CN114013557B - Cavity body air-compression type water-entering combined load-reducing device - Google Patents
Cavity body air-compression type water-entering combined load-reducing device Download PDFInfo
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- CN114013557B CN114013557B CN202111275482.8A CN202111275482A CN114013557B CN 114013557 B CN114013557 B CN 114013557B CN 202111275482 A CN202111275482 A CN 202111275482A CN 114013557 B CN114013557 B CN 114013557B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
- B63B1/32—Other means for varying the inherent hydrodynamic characteristics of hulls
- B63B1/34—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction
- B63B1/38—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction using air bubbles or air layers gas filled volumes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63C—LAUNCHING, HAULING-OUT, OR DRY-DOCKING OF VESSELS; LIFE-SAVING IN WATER; EQUIPMENT FOR DWELLING OR WORKING UNDER WATER; MEANS FOR SALVAGING OR SEARCHING FOR UNDERWATER OBJECTS
- B63C11/00—Equipment for dwelling or working underwater; Means for searching for underwater objects
- B63C11/52—Tools specially adapted for working underwater, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
- B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B1/00—Hydrodynamic or hydrostatic features of hulls or of hydrofoils
- B63B1/32—Other means for varying the inherent hydrodynamic characteristics of hulls
- B63B1/34—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction
- B63B1/38—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction using air bubbles or air layers gas filled volumes
- B63B2001/382—Other means for varying the inherent hydrodynamic characteristics of hulls by reducing surface friction using air bubbles or air layers gas filled volumes by making use of supercavitation, e.g. for underwater vehicles
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T70/00—Maritime or waterways transport
- Y02T70/10—Measures concerning design or construction of watercraft hulls
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- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Ocean & Marine Engineering (AREA)
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- General Engineering & Computer Science (AREA)
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Abstract
The invention provides a cavity body air-compression type water-entering combined load-reducing device which comprises a separated fairing, a navigation body, a hard polymer foam layer, a buffer device and a cavitator, wherein the buffer device is used for buffering acting force between the navigation body and water when the navigation body enters the water, the front end of the separated fairing is conical, and the cavity body air-compression type water-entering combined load-reducing device also comprises a side fairing; the radome fairing lateral wall includes the radome fairing main part, and the front and back end of radome fairing main part is equipped with high-pressure air chamber and time high-pressure air chamber respectively, through step-down jogged joint between high-pressure air chamber and time high-pressure air chamber, and the plugging device who opens or seal the step-down hole is installed to the front end of radome fairing main part, and buffer is located the high-pressure air intracavity. The invention adds air cushion type buffering on the basis of the traditional buffering device, and can further protect the head of the navigation body from being damaged.
Description
Technical Field
The invention relates to the technical field of water entry load shedding of a navigation body, in particular to a cavity air-compression type water entry combined load shedding device.
Background
Underwater vehicles require a more flexible launching mode to effectively avoid the tracking of remote detection equipment, and more countries adopt an aerial launching mode to deliver the vehicles. When the underwater vehicle falls from high altitude at a high initial speed, the main structure is subjected to huge instantaneous overload at the moment of water contact. Research has shown that such overload can cause unpredictable damage to the internal structure of the vehicle, and in severe cases can cause the whole vehicle to lose due functions and thus lose fighting power. In addition, the acceleration of the overload also increases significantly with the increase in the water contact speed. Therefore, it is necessary to adopt an appropriate structure to reduce the impact acceleration so as to protect the structure and reduce the risk of structural damage or functional failure of the navigation body. Most of the existing sailing bodies enter water and carry load reduction are carried out by adopting structures such as hydraulic cylinders, but the load reduction capacity is limited.
Disclosure of Invention
According to the technical problem, a hollow cavity pneumatic water inlet combined load reducing device is provided.
