CN113879450B - High-speed water-entering composite buffer structure with wing type multistage linkage cavitation device - Google Patents
High-speed water-entering composite buffer structure with wing type multistage linkage cavitation device Download PDFInfo
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- CN113879450B CN113879450B CN202111272577.4A CN202111272577A CN113879450B CN 113879450 B CN113879450 B CN 113879450B CN 202111272577 A CN202111272577 A CN 202111272577A CN 113879450 B CN113879450 B CN 113879450B
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- 239000002131 composite material Substances 0.000 title claims abstract description 21
- 238000009423 ventilation Methods 0.000 claims description 37
- 239000012530 fluid Substances 0.000 claims description 17
- 230000006835 compression Effects 0.000 claims description 16
- 238000007906 compression Methods 0.000 claims description 16
- 239000010720 hydraulic oil Substances 0.000 claims description 14
- 239000003921 oil Substances 0.000 claims description 12
- 238000002347 injection Methods 0.000 claims description 4
- 239000007924 injection Substances 0.000 claims description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 16
- 230000003139 buffering effect Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 7
- 230000009467 reduction Effects 0.000 description 6
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- 238000005474 detonation Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004880 explosion Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 238000001179 sorption measurement Methods 0.000 description 2
- 238000013022 venting Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
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Classifications
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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
-
- 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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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Ocean & Marine Engineering (AREA)
- Toys (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a high-speed water-entering composite buffer structure of a wing-type multistage linkage cavitation device, which comprises a cavitation device arranged at the head end of a navigation body, wherein the cavitation device comprises a cavitation device main body and a plurality of cavitation device disc telescopic pieces which are in sliding connection with the cavitation device main body, the center of the cavitation device main body is connected with the center of the head of the navigation body through a damper, the front end of the cavitation device main body is detachably connected with a head fairing device, and a first telescopic arm which drives the cavitation device disc telescopic pieces to stretch along the radial direction of the cavitation device main body is arranged on the cavitation device main body. According to the high-speed water-entering composite buffer structure of the wing-type multistage linkage cavitation device, provided by the invention, the effective disk surface diameter of the cavitation device is changed through the cooperation of the cavitation device main body, the cavitation device disk expansion piece and the first expansion arm, so that the purpose of controlling the size of supercavitation bubbles is realized.
Description
Technical Field
The invention relates to the technical field of cavitation device water inlet, in particular to a high-speed water inlet composite buffer structure of a wing-type multistage linkage cavitation device.
Background
In order to effectively reduce the navigation resistance, the head of the underwater navigation body is generally provided with a cavitation device, and the navigation body is wrapped by utilizing supercavitation generated by the cavitation device. However, the conventional cavitator is an integrated fixed disk surface, and does not have the function of changing the supercavitation navigation state. While various working conditions are faced in the underwater navigation process of the navigation body, the state that the navigation body is completely wrapped by the supercavitation is difficult to maintain in some cases, because the supercavitation generated by the cavitation device with fixed size is fixed under the condition of the same navigational speed, when the navigational state is changed, the traditional cavitation device is likely to not ensure that the navigational body is in the supercavitation navigational state at any time. In this regard, designing an adjustable cavitation device, which can adjust and compensate the cavitation device disk surface when the navigation state changes, ensures that the navigation body can keep the supercavitation navigation state at any time becomes an important task. The flexible cavitation device adjusting device is matched with a stable and precise control system, so that the effective control on the supercavitation navigation of the navigation body can be realized, the supercavitation navigation can be maintained, the device has a better water-entering impact load-reducing function, and the device with the combined function becomes the key point and the difficulty of the development of the underwater navigation body in the future. Meanwhile, the method has good application prospect and engineering value.
The existing navigation bodies are subjected to load shedding by adopting foam materials or traditional dampers, and the load shedding capacity is limited.
Disclosure of Invention
According to the technical problems, the invention provides a high-speed water-entering composite buffer structure of a wing-type multistage linkage cavitation device, wherein the size of supercavitation is controlled by adjusting the diameter of an effective disc surface of the cavitation device, and the supercavitation generated by the navigation of a water-entering navigation body is adjusted by utilizing the linkage of a wing-type adjusting piece device, a first telescopic arm and a cavitation disc telescopic piece, so that the purpose of reducing navigation resistance to the greatest extent while ensuring that the supercavitation of the navigation body has enough size to completely wrap the navigation body is achieved. The device also adopts multistage buffering load-reducing measures such as reverse air injection, a damper, non-Newtonian fluid, a buffering air bag and the like. The device has the advantages of realizing control of the cavitation process of the navigation body and simultaneously having a stronger buffering load-reducing function.
