228results about "Rocket launchers" patented technology

The invention relates to the technical field of rockets, in particular to a supporting device for a rocket and a transferring and erecting integrated launching vehicle. The supporting device comprises an erecting arm body and a plurality of auxiliary supporting mechanisms. The auxiliary supporting mechanism comprises a supporting bracket, a disc spring force limiter and at least two linear guide rails. The pre-pressure of the disc spring force limiter is adjustable, so that the rigidity of the supporting bracket is matched with the rigidity of the rocket body; the linear guide rails are arranged on the two sides of the supporting bracket respectively. According to the supporting device for the rocket and the transferring and erecting integrated launching vehicle, the supporting bracket is kept to be in a balanced state through the linear guide rail, the floating function is achieved, and the clamping stagnation phenomenon is prevented; force limiting supporting is achieved by adjusting the pre-pressure of the disc spring force limiter, the rigidity of the supporting bracket is made to be close to the rigidity of a rocket body, and therefore it is guaranteed that the additional bending moment cross section load generated by the erecting arm to the rocket is within the allowable range.

The utility model discloses a flow and pressure controllable water spraying noise reduction system and rocket launching auxiliary equipment relates to rocket launching auxiliary equipment technical field, and it is including: water storage tank, flow pump group, flow pump group connects water storage tank and drainage pipeline, water spraying pipe, water spraying pipe's first end connects drainage pipeline, and the second end of water spraying pipe sets up first control valve, circulating water pipe, circulating water pipe's first end connects drainage pipeline, and the second end of circulating water pipe connects water storage tank, and sets up second control valve on circulating water pipe. The above-mentioned flow and pressure controllable water spraying noise reduction system has solved the technical problem that the current water spraying noise reduction system cannot adjust water spraying flow, and water spraying timeliness is poor, and cannot provide large flow water flow in time, and influences the noise reduction effect, and before the rocket launches, the cooling water in the drainage pipeline keeps certain flow rate circulation, guarantees that the cooling water in the water spraying pipe can be in time, and the sufficient amount of water spraying pipe is sprayed from water spraying pipe, reaches the best noise reduction effect.

The invention relates to the technical field of rocket launching, in particular to a steam protection rocket launching system which comprises a steam energy storage system, a steam conveying system, a steam releasing system and a launching rack structure. The steam energy storage system comprises a steam boiler, a steam pressure accumulator and a steam energy storage control unit and is used for preparing and storing high-pressure steam before rocket launching. The steam conveying system comprises a steam blending table and a steam supply pipeline and is used for conveying high-pressure steam in the steam pressure accumulator to the steam release system; the steam release system comprises a steam injection unit and a steam injection control system and is used for releasing steam when the rocket is ignited, launched or recovered, forming a steam protection air curtain and reducing thermal shock of high-temperature airflow on the structure. By establishing the high-pressure steam protection air curtain, active protection of structural parts, pipeline parts, hydraulic parts and other parts of the rocket launching system influenced by the gas tail flame area of the rocket engine is achieved, and the durability and reliability of the launching system are improved.

Spacers include a base configured to be placed within depressions of one of a cover or a baseplate of a reticle pod, and a contact surface configured to contact the other of the cover and the baseplate. The spacers are configured to space the cover and the baseplate apart from one another such that sealing surfaces of the cover and the baseplate are separated by a gap. The depressions can be gripper pockets of the baseplate. Multiple spacers can be used in a reticle pod to provide the gap between sealing surfaces. The spacers can be installed to prepare a reticle pod for shipment.

A hybrid pad system positioned between a missile and a launch tube is provided herein. The hybrid pad system includes an outer sheet and an inner sheet spaced from the outer sheet. A web region can be positioned between the outer sheet and the inner sheet. A restoration region can be positioned between the outer sheet and the inner sheet and tangentially offset from the web region. A support can be operably coupled with the inner sheet.

Modular ammunition launching system comprising a reloadable ammunition receiver in multiple positions. The modular launching system (1) comprises: a chassis (2) defining at least one housing (6), an ammunition receiver (4), said receiver (4) being movable relative to said chassis (2) between a functional position and a reloading position. Said modular launching system comprises a coupling plate (24) integral with the receiver (4) and mounted to slide on a rail (26, 28) integral with the chassis (2) so as to allow movement of the receiver (4) between the functional position and the reloading position, said coupling plate (24) being movable in rotation relative to the rail (26, 28) about a reloading rotation axis (R3) when the receiver (4) is in the reloading position. Figure for the abbreviation: 7