The technical means adopted by the invention are as follows:
a cavity body air-compression type water-entering combined load-reducing device comprises a separated fairing, a navigation body, a hard polymer foam layer, a buffering device and a cavitator, wherein the buffering device is used for buffering acting force between the navigation body and water when the navigation body enters the water, the front end of the separated fairing is conical, and the cavity body air-compression type water-entering combined load-reducing device also comprises a side fairing;
the side fairing is split, a plurality of split bodies are hermetically spliced into a whole around the axis of the side fairing, and the split bodies are separably connected; the side fairing comprises a fairing side wall, the head end of the navigation body is detachably connected with the rear end of the fairing side wall, and the rear end of the separated fairing is detachably connected with the front end of the side fairing; the cavitator and the buffer device are positioned in the side fairing; the hard polymer foam layer is filled in the split type fairing, and a cavity is formed between the front end of the hard polymer foam layer and the front end of the split type fairing; the front end of the cavitator abuts against the rear end of the rigid polymer foam layer, the rear end of the cavitator is fixedly connected with the output end of the buffer device, the mounting end of the buffer device is connected with the head of the navigation body through a connecting structure, and the outer edge of the cavitator is in sealed sliding connection with the side wall of the fairing;
the side fairing also comprises a fairing main body arranged in the side wall of the fairing, a high-pressure air cavity is formed by the cavitator and the part of the fairing main body, which is positioned between the side walls of the fairing, the high-pressure air cavity is internally provided with high-pressure gas, a secondary high-pressure air cavity is formed by the fairing main body and the part of the head of the navigation body, which is positioned between the side walls of the fairing, the fairing main body is internally provided with a pressure reduction hole, the two ends of the pressure reduction hole are respectively communicated with the high-pressure air cavity and the secondary high-pressure air cavity, and the pressure reduction hole is used for reducing the pressure of the high-pressure gas in the high-pressure air cavity and transmitting the high-pressure gas to the secondary high-pressure air cavity; the front end of the fairing main body is provided with a plugging device for opening or closing the depressurization hole; the buffer device is positioned in the high-pressure air cavity.
The plugging device comprises a central rod, the front end of the central rod penetrates through the fairing main body and is in sealed rotary connection with the fairing main body and then is fixedly connected with the mounting end of the buffer device, the central rod is of a connecting structure, and the rear end of the central rod is axially limited and mounted in the head of the navigation body and is in rotary connection with the head of the navigation body; the plurality of pressure reducing holes are divided into a plurality of groups, the plurality of groups of pressure reducing holes are uniformly distributed around the axis of the fairing main body, and the plurality of pressure reducing holes in each group of pressure reducing holes are uniformly distributed along the radial direction of the fairing main body;
the side wall of the central rod is provided with a plurality of fan blades with the same number as the pressure reduction holes, the fan blades are used for plugging or opening the pressure reduction holes, and the part of the central rod positioned in the head of the navigation body is connected with a rotation driving device for driving the central rod to rotate.
Buffer includes the outer sleeve, is equipped with the inner skleeve in the outer sleeve, and the part between outer sleeve and the inner skleeve forms the oil storage chamber, is equipped with the piston rod in the inner skleeve, and the outer sleeve is worn out to the front end of piston rod and inner skleeve and cavitator fixed connection, and the rear end of piston rod has the piston, and the part between piston and the inner skleeve front end is equipped with the spring that draws of cover on the piston rod, the rear end of outer sleeve and well core rod's front end fixed connection, the piston with part between the inner skleeve rear end form with the hydraulic pressure oil cavity body of oil storage chamber intercommunication.
The front end of the cavitator is provided with a back blowing system which blows air forwards.
