662results about "Rocket launchers" patented technology

An unmanned aerial vehicle (UAV) 1 of the vertical take-off and landing (VTOL)-type that can be launched from a launcher tube 2 is provided. A launcher 2 for launching the UAV 1 is also provided. The UAV 1 comprises a housing 10 and a transition mechanism 100 for transitioning the UAV 1 between a collapsed configuration for stowing the UAV 1 in a launcher tube 21 and a flight configuration. The housing 10 and the transition mechanism 100 are configured so that one or more rotors 12a-d that, in use, are connected to the transition mechanism 100 are located substantially within the housing 10 in the collapsed configuration and outside the housing 10 in the flight configuration. The launcher 2 comprises a hollow tube 21 for receiving a UAV 1 in a collapsed configuration and a trigger mechanism 26 for triggering a propulsion mechanism for propelling the UAV 1 out of an end of the hollow tube 21. A system comprising both the UAV 1 and the launcher 2, and a kit of part which, when assembled, provide the UAV 1 are also provided.

The invention provides an offshore launch rocket stabilizing device which comprises a first anti-overturning device and a second anti-overturning device, the first anti-overturning device and the second anti-overturning device are fixedly connected with a launching pad, and the first anti-overturning device and the second anti-overturning device are connected to the two sides of a rocket in a supporting mode correspondingly; the first anti-overturning device and the second anti-overturning device are the same in structure; each of the first anti-overturning device and the second anti-overturning device comprises an anti-overturning device underframe, an anti-overturning arm and a bracket; the bottom end of the anti-overturning arm is installed on the anti-overturning device bottom frame, the bracket is fixedly connected to the top end of the anti-overturning arm, and the bracket is used for being fixedly connected to the side portion of a rocket body of a rocket in a clasping mode. The end, close to the rocket, of the bottom of the anti-overturning arm is rotationally connected with the anti-overturning device underframe, and the other end of the anti-overturning arm is supported on the anti-overturning device underframe through a supporting and rapid separating mechanism. After the rocket is erected and parked on the launching platform, the rocket body is stabilized, the rocket is prevented from toppling over, and the stability and safety of the rocket are improved.

The present application discloses a rocket support device, which is installed on a vertical frame and used to support a rocket, and includes an arrow support seat, a lifting device, a base and a buffer device; the arrow support seat includes an arrow support surface, and the arrow support surface is used to carry the rocket; the base is fixedly installed on the vertical frame, and the fixed end of the lifting device is fixedly arranged on the side of the base away from the vertical frame, and the driving end of the lifting device is drivingly connected to the buffer device, and the end of the buffer device away from the base is connected to the side of the arrow support seat away from the rocket; the lifting device can drive the arrow support seat to rise and fall through the buffer device. In the present application, the height of the arrow support seat is adjusted by the lifting device, so that each arrow support seat can play a supporting role on the rocket, so that the rocket is balanced in force during transportation or launching, and the safety of the rocket and the service life of the rocket arrow support seat are guaranteed.

Various countermeasure dispensing systems (or CMDSs) and method of use are described herein. CMDS may include a dispenser assembly operably engaged with a platform where at least one electrical connection provides electrical communication between the dispenser assembly and a sequencer. CMDS may also include a magazine assembly operably engaged with the dispenser assembly, wherein the magazine assembly comprises a magazine configured to hold at least two countermeasure expendables. CMDS may also include a breechplate assembly operably engaged with the magazine assembly and adapted to dispense the at least two countermeasure expendables. CMDS may also include at least one magazine identification switch (MIS) operably engaged with the magazine assembly and the breechplate assembly. CMDS may also include that the at least one MIS is configured to enable the sequencer and the breechplate assembly to selectively dispense at least one countermeasure expendable from the at least two countermeasure expendables.

The invention provides a launching pad and a carrier rocket launching method. The launching pad comprises a launching pad body provided with a through flow guide opening, a first heat-proof plate, a second heat-proof plate and a driving structure. The second heat-proof plate detachably covers the inner side wall of the second edge side of the flow guide opening, the first heat-proof plate is rotationally arranged on the inner side wall of the first edge side of the flow guide opening, and the driving structure is arranged at the bottom of the launching pad body and used for driving the first heat-proof plate to rotate to be in an unfolded state or a folded state. And the first heat-proof plate is horizontally arranged at the top of the flow guide opening. During maintenance, the second heat-proof plate can be quickly disassembled so as to facilitate maintenance or replacement, meanwhile, the first heat-proof plate can be rotated to a horizontal unfolding state through the driving structure, a worker stands on the first heat-proof plate to maintain the heat-proof coating, high-altitude operation is not needed, and the safety and convenience of maintenance are improved; and the heat-proof coating is coated in the horizontal state, so that adhesion and uniform distribution of the heat-proof coating are facilitated.

