CN112413040A - Pneumatic damping type load reducing device for large-angle inclined water entering of navigation body - Google Patents

Pneumatic damping type load reducing device for large-angle inclined water entering of navigation body Download PDF

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Publication number
CN112413040A
CN112413040A CN202011306013.3A CN202011306013A CN112413040A CN 112413040 A CN112413040 A CN 112413040A CN 202011306013 A CN202011306013 A CN 202011306013A CN 112413040 A CN112413040 A CN 112413040A
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CN
China
Prior art keywords
head
fairing
wall
tail
pneumatic damping
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Granted
Application number
CN202011306013.3A
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Chinese (zh)
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CN112413040B (en
Inventor
李尧
宗智
孙铁志
张宝剑
李海涛
史崇镔
王世晟
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Dalian University of Technology
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Dalian University of Technology
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Publication of CN112413040A publication Critical patent/CN112413040A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/022—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using dampers and springs in combination
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63C—LAUNCHING, HAULING-OUT, OR DRY-DOCKING OF VESSELS; LIFE-SAVING IN WATER; EQUIPMENT FOR DWELLING OR WORKING UNDER WATER; MEANS FOR SALVAGING OR SEARCHING FOR UNDERWATER OBJECTS
    • B63C3/00—Launching or hauling-out by landborne slipways; Slipways
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B1/00—Devices for securing together, or preventing relative movement between, constructional elements or machine parts
    • F16B1/02—Means for securing elements of mechanisms after operation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/023—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/023—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means
    • F16F15/0232—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means with at least one gas spring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
    • F16F15/046—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means using combinations of springs of different kinds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
    • F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
    • F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
    • F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
    • F16F15/085—Use of both rubber and metal springs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B19/00—Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B2200/00—Constructional details of connections not covered for in other groups of this subclass
    • F16B2200/83—Use of a magnetic material

Abstract

The invention provides a pneumatic damping type load-reducing device for a large-angle inclined water inlet of a navigation body, which comprises a fairing, wherein the fairing is installed at the head of a main projectile body and is detachably connected with the head of the main projectile body, a cavitator is arranged in the main projectile body, a pneumatic damping device which is overlapped with the axis of the fairing is arranged between the cavitator and the main projectile body, and a plurality of lateral hydraulic dampers are arranged between the pneumatic damping device and the inner wall of the fairing. When the main projectile body falls from high altitude and touches water, the fairing can be disintegrated and broken due to impact load, a part of energy can be absorbed, and fragments are separated from the device. The pneumatic damping device mainly absorbs the normal impact energy from the front of the water surface, the side hydraulic damper can absorb most of the impact energy of the water surface on the side surface of the fairing, and the pneumatic damping device is particularly suitable for the water entering working condition of a navigation body with a large inclination angle and an attack angle gesture.

Description

Pneumatic damping type load reducing device for large-angle inclined water entering of navigation body
Technical Field
The invention relates to the technical field of large-angle water entry of a navigation body, in particular to a load reduction device for buffering in a mode of combining pneumatic damping type load reduction and physical foam type load reduction, and particularly relates to a pneumatic damping type load reduction device for large-angle inclined water entry of a navigation body.
Background
Modern wars require that an underwater vehicle has an excellent anti-detection function, the most direct is to avoid the tracking of detection equipment such as radars, and the adoption of a more flexible air-jet mode to launch underwater weapons becomes a trend, and the capture characteristic of the underwater weapons is verified. However, the high-altitude shooting mode can cause huge impact pressure at the moment of the water touch of the navigation body, and the slamming action is likely to shake out instruments installed inside the head of the navigation body if the slamming action is not taken into account. This impact load increases rapidly as the water contact velocity, the mass of the projectile, increases. Therefore, it is necessary to take measures to reduce the impact load of the head in order to protect the internal structure of the navigation body, reducing the risk of instrument failure due to overloads and vibrations.
