WO2014183614A1 - 具防爆缓冲功能的武装直升机透明件紧固结构及紧固方法 - Google Patents

具防爆缓冲功能的武装直升机透明件紧固结构及紧固方法 Download PDF

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Publication number
WO2014183614A1
WO2014183614A1 PCT/CN2014/077243 CN2014077243W WO2014183614A1 WO 2014183614 A1 WO2014183614 A1 WO 2014183614A1 CN 2014077243 W CN2014077243 W CN 2014077243W WO 2014183614 A1 WO2014183614 A1 WO 2014183614A1
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WO
WIPO (PCT)
Prior art keywords
helicopter
cockpit
fastening
transparent member
cabin
Prior art date
Application number
PCT/CN2014/077243
Other languages
English (en)
French (fr)
Inventor
谢晓斌
李震
谢隽永
Original Assignee
一禾科技发展（上海）有限公司
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 一禾科技发展（上海）有限公司 filed Critical 一禾科技发展（上海）有限公司
Publication of WO2014183614A1 publication Critical patent/WO2014183614A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B64C1/1476—Canopies; Windscreens or similar transparent elements
    • B64C1/1492—Structure and mounting of the transparent elements in the window or windscreen
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D7/00—Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters

Definitions

  • the invention relates to a military helicopter in the field of national defense construction, in particular to a fastening structure and a fastening method for a transparent part of an armed helicopter cockpit. Background technique
  • the cockpit transparent parts of the helicopter gunship mainly include fixed front windshield transparent parts and movable top or side windshield transparent parts.
  • the cockpit transparent parts must have the following functions as important optical structural parts on the armed helicopter: For structural parts, it must have sufficient strength to resist external impact loads, such as bullet shooting, explosion shock, bird impact, etc. Second, as a transparent observation window, it must have good optical properties, including transmittance, haze, Resolution, optical angular deviation, optical distortion, ghosting, binocular parallax, birefringence and many other important performance indicators; the third is must have reliability and long service life. Its structural integrity, robustness and stability of use are closely related to the pilot's living environment and will directly affect flight safety and the completion of military missions.
  • the transparent parts of the helicopter helicopter cockpit are mainly installed with bolts or inlays, and the two installation methods have their own drawbacks.
  • the inlaying method is to place the transparent part of the cockpit in the reserved gap of the skeleton of the fuselage, and then install and fasten by injecting structural glue or filler, so that the installation difficulty can be reduced, and the transparent part of the cockpit is not
  • the internal stress causes damage, but the cockpit transparent piece cannot be integrated with the helicopter cockpit, and the cockpit transparent piece can easily escape as a whole when subjected to an external impact.
  • the bolt connection is a way of opening the hole in the transparent part of the cockpit and directly connecting with the skeleton of the fuselage through hardware such as bolts.
  • the advantage is that the strength is high and the integrity is good, but the following defects are usually present:
  • the manufacturing process of the armed helicopter is highly demanding on the processing technology of the transparent part of the cockpit. Once the processing size or curvature of the transparent part of the cockpit has a slight error, it affects the fit of the fuselage skeleton; or on the transparent part of the cockpit The center of the bolt hole is not completely aligned with the center of the corresponding hole on the frame of the fuselage; or the bolt hole provided in the transparent part of the cockpit has defects such as cracks, notches, and poor polishing. The above situation will directly lead to difficulty in installing the transparent part of the cockpit. There is stress concentration after installation, and the interchangeability of the cockpit transparent parts is poor;
  • the cockpit transparent parts have more or less certain defects or residual stresses during the manufacturing and processing process, which may cause the defects or stress to gradually enlarge during transportation, storage or assembly. If not found and effective in time Disposal or scrapping, once the crack in the transparent part of the cockpit will significantly reduce its tensile strength and impact toughness, it will bring great safety hazards for future use;
  • the cockpit transparent part When the outer shape of the cockpit transparent part is smaller than the inner diameter of the cockpit frame, the cockpit transparent part will fall off from the whole body frame; if the cockpit transparent part is bolted to the fuselage frame, when subjected to external impact load, The cockpit transparent part and the fuselage frame are bolted to the overall rigidity. Therefore, most of the impact load on the moment of external impact is absorbed by the transparent part of the cockpit. Most of the cockpit transparent parts are transmitted to the fuselage frame through bolts. Therefore, the stress near the bolt hole of the transparent part of the cockpit will increase instantaneously, and the superposition of the residual stress and the assembly stress will cause cracks in the transparent part of the cabin, and in serious cases, the transparent part of the cabin may be damaged.
  • the fastening installation structure of the transparent parts of the armed helicopter cockpit in the world is almost the same, but the material and manufacturing process of the transparent part of the cockpit are improved.
  • the fastening structure of the transparent part of the cockpit and the skeleton of the fuselage has not been fundamentally changed. Still exist, the cockpit transparent member fastening installation structure has also become a major problem for the relevant technical personnel.