The back-blowing system comprises a first vent pipe, the front end of the first vent pipe sequentially penetrates through the central rod, the center of the rear end of the outer sleeve and the center of the rear end of the inner sleeve, penetrates into the piston rod and is hermetically and slidably connected with the inner wall of the piston rod, the first vent pipe is rotatably connected with the central rod, a buffer air cavity is arranged inside the piston rod close to the front end of the piston rod, the rear end of the buffer air cavity is communicated with the front end of the first vent pipe, a pressure spring with the axis coincident with the axis of the piston rod is arranged in the buffer air cavity, the end surface of the first vent pipe is abutted against the pressure spring, a through hole communicated with the buffer air cavity is arranged at the front end of the piston rod, and the front end of the through hole is communicated with an air jet port arranged on the cavitator; the rear end of the first vent pipe is communicated with an air storage tank arranged in the navigation body; the air jet opening is provided with a reverse air jet valve.
And a second vent pipe communicated with the through hole is arranged on the side wall of the front part of the piston rod and communicated with the high-pressure air cavity, and a second vent valve is arranged in the second vent pipe.
The pressure reducing hole is a Tesla valve hole.
The secondary high-pressure air cavity is provided with a one-way pressure relief valve.
The rear end of the side fairing is detachably connected with the navigation body through an electromagnet device arranged in the navigation body.
Compared with the prior art, the invention has the following advantages:
1. the invention adds air cushion type buffering (realized by the pressure reducing hole, the high-pressure air cavity, the secondary high-pressure air cavity and the plugging device) on the basis of the traditional buffering device, and can further protect the head of the navigation body from being damaged.
2. The invention is also provided with a back blowing system, can buffer after entering water and can better form supercavity at the same time, thus being beneficial to the formation of supercavity of the cavitator.
3. The pressure reducing hole adopts a Tesla valve hole structure, so that the problem that gas is decelerated when entering a secondary high-pressure air cavity from a high-pressure air cavity can be solved, pressure reduction is realized, and a navigation body is prevented from being damaged by the gas. The Tesla valve hole is a chain structure which is repeated continuously, the more times of structure repetition, the better the pressure reduction effect, that is to say, the smaller the size of the repeated single structure, the better the pressure reduction effect. The pressure reduction can be realized on the basis of not consuming energy by utilizing the directional function of the Tesla valve hole to gas deceleration.
Based on the reasons, the invention can be widely popularized in the fields of sailing bodies entering water and the like.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a front view of a hollow cavity pneumatic water inlet combined load-reducing device according to an embodiment of the present invention.
Fig. 2 isbase:Sub>A sectional view taken along linebase:Sub>A-base:Sub>A in fig. 1.
Fig. 3 is an enlarged front view of fig. 1.
Fig. 4 is a schematic structural diagram of a buffering device and a plugging device in an embodiment of the present invention.
Fig. 5 is a three-dimensional view of a block-out device according to an embodiment of the invention.
Fig. 6 is a schematic view of the plugging device not plugging the pressure-reducing hole according to the embodiment of the present invention.
Fig. 7 is a schematic view of a plugging device plugging a pressure relief vent in an embodiment of the present invention.
FIG. 8 is a schematic diagram of a pressure-reducing pore structure in an embodiment of the present invention.
Fig. 9 is a schematic view of the navigation body navigating near the water surface in the embodiment of the invention.
Fig. 10 is a schematic diagram of reverse air injection after the sailing body impacts the water surface in the embodiment of the invention.
FIG. 11 is a schematic view of the pressure linkage load shedding of the buffer device according to the embodiment of the present invention.
FIG. 12 is a schematic view of the side fairing of the present invention after separation.