Disclosure of Invention
The invention aims to provide a buffering and vibration damping device, which solves the problem of instantaneous overload of the head of a navigation body under the working condition of medium-high speed water entry and adopts a pneumatic damping device to realize flexible load reduction on the front surface and the side surface of a projectile body. Most of air-launched torpedoes or navigation bodies firstly touch water on the side face of the fairing at the moment of water touch, the previous vibration reduction and load reduction devices mostly pay attention to positive load reduction, and the working condition that large-angle side faces enter water at high speed is seldom paid attention to. The invention is specially designed for the problem of large-angle inclined water inlet, and multi-directional load reduction of the main projectile body is realized through the side hydraulic damper.
The technical means adopted by the invention are as follows:
a pneumatic damping type load reducing device for a navigation body inclined into water at a large angle comprises:
the head of the fairing is sealed and is in a pointed arch shape, the inner wall of the tail end of the fairing is detachably connected with the outer wall of the head of the main projectile body, and the fairing is made of fragile ceramic matrix composite materials;
the cavitator is of a disc type structure, the axis of the cavitator is superposed with the axis of the fairing, is arranged in the head of the fairing and is in contact connection with the inner wall of the head of the fairing;
the aerodynamic damping device is arranged in the fairing, is positioned between the cavitator and the main elastic body, and has an axis coincident with that of the fairing;
the plurality of side hydraulic dampers are distributed around the axis of the pneumatic damping device, one end of each side hydraulic damper is connected with the pneumatic damping device through an installation mechanism, and the other end of each side hydraulic damper is connected with the inner wall of the fairing;
the metal-based foam layer is arranged in the fairing, the tail end face of the metal-based foam layer is in contact connection with the head end face of the cavitator, a deformation cavity is arranged between the head end face of the metal-based foam layer and the head of the fairing, and the side wall of the metal-based foam layer is matched with and in contact connection with the inner wall of the fairing;
a polyurethane foam layer arranged between the fairing and the side hydraulic damper, wherein one end of the side hydraulic damper, which is far away from the pneumatic damping device, is fixedly connected with the polyurethane foam layer, the polyurethane foam layer is in contact connection with the inner wall of the fairing, and the polyurethane foam layer has a density of 200-300kg/m3The rigid polyurethane foam of (1).
The pneumatic damping device comprises:
the mounting seat is arranged in the tail part of the fairing and is in contact connection with the head end face of the main projectile body;
sealing the pressure cylinder;
the air cavity external protection cylinder is sleeved outside the sealing pressure cylinder and fixedly connected with the sealing pressure cylinder, and the tail end of the air cavity external protection cylinder is fixedly connected with the mounting seat;
the piston is arranged in the sealing pressure cylinder and is matched with the sealing pressure cylinder;
the tail part of the piston rod penetrates into the sealed pressure cylinder and is fixedly connected with the piston, and the head part of the piston rod is hinged with the cavitator through a ball head;
the tension spring is sleeved on the piston rod, the tail end of the tension spring is fixedly connected with the head end face of the piston, and the head end of the tension spring is fixedly connected with the head end face of the sealing pressure cylinder;
the air cavity is a cavity between the piston and the tail part of the sealing pressure cylinder;
the buffer gas is filled in the air cavity; the buffer gas is high-pressure inert gas;
the mounting mechanism includes:
the hinge seat is fixed on the outer wall of the tail part of the protection cylinder outside the air cavity;
one end of the hinge column is hinged with the hinge seat through a hinge shaft matched with the hinge seat; the hinge post is made of high-strength alloy;
the gas spray pipe is arranged in the hinge column and is made of high-pressure-resistant and high-strength plastic materials;
one end of the vent pipe is communicated with the air cavity through a pneumatic valve, and the other end of the vent pipe is communicated with one end of the gas spray pipe close to the hinge seat;
the mounting groove is processed the side hydraulic damper is close to the one end of hinge post, and with the hinge post phase-match, the hinge post is installed in the mounting groove, and with the mounting groove contact is connected.