The invention adopts the following technical means:
the utility model provides a take high-speed water composite buffer structure of multistage linkage cavitation ware of wing, includes the cavitation ware of setting at the head end of navigation body, the cavitation ware includes the cavitation ware main part, the center of cavitation ware main part pass through the attenuator with the head center of navigation body is connected, the front end separable of cavitation ware main part is connected with the head fairing device, the cavitation ware is still including setting up a plurality of cavitation ware disc expansion pieces in the cavitation ware main part, a plurality of cavitation ware disc expansion pieces centers on the axis evenly distributed of cavitation ware main part, and with cavitation ware main part sliding connection is equipped with the drive in the cavitation ware main part the cavitation ware disc expansion piece is followed the radial flexible first flexible arm of cavitation ware main part.
The cavitation device disc expansion piece has a fan-shaped structure;
the cavitation device comprises a cavitation device main body, a first telescopic arm, a cavitation device disc telescopic sheet, a notch and a first telescopic arm, wherein the cavitation device main body is hinged with the mounting end of the first telescopic arm, the first telescopic arm extends radially, one end of the cavitation device disc telescopic sheet, which is close to the cavitation device main body, is of a double-sheet structure, the cavitation device main body is clamped in the middle, the cavitation device disc telescopic sheet is provided with the notch, the first telescopic arm is positioned in the notch, and the output end of the first telescopic arm is hinged with the end of the notch.
An airfoil shaped adjusting piece device is arranged around the axis of the damper;
the wing section adjusting piece device comprises a plurality of hollow outer wing section adjusting pieces, an inner wing section adjusting piece is arranged between two adjacent outer wing section adjusting pieces, and two sides of the inner wing section adjusting piece are arranged in the outer wing section adjusting pieces and are in sliding connection with the outer wing section adjusting pieces; the inner wing type adjusting piece corresponds to the cavitation disc telescopic piece;
the rear end of the outer wing type adjusting piece is hinged with the outer edge of the navigation body, one side of the inner wing type adjusting piece, which is close to the front end of the inner wing type adjusting piece, is hinged with the output end of a second telescopic arm which is obliquely arranged, and the fixed end of the second telescopic arm is fixedly connected with a cavitation device disc telescopic piece corresponding to the inner wing type adjusting piece.
In one development, a plurality of buffer air bags are arranged around the axis of the damper, the front ends of the buffer air bags are connected with non-Newtonian fluid storage bags, non-Newtonian fluid is arranged in the non-Newtonian fluid storage bags, and the non-Newtonian fluid storage bags and the buffer air bags are located in a space surrounded by the navigation body, the wing-shaped adjusting piece device and the cavitation device.
The air storage device is arranged in the navigation body, a first air nozzle is arranged in the center of the front end of the cavitation device main body, and the air storage device is communicated with the first air nozzle through a first ventilation pipeline system.
According to the development, the damper comprises a first outer sleeve, a first oil storage cavity is formed in the first outer sleeve, a first piston rod is arranged in the first outer sleeve, the front end of the first piston rod penetrates out of the first outer sleeve and is fixedly connected with the cavitation device main body, a first piston is arranged at the rear end of the first piston rod, a pull spring sleeved on the first piston rod is arranged at the portion between the first piston and the front end of the first outer sleeve, the rear end of the first outer sleeve is fixedly connected with the head end of the navigation body, a first hydraulic oil cavity is formed at the portion between the rear end of the first outer sleeve and the first piston, and the first hydraulic oil cavity is communicated with the first oil storage cavity.
The first ventilation pipeline system comprises a first ventilation pipe, the rear end of the first ventilation pipe is communicated with the gas storage device through a first ventilation valve, the front end of the first ventilation pipe sequentially penetrates through the center of the rear end of the first outer sleeve and the center of the first piston, penetrates into the first piston rod and is in airtight sliding connection with the first piston rod and the inner wall of the first piston, a buffer air cavity is arranged in the first piston rod close to the front end of the first piston rod, the rear end of the buffer air cavity is communicated with the front end of the first ventilation pipe, a first compression spring with the axis coincident with the axis of the first piston rod is arranged in the buffer air cavity, the end face of the first ventilation pipe is abutted against the first compression spring, a through hole communicated with the buffer air cavity is formed in the front end of the first piston rod, and the front end of the through hole is communicated with the first air spraying port through a second ventilation valve.