In the figure: 1. a split cowl; 2. a navigation body; 3. a rigid polymeric foam layer; 4. a buffer device; 401. an outer sleeve; 402. an inner sleeve; 403. a piston rod; 404. a piston; 405. pulling a spring; 5. a cavitator; 6. a side fairing; 601. a cowl side wall; 602. a cowl main body; 603. a high pressure air chamber; 604. a secondary high pressure air chamber; 605. a pressure reduction well; 7. a plugging device; 701. a center pole; 702. a fan blade; 703. a gear; 8. a back-blowing system; 801. a first breather pipe; 802. a buffer air cavity; 803. pressing a spring; 804. a through hole; 805. an air jet port; 806. a gas storage tank; 807. a reverse jet valve; 808. a second vent pipe; 809. a second vent valve.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the invention. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. Any specific values in all examples shown and discussed herein are to be construed as exemplary only and not as limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are used for convenience of description and simplicity of description only, and in the absence of any contrary indication, these directional terms are not intended to indicate and imply that the device or element so referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore should not be considered as limiting the scope of the present invention: the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
For ease of description, spatially relative terms such as "over 8230 \ 8230;,"' over 8230;, \8230; upper surface "," above ", etc. may be used herein to describe the spatial relationship of one device or feature to another device or feature as shown in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary terms "at 8230; \8230; 'above" may include both orientations "at 8230; \8230;' above 8230; 'at 8230;' below 8230;" above ". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and unless otherwise stated, the terms have no special meaning, and therefore, the scope of the present invention should not be construed as being limited.
As shown in fig. 1 to 12, a cavity pneumatic water entry combined load shedding device comprises a separated fairing 1, a navigation body 2, a rigid polymer foam layer 3, a buffer device 4 and a cavitator 5, wherein the buffer device 4 is used for buffering the acting force between the navigation body 2 and water when the navigation body 2 enters water, the front end of the separated fairing 1 is conical, and the cavity pneumatic water entry combined load shedding device further comprises a side fairing 6;
the side fairing 6 is split, and a plurality of split bodies are hermetically spliced into a whole around the axis of the side fairing 6; the side fairing 6 comprises a fairing side wall 601, the head end of the navigation body 2 is detachably connected with the rear end of the fairing side wall 6, and the rear end of the separated fairing 6 is detachably connected with the front end of the side fairing 6; the cavitator 5 and the buffer device 4 are positioned in the side fairing 6; the hard polymer foam layer 3 is filled in the split type fairing 1, and a cavity is formed between the front end of the hard polymer foam layer 3 and the front end of the split type fairing 1; the front end of the cavitator 5 is abutted against the rear end of the rigid polymer foam layer 3, the rear end of the cavitator 5 is fixedly connected with the output end of the buffer device 4, the mounting end of the buffer device 4 is connected with the head of the navigation body 2 through a connecting structure, and the outer edge of the cavitator 5 is in sealed sliding connection with the side wall of the fairing;
the side fairing 6 further comprises a fairing main body 602 arranged in the fairing side wall 601, a high-pressure air cavity 603 is formed by the part, located between the fairing side wall 601, of the cavitator 5 and the fairing main body 602, high-pressure gas is arranged in the high-pressure air cavity 603, a secondary high-pressure air cavity 604 is formed by the fairing main body 602 and the part, located between the fairing side wall 601, of the head of the navigation body 2, a plurality of depressurization holes 605 are formed in the fairing main body 602, two ends of each depressurization hole are respectively communicated with the high-pressure air cavity 603 and the secondary high-pressure air cavity 604, and the depressurization holes 605 are used for depressurizing and transmitting the high-pressure gas in the high-pressure air cavity 603 to the secondary high-pressure air cavity 604; the front end of the fairing main body 602 is provided with a plugging device 7 for opening or closing the depressurization hole 605; the damping device 4 is located in the high pressure air chamber 603.
