WO2023072201A1 - 一种可调制的双层伸缩片空化器结构 - Google Patents

一种可调制的双层伸缩片空化器结构 Download PDF

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Publication number
WO2023072201A1
WO2023072201A1 PCT/CN2022/127981 CN2022127981W WO2023072201A1 WO 2023072201 A1 WO2023072201 A1 WO 2023072201A1 CN 2022127981 W CN2022127981 W CN 2022127981W WO 2023072201 A1 WO2023072201 A1 WO 2023072201A1
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WIPO (PCT)
Prior art keywords
cavitator
layer
telescopic
airfoil
buffer
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2022/127981
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English (en)
French (fr)
Inventor
孙铁志
李尧
宗智
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Dalian University of Technology
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Dalian University of Technology
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Filing date
Publication date
Application filed by Dalian University of Technology filed Critical Dalian University of Technology
Priority to US18/550,559 priority Critical patent/US20240149980A1/en
Publication of WO2023072201A1 publication Critical patent/WO2023072201A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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
    • 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

Definitions

  • the invention relates to the technical field of water entry of a vehicle, in particular to an adjustable double-layer telescopic sheet cavitator structure.
  • most underwater vehicles are designed with a fixed cavitator device, and the generated supercavitation depends on the fixed diameter of the cavitator disk, and the generated supercavitation cannot be flexibly adjusted according to the actual situation. .
  • the size of the supercavitation generated by the cavitator will be significantly reduced.
  • the supercavitation generated by the cavitator may not be enough to completely cover the vehicle, resulting in an increase in its navigation resistance; if the original diameter of the cavitator is too large, it may cause The navigation resistance is too large (the cavitator is a plane, the larger the area, the greater the resistance).
  • designing a cavitation device that can flexibly adjust the generation of supercavitation has become a new topic. The adjustment of the cavitation process can greatly improve the adaptability and survivability of the aircraft body, and at the same time increase the voyage, which has high military value.
  • an adjustable double-layer telescopic sheet cavitator structure is provided.
  • An adjustable double-layer telescopic sheet cavitator structure including a cavitator arranged at the head end of the vehicle, the cavitator includes a cavitator body, and the center of the cavitator body is connected to the head of the vehicle through a damper Central connection, the front end of the cavitator body is detachably connected with a head fairing device, the cavitator body is a double-layer structure, including the first layer and the second layer, and multiple The cavitator disk expansion sheet, a plurality of cavitator disk expansion sheets are evenly distributed around the axis of the cavitator body, and are slidably connected with the corresponding first or second layer, and the head end of the vehicle is equipped with a drive cavitator A buffer drive mechanism in which the telescopic sheet on the surface of the cavitator slides along the radial direction of the main body of the cavitator, and a plurality of telescopic sheets on the surface of the cavitator and the main body of the cavitator form a circle.
  • the telescopic piece on the surface of the cavitator disk is fan-shaped, and a groove is processed inside it, and the groove wraps the first layer or the second layer, and the first layer and the second layer are processed with sliding U-shaped limiters extending radially. Slots, sliding limit protrusions that match the sliding U-shaped limit grooves are processed on the telescopic sheets of the cavitator disk, and the multiple telescopic sheets of the cavitator disk on the first layer are arranged on the second layer.
  • a plurality of telescopic sheets on the surface of the cavitator panel are arranged in a staggered manner.
  • the buffer driving mechanism includes a plurality of airfoil adjustment pieces, the number of the airfoil adjustment pieces matches the number of the cavitator disk telescopic pieces, and is evenly distributed around the axis of the cavitator main body, and each airfoil adjustment piece is opposite to A telescopic piece on the surface of the cavitator, the rear end of the airfoil adjustment piece is hinged with the outer edge of the head end of the vehicle body, the airfoil adjustment piece is hinged with one end of the first buffer telescopic arm on the side close to the rear end, and hinged on the side close to the front end of the airfoil adjustment piece
  • One side of the second buffer telescopic arm is hinged to one end of the second buffer telescopic arm, and the other end of the first buffer telescopic arm is hinged to the front end of the head end of the navigation body, and the other end of the second buffer telescopic arm is fixed to the upper part of the cavitator panel telescopic sheet connected, the section
  • the airfoil regulating piece is provided with a gas accelerating hole
  • the gas accelerating hole is a Tesla valve hole
  • the front end of the gas accelerating hole communicates with the third gas injection port arranged at the front end of the airfoil regulating piece
  • the rear end of the gas accelerating hole It communicates with the air storage device arranged in the navigation body through the flexible pipe and the third vent valve.
  • a booster engine is installed at the tail of the vehicle body, and an exhaust gas collection device is installed in the vehicle body.
  • the exhaust gas collection device includes a turbine suction drive device, and one end of the turbine suction drive device passes through the pipeline and the exhaust end of the booster engine. In communication, the other end of the turbo suction driving device communicates with the inlet of the gas storage device.
  • the center of the front end of the cavitator main body is provided with a first air injection port, and the gas storage device and the first air injection port are communicated through a first ventilation pipeline system.
  • the damper includes a first outer sleeve, an oil storage chamber is arranged in the first outer sleeve, a first piston rod is arranged in the first outer sleeve, and the front end of the first piston rod passes through the first outer sleeve It is fixedly connected with the main body of the cavitator, the rear end of the first piston rod has a first piston, and the part between the first piston and the front end of the first outer sleeve is provided with a tension spring sleeved on the first piston rod.
  • the rear end of the sleeve is fixedly connected to the head end of the sailing body, and the part between the rear end of the first outer sleeve and the first piston forms a first hydraulic oil chamber, and the first hydraulic oil chamber communicates with the oil storage chamber .
  • the first ventilation pipeline system includes a first ventilation tube, the rear end of the first ventilation tube communicates with the gas storage device, a first ventilation valve is arranged inside the first ventilation tube, and the front end of the first ventilation tube passes through the first ventilation tube in turn.
  • There is a buffer air chamber inside the rear end of the buffer air chamber communicates with the front end of the first air pipe, the buffer air chamber is provided with a first compression spring whose axis coincides with the axis of the first piston rod, and the end surface of the first air pipe is in contact with the first
  • the compression spring is offset, and the front end of the first piston rod is provided with a through hole communicating with the buffer air cavity, and the front end of the through hole is communicated with the first air injection port.
  • the head fairing device includes a head fairing and a connecting device, the head fairing is detachably connected to the front end of the connecting device, the rear end of the connecting device is detachably connected to the center of the cavitator main body, and the head of the connecting device The end is provided with a second air injection port, and the second air injection port communicates with the first air injection port.
  • the connecting device includes a connecting pipe fixed at the front end of the first air injection port.
  • the middle part of the connecting pipe is symmetrically processed with bolt installation holes up and down.
  • the two bolt installation holes are respectively equipped with trapezoidal trapezoidal fixed bolts, and the two trapezoidal fixed
  • the bolts are connected by a second pressure spring, and an electromagnet is fixed on the side of the trapezoidal fixed bolt close to the axis of the connecting pipe;
  • the rear end of the fairing fixing rod has a connecting groove matching the connecting pipe, and the groove wall of the connecting groove is processed with a card groove matching the trapezoidal fixing bolt;
  • the front end of the fairing fixed rod is fixed with a connecting piece, and the connecting piece is fixedly connected with the rear end inner wall of the head fairing;
  • a second air pipe is arranged in the fairing fixed rod, and the second air port is arranged on the front end of the fairing fixed rod, and the front end of the second air pipe communicates with the second air port, and the rear end communicates with the connecting groove.
