CN110701965B - 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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- CN110701965B CN110701965B CN201910939919.XA CN201910939919A CN110701965B CN 110701965 B CN110701965 B CN 110701965B CN 201910939919 A CN201910939919 A CN 201910939919A CN 110701965 B CN110701965 B CN 110701965B
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- 238000004088 simulation Methods 0.000 title claims abstract description 146
- 230000007246 mechanism Effects 0.000 claims abstract description 94
- 238000007789 sealing Methods 0.000 claims abstract description 85
- 238000001514 detection method Methods 0.000 claims abstract description 35
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- 230000003014 reinforcing effect Effects 0.000 claims description 3
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- 238000000034 method Methods 0.000 abstract description 19
- 230000008569 process Effects 0.000 abstract description 17
- 238000002474 experimental method Methods 0.000 abstract description 6
- 238000012544 monitoring process Methods 0.000 abstract description 5
- 238000012360 testing method Methods 0.000 description 21
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Classifications
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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 universal 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 filling 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 at one end, close to the simulation bin sealing cover, of the simulation bin 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 bin body, the simulation bin sealing cover, the sealing plate and the transmitting mechanism form a sealing simulation bin, and an observation and detection mechanism is arranged on the sealing simulation bin; aiming at the experiment under the laboratory condition, the invention satisfies 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 application range of large deepwater environment variation.
Description
Technical Field
The invention relates to the technical field of missile launching devices, in particular to a universal large-depth submarine-launched missile launching simulation system.
Background
The research and test of the water inflow are developed in succession from the end of 60 s in China, a great deal of experimental research and theoretical analysis work is performed under the condition of limited equipment, and a certain result is obtained. However, from the current domestic situation, the test equipment of the scaling model is still imperfect, the simulation is not yet true, and especially the stability of the transverse wave test is poor and the dispersion is large, so that only qualitative analysis can be illustrated, but not quantitative results can be illustrated.
For underwater emission studies, a large number of complex and delicate test works are required. In order to perform the underwater launching research test, a plurality of large-scale underwater test equipment are needed, not only a long construction period is needed, but also a great amount of investment is needed, because the aim of building what facilities is needed is to be considered cautiously for a target range, in order to make China build proper missile underwater launching test facilities to achieve the maximum use effect, the missile underwater launching test task is effectively completed, and in the research of the underwater missile launching technology, a test facility which has a simple structure and can simulate various water depth environments and multiple data monitoring is needed. Thus, we can draw a feasible method and avoid repeated routing.
Disclosure of Invention
The invention aims to solve the problems, and adopts the technical scheme that:
the universal 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 simulation device comprises a simulation bin body, the upper end of the simulation bin body is connected with a simulation bin sealing cover, a bin filling pressure measuring 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 at one end, close to the simulation bin sealing cover, of the simulation bin 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 bin body, the simulation bin sealing cover, the sealing plate and the transmitting mechanism form a sealing simulation bin, and an observation and detection mechanism is arranged on the sealing simulation bin.
Preferably, the simulation bin body is of a cylindrical structure, the circumference of the outer eave at the upper end of the simulation bin body is provided with a matched eave, the circumference of the outer eave of the simulation bin sealing cover is provided with a connecting eave, and the connecting eave is connected with the matched eave through a screw of a circumferential array; the circumference 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 circumference of the inner eave of the sealing cover of the simulation bin body is provided with a pressing part which is matched with the containing groove to press the sealing ring.
Preferably, the anti-collision mechanism comprises a buffer assembly and an anti-collision pad, the buffer assembly comprises an anti-collision disc, an outer eave of the anti-collision disc is connected with a plurality of buffer springs with the circumference of 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 arranged on the inner wall of the sealing cover of the simulation bin.
Preferably, the upper end of the transmitting mechanism penetrates through the sealing plate to enter the simulation bin body, and a plurality of reinforcing ribs are arranged between the outer wall of the transmitting mechanism and the sealing plate in a circumferential manner.