In one development, the head fairing device comprises a head fairing and a fairing bracket, wherein the head fairing is detachably connected with the front end of the fairing bracket, and the rear end of the fairing bracket is detachably connected with the first air port of the cavitation device main body.
The first telescopic boom comprises a telescopic boom outer sleeve, a telescopic boom piston matched with the telescopic boom outer sleeve is arranged in the telescopic boom outer sleeve, the telescopic boom piston divides the telescopic boom outer sleeve into two parts, one part is a telescopic boom air cavity, and the telescopic boom air is communicated with the through hole through a hose and a third ventilation valve; the other part is provided with a telescopic arm piston rod which penetrates out of the telescopic arm outer sleeve, and the part of the telescopic arm piston rod positioned in the telescopic arm outer sleeve is sleeved with a second compression spring;
the telescopic arm outer sleeve is connected with the cavitation device main body, and one end, far away from the telescopic arm piston, of the telescopic arm piston rod is connected with the cavitation device disc telescopic sheet.
According to the first improvement, the second telescopic arm comprises a second outer sleeve, a second oil storage cavity is formed in the second outer sleeve, a second piston rod is arranged in the second outer sleeve, the rear end of the second piston rod penetrates out of the second outer sleeve and is hinged to the inner wing type adjusting piece, a second piston is arranged at the front end of the second piston rod, a third compression spring sleeved on the second piston rod is arranged at the part between the second piston and the front end of the second outer sleeve, the front end of the second outer sleeve is hinged to the cavitation disc telescopic piece, a second hydraulic oil cavity is formed at the part between the front end of the second outer sleeve and the second piston, and the second hydraulic oil cavity is communicated with the second oil storage cavity.
Compared with the prior art, the invention has the following advantages:
1. according to the high-speed water-entering composite buffer structure of the wing-type multistage linkage cavitation device, provided by the invention, the effective disk surface diameter of the cavitation device is changed through the cooperation of the cavitation device main body, the cavitation device disk expansion piece and the first expansion arm, so that the purpose of controlling the size of supercavitation bubbles is realized.
2. The invention realizes the adjustment of the size of supercavitation bubbles generated by the navigation body by utilizing the linkage of the wing section adjusting piece device, the first telescopic arm and the cavitation disc telescopic piece, can reduce the navigation resistance to the greatest extent, and can realize the large-range reduction of the navigation resistance of the navigation body in the flight process.
3. The invention adopts multistage buffering load reduction measures such as reverse air injection of the first air injection port, damping buffering of the damper, flexible buffering of the non-Newtonian fluid and the buffering air bag and the like to realize multistage load reduction in the water entering process of the navigation body.
4. After the cavitation device disc telescopic sheets are fully stretched out before entering water, high-speed air flow which is right against the water surface has a thrust F which is outwards from the inner side of the wing-shaped regulating sheets according to Bernoulli principle when passing through the surfaces of the wing-shaped regulating sheets, and the telescopic arms are assisted to keep the cavitation device disc telescopic sheets in a stretched stable state all the time before entering water. The larger cavitation disk area is more beneficial to the generation of large supercavitation.
Based on the reasons, the invention can be widely popularized in the fields of water entry of navigation bodies 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 that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a three-dimensional view of a high-speed water-entry composite buffer structure with a wing-type multistage linkage cavitation device in an embodiment of the invention.
Fig. 2 is a front view of a high-speed water-entering composite buffer structure of a winged multi-stage linkage cavitation device in an embodiment of the invention.
Fig. 3 is a cross-sectional view taken along A-A in fig. 2.
Fig. 4 is an enlarged schematic diagram of the front end of a high-speed water-entering composite buffer structure of a winged multi-stage linkage cavitation device in an embodiment of the invention.
FIG. 5 is a schematic illustration of a cavitation device (only one cavitation device disk expansion plate, one outer wing-type adjusting plate and one inner wing-type adjusting plate are reserved) in an embodiment of the invention.