As shown in fig. 4 and 5, the plugging device 7 includes a central rod 701, a front end of the central rod 701 penetrates through the fairing body 602, and is in sealed rotary connection with the fairing body 602, and then is fixedly connected with a mounting end of the buffer device 4, the central rod is in a 701 connection structure, and a rear end of the central rod 701 is axially and limitedly mounted in the head of the navigation body 2 and is in rotary connection with the head of the navigation body 2; the plurality of depressurization holes 605 are divided into a plurality of groups, and the plurality of depressurization holes 605 are uniformly distributed around the axis of the fairing body 602, and the plurality of depressurization holes 605 in each group of depressurization holes 605 are uniformly distributed in the radial direction of the fairing body 602;
the side wall of the central rod 701 is provided with a plurality of fan blades 702 with the same number as the group number of the pressure reducing holes 605, the fan blades 702 are used for plugging or opening the pressure reducing holes 605, the part of the central rod 701, which is positioned in the head of the navigation body 2, is connected with a rotation driving device for driving the central rod 701 to rotate, the rotation driving device comprises a driving motor arranged in the head of the navigation body and a gear 702 fixed at the rear end of the central rod, the driving motor is provided with a driving gear meshed with the gear 702, the rotation of the driving gear and the gear 702 is driven through the rotation of the driving motor, the rotation of the central rod 701 is realized, and then the fan blades 702 shield the pressure reducing holes 605 or do not shield the pressure reducing holes 605. Fan blade 702 does not shield the step-down aperture 605 as shown in fig. 6 and shields the step-down aperture 605 as shown in fig. 7.
Buffer 4 is as shown in fig. 4, including outer sleeve 401, be equipped with inner sleeve 402 in the outer sleeve 401, the part between outer sleeve 401 and the inner sleeve 402 forms the oil storage chamber, be equipped with piston rod 403 in the inner sleeve 402, outer sleeve 401 and inner sleeve 402 and cavitator 5 fixed connection are worn out to the front end of piston rod 403, the rear end of piston rod 403 has piston 404, the part between piston 404 and the inner sleeve 402 front end is equipped with the spring 405 that draws of cover on piston rod 403, the rear end of outer sleeve 401 and the front end of well core rod 701 adopt the screw-thread formula cooperation to carry out fixed connection, piston 404 with part between the inner sleeve 402 rear end form with the hydraulic pressure oil cavity body of oil storage chamber intercommunication.
The front end of the cavitator 5 has a blowback system 8 that blows air forward.
The back-blowing system 8 comprises a first vent pipe 801, the front end of the first vent pipe 801 sequentially penetrates through a center rod 701, the center of the rear end of an outer sleeve 401 and the center of the rear end of an inner sleeve 402, penetrates into a piston rod 403 and is hermetically and slidably connected with the inner wall of the piston rod 403, the first vent pipe 801 is rotatably connected with the center rod 701, a buffer air cavity 802 is arranged inside the piston rod 403 close to the front end of the piston rod 403, the rear end of the buffer air cavity 802 is communicated with the front end of the first vent pipe 801, a compression spring 803 with the axis coincident with the axis of the piston rod 403 is arranged in the buffer air cavity, the end surface of the first vent pipe 801 is abutted against the compression spring 803, a through hole 804 communicated with the buffer air cavity 802 is arranged at the front end of the piston rod 403, and the front end of the through hole 804 is communicated with an air jet 805 arranged on the cavitator 5; the rear end of the first breather pipe 801 communicates with an air tank 806 provided in the aircraft body 2; a reverse air injection valve 807 is provided at the air injection port 805.
A second vent pipe 808 communicated with the through hole 804 is arranged on the side wall of the front part of the piston rod 403, the second vent pipe 808 is communicated with the high-pressure air chamber 603, and a second vent valve 809 is arranged in the second vent pipe 808.
The secondary high-pressure air chamber 604 is provided with a one-way constant-pressure relief valve, and the one-way constant-pressure relief valve is opened to exhaust air after the preset pressure is exceeded.
The rear end of the side fairing 601 is detachably connected to the navigation body 2 via an electromagnet arrangement installed in the navigation body 2.
The reverse injection valve 807 and the second vent valve 809 are solenoid valves. The side fairing 5 is made of high-strength aluminum alloy material. The split cowl is made of a brittle ceramic material.
The working principle is as follows: as shown in fig. 9, when the vehicle 2 is approaching the water surface while sailing, the second breather valve is opened, and the high-pressure air stored in the air tank 806 is introduced into the high-pressure air chamber 603 through the first breather pipe 801 and the second breather pipe 808. At this time, the piston rod 403 is in an extended state by the pull spring 405 and the hydraulic oil, the fan blade 702 is in a state of blocking the pressure reducing hole 605, and the high-pressure gas cannot enter the sub-high-pressure air chamber 604 from the high-pressure air chamber 603.
