CN110701965A - Universal large-depth submarine-launched missile launching simulation system - Google Patents
Universal large-depth submarine-launched missile launching simulation system Download PDFInfo
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- CN110701965A CN110701965A CN201910939919.XA CN201910939919A CN110701965A CN 110701965 A CN110701965 A CN 110701965A CN 201910939919 A CN201910939919 A CN 201910939919A CN 110701965 A CN110701965 A CN 110701965A
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- 238000004088 simulation Methods 0.000 title claims abstract description 147
- 230000007246 mechanism Effects 0.000 claims abstract description 87
- 238000007789 sealing Methods 0.000 claims abstract description 74
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 30
- 238000001514 detection method Methods 0.000 claims description 33
- 239000012528 membrane Substances 0.000 claims description 7
- 239000005341 toughened glass Substances 0.000 claims description 6
- 238000003825 pressing Methods 0.000 claims description 2
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- 238000000034 method Methods 0.000 abstract description 21
- 230000008569 process Effects 0.000 abstract description 19
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- 238000002474 experimental method Methods 0.000 abstract description 7
- 238000012544 monitoring process Methods 0.000 abstract description 5
- 238000012360 testing method Methods 0.000 description 17
- 230000005540 biological transmission Effects 0.000 description 12
- 238000009434 installation Methods 0.000 description 9
- 230000003139 buffering effect Effects 0.000 description 8
- 230000033001 locomotion Effects 0.000 description 7
- 238000012986 modification Methods 0.000 description 4
- 230000004048 modification Effects 0.000 description 4
- 238000011160 research Methods 0.000 description 4
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- 238000002360 preparation method Methods 0.000 description 3
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- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000007306 turnover Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
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- 239000006185 dispersion Substances 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 238000001727 in vivo Methods 0.000 description 1
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- 238000004451 qualitative analysis Methods 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
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Abstract
The invention discloses a general large-depth submarine-launched missile launching simulation system, which comprises a fixed platform and a sealing simulation device erected on the fixed platform, wherein the lower end of the sealing simulation device is connected with a launching mechanism; the simulation device comprises a simulation bin body, wherein the upper end of the simulation bin body is connected with a simulation bin sealing cover, a bin charging pressure hole is formed in the simulation bin sealing cover, the lower end of the simulation bin body is connected with a sealing plate, an anti-collision mechanism is arranged in the simulation bin body and close to one end of the simulation bin sealing cover, the sealing plate is connected with a transmitting mechanism, an automatic flip mechanism is arranged between the transmitting mechanism and the inner wall of the simulation bin body, the simulation bin sealing cover, the sealing plate and the transmitting mechanism form a sealed simulation bin; aiming at the experiment under the laboratory condition, the invention meets the monitoring of parameters such as missile speed, attitude, launching port flow field and the like in the launching process under various pressure environments and temperature environments, and ensures the wide application range of deep water environment change.
Description
Technical Field
The invention relates to the technical field of missile launching devices, in particular to a general large-depth submarine-launched missile launching simulation system.
Background
The research and the experiment of water inlet and outlet are successively developed from the late 60 years in China, a large amount of experimental research and theoretical analysis work is carried out under the condition of limited equipment, and certain achievements are obtained. However, from the current domestic situation, the test equipment of the scaling model is not perfect, the simulation is not true, particularly, the stability of the shear wave test is poor, and the dispersion is large, so that only qualitative analysis can be explained, but not quantitative results.
In order to conduct underwater launch studies, a great deal of complex and detailed experimental work is required. In order to carry out the research and test of underwater launching, a plurality of large-scale underwater test devices are needed, the construction period is very long, a large amount of investment is needed, and due to the fact that what kind of facilities are tried to be constructed, the problem that the target range is carefully considered is solved. Therefore, a feasible method can be drawn, and repeated curved road walking is avoided.
Disclosure of Invention
The invention aims to solve the problems and adopts the technical scheme that:
a general large-depth submarine-launched missile launching simulation system comprises a fixed platform and a sealing simulation device erected on the fixed platform, wherein the lower end of the sealing simulation device is connected with a launching mechanism;
the simulator comprises a simulation cabin body, the upper end of the simulation cabin body is connected with a simulation cabin sealing cover, a cabin filling pressure measuring hole is formed in the simulation cabin sealing cover, the lower end of the simulation cabin body is connected with a sealing plate, an anti-collision mechanism is installed at one end, close to the simulation cabin sealing cover, of the interior of the simulation cabin body, the sealing plate is connected with a transmitting mechanism, an automatic flip mechanism is arranged between the transmitting mechanism and the inner wall of the simulation cabin body, the simulation cabin sealing cover, the sealing plate and the transmitting mechanism form a sealed simulation cabin, and an.