  • the present invention has the following advantages:
  • the telescopic piece on the cavitator panel of the present invention can be stretched under the action of the first buffer telescopic arm and the second buffer telescopic arm, and then the cavitator composed of the main body of the cavitator and the telescopic piece on the cavitator panel can be adjusted.
  • the size of the outer diameter of the cavitator can be adjusted according to the needs. The larger the size of the cavitator, the larger the supercavitation can be generated, which can keep the underwater vehicle completely wrapped by the supercavitation in real time. reduce its sailing resistance.
  • the main body of the cavitator used in the present invention has a double-layer structure, and each layer is provided with a cavitator panel expansion sheet, and a plurality of cavitator panel expansion sheets can form a complete circle when stretched out.
  • the present invention adopts multi-stage load reduction, the second air jet port air jet load reduction, the third air jet port air jet load reduction, the first air jet port air jet load reduction before the navigation body enters the water, the first telescopic arm and the second telescopic arm during the water entry process
  • the arm can perform damping and load reduction, and the damper will also perform damping and load reduction.
  • the air jet from the third jet port is conducive to the formation of larger supercavitation.
  • the gas acceleration hole in the present invention adopts the Tesla valve hole structure, which can solve the problem of automatic acceleration after the gas enters.
  • the Tesla valve hole is a continuously repeating chain structure. The more times the structure is repeated, the faster the acceleration effect will be. The better, that is to say, the smaller the size of the repeated single structure, the better the pressure-reducing effect. Utilizing the directional function of the Tesla valve hole to accelerate the gas can realize acceleration without consuming energy.
  • the present invention can be widely promoted in fields such as water entry of a vehicle.
  • Fig. 1 is a three-dimensional view of the structure of an adjustable double-layer telescopic sheet cavitator in a specific embodiment of the present invention.
  • Fig. 2 is a front view of the structure of an adjustable double-layer telescopic sheet cavitator in the specific embodiment of the present invention.
  • Fig. 3 is a sectional view along A-A in Fig. 2 .
  • Fig. 4 is a schematic diagram of the main body structure of a cavitator according to a specific embodiment of the present invention.
  • Fig. 5 is a side view of the main body of the cavitator according to the specific embodiment of the present invention.
  • Fig. 6 is a schematic structural view of the telescopic sheet on the disk surface of the hollowizer according to the specific embodiment of the present invention.
  • Fig. 7 is a schematic diagram of the contraction of the telescopic sheet on the disk surface of the hollow device according to the specific embodiment of the present invention.
  • Fig. 8 is a schematic diagram of a specific embodiment of the present invention when the telescopic sheet on the surface of the cavitation device is stretched out.
  • Fig. 9 is a schematic diagram of the damper and the first ventilation pipeline system in the specific embodiment of the present invention.
  • Fig. 10 is a schematic diagram of the gas acceleration hole structure in a specific embodiment of the present invention.
  • Fig. 11 is a schematic diagram of the structure of the second buffer telescopic arm in a specific embodiment of the present invention.
  • Fig. 12 is a schematic structural view of the head fairing device in a specific embodiment of the present invention.
  • Fig. 13 is a schematic diagram of the structure of the connection device in the specific embodiment of the present invention (when separated).
  • Fig. 14 is a schematic structural diagram of the tail gas recovery system in the specific embodiment of the present invention.
  • Fig. 15 is a schematic diagram of the vehicle before entering the water in a specific embodiment of the present invention.
  • Fig. 16 is a schematic diagram of the second jet port jetting when the fairing of the head of the navigation body close to the water surface is detached in the specific embodiment of the present invention.
  • Fig. 17 is a schematic diagram showing the separation of the second air injection port of the navigation body close to the water surface in the specific embodiment of the present invention.
  • Fig. 18 is a schematic diagram of air injection from the first air injection port of the vehicle near the water surface in a specific embodiment of the present invention.
  • Fig. 19 is a schematic diagram of simultaneous air injection from the first air jet port and the third air jet port near the water surface in the specific embodiment of the present invention.
  • Fig. 20 is a schematic diagram of traveling under supercavitation after the vehicle enters water in a specific embodiment of the present invention.
  • orientation words such as “front, back, up, down, left, right", “horizontal, vertical, vertical, horizontal” and “top, bottom” etc. indicate the orientation Or positional relationship is generally based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description. In the absence of a contrary description, these orientation words do not indicate or imply the device or element referred to. It must have a specific orientation or be constructed and operated in a specific orientation, so it should not be construed as limiting the scope of the present invention: the orientation words “inside and outside” refer to inside and outside relative to the outline of each part itself.
  • spatially relative terms may be used here, such as “on !, “over !, “on the surface of !, “above”, etc., to describe the The spatial positional relationship between one device or feature shown and other devices or features. 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 the device in the figures is turned over, devices described as “above” or “above” other devices or configurations would then be oriented “beneath” or “above” the other devices or configurations. its underlying device or construction". Thus, the exemplary term “above” can encompass both an orientation of “above” and “beneath”. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptions used herein interpreted accordingly.
  • an adjustable double-layer telescopic sheet cavitator structure includes a cavitator 2 arranged at the head end of the vehicle 1, the cavitator 2 includes a cavitator main body 201, and the cavitator The center of the main body 201 is connected to the center of the head of the vehicle 1 through the damper 3. The front end of the cavitator main body 201 is detachably connected to the head fairing device 4.
  • the cavitator main body 201 has a double-layer structure, including the first layer and the second layer (as shown in Figure 5), the first layer and the second layer are equipped with a plurality of cavitator disk surface expansion sheets 202, and a plurality of cavitator disk surface expansion sheets 202 surround the axis of the cavitator main body 201 Evenly distributed and slidingly connected with the corresponding first or second layer, the head end of the flying body 1 is equipped with a buffer drive mechanism 5 that drives the cavitator disk telescopic piece 202 to slide along the radial direction of the cavitator main body 201 , a plurality of cavitator panel telescopic sheets 202 and the cavitator main body 201 form a circle (as shown in FIGS. 7 and 8 ).
  • the expansion plate 202 on the surface of the cavitator is fan-shaped, and a groove 203 is processed inside it (as shown in Figure 6).
  • the groove 203 wraps the first layer or the second layer (that is, the first layer or the second layer is inserted into the groove 203 ), the first layer and the second layer are all processed with a radially extending sliding U-shaped limiting groove 204 (as shown in Figure 4), and the cavitator disk surface telescopic piece 202 is processed with a sliding U-shaped limiting groove 204 cooperate with the sliding limit protrusions 205, and the plurality of cavitator panel expansion sheets 202 arranged on the first layer and the plurality of cavitator panel expansion sheets 202 arranged on the second layer are alternately arranged.
