43results about How to "Launch safety" patented technology

The present airship-shaped space craft has a middle fuselage extending in a fore-and-aft direction, and a pair of two outer fuselages extending in the fore-and-aft direction located symmetrically on both sides of the middle fuselage. In the above fuselages, gas of a specific gravity of which is smaller than that of air is filled, and the middle fuselage is connected with the outer fuselages by a horizontal wing. The horizontal wing is provided with propelling devices supported in a gimbal fashion for generating thrust in any optional direction, jet engines with backwards directed nozzles to be controlled within a range from a slantwise upward direction to a slantwise downward direction, and rocket engines with ejection nozzles to be controlled in right-and-left and up-and-down directions. During ascent of the space craft, at first the propelling devices, then the jet engines and at last the rocket engines are actuated so as to make the space craft reach and fly along a satellite orbit. Upon return of the space craft, the rocket engines, the jet engines and the propelling devices are actuated in reverse order, and aerodynamic heating at reentry into the atmospheric space can be reduced by making the space craft descend slowly. Also, control of the flight in the atmospheric space becomes easy, so that the space craft can safely and easily land on a predetermined narrow area of the ground.

The invention discloses a low-impact overall ejection type launching canister front cover and belongs to the technical field of rocket and missile launching. The low-impact overall ejection type launching canister front cover comprises a movable impact part, an energy storage spring, fixing fulcrum bars, pull bars, fixing locking rings, locking tongue pieces, a front cover body and a fixed support. The fixed support is fixed to the center of the front cover body. A hollow pipe of the movable impact part and a guide bar of the fixed support are in hole and shaft fit. The outer surface of the hollow pipe of the movable impact part and the outer surface of the guide bar of the fixed support are sleeved with the energy storage spring. One end of each fixing fulcrum bar is fixed to a flat plate of the movable impact part. One end of each pull bar is movably connected to the other end of the corresponding fixing fulcrum bar. Each locking tongue piece is movably connected to the other end of the corresponding pull bar. The fixing locking rings are fixed to flanges of a launching canister body. The front cover body is installed at the open end of the launching canister body through the cooperation of the locking tongue pieces and the fixing locking rings. The launching canister front cover can be effectively sealed and reliably opened and safely disengage.

An onboard combustion-gas-powered engine supplies power to a paintball marker or other projectile launcher by generating gas pressure pulses for propelling paintballs and other projectiles. The combustion gases produced by the engine can be allowed to rise in pressure within a confined volume of space before being released through a valve into a barrel for applying enhanced pressure pulses to the projectiles. A loading system is linked to a combustion accelerating system for automatically loading projectiles into the launcher.

The invention belongs to the technical field of missile weaponry launching control, and particularly relates to a safely and credibly launching control method for a missile. The safely and credibly launching control method for the missile particularly relates to a starting operation control method achieved for missile launching preparation software based on safety control methods of identity authentication, real-time authorization and the like. A launching control computer is revised, a safety control module is designed and added, and a set of brand new authentication, identification and starting control process is designed through an external interface, so that reliable and effective missile launching control is achieved. Above all, the strict safety control process for starting and software operation of an embedded type system is designed, so that launching of the missile can be safely and effectively controlled. A severe result possibly caused by misoperations or deliberate sabotage is avoided while reliably launching of the core missile system is ensured, and therefore safety and reliability of the core missile system are ensured.

A satellite deployment system has a plurality of releasable dispenser modules that are attached to each other with each module carrying satellites. Each dispenser module acts as an individual final stage with its own propulsion unit and deploys a subset of satellites to the appropriate altitude and orbit. Since each dispenser module can deploy its satellites far from other dispenser modules, the risk of collision among the satellites is greatly reduced, which allows a large number of satellites to be launched in a safe, timely and cost-effective manner.

An automatic reversing-reposition rocker arm includes a rocker arm body, and the rocker arm body is a steel box beam. A rocker arm pivoting shaft is attached on a middle of the body. The rocker arm body has a ballast tank, a water inlet, and a water outlet. The ballast tank is located in a back end of the rocker arm body. The water inlet is located in an upper edge of the ballast tank. The water outlet is located in a lower edge of the ballast tank. A left side and a right side of a lengthwise forth end of the rocker arm pivoting shaft match each other, and a plurality of connecting devices are attached on the forth end of the rocker arm body. A plurality of gas-liquid buffers connects with the rocker arm body via the connecting devices.