Various systems and methods for leveraging legacy countermeasure dispensing systems (CMDSs). The legacy CMDSs are leveraged through the expansion of breechplates and magazines in a CMDS by expanding the amount of expendables carried by a CMDS while still maintaining the legacy sequencer and dispenser in a legacy military platform, such as an aircraft. In addition, various circuitry systems are included in a circuit card of the breechplate for duplicating and / or expanding the firing lines provided in a legacy CMDS.

The invention discloses a structural bearing associated rocket time-phased Q alpha release value design implementation method. The method comprises the following steps: carrying out statistical analysis on actually measured high-altitude wind data aiming at a rocket launching site position to form a high-altitude wind statistical result; carrying out flight standard trajectory design of the rocket to form a standard trajectory data result; developing an attack tilt angle calculation result under a rocket standard trajectory to obtain a Q alpha preliminary design result changing along with flight time; rocket flight load calculation and rocket structure design and optimization are carried out, so that the structure of the rocket meets the carrying capacity; the time-phased Q alpha release value of the rocket launching site is formulated, multiple incremental Q alpha values are obtained on the basis of the preliminary design result of Q alpha, and the corresponding maximum Q alpha release value meeting the maximum bearing bending moment requirement serves as the time-phased Q alpha release value to be output according to the transverse bending moment load corresponding to the Q alpha values; and before emission, emission release evaluation is performed according to the release value of the time-segmented Qalpha. Therefore, the problem of low release probability in a traditional method is solved.

The invention discloses a universal liquid carrier rocket launching pad technology. A satellite general assembly test subsystem realizes recovery and detection of a satellite and forms a star cover assembly; the rocket horizontal final assembly test subsystem realizes subsystem test, matching test and total inspection test of a first-stage rocket body and a second-stage rocket body in a horizontal state, and the first-stage rocket body, the second-stage rocket body and a star cover combination body form a whole rocket in the horizontal state; the rocket horizontal transfer subsystem transfers the whole rocket to the fixed launching platform in a horizontal state; the rocket launching subsystem erects the whole rocket and achieves testing, filling and launching of the whole rocket. According to the universal liquid carrier rocket launching pad technology, by adopting a three-plane test launching mode of horizontal final assembly testing, horizontal transferring and vertical launching, the construction cost of a rocket launching site is effectively reduced, the operation process is simplified, the rocket launching efficiency and frequency are improved, and the requirement for rapid and batch launching is met.

The invention belongs to the technical field of rocket launching, and particularly relates to a carrier rocket launching perpendicularity control method and device and a storage medium, the perpendicularity control method comprises the following steps: constructing an attitude dynamic model in a carrier rocket launching process, and the attitude dynamic model is used for describing change rules of rocket attitudes under different conditions; setting a prediction window; according to the real-time attitude state information of the rocket, predicting attitude changes of a plurality of time steps in the future in the current prediction window; designing an objective function, and optimizing the objective function through a predictive control algorithm in each time step to obtain an optimal control signal sequence; in each prediction period, executing a first signal in the obtained optimal control signal sequence, and transmitting the first signal to a rocket attitude control device; and repeating the steps. According to the invention, the launch attitude control precision of the carrier rocket can be improved, and the response speed of the system is optimized.

The invention discloses a rocket seaborne alignment method based on federated filtering and a system thereof. The rocket seaborne alignment method based on federated filtering comprises the following steps of performing equipment power-up and filter filtering parameter initialization; after equipment power-up and initialization of filtering parameters of the filter are completed, whether coarse alignment calculation can be carried out or not is judged; if the coarse alignment calculation can be carried out, carrying out coarse alignment calculation to obtain an attitude angle; and after coarse alignment calculation is completed and an attitude angle is obtained, fine alignment calculation is performed. According to the method, data of the multiple sensors are fused through the federated filtering algorithm, and the alignment precision of the rocket during offshore launching is remarkably improved. Meanwhile, the influence of the complex marine environment on rocket alignment can be effectively dealt with, and the stability of the launching process is improved. Moreover, by optimizing the structure of the federated filter, the fault tolerance performance of the system is improved, and even if a certain sensor breaks down, accurate alignment of the rocket can be ensured.