The stop surface is obliquely arranged at the rear part of the protection cylinder outside the air cavity;
the damper external sleeve is sleeved outside the air cavity external protection cylinder and is in sliding fit with the air cavity external protection cylinder, and the tail part of the damper external sleeve is provided with an external impact stop block matched with the stop surface;
and the damper protection corrugated dustproof sleeve is arranged on the outer wall of the outer sleeve of the damper.
The corrugated dirt proof boot is protected to attenuator includes:
the head structure is divided into four sections which are sequentially connected and respectively comprise a sealing section, a head section, a middle section and a tail section, the extending direction of the sealing section is perpendicular to the axis direction of the pneumatic damping device, one end of the sealing section is fixedly connected with the outer wall of the piston rod, and the other end of the sealing section is fixedly connected with the head end of the head section; the outer wall of the head section extends from the head part of the head section to the tail part of the head section in the axial direction far away from the pneumatic damping device; the outer wall of the middle section extends from the tail part of the head section to the tail part of the middle section in the axial direction close to the pneumatic damping device; the outer wall of the tail section extends from the tail part of the middle section to the tail part of the tail section in the direction parallel to the axis of the pneumatic damping device;
the head end of the corrugated pipe is fixedly connected with the outer wall of the tail section, and the tail end of the corrugated pipe is fixedly connected with the tail end of the sleeve outside the damping block;
and one end of the connecting sheet is fixedly connected with the tail part of the middle section, and the other end of the connecting sheet is bent to extend towards the tail part of the middle section after extending towards the tail section direction and is fixedly connected with the head part of the outer sleeve of the damper.
The damper protection corrugated dustproof sleeve is internally provided with a rubber anti-collision block, the inner wall of the rubber anti-collision block is fixedly connected with the outer wall of the piston rod, and the head end of the rubber anti-collision block is fixedly connected with the sealing section.
The tail of the fairing is detachably connected with the outer wall of the head of the main projectile body through a connecting mechanism.
The connecting mechanism includes:
the metal sheets are distributed around the axis of the main elastic body, one end of each metal sheet is fixedly connected with the tail end of the fairing, the other end of each metal sheet extends towards the head end of the fairing and then returns to the tail end of the fairing to extend, the metal sheets penetrate into metal sheet clamping grooves in the outer wall of the main elastic body to be processed, then arc bending occurs, and the end portions of the metal sheets are in contact connection with the outer wall of the main elastic body.
And the electromagnet is arranged in the head of the main projectile body and used for adsorbing the mounting seat.
A rubber soft pad is arranged between the mounting seat and the main elastic body. The mounting seat is made of a material which can be absorbed by electromagnetism.
Compared with the prior art, the invention has the following advantages:
the invention provides a pneumatic damping type buffering vibration damper with a fairing, which is used for head load reduction in the process of aerial delivery of a navigation body or medium-high speed launching of the navigation body into water and can be suitable for buffering load reduction of vertical or large-angle inclined water entering of the navigation body from 20m/s to 100 m/s. The device structure is comparatively simple, is convenient for implement and installation, and the material easily acquires and processes, and according to operating condition needs, the adjustable or different dampers of reloading realize the purpose of carrying that falls of different degrees. The side hydraulic damper can rotate around the hinge seat by different angles.
The front end of the main projectile body is additionally provided with the electromagnet, and the gas damping device is connected with the head of the main projectile body through the electromagnet, so that impact vibration caused by rigid connection is avoided. A metal-based foam layer is additionally arranged between the cavitator and the fairing. The fairing is made of ceramic-based fragile composite materials, and the end part of the fairing is connected with the navigation body in a metal sheet bolt mode. The device has high reliability and low cost, can effectively reduce the load after entering water, the front end cavitator of the damping device is favorable for forming cavitation bubbles after entering water after the hood is broken, and the supercavitation generated in the underwater medium-high speed navigation process is proved to be capable of obviously reducing the navigation body resistance and simultaneously is favorable for keeping the course stability of underwater navigation.