Preferably, the transmitting mechanism comprises a transmitting bin and a transmitting bin cover arranged at the upper end of the transmitting bin, one end, close to the transmitting bin cover, of the transmitting bin is provided with a waterproof membrane, a transmitting cylinder and a positioning locking mechanism for positioning the transmitting cylinder are coaxially arranged in the transmitting bin, the lower end of the transmitting cylinder is connected with a driving seat, the driving seat and the lower end of the transmitting cylinder enclose a driving bin, the lower end of the driving seat is communicated with a pressure bin through a gas transmission pipe, a solenoid valve is arranged on the gas transmission pipe, the lower end of the pressure bin is connected with an inflation pipe, the side of the joint of the inflation pipe and the pressure bin is provided with a gas outlet pipe communicated with the transmitting bin, the gas outlet pipe is provided with a control valve, the joint, close to the pressure bin, of the inflation pipe is provided with an inflation branch pipe, and the inflation branch pipe is provided with a control valve; the free end of the inflation conduit passes through the bottom of the launching bin and is connected with an air source assembly.
Preferably, the positioning locking mechanism comprises a positioning ring arranged at the upper end of the inner wall of the transmitting bin and a locking part arranged at the lower end of the inner wall of the transmitting bin, a circumferential array of the lower end of the outer wall of the transmitting cylinder is provided with a locking convex eave matched with the locking part, an adapter is arranged between the upper end of the outer wall of the transmitting cylinder and the upper end of the inner wall of the transmitting bin, and the lower end face of the adapter is matched with the upper end face of the positioning ring.
Preferably, the automatic flip mechanism comprises a linear motor axially arranged along the inner wall of the simulation bin body and a connecting rod, wherein one end of the connecting rod is positioned 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 flip rod is hinged to the other end of the connecting rod and the launching mechanism.
Preferably, the observation 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 bin body and comprises a high-speed camera and a ripple meter.
Preferably, the simulation storehouse body is last to be equipped with the observation window, and the observation window is established to the cylinder, installs toughened glass in the observation window, and the great one end of observation window diameter is connected with the simulation storehouse body, and the level of the less one end of observation window diameter can be dismantled and is connected with places the platform, has placed high-speed photographic appearance and ripple appearance on placing the bench.
Preferably, the observation window is axially provided with a plurality of groups along the simulation bin body, toughened glass is arranged in the observation window, and the outer sides of the observation windows are respectively and correspondingly provided with a placing table.
The invention has the beneficial effects that:
1. the invention relates to an underwater missile launching simulation device which is compact in structure, convenient to use, small in size and light in weight on the premise of meeting the requirements of experimental environmental conditions in the design process aiming at experiments under laboratory conditions; meanwhile, the device has reliable structure, sufficient safety margin for structural strength and sealing effect, can meet the monitoring of parameters such as missile speed, attitude, launching opening flow field and the like in the launching process under various pressure environments and temperature environments, and ensures a large application range of deep water environment change.
2. The invention is provided with an observation and detection mechanism, which can synchronously detect the relevant parameters of missiles in different test environments, and the detection process is carried out aiming at the inner aspect and the outer aspect, (a) the inside: internal parameter detection equipment such as a water pressure sensor, a speed sensor, a laser velocimeter and the like detects flow field parameters, missile motion speed and attitude parameters. (b) outside: the high-speed camera and the ripple wave instrument are used for detecting parameters such as the dynamic attitude of the missile water outlet, the formation and dissipation process of supercavitation, the dynamic process of flow field change and the like, so that the omnibearing parameter detection under the synchronous condition is realized, and the real matching of experimental data is reliably ensured.
3. The invention is provided with the transmitting mechanism, and the transmitting mechanism adopts multiple caliber matching to realize the tests of transmitting devices with different types and different calibers aiming at different test requirements, so that the device has wide application range.
4. The universal large-depth submarine-launched missile launching simulation device is provided with the anti-collision mechanism, so that after the simulated missile launching parameters are detected, the simulated missile can be reliably stopped in the device, 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 an anti-collision mechanism of the present invention;
FIG. 4 is a schematic diagram of a launching mechanism of the present invention;
FIG. 5 is an enlarged view of the invention at the transmitting mechanism A;
FIG. 6 is a schematic view 1 of the present invention in use;
fig. 7 is a schematic view 2 of the usage state of the present invention.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
Embodiment 1:
as shown in fig. 1, in order to perform theoretical research on a deep-penetration missile, sufficient experimental data is required as a support, and in this context, a universal large-depth penetration 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, the length and diameter ratio of the simulated bullet is not more than 20:1, the temperature is-10-40 ℃ and the maximum environmental pressure is not more than 2Mpa.