The utility model provides a kind of automatic stop's suspension general hanging beam device, fixedly connected on ground or vehicle-mounted launcher, missile and guide launcher form missile launcher combined system, missile launcher combined system is hung in suspension general hanging beam device, press tightly stopper, fixed guide launcher and electrical connector pass through suspension general hanging beam device, suspension general hanging beam device includes beam body, automatic stop mechanism, hook assembly and anti-swing stop mechanism, wherein, automatic stop mechanism, hook assembly and anti-swing stop mechanism are respectively installed on beam body, when guide launcher is hung, hook assembly hook can be automatically inserted into lifting lug hole, with safety pin stop hook, guide launcher can be hung, i.e. It is realized;When guide launcher is unloaded, pull handle, drive hook to be stopped by automatic stop mechanism, guide launcher can be conveniently unloaded, and operation is simple.

The modular launching system (1) comprises: - a chassis (2) defining at least one housing (6), - an ammunition receiving pod (4), said receiving pod (4) being movable relative to said chassis (2) between a functional position and a reloading position. Said modular launching system includes a coupling plate (24) integral with the receiving pod (4) and mounted to slide on a rail (26, 28) integral with the chassis (2) so as to allow movement of the receiving pod (4) between the functional position and the reloading position, said coupling plate (24) being movable in rotation relative to the rail (26, 28) around a reloading rotation axis (R3) when the receiving pod (4) is in the reloading position.

The utility model provides a launcher enabling a rocket to rotate forwards, which comprises a rocket body, a rocket airfoil mounted at the tail of the rocket body, a fixing frame arranged on the outer side of the rocket body, a fixing plate mounted on the inner side wall of the fixing frame, an adjusting ring arranged in the fixing plate, clamping pressure plates arranged on the upper surfaces of the fixing plate and the adjusting ring, and bolts arranged in the clamping pressure plates. Bolts penetrate through the clamping pressing plates to be spirally connected with nuts, and spiral guide rails are movably installed at the tail ends of the inner sides of the adjusting rings. According to the launching device capable of enabling the rocket to rotate forwards, the safety, stability and reliability of the rocket during launching can be improved, and the anti-jamming capability of the rocket is effectively improved.

The invention belongs to the technical field of noise elimination and flame suppression equipment, and particularly discloses a noise elimination and flame suppression device which comprises a noise elimination and flame suppression shell, the noise elimination and flame suppression shell is in a hollow ring shape, the noise elimination and flame suppression shell is filled with a noise elimination and flame suppression agent, and the noise elimination and flame suppression shell can be crushed under the action of high-temperature and high-pressure fuel gas. The two-phase mixed combustion noise reduction and flame reduction technology is adopted, so that the emission noise is greatly reduced, when the initial velocity of a bullet is about 200 m / s, the emission noise can be reduced to 170-175 decibels under the open field condition, the noise can be reduced to 180-185 decibels when the bullet is emitted in a limited space, the emission noise can be remarkably reduced, the sound pressure can be reduced to 1 / 3 of the sound pressure which is not additionally provided with the noise elimination and flame reduction device, and the noise reduction and flame reduction effects are good. After emission, a calcium chloride solution at the emission port and the tail part of an emission object is atomized to wrap flames, so that flame at the emission port and emission tail flames can be obviously reduced, and flame visible to naked eyes basically does not exist; the training clothes can be kept complete when being launched in a limited space, and cannot be burnt out, broken down or ignited by tail flames or post-spraying objects.

The invention belongs to the technical field of marine rocket launching, and particularly relates to a marine rocket launching platform with a rocket body stabilizing structure. A base for mounting a rocket is arranged on the ship body; a group of fixing rings are arranged on the ship body, and a group of first hydraulic rods which are annularly and uniformly distributed are fixedly connected to the inner walls of the fixing rings; the output end of the first hydraulic rod is fixedly connected with a supporting and stabilizing block which is used for supporting and stabilizing a rocket. The rocket is installed on the base, at the moment, the rocket is located in the center of the fixing ring, when the ship body operates on the sea, the first hydraulic rod is started, the output end of the first hydraulic rod pushes the supporting and stabilizing block, the supporting and stabilizing block moves towards the side close to the rocket body, and at the moment, the supporting and stabilizing block makes contact with the rocket body; and therefore, the rocket body is supported stably, and the stability of the rocket during transportation is improved.