Preferably, the simulation bin body is of a cylindrical structure, the circumference of the outer edge of the upper end of the simulation bin body is provided with a matching convex edge, the circumference of the outer edge of the sealing cover of the simulation bin is provided with a connecting convex edge, and the connecting convex edge is connected with the matching convex edge through screws in a circumferential array; the periphery of the inner eave of the upper end of the simulation bin body is provided with a containing groove, a sealing ring is arranged in the containing groove, and the periphery of the inner eave of the sealing cover of the simulation bin body is provided with a pressing portion which is matched with the containing groove to press the sealing ring.
Preferably, anticollision institution is including buffering subassembly and crash pad, the buffering subassembly includes the anticollision dish, and the outer eaves of anticollision dish is connected with a plurality of buffering springs with simulation storehouse internal wall circumference, the anticollision dish upside is equipped with the crash pad, the crash pad is installed at the sealed internal wall of lid in simulation storehouse.
Preferably, the upper end of the launching mechanism penetrates through the sealing plate to enter the simulation cabin body, and a plurality of reinforcing ribs are circumferentially arranged between the outer wall of the launching mechanism and the sealing plate.
Preferably, the launching mechanism comprises a launching bin and a launching bin cover arranged at the upper end of the launching bin, one end of the launching bin close to the launching bin cover is provided with a waterproof membrane, a launching barrel and a positioning locking mechanism used for positioning the launching barrel are coaxially arranged in the launching bin, the lower end of the launching barrel is connected with a driving seat, the driving seat and the lower end of the launching barrel enclose a driving bin, the lower end of the driving seat is communicated with a pressure bin through a gas transmission conduit, the gas transmission conduit is provided with an electromagnetic valve, the lower end of the pressure bin is connected with an inflation conduit, the side of the connection part of the inflation conduit and the pressure bin is provided with a gas outlet conduit communicated with the launching bin, the gas outlet conduit is provided with a control valve, the connection part of the inflation conduit close; the free end of the inflation conduit passes through the bottom of the launching bin and is connected with the air source assembly.
Preferably, location blocked mechanical system is including installing the holding ring in launching storehouse inner wall upper end and installing the locking portion at launching storehouse inner wall lower extreme, launching tube outer wall lower extreme circumference array has the protruding eaves of locking with locking portion cooperation installation, installs the adapter between the upper end of launching tube outer wall and launching storehouse inner wall upper end, and the lower terminal surface and the holding ring up end cooperation installation of adapter.
Preferably, the automatic cover turning mechanism comprises a linear motor arranged along the axial direction of the inner wall of the simulation bin body and a connecting rod arranged below the linear motor and hinged to the inner wall of the simulation bin body, a power rod is hinged between the linear motor and the connecting rod, and a turning rod is hinged to the other end of the connecting rod and the launching mechanism.
Preferably, the observation and detection mechanism comprises an internal detection mechanism and an external detection mechanism, the internal detection mechanism is arranged in the simulation bin body and comprises a water outlet detection mechanism and a water pressure sensor, and the water outlet detection mechanism is arranged at one end, close to the anti-collision mechanism, of the inner wall of the simulation bin body; the external detection mechanism is arranged outside the simulation cabin body and comprises a high-speed camera and a corrugation instrument.
Preferably, the simulation cabin body is provided with an observation window, the observation window is set to be a conical cylindrical surface, toughened glass is installed in the observation window, the end with the larger diameter of the observation window is connected with the simulation cabin body, the end with the smaller diameter of the observation window is horizontally detachably connected with a placing table, and a high-speed camera and a corrugation instrument are placed on the placing table.
Preferably, the observation windows are provided with a plurality of groups along the axial direction of the simulation cabin body, toughened glass is installed in the observation windows, and the outer sides of the observation windows are respectively and correspondingly provided with a placing table.
The invention has the following beneficial effects:
1. the invention relates to an underwater missile launching simulation device, which aims at the test under the laboratory condition, has compact structure, convenient use, small volume and light weight on the premise of meeting the requirement of the experimental environment condition in the design process; meanwhile, the device has a reliable structure, has sufficient safety margin in structural strength and sealing effect, can meet the requirements of monitoring parameters such as missile speed and posture in the launching process under various pressure environments and temperature environments, the launching port flow field in the launching process of the launching tube and the like, and ensures a large application range of deep water environment change.
2. The invention is provided with an observation detection mechanism, can synchronously detect the relevant parameters of the guided missiles in different test environments, and the detection process is carried out aiming at the internal and external aspects, wherein (a) the internal part is as follows: and internal parameter detection equipment such as a water pressure sensor, a speed sensor, a laser velocimeter and the like detects flow field parameters, missile movement speed and attitude parameters. (b) External: the high-speed camera and the ripple instrument are used for detecting parameters of dynamic attitude of missile water outlet, dynamic processes such as supercavity forming and dissipating process, flow field change and the like, so that omnibearing parameter detection under synchronous conditions is realized, and true matching of experimental data is reliably ensured.