  • the buffer drive mechanism 5 includes a plurality of airfoil adjustment pieces 501, the number of the airfoil adjustment pieces 501 matches the number of the cavitator disk telescopic pieces 202, and surrounds the axis of the cavitator main body 201 Evenly distributed, each airfoil adjustment piece 501 is opposite to a cavitator disk surface expansion piece 202;
  • the outer edge of the head end is hinged (that is, the cylindrical side fairing 502 is connected to the head end of the vehicle 1, and the rear end of the airfoil adjusting piece 501 is hinged to the front end of the side fairing 502), and the side rectification
  • the cover 502 is connected to the navigation body 1 by electromagnet adsorption; the airfoil adjustment piece 501 is hinged with one end of the first buffer telescopic arm 503 on the side near the rear end, and connected with the second buffer telescopic arm 504 on the side near the front end.
  • One end is hinged, and the other end of the first buffer telescopic arm 503 is hinged to the outer periphery of the vehicle 1, the other end of the second buffer telescopic arm 504 is fixedly connected to the upper part of the cavitator panel telescopic piece 202, the first buffer telescopic arm 503 and The second buffer telescopic arm 504 is all inclined to set, and the section of the airfoil adjusting piece 501 is an airfoil, and the two adjacent airfoil adjusting pieces 501 are closely attached; the section of 3/2 of the airfoil adjusting piece 501 is thinner.
  • the section of 3/1 is a thick airfoil section
  • the purpose of this design is that the adjacent airfoil adjustment pieces 501 can be closely attached together, the gap is minimized, and the head fairing device 4 is installed.
  • the entire profile of the flying body 1 reaches the best streamlined shape.
  • the airfoil adjusting piece 501 shrinks radially inward, the thicker end can smoothly slide to the inner side of the thinner end of the adjacent airfoil adjusting piece 501, so that the overall shape can be kept in a good shape without being obtrusive.
  • the structures of the first buffer telescopic arm 503 and the second buffer telescopic arm 504 in this embodiment are the same hydraulic telescopic rod type, which include: a second outer sleeve 505, a second outer sleeve 505 is provided with a second piston rod 506 passing through the second outer sleeve 505, and one end of the second piston rod 506 in the second outer sleeve 505 has a second piston 507 that matches the second outer sleeve 505 , the part of the second outer sleeve 505 located on both sides of the second piston 507 has a second hydraulic oil cavity 509 and a third pressure spring 508 respectively, and the third pressure spring 508 is located near the second piston rod 506 and passes through the second outer sleeve At one end of the sleeve 505 , the second outer sleeve 505 has an oil storage cavity, and the oil storage cavity communicates with the second hydraulic oil cavity 509 .
  • the hydraulic oil in the oil storage chamber of the second outer sleeve 505 enters the second hydraulic oil chamber 509, pushing the second piston rod 506 to elongate, at this time the third pressure spring 508 Otherwise, the hydraulic oil in the second hydraulic oil cavity 509 returns to the second outer sleeve 505, and the second piston rod 506 contracts under the action of air pressure and the third compression spring.
  • the first buffer telescopic arm 503 and the second buffer telescopic arm 504 By adjusting the first buffer telescopic arm 503 and the second buffer telescopic arm 504, the radial sliding of the telescopic plate 202 on the cavitator panel can be realized. When sliding out, the area of the cavitator 2 is enlarged, and when sliding in, the area of the cavitator 2 is reduced. .
  • the transmitted force is also an oblique force, resulting in a A larger force component along the direction of water entry (the left and right direction in Figure 14) (the force that makes the telescopic sheet 30 slide along the radial direction of the cavitator disk, perpendicular to the direction of this force component), the force component will move to the right (Water entry direction) Squeeze the telescopic plate 202 on the cavitator panel to make it squeeze and hit the cavitator main body 201.
  • Too fast impact may cause damage to the U-shaped limit groove 204 and sliding limit protrusion 205 and lose the adjustment space. function of the size of the variator. Therefore, a hydraulic type is adopted in the specific embodiment, and the hydraulic type has a significant buffering effect on the transmission of motion, which makes the transmission of the motion of the buffer drive mechanism 5 more gentle and prolongs the life of the device.
  • the airfoil regulating piece 501 is provided with a gas accelerating hole 7, the gas accelerating hole 7 is a Tesla valve hole, and the front end of the gas accelerating hole 7 is connected to the third third hole arranged at the front end of the airfoil regulating piece 501.
  • the gas injection port 701 communicates, and the rear end of the gas acceleration hole 7 communicates with the gas storage device 6 arranged in the navigation body 1 through a hose 702 and a third ventilation valve 703 .
  • a through-type cylindrical channel is processed at the widest part of the flange of the airfoil adjusting piece 501.
  • the airfoil adjusting piece 501 and the hinge connection structure are made of high-strength alloy, and the through-type cylindrical channel is inserted into the through-type cylindrical channel.
  • the hollow column is made of resin-based composite material with a mold.
  • the gas ejected from the third air injection port 701 can be used not only to buffer the load reduction but also to form larger air bubbles, which is beneficial to the formation of large air bubbles.
  • a booster engine 9 is installed at the tail of the vehicle 1, and an exhaust gas collection device 8 is installed in the vehicle 1.
  • the exhaust gas collection device 8 includes a turbine suction drive device 801, and the turbine suction drive device 801 is located at the turbine.
  • one end of the turbo air suction driving device 801 communicates with the exhaust end of the booster engine 9 through a pipeline, and the other end of the turbo air suction driving device 801 communicates with the inlet of the air storage device 6 .
  • each tail gas recovery device 8 is provided with a plurality of series-connected turbo suction drive devices 801, and each tail gas recovery device 8 is equipped with a gas storage device 6, and multiple gas storage devices
  • the outlet end of 6 is collected into the collection pipeline 803 through the second vent valve 802.
  • the turbo suction driving device of the present invention includes a turbo fan, and absorbs exhaust gas by driving the turbo fan to rotate.
  • the center of the front end of the cavitator body 201 is provided with a first air injection port 601 , and the gas storage device 6 communicates with the first air injection port 601 through a first ventilation pipeline system.
  • the damper 3 includes a first outer sleeve 302, the first outer sleeve 302 is provided with an oil storage chamber 301, the first outer sleeve 302 is provided with a first piston rod 303, and the front end of the first piston rod 303 passes through the first
  • An outer sleeve 302 is fixedly connected with the cavitator main body 201, the rear end of the first piston rod 303 has a first piston 304, and the part between the first piston 304 and the front end of the first outer sleeve 302 is provided with a first
  • the tension spring 305 on the piston rod 303, the rear end of the first outer sleeve 302 is fixedly connected with the head end of the vehicle 1, and the part between the rear end of the first outer sleeve 302 and the first piston 304 forms the first hydraulic pressure.
  • the oil cavity 306, and the first hydraulic oil cavity 306 communicates with the oil storage cavity.
  • the first ventilation pipeline system includes a first ventilation tube 602, the rear end of the first ventilation tube 602 communicates with the gas storage device 6, a first ventilation valve 603 is arranged inside the first ventilation tube 602, and the front end of the first ventilation tube 602 is sequentially Pass through the center of the rear end of the first outer sleeve 302, the center of the first piston 304, and penetrate into the first piston rod 303, the first air pipe 602 is in sealing connection with the first outer sleeve 302, and is connected with the first piston
  • the inner wall of the rod 303 and the first piston 304 is airtightly slidably connected, and the inside of the third piston rod 303 near its front end has a buffer air chamber, and the rear end of the buffer air chamber communicates with the front end of the first ventilation pipe 602, and the inside of the buffer air chamber
  • There is a first pressure spring 604 whose axis coincides with the axis of the first piston rod 303.