  • An object of the present invention is to overcome the deficiencies of the prior art and to provide a completely new mounting structure for a cabin transparent member reinforced by a bezel.
  • the present invention discloses a helicopter helicopter cockpit transparent member mounting structure, comprising a mounting frame and a cabin transparent member fixed to the helicopter body through the mounting frame; the mounting frame is formed first a mounting groove, the side of the transparent part of the cockpit is inserted into the first mounting groove; the side of the transparent part of the cockpit is coupled with a frame body, and the frame body is formed between the frame and the first mounting groove There is a mating mounting structure, the frame body includes a pressing assembly and a fastening assembly, and the fastening assembly generates a pre-stress by the cooperation of the pressing assembly and the cabin transparent member to thereby fasten the cabin transparent member.
  • the fastening assembly includes two arcuate arms symmetrically clamped on opposite sides of the transparent part of the cabin, and the two arcuate arms are interposed to form an enclosure space, and the arcuate arms include the first a force arm and a second force arm connecting the first force arm, a joint of the first force arm and the second force arm forming a slip end, the first force arm being away from the second force One side of the arm forms a pressure receiving end, and the second force arm forms a fastening end on a side away from the first force arm, and the pressure end of the first force arm receives the pressing force of the pressing component and cooperates
  • the cabin transparency drives the first and second force arms to generate a pre-stress.
  • the compression assembly includes a first pressure strip and a second pressure strip; the two sliding ends of the arcuate arm abut against the surface of the first pressure strip; The pressing end abuts against the outer side surface of the second pressure strip, and the two fastening ends of the arcuate arm are disposed on both sides of the transparent part of the cabin;
  • the first pressure bar and the second pressure bar are fastened by bolts, and the second pressure bar presses two of the arcuate arms
  • the pressure receiving end is displaced toward the first pressure bar, and the two sliding ends of the arcuate arm are displaced away from each other on the surface of the first pressure bar, and the two fastening ends of the arcuate arm are received by the cockpit
  • the restriction of the transparent member drives the first force arm and the second force arm to generate pre-stressed fastening of the cabin transparency.
  • a further improvement of the present invention is that the cabin transparency is adjusted in a first direction and a second direction by the enclosure space.
  • a further improvement of the present invention is that the mounting frame forms the first pressure strip, and the first pressure strip and the second pressure strip are fastened by bolts to form the mounting structure to install the cabin transparent member In the first installation slot.
  • the first pressure bar and the mounting frame form a matching portion; the at least one elastic buffer member is disposed between the frame and the mounting frame.
  • a further improvement of the invention is that the bottom of the frame is provided with a sliding buffer device.
  • the mounting frame includes a frame and a cover plate fixed to the frame, and the frame and the cover plate cooperate to form the first mounting groove.
  • a further improvement of the present invention is that the side of the cockpit transparent member is recessed to form a second mounting groove and is coupled with a T-shaped member;
  • the T-shaped member includes a back plate and a ridge formed on the back plate, a ridge is embedded in the second mounting groove, the back plate abuts against the second pressure strip, and the first pressure bar, the second pressure bar and the T-shaped piece are fastened through a bolt
  • the backing plate and the ribs drive the first and second force arms of the fastening assembly to generate pre-stressed fastening of the cabin transparency.
  • a gasket is disposed between the cabin transparency and the backing plate.
  • the sliding end of the arcuate arm has a circular arc surface or a sloped surface.
  • a further improvement of the invention is that the thickness of the second force arm forms a thick to thin gradient from the slip end to the fastening end.
  • the compressed end of the arcuate arm of the fastening component extends downward to form a rotational positioning rib, and the second pressure strip is formed with a rotational positioning corresponding to the rotational positioning edge of the fastening component. groove.
  • the invention engages the plane of the transparent part of the cockpit through the prestressed structure, and generates a rigid frame integrated with the transparent part of the cockpit, and fixes the transparent part of the cockpit to the fuselage frame through the frame, thereby forming a
  • the new integrated force structure of the cockpit transparent part with pre-stress buffer function and the cockpit effectively transmits the load on the transparent part of the cockpit to the fuselage through the prestressed structure, ensuring the integrity of the cockpit structure;
  • the transparent part of the cockpit is fastened by the prestressed frame and the skeleton of the fuselage, and the bolt hole is no longer needed on the transparent part of the cockpit, and the internal stress balance of the transparent part of the cockpit is not damaged, and the original transparent part of the cockpit is maintained.
  • the cockpit transparent member is fastened to the fuselage frame in a positionally adjustable manner, and the fastening assembly has a certain tolerance for the manufacturing error of the cockpit transparent member, thereby assembling the cockpit transparent member and the skeleton. It is more convenient, avoids the generation of assembly stress, and can greatly improve the assembly interchangeability of the transparent parts of the cabin;
  • the edge of the transparent part of the cockpit of some armed helicopters has a circular arc surface.