3. The invention is provided with the launching mechanism, and aiming at different test requirements, the launching mechanism adopts multiple caliber matching to realize the test of launching devices with different models and different calibers, so that the device has wide application range.
4. The general large-depth submarine-launched missile launching simulation device is provided with the anti-collision mechanism, so that the simulated missile can be reliably stopped in the device after the simulated missile launching parameters are detected, and the safety of experimental equipment can be ensured.
Drawings
FIG. 1 is a schematic front view of the present invention;
FIG. 2 is a right side view of the present invention;
FIG. 3 is a partial schematic view of a crash prevention mechanism according to the present invention;
FIG. 4 is a schematic view of a firing mechanism of the present invention;
FIG. 5 is an enlarged view of the launching mechanism A of the present invention;
FIG. 6 is a schematic view of the present invention in use 1;
fig. 7 is a schematic view of the present invention in use 2.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
Embodiment mode 1:
as shown in fig. 1, in order to perform theoretical research on a deep submarine-launched missile, sufficient experimental data is required as a support, and on this background, a general large-depth submarine-launched missile launching simulation device is developed and designed, and the application range of the device is as follows: the water depth is 0-300 m under the marine environment condition, the length-diameter ratio of the simulated bomb is not more than 20:1, the temperature is-10-40 ℃ under the marine environment, and the maximum environmental pressure is not more than 2 Mpa.
As shown in fig. 1, a general large-depth submarine-launched missile launching simulation system is designed according to the above experimental conditions, and includes a fixed platform 7 and a sealing simulation device erected on the fixed platform 7, in this embodiment, the fixed platform 7 is a concrete platform, and the sealing simulation device is erected on the fixed platform 7 through a bracket assembly 8, in this embodiment, the bracket assembly 8 is the prior art and is not described herein again, and the lower end of the sealing simulation device is connected with a launching mechanism 6;
as shown in fig. 1-3, the simulation device includes a simulation cabin body 3, the upper end of the simulation cabin body 3 is connected with a simulation cabin sealing cover 1, preferably, the outer side of the simulation cabin sealing cover 1 is provided with a convex spherical surface, the inner side of the simulation cabin sealing cover 1 is provided with a concave spherical surface, the concave spherical surface is provided to extend the buffer circuit of the simulation missile 65, a plurality of hanging rings 12 are circumferentially arrayed on the convex spherical surface to facilitate the hoisting machinery to hoist the simulation cabin sealing cover 1, a cabin charging pressure hole 11 is installed on the simulation cabin sealing cover 1, and can be used for injecting water, realizing the pressure required for the experiment in the sealed simulation cabin by charging pressure, and also installing a pressure gauge to monitor the pressure in the sealed simulation cabin;
as shown in fig. 1-3, a sealing plate 5 is connected to the lower end of the simulation bin body 3, an anti-collision mechanism 2 is installed at one end, close to the simulation bin sealing cover 1, inside the simulation bin body 3, the sealing plate 5 is connected with a launching mechanism 6, an automatic flip mechanism 9 is arranged between the launching mechanism 6 and the inner wall of the simulation bin body 3, and the automatic flip mechanism 9 is used for opening the launching mechanism 6 to launch a simulation missile 65; the upper end of the preferred launching mechanism 6 penetrates through the sealing plate 5 to enter the simulation cabin body 3, a launching mechanism mounting opening 51 connected with the launching mechanism 6 is formed in the preferred sealing plate 5, and a plurality of reinforcing ribs 52 are circumferentially arranged between the outer wall of the launching mechanism 6 and the sealing plate 5. The simulation cabin body 3, the simulation cabin sealing cover 1, the sealing plate 5 and the emission mechanism 6 form a sealed simulation cabin, and an observation detection mechanism is arranged on the sealed simulation cabin.
As shown in fig. 1-3, in order to realize the sealing connection between the simulation bin body 3 and the simulation bin sealing cover 1 and ensure the stable air pressure inside the sealed simulation bin to achieve the simulation environment, a matching convex brim 31 is arranged on the circumference of the outer brim at the upper end of the simulation bin body 3, a connecting convex brim 13 is arranged on the circumference of the outer brim of the simulation bin sealing cover 1, and the connecting convex brim 13 is connected with the matching convex brim 31 through a screw of a circumferential array; for better realization sealing effect, install sealing washer 33 between the sealed lid 1 of simulation storehouse body 3 and simulation storehouse, the eaves circumference is equipped with holding tank 32 in the 3 upper ends of the simulation storehouse body, installs sealing washer 33 in the holding tank 32, the eaves circumference is equipped with the portion 14 that compresses tightly sealing washer 33 with holding tank 32 cooperation in the sealed lid 1 of simulation storehouse, the portion 14 that compresses tightly of the sealed lid 1 of simulation storehouse is for compressing tightly the face towards sealing washer 33 one side, is equipped with the groove that compresses tightly dorsad on one side of sealing washer 33.