The application provides a modular airborne detection and attack micro-rocket launching device, which comprises a weapon station module, a shell cabin module and a female head, a male head and a transmission module are respectively electrically connected to two ends of an electric control module and are controlled by the electric control module; a rotating shaft rotates along an axis; the shell cabin module is detachably connected to the rotating shaft and rotates with the rotating shaft; a shell cabin body is used for accommodating spare bullets; the female head is detachably connected to the male head, at this time, the weapon station module, the female head and the shell cabin module are in a non-integral structure, and the weapon station module, the female head and the shell cabin module can be separately disassembled, so that the modules of the modular airborne detection and attack micro-rocket launching device cannot be separately maintained, the maintenance convenience of the modules of the modular airborne detection and attack micro-rocket launching device is improved, in addition, the shell cabin module is detachably connected to the rotating shaft and rotates with the rotating shaft, so that the angle of the shell cabin module relative to the transmission module can be adjusted.

Provided is a detent apparatus for a rocket, The detent apparatus includes a detent including a first end portion, a second end portion opposite to the first end portion, an extension extending between the first end portion and the second end portion, and a detent protrusion configured to engage with the rocket, a first elastic body configured to elastically support the first end portion of the detent and connected to the first end portion, and an electrical safety device configured to prevent rotation of the detent including a hinge fixing frame having a hinge axis parallel to the detent rotation axis, a detent support configured to rotate around the hinge axis and support the detent, a hinge axis shaft arranged on the hinge axis, a solenoid configured to rotate the detent support by pushing the detent support, and a micro switch activated when the detent support rotates.

The application discloses a manual adjusting device for the caliber of a human shadow rocket launcher director, which comprises a track assembly and a supporting assembly. The supporting assembly comprises four bearing rail frames. The track assembly comprises two groups of U-shaped track assemblies arranged in the left and right openings of the supporting assembly. Each U-shaped track assembly comprises an upper U-shaped large track, an upper U-shaped small track, a lower U-shaped large track and a lower U-shaped small track. The upper U-shaped small tracks are connected through a first linkage rod. The lower U-shaped small tracks are connected through a second linkage rod. A linkage plate is arranged between the two groups of U-shaped track assemblies. First and second inclined grooves are formed in the side walls of the linkage plate. The first and second linkage rods pass through the first and second inclined grooves respectively. The diameter of the envelope circle of the U-shaped small tracks can be changed through manual adjustment, so that one director can adapt to the launching requirements of rocket projectiles with various calibers.

The application provides a composite power driving system and control method for launching rocket erection, belonging to the field of launching rocket erection, and the driving system comprises a track combination system, a matching system, a whole rocket transport vehicle and a central control system. The track combination system is composed of a sliding mechanism and a swing boom; the matching system comprises a supporting rack and a buffer damping device. The central control system coordinates the work of each component, the whole rocket transport vehicle transports the launching rocket along the supporting rack slope to the horizontal plane, and the sliding mechanism and the swing boom cooperate to push the rocket to move. The laser sensor is used to realize the accurate positioning and connection of the rocket and the boom, the buffer damping device reduces the swing, and the stable erection of the rocket is ensured. The system also integrates a solar energy collection matrix and a gas flow collection and power generation device, and recycles energy to supply power for the transport vehicle. The application realizes the high-precision, automatic and efficient erection of the launching rocket, and reduces the energy consumption and operation complexity.

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).

The application discloses a kind of multifunctional autonomous semi-submersible ship, it includes main deck, main deck includes main deck bow, main deck stern and main deck middle section;Main deck middle section is located between main deck bow and main deck stern;The side ballast tank, bottom ballast tank, power equipment room and pipe and control equipment room are equipped below main deck middle section;Power equipment room and pipe and control equipment room are equipped in the area surrounded by side ballast tank and bottom ballast tank;Control center and control room auxiliary equipment room are equipped below main deck bow and below main deck stern;Main deck bow is further equipped with front ballast tank, and main deck stern is further equipped with rear ballast tank;Main deck middle section includes upper photovoltaic panel and lower photovoltaic panel;The outer side of upper photovoltaic panel is equipped with high-temperature-resistant material layer.The application realizes the multifunctionalization and autonomy of semi-submersible ship, and the environmental protection degree is high.

The application relates to the field of rocket sea launching, in particular to a rocket far-sea launching method and an integrated sea launching ship, which comprises a launching ship body, an environment guarantee plant and a launching device. A rocket storage cabin is arranged in the cabin of the launching ship body, a fairing storage cabin and a satellite storage cabin are arranged on the bow cabin of the launching ship body, a rocket in-out cabin lifting device is arranged at the cabin opening of the rocket storage cabin, a rocket parking adjusting device is arranged in the rocket storage cabin, a helicopter lifting platform is arranged on the top of the satellite storage cabin and / or the fairing storage cabin, a satellite transfer lifting ladder is arranged on the bow cabin of the launching ship body, a flat transport vehicle is arranged on the deck of the launching ship body, the environment guarantee plant is movably arranged on the deck of the launching ship body, and the launching device is fixedly arranged on the deck of the launching ship body. The application can realize far-sea multiple launching and continuous launching, greatly shortens the period of sea launching, reduces the cost of sea launching and guarantees the reliability of sea launching.