FIG. 6 is a schematic view of a cavitation device in accordance with an embodiment of the present invention when the disk telescoping pieces are retracted.
FIG. 7 is a schematic view of a cavitation device in accordance with an embodiment of the present invention with the disc telescoping pieces deployed.
Fig. 8 is a schematic diagram of a damper and a first vent line system in accordance with an embodiment of the invention.
Fig. 9 is a schematic structural view of a first telescopic arm and a second telescopic arm according to an embodiment of the present invention.
Fig. 10 is a schematic view of a structure of a head fairing according to an embodiment of the invention.
Fig. 11 is a schematic view of a navigation body in an air navigation state according to an embodiment of the present invention.
Fig. 12 is a schematic view of a vehicle following removal of a fairing near the head of the water in an embodiment of the invention.
Fig. 13 is a schematic view of a vehicle approaching a surface fairing bracket after removal according to an embodiment of the invention.
FIG. 14 is a schematic view of the jet of a first jet of a vehicle near the surface of water according to an embodiment of the present invention.
Fig. 15 is a schematic view of a vehicle sailing in supercavitation according to an embodiment of the present invention.
FIG. 16 is a schematic view showing the stress of the front end of the blade-type adjusting blade device after expansion in the embodiment of the invention.
In the figure: 1. a navigation body; 2. a cavitation device; 201. a cavitation body; 202. a cavitation disc expansion piece; 3. a damper; 301. a damper base; 302. a first outer sleeve; 303. a first piston rod; 304. a first piston; 305. a pull spring; 306. a first hydraulic oil chamber; 4. a head fairing device; 401. a head fairing; 402. a cowling bracket; 5. a first telescopic arm; 501. an outer sleeve of the telescopic arm; 502. a telescopic arm piston; 503. a telescopic arm air cavity; 504. a hose; 505. a telescopic arm piston rod; 506. a second compression spring; 507. a third vent valve; 6. a gas storage device; 601. a first gas nozzle; 602. a first vent pipe; 603. a first vent valve; 604. a first compression spring; 605. a through hole; 606. a second vent valve; 7. an airfoil adjustment vane arrangement; 701. an outer wing type adjusting piece; 702. an inner wing type adjusting piece; 703. a side fairing; 8. a buffer air bag; 9. a non-newtonian fluid storage bag; 10. a second telescopic arm; 1001. a second outer sleeve; 1002. a second piston rod; 1003. a second piston; 1004. a third compression spring; 1005. and the second hydraulic oil cavity.
Detailed Description
It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other. The invention will be described in detail below with reference to the drawings in connection with embodiments.
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the 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 present invention. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be clear that the dimensions of the respective parts shown in the drawings are not drawn in actual scale for 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. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
In the description of the present invention, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present invention and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present invention: the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.
As shown in fig. 1 to 16, the invention discloses a high-speed water-entering composite buffer structure of a wing-type multistage linkage cavitation device, which comprises a cavitation device 2 arranged at the head end of a navigation body 1, wherein the cavitation device 2 comprises a cavitation device main body 201, the center of the cavitation device main body 201 is connected with the center of the head of the navigation body 1 through a damper 3, the front end of the cavitation device main body 201 is detachably connected with a head fairing device 4, the cavitation device 2 further comprises a plurality of cavitation device disc telescopic sheets 202 arranged on the cavitation device main body 201, the plurality of cavitation device disc telescopic sheets 202 are uniformly distributed around the axis of the cavitation device main body 201 and are in sliding connection with the cavitation device main body 201, and a first telescopic arm 5 for driving the cavitation device disc telescopic sheets 202 to extend and retract along the radial direction of the cavitation device main body 201 is arranged on the cavitation device main body 201.
An airfoil shaped adjusting piece means 7 is provided around the axis of the damper 3;
a plurality of buffer air bags 8 are arranged around the axis of the damper 3, the front ends of the buffer air bags 8 are connected with non-Newtonian fluid storage bags 9, non-Newtonian fluid is arranged in the non-Newtonian fluid storage bags 9, and the non-Newtonian fluid storage bags 9 and the buffer air bags 8 are positioned in a space surrounded by the navigation body 1, the wing-shaped adjusting piece device 7 and the cavitation device 2.