  • the fastening group The second force arm is split into a plurality of jaws, so that the fastening end of the fastening component can be more closely attached to the arc surface of the transparent part of the cabin, so that the fastening component does not damage the internal stress of the cabin transparent member itself. , securely and stably fasten the cockpit transparent parts;
  • the fastening component is made of a material having considerable strength and a certain elasticity and toughness.
  • the deformation and stress change of the transparent part of the cabin due to the external impact load can be passed through the fastening component.
  • the release of pre-stress and the process of regeneration are buffered, which not only does not superimpose various complex stresses, but can eliminate or reduce the concentration of stress to a certain extent, and maintain the safety and stability of the cockpit structure. ;
  • the anti-escape structure is formed on the frame of the transparent part of the cockpit in the invention, and the limit structure is arranged between the anti-escape structure and the skeleton of the fuselage, so that the transparent part of the cockpit cannot escape from the fuselage skeleton after being subjected to the external impact load;
  • the use of the sliding buffer device of the present invention provides a very effective cushioning effect for the first time after the armed helicopter is subjected to an external impact load, which can significantly slow down and reduce the time of crushing of the transparent part of the cabin after being subjected to an external impact load.
  • the present invention engages the plane of the transparent part of the cockpit through the prestressed structure, and generates a rigid frame integrally formed therewith.
  • the rigid frame can provide outward for the transparent part of the cockpit. Pulling force to resist deformation caused by impact, and effectively slow down the time and extent of deformation, effectively maintain the integrity of the transparent part of the cabin, and improve the impact resistance of the transparent part of the cabin;
  • the hull transparent parts will realize the prestressed structure edging after processing, and the section will not be damaged during transportation and installation, and the transparent parts of the cockpit will always be the plane force, not the section force, and will not produce destructive internal stress. The safety of the cockpit transparent parts is guaranteed.
  • the present invention has made positive contributions to the improvement of the stability of the cockpit transparent member, the extension of the life span, and the reduction of the maintenance strength because of the above characteristics;
  • the prestressed fastening process of the present invention is to pre-stress the fastening component by tightening the relevant bolts.
  • the selection of the raw materials of each component and the geometric design are adopted in the previous design module. After the workers can tighten the relevant bolts in place, the preset tightening force can be obtained without being affected by uncertain factors such as the operating force, which greatly reduces the operating conditions and technical requirements.
  • FIG. 1 is a perspective view showing the overall structure of a helicopter of a helicopter cockpit transparent member mounting structure of the present invention
  • FIG. 2 is a cross-sectional view showing a connection structure of a cushioned cockpit transparent member and a mounting frame according to a first embodiment of the present invention
  • FIG. 3 is a perspective view showing a connection structure of a cushioned cockpit transparent member and a mounting frame according to a first embodiment of the present invention
  • Figure 4 is an exploded view of Figure 3;
  • Figure 5 is a perspective view showing the connection structure of the cushioned cockpit transparent member and the frame body according to the first embodiment of the present invention
  • Figure 6 is an exploded view of Figure 5;
  • Figure 7 is a plan view showing the connection structure of the cushioned cockpit transparent member and the frame body according to the first embodiment of the present invention.
  • Figure 8 is a plan view showing the fastening assembly of the present invention.
  • Figure 9 is a perspective view of a first pressure bar according to a first embodiment of the present invention.
  • Figure 10 is a perspective view of a second pressure strip of the present invention.
  • FIG. 11 is a schematic view showing the principle of the fastening process of the frame body and the transparent member in the transparent structure of the helicopter cockpit of the present invention
  • FIG. 12 is a schematic structural view of the pulley assembly of the present invention
  • 13-14 are schematic structural views of the system when the transparent member of the cockpit is impacted according to the present invention
  • Figure 15 is a cross-sectional view showing the connection structure of the transparent member and the mounting frame of the helicopter cockpit transparent member mounting structure according to the second embodiment of the present invention.
  • Figure 16 is a perspective view showing the connection structure of the transparent member and the mounting frame of the helicopter cockpit transparent member mounting structure according to the second embodiment of the present invention.
  • Figure 17 is an exploded view of Figure 16;
  • 18-20 are cross-sectional views of a frame of various embodiments of the present invention.
  • Figure 21 is a schematic view of another preferred embodiment of the fastening assembly of the helicopter cockpit transparent member fastening structure of the present invention. detailed description
  • a mounting frame 1 and a cabin transparent member 2 fixed to the helicopter body 5 through the mounting frame 1 are included ( Explosion-proof glass or bullet-proof glass, etc. may be selected, not limited); the mounting frame 1 is formed with a first mounting groove 10, the side of the cabin transparent member 2 is inserted into the first mounting groove 10; and the side of the cabin transparent member 2
  • the frame 3 is combined with the first mounting groove 10 to form an interfitting mounting structure.