As shown in fig. 1, a general large-depth submarine-launched missile launching simulation system is designed according to the above experimental conditions, and comprises a fixed platform 7 and a sealing simulation device erected on the fixed platform 7, wherein the fixed platform 7 is a concrete platform in the embodiment, the sealing simulation device is erected on the fixed platform 7 through a bracket component 8, the bracket component 8 in the embodiment is in the prior art, 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 comprises a simulation bin body 3, the upper end of the simulation bin body 3 is connected with a simulation bin sealing cover 1, preferably, the outer side of the simulation bin sealing cover 1 is a convex spherical surface, the inner side of the simulation bin sealing cover 1 is a concave spherical surface, the concave spherical surface plays a role in prolonging a buffer line of a simulation missile 65, a plurality of hanging rings 12 are arrayed on the circumference of the convex spherical surface, a hoisting machine is convenient for hoisting the simulation bin sealing cover 1, a bin filling pressure hole 11 is arranged on the simulation bin sealing cover 1, and the simulation bin sealing device can be used for filling water, can be used for filling pressure needed by experiments in a sealing simulation bin, and can also be used for installing a pressure meter to monitor the pressure in the sealing simulation bin;
as shown in fig. 1-3, the lower end of the simulation bin body 3 is connected with a sealing plate 5, one end, close to the simulation bin sealing cover 1, of the simulation bin body 3 is provided with an anti-collision mechanism 2, the sealing plate 5 is connected with a transmitting mechanism 6, an automatic flip mechanism 9 is arranged between the transmitting mechanism 6 and the inner wall of the simulation bin body 3, and the automatic flip mechanism 9 is used for opening the transmitting mechanism 6 to finish the transmission of a simulation missile 65; the upper end of the preferable launching mechanism 6 penetrates through the sealing plate 5 to enter the simulation bin body 3, a launching mechanism mounting opening 51 for connecting the launching mechanism 6 is arranged on the preferable sealing plate 5, and a plurality of reinforcing ribs 52 are arranged between the outer wall of the launching mechanism 6 and the circumference of the sealing plate 5. The simulation bin body 3, the simulation bin sealing cover 1, the sealing plate 5 and the transmitting mechanism 6 form a sealing simulation bin, and the sealing simulation bin is provided with an observation and detection mechanism.
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, the air pressure in the sealed simulation bin is ensured to be stable, the simulation environment is achieved, the circumference of the outer eave at the upper end of the simulation bin body 3 is provided with a matched eave 31, the circumference of the outer eave of the simulation bin sealing cover 1 is provided with a connecting eave 13, and the connecting eave 13 is connected with the matched eave 31 through screws in a circumferential array; for better realization sealed 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 upper end of the simulation storehouse body 3, installs sealing washer 33 in the holding tank 32, the eaves circumference is equipped with the tight portion 14 that compresses tightly sealing washer 33 with holding tank 32 cooperation in the sealed lid 1 of simulation storehouse, the tight portion 14 of the sealed lid 1 of simulation storehouse is towards sealing washer 33 one side for the tight face of compression, is equipped with the tight groove of compression dorsad 33 one side.
1-3, after the simulated missile 65 is launched during an experiment, the simulated missile 65 passes through a water area arranged in a sealed simulation cabin, flow field parameters are detected and recorded by an observation detection mechanism, the movement speed and the gesture parameters of the simulated missile 65, and parameters such as the dynamic gesture of the water outlet of the simulated missile, the supercavitation formation and dissipation process, the flow field change and the like are detected, and the simulated missile 65 needs to stop in time after being flushed out of the arranged water area, so that the simulated missile 65 is prevented from damaging the sealed simulation cabin; the anti-collision mechanism 2 corresponding to the simulated missile 65 is arranged, the anti-collision mechanism 2 comprises a buffer assembly and an anti-collision pad 21, the buffer assembly comprises an anti-collision disc 22, the periphery of the outer eave of the anti-collision disc 22 and the periphery of the inner wall of the simulated bin body 3 are connected with a plurality of buffer springs 23, the buffer springs 23 in the embodiment are not less than 17.8N/mm according to the design requirement K value, the anti-collision pad 21 is arranged on the inner wall of the simulated bin sealing cover 1, and the edge of the anti-collision pad 21 is fixedly arranged in a compression groove of the simulated bin sealing cover 1.