The wing section adjusting plate device 7 comprises a plurality of hollow outer wing section adjusting plates 701, an inner wing section adjusting plate 702 is arranged between two adjacent outer wing section adjusting plates 701, and two sides of the inner wing section adjusting plate 702 are arranged in the outer wing section adjusting plates 701 and are connected with the outer wing section adjusting plates 701 in a sliding manner; the inner wing type adjusting piece 702 corresponds to the cavitation disc telescopic piece 202 (the number and the position correspond to each other); the cavity requirement of the outer wing type adjusting piece 701 can enable the inner wing type adjusting piece 702 to finish certain up-down and left-right movement in the cavity requirement, the purpose of limiting the movement of the outer wing type adjusting piece 701 can be achieved by accurately calculating the section of the outer wing type adjusting piece 701, the limit on the radial movement range of the cavitation device disc expansion piece 202 is indirectly achieved, and finally the disc expansion size of the cavitation device 2 is limited.
The rear end of the outer wing type adjusting plate 701 is hinged to the outer edge of the navigation body 1 (in this embodiment, a side fairing 703 is fixed to the outer edge of the navigation body 1, the rear end of the outer wing type adjusting plate 701 is hinged to the side fairing 703, the side fairing 703 is integrally formed, the material is a high-strength aluminum alloy material), one side of the inner wing type adjusting plate 702 near the rear end of the inner wing type adjusting plate 702 is hinged to the output end of the second telescopic arm 10 which is obliquely arranged, and the fixed end of the second telescopic arm 10 is fixedly connected with the cavitation disc telescopic plate 202 corresponding to the inner wing type adjusting plate 702.
The second telescopic arm 10 comprises a second outer sleeve 1001, a second oil storage cavity is formed in the second outer sleeve 1001, a second piston rod 1002 is arranged in the second outer sleeve 1001, the rear end of the second piston rod 1002 penetrates out of the second outer sleeve 1001 and is hinged to the inner wing type adjusting plate 702, a second piston 1003 is arranged at the front end of the second piston rod 1002, a third compression spring 1004 sleeved on the second piston rod 1002 is arranged at a part between the second piston 1003 and the front end of the second outer sleeve 1001, the front end of the second outer sleeve 1001 is hinged to the cavitation disc telescopic plate 202, a second hydraulic oil cavity 1005 is formed at a part between the front end of the second outer sleeve 1001 and the second piston 1003, and the second hydraulic oil cavity 1005 is communicated with the second oil storage cavity.
The air storage device 6 is arranged in the navigation body 1, a first air nozzle 601 is arranged in the center of the front end of the cavitation device main body 201, and the air storage device 6 is communicated with the first air nozzle 601 through a first ventilation pipeline system.
The damper 3 comprises a first outer sleeve 302, the rear end of the first outer sleeve 302 is fixedly connected with the head of the navigation body 1 through a damper base 301, a first oil storage cavity is formed in the first outer sleeve 302, a first piston rod 303 is arranged in the first outer sleeve 302, the front end of the first piston rod 303 penetrates out of the first outer sleeve 302 and is fixedly connected with the cavitation device main body 201, a first piston 304 is arranged at the rear end of the first piston rod 303, a pull spring 305 sleeved on the first piston rod 303 is arranged at the part between the first piston 304 and the front end of the first outer sleeve 302, a first hydraulic oil cavity 306 is formed at the part between the rear end of the first outer sleeve 302 and the first piston 304, and the first hydraulic oil cavity 306 is communicated with the first oil storage cavity.
The first ventilation pipe system comprises a first ventilation pipe 602, the rear end of the first ventilation pipe 602 is communicated with the gas storage device 6 through a first ventilation valve 603, the front end of the first ventilation pipe 602 sequentially penetrates through the center of the rear end of the first outer sleeve 302 and the center of the first piston 304 and penetrates into the first piston rod 303, the first ventilation pipe 602 is in sealing connection with the first outer sleeve 302 and is in airtight sliding connection with the first piston rod 303 and the inner wall of the first piston 304, a buffer air cavity is arranged in the first piston rod 303 close to the front end of the first piston rod, the rear end of the buffer air cavity is communicated with the front end of the first ventilation pipe 602, a first compression spring 604 with the axis coincident with the axis of the first piston rod 303 is arranged in the buffer air cavity, the end face of the first ventilation pipe 602 is abutted against the first compression spring 604, the front end of the first piston rod 303 is provided with a through hole 605 communicated with the buffer air cavity, and the front end of the through hole 605 is communicated with the first air nozzle 601 through a second ventilation valve 606.