A system and method for using a pneumatic line to automate the launch a cement plug from a cement head. The pneumatic line is in communication with the valves and retaining devices normally found on a typical cement head. The system ensures that the proper sequence of opening and closing valves in combination with the removal of the retaining device is used to safely launch a cement plug from the cement head. The pressure in the single pneumatic line may be varied to launch multiple cement plugs from a cement head. The system may be used to remotely launch a cement plug from a cement head. A wireless remote may be used to regulate the pressure in the pneumatic line to launch cement plugs from the cement head as desired.

The invention relates to the technical field of ammunition, and particularly discloses a multi-connected cartridge shooting patrol bomb, a system and a working method. A patrol bomb unit comprises a bomb body; a left front wing and a right front wing are arranged on the two sides of the front end of the bomb body; a left rear wing and a right rear wing are arranged on the two sides of the rear endof the bomb body; a left vertical fin and a right vertical fin are arranged on the two sides of the bomb body; a motor is arranged at the rear end of the bomb body; the output end of the motor is connected with a folding propeller; a warhead is arranged in the front end of the bomb body; a battery pack and a power management system are arranged in the middle of the bomb body; and a data transmission, navigation and flight control system and an electronic speed controller are arranged in the rear end of the bomb body. The multi-connected cartridge shooting patrol bomb, the system and the working method have the advantages that a plurality of patrol bombs with bomb body wing surfaces capable of being folded and stored are loaded by adopting a multi-connected launching cartridge with high integration level, so that the multi-connected cartridge shooting patrol bomb can be conveniently installed on a vehicle-mounted or ship-mounted platform in a modular mode, the maneuvering deployment isflexible, meanwhile, multi-shot continuous launching can be realized, the multi-connected cartridge shooting patrol bomb can be used for carrying out group disturbance attack operation on enemy fieldoperation air defense positions, field operation parking places, artillery positions and the like, and the operation flexibility is improved.

The invention relates to an orbit accelerating airplane capable of completing lift-off of a two-stage rocket spacecraft with two-stage moving platforms, which comprises an orbit, an orbit moving platform, an airplane platform and the two-stage rocket spacecraft, and is characterized in that the orbit moving platform and the airplane platform complete start, acceleration and lift-off by means of different power sources and pass through a troposphere to enter a stratosphere, and a relaying launch means of sending the spacecraft by a rocket in the stratosphere is realized. Compared with the prior art, the orbit accelerating airplane has the notable advantages that fuels of a jet engine are saved, the rocket is small in size and low in cost, launch is less limited by a launch site, the weather and the climate, a launch window can be selected, the orbit moving platform and the airplane platform can bear various spacecrafts and is reusable and the like, thereby having quite good use value.

The invention discloses an aerial anti-unmanned aerial vehicle catching device based on electromagnetic launching technology. The aerial anti-unmanned aerial vehicle catching device comprises a takingoff and landing support, a connector and a locating mechanism. The taking off and landing support is fixed to the bottom of an unmanned aerial vehicle. The connector is installed on the taking off and landing support. The locating mechanism is fixed to the bottom of the unmanned aerial vehicle and is located in the taking off and landing support. A catching device is installed below the taking off and landing support through the connector and comprises launching pipes, a net storage barrel, a catching net and a circuit device. The circuit device is installed at the tail of the interior of thecatching device. The n launching pipes are installed at the front end of the catching device, and meanwhile the rear ends of the launching pipes are connected with the locating mechanism through connection rods. The net storage barrel is put among the launching pipes. The catching net is put in the net storage barrel. With the use of the aerial anti-unmanned aerial vehicle catching device, a target unmanned aerial vehicle can be caught effectively and precisely.

The invention discloses a powered teaching rocket launcher. The launcher comprises a launcher base, wherein a pitch angle adjustment support rod and a guide rail sliding table bracket are installed atthe front and rear ends of the launcher base respectively, guide rail sliding table frames are installed on the pitch angle adjustment support rod and the guide rail sliding table bracket, a rocket sliding groove for a rocket to move forwards is formed in the middle axis of a guide rail sliding table, and a launch booster for pushing the rocket forwards is arranged at the tail end of the guide rail sliding table. Compared with a traditional launcher, the launcher provides power required for the teaching rocket to fly through the launch booster, so that the mass of the teaching rocket is reduced by at least 30%, and more built-in instrument and equipment reduce the design cost and difficulty of the rocket. Due to the use of the launch booster, an engine of the rocket is canceled, so that the process of launch, storage and transportation is safer, and the purposes of low-cost required for tests and safe launch of the rocket are achieved relevantly.

