CN111392010B - Asymmetric buffering head cap for high-speed underwater entry of aircraft - Google Patents

Asymmetric buffering head cap for high-speed underwater entry of aircraft Download PDF

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CN111392010B
CN111392010B CN202010262193.3A CN202010262193A CN111392010B CN 111392010 B CN111392010 B CN 111392010B CN 202010262193 A CN202010262193 A CN 202010262193A CN 111392010 B CN111392010 B CN 111392010B
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aircraft
section
head cap
arc
asymmetric
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CN111392010A (en
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施瑶
潘光
高兴甫
宋保维
黄桥高
姜军
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Northwestern Polytechnical University
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
    • B63G8/001—Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
    • 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
    • B63B1/40—Other means for varying the inherent hydrodynamic characteristics of hulls by diminishing wave resistance
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63C—LAUNCHING, HAULING-OUT, OR DRY-DOCKING OF VESSELS; LIFE-SAVING IN WATER; EQUIPMENT FOR DWELLING OR WORKING UNDER WATER; MEANS FOR SALVAGING OR SEARCHING FOR UNDERWATER OBJECTS
    • B63C11/00—Equipment for dwelling or working underwater; Means for searching for underwater objects
    • B63C11/52—Tools specially adapted for working underwater, not otherwise provided for
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T70/00—Maritime or waterways transport
    • Y02T70/10—Measures concerning design or construction of watercraft hulls

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Ocean & Marine Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
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Abstract

The invention relates to an asymmetric buffering head cap for high-speed underwater entering of an aircraft, which consists of an outer housing, a buffering piece and a connecting piece. The cover shell is a pointed arch body connected with a cylindrical section, a buffer part is arranged between the pointed arch body and the aircraft, a combining part is arranged between the cylindrical section and the aircraft, and an asymmetric head cap relative to the axis is formed at the top end of the pointed arch body. The cover shell enables the aircraft to have a good pneumatic head shape, the stability of the whole structure of the buffering head cap is guaranteed in the air flight stage, the aircraft is not broken when entering water, the aircraft is enabled to be under the action of smaller resistance of fluid when moving in the water and a flow field, and the aircraft can be separated after reaching a preset posture, so that the subsequent movement of the aircraft is not influenced. The buffer part is a revolving body, and hard polyurethane foam plastic is selected as a material for manufacturing the foam plastic buffer. The connecting piece adopts an explosion screw to tightly fix the head cap on the aircraft, and after the aircraft completely enters water and deviates to a preset posture, the bolt explodes, so that the head cap is separated from the aircraft.