As shown in fig. 1-3, after the simulated missile 65 is launched during the experiment, the simulated missile passes through a water area arranged in the sealed simulation bin, the observation detection mechanism can detect and record flow field parameters, the motion speed and the attitude parameters of the simulated missile 65, and parameters of dynamic processes such as the detection of the dynamic attitude of the water discharged from the missile, the formation and dissipation process of supercavity, the flow field change and the like, and the simulated missile 65 needs to be stopped in time after rushing out of the arranged water area, so that the damage of the simulated missile 65 to the sealed simulation bin is avoided; corresponding anticollision institution 2 has been set up to simulation guided missile 65, anticollision institution 2 is including buffer assembly and crashproof pad 21, buffer assembly includes crashproof dish 22, and the outer eaves of crashproof dish 22 is connected with a plurality of buffering springs 23 with simulation storehouse 3 inner wall circumference in vivo, and buffering spring 23 is not less than 17.8N/mm according to the design requirement K value in this embodiment, crashproof pad 21 is installed at the sealed 1 inner wall in simulation storehouse, and crashproof pad 21 border fastening installation is in the sealed inslot that compresses tightly of 1 in simulation storehouse.
In order to ensure the structure reliability of the buffer assembly, after the launching parameters of the simulated missile 65 are detected, the simulated missile 65 can be reliably stopped, so that the safety of experimental equipment is ensured, a convex spherical surface is arranged on one side, close to the simulated cabin sealing cover 1, of the anti-collision disc 22, a concave spherical surface is arranged on one side, back to the simulated cabin sealing cover 1, of the anti-collision disc 22, and a plurality of pull holes matched with the buffer springs 23 are formed in the circumferential array of the outer eaves of the anti-collision disc 22; the 3 inner walls in the simulation storehouse body are equipped with a plurality of connecting seats of connecting buffering spring 23, are equipped with the through-hole on the connecting seat, install the screw in the through-hole, and buffering spring 23 one end is installed in the trombone, and the other end suit is on the screw, the card is on the connecting seat.
As shown in fig. 4-5, in the testing experiment process, in order to realize the launching of the general large-depth submarine-launched simulated missile 65, a corresponding launching device is provided, and the launching device for the general large-depth submarine-launched simulated missile 65 comprises a launching cabin 62 and a launching cabin 62 cover 61 installed at the upper end of the launching cabin 62, preferably, the launching cabin 62 is designed in a cylindrical shape, the launching cabin 62 cover 61 can be opened in a rotating manner relative to the launching cabin 62, one end of the launching cabin 62, which is close to the launching cabin 62 cover 61, is provided with a waterproof membrane, the waterproof membrane is used for separating the launching environment of the simulated missile 65 from the experimental environment, a launching barrel 63 and a positioning locking mechanism 64 for positioning the launching barrel 63 are coaxially installed in the launching cabin 62, preferably, the launching barrel 63 is cylindrical, the lower end of the launching barrel 63 is connected with a driving seat 67, the driving seat 67 and the lower end of the launching barrel 63 form a driving cabin 671, the lower, the electromagnetic valve 681 is arranged on the gas transmission conduit, the lower end of the pressure bin 68 is connected with the gas transmission conduit 693, a gas transmission conduit 695 communicated with the launching bin 62 is arranged at the connection part of the gas transmission conduit 693 and the pressure bin 68, a control valve is arranged on the gas transmission conduit 695, a gas transmission branch pipe 694 is arranged on the gas transmission conduit 693 close to the connection part of the pressure bin 68, and a control valve is arranged on the gas transmission branch pipe 694; when the inflation branch pipe 694 is in a working state, the inflation branch pipe 694 is connected with the same air source with the bin inflation pressure measuring hole 11, and the filled air is guided into the launching bin 62 through the air outlet guide pipe 695, so that the pressure intensity in the launching bin 62 and the pressure intensity in the sealed simulation bin are kept consistent; the free end of the inflation conduit 693 penetrates through the bottom of the launching bin 62 to be connected with the air source assembly 69, the air source assembly 69 comprises a high-pressure air source, the high-pressure air source is connected with the free end of the inflation conduit 693, an air source stop valve 692 is installed on the inflation conduit 693 close to the high-pressure air source end, the input and the output of an air source are controlled through the air pressure value of the pressure bin 68, the high-pressure air bottle 691 in the embodiment is a high-pressure air bottle 691 with the pressure of 30Mpa, and the high-pressure air bottle 691.