The application discloses a kind of oblique launch support orientation device and the launch method using it, in the device, by setting the guide rail of special form, adapter and projectile foot, by guide rail and projectile foot cooperation to constrain projectile lateral movement and circumferential rotation, by the adapter for projectile provides upward support force, by projectile foot for projectile provides downward support force, to constrain the low disturbance and subsidence of projectile, and with simple structure, action reliable, little features such as the influence of projectile aerodynamics, can provide guarantee for safe and reliable oblique launch.

- Attachment and ejection system and method for ejectable equipment. - The system (1), intended to ejectably hang an equipment (2) from a support structure (3), comprises a hooking body (4), a movable plunger (12), a displacement device (16) and a plurality of locking elements (22) on which the plunger (12) is configured to act, said system (1) being configured to take, successively, a locked configuration in which the plunger (12) acts on the locking elements (22) to lock the equipment (2) on the support structure (3), an unlocked configuration in which the plunger (12) is moved by the displacement device (16) to release the locking elements (22) and an ejection configuration in which the plunger (12) continues to be moved by the displacement device (16) so as to exert a force on the equipment (2) to eject it from the support structure (3),said system (1) thus making it possible to carry out the unlocking and ejection of the equipment (2) in a sequenced, reliable and secure manner.

The invention discloses a bonding type continuous composite flow guide strip which comprises a plurality of flow guide bodies, a conductive sheet, a polyester sheet, an insulating coating and a conductive paint belt, wherein the plurality of flow deflectors are in clearance connection to form a flow deflector layer; the polyester sheet is connected with the lower surface of the flow guide body layer and is adhered to the upper surfaces of the heat-proof layer and the conductive sheet; the conductive sheet is positioned on the lower surface of the polyester sheet and is adhered to the upper surface of the external machine body heat-proof layer; the conductive sheet is used for generating electromagnetic induction eddy current; the upper surface and the periphery of a joint between the flow guide bodies are covered with silicone rubber or a heat-proof coating to form an insulating coating; the insulating coating covers the end part of the flow guide body; and the upper surface of the insulating coating is brushed with conductive paint to form a conductive paint belt.

The modular ammunition launching system (1) comprises: - a chassis (2) defining at least one housing (6), - an ammunition receiving pod (4) movable relative to said chassis (2) between a functional position and a reloading position. Said modular launching system comprises a coupling plate (24) integral with the receiving pod (4) and mounted removably and movablely on the chassis (2), said modular system comprising at least one pairing device comprising a first pairing element (52, 56) integral with the chassis (2), a second pairing element (54, 58) integral with the coupling plate (24), the movement of the coupling plate (24) from the reloading position to the functional position resulting in the coupling of the first pairing element (52, 56) and the second pairing element (54, 58) in the functional position.

The application provides a space shell-and-missile separation auxiliary support mechanism and a launching cylinder in the technical field of shell-and-missile separation, which comprises front auxiliary supports and rear auxiliary supports, the front auxiliary supports are uniformly installed on the front end of the surface of the missile body, and the rear auxiliary supports are uniformly installed on the rear end of the surface of the missile body. The front auxiliary support comprises a lower cylinder, a compression spring and a limiting screw, the compression spring is arranged in the front auxiliary support, and the front auxiliary support is arranged in close contact with the launching cylinder guide rail through the compression spring. The lower cylinder is internally provided with a clamping groove, the clamping groove and the limiting screw are arranged in cooperation and are provided with a redundant design for realizing the collection and fixation of the front auxiliary support after the shell-and-missile separation. The rear auxiliary support is arranged in clearance fit with the launching cylinder guide rail and is used for controlling the movement state of the missile body in the flight process. The application can realize reliable support and sliding separation between the launching cylinder and the missile body, and meanwhile, beneficial effects such as simple structure and light mass are achieved.