The invention relates to a folding door, in particular to a target drone zero-length booster rocket launching opening folding door mechanism. The mechanism comprises a folding door plate, a torsional spring hinge, a quick-release lock and a quick-release lock locking mechanism, the number of the folding door plates is two, the folding door plates are oppositely arranged at the rocket launching port, and when the two folding door plates are in a closed state, the folding door plates are matched with the rocket launching port; the torsional spring hinges are divided into two groups; one ends of the two groups of torsion spring hinges are respectively mounted on the two folding doors, and the other ends are respectively mounted at rocket launching ports of the target drone; the quick-release locks are divided into two groups; the two groups of quick-release locks are respectively mounted on the two folding doors; the quick-release lock locking mechanisms are divided into two sets, and the two sets of quick-release lock locking mechanisms are installed at rocket launching ports of the target drone respectively and correspond to the two sets of quick-release locks respectively. According to the target drone zero-length booster rocket launching opening composite material folding door mechanism, the function that a folding door is rapidly and reliably closed after work of a zero-length booster rocket in the launching stage is completed and cold separation is conducted can be achieved.

The invention relates to a shadow rocket launch control terminal, method and system, and belongs to the technical field of shadow rocket launch control, the launch control terminal comprises an identity authentication module, an operation information acquisition module, an operation control module, a launch control module and an operation log module; through whole-process management of identity authentication, data acquisition, attitude adjustment, state detection, ignition control and operation logs, safety, accuracy and data traceability of rocket launching operation are realized. Wherein the identity authentication ensures the safety of the operation authority, the data acquisition provides real-time information support for posture adjustment and state detection, the posture adjustment and the safe firing range judgment ensure the accuracy and the safety of launching, and the ignition control ensures that the launching is carried out under authorization; the recording and uploading of the job log enable the emission operation to have complete data record and traceability. The automation degree and reliability of figure rocket launching are improved.

The invention discloses an offshore rocket launching clamp system which comprises a rack and a clamping mechanism arranged on the rack, the clamping mechanism comprises two opposite clamping arms, and a clamping cavity used for containing a rocket is formed between the two clamping arms; the two clamping arms are driven by the driving device to be closed to clamp the rocket body or to be opened to release the rocket body. The clamping device is characterized in that the driving device is provided with a clamping force adjusting control mechanism used for conducting self-adaptive adjustment on clamping force of the clamping mechanism in the clamping process. The device has the advantages that the structure is simple, the clamping force adjusting and controlling mechanism used for conducting self-adaptive adjustment on the clamping force of the clamping mechanism during clamping is arranged on the driving device part on the basis of many unstable factors existing in the marine launching environment, the clamping force is adjusted in real time through the clamping force adjusting and controlling mechanism, and the clamping force adjusting and controlling mechanism is used for adjusting the clamping force in real time; therefore, it is ensured that the rocket body can be stably clamped.

The invention discloses a fixing device for a rocket, and relates to the technical field of spaceflight launching equipment, and the device comprises a bearing mechanism which is provided with an embracing clamp assembly and an embracing clamp adjusting assembly for driving the embracing clamp assembly to act; the holding clamp assembly comprises two holding clamp main bodies, each holding clamp main body is provided with a connecting section and a clamping section, the holding clamp adjusting assembly comprises a first mounting seat, a second mounting seat and a limiting seat which are mounted on the bearing mechanism, a driving part is arranged on the first mounting seat, a driving screw rod is rotationally connected between the second mounting seat and the limiting seat, and a driving shaft of the driving part is connected with the driving screw rod; the driving lead screw is provided with a first lead screw section and a second lead screw section which are oppositely arranged in a threaded mode, the driving lead screw is driven by the driving piece to rotate, so that the first driving nut and the second driving nut move along the driving lead screw, then the two holding clamp bodies are driven to rotate relative to the bearing mechanism, and the two clamping sections are matched to clamp or loosen a rocket to be fixed. And the operation process is simple and efficient.