When the navigation body (main projectile body) falls from high altitude and touches water, the fairing made of the ceramic matrix composite material can be disintegrated and broken due to impact load, a part of energy can be absorbed, and fragments are separated from the device. The water pressure transmitted by the fairing quickly crushes the metal-based foam layer and then transmits the pressure to the cavitator, so that most impact energy is absorbed by the device. When the impact occurs, the sealing pressure cylinder and the piston move relatively, the buffer gas and the tension spring buffer the piston, the side hydraulic damper buffers simultaneously, the buffer gas is extruded into the gas jet pipe and ejects the side hydraulic damper, and after the electromagnet is powered off, the cavitator and the pneumatic damping device are separated from the main elastic body.
The pneumatic damping device mainly absorbs the front normal impact energy from the water surface, the side hydraulic damper can absorb most of the impact energy of the water surface on the side surface of the fairing, and the pneumatic damping device is particularly suitable for the water entering working condition of the navigation body with large inclination angle and attack angle posture
Based on the reasons, the invention can be widely popularized in the fields of research on the water entry of the aircraft and the like.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic structural view of a pneumatic damping type load shedding device for a navigation body which is inclined into water at a large angle in an embodiment of the invention.
Fig. 2 is a sectional view taken along line a-a in fig. 1.
FIG. 3 is an enlarged view of the fairing.
FIG. 4 is a schematic structural diagram of a gas damping device according to an embodiment of the present invention.
FIG. 5 is a schematic view of a mounting mechanism according to an embodiment of the present invention.
Fig. 6 is a schematic structural diagram of a connection mechanism according to an embodiment of the present invention.
FIG. 7 is a side hydraulic damper profile of an embodiment of the present invention.
Fig. 8 is a water inlet diagram of the pneumatic damping load-reducing device for the large-angle inclined water inlet of the navigation body according to the embodiment of the invention.
FIG. 9 is a schematic illustration of the side hydraulic damper release in accordance with an embodiment of the present invention.
In the figure: 1. a cowling; 2. a main projectile body; 3. a cavitator; 4. a pneumatic damping device; 401. a mounting seat; 402. sealing the pressure cylinder; 403. an air cavity external protection cylinder; 404. a piston; 405. a piston rod; 406. a ball head; 407. a tension spring; 408. an air cavity; 409. a stop surface; 410. a damper outer sleeve; 411. an external impact stop; 412. the damper protects the corrugated dustproof sleeve; 413. a sealing section; 414. a head section; 415. a middle section; 416. a tail section; 417. a bellows; 418. connecting sheets; 419. a rubber anti-collision block; 5. a side hydraulic damper; 6. an installation mechanism; 601. a hinged seat; 602. a hinged column; 603. hinging a shaft; 604. a gas nozzle; 605. a breather pipe; 7. a metal-based foam layer; 701. a deformable cavity; 8. a polyurethane foam layer; 9. an electromagnet; 10. a connecting mechanism; 1001. a metal sheet; 1002. a metal sheet clamping groove.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the invention. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. Any specific values in all examples shown and discussed herein are to be construed as exemplary only and not as limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are used for convenience of description and simplicity of description only, and in the absence of any contrary indication, these directional terms are not intended to indicate and imply that the device or element so referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore should not be considered as limiting the scope of the present invention: the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship 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 of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of the present invention should not be construed as being limited.
As shown in fig. 1 to 9, a pneumatic damping type load-reducing device for a navigation body inclined into water at a large angle comprises:
the head of the fairing 1 is sealed and is in a pointed arch shape, the inner wall of the tail end of the fairing is detachably connected with the outer wall of the head of the main projectile body 2, and the fairing 1 is made of fragile ceramic matrix composite materials;
the cavitator 3 is of a disc type structure, the axis of the cavitator coincides with the axis of the fairing 1, is arranged in the head of the fairing 1 and is in contact connection with the inner wall of the head of the fairing 1;
the pneumatic damping device 4 is arranged in the fairing 1, is positioned between the cavitator 3 and the main elastic body 2, and has an axis coincident with that of the fairing 1;
the plurality of side hydraulic dampers 5 are distributed around the axis of the pneumatic damping device 4, one end of each side hydraulic damper 5 is connected 6 with the pneumatic damping device 4 through a mounting mechanism, and the other end of each side hydraulic damper 5 is connected with the inner wall of the fairing 1;
the metal-based foam layer 7 is arranged in the fairing 1, the tail end face of the metal-based foam layer is in contact connection with the head end face of the cavitator 3, a deformation cavity 701 is arranged between the head end face of the metal-based foam layer and the head of the fairing 1, and the side wall of the metal-based foam layer is matched with and in contact connection with the inner wall of the fairing 1;
a polyurethane foam layer 8 arranged between the fairing 1 and the side hydraulic damper 5, wherein one end of the side hydraulic damper 5 far away from the pneumatic damping device 4 is fixedly connected with the polyurethane foam layer 8, the polyurethane foam layer 8 is in contact connection with the inner wall of the fairing 1, and the polyurethane foam layer 8 has a density of 200 and 300kg/m3The rigid polyurethane foam of (1).