When the vehicle 2 is in high speed impact with the water surface in front, as shown in fig. 10, the separate cowling 1 is first broken and the rigid polymer foam layer 3 is compressed and broken apart. Meanwhile, the electromagnetic valve is controlled to be triggered through the pressure sensor on the front end face of the cavitator 6, the reverse air injection valve 807 is used, high-pressure air in the air storage tank 806 is injected out of the air injection port 805, and reversely injected air impacts the water surface to form a reaction force, so that the speed of the navigation body 2 is reduced, and larger cavitation bubbles are facilitated to be formed.
After the reverse air injection is finished, the water surface is in full contact with the surface of the cavitator 5, and the cavitator 5 continues to perform cavitation operation, so that the navigation body is in an air-wrapped state, and the navigation resistance of the navigation body is greatly reduced. As shown in fig. 11, at the moment when the cavitator 5 touches water, the pressure load received by the buffer device 4 is buffered in the process, and when the cavitator 5 moves backwards, the high-pressure air in the high-pressure air chamber 603 is compressed, and at the same time, the driving motor inside the navigation body 2 drives the gear 703 to rotate by a certain angle, so that the fan blade 702 rotates to expose the pressure reduction hole 605, the compressed air enters the sub-high-pressure air chamber 604 through the pressure reduction hole 605, because the pressure reduction hole 605 can automatically decelerate the flowing air, the air entering the sub-high-pressure air chamber 604 is sub-high-pressure air, which will not damage the head of the navigation body 2, if the pressure in the sub-high-pressure air chamber 604 further rises, and reaches the warning pressure, the one-way constant-pressure relief valve is automatically opened to perform the chamber, and the pressure relief structure is not damaged by too high pressure.
Finally, the end part of the side fairing 6 is in adsorption connection with the de-energized electromagnet at the head part of the navigation body 2, and the side fairing 6 is of a separable structure, so that the electromagnet can be powered off, and at the moment, the side fairing 6 can be automatically separated from the navigation body 2, and the final state is shown in fig. 12. The cavitation device 5 and the plugging device 7 are not separable from the navigation body 2 as a whole. Because of the function of expanding the radial size of the cavitation bubbles by reverse air injection, the cavitation bubbles opened by the navigation body 2 have larger size than the cavitation bubbles of the pure cavitator 5, which is beneficial to maintaining the navigation state of the navigation body in water with smaller resistance.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (8)
1. A cavity compressed air type water inlet combined load reduction device comprises a separated fairing, a navigation body, a buffering device and a cavitator, wherein the buffering device is used for buffering acting force between the navigation body and water when the navigation body enters the water;
the side fairing is split, a plurality of split bodies are hermetically spliced into a whole around the axis of the side fairing, and the split bodies are separably connected; the side fairing comprises a fairing side wall, the head end of the navigation body is detachably connected with the rear end of the fairing side wall, and the rear end of the separated fairing is detachably connected with the front end of the side fairing; the cavitator and the buffer device are positioned in the side fairing; the rear end of the cavitator is fixedly connected with the output end of the buffer device, the mounting end of the buffer device is connected with the head of the navigation body through a connecting structure, and the outer edge of the cavitator is in sealed sliding connection with the side wall of the fairing;
the side fairing further comprises a fairing main body arranged in the side wall of the fairing, a high-pressure air cavity is formed by the cavitator and the part of the fairing main body, which is positioned between the side walls of the fairing, and high-pressure gas is arranged in the high-pressure air cavity; the front end of the fairing main body is provided with a plugging device for opening or closing the depressurization hole; the buffer device is positioned in the high-pressure air cavity.