  • the frame 3 includes a pressing component 31 and a fastening component 32, and the pressing component 31 and the cockpit transparent part are formed.
  • the mating compression fastening assembly 32 of 2 generates a pre-stress to secure the cabin transparency 2 .
  • the frame 3 and the mounting frame 1 form a limiting portion 3111, 111 that cooperates with each other; and at least one elastic buffer member 35 is disposed between the frame 3 and the mounting frame 1.
  • the bottom of the frame body 3 is provided with a sliding buffer device.
  • the sliding buffer device is provided with a pulley assembly 33; the cabin transparent member 2 to which the frame body 3 is mounted is placed on the lower frame 11 via the pulley assembly 33.
  • the limiting portions 3111, 111, the sliding cushioning device, and the elastic cushioning member 35 collectively form a mounting structure.
  • the pulley assembly 33 includes a pulley seat 331 and a pulley 332 disposed in the pulley seat 331; wherein the pulley seat 331 is fastened to the bottom of the first pressure bar 311 by bolts.
  • the fastening component 32 includes two arcuate arms 321 symmetrically clamped on both sides of the transparent part 2 of the cabin, and the material thereof should be selected from materials having considerable strength and elasticity and toughness, such as metal.
  • the arcuate arm 321 includes a first force arm 3211 and a second force arm 3212 connecting the first force arm 3211.
  • the joint of the force arm 3211 and the second force arm 3212 forms a sliding end 3213, and the sliding end 3213 has a circular arc surface or a sloped surface to ensure less resistance during the sliding process; the first force arm 3211 is far away
  • One side of the second force arm 3212 forms a compression end 3214, and the pressure receiving end 3214 extends downward to form a rotation positioning edge 3217.
  • the second force arm 3212 forms a fastening end 3215 on a side away from the first force arm 3211.
  • a pressing plate 3216 is coupled to the fastening end 3215, and a connecting portion of the pressing plate 3216 and the second force arm 3212 is recessed inwardly to form a pressing plate position adjusting portion 3218.
  • the pressing plate position adjusting portion 3218 can realize the pressing plate 3216 in the fastening process. Adjust its own position to make it more flat Transparent cockpit attachment member 2, the pressure receiving end of the first arm 3211 of the compression assembly 3214 to accept the compression fitting 31 and a transparent cockpit urge the first arm member 2 and the second arm 3212 3211 prestress generated.
  • the first force arm 3211 is a short straight arm
  • the second force arm 3212 is an arcuate arm
  • the thickness of the second force arm 3212 forms a thickness from the sliding end 3213 to the fastening end 3215. Thin gradient, this structure can ensure the full and uniform deformation of the entire curved arm, not easy to fold Broken.
  • a plurality of bolt holes are formed between the two pressure receiving ends 3214 of the fastening component 32.
  • An adhesive such as UV glue
  • a double-sided tape such as 3M glue
  • a cushion such as a rubber sheet
  • the direction in which the length of the cabin transparent member 2 extends in FIG. 4 is taken as the X-axis direction, and the thickness direction of the cabin transparent member 2 is taken as the Y-axis direction.
  • the height direction of the cabin transparent member 2 is taken as the Z-axis direction, and the X-axis is perpendicular to the Y-axis, and the Z-axis is perpendicular to the plane formed by the X-axis and the Y-axis.
  • the mounting frame 1 includes a frame 11 and a cover 12 fixed to the frame 11, and the frame 11 and the cover 12 cooperate to form a first mounting groove 10.
  • the compression assembly 31 includes a first pressure strip 311 and a second pressure strip 312.
  • the first pressure strip 311 is folded to form a limiting portion 3111, and the first pressure strip 311 has a cross section of ","; the middle portion of the surface of the second pressure strip 312 is coupled with the rotating positioning edge 3217 along the X-axis direction to provide two lengthwise rotations.
  • the positioning groove 3121 has a radius equal to or slightly larger than the radius of the rotating positioning edge 3217, so that when the system is in the pre-fastening and fastening state, the rotating positioning edge 3217 can be effectively positioned in the rotating positioning groove 3121. With the rotation, the two sliding ends 3213 are displaced only in the Y-axis direction on the inner side surface of the fixed plate 1211.
  • the two sliding ends 3213 of the arcuate arm 321 abut against the surface of the first pressure bar 311; the two pressure receiving ends 3214 of the arcuate arm 321 abut against the surface of the second pressure bar 312, and the two fastening ends 3215 of the arcuate arm 321 abut Relying on the two sides of the cockpit transparent part 2.
  • the first pressure strip 311 and the second pressure strip 312 are fastened by bolts, and the second pressure strip 312 presses the two pressure receiving ends 3214 of the bow arm 321 to the first pressure strip 311, and the two sliding ends 3213 of the arcuate arm 321 are
  • the surfaces of the first pressure strip 311 are displaced from each other, and the two fastening ends 3215 of the arcuate arms 321 are constrained by the cabin transparent member 2, thereby driving the first force arm 3211 and the second force arm 3212 to generate a pre-stressed fastening cabin transparent.