In order to ensure reliable structure of the buffer assembly, after the emission 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, one side of the anti-collision disc 22, which is close to the simulated bin sealing cover 1, is provided with a convex spherical surface, one side of the anti-collision disc 22, which is away from the simulated bin sealing cover 1, is provided with a concave spherical surface, and a plurality of pull holes which are matched with the buffer springs 23 are formed in the circumferential array of the outer eave of the anti-collision disc 22; the inner wall of the simulation bin body 3 is provided with a plurality of connecting seats for connecting the buffer springs 23, through holes are formed in the connecting seats, screws are installed in the through holes, one end of each buffer spring 23 is installed in each pulling hole, and the other end of each buffer spring is sleeved on each screw and clamped on the connecting seat.
As shown in fig. 4-5, in order to realize the launching of the universal large-depth submarine-launched simulated missile 65 in the test process, a corresponding launching device is provided, which comprises a launching bin 62 and a launching bin 62 cover 61 installed at the upper end of the launching bin 62, preferably, the launching bin 62 is in a cylindrical design, the launching bin 62 cover 61 is rotatably opened relative to the launching bin 62, one end of the launching bin 62, which is close to the launching bin 62 cover 61, is provided with a waterproof membrane for isolating the launching environment and the experimental environment of the simulated missile 65, a launching tube 63 and a positioning locking mechanism 64 for positioning the launching tube 63 are coaxially installed in the launching bin 62, the preferred launching tube 63 is in a cylindrical shape, the lower end of the launching tube 63 is connected with a driving seat 67, the driving seat 67 and the lower end of the launching tube 63 form a driving bin 671, the lower end of the driving seat 67 is communicated with a pressure bin 68 through an air delivery conduit, an electromagnetic valve 681 is installed on the air delivery conduit, the lower end of the pressure bin 68 is connected with an inflation conduit 693, the side of the launching conduit 693, which is connected with an air outlet conduit 695, and the upper inflation conduit 694 is installed on the air outlet conduit 694; when the inflation branch pipe 694 is in a working state, the inflation branch pipe is connected with the same air source with the bin inflation pressure measuring hole 11, and the inflated air is led into the emission bin 62 through the air outlet conduit 695, so that the pressure in the emission bin 62 is kept consistent with the pressure in the sealed simulation bin; the free end of the inflation conduit 693 passes through the bottom of the emission bin 62 and is 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 arranged on the inflation conduit 693 close to the high-pressure air source end, the input and output of the air source are controlled by the air pressure value of the pressure bin 68, in this embodiment, the high-pressure air bottle 691 is a high-pressure air bottle 691 with the pressure of 30Mpa, and the high-pressure air bottle 691 can be inflated at any time.
As shown in fig. 4-5, in order to realize the launching of the simulated missile 65 with different models, the launching tube 63 needs to be convenient to detach and has good locking and positioning relative to the launching bin 62, the positioning and locking mechanism 64 comprises a positioning ring 641 installed at the upper end of the inner wall of the launching bin 62 and a locking part installed at the lower end of the inner wall of the launching bin 62, the circumferential array of the lower end of the outer wall of the launching tube 63 is provided with a plurality of locking eaves 631 installed in cooperation with the locking part, the number of the locking eaves 631 is preferably two in 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 preferably circular, the adapter 642 is used for positioning the upper end of the launching tube 63, the upper end of the launching tube 63 is prevented from inclining in the launching bin 62, the water inlet route of the simulated missile 65 is influenced, and the positioning ring 641 is used for positioning the position of the adapter 642; the locking part is installed with the cooperation of locking eaves 631 for the location supports the transmission section of thick bamboo 63 lower extreme, guarantees that transmission section of thick bamboo 63 is connected reliably with transmission storehouse 62, and the cooperation of locking part and locking eaves 631 simultaneously can realize unblanking and locking two kinds of states, and the transmission section of thick bamboo 63 of unblanking is convenient for dismantle, and the axial motion of transmission section of thick bamboo 63 relative transmission storehouse 62 can be restricted to the locking state, guarantees that transmission section of thick bamboo 63 can realize the transmission of simulation guided missile 65, and the drive storehouse 671 that transmission section of thick bamboo 63 lower extreme and actuating seat 67 of also being convenient for forms is sealed, avoids the atmospheric pressure loss, influences the transmission power of simulation guided missile 65.