And the electromagnet 9 is arranged in the head of the main projectile body 2 and is used for adsorbing the pneumatic damping device 4.
Said pneumatic damping means 4 comprise:
the mounting seat 401 is arranged in the tail part of the fairing 1 and is in contact connection with the head end face of the main projectile body 2;
a seal pressure cylinder 402;
an air cavity external protection cylinder 403 which is sleeved outside the sealing pressure cylinder 402, is fixedly connected with the sealing pressure cylinder 402, and has the tail end fixedly connected with the mounting seat 401;
a piston 404 disposed within the seal cylinder 402 and cooperating with the seal cylinder 402;
a piston rod 405, the tail part of which penetrates into the sealed pressure cylinder 402 and is fixedly connected with the piston 404, and the head part of which is hinged with the cavitator 3 through a ball head 406;
a tension spring 407, which is sleeved on the piston rod 405, and has a tail end fixedly connected to the head end surface of the piston 404 and a head end fixedly connected to the head end surface of the sealing pressure cylinder 402;
an air chamber 408, a cavity between the piston 404 and the tail of the sealing cylinder 402;
buffering high-pressure inert gas, and filling the gas cavity 408;
a stop surface 409 obliquely arranged at the rear part of the air cavity outer protection cylinder 403;
the damper outer sleeve 410 is sleeved outside the air cavity outer protection cylinder 403 and is in sliding fit with the air cavity outer protection cylinder 403, and the tail part of the damper outer sleeve is provided with an outer impact stop block 411 matched with the stop surface 409;
and a damper protection corrugated dustproof sleeve 412 which is arranged on the outer wall of the damper outer sleeve 410.
The damper protective corrugated dust boot 412 includes:
the head structure is divided into four sections which are connected in sequence, namely a sealing section 413, a head section 414, a middle section 415 and a tail section 416, wherein the extending direction of the sealing section 413 is perpendicular to the axial direction of the pneumatic damping device 4, one end of the sealing section is fixedly connected with the outer wall of the piston rod 405, and the other end of the sealing section is fixedly connected with the head end of the head section 414; the outer wall of the head section 414 extends from the head of the head section 414 to the tail thereof in the axial direction away from the pneumatic damping device 4; the outer wall of the middle section 415 extends from the rear of the head section 414 to the rear of the middle section 415 in the axial direction close to the pneumatic damping device 4; the outer wall of the tail section 416 extends from the tail of the middle section 415 to the tail of the tail section 416 in a direction parallel to the axis of the aerodynamic damping device 4;
a bellows 417, a head end of which is fixedly connected to an outer wall of the tail section 416, and a tail end of which is fixedly connected to a tail end of the damping block outer sleeve 410;
and a connecting piece 418, one end of which is fixedly connected with the tail of the middle section 415, and the other end of which extends towards the tail section 416, bends to extend towards the tail of the middle section 416, and is fixedly connected with the head of the damper outer sleeve 410.
A rubber anti-collision block 419 is arranged in the damper protection corrugated dustproof sleeve 412, the inner wall of the rubber anti-collision block 419 is fixedly connected with the outer wall of the piston rod 405, and the head end of the rubber anti-collision block 419 is fixedly connected with the sealing section 413.