  • the cockpit transparent member 2 is adjusted in the X-axis direction and the Z-axis direction by the enclosed space 320.
  • the side of the cockpit transparent member 2 is recessed to form a second mounting groove 21 and is coupled with a T-shaped member 22;
  • the T-shaped member 22 includes a back plate 221 and a rib 222 formed on the back plate 221, and the rib 222 is embedded and passed through the structure.
  • the glue 25 is fixed in the second mounting groove 21, the back plate 221 abuts against the second pressure strip 312, and the gasket 24 is disposed between the back plate 221 and the cabin transparent member 2; the first pressure bar 311 and the fastening component 32 And the second pressure bar 312 forms a plurality of through holes, wherein the back plate 221 and the rib 222 form a plurality of screw holes that are engaged with the through hole; the first pressure bar 311, the fastening component 32 are fastened through the bolt, The second pressure strip 312 and the T-piece 22 thereby drive the first force arm 3211 and the second force arm 3212 of the fastening assembly 32 to generate a pre-stressed fastening cabin transparency 2.
  • the second pressure strip 312 presses the two pressure receiving ends 3214 of the arcuate arms 321 of the fastening assembly 32 toward the first pressure strip 311, and the two sliding ends 3213 of the arcuate arms 321 of the fastening assembly 32 are
  • the surfaces of the first pressure strip 311 are displaced from each other, and the two fastening ends 3215 of the arcuate arms 321 of the fastening assembly 32 are constrained by the cabin transparent member 2, thereby driving the first force arms 3211 and the second of the fastening assembly 32.
  • the force arm 3212 generates a pre-stressed fastening cabin transparency 2 .
  • the connection area of the T-shaped member 22 and the cabin transparent member 2 is increased, thereby increasing the frame 3 and the cockpit transparent member 2.
  • the overall joint strength, while the T-piece 22 increases the screw hole length for the bolts that are disposed between the first pressure strip 311, the fastening assembly 32, and the second pressure strip 312, so that the bolt has a longer pitch and is enhanced.
  • the strength and reliability of the screwing between the first pressure bar 311 and the second pressure bar 312 further ensure a stable and firm connection between the frame body 3 and the cabin transparent member 2.
  • the T-shaped piece 22 is first joined to the second side of each side of the cockpit transparent part 2 by the structural adhesive.
  • the groove 21 is mounted, and then the frame 3 is mounted, and the first pressure bar 311 is disposed on the outer side of the first force arm 3211 of the fastening component 32; the second pressure bar 312 is disposed on the first force arm 3211 and the T-piece of the fastening component 32.
  • the two sliding ends 3213 of the tight arching arms 321 are displaced away from each other on the surface of the first pressure strip, and the two fastening ends 3215 of the arcuate arms 321 are constrained by the cabin transparent member 2, thereby driving the arching arms 321 to generate prestressing tension.
  • a slide cushioning device is attached to the frame 3 at the bottom of the cockpit transparent member 2, which is a pulley assembly 33. Then, the cabin transparent member 2 to which the frame 3 has been mounted is disposed in the first mounting groove 10, and the limiting portions 3111, 111 are fitted to each other, and then the elastic cushioning member 35 is disposed between the frame 3 and the frame 11.
  • the cover plate 12 is mounted and fixed on the frame 11 to form a notch; at this time, the elastic buffering member 35 is located in a space surrounded by the frame body 3, the frame 11 and the cover plate 12; the cabin transparent member 2 is adjusted to a preset After the position, the rubber strip 14 is sealed at the notch.
  • the operation principle of the entire fastening process is further described below with reference to FIGS. 7 and 11.
  • the two compression ends 3214 of the arcuate arms 321 are displaced toward the first pressure bar 311 by the compression of the second pressure bar 312, and the rotation positioning edge 3217 is rotated.
  • the cooperation with the rotary positioning groove 3121 ensures that the compression end 3214 does not shift in the X and Y directions during the movement, and the distance between the compression ends 3214 of the two arch arms is controllable during the fastening process (
  • the two sliding ends 3213 abut against the surface of the first pressure strip 311 in the Y-axis direction, and the two fastening ends 3215 are displaced close to each other in the Y-axis direction until they abut against the cockpit.
  • the pressing end 3214 is displaced toward the first pressure strip 311, thereby driving the two sliding ends 3213 to continue away from each other in the Y-axis direction, and the two fastening ends 3215 are now abutted against the side of the cabin transparent member 2 and thereby received
  • the first force arm 3211 and the second force arm 3212 are deformed and generate pre-stress, and thus the cabin transparent member 2 with the stable pre-stressed structure and the frame 3 are tightened, and the cabin transparent member 2 is fastened. .