As shown in fig. 4-5, in order to launch different types of simulated missiles 65, the launching tube 63 needs to be easily disassembled and has good locking and positioning relative to the launching bin 62, the locking mechanism 64 includes a positioning ring 641 installed on the upper end of the inner wall of the launching bin 62 and a locking part installed on the lower end of the inner wall of the launching bin 62, a plurality of locking flanges 631 are arranged on the circumferential array of the lower end of the outer wall of the launching tube 63 and are matched with the locking part, preferably two locking flanges 631 are arranged on the circumferential array of the outer wall of the launching tube 63, an adapter 642 is installed between the upper end of the outer wall of the launching tube 63 and the upper end of the inner wall of the launching bin 62, the lower end surface of the adapter 642 is matched with the upper end surface of the positioning ring 641, the adapter 642 is preferably circular, and is used for positioning the upper end of the launching tube 63 to prevent the upper end, affecting the water intake path of the simulated missile 65, the positioning ring 641 is used to position the adapter 642; locking portion and the protruding eaves 631 cooperation installation of locking, be used for the location to support launching tube 63 lower extreme, it is reliable to guarantee that launching tube 63 is connected with launching bin 62, locking portion can realize unblanking and shutting two kinds of states with the cooperation of the protruding eaves 631 of locking simultaneously, the state of unblanking is convenient for launching tube 63 and is dismantled, the axial motion of launching tube 63 relative launching bin 62 can be restricted to the shutting state, guarantee that launching tube 63 can realize the transmission of simulation guided missile 65, it is sealed with the drive storehouse 671 that the drive seat 67 formed also to be convenient for launching tube 63 lower extreme, avoid the atmospheric pressure loss, influence the transmission power of simulation guided missile 65.
As shown in fig. 4-5, in order to better achieve locking and positioning of the launch barrel 63 relative to the launch bin 62, the locking portion includes positioning seats 645 and locking seats 643 which are installed at intervals along the axial direction of the launch bin 62, the positioning seats 645 are disposed near the lower end of the launch bin 62, the inner wall of the positioning seats 645 is connected with the outer wall of the driving seat 67, preferably, seamless welding is adopted, the inner wall of the locking seats 643 is installed in cooperation with the outer wall of the launch barrel 63, a locking cavity 644 is formed between the positioning seats 645 and the locking seats 643, and the locking cavity 644 is installed in cooperation with the locking ledge 631 for locking; the locking seat 643 is circumferentially arrayed with locking slots for matching with the locking brim 631. When the device is in an installation state, the launching tube 63 is hoisted to axially enter the launching bin 62 along the launching bin 62, the locking convex eaves 631 at the lower end of the launching tube 63 enter the locking cavity 644 along the unlocking groove, the launching tube 63 is rotated to realize dislocation of the locking convex eaves 631 and the unlocking groove, at the moment, locking action is completed, and the launching tube 63 cannot axially move relative to the launching bin 62; when the installation state is disassembled, the locking convex eaves 631 rotate to the unlocking groove, so that the locking convex eaves 631 and the unlocking groove are aligned, and the launching tube 63 is axially hung out of the launching bin 62.
As shown in fig. 4-5, in order to launch the simulated missile 65 out of the launcher 63, a driving piston 66 is arranged at the bottom of the launcher 63, the driving piston 66 is in contact with the bottom of the simulated missile 65, during launching, high-pressure gas pushes the driving piston 66 to move, the driving piston 66 indirectly drives the simulated missile 65 to fly out of the launcher 63 in an accelerating manner, a piston stopper 632 is arranged at the top of the launcher 63, the driving piston 66 is prevented from flying out of the launcher 63 together with the simulated missile 65, certain influence is generated on the test of the simulated missile 65, and meanwhile, the driving piston 66 is convenient to be recycled for multiple times.