The embodiment of the invention discloses an erecting control system for a rocket launched on the sea. The erecting control system for the rocket launched on the sea comprises a control module, a tilt angle sensor, a rotary encoder and an erecting frame. The first input end of the control module is in communication connection with the output end of the tilt angle sensor; the second input end of the control module is in communication connection with the output end of the rotary encoder; the input end of the tilt angle sensor is in communication connection with the erecting frame; the input end of the rotary encoder is in communication connection with the erecting frame; the marine launching angle is adjusted through the tilt angle sensor and the rotary encoder, relying on a launching ship is not needed, the launching cost is reduced, the launching maneuverability is improved, the launching period is shortened, the device can be suitable for different types of rockets, and high marine launching flexibility, good task adaptability and high launching economical efficiency are achieved.

The invention relates to the technical field of integrated special vehicle equipment, in particular to an integrated special vehicle equipment system for monitoring, commanding and operating meteorological data. The device comprises a second-class chassis, a square cabin is installed at the upper end of the second-class chassis, a vehicle-mounted air conditioner is installed at the upper end of the square cabin, an installation area is arranged at the upper end of the square cabin, a lodging mechanism and a radar are arranged on the inner wall of the installation area, and an installation area, an operation area, a power generation area and a loading area are arranged on the inner wall of the square cabin. The problems that when a rocket projectile is launched, a launching rack and a trolley platform need to be installed and fixed, when the launching rack is installed, a plurality of installing holes in the launching rack and installing holes in the trolley platform need to be horizontally and vertically aligned, then screws are screwed into the installing holes for fixing, and the installing holes are misplaced possibly in the screw screwing process, so that the launching rack is damaged are solved. And therefore, the problem that the launcher is relatively tedious to mount and fix due to the fact that the mounting hole needs to be aligned again and then the screw rod is screwed in is solved.

The utility model provides a supporting and quick separating mechanism of a rocket stabilizing device, the supporting and quick separating mechanism is connected to the bottom of the rocket stabilizing device, and the supporting and quick separating mechanism is connected to an anti-overturning device chassis of the rocket stabilizing device and is supported at the bottom of an anti-overturning arm of the rocket stabilizing device; after the rocket is ignited, the supporting and quick separating mechanism is unlocked, and the anti-overturning arm is released; before the rocket is not ignited, the supporting and rapid separating mechanism is connected to the bottom of the anti-overturning arm in a supporting mode. The supporting and rapid separating mechanism comprises a two-stage deloading supporting mechanism and an aluminum strip; the two-stage load shedding supporting mechanism is connected to the anti-overturning device underframe and is connected to the bottom of the anti-overturning arm in a supporting manner; the aluminum strip is arranged at the bottom of the rocket, and the two ends of the aluminum strip are connected with the two-stage load shedding supporting mechanisms correspondingly. According to the supporting and rapid separating mechanism, stable supporting and unlocking releasing of the anti-overturning arm of the rocket stabilizing device are achieved, so that the anti-overturning arm is rapidly opened, and rocket launching is not hindered.

The invention relates to the technical field of underwater robots, and discloses an underwater launching foundation platform which comprises a cabin body, a launching well, a launching mechanism, a cover opening air bag and an air compressor, the cabin body comprises a cabin shell and a cabin cover, an opening is formed in one end of the cabin shell, and a monitoring camera is installed on the cabin shell; the cabin cover covers the opening and is detachably connected with the cabin shell; the launching well is arranged in the cabin shell, a well opening is formed in the top of the launching well and is opposite to the opening, and a well lid is fixedly arranged at the well opening in a heat sealing mode; the launching mechanism is arranged in the launching well and is used for launching a striking instrument; the uncovering airbag is fixed in the cabin shell and is close to the opening; the air compressor is arranged in the cabin shell and communicates with the inner space of the uncovering air bag and the inner space of the launching well. The underwater launching foundation platform is higher in detection capacity, opening of the well lid and the hatch cover can be achieved through cooperation of the air compressor, the cover opening air bag and the heat sealing well lid, smoothness of a launching channel is guaranteed, energy consumption of the underwater launching foundation platform is reduced, meanwhile, fault tolerance of the hatch cover and the well lid is improved, and cost is reduced.