This invention discloses a rocket body protrusion protection mechanism and its operating method, belonging to the technical field of launch vehicles. It includes a thermal insulation cover and a control module. The key feature is that a passive spring module is located below the thermal insulation cover, and a ball joint flange connects the thermal insulation cover and the passive spring module. The two ends of the ball joint flange are connected to the thermal insulation cover and the passive spring module, respectively. An active adjustment module is located below the passive spring module. The active adjustment module includes an X-axis adjustment component, a Y-axis adjustment component, and a Z-axis adjustment component, which are stacked vertically. Both the passive spring module and the active adjustment module contain sensor components for signal feedback, and these sensor components are connected to the control module. This invention is a rocket body protrusion protection mechanism that actively adjusts its position and passively adapts to the rocket body's roll and linear displacement attitude.

The invention discloses a method for providing reliable de-protection environmental force for a fuze and a film type pressure switch thereof, which can realize rapid induction of the pressure of an inner cavity when an engine works, and instantaneously convert the equivalent impedance of a core body in a circuit into an irreversible open-circuit state when the pressure of the inner cavity exceeds a designed threshold value, namely, before de-protection of the fuze is carried out, the equivalent impedance of the core body in the circuit is converted into the irreversible open-circuit state. The equivalent circuit of the film pressure switch is a constant resistor, and in the de-protection state, the equivalent circuit is in an irreversible open circuit state (the impedance is infinite), so that a method for providing reliable de-protection signals for fuze is realized. And through the design of adjusting the stress of the film core body, a series of film pressure switch products with various preset pressure de-holding thresholds can be met.

A Single Armament Control Unit (SACU) that operates a single missile tube as opposed to multiple tubes. The SACU provides for interlock pin and umbilical depression from the housing on the rotation of a single crankshaft controlled by a single motor where the rotor of the motor and the rotational axis of the crankshaft are generally parallel to the missile tube.

The invention provides an offshore efficient maritime launching and recycling system and method for a liquid carrier rocket. The system comprises a wharf plant, a maritime transportation launching platform, a measurement and control command ship, a propellant filling ship, a maritime recycling transportation platform, a rocket horizontal transfer system, a rocket incendiary agent filling system and a rocket oxidizing agent filling system. The method comprises the steps that firstly, final assembly and butt joint of a rocket and a satellite are completed at a wharf; then the satellite-rocket combination body is horizontally rolled to an offshore launching platform and navigated to a preset sea area together with the filling ship; on the sea, the rocket is transferred to a launching position and erected, an oxidizing agent and an incendiary agent are injected through the platform and the injection ship respectively after personnel evacuate, and then ignition and launching are conducted. The whole process is compact and efficient, the whole sea transportation mode is adopted, the rocket body size limitation of land transportation is avoided, meanwhile, the propellant filling ship is independently arranged, and the launching safety is improved.

The invention discloses a two-way rocket launching window searching method, system and device and a medium, and the method comprises the steps: rapidly calculating two nearest launching windows of an ascending orbit and a descending orbit of a rocket according to the attributes of a central body, target orbit plane parameters, the geographic coordinates of launching points and the flight duration of the rocket; according to the method, the problem is converted into numerical calculation based on space geometry, the crossing moment is directly solved by using the geometrical relationship between the normal vector of the orbital plane and the inertial position vector of the launching point location and adopting efficient numerical methods such as dichotomy and the like, and complex dynamic iteration is avoided. According to the method, the calculated amount is greatly reduced, rapid searching of the launching window is achieved, the method is suitable for an interstellar detection task scene needing rapid response or multiple times of calculation, and the real-time performance of task planning is remarkably improved.

The invention discloses a rapid docking device for rocket air conditioners, and relates to the technical field of rocket launching, the rapid docking device comprises a mounting ring, the bottom of the mounting ring is provided with a plurality of moving roller mechanisms and a plurality of supporting mechanisms, the mounting ring is provided with an annular mounting groove, and the annular mounting groove is provided with two symmetrically arranged moving frames; the movable frames are connected with the mounting ring in a sliding mode, a rotary displacement mechanism is arranged on one movable frame, a folding displacement mechanism is arranged on the movable frame, a rotation limiting clamping block mechanism is arranged on the folding displacement mechanism, a movable displacement mechanism is arranged on the folding displacement mechanism, a deflection ring mechanism is arranged on the movable displacement mechanism, and a butt joint mechanism is arranged on the deflection ring mechanism. According to the rocket air conditioner butt joint device, rapid movement of the device can be achieved through the arrangement of the moving roller mechanisms, positioning and leveling of the device can be achieved through the cooperation of the moving roller mechanisms and the supporting mechanisms, rotary displacement of the butt joint mechanisms can be achieved through the rotary displacement mechanisms, and the efficiency of rocket air conditioner butt joint is improved.