  • the cabin transparent member 2 of the present invention when the cabin transparent member 2 of the present invention is subjected to impact, if the impact force is small, the cabin transparent member 2 is not deformed and generates an impact direction displacement under the impact force, and the elastic buffer member 35 is pressed.
  • the rubber strip 14 serves as a cushioning effect, and the cabin transparent member 2 can be reset by the elastic cushioning member 35 after the impact force disappears.
  • the cockpit transparent member 2 of the present invention when the cockpit transparent member 2 of the present invention receives a large impact, since the cockpit transparent member 2 is made of a laminated glass such as bulletproof or explosion-proof glass, the cockpit transparent member is still bonded to the film by a film. At this time, although the middle portion of the cockpit transparent member 2 is deformed by the impact, the presence of the frame body 3 ensures that the periphery of the cockpit transparent member 2 is substantially free from deformation and contraction, thereby preventing preliminary escape; deformation of the cockpit transparent member 2 occurs.
  • connection structure of the second pressure bar 312 and the cabin transparent member 2 in this embodiment is as shown in FIG. 18.
  • a convex portion is formed in the middle of the second pressure bar 312 itself.
  • the T-shaped member 22 is not needed, and the rib of the second pressure strip 312 can be directly fixed in the second mounting groove 21 through the structural adhesive 25, and the spacer 24 is disposed at the second The second pressure strip 312 is between the cabin transparent member 2.
  • the second mounting groove 21 is not provided on the side of the cockpit transparent member 2, and the T-shaped member 22 is not required, and the cabin transparent member 2 is fastened only by the prestressed structure.
  • a helicopter cockpit transparent member mounting structure of the present invention has the same main structure as that of the first embodiment, except that the first embodiment is not provided.
  • a buffer structure and the mounting frame 1 forms a first pressure strip 311, and the first pressure strip 311 and the second pressure strip 312 are fastened by bolts to form a mounting structure to mount the cabin transparent member 2 in the first mounting slot. 10.
