194 results about "Launch pad" patented technology

The present invention provides launch pads on the display of a computer system as interactive interfaces between a user and wizards. The present invention includes: (a) providing a link on a launch pad, where the link is associated with a wizard, where the launch pad comprises a first visual object, where the first visual object in the launch pad relates to the task performed by the wizard; and providing the wizard when the link is selected, where the wizard comprises a second visual object, where the second visual object is associated with the first visual object. In the preferred embodiment, the second visual object in the wizard provides more information concerning the task than the first visual object. In this manner, a user is provided a visual connection between the information provided on the launch pad and the information provided on the wizard concerning the task performed by the wizard.

A radio is presented in which a short-range antenna, along with a speaker, is contained within a non-conductive speaker bracket. The antenna is a PIFA that is bent and extends through the speaker bracket so that the distance between the free end of the PIFA and various metallic components of the radio including the chassis and speaker is maximized. The structure containing the PIFA is flexible and also contains a contact area where feed / ground contact for the PIFA is made as well as contact for audio components including a speaker and microphone. A flexible cable and extension portion of the flexible structure routes the signals to the audio components far enough away from the PIFA so that the amount of crosstalk is insignificant. The free end of the PIFA and launch pad where feed / ground contact for the PIFA is made are non-planar.

Provided is a user-interest driven launching pad of a mobile application and method of operating the same. The user-interest driven launching pad inputs metadata of data elements related to a mobile device, forms a set of data elements having the same metadata, marks the set of data elements with user-interest reflecting tags, and executes the mobile application relating to the set of data elements.

The invention discloses a method of taking off and landing of an aircraft carrier plane and a device thereof. The device comprises a windmill type rotating mechanism arranged on an aircraft carrier body, wherein, the rotating mechanism is provided with a group of cantilever arms; a protruding end of each cantilever arm is provided with a lift platform with adjustable inclination angle and a launch pad. The plane is fixed on the launch pad before taking off; the rotating mechanism is started, when the plane reaches takeoff altitude and takeoff speed, a fixed device is released to lead the plane to take off automatically along the tangential line, so that the takeoff of the plane is completed; when the plane lands, the lift platform floats on sea level, when the plane approaches the lift platform of the rotating mechanism, the inclination angle of the launch pad is matched with the flight altitude and speed of the plane, an arresting device is used for leading the plane to directly land on the lift platform, the rotating speed of the rotating mechanism is gradually reduced until the rotating mechanism stops, thereby the landing of the plane is completed. The method and the device of the invention change the mode of the original aircraft carrier body, can change the shape of the aircraft carrier body, improves the flexibility and reduces the use cost.

The invention provides a rocket erecting arm. The rocket erecting arm comprises an erecting arm body, wherein a rocket supporting and holding device, a rocket auxiliary hydraulic supporting device anda rocket rear fulcrum supporting and adjusting device are sequentially arranged on the erecting arm body in the length direction of the erecting arm body; the rocket supporting and holding device isused for adjustably supporting and holding the front end of a supported rocket, and the rocket auxiliary hydraulic supporting device is used for floating and supporting the middle of the supported rocket; and the rocket rear fulcrum supporting and adjusting device is used for adjustably supporting the rear end of the rocket and further used for adjusting rotation of the rocket during erecting andpositioning and butt joint of the rocket and a launching pad. According to the rocket erecting arm, the rocket can be safely and reliably supported and erected, multi-degree-of-freedom adjustment canbe conveniently carried out on the rocket in the supporting and butt joint process, and the butt joint and adjustment difficulty of the rocket during transferring is effectively reduced; and the launching time of the rocket can be greatly shortened, and the launching efficiency is remarkably improved.

A toy gun for launching a foam projectile includes a housing having an outlet, an inlet, and a passage sized to receive the projectile. A launch station disposed in the housing and is arranged to receive the projectile, a crank rotates a resilient actuating paddle. The paddle is shiftable between an undeflected position and an energy storing deflected position, and moves along a path in response to rotation of the crank and extends into the launch station. A post is disposed in the path and is positioned to shift the paddle to the deflected position in response to rotation of the wheel, with the paddle arranged to disengage the post in response to continued rotation of the wheel thereby releasing stored energy as the paddle returns to the undeflected position and travels through the launch station.

The invention discloses an air path inserting-pulling combined connector, comprising a socket on a rocket, a connector body, a ball lock, a cylinder and a steel rope, wherein the socket on the rocket and a rocket body are in threaded connection; the connector body is positioned below and is contacted with the socket on the rocket; the ball lock is in threaded connection with the connector body; the upper part of the cylinder is fixedly connected with a connection rod in the ball lock; the lower part of the cylinder is fixedly connected with the steel rope; one end of the steel rope is connected with the cylinder; the other end of the steel rope is fixed on an external launcher frame. The ball lock also comprises a lock body, a lock cylinder, a steel ball, a lock cylinder spring, the connection rod, a first guide pin, a movable sleeve, a movable sleeve spring, a second guide pin and a third guide pin. By applying the air path inserting-pulling combined connector, the fast and reliable separating between the connector body and the socket on the rocket can be realized.