  • the end surface of the first vent pipe 602 is against the first pressure spring 604.
  • the front end of the first piston rod 303 is provided with a through hole communicating with the buffer air chamber 605 , the front end of the through hole 605 communicates with the first air injection port 601 .
  • the head fairing device 4 comprises a head fairing 401 and a connecting device, the head fairing 401 is detachably connected with the front end of the connecting device, and the head fairing 401 is conical or pointed arched , the head fairing 401 is composed of multi-lobed shells, and the adjacent two shells are connected by a connecting structure; the connecting structure is provided with a blasting device, and the detonating device for detonating the blasting device is provided in the navigation body 1, and the detonating device After detonating the blasting device, the fairing is separated along the connecting structure between the two adjacent shells.
  • connection structure is a "weak structure", which can be superglue, which bonds the two adjacent shells together, or it can be a thin plate, which is fixedly connected with the adjacent two shells, that is, it must have a certain strength and be able to withstand air.
  • the air resistance during high-speed flight maintains airtightness and will not be deformed or damaged; at the same time, it can be exploded and disassembled by the wire explosion structure installed on the inside, so that the head fairing 401 made of alloy can be separated.
  • the rear end of the connecting device is detachably connected to the center of the cavitator main body 201 .
  • the connecting device includes a connecting pipe 403 fixed on the front end of the first air injection port 601.
  • the middle part of the connecting pipe 403 is symmetrically processed with bolt installation holes up and down.
  • the two bolt installation holes are respectively equipped with trapezoidal trapezoidal fixing bolts 404, and the two trapezoidal
  • the fixing pin 404 is connected by the second pressure spring 405, and the trapezoidal fixing pin 404 is fixed with an electromagnet 406 near the axis of the connecting pipe 403;
  • the groove wall of connecting groove 408 is processed with the draw-in groove 409 that cooperates with trapezoidal fixed bolt 404; connect.
  • a second air pipe 411 is disposed inside the fairing fixing rod 407 , the rear end of the second air pipe 411 communicates with the connecting groove 408 , and the front end of the second air pipe 411 communicates with the second air outlet 402 .
  • the trapezoidal fixing pin 404 When the front end of the connecting pipe 403 is inserted into the connecting groove 408, the trapezoidal fixing pin 404 is pushed into the engaging groove 409 under the action of the second compression spring 405, so that the reliable connection between the connecting pipe 403 and the fairing fixing rod 407 is realized.
  • the electromagnet 406 works, and the two trapezoidal fixing pins 404 are adsorbed so that the outer edge surface thereof is lower than or coincides with the outer edge surface of the connecting pipe 403. At this time, the trapezoidal fixing pins 404 does not limit fit with the slot 409 .
  • the first buffer telescopic arm 503 and the second buffer telescopic arm 504 make the cavitator disk surface telescopic sheet 202 shrink radially inward , and the side of the airfoil adjustment piece 501 close to the head fairing 401 shrinks inwardly, so that the whole presents a better streamlined shape and reduces the flight wind resistance (as shown in Figure 7).