A rubber cushion is arranged between the mounting seat 401 and the main projectile body 2. The mount 401 is made of a material that can be electromagnetically attracted.
The mounting mechanism 6 includes:
the hinge base 601 is fixed on the outer wall of the tail part of the air cavity outer protection cylinder 403;
a hinge column 602, one end of which is hinged to the hinge seat 601 through a hinge shaft 603 matched with the hinge seat 601; the hinge post 602 is made of a high strength alloy;
the gas nozzle 604 is arranged in the hinged column 602, and the gas nozzle 604 is made of high-pressure-resistant and high-strength plastic materials;
one end of a vent pipe 605 is communicated with the air cavity 408 through a pneumatic valve 606, and the other end is communicated with one end of the gas nozzle 604 close to the hinge base 601;
the mounting groove is processed the side hydraulic damper 6 is close to the one end of articulated post 602, and with articulated post 602 phase-match, articulated post 602 install in the mounting groove, and with the mounting groove contact is connected.
The tail part of the fairing 1 is detachably connected with the outer wall of the head part of the main projectile body 2 through a connecting mechanism 10.
The connecting mechanism 9 includes:
the missile body 2 comprises a plurality of metal sheets 1001, wherein the metal sheets 1001 are distributed around the axis of the main missile body 2, one end of each metal sheet 1001 is fixedly connected with the tail end of the fairing 1, the other end of each metal sheet extends towards the head end of the fairing 1 and then returns to the tail end of the fairing 1 to extend, each metal sheet penetrates through a metal sheet clamping groove 1002 machined in the outer wall of the main missile body 2 to be bent in an arc shape, and the end part of each metal sheet is in contact connection with the outer wall of the main missile body 2.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims (10)

1. The utility model provides a pneumatic damping formula of body of navigating wide-angle slope income water carries device that falls which characterized in that includes:
the head of the fairing is sealed and is in a pointed arch shape, and the inner wall of the tail end of the fairing is detachably connected with the outer wall of the head of the main projectile body;
the cavitator is of a disc type structure, the axis of the cavitator is superposed with the axis of the fairing, is arranged in the head of the fairing and is in contact connection with the inner wall of the head of the fairing;
the aerodynamic damping device is arranged in the fairing, is positioned between the cavitator and the main elastic body, and has an axis coincident with that of the fairing;
the aerodynamic damping device comprises a plurality of side hydraulic dampers, wherein the side hydraulic dampers are distributed around the axis of the aerodynamic damping device, one ends of the side hydraulic dampers are detachably connected with the aerodynamic damping device, and the other ends of the side hydraulic dampers are connected with the inner wall of the fairing.
2. The pneumatic damping type load reducing device for the large-angle inclined water of the navigation body according to claim 1, is characterized by further comprising:
and the electromagnet is arranged in the head of the main projectile body and is used for adsorbing the pneumatic damping device.
3. The composite load-reducing device for the high-speed water entering of the navigation body according to claim 1, is characterized by further comprising:
the metal-based foam layer is arranged in the fairing, the tail end face of the metal-based foam layer is in contact connection with the head end face of the cavitator, a deformation cavity is arranged between the head end face of the metal-based foam layer and the head of the fairing, and the side wall of the metal-based foam layer is matched with and in contact connection with the inner wall of the fairing;
a polyurethane foam layer arranged between the fairing and the side hydraulic damper, wherein one end of the side hydraulic damper, which is far away from the pneumatic damping device, is fixedly connected with the polyurethane foam layer, the polyurethane foam layer is in contact connection with the inner wall of the fairing, and the polyurethane foam layer has a density of 200-300kg/m3The rigid polyurethane foam of (1).