The cavitation device disc expansion piece 202 is in a fan-shaped structure;
the cavitation device body is hinged with the mounting end of the first telescopic arm 5, the first telescopic arm 5 extends radially, one end, close to the cavitation device body 201, of the cavitation device disc telescopic piece 202 is of a double-piece structure, the cavitation device body 201 is clamped in the middle by the two pieces, and a notch is formed in the cavitation device disc telescopic piece 202; the first telescopic boom 5 comprises a telescopic boom outer sleeve 501, a telescopic boom piston 502 matched with the telescopic boom outer sleeve 501 is arranged in the telescopic boom outer sleeve 501, the telescopic boom piston 502 divides the telescopic boom outer sleeve 501 into two parts, one part is a telescopic boom air cavity 503, and the telescopic boom air 503 is communicated with the through hole 605 through a hose 504 and a third air-through valve 507; the other part is provided with a telescopic arm piston rod 505, the telescopic arm piston rod 505 penetrates out of the telescopic arm outer sleeve 501, and a second compression spring 506 is sleeved on the part of the telescopic arm piston rod 505 positioned in the telescopic arm outer sleeve 501; the telescopic arm outer sleeve 501 is located in the notch, the end of the telescopic arm outer sleeve 501 is hinged to the cavitation device main body 201, and the output end of the telescopic arm piston rod 505 is hinged to the end of the notch. Venting of the telescopic arm air chamber 503 may be achieved by providing a venting valve or other means.
The head fairing device 4 includes a head fairing 401 and a fairing bracket 402, where the head fairing 401 is detachably connected to a front end of the fairing bracket 402, and a rear end of the fairing bracket 402 is detachably connected to the first air vent 601 of the cavitation body 201. The head fairing 401 is cone-shaped or pointed arch-shaped, the head fairing 401 is composed of multiple-petal shells, and two adjacent-petal shells are connected through a connecting structure; the connecting structure is provided with a blasting device, the navigation body 1 is internally provided with a detonation device for detonating the blasting device, and after the detonation device detonates the blasting device, the fairing is separated along the connecting structure between the two adjacent shells. The connecting structure is a weak structure, can be made of strong glue, and can be made of a thin plate, and the connecting structure is fixedly connected with the two adjacent shells, namely, the connecting structure has certain strength, can bear air resistance in high-speed flight in air, keeps air tightness and cannot be deformed or destroyed; meanwhile, the explosion decomposition of the wire explosion structure mounted on the inner side can be realized, so that the head fairing 401 made of the alloy is separated. The rear end of the fairing bracket 402 is in adsorption connection with the first air jet 601 through an electromagnet, and when the electromagnet is not in adsorption, the gas sprayed out of the first air jet 601 blows away the fairing bracket 402.
The working state is as follows:
as shown in fig. 11, the aircraft 1 first flies a certain distance in the air, and at this time, in order to reduce the flying resistance, the first telescopic arm 5 and the second telescopic arm 10 are adjusted to enable the disc telescopic piece 202 of the air conditioner to retract inwards in the radial direction, and one side of the wing type adjusting piece device 7 close to the head fairing 401 is retracted inwards, so that the air conditioner 2 and the wing type adjusting piece device 7 are in a better streamline shape as a whole, and the flying wind resistance is reduced (fig. 6).
As shown in fig. 12, when the sensor detects that the navigation body 1 is located at a certain distance from the water surface, the blasting device is detonated by the detonating device in the navigation body 1, and blasting is performed on the junction of the multi-lobe structure of the head fairing 401, so that the head fairing housing 401 is decomposed and separated.
As shown in fig. 13, the electromagnet fixing the cowling bracket 402 and the first air nozzle 601 is powered off, and under the action of high-pressure air, the cowling bracket 402 is blown out to be separated from the cavitation device 2, thereby completing the separation of the head cowling 401 and the cowling bracket 402 from the cavitation device 2.
As shown in fig. 14, the first ventilation valve 603 and the second ventilation valve 606 are controlled to be opened, and at this time, the high-pressure gas stored in the gas storage device 6 is ejected from the first air ejection port 601 through the first ventilation pipe 602 and the through hole 605, and ejected toward the water surface, so that the aircraft 1 performs reverse jet and speed reduction and load reduction.