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 invention relates to a solid carrier rocket transporting and erecting device and launching implementation steps, and the solid carrier rocket transporting and erecting device comprises a transfer platform, an erecting arm is hinged to one end of the transfer platform, and the erecting arm is used for fixing a rocket body; the first erecting oil cylinder is hinged to the transfer platform, the output end of the first erecting oil cylinder is in driving connection with a bracket, the bracket is located on the side edge of the erecting arm, the end of the bracket is hinged to the hinged end of the erecting arm, and the bracket is used for supporting the erecting arm to reach a first erecting angle; the second erecting oil cylinder is hinged to the bracket, the output end of the second erecting oil cylinder is in driving connection with the erecting arm, and the second erecting oil cylinder is used for driving the erecting arm to be away from or close to the bracket to reach a second erecting angle. The device meets the transfer requirements of different rocket bodies, has a horizontal transportation butt joint mode and a vertical transportation butt joint mode, improves the adaptability, reduces the launching cost and improves the transfer speed. Therefore, the problems that in the prior art, a transportation and transfer device is single in structure, and horizontal butt-joint transportation and vertical butt-joint transportation cannot be achieved at the same time are solved.

The invention relates to the technical field of launching platforms, and discloses an offshore suspension type rocket launching platform structure which comprises a ship body assembly, overturning assemblies, a floating assembly, a feeding assembly and a launching assembly, the overturning assemblies are symmetrically hinged to the two sides of the ship body assembly, and the floating assembly is connected with the overturning assemblies through a stabilizing assembly; the feeding assemblies are symmetrically arranged on the top of the ship body assembly, and the launching assembly is installed in the middle of the ship body assembly. A first overturning frame is installed on the floating assembly, a second overturning frame is rotationally connected to the middle of the first overturning frame, a third overturning frame is rotationally connected to the middle of the second overturning frame, propellers are installed in the middle of the third overturning frame, and the propellers are installed on the first overturning frame in a four-corner distribution mode; the problems that in the prior art, an existing offshore suspension type rocket launching platform is poor in stability due to fluctuation of seawater, and the launching angle cannot be adjusted are solved.

The invention relates to the technical field of carrier rocket transfer, in particular to a carrier rocket transfer device which comprises a carrier and a position adjusting mechanism. The carrier is used for bearing and transporting the erecting arm carrying the carrier rocket so as to transfer the carrier rocket to the position close to the fixed launching pad. The position adjusting mechanism is installed on the carrier. The carrier can drive the position adjusting mechanism to move up and down so as to drive the erecting arm to move up and down. The position adjusting mechanism can drive the erecting arm to move or rotate in the plane where the position adjusting mechanism is located. When the rotating base arranged at one end of the erecting arm is in butt joint with the rotating base arranged on the fixed launching pad, the erecting arm is driven by the carrier to conduct position coarse adjustment, then the erecting arm is driven by the position adjusting mechanism to move or rotate in the plane where the position adjusting mechanism is located, the position of the erecting arm is accurately adjusted, the butt joint difficulty is greatly reduced, and the butt joint efficiency is improved. The butt joint precision and the butt joint efficiency are improved when the rotating seat of the erecting arm is in butt joint with the rotating seat of the fixed launching pad.

The invention discloses an on-rocket air conditioner connector, which relates to the technical field of spaceflight and comprises a main sleeve, at least one set of ball lock mechanism and an air valve mechanism, the main sleeve at least comprises a sleeve body, a mounting base is arranged on the outer side of one end of the sleeve body, and the other end of the sleeve body communicates with an air conditioner pipe. The ball lock mechanism at least comprises a locking pin and a locking sleeve matched with the locking pin. The locking pin is arranged on the mounting seat; the locking sleeve is arranged on the rocket body fairing; the air valve mechanism is arranged on the mounting seat and is communicated with the locking pin of the ball lock mechanism; during locking, the air valve mechanism does not supply air into the locking pin of the ball lock mechanism, and the locking pin and the locking sleeve are in a locking state; and during separation, the air valve mechanism supplies air to the locking pin of the ball lock mechanism, and the locking pin and the locking sleeve are in a separated state. The device has the advantages of being reliable in locking, small in unlocking force, capable of achieving redundant unlocking and the like, and a rocket can automatically fall off before taking off in an unattended state and can be effectively separated from a rocket body.

The invention provides a launch device of a carrier rocket, a use method and a launch system. The launching device is used for executing a launching task or a test run task, and comprises a fixed launching pad which is fixed at a launching site, is in butt joint with a carrier rocket during execution of the launching task, is in butt joint with a movable launching pad during execution of the test run task, and comprises a traction assembly; the bottom end of the movable launching pad is butted with the fixed launching pad, and the top end is butted with a carrier rocket sub-stage during a test run task execution period; one end of the mooring tool is used for being detachably connected with the top end of the carrier rocket sub-stage during the test run task execution period, and the other end of the mooring tool is in transmission connection with the traction assembly in a detachable mode; and the control system is in communication connection with the traction assembly and the mooring tool during execution of the test run task, and controls the traction assembly to adjust the pre-tightening force of the traction assembly according to the pre-tightening force information fed back by the mooring tool. According to the launching device, manpower, material resources and time cost can be greatly saved, and the structural integrity of the rocket body is guaranteed.