As shown in fig. 4-5, in order to better realize the locking and positioning of the transmitting cylinder 63 relative to the transmitting bin 62, the locking part comprises a positioning seat 645 and a locking seat 643 which are axially and alternately arranged along the transmitting bin 62, the positioning seat 645 is arranged close to the lower end of the transmitting bin 62, the inner wall of the positioning seat 645 is connected with the outer wall of the driving seat 67, preferably, seamless welding is adopted, the inner wall of the locking seat 643 is matched with the outer wall of the transmitting cylinder 63, a locking cavity 644 is formed between the positioning seat 645 and the locking seat 643, and the locking cavity 644 is matched with the locking convex eave 631 to install for locking; the locking seat 643 is provided with a circumferential array of unlocking grooves for matching with the locking convex eaves 631. When in an installation state, the hoisting emission cylinder 63 axially enters the emission chamber 62 along the emission chamber 62, the locking convex eave 631 at the lower end of the emission cylinder 63 enters the locking cavity 644 along the unlocking groove, the emission cylinder 63 is rotated to realize dislocation of the locking convex eave 631 and the unlocking groove, at the moment, locking action is completed, and the emission cylinder 63 cannot axially move relative to the emission chamber 62; in the disassembly state, the locking convex eave 631 rotates to the unlocking groove to realize the alignment of the locking convex eave 631 and the unlocking groove, and the emission barrel 63 is lifted out along the axial direction of the emission bin 62.
As shown in fig. 4-5, in order to facilitate the launching of the simulated missile 65 out of the launching tube 63, a driving piston 66 is disposed at the bottom of the launching tube 63, the driving piston 66 contacts 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 accelerate to fly out of the launching tube 63, a piston stopper 632 is mounted at the top of the launching tube 63, so that the driving piston 66 is prevented from flying out of the launching tube 63 along with the simulated missile 65, a certain influence is generated on the test of the simulated missile 65, and multiple recycling of the driving piston 66 is facilitated.
As shown in fig. 4-5, in order to control the simulated missile 65 to enter the simulated cabin body 3 from the launching cabin 62 during launching, a mechanism for controlling the cover 61 of the launching cabin 62 to turn over is required to be arranged, the automatic flip mechanism 9 comprises a linear motor 92 axially arranged along the inner wall of the simulated cabin body 3 and a connecting rod 94 with one end hinged to the inner wall of the simulated cabin body 3 below the linear motor 92, a power rod 93 is hinged between the linear motor 92 and the connecting rod 94, a flip 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, the relevant parameters of the missiles of different test environments are synchronously detected, the observation and 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 simulation bin body 3 and comprises a water outlet detection mechanism speed sensor and a water pressure sensor, and the water detection mechanism is preferably a laser velocimeter 15, and in this embodiment, the laser velocimeter 15 is adopted; the water outlet detection mechanism is arranged at one end, close to the anti-collision mechanism 2, of the inner wall of the simulation bin body 3, and can be used for detecting equipment and flow field parameters, missile motion speed and attitude parameters.
As shown in fig. 2 and 6, the external detection mechanism is installed outside the simulation bin body 3, and comprises a high-speed camera and a corrugating instrument 16, so that parameters such as a missile water outlet dynamic posture, a supercavitation formation and dissipation process, a flow field change and other dynamic processes can be detected; therefore, the inner and outer coordination realizes the omnibearing parameter detection under the synchronous condition, and the real matching of experimental data is reliably ensured.
As shown in fig. 2 and 6, in order to monitor and photograph the missile water outlet dynamic gesture, supercavitation formation and dissipation process, flow field change and other dynamic processes in real time, the setting of the observation window 4 is convenient, the connection of the simulation bin body 3 and the observation window 4 is convenient, the observation window 4 is axially provided with a plurality of groups along the simulation bin body 3, toughened glass is arranged in the observation window 4, the outer sides of the observation window 4 are respectively and correspondingly provided with a placement table, and a high-speed camera and a ripple meter 16 are respectively placed on the placement table.