  • the second force arm 3212 of the fastening component 32 can be split into a plurality of jaws to better conform to the circular arc surface of the cabin transparent member 2.
  • the fastening assembly is used to secure the cabin transparent member 2 more firmly and stably without damaging the internal stress of the cabin transparent member 2.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Window Of Vehicle (AREA)
  • Connection Of Plates (AREA)
  • Tents Or Canopies (AREA)

Abstract

一种具防爆缓冲功能的武装直升机透明件紧固结构及紧固方法，包括安装框体（1）和通过安装框体（1）固定于直升机主体（5）上的座舱透明件（2），安装框体（1）形成有第一安装槽（10），座舱透明件（2）的侧边插设于第一安装槽（10）内，座舱透明件（2）侧边结合有一圈框体（3），框体（3）与第一安装槽（10）之间形成有相互配合的安装结构，框体（3）包括压迫组件（31）和紧固组件（32），通过压迫组件（31）和座舱透明件（2）的配合压迫紧固组件（32）生成预应力进而紧固座舱透明件（2）。该紧固结构强度高，适应面广。

Description

具防爆緩冲功能的武装直升机透明件紧固结构及紧固方法 技术领域
本发明涉及国防建设领域的军用直升机，尤指一种武装直升机座舱透明件的紧固结构及 紧固方法。 背景技术
武装直升机的座舱透明件主要包括固定的前风挡透明件及可活动的顶部或侧部风挡透 明件等， 而座舱透明件作为武装直升机上重要的光学结构件必须具备以下多种功能： 首先既 称为结构件， 必须具有足够的强度， 以对抗外来冲击荷载， 如子弹射击、 爆炸冲击、 飞鸟撞 击等； 第二是作为透明观察窗， 必须具有良好的光学性能， 包括透光度、 雾度、 分辨率、 光 学角偏差、 光学畸变、 重影、 双目视差、 双折射等多项重要的性能指标； 第三是必须具有使 用可靠性和较长的使用寿命。 其结构的完整性、 安装的牢固性和使用的稳定性与飞行员的生 存环境密切相关， 将直接影响到飞行安全和军事任务的完成。
目前武装直升机座舱透明件主要以螺栓连接或镶嵌的方式与机体安装， 而这两种安装方 式各有弊端。
其中镶嵌的方式是将座舱透明件放置于机身骨架的预留缝隙中，再以注入结构胶或填充 物等方式安装紧固， 这样虽然可以使安装难度降低， 且不会对座舱透明件自身内应力造成破 坏， 但无法使座舱透明件与直升机座舱连接为一体， 在受到外来冲击时座舱透明件很容易整 体逃逸。
而螺栓连接即是在座舱透明件上开孔并通过螺栓等五金件直接与机身骨架硬连接的方 式， 优点是强度较高、 整体性较好， 但是通常存在以下缺陷：
1、 武装直升机生产制造过程对座舱透明件的加工工艺要求较高， 一旦座舱透明件的加 工尺寸或弧度等出现少许误差而影响了其与机身骨架的贴合度；或者在座舱透明件上开设螺 栓孔的中心与机身骨架上相应孔的中心没有完全对准；或者在座舱透明件上开设的螺栓孔存 在裂紋、 缺口、 抛光不好等缺陷， 以上情况都会直接导致座舱透明件安装困难、 安装后存在 应力集中， 且座舱透明件制品的互换性差；
2、 座舱透明件在生产制造及加工过程中或多或少存在一定的缺陷或残余应力， 在运输、 仓储或装配的过程中都可能导致该缺陷或应力逐渐放大，若没有及时发现并进行有效处理或 报废， 一旦座舱透明件产生裂紋会使其抗拉强度和抗冲击韧性等性能明显下降， 给将来使用 来带极大的安全隐患；
3、 在座舱透明件上开孔就已经破坏了座舱透明件起初的内应力平衡， 螺孔附近成为强 度上的薄弱环节， 在加上可能叠加的加工缺陷与装配应力， 座舱透明件上很容易产生裂紋， 不但存在隐患而且对维修保养工作也是很严峻的考验。 当武装直升机座舱透明件受到如子弹射击、 爆炸冲击、 飞鸟撞击等外来冲击荷载时： 座 舱透明件若镶嵌于机身骨架上， 在受到外来冲击荷载时， 座舱透明件会因冲击向一边弯曲变 形， 当座舱透明件外形尺寸小于座舱边框的内径时， 座舱透明件会从机身骨架内整体脱落； 座舱透明件若以螺栓连接的方式安装于机身骨架上， 在受到外来冲击荷载时， 因座舱透明件 与机身骨架釆用螺栓连接处整体刚性较大，故在受到外来冲击瞬间的冲击荷载除小部分由座 舱透明件吸收外， 大部分将由座舱透明件通过螺栓传递至机身骨架， 因此座舱透明件螺栓孔 附近的应力将瞬间增大，与上述残余应力、装配应力等叠加后同样会使座舱透明件产生裂紋， 严重时可造成座舱透明件破坏。
在实战中， 武装直升机很容易受到地面及空中的炮火攻击， 若座舱透明件因炮火冲击荷 载而从机身骨架上逃逸或被破坏时， 直升机内的机组成员及仪器设备就暴露于炮火之中， 这 将直接威胁机组成员的人身安全， 影响军事任务的完成。
目前世界上武装直升机座舱透明件的紧固安装结构大致相同，只是在座舱透明件的材质 及制造工艺上有所改进， 座舱透明件与机身骨架的紧固安装结构并无根本改变， 上述问题依 然存在， 座舱透明件紧固安装结构亦成为困扰相关技术人员的一大难题。
然而随着时代的进步， 武装直升机在国家军事实力中的地位日益重要， 如果上述问题没 有合理的解决方案， 那么武装直升机的发展与进步也将受到影响。 针对此类关系到国家军事 实力的重要问题， 目前尚无比较合理的解决方式， 而本发明填补了此领域的空白。 发明内容