The invention provides a generation method for the three-dimension model of an electromagnetic field, a system and a device thereof, belonging to the engineering design technical field. The method comprises the steps of: processing the signal parameter information attained at the check point; according to the signal parameter information and the actual landform in a preset signal coverage region, plotting a three-dimension field intensity distribution model. In the embodiment of the invention, a three-dimension field intensity distribution model of virtual wireless launch points at actual landform is built on an electric map to accurately represent the signal field intensity distribution of a launching pad and provide a reference platform for the location of new signal launch points.

The invention discloses a thermal protection method for a launch pad. The thermal protection method is characterized in that water spray main channels are arranged on components of the launch pad, water nozzles are formed in the various water spray main channels, cooling water sources are connected with the various water spray main channels, cooling water is sprayed out of the various water nozzles after a rocket is ignited, is sprayed on flame of a nozzle of an engine of the rocket and is preliminarily mixed with high-temperature gas flow sprayed out of the nozzle of the engine to form cooling water mist, and momentum and heat are exchanged between the high-temperature and high-speed gas flow and water flow sprayed out of the water nozzles in the procedure, so that the temperature of the gas flow sprayed on the launch pad can be reduced. The thermal protection method has the advantages that the intensity of ablation of the gas spray flow to launch equipment in a rocket launch procedure can be effectively reduced, and the cost is low.

The invention provides a novel frequency domain aviation extremely low frequency electromagnetic method. According to the method, an extremely low frequency electromagnetic signal which is transmitted by a ground high power launching pad is used. A launch vehicle takes a magnetic sensor to synchronously receive the magnetic signal of the launching pad above a target zone to identify a target. The method overcomes the disadvantages of shallow detection depth, heavy equipment, rigour construction demanding, high economic cost and the like of the existing frequency domain aviation electromagnetic method, takes into account the advantages of aviation extremely low frequency method and aviation natural electromagnetic field method, and has the advantages of deep detection depth, simple construction condition, portable equipment, high operability, low economic cost and the like.

The invention provides a control system and method for erection of a carrier rocket. The control system comprises a control system body, a signal collecting system and an executing mechanism. The control system and method have the functions of automatic leveling, automatic weak leg detection and secondary leveling for a launching platform. By means of the control system and method, an erection device can be made to hold the rocket, full automatic erection is achieved, the rocket can safely and reliably land on the launching platform, and the total erection time is not longer than 10 min; a rocket holding mechanism on the erection device can be rapidly opened; a rocket supporting device and bearing device can automatically ascend and descend; and the erection device can quickly fall back before the rocket is about to be launched.

The invention relates to a photoelectric warfare infield semi-physical simulation system based on a mechanical arm and belongs to the field of infield simulation and research. The system is used for realizing the full real-time dynamic semi-physical simulation, is reasonable in cost and is used for estimating the research and development on a foundation and onboard photoelectric warfare weapon system in wave bands such as visible light and medium / long wave infrared. The system comprises a guided missile guider, an interference laser emitter, a target simulation source and a launching pad, wherein the guided missile guider is hung on the mechanical arm; a linear motor is used for driving the mechanical arm to move on a cross beam; and the interference laser emitter and the target simulation source are fixed on the launching pad. A simulation interference system equivalent a laser divergence angle is used for performing real-time estimation on the tracking, the fighting time selection and the fighting performance of a laser warfare weapon after an infrared terminal guided missile attacks from a place 10km away. Meanwhile, the system provided by the invention is applied to other interference devices such as heat source and point source jammers for estimating an terminal guided section of an attacking missile.

The invention provides a stable erection and rapid back-falling electrical control system of a rocket erection device. The electrical control system comprises the erection device, the erection device is provided with a rocket clamping mechanism, and an erection oil cylinder and a limiting switch are mounted on the lower portion of the erection device; the erection oil cylinder is connected with an oil pump motor, and the oil pump motor is controlled through an oil pump motor control cabinet; and the oil pump motor control cabinet is connected to an electrical control combination; and according to the system, the erection device can be made to clamp a rocket to carry out full-automatic erection, and the rocket can be made to safely and reliably fall on a launching pad; the whole erection time does not exceed 10 min; according to the system, the rocket clamping mechanism on the erection device can carry out rapid opening, and before the rocket is launched, the erection device can be subject to itself rapid back falling; and according to the system, in the erection and back-falling process, self-adaptation control over the erection device can be achieved, and safety and reliability are achieved.