Description

Asymmetric buffering head cap for high-speed underwater entry of aircraft
Technical Field
The invention belongs to the field of design of an underwater vehicle entering buffer device, and relates to a high-speed underwater entering asymmetric buffer head cap of an aircraft.
Background
Most underwater vehicles are revolved bodies, and the appearance enables the vehicles to have high ballistic stability. When the underwater vehicle is launched in an air-drop or rocket assisted flying mode, the water entry angle is generally larger and close to 90 degrees, and the vehicle bounces on the water surface when entering water at a small angle is avoided. However, the underwater vehicle is in a horizontal state when working normally, ballistic control is required to be carried out through the fin rudder at the tail part of the vehicle, the time is long, the water entry ballistic can be changed by changing the head shape of the vehicle, but the subsequent movement of the vehicle is influenced, and therefore an efficient and detachable water entry ballistic control device is required. Meanwhile, when the aircraft enters water at a high speed, huge impact load can be applied, and the structure of the aircraft can be damaged, so that the underwater buffer device is needed.
Disclosure of Invention
Technical problem to be solved
In order to avoid the defects of the prior art, the invention provides the high-speed underwater asymmetric buffering head cap for the aircraft, which can enable the aircraft to quickly reach the operational attitude after entering the water, and can reduce the impact load acting on the aircraft, so that the aircraft can safely and reliably enter the water. After entering water, the head cap is separated from the aircraft, and the subsequent movement of the aircraft is not influenced.
Technical scheme
An asymmetric buffering head cap for high-speed water entry of an aircraft is characterized by comprising a housing 1, a buffering part 2 and a combining part 3; the encloser 1 is a sharp arch body connected with a cylindrical section, a buffer part 2 is arranged between the sharp arch body and the aircraft 4, and a combining part 3 is arranged between the cylindrical section and the aircraft 4; the pointed arch body is a ball head section arc CC1An arc AB connecting the pointed arch body section is symmetrical to the axis, the circle center is the maximum diameter extension point P of the pointed arch body section, and the radius is R1(ii) a Ball head section arc CC1Is an arc with an asymmetric axis, the center of the arc is on the maximum diameter of the ogival section and is deviated from the axis point P1Radius R3(ii) a Ball head section arc CC1An asymmetric head cap 5 relative to the axis is formed at the top end of the ogival; and a circular groove matched with the head of the aircraft 4 is formed in the connecting part of the buffer 2 and the aircraft 4.
The sizes of the pointed arch body and the cylindrical section satisfy the relation:
Figure BDA0002439826400000021
Figure BDA0002439826400000022
wherein: r1Radius of arc AB of a cuspid arch segment, R0The radius of a cylindrical section is defined, alpha is the cone apex angle at the top end of the sharp arch body, beta is the scanning angle AB of the arc section of the sharp arch body section, y is the radius of any section on the sharp arch body and the cylindrical section, and x is the axial length of the head cap;
the constraint conditions are as follows: r3＜R1，L0＜R1-R0；L0As the center of a circle which is on the maximum diameter of the ogival section and is deviated from the axle center point P1Distance to the axis.
The binder 3 is an explosive screw.
The housing is freshly forged from a high strength alloy.
The material of the buffer 2 is polyurethane foam.
Advantageous effects
The invention provides an asymmetric buffering head cap for high-speed water entering of an aircraft, which consists of an outer housing, a buffering piece and a connecting piece. The above is a definition of the casing, which is made of a rigid material, which does not break during entry into the water, which can continue to reduce drag and which can rapidly change the water entry trajectory of the craft. The cover shell enables the aircraft to have a good pneumatic head shape, the stability of the whole structure of the buffering head cap is guaranteed in the air flight stage, the aircraft is not broken when entering water, the aircraft is enabled to be under the action of smaller resistance of fluid when moving in the water and a flow field, and the aircraft can be separated after reaching a preset posture, so that the subsequent movement of the aircraft is not influenced. The buffer piece can isolate impact when entering water, reduces and limits the water-entering impact load acting on the aircraft, is a revolving body, is limited by the inner space of the housing in specific shape, is bonded at the front end in the housing, and selects hard polyurethane foam plastic as a material for manufacturing the foam plastic buffer. The connecting piece adopts an explosion screw to tightly fix the head cap on the aircraft, and after the aircraft completely enters water and deviates to a preset posture, the bolt explodes, so that the head cap is separated from the aircraft.
Drawings
FIG. 1 is an explanatory view of a ogival cover
FIG. 2 is an explanatory view of an asymmetric cover, and a cut-away portion is a hatched portion
FIG. 3 is a diagram of an asymmetric bumper headgear structure, 1-hood, 2-bumper, 3-coupler, 4-vehicle, 5-asymmetric headgear.
Detailed Description
The invention will now be further described with reference to the following examples and drawings:
FIG. 1 shows a symmetrical bumper headgear housing profile, line AA1The following is the ogive portion, AA1The above is a cylindrical section portion. The apex arch body is composed of AB and BB1Two circular arcs, symmetrical about the middle axis, wherein the radius of the segment AB is R1The center of the circle is a point P. BB1Is a ball head section, the circle center is a point Q, and the radius is R2The spherical segment and the ogive segment are tangent to point B and point B1H is the length of the ogival, and r is the half chord length of the ball head arc. The cut-off arc is denoted as CC in FIG. 21，CC1Is a circular arc with a corresponding central point of P1Radius R3Wherein the center point P1Located on a straight line AA1Upper, with point O1Is a distance L0。
By cutting off a portion of the symmetrical cushioning headgear. The revolving body buffer head cap is in an ogival-cylindrical revolving body head shape, and the cutting method is to cut off a part of the ogival head shape by using an arc surface.
As shown in FIG. 1, the buffering headgear casing is composed of a ogival segment and a cylinder segment, and establishes a coordinate system as shown in the figure, wherein the origin of coordinates is a point O, the central axis is an x-axis, and the radius R is1Radius R of cylindrical section0The cone vertex angle alpha and the arc segment scanning angle beta have the following relationship:
Figure BDA0002439826400000031
the axial length x of the head cap and any section radius y have the following relationship:
Figure BDA0002439826400000041
therefore, the line shape of the housing can be formed by the radius R of the circular arc section1The cone apex angle alpha and the arc segment scan angle beta are completely defined.
As shown in FIG. 2, the asymmetric shell is created by cutting away a portion of the shell, the cut-away arc being shown as arc CC in the figure1Corresponding to the center point of the circle being P1Radius R3Wherein the center point P1Located on a straight line AA1Upper, with point O1Is a distance L0. The CC1Can be composed of L0And R3And (4) completely defining. The following constraint conditions are required to be met during excision:
R3＜R1，L0＜R1-R0
the example is described for a flat head vehicle with a diameter of 200 mm.
The method comprises the following steps: the encloser is formed by forging and processing high-strength alloy steel, under different water entry speeds and water entry angles, the strength interval of the outer encloser 1 of the buffering head cap is determined according to the maximum water entry impact load of an aircraft, the thickness of the outer encloser is determined to be 5mm, and then the L is determined according to the water entry trajectory requirement0And R3。
Step two: the buffer 2 is made of polyurethane foam, the geometrical shape of the buffer is determined by the internal shape of the housing 1, the buffer is tightly attached to the inner wall of the housing, and the length of the cylindrical section is determined to be 150mm according to the requirement of buffering performance.
Step three: the total length of the encloser shell designed by the invention is 400mm, the length of the cylindrical section is 150mm, the thickness of the shell is 5mm, the radius of the small ball head is 6.8mm, the inner diameter of the pointed arch body is 162mm, and the length of the part of the encloser connected with an aircraft is about 50 mm. The specific size of the buffering headgear is determined according to the geometric shape of the aircraft 4 and the water inlet condition when in specific use.
Step four: the connector 3 adopts explosion screws, and four bolts are uniformly distributed on the housing and are tightly connected with the aircraft.
Step five: will be provided withThe gauged bumper caps are mounted on the vehicle 4 and compacted. When the aircraft enters water, impact load firstly acts on the shell of the buffer device, foam is compressed and deformed to have a buffer effect, the load transmitted to the aircraft is limited to be small, the aircraft is protected from being damaged in the water entering process, meanwhile, the asymmetric head cap enables the aircraft to be subjected to asymmetric load, radial acceleration is generated, a trajectory deflects, and the deflection angle is L0And R3And (6) determining.

