is provided with a rectification structure, and high-pressure gas provided by the driving source enables a carbon body loaded on the emitter to be released at a certain initial speed; the rectification structure is used for reducing interference generated by gas turbulence in the radial direction of the launcher when the projectile body leaves the launcher. According to the invention, a stable wave page is generated through the cooperation of the motion phases of the two wave generators, the process that a projectile body enters water under a real sea condition is simulated, and more accurate experimental data is provided for the design and optimization of a cross-medium motion body.

An underwater video monitoring assembly for monitoring objects in proximity to a boat includes a set of video capturing modules and a computer, which are mountable to a hull of a boat and to the boat, respectively. The computer comprises an onboard transceiver. An onboard display is operationally engaged to the computer and is mountable to the boat. Each video capturing module comprises a transparent housing. A camera and a transmitter are attached to and positioned in the transparent housing, with the transmitter being communicatively engaged to the camera. The camera captures video in a space around the hull and the transmitter transmits the video to the computer, which evaluates an object in the video and selectively signals the onboard display to present one or more of a position of the object, a proximity warning, and a threat warning.

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.

The present invention provides a drone tear gas launcher, which includes a magazine fixing part that is provided with a plurality of launch ports along its length direction and trigger slot holes corresponding to the launch ports; a magazine that is placed inside the magazine fixing part, and the magazine is provided with accommodation cavities corresponding to the launch ports one by one; a launching part that can move along the length direction of the magazine fixing part, one end of which is fixedly provided with a launch tube, and the other end is fixedly provided with a trigger unit. The trigger unit includes a firing pin and a firing hammer. The firing hammer can strike the firing pin, and when the end of the firing pin can enter the accommodation cavity. The present invention uses the cooperation of the magazine fixing part and the magazine to place a plurality of tear gas bombs in the accommodation cavities, and uses the firing hammer and firing pin of the trigger unit to launch the tear gas bombs in sequence.

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 belongs to but not limited to the technical field, and discloses a single-point training missile traction interception net launching device and method, the device comprises a base, a power device is arranged on the base, and a launcher is arranged at the front end of the power device; and the intercepting net is connected with the emitter through a traction rope. The folding mode of the intercepting net comprises four-corner star folding and parallel folding. And the intercepting net is provided with a mass block and a non-uniform buoy. The working environment of the underwater navigation body touch net associated body motion model is in seawater; a plurality of counterweights are suspended in sea water by the two buoys through the net body, the net body is vertically unfolded by tensile force between the buoys and the counterweights, and the net body is basically not affected by stress in the horizontal direction and moves along with sea waves; when the navigation body vertically touches the net body at a certain navigation speed, the net body drives the buoy and the counter weight to do associated motion.

The utility model relates to the technical field of fire-fighting lifesaving equipment, and discloses a high-thrust long-distance lifesaving throwing device which comprises a throwing vehicle. A user adjusts the height of the emitter through the pushing and shooting angle, a second motor is driven to drive a threaded rod to rotate, the threaded rod is rotated to drive a threaded sleeve and a third rotating seat to move, the third rotating seat is moved to drive a guide plate to be supported, and then the guide plate drives the emitter to adjust the height; when a user needs to take back the lifesaving equipment mounting rod, push back a moving plate from a convex groove, eject a spring under extrusion, connect a transmission rod with a storage rod, and then drive a first motor to drive a rotating rod, the transmission rod and the storage rod to rotate, the lifesaving equipment mounting rod drives the connecting rope to fly out, and the user needs to take back the lifesaving equipment mounting rod, push back the moving plate from the convex groove, eject the spring under extrusion and connect the transmission rod with the storage rod. And the storage rod winds the connecting rope, and the transmission rod is disconnected with the storage rod, so that the resistance of the connecting rope launched by the life-saving equipment mounting rod is reduced to the minimum.

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.

Disclosed is a method for ejecting at least two satellites (2; 2a, 2b) from a launcher (3), said at least two satellites (2; 2a, 2b) being oriented along a central axis coinciding with a longitudinal axis (A) of the launcher and secured together side by side, the method comprising: a. an initial orientation of the direction of the longitudinal axis (A) of the launcher, so as to form a predetermined angle (θ) with an orbital speed axis (X), the predetermined angle (θ) being between 20° and 60°, b. a first separation comprising the simultaneous separation from the launcher (3) of said satellites (2; 2a, 2b) along the longitudinal axis (A) with a first predetermined differential speed (dV1) relative to the launcher (3), said at least two satellites (2; 2a, 2b) remaining secured together, then c. a second separation comprising the separation of said satellites (2; 2a, 2b) from each other along an axis perpendicular to the central axis and included in the orbital plane, with a second predetermined differential speed (dV2).

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.

1. The name of the design product: toy airplane pneumatic launcher. 2. The use of the design product: for children's entertainment and play. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 1.

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.