Embodiment 2:
as shown in fig. 7, in order to facilitate real-time monitoring and photographing of the missile water outlet dynamic gesture, supercavitation formation and dissipation process, flow field change and other dynamic processes, the difference from embodiment 1 is that the placement position of the observation detection mechanism is set on the simulation bin body 3, so that the structure is compact; the simulated bin body 3 is provided with a plurality of observation windows 4, 2 observation windows 4 are preferably designed along the circumferential array of the simulated bin body 3, the observation windows 4 are conical cylindrical surfaces, the cone angle of the observation windows 4 is 108 degrees, all conditions that the simulated missile 65 runs in the simulated bin body 3 can be observed through the observation windows 4, toughened glass is arranged in the observation windows 4, one end of the observation windows 4 with larger diameter is connected with the simulated bin body 3, and the observation windows 4 are preferably connected with the simulated bin body 3 in a welding mode; the smaller diameter end of the observation window 4 is horizontally and detachably connected with a placing table, and a high-speed camera and a ripple meter 16 are placed on the placing table.
In this embodiment, the laser velocimeter 15, the high-speed camera and the ripple meter 16 are all of the prior art, and are not described herein, and the linear motor 92 and the solenoid valve 681 are also of the prior art, and are not described herein.
Taking a simulated 200m water depth emission experiment as an example, the test process is as follows:
1. test preparation procedure
The staff adjusts the parts of the simulation bin body 3 connected with the simulation bin sealing cover 1, and opens the simulation bin sealing cover 1; the anti-collision buffer device is disassembled, the linear motor 92 is driven, the linear motor 92 axially moves along the inner wall of the simulation bin 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 emission bin 62 cover 61 at the upper end of the emission bin 62 is opened, the emission tube 63 to be tested is axially hoisted into the emission bin 62 along the emission bin 62, the locking convex eaves 631 on the emission tube 63 are aligned with the unlocking grooves by adjusting the relative positions of the emission tube 63 and the emission bin 62, the emission tube 63 is continuously hoisted to enable the locking convex eaves 631 at the lower end of the emission tube 63 to enter the locking cavity 644 through the unlocking grooves on the locking seat 643, the emission tube 63 is screwed to realize dislocation of the locking convex eaves 631 and the unlocking grooves, and the emission tube 63 is locked; sequentially hoisting a driving piston 66 and a simulated missile 65 into the launching tube 63 along the axial direction of the launching tube 63, and then adjusting the launching tube 63 to be vertical to the installation adapter 642 of the launching tube 63; at this time, a waterproof membrane and a screwing installation piston stopper 632 are sequentially installed at the opening of the emission bin 62, after the installation is finished, the linear motor 92 is controlled to move, the power rod 93 controls the turning rod 91 to turn down through the connecting rod 94, and the emission bin 62 cover 61 at the upper end of the emission bin 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 filling pressure measuring holes 11 to enable the water depth to reach 2m, injecting gas into the sealed simulation bin through the bin filling pressure measuring holes 11 to increase the pressure to 2Mpa, and simultaneously injecting gas into the emission bin 62 through the gas filling branch pipe 694 from the same gas source to increase the pressure to 2.02Mpa to achieve the balance of the upper pressure and the lower pressure of the cover 61 of the emission bin 62; checking and observing the detection mechanism, ensuring that the mechanism can work normally, opening an air source stop valve 692, enabling air in a high-pressure air cylinder 691 to enter a pressure bin 68 through an inflation conduit 693, closing the air source stop valve 692 when a pressure gauge on the pressure bin 68 reaches a required value, and punching to 7Mpa in the pressure bin 68 in the embodiment; at this point the preparation is completed.
2. Principle of test operation
The test is started on the premise that all the devices are normal before the preparation work is completed,
(1) The linear motor 92 drives the firing chamber 62 with the cover 61 open, at which time the firing chamber 62 is separated from the sealed analog chamber by a waterproof membrane.
(2) Test observation detection mechanism: the laser velocimeter 15, the high-speed camera and the ripple meter 16 are started.