  • the head fairing 401 is controlled to decompose, and the second ventilation valve 802 and the first ventilation valve 603 are controlled to be opened.
  • the high-pressure gas support frame is ejected from the second air injection port 402, and the air is sprayed toward the water surface to perform the first reverse injection of air on the vehicle 1 to reduce the speed to achieve the purpose of load reduction.
  • the first buffer telescopic arm 503 and the second buffer telescopic arm 504 are adjusted to drive the airfoil adjustment piece 501 and the cavitator disk surface telescopic piece 202 to expand outwards to achieve The expansion purpose of the size of the cavitator 2 (as shown in Figure 8).
  • the third reverse jet deceleration and load reduction Open the third ventilation valve 703 while unfolding, so that the high-pressure air in the gas storage device 6 enters the gas acceleration hole 7 through the hose 702 to accelerate, and after being accelerated, it is sprayed out from the third jet 701, so as to realize the protection of the water-entry vehicle 1.
  • the first buffer telescopic arm 503 and the second buffer telescopic arm 504 can perform damping and buffering, and the damper 3 can also play a buffering effect.
  • the vehicle 1 performs supercavitation navigation after entering the water. During supercavitation voyage, the size of the cavitator 2 can be adjusted as required.

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  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

一种可调制的双层伸缩片空化器结构，包括设置在航行体（1）的头端的空化器（2），空化器（2）包括空化器主体（201），空化器主体（201）的中心通过阻尼器（3）与航行体（1）的头部中心连接，空化器主体（201）的前端可分离连接有头部整流罩装置（4），空化器主体（201）为双层结构，包括第一层和第二层，第一层和第二层上均安装有多个空化器盘面伸缩片（202），多个空化器盘面伸缩片（202）围绕空化器主体（201）的轴线均匀分布，并与其所对应的第一层或第二层滑动连接，航行体（1）的头端安装有驱动空化器盘面伸缩片（202）沿空化器主体（201）的径向方向滑动的缓冲驱动机构（5），多个空化器盘面伸缩片（202）和空化器主体（201）拼成一个圆。

Description

一种可调制的双层伸缩片空化器结构 技术领域
本发明涉及航行体入水技术领域，具体而言是一种可调制的双层伸缩片空化器结构。
背景技术
水下超空泡航行体及水下兵器主要依靠产生超空泡将本体完全包裹以达到降低其航行阻力的目的。但目前水下航行体大多设计了固定不变的空化器装置，生成的超空泡依赖于固定不变的空化器圆盘盘面直径，不能够根据实际情况灵活调节所生成的超空泡。例如，当航行体因燃料耗尽使得航速明显下降时，空化器产生的超空泡尺寸就会显著变小。若原本的空化器盘面直径较小，可能会使空化器生成的超空泡不足以完全包覆住航行体，导致其航行阻力增加；若原本的空化器直径太大，有会导致航行阻力过大(空化器为平面，面积越大阻力也越大)。对此，设计一款可以灵活调节生成超空泡的空化装置就成为一个新的课题。对空化过程的调节可以大大提高航行体的适应和生存能力，同时可以增加航程，具有较高的军用价值。
同时现有的航行体入水过程中多数采用阻尼器进行单次阻尼降载，降载能力有限，不利于保护航行体。
发明内容
根据上述技术问题，而提供一种可调制的双层伸缩片空化器结构。
本发明采用的技术手段如下：
一种可调制的双层伸缩片空化器结构，包括设置在航行体的头端的空化器，空化器包括空化器主体，空化器主体的中心通过阻尼器与航行体的头部中心连接，空化器主体的前端可分离连接有头部整流罩装置，空化器主体为双层结构，包括第一层和第二层，第一层和第二层上均安装有多个空化器盘 面伸缩片，多个空化器盘面伸缩片围绕空化器主体的轴线均匀分布，并与其所对应的第一层或第二层滑动连接，航行体的头端安装有驱动空化器盘面伸缩片沿空化器主体的径向方向滑动的缓冲驱动机构，多个空化器盘面伸缩片和空化器主体拼成一个圆。
进一步地，空化器盘面伸缩片呈扇形，其内部加工有凹槽，凹槽包裹第一层或第二层，第一层和第二层上均加工有呈径向延伸的滑动U形限位槽，空化器盘面伸缩片上加工有与滑动U形限位槽相配合的滑动限位凸起，设置在第一层上的多个空化器盘面伸缩片与设置在第二层上的多个空化器盘面伸缩片交错设置。
进一步地，缓冲驱动机构包括多个翼型调节片，翼型调节片的数量与空化器盘面伸缩片的数量相匹配，且围绕空化器主体的轴线均匀分布，每个翼型调节片相对一个空化器盘面伸缩片，翼型调节片的后端与航行体的头端外沿铰接，翼型调节片在其靠近后端的一侧与第一缓冲伸缩臂的一端铰接，在其靠近前端的一侧与第二缓冲伸缩臂的一端铰接，且第一缓冲伸缩臂的另一端与航行体的头端的前端面铰接，第二缓冲伸缩臂的另一端与空化器盘面伸缩片的上部固定连接，翼型调节片的截面呈翼型，相临两个翼型调节片紧密贴合。
进一步地，翼型调节片内设有气体加速孔，气体加速孔为特斯拉阀孔，气体加速孔的前端与设置在翼型调节片前端的第三喷气口连通，气体加速孔的后端通过软管和第三通气阀门与设置在航行体内的储气装置连通。
进一步地，航行体的尾部安装有助推发动机，且航行体内安装有尾气收集装置，尾气收集装置包括涡轮吸气驱动装置，涡轮吸气驱动装置的一端通过管路和助推发动机的排气端连通，涡轮吸气驱动装置的另一端与储气装置的入口连通。
进一步地，空化器主体的前端中心设有第一喷气口，储气装置和第一喷气口通过第一通气管路系统连通。
进一步地，阻尼器包括第一外套筒，第一外套筒内设有储油腔，第一外套筒内设有第一活塞杆，第一活塞杆的前端穿出第一外套筒与空化器主体固定连接，第一活塞杆的后端具有第一活塞，第一活塞与第一外套筒前端之间的部分设有套在第一活塞杆上的拉弹簧，第一外套筒的后端与航行体的头端 固定连接，第一外套筒的后端与第一活塞之间的部分形成第一液压油腔体，且第一液压油腔体与储油腔连通。