As shown in fig. 4-5, in order to facilitate the control of the simulated missile 65 entering the simulated cabin 3 from the launching cabin 62 during launching, a mechanism for controlling the turnover of the cover 61 of the launching cabin 62 is required, the automatic cover-turning mechanism 9 comprises a linear motor 92 arranged along the axial direction of the inner wall of the simulated cabin 3 and a connecting rod 94 positioned below the linear motor 92 and hinged to the inner wall of the simulated cabin 3, a power rod 93 is hinged between the linear motor 92 and the connecting rod 94, a turnover rod 91 is hinged between the free end of the connecting rod 94 and the launching mechanism 6,
as shown in fig. 2 and 6, in order to realize the monitoring of the motion data of the simulated missile 65 in the simulated cabin body 3 and synchronously detect the relevant parameters of the missiles in different test environments, the observation detection mechanism comprises an internal detection mechanism and an external detection mechanism,
as shown in fig. 2 and 6, the internal detection mechanism is installed inside the simulated bin body 3 and comprises a water outlet detection mechanism speed sensor and a water pressure sensor, preferably, the water detection mechanism is a laser velocimeter 15, and the laser velocimeter 15 is adopted in the embodiment; the water outlet detection mechanism is arranged at one end, close to the anti-collision mechanism 2, of the inner wall of the simulation cabin body 3, and can realize detection of equipment and flow field parameters, missile movement speed and attitude parameters.
As shown in fig. 2 and 6, the external detection mechanism is installed outside the simulation cabin body 3, and comprises a high-speed camera and a wavemeter 16, so that parameters such as dynamic processes of missile water outlet dynamic attitude, supercavity forming and dissipating processes, flow field changes and the like can be detected; therefore, the inside and outside matching realizes the omnibearing parameter detection under the synchronous condition, and the true matching of experimental data is reliably ensured.
As shown in fig. 2 and 6, in order to facilitate real-time monitoring and photographing of dynamic processes such as a missile water outlet dynamic posture, a supercavitation formation and dissipation process, flow field change and the like, the arrangement of an observation window 4 is facilitated, the connection of a simulation cabin body 3 and the observation window 4 is facilitated, a plurality of groups of observation windows 4 are axially arranged along the simulation cabin body 3, toughened glass is installed in the observation windows 4, placing tables are correspondingly arranged on the outer sides of the observation windows 4 respectively, and a high-speed camera and a corrugation meter 16 are placed on the placing tables respectively.
Embodiment mode 2:
as shown in fig. 7, in order to facilitate real-time monitoring and photographing of dynamic processes such as a missile water-outlet dynamic attitude, a supercavity formation and dissipation process, and a flow field change, the difference from the embodiment 1 is that a placement position of an observation and detection mechanism is arranged on the simulation cabin body 3, so that the structure is compact; the simulation cabin body 3 is provided with a plurality of observation windows 4, the observation windows 4 are arrayed along the circumference of the simulation cabin body 3, 2 observation windows 4 are preferably designed, the observation windows 4 are set to be conical cylindrical surfaces, the cone angle of each observation window 4 is designed to be 108 degrees, all conditions of the simulated missile 65 running in the simulation cabin body 3 can be observed through the observation windows 4, toughened glass is arranged in each observation window 4, one end of each observation window 4 with the larger diameter is connected with the simulation cabin body 3, and the observation windows 4 and the simulation cabin body 3 are preferably connected in a welding mode; the horizontal detachable connection of the less one end level of observation window 4 diameter has placed the platform, places the bench and has placed high-speed camera and ripple appearance 16.
In this embodiment, the laser velocimeter 15, the high-speed camera and the ripple meter 16 are all the prior art, and are not described herein, and the linear motor 92 and the electromagnetic valve 681 are also the prior art and are not described herein again.
The invention takes the simulation of a 200m deep water launching experiment as an example, and the test process is as follows:
1. test preparation procedure
A worker adjusts parts connected with the simulation bin body 3 and the simulation bin sealing cover 1, and opens the simulation bin sealing cover 1; the anti-collision buffer device is detached, the linear motor 92 is driven, the linear motor 92 moves along the axial direction of the inner wall of the simulation cabin body 3 to control the power rod 93 to move, the power rod 93 controls the turning rod 91 to turn upwards through the connecting rod 94, the cover 61 of the launching cabin 62 at the upper end of the launching cabin 62 is opened, the launching barrel 63 to be tested is hoisted along the axial direction of the launching cabin 62 to enter the launching cabin 62, the locking convex eaves 631 on the launching barrel 63 are aligned with the unlocking grooves by adjusting the relative positions of the launching barrel 63 and the launching cabin 62, the launching barrel 63 is continuously hoisted to enable the locking convex eaves 631 at the lower end of the launching barrel 63 to enter the locking cavity 644 through the unlocking grooves on the locking seats 643, the launching barrel 63 is screwed to achieve the dislocation of the locking convex eaves; sequentially hoisting the driving piston 66 and the simulated missile 65 into the launching tube 63 along the axial direction of the launching tube 63, and then installing the adapter 642 on the launching tube 63 to adjust the launching tube 63 to be vertical to complete installation; at the moment, a waterproof membrane and a screwing installation piston stopper 632 are sequentially installed at the opening of the launching cabin 62, after the installation is finished, a linear motor 92 is controlled to move, a power rod 93 is controlled to move, the power rod 93 controls a turning rod 91 to turn downwards through a connecting rod 94, and the launching cabin 62 cover 61 at the upper end of the launching cabin 62 is buckled; installing an anti-collision buffer device, and closing the simulation bin sealing cover 1; injecting water into the sealed simulation bin through the bin charging pressure measuring hole 11 to enable the water depth to reach 2m, then injecting gas into the sealed simulation bin through the bin charging pressure measuring hole 11 to increase the pressure to 2Mpa, and simultaneously injecting gas into the launching bin 62 through the charging branch pipe 694 by the same gas source to increase the pressure to 2.02Mpa, so that the upper and lower pressure balance of the cover 61 of the launching bin 62 is realized; checking, observing and detecting the mechanism to ensure that the mechanism can normally work, opening the air source stop valve 692, enabling the gas in the high-pressure gas cylinder 691 to enter the pressure chamber 68 through the inflation conduit 693, and closing the air source stop valve 692 when a pressure gauge on the pressure chamber 68 reaches a required value, wherein the pressure chamber 68 is punched to be 7Mpa in the embodiment; at this point the preparation is complete.