(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 accelerate under the action of the gas pressure, when the simulated missile 65 reaches the opening of the launching tube 63, the driving piston 66 is separated from the simulated missile 65 under the limitation of the piston stopper 632 at the opening of the launching tube 63, the simulated missile 65 breaks through a waterproof membrane and enters the sealed simulated bin, the process that the simulated missile 65 flies out of the launching bin 62 is recorded by the high-speed photography and ripple meter, and the process of forming air bubbles in the sealed simulated bin is detected and recorded, and meanwhile, the running speed change and the gesture change of the simulated missile 65 are detected and recorded. When the simulated missile 65 flies out of the water, the high-speed photography and ripple instrument records the supercavitation disappearance process, and the laser velocimeter 15 detects and records the water outlet speed of the simulated missile 65.
(4) After the simulated missile 65 discharges water, the warhead of the simulated missile 65 starts to contact the anti-collision disc 22 and drives the anti-collision disc 22 to move together, the buffer spring 23 which is circumferentially connected with the inner wall of the simulated bin body 3 starts to pull the anti-collision disc 22, the moving speed of the anti-collision disc 22 is slowed down, the simulated missile 65 is indirectly braked, the rigidity K value of the buffer spring 23 is set according to the initial moving speed of the simulated missile 65 and the quality parameter, in the embodiment, the K value is not smaller than 17.8N/mm, the anti-collision disc 22 is prevented from being provided with the simulated bin sealing cover 1, and if the anti-collision disc 22 collides with the simulated bin sealing cover 1, the anti-collision pad 21 arranged on the simulated bin sealing cover 1 plays a certain buffering role, so that a damage device is avoided.
(5) After the test is finished, the pressure is released, water is discharged, then the simulated bin sealing cover 1 is opened, the anti-collision buffer device is detached, the simulated missile 65 is recovered, and the experiment is completed.
The present embodiment is not limited in any way by the shape, material, structure, etc. of the present invention, and any simple modification, equivalent variation and modification made to the above embodiments according to the technical substance of the present invention are all included in the scope of protection of the technical solution of the present invention.
In the description of the present invention, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate description of the present invention and simplify the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the protection of the present invention.
If the terms "first," "second," etc. are used herein to define a part, those skilled in the art will recognize that: the use of "first" and "second" is for convenience only as well as for simplicity of description, and nothing more than a particular meaning of the terms is intended to be used unless otherwise stated.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the 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: the technical solutions described in the foregoing embodiments may be modified or some technical features may be replaced with others, which may not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (7)
1. The universal 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 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 filling pressure measuring 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 at one end, close to the simulation bin sealing cover, of the simulation bin 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 bin body, the simulation bin sealing cover, the sealing plate and the transmitting mechanism form a sealed simulation bin, and an observation and detection mechanism is arranged on the sealed simulation bin;
the launching mechanism comprises a launching bin and a launching bin cover arranged at the upper end of the launching bin, one end, close to the launching bin cover, of the launching bin is provided with a waterproof membrane, a launching tube and a positioning locking mechanism for positioning the launching tube are coaxially arranged in the launching bin, the lower end of the launching tube is connected with a driving seat, 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 transmission pipe, a solenoid valve is arranged on the gas transmission pipe, the lower end of the pressure bin is connected with a gas charging pipe, the side of the joint of the gas charging pipe and the pressure bin is provided with a gas outlet pipe communicated with the launching bin, the gas outlet pipe is provided with a control valve, the joint, close to the pressure bin, of the gas charging pipe is provided with a gas charging branch pipe, and the gas charging branch pipe is provided with a control valve; the free end of the inflatable catheter passes through the bottom of the launching bin and is connected with an air source assembly;
the positioning locking mechanism comprises a positioning ring arranged at the upper end of the inner wall of the transmitting bin and a locking part arranged at the lower end of the inner wall of the transmitting bin, a locking convex eave which is matched with the locking part is arranged at the circumferential array of the lower end of the outer wall of the transmitting cylinder, an adapter is arranged between the upper end of the outer wall of the transmitting cylinder and the upper end of the inner wall of the transmitting bin, and the lower end face of the adapter is matched with the upper end face of the positioning ring;
the automatic flip mechanism comprises a linear motor axially arranged along the inner wall of the simulation bin body and a connecting rod, one end of the connecting rod is hinged to the inner wall of the simulation bin body, the middle of the linear motor and the connecting rod is hinged to a power rod, and the other end of the connecting rod is hinged to the launching mechanism.