2. A hollow cavity pneumatic water-entering combined load-reducing device as claimed in claim 1, wherein the blocking device comprises a central rod, the front end of the central rod penetrates through the fairing body, is connected with the fairing body in a sealing and rotating manner, and is then fixedly connected with the mounting end of the buffer device, the central rod is the connecting structure, and the rear end of the central rod is axially limited and mounted in the head of the navigation body and is connected with the head of the navigation body in a rotating manner; the plurality of pressure reducing holes are divided into a plurality of groups, the plurality of groups of pressure reducing holes are uniformly distributed around the axis of the fairing main body, and the plurality of pressure reducing holes in each group of pressure reducing holes are uniformly distributed along the radial direction of the fairing main body;
the side wall of the central rod is provided with a plurality of fan blades with the same number as the pressure reduction holes, the fan blades are used for plugging or opening the pressure reduction holes, and the part of the central rod, which is positioned in the head of the navigation body, is connected with a rotation driving device for driving the central rod to rotate.
3. A cavity body pneumatics formula combination of entrying falls and carries device according to claim 2, characterized in that, buffer includes the outer sleeve, be equipped with the inner skleeve in the outer sleeve, the outer sleeve with part between the inner skleeve forms the oil storage chamber, be equipped with the piston rod in the inner skleeve, the front end of piston rod is worn out the outer sleeve with the inner skleeve with cavitator fixed connection, the rear end of piston rod has the piston, the piston with part between the inner skleeve front end is equipped with the cover and is in the spring that draws on the piston rod, the rear end of outer sleeve with well core rod's front end fixed connection, the piston with part between the inner skleeve rear end form with the hydraulic oil cavity body of oil storage chamber intercommunication.
4. A cavity pneumatic water inlet combined load-reducing device as claimed in claim 3, wherein the front end of the cavitator is provided with a back-blowing system for blowing air forwards;
the back-blowing system comprises a first vent pipe, the front end of the first vent pipe sequentially penetrates through the center rod, the center of the rear end of the outer sleeve and the center of the rear end of the inner sleeve, penetrates into the piston rod and is hermetically and slidably connected with the inner wall of the piston rod, the first vent pipe is rotatably connected with the center rod, a buffer air cavity is formed in the piston rod close to the front end of the piston rod, the rear end of the buffer air cavity is communicated with the front end of the first vent pipe, a compression spring with the axis coincident with the axis of the piston rod is arranged in the buffer air cavity, the end surface of the first vent pipe abuts against the compression spring, a through hole communicated with the buffer air cavity is formed in the front end of the piston rod, and the front end of the through hole is communicated with an air jet port formed in the cavitator; the rear end of the first breather pipe is communicated with an air storage tank arranged in the navigation body; and a reverse air injection valve is arranged at the air injection port.
5. A hollow body pneumatic water inlet combination load-reducing device as claimed in claim 4, wherein a second vent pipe communicated with the through hole is arranged on the side wall of the front part of the piston rod, the second vent pipe is communicated with the high-pressure air chamber, and a second vent valve is arranged in the second vent pipe.
6. A hollow pneumatic water inlet combination load reducing device as claimed in claim 1, wherein the pressure reducing hole is a tesla valve hole.
7. A hollow-body pneumatic-type water-entering combined load-reducing device as claimed in claim 1, wherein the secondary high-pressure air chamber is provided with a one-way pressure-relief valve.
8. A cavity pneumatic entry combination offloading device as recited in claim 1, wherein the rear ends of the side fairings are detachably connected to the navigation body by means of electromagnet devices mounted in the navigation body.
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| CN114701599B (en) * | 2022-04-19 | 2023-02-28 | 吉林大学 | Buffer device for high-speed water entry of navigation body |
| CN115071880B (en) * | 2022-06-12 | 2023-11-17 | 西北工业大学 | Built-in energy-absorbing type combined load reduction structure and method for high-speed water entry of aircraft |
| CN115854800A (en) * | 2022-12-14 | 2023-03-28 | 哈尔滨工程大学 | High-speed water-entering projectile body structure with elastic buffering structure and transient impact force measuring system |
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