2. Principle of operation of test
The test is started on the premise that each device is normal before the preparation work is completed,
(1) the linear motor 92 drives the launching silo 62 to open the cover 61, and the launching silo 62 is separated from the sealed simulation silo through the waterproof membrane.
(2) Test observation detection mechanism: the laser velocimeter 15, the high-speed camera and the ripple meter 16 start to operate.
(3) The electromagnetic valve 681 is opened, gas in the pressure bin 68 enters the driving bin 671, the pressure in the driving bin 671 is gradually increased, the driving piston 66 pushes the simulated missile 65 to move in an accelerated mode under the action of the gas pressure, when the driving piston reaches the opening of the launching tube 63, the driving piston 66 is limited by the piston stopper 632 at the opening of the launching tube 63 to be separated from the simulated missile 65, the simulated missile 65 breaks through the waterproof membrane and enters the sealed simulation bin, the high-speed photography and ripple meter records the process of the simulated missile 65 flying out of the launching bin 62, the process of forming air bubbles in the sealed simulation bin is achieved, and the operation speed change and the posture change of the simulated missile 65 are detected and recorded at the same. When the simulated missile 65 flies out of the water surface, the high-speed photography and the ripple meter record the disappearance process of the supercavity, and the laser velocimeter 15 detects and records the water outlet speed of the simulated missile 65.
(4) After the simulated missile 65 is out of water, the warhead of the simulated missile 65 starts to contact the anti-collision disk 22 and drives the anti-collision disk 22 to move together, the anti-collision disk 22 and the buffer spring 23 connected with the inner wall circumference of the simulated cabin body 3 start to generate tensile force on the anti-collision disk 22, the movement speed of the anti-collision disk 22 is reduced, meanwhile, the simulated missile 65 is indirectly decelerated and stopped, the rigidity K value of the buffer spring 23 is generally set according to the initial movement speed and quality parameters of the simulated missile 65, the K value is not less than 17.8N/mm in the embodiment, the anti-collision disk 22 is prevented from being mounted on the simulated cabin sealing cover 1, if the anti-collision disk 22 collides on the simulated cabin sealing cover 1, a certain buffering effect can be achieved through the anti-collision pad 21 mounted on the.
(5) And after the test is finished, releasing pressure and draining water, then opening the simulation bin sealing cover 1, dismounting the anti-collision buffer device, recovering the simulation missile 65, and finishing the experiment.
The present embodiment is not intended to limit the shape, material, structure, etc. of the present invention in any way, and any simple modification, equivalent change and modification made to the above embodiments according to the technical spirit of the present invention are within the scope of the technical solution of the present invention.
In the description of the present invention, it is to be understood that the terms "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be considered as limiting the scope of the present invention.
If the terms "first," "second," etc. are used herein to define parts, those skilled in the art will recognize that: the use of "first" and "second" is merely for convenience in describing the invention and to simplify the description, and unless otherwise stated the above words are not intended to have a special meaning.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: it is to be understood that modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, but such modifications or substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A general large-depth submarine-launched missile launching simulation system is characterized by comprising a fixed platform and a sealing simulation device erected on the fixed platform, wherein the lower end of the sealing simulation device is connected with a launching mechanism;
the simulator comprises a simulation cabin body, the upper end of the simulation cabin body is connected with a simulation cabin sealing cover, a cabin filling pressure measuring hole is formed in the simulation cabin sealing cover, the lower end of the simulation cabin body is connected with a sealing plate, an anti-collision mechanism is installed at one end, close to the simulation cabin sealing cover, of the interior of the simulation cabin body, the sealing plate is connected with a transmitting mechanism, an automatic flip mechanism is arranged between the transmitting mechanism and the inner wall of the simulation cabin body, the simulation cabin sealing cover, the sealing plate and the transmitting mechanism form a sealed simulation cabin, and an.