2. The universal large-depth submarine-launched missile launching simulation system according to claim 1, wherein the simulation bin body is of a cylindrical structure, the circumference of the outer eave at the upper end of the simulation bin body is provided with a matched eave, the circumference of the outer eave of the sealing cover of the simulation bin is provided with a connecting eave, and the connecting eave is connected with the matched eave through bolts of a circumferential array; the circumference 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 circumference of the inner eave of the sealing cover of the simulation bin body is provided with a pressing part which is matched with the containing groove to press the sealing ring.
3. The universal 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, an outer eave of the anti-collision disc is circumferentially connected with 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 the simulation bin sealing cover.
4. The universal large-depth submarine-launched missile launching simulation system according to claim 1, wherein the upper end of the launching mechanism penetrates through the sealing plate to enter the simulation bin body, and a plurality of reinforcing ribs are arranged between the outer wall of the launching mechanism and the sealing plate in a circumferential manner.
5. A universal large depth submarine-launched missile launching simulation system according to claim 1, wherein the observation and detection mechanism includes 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 bin body and comprises a high-speed camera and a ripple meter.
6. The universal large-depth submarine-launched missile launching simulation system according to claim 5, wherein the simulation bin body is provided with an observation window, the observation window is arranged into a conical cylinder, toughened glass is arranged in the observation window, one end of the observation window with a larger diameter is connected with the simulation bin body, the other end of the observation window with a smaller diameter is horizontally and detachably connected with a placing table, and a high-speed camera and a ripple instrument are placed on the placing table.
7. The universal large-depth submarine-launched missile launching simulation system according to claim 6, wherein a plurality of groups of observation windows are arranged along the axial direction of the simulation bin body, toughened glass is arranged in the observation windows, and placing tables are correspondingly arranged on the outer sides of the observation windows respectively.
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| CN201910939919.XA CN110701965B (en) | 2019-09-30 | 2019-09-30 | Universal large-depth submarine-launched missile launching simulation system |
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| CN201910939919.XA CN110701965B (en) | 2019-09-30 | 2019-09-30 | Universal large-depth submarine-launched missile launching simulation system |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102155885A (en) * | 2010-12-31 | 2011-08-17 | 北京威标至远科技发展有限公司 | Cruise target projectile |
| DE102012017891A1 (en) * | 2012-09-11 | 2014-05-15 | Mbda Deutschland Gmbh | Missile testing device for testing correct communication between missile and carrier aircraft, has communication interface connected with carrier aircraft for exchanging milbus signals and receiver for navigation signals |
| DE102012022894A1 (en) * | 2012-11-23 | 2014-05-28 | Gabriele Lisa Trinkel | System for identification, verification and/or authentication of projectile e.g. railgun projectile, has sensor, communication unit, processing unit and power supply or power generation unit which are arranged in housing of projectile |
| CN104048562A (en) * | 2013-09-30 | 2014-09-17 | 中国人民解放军国防科学技术大学 | Whole-missile vertical vibration test protection device |
| CN109974541A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | Multi nozzle rocket dynamic jet test system |
| CN211012685U (en) * | 2019-09-30 | 2020-07-14 | 湖南国防工业职业技术学院 | Universal large-depth submarine-launched missile launching simulation system |
-
2019
- 2019-09-30 CN CN201910939919.XA patent/CN110701965B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102155885A (en) * | 2010-12-31 | 2011-08-17 | 北京威标至远科技发展有限公司 | Cruise target projectile |
| DE102012017891A1 (en) * | 2012-09-11 | 2014-05-15 | Mbda Deutschland Gmbh | Missile testing device for testing correct communication between missile and carrier aircraft, has communication interface connected with carrier aircraft for exchanging milbus signals and receiver for navigation signals |
| DE102012022894A1 (en) * | 2012-11-23 | 2014-05-28 | Gabriele Lisa Trinkel | System for identification, verification and/or authentication of projectile e.g. railgun projectile, has sensor, communication unit, processing unit and power supply or power generation unit which are arranged in housing of projectile |
| CN104048562A (en) * | 2013-09-30 | 2014-09-17 | 中国人民解放军国防科学技术大学 | Whole-missile vertical vibration test protection device |
| CN109974541A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | Multi nozzle rocket dynamic jet test system |
| CN211012685U (en) * | 2019-09-30 | 2020-07-14 | 湖南国防工业职业技术学院 | Universal large-depth submarine-launched missile launching simulation system |
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