The invention belongs to the technical field of offshore launching platforms, and discloses a self-lifting and moving offshore launching platform which comprises a damping plate and a bearing ship body, a bottom plate is arranged above the bearing ship body, a rotating mechanism is arranged between the bearing ship body and the bottom plate, a stabilizing plate is arranged above the bottom plate, and a stabilizing mechanism is arranged between the bottom plate and the stabilizing plate. A lifting mechanism is arranged on the upper surface of the stabilizing plate, a vibration isolation mechanism is arranged between the moving plate and the vibration reduction plate, through the arrangement of the vibration isolation mechanism, in the rocket launching process, vibration is firstly transmitted to the vibration reduction plate, a first damper and a first spring absorb and buffer part of vibration energy, and meanwhile through linkage of a series of components, the vibration reduction effect is achieved. The vibration energy is further dispersed and consumed, finally, through secondary buffering of a second damper and a second spring, it is ensured that vibration cannot cause too large influence on the moving plate and the structure above the moving plate, the vibration control effect is remarkably enhanced, and the negative influence of vibration on a rocket is reduced.

The present invention discloses a noise reduction and flow guiding device for a launch ship guide trough and a design method, which belongs to the field of rocket launch technology, wherein the noise reduction and flow guiding device for a launch ship guide trough comprises a curved guide plate and a fixed bracket; the bottom surface of the guide plate is fixedly connected to the side edge of the guide trough outlet arranged on the launch ship; the lower end of the guide plate is smoothly transitioned to the edge of the guide trough outlet; the projection of the upper end of the guide plate in the vertical direction at least covers a part of the guide trough; the fixed bracket is fixedly arranged on the launch ship and fixedly connected to the guide plate. The present invention can change the direction of the gas jet at the outlet of the guide trough, thereby reducing the influence of the vibration noise generated by the jet tail flame on the rocket body.

The invention relates to the technical field of fixed launching pad structures, in particular to a fixed launching pad structure which comprises a table body, a partition is connected to the center of the interior of one side of the table body in a partition mode, handrails are symmetrically and fixedly connected to the edge of the upper end of the table body in parallel, and turning plates are rotationally connected to the front side and the rear side of the table body through connecting shafts. The inner wall of the upper end of the inner side of the table body is fixedly connected with a first rotating shaft, the inner side of the first rotating shaft is rotationally connected with a frame, the upper end of the frame is fixedly connected with multiple sets of corrugated boards, the inner walls of the two sides and the rear side of the interior of the table body are fixedly connected with second rotating shafts, and the inner sides of the second rotating shafts are rotationally connected with connecting rods. The rear side of the connecting rod is fixedly connected with an overturning oil cylinder, the tail end of one side of the connecting rod is fixedly connected with a connecting rod, the center of the connecting rod is fixedly connected with an overturning shaft, and the tail end of the upper end of the connecting rod is rotationally connected with a frame. And the four-bar mechanism is driven by the overturning oil cylinder, and the stability of the cover plate is improved by utilizing a connecting rod dead point.

The invention discloses a bomb blocking and locking device and a design method, the bomb blocking and locking device is installed between a launching tube and a launching power device, the bomb blocking and locking device comprises a flange plate, a locking piece and an anti-rotating pin, and the flange plate is connected with the launching tube and the launching power device through mechanical interfaces; a locking ring face protruding out of the front disc face is coaxially formed on the front disc face of the flange disc, the rear end of the launching tube is matched with the front disc face of the flange disc, and the locking ring face is inserted into the launching tube and matched with the rear end of the aircraft. Locking through holes are distributed in the locking ring face in the circumferential direction and comprise straight-through holes and step through holes which are distributed in a staggered mode. And bullet tail threaded holes matched with the locking through holes in a one-to-one mode are formed in the rear end face of the aircraft, after the aircraft is assembled in the launching tube, the anti-rotating pins are assembled into the corresponding bullet tail threaded holes through the straight through holes, and the locking pieces are assembled into the corresponding bullet tail threaded holes through the step through holes so as to achieve bullet blocking and locking of the aircraft.