A flexible base with a protecting layer comprises a bottom plate and side walls, wherein the bottom plate and the side walls form a barrel; a reinforcing layer is arranged on the surface of the inner side of the bottom plate; a butyl rubber plate and an aramid adhesive tape are sequentially adhered to the reinforcing layer from inside to outside; shielding layers are arranged on the aramid adhesive tape and the surfaces of the inner sides of the side walls; and butyl adhesive tapes are adhered to the outer sides of the shielding layers. The rigidity of the flexible base with the protecting layer is increased; a transmitting process is safe; and moreover, the flexible base can resist high-temperature and high-pressure gas.

The invention discloses a pressure relief pneumatic fire extinguishing bomb. The fire extinguishing bomb comprises a fire extinguishing bomb body filled with a fire extinguishing agent, wherein a pressure relief cabin section is fixedly connected to the tail portion of the fire extinguishing bomb body, an inflatable pressure relief opening is formed in the outer wall of the pressure relief cabin section, a high-pressure cabin section is arranged on the tail portion of the pressure relief cabin section, the high-pressure cabin section comprises a high-pressure cabin shell with a top opening, apressure control membrane is arranged at the top of the high-pressure cabin shell, a high-pressure cabin inflation port is formed in the bottom of the high-pressure cabin shell, the front portion of the high-pressure cabin shell is embedded into an inner cavity of the pressure relief cabin section in a sealed mode, and the outer wall of the high-pressure cabin shell is connected with the outer wall of the pressure relief cabin section through a breakable connecting frame. According to the fire extinguishing bomb, no initiating explosive device is used, high-pressure gas is adopted for firing of the fire extinguishing bomb and spraying of the fire extinguishing agent, the firing process is safer, potential safety hazards existing in the production, storage, transportation and use processesof the fire extinguishing bomb are avoided, a secondary fire is eradicated, and the fire extinguishing bomb is lighter than a traditional fire extinguishing bomb by adopting compressed gas driving.

The invention provides a flexible base transmitting ejection loads. The flexible base comprises a bottom plate and a side wall. The bottom plate and the side wall form a barrel shape. The longitudinal section of the side wall is of an S shape. The flexible base transmitting the ejection loads has high self-deformation ability, and can meet the requirements for different ground unevenness, and control the ejection loads within the safety range.

The invention provides a medium-low temperature high-speed impact test device and a test method thereof. A protection tank body is used as a safety protection device for a projectile impact test; theprotection tank body is provided with a through hole for threading and a pipeline, and one end of the protection tank body is provided with a tank door; a test table board and an illuminating lamp arearranged in the protection tank body; a gunpowder gun and an environment box are arranged in the test table board; a target frame and a liquid nitrogen evaporation plate are arranged in the environment box; the measurement and control cable of the temperature control device is connected with the environment box, and the refrigeration pipeline of the temperature control device is connected with aself-pressurization liquid nitrogen tank; the self-pressurization liquid nitrogen tank is connected with the liquid nitrogen evaporation plate; an electromagnetic velometer is connected with the detachable gun barrel of the gunpowder gun and connected with an oscilloscope through a cable. The device has the advantages of being low in manufacturing cost, small in size, simple in structure, convenient to operate and high in launching safety and reliability and reducing professional requirements of operation.

The invention discloses a fuse monitoring bracket for external protection of a high-voltage capacitor. The included angle between the fixing plate and the mounting plate is an obtuse angle. The sensor mounting hole is installed on the mounting plate. The lower part of the mounting plate is provided with an upper clasp fastener. Features under hugging fastening. In the online monitoring method, the sensor is fixed on the monitoring bracket, and the signal transmitter is also fixed on the monitoring bracket at the same time. The signal transmitter is connected to the sensor, and the signal receiver and WEB server are set in the monitoring room. A monitoring bracket is installed on the base of the ejection tube. The angle of inclination of the mounting plate on the monitoring bracket cannot affect the performance of the fuse blowing. Fasteners and fastenings, hold the base of the paralyzed tube tightly. The invention has the advantages that no need to change the structure of the existing fuse tube, the universality is greatly improved, the state of the fuse tube can be accurately detected and the guardians can be notified in time.