As shown in fig. 15, when the navigation body 1 approaches the water surface further, the first ventilation valve 603 and the third ventilation valve 507 are opened, the high-pressure gas in the gas storage device 6 enters the telescopic arm air cavity 503 through the first ventilation pipe 602, the through hole 605 and the flexible pipe 504, the telescopic arm piston rod 505 is pushed outwards (along the radial direction) thereby to squeeze the second compression spring 506, and the cavitation disc expansion piece 202 expands outwards along the radial direction of the disc under the pushing of the telescopic arm piston rod 505, so that the deployment of the cavitation device 2 is realized (fig. 7). Simultaneously, under the drive of the second telescopic arm 10, the inner wing type adjusting piece 702 also stretches outwards to drive the outer wing type adjusting piece to stretch outwards, so that the radial size of the cavitation device 2 is enlarged, and meanwhile, high-speed air flow passes through the wing tips of the outer wing type adjusting piece 701 and the inner wing type adjusting piece 702 to generate larger outward thrust (as shown in fig. 16), so that the first telescopic arm 5 and the second telescopic arm 10 are assisted to keep the wing type adjusting piece device in an expanded state until the navigation body 1 collides with water. In the millisecond-level time of water collision, the damper 3, the non-Newtonian fluid in the non-Newtonian fluid storage bag 9, the buffer air bag 8 and the second telescopic arm 10 simultaneously carry out load reduction on the navigation body 1. After entering the water, the navigation body 1 can continuously keep the state of being completely wrapped by the supercavitation.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; 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 scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (9)
1. The high-speed water-entering composite buffer structure of the wing-type multistage linkage cavitation device comprises a cavitation device arranged at the head end of a navigation body, wherein the cavitation device comprises a cavitation device main body, and is characterized in that the center of the cavitation device main body is connected with the head center of the navigation body through a damper, the front end of the cavitation device main body is detachably connected with a head fairing device, the cavitation device further comprises a plurality of cavitation device disc telescopic sheets arranged on the cavitation device main body, the plurality of cavitation device disc telescopic sheets are uniformly distributed around the axis of the cavitation device main body and are in sliding connection with the cavitation device main body, and a first telescopic arm for driving the cavitation device disc telescopic sheets to extend and retract along the radial direction of the cavitation device main body is arranged on the cavitation device main body;
an airfoil shaped adjusting piece device is arranged around the axis of the damper;
the wing section adjusting piece device comprises a plurality of hollow outer wing section adjusting pieces, an inner wing section adjusting piece is arranged between two adjacent outer wing section adjusting pieces, and two sides of the inner wing section adjusting piece are arranged in the outer wing section adjusting pieces and are in sliding connection with the outer wing section adjusting pieces; the inner wing type adjusting piece corresponds to the cavitation disc telescopic piece;
the rear end of the outer wing type adjusting piece is hinged with the outer edge of the navigation body, one side of the inner wing type adjusting piece, which is close to the front end of the inner wing type adjusting piece, is hinged with the output end of a second telescopic arm which is obliquely arranged, and the fixed end of the second telescopic arm is fixedly connected with a cavitation device disc telescopic piece corresponding to the inner wing type adjusting piece.
2. The high-speed water-entering composite buffer structure of the winged multi-stage linkage cavitation device according to claim 1, wherein the cavitation device disc expansion piece is in a fan-shaped structure;
the cavitation device comprises a cavitation device main body, a first telescopic arm, a cavitation device disc telescopic sheet, a notch and a first telescopic arm, wherein the cavitation device main body is hinged with the mounting end of the first telescopic arm, the first telescopic arm extends radially, one end of the cavitation device disc telescopic sheet, which is close to the cavitation device main body, is of a double-sheet structure, the cavitation device main body is clamped in the middle, the cavitation device disc telescopic sheet is provided with the notch, the first telescopic arm is positioned in the notch, and the output end of the first telescopic arm is hinged with the end of the notch.
3. The high-speed water-entering composite buffer structure of the winged multistage linkage cavitation device according to claim 1, wherein a plurality of buffer air bags are arranged around the axis of the damper, the front ends of the buffer air bags are connected with non-Newtonian fluid storage bags, non-Newtonian fluid is arranged in the non-Newtonian fluid storage bags, and the non-Newtonian fluid storage bags and the buffer air bags are located in a space surrounded by the navigation body, the wing-shaped adjusting sheet device and the cavitation device.