4. The pneumatic damping type load reducing device for the large-angle inclined water of the navigation body according to claim 1, wherein the pneumatic damping device comprises:
the mounting seat is arranged in the tail part of the fairing and is in contact connection with the head end face of the main projectile body;
sealing the pressure cylinder;
the air cavity external protection cylinder is sleeved outside the sealing pressure cylinder and fixedly connected with the sealing pressure cylinder, and the tail end of the air cavity external protection cylinder is fixedly connected with the mounting seat;
the piston is arranged in the sealing pressure cylinder and is matched with the sealing pressure cylinder;
the tail part of the piston rod penetrates into the sealed pressure cylinder and is fixedly connected with the piston, and the head part of the piston rod is hinged with the cavitator through a ball head;
the tension spring is sleeved on the piston rod, the tail end of the tension spring is fixedly connected with the head end face of the piston, and the head end of the tension spring is fixedly connected with the head end face of the sealing pressure cylinder;
the air cavity is a cavity between the piston and the tail part of the sealing pressure cylinder;
and the buffer gas is filled in the air cavity.
5. The compound offloading device for high-speed water entry for a vehicle of claim 4, wherein the pneumatic damping device further comprises:
the stop surface is obliquely arranged at the rear part of the protection cylinder outside the air cavity;
the damper external sleeve is sleeved outside the air cavity external protection cylinder and is in sliding fit with the air cavity external protection cylinder, and the tail part of the damper external sleeve is provided with an external impact stop block matched with the stop surface;
and the damper protection corrugated dustproof sleeve is arranged on the outer wall of the outer sleeve of the damper.
6. The pneumatic damping type load reducing device for the large-angle inclined water of the navigation body according to claim 5, wherein the damper protection corrugated dustproof sleeve comprises:
the head structure is divided into four sections which are sequentially connected and respectively comprise a sealing section, a head section, a middle section and a tail section, the extending direction of the sealing section is perpendicular to the axis direction of the pneumatic damping device, one end of the sealing section is fixedly connected with the outer wall of the piston rod, and the other end of the sealing section is fixedly connected with the head end of the head section; the outer wall of the head section extends from the head part of the head section to the tail part of the head section in the axial direction far away from the pneumatic damping device; the outer wall of the middle section extends from the tail part of the head section to the tail part of the middle section in the axial direction close to the pneumatic damping device; the outer wall of the tail section extends from the tail part of the middle section to the tail part of the tail section in the direction parallel to the axis of the pneumatic damping device;
the head end of the corrugated pipe is fixedly connected with the outer wall of the tail section, and the tail end of the corrugated pipe is fixedly connected with the tail end of the sleeve outside the damping block;
and one end of the connecting sheet is fixedly connected with the tail part of the middle section, and the other end of the connecting sheet is bent to extend towards the tail part of the middle section after extending towards the tail section direction and is fixedly connected with the head part of the outer sleeve of the damper.
7. The pneumatic damping type load reducing device for the large-angle inclined water of the navigation body as claimed in claim 6, wherein a rubber anti-collision block is arranged in the damper protection corrugated dustproof sleeve, the inner wall of the rubber anti-collision block is fixedly connected with the outer wall of the piston rod, and the head end of the rubber anti-collision block is fixedly connected with the sealing section.
8. The pneumatic damping type load-reducing device for the large-angle inclined water of the navigation body as claimed in claim 4, wherein one end of the side hydraulic damper is detachably connected with the pneumatic damping device through a mounting mechanism, and the mounting mechanism comprises:
the hinge seat is fixed on the outer wall of the tail part of the protection cylinder outside the air cavity;
one end of the hinge column is hinged with the hinge seat through a hinge shaft matched with the hinge seat;
the gas spray pipe is arranged in the hinge column;
one end of the vent pipe is communicated with the air cavity through a pneumatic valve, and the other end of the vent pipe is communicated with one end of the gas spray pipe close to the hinge seat;
the mounting groove is processed the side hydraulic damper is close to the one end of hinge post, and with the hinge post phase-match, the hinge post is installed in the mounting groove, and with the mounting groove contact is connected.
9. The pneumatic damping type load reducing device for the large-angle inclined water of the navigation body as claimed in claim 1, wherein the tail part of the fairing is detachably connected with the outer wall of the head part of the main projectile body through a connecting mechanism.