The invention discloses a stamping pneumatic fire extinguishing bomb. The fire extinguishing bomb comprises a fire extinguishing bomb body filled with a fire extinguishing agent, wherein a fire extinguishing bomb firing section filled with high-pressure gas is arranged on the tail portion of the fire extinguishing bomb body, and the top of the fire extinguishing bomb firing section is connected with the outer wall of the fire extinguishing bomb body through a breakable connecting frame. According to the fire extinguishing bomb, no initiating explosive device is used, the high-pressure gas is adopted for firing of the fire extinguishing bomb and spraying of the fire extinguishing agent, the firing process is safer, and potential safety hazards existing in the production, storage, transportation and use processes of the fire extinguishing bomb are avoided.

The invention discloses a low-impact overall ejection type launching canister front cover and belongs to the technical field of rocket and missile launching. The low-impact overall ejection type launching canister front cover comprises a movable impact part, an energy storage spring, fixing fulcrum bars, pull bars, fixing locking rings, locking tongue pieces, a front cover body and a fixed support. The fixed support is fixed to the center of the front cover body. A hollow pipe of the movable impact part and a guide bar of the fixed support are in hole and shaft fit. The outer surface of the hollow pipe of the movable impact part and the outer surface of the guide bar of the fixed support are sleeved with the energy storage spring. One end of each fixing fulcrum bar is fixed to a flat plate of the movable impact part. One end of each pull bar is movably connected to the other end of the corresponding fixing fulcrum bar. Each locking tongue piece is movably connected to the other end of the corresponding pull bar. The fixing locking rings are fixed to flanges of a launching canister body. The front cover body is installed at the open end of the launching canister body through the cooperation of the locking tongue pieces and the fixing locking rings. The launching canister front cover can be effectively sealed and reliably opened and safely disengage.

The invention discloses a splicing, butt joint and in-place method of large floating mats in natural rivers. The method comprises the following steps that a processing site is arranged on a river bankclose to an installation position of floating mats; segmented floating mats are assembled on slide way steel pipes of the processing site; after machining of one segmented floating mat is completed,the segmented floating mats slide into a water surface along the sliding ways and are connected with anchor rings pre-buried on a shore till that machining of all the segmented floating mats is completed; all the segmented floating mats are launched in sequence, and the multiple segmented floating mats are spliced and combined into an integrated large floating mat under traction of a barge; and connection between a connecting device and the large floating mat is completed on the water surface, and in-place of the large floating mat is completed. The integral large floating mat is finally formed by processing, launching and connecting the segmented floating mats so that a requirement on a processing site area of the floating mat can be reduced, and the processing, launching and positioningof the floating mat can be simplified, and a construction period is shortened.

The invention discloses a fire-fighting fire extinguishing bomb without an initiating explosive device. The fire-fighting fire extinguishing bomb without the initiating explosive device comprises a bomb head, a bomb body and a tail fin, wherein an inner cavity of the bomb body is filled with a fire extinguishing agent, the bomb body comprises a plurality of segmented bomb slices arranged in an annular mode, the upper end of each segmented bomb slice is fixedly connected with a clamping part, all the clamping parts surround and are clamped on a bomb head locking device, the lower end of each segmented bomb slice is hinged onto a bomb body base, the bomb body base is connected with the tail fin through a tail fin rod, and the bomb head sleeves all the clamping parts and is connected with thebomb head locking device. The fire-fighting fire extinguishing bomb without the initiating explosive device adopts a fire extinguishing bomb launching method which uses compressed gas as launching power, and is safe in the launching process, and the fire-fighting fire extinguishing bomb does not use any initiating explosive device, and therefore potential safety hazards in processes of production, storage, transport and use of the fire extinguishing bomb are avoided.

The invention discloses a stamping pneumatic fire extinguishing bomb, which comprises a fire extinguishing bomb body equipped with fire extinguishing agent. The broken connecting frame is connected with the outer wall of the fire extinguishing projectile. The present invention does not use any pyrotechnics, high-pressure gas is used for firing the fire extinguishing bomb and spraying of the fire extinguishing agent, the launching process is safer, and the potential safety hazards in the production, storage, transportation and use of the fire extinguishing bomb are avoided.