Managing peer-to-peer application components. A method may be performed, for example, at a computer system that includes application components including peer-to-peer application components. The peer-to-peer application components allow the computer system to communicate with other agents, such as host computers, operating systems, frameworks, application code and the like, in a peer-to-peer fashion. The computer system includes a launch pad module for coordinating the peer-to-peer application components. The method includes providing an extensible interface that allows peer-to-peer application components to be registered with the launch pad module. Peer-to-peer application components are registered with the launch pad module. Requests are accepted from agents directed to the peer-to-peer application components registered with the launch pad module. Launch functions are performed for the peer-to-peer application components registered with the launch pad module in response to the requests.

The invention provides an auxiliary experimental device for the water entry experiments of structures. The auxiliary experimental device comprises a launch pad and an impact water tank; the tilt angleof the launch pad can be adjusted within a range of 0 to 90 degrees, and the position of the launch pad can be also adjusted along a longitudinal direction; the problem of the oscillation of the launch pad under the impact of a reaction force is specially designed, so that the stability of the launch pad can be ensured; as a platform, the launch pad can be configured with different launch modulesto form a launch system; the wall surface of the impact water tank is made of a transparent material, and therefore, the impact water tank enables a good view-finding field of vision; the water tankis reinforced, and the deformation degree of the water tank at a depth of two meters of water is limited to a range in which the light of a camera is not significantly refracted; since the depth of the water tank is large, the water tank can be used for the high-speed water entry experiments of the structures.

The invention relates to the technical field of unmanned ships and provides a method and device for assisting an unmanned ship in capturing an unmanned aerial vehicle. A cannonball launching pad of the device is provided with a catching net bullet which is divided into a fore quarter part and a rear quarter part from the function and is symmetrically divided into two sections or three sections or four sections about the central axis from the connecting structure. One or more pairs of electromagnetic suckers are arranged at the positions, among the sections of the bullet, on the contact face of the fore quarter part. A micro processing panel is arranged at the position, located on the fore quarter part, on one or more sections of the bullet. Storage batteries are arranged in the corresponding sections of the bullet, and the storage batteries supply electricity to the electromagnetic suckers and the micro processing panel. An unmanned aerial vehicle is arranged in a hollow zone, formed by the rear quarter part, among all the sections of the bullet. Compared with the prior art, the capturing manner of the method and the device is more flexible, and the method and the device can be used for dealing with the complex environment of multiple target unmanned aerial vehicles.

Systems, apparatuses, methods, and computer-readable mediums for preventing return oriented programming (ROP) attacks. A compiler may insert landing pads adjacent to valid return targets in an instruction sequence. When a return instruction is executed, the processor may treat the return as suspicious if the target of the return instruction does not have an adjacent landing pad. Additionally, each landing pad may be encoded with a color, and a colored launch pad may be inserted into the instruction stream next to each return instruction. When a return instruction is executed, the processor may determine if the target of the return has a landing pad with the same color as the launch pad of the return instruction. Return-target pairs with color mismatches may be treated as suspicious and the offending process may be killed.

The present invention relates to a method for synchronizing a plurality of low-power sending stations which are dominated by a high-power sending station, each low-power sending station receives the reference synchronizing signal transmitted by the high-power sending station, does synchronizing according to the synchronizing signal and respectively compensates the signal transmission time delay. The high-power sending station can be broadcasting television base station and the low-power sending station can be one or a plurality of base stations selected from wireless metropolitan area network cellular base station, wireless local area network base station and wireless personal area network. The present invention settles the problem of synchronizing the considerable sending stations and can be widely used in the wireless communication system that needs to be done with network synchronizing, and reduces the cost of realizing the network synchronizing.

Disclosed herein is an apparatus and method for launching a toy rocket that includes rotating a launch tube about an axis that is parallel with a connecting tube, which is rotatably connected to the launch tube; extending the launch tube in a perpendicular direction; progressively closing a safety valve by rotating the launch tube toward a vertical position, relative to a launch pad assembly; loading the toy rocket onto a distal end of the extended launch tube; and rapidly compressing a bellows in communication with the launch tube.

The present invention generally relates to a system and method of a docking system (1) for fixed wing unmanned aerial vehicle, or non-fixed wing unmanned aerial vehicle (2) such as rotorcraft, or combination thereof, comprising at least a docking and / or launching pad capable of being arranged in an array or staggered manner; said pad has a surface (6) for said vehicle docking and launching, said docking and launching surface (6) comprising moveable pads (31) which include electromagnets that can be energized to capture a docking vehicle (2); and another energy harvesting surface (4) has photovoltaic panel to harness solar energy to generate electricity or hydrogen fuel for a variety of on-board applications such as to charge said vehicle (2) and to power the docking system and providing a safe stowage and protected storage for the said vehicle (2).