进一步地，第一通气管路系统包括第一通气管，第一通气管的后端与储气装置连通，第一通气管内设有第一通气阀门，第一通气管的前端依次穿过第一外套筒的后端中心、第一活塞的中心，并穿入第一活塞杆内，且与第一活塞杆和第一活塞的内壁气密式滑动连接，第三活塞杆靠近其前端的内部具有缓冲气腔，缓冲气腔的后端与第一通气管的前端连通，缓冲气腔内设有轴线与第一活塞杆轴线重合的第一压弹簧，第一通气管的端面与第一压弹簧相抵，第一活塞杆的前端设有与缓冲气腔连通的通孔，通孔的前端与第一喷气口连通。
进一步地，头部整流罩装置包括头部整流罩和连接装置，头部整流罩与连接装置的前端可分离连接，连接装置的后端与空化器主体的中心可分离连接，连接装置的头端设有第二喷气口，第二喷气口与第一喷气口连通。
进一步地，连接装置包括固定在第一喷气口前端的连接管，连接管的中部上下对称加工有插销安装孔，两个插销安装孔内分别安装有呈梯形的梯形固定插销，且两个梯形固定插销通过第二压弹簧连接，梯形固定插销靠近连接管轴线的一侧固定有电磁铁；
整流罩固定杆的后端具有与连接管相匹配的连接凹槽，且连接凹槽的槽壁上加工有与梯形固定插销相配合的卡槽；
整流罩固定杆的前端固定有连接件，连接件与头部整流罩的后端内壁固定连接；
整流罩固定杆内设有第二通气管，第二通气口设置在整流罩固定杆的前端，且第二通气管的前端与第二通气口连通，后端与连接凹槽连通。
较现有技术相比，本发明具有以下优点：
1、本发明的空化器盘面伸缩片在第一缓冲伸缩臂和第二缓冲伸缩臂的作用下可以实现伸缩，进而调节了空化器主体和空化器盘面伸缩片所组成的空化器的外径的大小，可以根据需要实施调节空化器的有效面积，空化器尺寸越大，越能生成更大直径的超空泡，可以保持航行体水下实时被超空泡完全包裹，降低其航行阻力。
2、本发明采用的空化器主体为双层结构，每层上都设有空化器盘面伸缩片，多个空化器盘面伸缩片伸出时能够组成一个完整的圆。
3、本发明采用了多级降载，航行体入水前第二喷气口喷气降载、第三喷气口喷气降载、第一喷气口喷气降载，入水过程中第一伸缩臂和第二伸缩臂能够起到阻尼降载，同时阻尼器也会起到阻尼降载。
4、第三喷气口的喷气有利于形成更大的超空泡。
5、本发明中的气体加速孔采用的是特斯拉阀孔结构，能够解决气体进入后进行自动加速，特斯拉阀孔为不断重复的链式结构，结构重复的次数越多，加速效果越好，也就是说重复的单一结构尺寸越小降压效果越好。利用特斯拉阀孔对气体加速的方向性功能可以在不消耗能源的基础上实现加速。
基于上述理由本发明可在航行体入水等领域广泛推广。
附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图做以简单地介绍，显而易见地，下面描述中的附图是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1为本发明具体实施方式中一种可调制的双层伸缩片空化器结构三维视图。
图2为本发明具体实施方式中一种可调制的双层伸缩片空化器结构主视图。
图3为图2中A-A向剖视图。
图4为本发明具体实施方式中空化器主体结构示意图。
图5为本发明具体实施方式中空化器主体侧视图。
图6为本发明具体实施方式中空化器盘面伸缩片结构示意图。
图7为本发明具体实施方式中空化器盘面伸缩片收缩时示意图。
图8为本发明具体实施方式中空化器盘面伸缩片伸出时示意图。
图9为本发明具体实施方式中阻尼器、第一通气管路系统示意图。
图10为本发明具体实施方式中气体加速孔结构示意图。
图11为本发明具体实施方式中第二缓冲伸缩臂结构示意图。
图12为本发明具体实施方式中头部整流罩装置结构示意图。
图13为本发明具体实施方式中连接装置结构示意图(分离时)。
图14为本发明具体实施方式中尾气回收系统结构示意图。
图15为本发明具体实施方式中航行体入水前示意图。
图16为本发明具体实施方式中航行体靠近水面头部整流罩脱离，第二喷气口喷气示意图。
图17为本发明具体实施方式中航行体靠近水面第二喷气口脱离示意图。
图18为本发明具体实施方式中航行体靠近水面第一喷气口喷气示意图。
图19为本发明具体实施方式中航行体靠近水面第一喷气口和第三喷气口同时喷气示意图。
图20为本发明具体实施方式中航行体入水后超空泡下行驶示意图。
图中：1、航行体；2、空化器；201、空化器主体；202、空化器盘面伸缩片；203、凹槽；204、滑动U形限位槽；205、滑动限位凸起；3、阻尼器；301、储油腔；302、第一外套筒；303、第一活塞杆；304、第一活塞；305、拉弹簧；306、第一液压油腔体；4、头部整流罩装置；401、头部整流罩；402、第二喷气口；403、连接管；404、梯形固定插销；405、第二压弹簧；406、电磁铁；407、整流罩固定杆；408、连接凹槽；409、卡槽；410、连接件；411、第二通气管；5、缓冲驱动机构；501、翼型调节片；502、侧部整流罩；503、第一缓冲伸缩臂；504、第二缓冲伸缩臂；505、第二外套筒；506、第二活塞杆；507、第二活塞；508、第三压弹簧；509、第二液压油腔体；6、储气装置；601、第一喷气口；602、第一通气管；603、第一通气阀门；604、第一压弹簧；605、通孔。7、气体加速孔；701、第三喷气口；702、软管；703、第三通气阀门；8尾气收集装置；801、涡轮吸气驱动装置；802、第二通气阀门；803、汇集管路；804、涡轮吸气装置保护罩；9、助推发动机。
具体实施方式
需要说明的是，在不冲突的情况下，本发明中的实施例及实施例中的特征可以相互组合。下面将参考附图并结合实施例来详细说明本发明。
为使本发明实施例的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。以下对至少一个示例性实施例的描述实际上仅仅是说明性的，决不作为对本发明及其应用或使用的任何限制。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
需要注意的是，这里所使用的术语仅是为了描述具体实施方式，而非意图限制根据本发明的示例性实施方式。如在这里所使用的，除非上下文另外明确指出，否则单数形式也意图包括复数形式，此外，还应当理解的是，当在本说明书中使用术语“包含”和/或“包括”时，其指明存在特征、步骤、操作、器件、组件和/或它们的组合。
除非另外具体说明，否则在这些实施例中阐述的部件和步骤的相对布置、数字表达式和数值不限制本发明的范围。同时，应当清楚，为了便于描述，附图中所示出的各个部分的尺寸并不是按照实际的比例关系绘制的。对于相关领域普通技术人员己知的技术、方法和设备可能不作详细讨论，但在适当情况下，所述技术、方法和设备应当被视为授权说明书的一部分。在这里示出和讨论的所有示例中，任向具体值应被解释为仅仅是示例性的，而不是作为限制。因此，示例性实施例的其它示例可以具有不同的值。应注意到：相似的标号和字母在下面的附图中表示类似项，因此，一旦某一项在一个附图中被定义，则在随后的附图中不需要对其进行进一步讨论。
在本发明的描述中，需要理解的是，方位词如“前、后、上、下、左、右”、“横向、竖向、垂直、水平”和“顶、底”等所指示的方位或位置关系通常是基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，在未作相反说明的情况下，这些方位词并不指示和暗示所指的装置或元件必须具有特定的方位或者以特定的方位构造和操作，因此不能理解为对本发明保护范围的限制：方位词“内、外”是指相对于各部件本身的轮廓的 内外。
为了便于描述，在这里可以使用空间相对术语，如“在……之上”、“在……上方”、“在……上表面”、“上面的”等，用来描述如在图中所示的一个器件或特征与其他器件或特征的空间位置关系。应当理解的是，空间相对术语旨在包含除了器件在图中所描述的方位之外的在使用或操作中的不同方位。例如，如果附图中的器件被倒置，则描述为“在其他器件或构造上方”或“在其他器件或构造之上”的器件之后将被定位为“在其他器件或构造下方”或“在其位器件或构造之下”。因而，示例性术语“在……上方”可以包括“在……上方”和“在……下方”两种方位。该器件也可以其他不同方式定位(旋转90度或处于其他方位)，并且对这里所使用的空间相对描述作出相应解释。
此外，需要说明的是，使用“第一”、“第二”等词语来限定零部件，仅仅是为了便于对相应零部件进行区别，如没有另行声明，上述词语并没有特殊含义，因此不能理解为对本发明保护范围的限制。