2. The system for simulating launching of a general large-depth submarine-launched missile according to claim 1, wherein the simulation bin body is of a cylindrical structure, a matching convex brim is arranged on the circumference of an outer brim at the upper end of the simulation bin body, a connecting convex brim is arranged on the circumference of an outer brim of a sealing cover of the simulation bin, and the connecting convex brim and the matching convex brim are connected through screws in a circumferential array; the periphery of the inner eave of the upper end of the simulation bin body is provided with a containing groove, a sealing ring is arranged in the containing groove, and the periphery of the inner eave of the sealing cover of the simulation bin body is provided with a pressing portion which is matched with the containing groove to press the sealing ring.
3. The general large-depth submarine-launched missile launching simulation system according to claim 1, wherein the anti-collision mechanism comprises a buffer assembly and an anti-collision pad, the buffer assembly comprises an anti-collision disc, a plurality of buffer springs are connected with the periphery of the outer edge of the anti-collision disc and the inner wall of the simulation bin body, the anti-collision pad is arranged on the upper side of the anti-collision disc, and the anti-collision pad is mounted on the inner wall of a sealing cover of the simulation bin.
4. The system of claim 1, wherein the upper end of the launching mechanism penetrates through the sealing plate and enters the simulation chamber, and a plurality of ribs are circumferentially arranged between the outer wall of the launching mechanism and the sealing plate.
5. The general large-depth submarine-launched missile launching simulation system according to claim 1, wherein the launching mechanism comprises a launching bin and a launching bin cover mounted at the upper end of the launching bin, a waterproof membrane is mounted at one end of the launching bin close to the launching bin cover, a launching tube and a positioning locking mechanism for positioning the launching tube are coaxially mounted inside the launching bin, a driving seat is connected to the lower end of the launching tube, the driving seat and the lower end of the launching tube enclose a driving bin, the lower end of the driving seat is communicated with a pressure bin through a gas delivery conduit, an electromagnetic valve is mounted on the gas delivery conduit, an inflation conduit is connected to the lower end of the pressure bin, a gas outlet conduit communicated with the launching bin is arranged at the joint of the inflation conduit and the pressure bin, a control valve is mounted on the gas outlet conduit, an inflation branch pipe is arranged at the joint of the inflation conduit close to the; the free end of the inflation conduit passes through the bottom of the launching bin and is connected with the air source assembly.
6. The launching simulation system of a universal large-depth submarine-launched missile according to claim 1, wherein the positioning and locking mechanism comprises a positioning ring mounted at the upper end of the inner wall of the launching bin and a locking part mounted at the lower end of the inner wall of the launching bin, locking convex eaves matched with the locking part are arranged on the circumferential array of the lower end of the outer wall of the launching barrel, an adapter is mounted between the upper end of the outer wall of the launching barrel and the upper end of the inner wall of the launching bin, and the lower end face of the adapter is matched with the upper end face of the positioning ring.
7. The system for simulating launching of a general large-depth submarine-launched missile according to claim 1, wherein the automatic cover-turning mechanism comprises a linear motor arranged along the axial direction of the inner wall of the simulating bin body and a connecting rod arranged below the linear motor and hinged to the inner wall of the simulating bin body at one end, a power rod is hinged between the linear motor and the connecting rod, and a turning rod is hinged to the other end of the connecting rod and the launching mechanism.
8. The system of claim 1, wherein the observation and detection mechanism comprises an internal detection mechanism and an external detection mechanism,
the internal detection mechanism is arranged in the simulation bin body and comprises a water outlet detection mechanism and a water pressure sensor, and the water outlet detection mechanism is arranged at one end, close to the anti-collision mechanism, of the inner wall of the simulation bin body;
the external detection mechanism is arranged outside the simulation cabin body and comprises a high-speed camera and a corrugation instrument.
9. The system of claim 8, wherein the simulated capsule body is provided with an observation window, the observation window is a conical cylinder, toughened glass is arranged in the observation window, the larger end of the observation window is connected with the simulated capsule body, the smaller end of the observation window is horizontally detachably connected with a placing table, and a high-speed camera and a wavemeter are placed on the placing table.
10. The system of claim 8, wherein the plurality of sets of observation windows are arranged along the axial direction of the simulation cabin, the observation windows are provided with toughened glass, and the outer sides of the observation windows are respectively provided with a placing table correspondingly.
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| CN110701965B (en) | 2024-04-12 |
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