Claims (4)

1. An asymmetric buffering head cap for high-speed water entry of an aircraft is characterized by comprising a cover shell (1), a buffering piece (2) and a combining piece (3); the encloser (1) is a pointed arch body connected with a cylindrical section, a buffer part (2) is arranged between the pointed arch body and the aircraft (4), and a combining part (3) is arranged between the cylindrical section and the aircraft (4); the pointed arch body is a ball head section arc CC1An arc AB connecting the pointed arch body section is symmetrical to the axis, the circle center is the maximum diameter extension point P of the pointed arch body section, and the radius is R1(ii) a Ball head section arc CC1Is an arc with an asymmetric axis, the center of the arc is on the maximum diameter of the ogival section and is deviated from the axis point P1Radius R3(ii) a Ball head section arc CC1An asymmetric head cap (5) relative to the axis is formed at the top end of the ogival body; a round groove matched with the head of the aircraft (4) is formed in the connecting part of the buffer piece (2) and the aircraft (4);
the sizes of the pointed arch body and the cylindrical section satisfy the relation:
Figure FDA0003181017710000011
Figure FDA0003181017710000012
wherein: r1Radius of arc AB of a cuspid arch segment, R0Is the radius of a cylindrical section, alpha is the vertex angle of the top end of the sharp arch body, beta is the scanning angle of an arc section AB of the sharp arch body section, and y is the sharp arch body and the circleAny section radius on the column section, and x is the axial length of the head cap;
the constraint conditions are as follows: r3＜R1，L0＜R1-R0；L0As the center of a circle which is on the maximum diameter of the ogival section and is deviated from the axle center point P1Distance to the axis.
2. The asymmetric buffering headgear for high-speed underwater entry of an aircraft as claimed in claim 1, wherein: the binder (3) adopts an explosive screw.
3. The asymmetric buffering headgear for high-speed underwater entry of an aircraft as claimed in claim 1, wherein: the housing is freshly forged from a high strength alloy.
4. The asymmetric buffering headgear for high-speed underwater entry of an aircraft as claimed in claim 1, wherein: the material of the buffer piece (2) is polyurethane foam.
CN202010262193.3A 2020-04-06 2020-04-06 Asymmetric buffering head cap for high-speed underwater entry of aircraft Active CN111392010B (en)

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CN113932661A (en) * 2021-10-25 2022-01-14 北京玻钢院复合材料有限公司 Carbon fiber composite slow-descending carrier head cover and preparation method thereof
CN114701599B (en) * 2022-04-19 2023-02-28 吉林大学 Buffer device for high-speed water entry of navigation body
CN116123939B (en) * 2023-04-03 2024-04-09 北京理工大学 Missile high-speed water-entering flat offset type head load-reducing stability-increasing device

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US3477376A (en) * 1968-03-06 1969-11-11 Us Navy Missile nose cap
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CN109387122A (en) * 2018-09-01 2019-02-26 哈尔滨工程大学 The reversed water spray bubbling crystallzation of one kind assists high speed to enter water attenuating shock loading mechanism

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US2889772A (en) * 1957-07-09 1959-06-09 Earle A Howard Protective nose cap for torpedoes
US3279405A (en) * 1965-03-29 1966-10-18 Allen K Billmeyer Torpedo nose cap retaining device
US3477376A (en) * 1968-03-06 1969-11-11 Us Navy Missile nose cap
US3674227A (en) * 1970-03-23 1972-07-04 Hughes Aircraft Co Fragmenting cover
CN109387122A (en) * 2018-09-01 2019-02-26 哈尔滨工程大学 The reversed water spray bubbling crystallzation of one kind assists high speed to enter water attenuating shock loading mechanism

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