如图1～20所示，一种可调制的双层伸缩片空化器结构，包括设置在航行体1的头端的空化器2，空化器2包括空化器主体201，空化器主体201的中心通过阻尼器3与航行体1的头部中心连接，空化器主体201的前端可分离连接有头部整流罩装置4，空化器主体201为双层结构，包括第一层和第二层(如图5所示)，第一层和第二层上均安装有多个空化器盘面伸缩片202，多个空化器盘面伸缩片202围绕空化器主体201的轴线均匀分布，并与其所对应的第一层或第二层滑动连接，航行体1的头端安装有驱动空化器盘面伸缩片202沿空化器主体201的径向方向滑动的缓冲驱动机构5，多个空化器盘面伸缩片202和空化器主体201拼成一个圆(如图7和8所示)。
空化器盘面伸缩片202呈扇形，其内部加工有凹槽203(如图6所示)，凹槽203包裹第一层或第二层(即第一层或第二层插入凹槽203内)，第一层和第二层上均加工有呈径向延伸的滑动U形限位槽204(如图4所示)，空化器盘面伸缩片202上加工有与滑动U形限位槽204相配合的滑动限位凸起205，设置在第一层上的多个空化器盘面伸缩片202与设置在第二层上的多个空化器盘面伸缩片202交错设置。
如图7～9所示，缓冲驱动机构5包括多个翼型调节片501，翼型调节片501的数量与空化器盘面伸缩片202的数量相匹配，且围绕空化器主体201的轴线均匀分布，每个翼型调节片501相对一个空化器盘面伸缩片202；翼型调节片501的后端通过安装在航行体1的头端外沿上的侧部整流罩502与航行体1的头端外沿铰接(即呈圆筒形的侧部整流罩502与航行体1的头端连接，翼型调节片501的后端与侧部整流罩502的前端铰接)，且侧部整流罩502与航行体1通过电磁铁吸附连接；翼型调节片501在其靠近后端的一侧与第一缓冲伸缩臂503的一端铰接，在其靠近前端的一侧与第二缓冲伸缩臂504的一端铰接，且第一缓冲伸缩臂503的另一端与航行体1的外周铰接，第二缓冲伸缩臂504的另一端与空化器盘面伸缩片202的上部固定连接，第一缓冲伸缩臂503和第二缓冲伸缩臂504均为倾斜设置，翼型调节片501的截面呈翼型，相临两个翼型调节片501紧密贴合；翼型调节片501的3/2的剖面为较薄的流线型形状，3/1的剖面为厚翼型剖面，这样设计的目的在于相邻的翼型调节片501能够紧密地贴合在一起，最大程度减小间隙，使安装头部整流罩装置4后的航行体1整个外形达到最佳的流线型。翼型调节片501沿着径向向内收缩时，较厚的一端可以顺畅地滑动到相邻翼型调节片501较薄的一端内侧，使整体能够保持较好的外形不突兀。
如图11所示，本实施例中的第一缓冲伸缩臂503和第二缓冲伸缩臂504的结构相同均为液压式伸缩杆式，其包括：第二外套筒505，第二外套筒505内设有穿出第二外套筒505的第二活塞杆506，且第二活塞杆506在第二外套筒505内的一端具有与第二外套筒505相配合的第二活塞507，第二外套筒505位于第二活塞507两侧的部分分别具有第二液压油腔体509和第三压弹簧508，第三压弹簧508位于靠近第二活塞杆506穿出第二外套筒505的一端，第二外套筒505内具有储油腔，且储油腔与第二液压油腔体509连通。通过航行体1内部的中控装置，第二外套筒505的储油腔内的液压油进入第二液压油腔体509内，推动第二活塞杆506伸长，此时第三压弹簧508被压缩，反之，第二液压油腔体509内的液压油回到第二外套筒505内，在气压和第三压弹簧的作用下第二活塞杆506收缩。通过调整第一缓冲伸缩臂503和第二缓冲伸缩臂504可以实现空化器盘面伸缩片202的径向滑动，滑出则为空化器2扩大面积，滑入则为空化器2缩小面积。
因为整个调节过程中，由于第一缓冲伸缩臂503和第二缓冲伸缩臂504是斜向连接翼型调节片501和空化器盘面伸缩片202，传递的力也是斜向力，导致传递过程有一个较大的沿着入水方向(图14中为左右方向)的分力(使伸缩片30滑动的力沿着空化器圆盘径向，与这个分力方向垂直)，分力会向右(入水方向)挤压空化器盘面伸缩片202，使其挤压撞击空化器主体201，过快的撞击可能会导致U形限位槽204和滑动限位凸起205受损失去调节空化器尺寸的功能。因此具体实施方式中采用了液压式，液压式是对运动的传递有显著的缓冲作用的，使得缓冲驱动机构5运动的传递更加平缓，延长了装置的寿命。
如图9和10所示，翼型调节片501内设有气体加速孔7，气体加速孔7为特斯拉阀孔，气体加速孔7的前端与设置在翼型调节片501前端的第三喷气口701连通，气体加速孔7的后端通过软管702和第三通气阀门703与设置在航行体1内的储气装置6连通。在翼型调节片501的翼缘最宽处加工有贯通式的圆柱通道，翼型调节片501连同铰链连接结构均为高强度合金制作，贯通式的圆柱通道内用胶粘固连的方式插入一根圆柱形空心柱，柱内为气体加速孔702，该空心圆柱为树脂基的复合材料用模具制作而成。第三喷气口701喷出的气体既可以用来缓冲降载也可以用来形成更大的空气泡，有利于大空气泡的形成。
如图14所示，航行体1的尾部安装有助推发动机9，且航行体1内安装有尾气收集装置8，尾气收集装置8包括涡轮吸气驱动装置801，涡轮吸气驱动装置801位于涡轮吸气装置保护罩804内，涡轮吸气驱动装置801的一端通过管路和助推发动机9的排气端连通，涡轮吸气驱动装置801的另一端与储气装置6的入口连通。可以采用多个尾气回收装置8，且每个尾气回收装置8中设有多个串联的涡轮吸气驱动装置801，且每个尾气回收装置8均配备一个储气装置6，多个储气装置6的出气端通过第二通气阀门802汇集到汇集管路803。本发明所述涡轮吸气驱动装置包括涡轮风扇，通过驱动涡轮风扇旋转吸收尾气。
如图9所示，空化器主体201的前端中心设有第一喷气口601，储气装置6和第一喷气口601通过第一通气管路系统连通。
阻尼器3包括第一外套筒302，第一外套筒302内设有储油腔301，第一 外套筒302内设有第一活塞杆303，第一活塞杆303的前端穿出第一外套筒302与空化器主体201固定连接，第一活塞杆303的后端具有第一活塞304，第一活塞304与第一外套筒302前端之间的部分设有套在第一活塞杆303上的拉弹簧305，第一外套筒302的后端与航行体1的头端固定连接，第一外套筒302的后端与第一活塞304之间的部分形成第一液压油腔体306，且第一液压油腔体306与储油腔连通。
第一通气管路系统包括第一通气管602，第一通气管602的后端与储气装置6连通，第一通气管602内设有第一通气阀门603，第一通气管602的前端依次穿过第一外套筒302的后端中心、第一活塞304的中心，并穿入第一活塞杆303内，第一通气管602与第一外套筒302密封连接，且与第一活塞杆303和第一活塞304的内壁气密式滑动连接，第三活塞杆303靠近其前端的内部具有缓冲气腔，缓冲气腔的后端与第一通气管602的前端连通，缓冲气腔内设有轴线与第一活塞杆303轴线重合的第一压弹簧604，第一通气管602的端面与第一压弹簧604相抵，第一活塞杆303的前端设有与缓冲气腔连通的通孔605，通孔605的前端与第一喷气口601连通。
如图12和13所示，头部整流罩装置4包括头部整流罩401和连接装置，头部整流罩401与连接装置的前端可分离连接，头部整流罩401呈锥型或尖拱型，头部整流罩401是由多瓣壳体组成，相邻两瓣壳体之间通过连接结构连接；连接结构处设有爆破装置，航行体1内设有引爆爆破装置的引爆装置，引爆装置引爆爆破装置后，整流罩沿相邻两瓣壳体之间的连接结构处分离。连接结构为“弱结构”，可以为强力胶，将相邻两瓣壳体粘结在一起，可以为薄板，与相邻两瓣壳体固定连接，即确保具有一定的强度，能够承受空气中高速飞行时的空气阻力，保持气密性，不会变形或者破坏；同时，可以被实现安装在内侧的线爆结构爆破分解，使得合金制作的头部整流罩401分离。连接装置的后端与空化器主体201的中心可分离连接。连接装置包括固定在第一喷气口601前端的连接管403，连接管403的中部上下对称加工有插销安装孔，两个插销安装孔内分别安装有呈梯形的梯形固定插销404，且两个梯形固定插销404通过第二压弹簧405连接，梯形固定插销404靠近连接管403轴线的一侧固定有电磁铁406；整流罩固定杆407的后端具有与连接管403相匹配的连接凹槽408，且连接凹槽408的槽壁上加工有与梯形固定插销 404相配合的卡槽409；整流罩固定杆407的前端固定有连接件410，连接件410与头部整流罩401的后端内壁固定连接。整流罩固定杆407内设有第二通气管411，第二通气管411的后端与连接凹槽408连通，且第二通气管411的前端与第二喷气口402连通。连接管403的前端插入连接凹槽408内时，梯形固定插销404在第二压弹簧405的作用下顶进卡槽409内，实现连接管403和整流罩固定杆407的可靠连接。当想让整流罩固定杆407与连接管403脱离时，电磁铁406工作，将两个梯形固定插销404吸附，使其外沿面低于或与连接管403的外沿面重合，此时梯形固定插销404与卡槽409不发生限位配合。打开第一通气阀门603，高压气体将整流罩固定杆407和连接件410吹走，实现整流罩固定杆407和连接件410与空化器主体201的分离。