10. The pneumatic damping type load reducing device for the large-angle inclined water of the navigation body according to claim 9, wherein the connecting mechanism comprises:
the metal sheets are distributed around the axis of the main elastic body, one end of each metal sheet is fixedly connected with the tail end of the fairing, the other end of each metal sheet extends towards the head end of the fairing and then returns to the tail end of the fairing to extend, the metal sheets penetrate into metal sheet clamping grooves in the outer wall of the main elastic body to be processed, then arc bending occurs, and the end portions of the metal sheets are in contact connection with the outer wall of the main elastic body.
CN202011306013.3A 2020-11-19 2020-11-19 Pneumatic damping type load reducing device for large-angle inclined water entering of navigation body Active CN112413040B (en)

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CN113879451A (en) * 2021-10-29 2022-01-04 大连理工大学 Combined disc type cavitation structure for underwater navigation of navigation body
CN113879449A (en) * 2021-10-29 2022-01-04 大连理工大学 Adjustable double-layer telescopic sheet cavitator structure
CN113879452A (en) * 2021-10-29 2022-01-04 大连理工大学 Underwater navigation body cavitation load reduction device capable of adjusting water entry angle
CN113879450A (en) * 2021-10-29 2022-01-04 大连理工大学 High-speed water-entering composite buffering structure with airfoil-shaped multistage linkage cavitator
CN113955055A (en) * 2021-10-29 2022-01-21 大连理工大学 Composite load-reducing device for navigation body
CN114013558A (en) * 2021-10-29 2022-02-08 大连理工大学 Pneumatic type multistage linkage cavitator adjustable structure
CN114162255A (en) * 2021-10-29 2022-03-11 大连理工大学 Adjustable cavitation damping device for high-speed water entry of navigation body
WO2023072198A1 (en) * 2021-10-29 2023-05-04 大连理工大学 Gas multi-channel recycling jet-propelled water-entry composite cushioning device

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CN113879451A (en) * 2021-10-29 2022-01-04 大连理工大学 Combined disc type cavitation structure for underwater navigation of navigation body
CN113879449A (en) * 2021-10-29 2022-01-04 大连理工大学 Adjustable double-layer telescopic sheet cavitator structure
CN113879452A (en) * 2021-10-29 2022-01-04 大连理工大学 Underwater navigation body cavitation load reduction device capable of adjusting water entry angle
CN113879450A (en) * 2021-10-29 2022-01-04 大连理工大学 High-speed water-entering composite buffering structure with airfoil-shaped multistage linkage cavitator
CN113955055A (en) * 2021-10-29 2022-01-21 大连理工大学 Composite load-reducing device for navigation body
CN114013558A (en) * 2021-10-29 2022-02-08 大连理工大学 Pneumatic type multistage linkage cavitator adjustable structure
CN114162255A (en) * 2021-10-29 2022-03-11 大连理工大学 Adjustable cavitation damping device for high-speed water entry of navigation body
CN114013558B (en) * 2021-10-29 2022-12-09 大连理工大学 Pneumatic multistage linkage cavitator adjustable structure
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WO2023072201A1 (en) * 2021-10-29 2023-05-04 大连理工大学 Modulatable double-layer telescopic sheet cavitator structure
WO2023072198A1 (en) * 2021-10-29 2023-05-04 大连理工大学 Gas multi-channel recycling jet-propelled water-entry composite cushioning device
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CN113879451B (en) * 2021-10-29 2023-10-31 大连理工大学 Combined disc type cavitation structure for underwater navigation of navigation body
CN113879449B (en) * 2021-10-29 2023-10-31 大连理工大学 Adjustable double-layer telescopic sheet cavitation device structure
CN113879452B (en) * 2021-10-29 2023-10-31 大连理工大学 Underwater vehicle cavitation load reduction device capable of adjusting water inlet angle
CN114162255B (en) * 2021-10-29 2023-10-31 大连理工大学 Adjustable cavitation damping device for high-speed water entry of navigation body
CN113879450B (en) * 2021-10-29 2023-10-31 大连理工大学 High-speed water-entering composite buffer structure with wing type multistage linkage cavitation device

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