4. The high-speed water-entering composite buffer structure of the winged multi-stage linkage cavitation device according to claim 1, wherein a gas storage device is arranged in the navigation body, a first gas jet is arranged in the center of the front end of the cavitation device body, and the gas storage device is communicated with the first gas jet through a first ventilation pipeline system.
5. The high-speed water-entering composite buffer structure of the winged multi-stage linkage cavitation device according to claim 4, wherein the damper comprises a first outer sleeve, a first oil storage cavity is formed in the first outer sleeve, a first piston rod is arranged in the first outer sleeve, the front end of the first piston rod penetrates out of the first outer sleeve to be fixedly connected with the cavitation device main body, a first piston is arranged at the rear end of the first piston rod, a pull spring sleeved on the first piston rod is arranged at a part between the first piston and the front end of the first outer sleeve, the rear end of the first outer sleeve is fixedly connected with the head end of the navigation body, a first hydraulic oil cavity is formed at a part between the rear end of the first outer sleeve and the first piston, and the first hydraulic oil cavity is communicated with the first oil storage cavity.
6. The high-speed water-entering composite buffer structure with wing type multistage linkage cavitation device according to claim 5, wherein the first ventilation pipeline system comprises a first ventilation pipe, the rear end of the first ventilation pipe is communicated with the gas storage device through a first ventilation valve, the front end of the first ventilation pipe sequentially penetrates through the center of the rear end of the first outer sleeve and the center of the first piston and into the first piston rod, the first ventilation pipe is hermetically and slidingly connected with the first piston rod and the inner wall of the first piston, a buffer air cavity is arranged in the first piston rod close to the front end of the first piston rod, the rear end of the buffer air cavity is communicated with the front end of the first ventilation pipe, a first compression spring with the axis coincident with the axis of the first piston rod is arranged in the buffer air cavity, the end face of the first ventilation pipe is abutted against the first compression spring, the front end of the first piston rod is provided with a through hole communicated with the buffer air cavity, and the front end of the through hole is communicated with the first air injection port through a second ventilation valve.
7. The high-speed water-entry composite buffer structure of a winged multi-stage linkage cavitation device according to claim 5, wherein the head fairing device comprises a head fairing and a fairing bracket, the head fairing is detachably connected with the front end of the fairing bracket, and the rear end of the fairing bracket is detachably connected with the first air vent of the cavitation device main body.
8. The high-speed water-entering composite buffer structure of the winged multi-stage linkage cavitation device according to claim 6, wherein the first telescopic arm comprises a telescopic arm outer sleeve, a telescopic arm piston matched with the telescopic arm outer sleeve is arranged in the telescopic arm outer sleeve, the telescopic arm piston divides the telescopic arm outer sleeve into two parts, one part is a telescopic arm air cavity, and the telescopic arm air cavity is communicated with the through hole through a hose and a third ventilation valve; the other part is provided with a telescopic arm piston rod which penetrates out of the telescopic arm outer sleeve, and the part of the telescopic arm piston rod positioned in the telescopic arm outer sleeve is sleeved with a second compression spring;
the end part of the telescopic arm outer sleeve is hinged with the cavitation device main body, and one end of the telescopic arm piston rod, which is far away from the telescopic arm piston, is hinged with the cavitation device disc telescopic sheet.
9. The high-speed water-entering composite buffer structure of the winged multi-stage linkage cavitation device according to claim 1, wherein the second telescopic arm comprises a second outer sleeve, a second oil storage cavity is formed in the second outer sleeve, a second piston rod is arranged in the second outer sleeve, the rear end of the second piston rod penetrates out of the second outer sleeve to be hinged with the inner winged adjusting piece, a second piston is arranged at the front end of the second piston rod, a third compression spring sleeved on the second piston rod is arranged at the part between the second piston and the front end of the second outer sleeve, the front end of the second outer sleeve is hinged with the cavitation disc telescopic piece, a second hydraulic oil cavity is formed at the part between the front end of the second outer sleeve and the second piston, and the second hydraulic oil cavity is communicated with the second oil storage cavity.
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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 |
| CN115009481B (en) * | 2022-06-12 | 2023-11-21 | 西北工业大学 | High-speed water-entering buffering wrapped type combined load reduction structure and method for aircraft |
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