使用状态下：
如图15，当航行体1首先在空中飞行一段距离，此时为了降低飞行阻力，通过第一缓冲伸缩臂503和第二缓冲伸缩臂504使空化器盘面伸缩片202沿径向向内收缩，而翼型调节片501靠近头部整流罩401的一侧向内收缩，这样使得整体呈现较好的流线型，降低飞行风阻(如图7)。
如图16，当传感器检测到航行体1距离水面一定的距离时，控制头部整流罩401分解，控制打开第二通气阀门802和第一通气阀门603，此时储存在储气装置6内的高压气体支撑架第二喷气口402喷出，喷向水面对航行体1实施第一次反向喷气，进行降速实现降载目的。
如图17所示，当航行体1进一步接近水面，实施整流罩固定杆407及连接件与空化器主体201的分离。
如图18所示，整流罩固定杆407及连接件与空化器主体201分离后仍实施高压气体从第一喷气口601向水面喷出，实现对入水航行体1的第二次反向喷气减速降载。
如图19所示，在空化器2撞水之前通过调节第一缓冲伸缩臂503和第二缓冲伸缩臂504，带动翼型调节片501、空化器盘面伸缩片202向外扩展，达到对空化器2尺寸的展开目的(如图8)。展开的同时打开通气第三通气阀门703，使储气装置6里的高压空气通过软管702进入气体加速孔7中加速，被加速后从第三喷气701喷出，实现对入水航行体1的第三次反向喷气减速降载。
如图20所示，航行体1触水后第一缓冲伸缩臂503和第二缓冲伸缩臂504能够进行阻尼缓冲，同时阻尼器3也能起到缓冲的效果。航行体1入水后进行超空泡航行。在超空泡航行过程中，空化器2的尺寸可以根据需要进行调节。
最后应说明的是：以上各实施例仅用以说明本发明的技术方案，而非对其限制；尽管参照前述各实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分或者全部技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的范围。

Claims (10)

  1. 一种可调制的双层伸缩片空化器结构，包括设置在航行体的头端的空化器，所述空化器包括空化器主体，所述空化器主体的中心通过阻尼器与所述航行体的头部中心连接，所述空化器主体的前端可分离连接有头部整流罩装置，其特征在于，所述空化器主体为双层结构，包括第一层和第二层，所述第一层和所述第二层上均安装有多个空化器盘面伸缩片，多个所述空化器盘面伸缩片围绕所述空化器主体的轴线均匀分布，并与其所对应的所述第一层或所述第二层滑动连接，所述航行体的头端安装有驱动所述空化器盘面伸缩片沿所述空化器主体的径向方向滑动的缓冲驱动机构，多个所述空化器盘面伸缩片和所述空化器主体拼成一个圆。
  2. 根据权利要求1所述的一种可调制的双层伸缩片空化器结构，其特征在于，所述空化器盘面伸缩片呈扇形，其内部加工有凹槽，所述凹槽包裹所述第一层或所述第二层，所述第一层和所述第二层上均加工有呈径向延伸的滑动U形限位槽，所述空化器盘面伸缩片上加工有与所述滑动U形限位槽相配合的滑动限位凸起，设置在所述第一层上的多个所述空化器盘面伸缩片与设置在所述第二层上的多个所述空化器盘面伸缩片交错设置。
  3. 根据权利要求1所述的一种可调制的双层伸缩片空化器结构，其特征在于，所述缓冲驱动机构包括多个翼型调节片，所述翼型调节片的数量与所述空化器盘面伸缩片的数量相匹配，且围绕所述空化器主体的轴线均匀分布，每个所述翼型调节片相对一个所述空化器盘面伸缩片，所述翼型调节片的后端与所述航行体的头端外沿铰接，所述翼型调节片在其靠近后端的一侧与第一缓冲伸缩臂的一端铰接，在其靠近前端的一侧与第二缓冲伸缩臂的一端铰接，且所述第一缓冲伸缩臂的另一端与所述航行体的头端的前端面铰接，所述第二缓冲伸缩臂的另一端与空化器盘面伸缩片的上部固定连接，所述翼型调节片的截面呈翼型，相临两个所述翼型调节片紧密贴合。
  4. 根据权利要求3所述的一种可调制的双层伸缩片空化器结构，其特征在于，所述翼型调节片内设有气体加速孔，所述气体加速孔为特斯拉阀孔，所述气体加速孔的前端与设置在所述翼型调节片前端的第三喷气口连通，所述气体加速孔的后端通过软管和第三通气阀门与设置在所述航行体内的储气装置连通。
  5. 根据权利要求4所述的一种可调制的双层伸缩片空化器结构，其特征在于，所述航行体的尾部安装有助推发动机，且所述航行体内安装有尾气收集装置，所述尾气收集装置包括涡轮吸气驱动装置，所述涡轮吸气驱动装置的一端通过管路和所述助推发动机的排气端连通，所述涡轮吸气驱动装置的另一端与所述储气装置的入口连通。
  6. 根据权利要求4或5所述的一种可调制的双层伸缩片空化器结构，其特征在于，所述空化器主体的前端中心设有第一喷气口，所述储气装置和所述第一喷气口通过第一通气管路系统连通。
  7. 根据权利要求6所述的一种可调制的双层伸缩片空化器结构，其特征在于，所述阻尼器包括第一外套筒，所述第一外套筒内设有储油腔，所述第一外套筒内设有第一活塞杆，所述第一活塞杆的前端穿出所述第一外套筒与所述空化器主体固定连接，所述第一活塞杆的后端具有第一活塞，所述第一活塞与所述第一外套筒前端之间的部分设有套在所述第一活塞杆上的拉弹簧，所述第一外套筒的后端与所述航行体的头端固定连接，所述第一外套筒的后端与所述第一活塞之间的部分形成第一液压油腔体，且所述第一液压油腔体与所述储油腔连通。
  8. 根据权利要求7所述的一种可调制的双层伸缩片空化器结构，其特征在于，所述第一通气管路系统包括第一通气管，所述第一通气管的后端与所述储气装置连通，所述第一通气管内设有第一通气阀门，所述第一通气管的前端依次穿过所述第一外套筒的后端中心、第一活塞的中心，并穿入所述第一活塞杆内，且与所述第一活塞杆和所述第一活塞的内壁气密式滑动连接，所述第三活塞杆靠近其前端的内部具有缓冲气腔，所述缓冲气腔的后端与第一通气管的前端连通，所述缓冲气腔内设有轴线与所述第一活塞杆轴线重合的第一压弹簧，所述第一通气管的端面与第一压弹簧相抵，所述第一活塞杆的前端设有与所述缓冲气腔连通的通孔，所述通孔的前端与所述第一喷气口连通。
  9. 根据权利要求6所述的一种可调制的双层伸缩片空化器结构，其特征在于，所述头部整流罩装置包括头部整流罩和连接装置，所述头部整流罩与所述连接装置的前端可分离连接，所述连接装置的后端与所述空化器主体的中心可分离连接，所述连接装置的头端设有第二喷气口，所述第二喷气口 与所述第一喷气口连通。
  10. 根据权利要求9所述的一种可调制的双层伸缩片空化器结构，其特征在于，所述连接装置包括固定在所述第一喷气口前端的连接管，所述连接管的中部上下对称加工有插销安装孔，两个所述插销安装孔内分别安装有呈梯形的梯形固定插销，且两个所述梯形固定插销通过第二压弹簧连接，所述梯形固定插销靠近所述连接管轴线的一侧固定有电磁铁；
    整流罩固定杆的后端具有与所述连接管相匹配的连接凹槽，且所述连接凹槽的槽壁上加工有与所述梯形固定插销相配合的卡槽；
    所述整流罩固定杆的前端固定有连接件，所述连接件与所述头部整流罩的后端内壁固定连接；
    所述整流罩固定杆内设有第二通气管，所述第二通气口设置在所述整流罩固定杆的前端，且所述第二通气管的前端与所述第二通气口连通，后端与所述连接凹槽连通。
PCT/CN2022/127981 2021-10-29 2022-10-27 一种可调制的双层伸缩片空化器结构 Ceased WO2023072201A1 (zh)

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