The invention relates to a mowing robot which comprises a robot body, a control system, a locating system and a mowing mechanism. The locating system comprises a signal receiving and sending device and a launching pad. The mowing mechanism comprises a cutting component. The center of rotation of the robot body, the center of rotation of the launching pad and the center of rotation of the cutting component are located on the same vertical shaft. Due to the design of the structure, program operations are greatly simplified, delay of the program operations is reduced, and accuracy for obtaining coordinates of the centers of the rotation through calculation of the robot is improved.

The invention discloses a structure of a thermal protective coating for a launching pad and an application of the structure. The thermal protective coating material comprises an organic base layer and an organic-inorganic composite surface layer, wherein the organic base layer comprises epoxy resin, polyamide as a curing agent and liquid rubber as a toughening agent; the organic-inorganic composite surface layer comprises organic glue epoxy resin, a polyurethane curing agent, sand and cement. The thermal protective coating material can bear the simulated combustion gas flow scouring of a rocket, the temperature of a metal back surface does not exceed 200 DEG C, and the coating has excellent thermal insulation property.

The invention relates to a physics teaching tool, in particular to a water injection and air inflation integrated water rocket launching device. The device solves the problems that the center-of-gravity position of the existing water rocket is unstable, the flying attitude in launching is inconsistent with the pre-designed flying attitude and has relatively great error and consequently the experimental effect is influenced. The upper end of a first pipeline sequentially penetrates through a launching pad and a water sleeve and is arranged in the water rocket body and located at the upper part of the water rocket body; the lower end of the first pipeline is communicated with the lower end of a second pipeline and one end of a third pipeline through a tee joint respectively; the upper end of the second pipeline is communicated with the lower end of a funnel; the second pipeline is provided with a first valve; the other end of the third pipeline is communicated with one end of a fourth pipeline; and the fourth pipeline is provided with a second valve and an air needle respectively. The device disclosed by the invention is applied to physics teaching.

The invention discloses a rocket mobile launching vehicle, which comprises a tractor, a chassis, a heat preservation cabin, an erecting system, a launching pad, temperature adjusting systems, a hydraulic system, a vehicle control system and power system wherein a traction seat is mounted on the tractor; the traction seat is connected with the chassis through a traction pin; the heat preservation cabin is fixedly mounted on the chassis; the erecting system is hinged to the rear end of the chassis; the launching pad is hinged to the rear end of the chassis; the launching pad and the erecting system are coaxial; the temperature adjusting systems are installed in front of and inside the heat preservation cabin; the hydraulic system is installed below the chassis; the vehicle control system isinstalled inside the heat preservation cabin; the operation panel is located outside the side wall of the heat preservation cabin; and the power systems are installed in the front of the chassis and inside the heat preservation cabin. The rocket mobile launching vehicle is ingenious in conception and reasonable in structural layout, the long-distance transportation time is greatly shortened, the stability in the transportation process is guaranteed, the shock absorption capacity is improved, the heat preservation cabin has good sealing performance, and meanwhile, the requirements for erectingand launching are met through the full-open design.

The invention discloses a marine rocket thermal launching erecting device and an erecting method, and belongs to the field of rocket thermal launching. The marine rocket thermal launching erecting device comprises a launching ship, a launching platform, an erecting component, a guiding piece, a driving oil cylinder, a sliding piece and a connecting piece. The sliding piece is matched with the guiding piece and moves along a straight line under the driving effect of the driving oil cylinder, one end of the connecting piece is hinged to the erecting component at a certain angle, the other end of the connecting piece is connected with the sliding piece, and the connecting piece is configured to act along with the sliding piece so as to push the erecting component to be erected onto the launching platform. The marine rocket thermal launching erecting device can effectively erect a marine thermal launching rocket, and is good in erecting effect and high in stability.

The invention discloses a vehicle-mounted missile launching single-side flow director and a launching vehicle with the same, and relates to the technical field of missile launching equipment. The vehicle-mounted missile launching single-side flow director comprises a flow guide part and a support, wherein the flow guide part comprises an arc-shaped main molded surface which is recessed downwardsand a connecting surface which is correspondingly connected with the head side and the tail side of the main molded surface, a plurality of convex strips are arranged on the upper surface of the mainmolded surface at intervals, the plurality of convex strips transversely penetrate through the whole main molded surface, the support is used for supporting the flow guide part, and the support is detachably connected with a launching station. According to the vehicle-mounted missile launching single-side flow director and the launching vehicle with the same, part of the acting force in the direction of the vehicle head can be counteracted, so that the shearing force generated by friction between hydraulic supporting legs and the ground is reduced, the risk that the hydraulic supporting legs are damaged under the action of the impact force of the fuel gas flow is reduced, and the reliability of a whole launching system is improved.