本发明的目的在于克服现有技术的缺陷， 而提供一种全新的通过边框加强的座舱透明件 的安装结构。
为解决上述技术问题， 本发明公开了一种武装直升机座舱透明件安装结构， 包括一安装 框体和通过所述安装框体固定于直升机主体的座舱透明件； 所述安装框体形成有第一安装 槽， 所述座舱透明件的侧边插设于所述第一安装槽内； 所述座舱透明件的侧边结合有一圏框 体， 所述框体与所述第一安装槽之间形成有相互配合的安装结构， 所述框体包括一压迫组件 和一紧固组件，通过所述压迫组件和座舱透明件的配合压迫所述紧固组件生成预应力进而紧 固所述座舱透明件。
本发明的进一步改进在于，所述紧固组件包括两个对称夹持于所述座舱透明件两侧的弓 形臂， 两弓形臂之间夹设形成一围合空间， 所述弓形臂包括第一力臂与连接所述第一力臂的 第二力臂， 所述第一力臂与所述第二力臂的连接处形成滑移端， 所述第一力臂于远离所述第 二力臂的一侧形成受压端， 所述第二力臂于远离所述第一力臂的一侧形成紧固端， 所述第一 力臂的受压端接受所述压迫组件的压迫并配合所述座舱透明件驱使所述第一力臂与第二力 臂生成预应力。
本发明的进一步改进在于， 所述压迫组件包括一第一压力条和一第二压力条； 所述弓形臂的两滑移端抵靠于所述第一压力条表面；所述弓形臂的两受压端抵靠于所述 第二压力条的外侧表面， 所述弓形臂的两紧固端^ I氏靠于所述座舱透明件两侧面；
通过螺栓紧固所述第一压力条与所述第二压力条，所述第二压力条压迫所述弓形臂的两 受压端向所述第一压力条方向位移，所述弓形臂的两滑移端于所述第一压力条的表面发生相 互远离的位移， 所述弓形臂的两紧固端受到所述座舱透明件的限位， 从而驱使所述第一力臂 与所述第二力臂生成预应力紧固所述座舱透明件。
本发明的进一步改进在于，所述座舱透明件通过所述围合空间进行一第一方向与一第二 方向的位置调整。
本发明的进一步改进在于， 所述安装框体形成所述第一压力条， 通过螺栓紧固所述第一 压力条与所述第二压力条形成所述安装结构进而将所述座舱透明件安装于所述第一安装槽 内。
本发明的进一步改进在于， 所述第一压力条与所述安装框体形成相互配合的限位部； 所 述框体与所述安装框体之间设置有至少一弹性緩冲件。
本发明的进一步改进在于， 所述框体的底部设置有滑动緩冲装置。
本发明的进一步改进在于， 所述安装框体包括框架和固定于所述框架上的盖板， 所述框 架和所述盖板配合形成所述第一安装槽。
本发明的进一步改进在于，所述座舱透明件的侧边凹陷形成第二安装槽并结合有一 T型 件； 所述 T型件包括一背板和形成于所述背板的凸条， 所述凸条嵌设于所述第二安装槽内， 所述背板抵靠所述第二压力条， 通过螺栓贯穿紧固所述第一压力条、 所述第二压力条以及所 述 T型件的背板与凸条，从而驱使所述紧固组件的第一力臂与第二力臂生成预应力紧固所述 座舱透明件。
本发明的进一步改进在于， 所述座舱透明件和所述背板之间设有一垫片。
本发明的进一步改进在于， 所述弓形臂的滑移端呈圆弧面或斜面。
本发明的进一步改进在于，所述第二力臂的厚度自所述滑移端至所述紧固端形成一由厚 至薄的渐变。
本发明的进一步改进在于，所述紧固组件的弓形臂的受压端向下延伸形成有一旋转定位 棱， 所述第二压力条对应所述紧固组件的所述旋转定位棱形成有旋转定位槽。
本发明由于釆用了以上技术方案， 使其具有的有益效果是：
1、 本发明通过预应力结构咬合座舱透明件平面， 并在座舱透明件周边生成了一圏与其 合为一体的刚性边框， 并通过该边框将座舱透明件固定于机身骨架， 由此形成一种全新的具 备预应力緩冲功能的座舱透明件与座舱一起的整体受力结构，有效地将座舱透明件承受的荷 载通过预应力结构传递至机身， 保证了座舱结构的完整性；
2、 本发明中座舱透明件通过预应力边框与机身骨架实施紧固， 座舱透明件上不再需要 开设螺栓孔， 不会破坏座舱透明件自身的内应力平衡， 保持了座舱透明件原有的强度、 没有 应力薄弱点， 不会产生因为螺栓孔的加工缺陷等而导致的装配困难以及装配过程的应力集 中； 在使用过程中也不存在上述应力的叠加与扩大；
3、 在本发明中， 座舱透明件以位置可调的方式紧固于机身骨架， 且紧固组件对座舱透 明件的生产制造误差有一定的宽容度， 因此使得座舱透明件与骨架的装配更便捷、避免装配 应力的产生， 同时可大幅提高座舱透明件制品的装配互换性；
4、 在实际运用当中， 部分武装直升机座舱透明件边缘呈圆弧面。 在本发明中， 紧固组 件第二力臂分裂成多个夹爪， 可使紧固组件中的紧固端更贴合于座舱透明件的圆弧面， 使紧 固组件在不破坏座舱透明件自身内应力的前提下， 更牢固与稳定地紧固座舱透明件；
5、 本发明中紧固组件选用具有相当强度， 同时兼具一定弹性与韧性的材料， 在飞行过 程中， 座舱透明件由于受到外来冲击荷载而产生的变形与应力变化， 均可通过紧固组件自身 蕴藏的预应力的释放与再生的过程进行緩冲， 不仅不会使各种复杂的应力相互叠加， 相反能 在一定程度起到消除或减小应力集中的作用， 保持座舱结构的安全与稳定；
6、 本发明中座舱透明件边框上生成一防逃逸结构， 防逃逸结构与机身骨架之间设有限 位结构， 使得座舱透明件受到外来冲击荷载后无法整体自机身骨架中逃出；
7、 本发明中滑动緩冲装置的釆用在武装直升机受到外来冲击荷载后的第一时间提供非 常有效地緩冲作用， 可明显减緩与降低座舱透明件受到外来冲击荷载后破碎的时间与概率；
8、 本发明通过预应力结构咬合座舱透明件平面， 在周边生成了一圏与其为一体的刚性 边框， 当座舱透明件受到外来冲击荷载时， 所述刚性边框可以为座舱透明件提供向外的拉力 来抵御冲击造成的形变， 并且有效减緩形变产生的时间与程度 , 有效地保持座舱透明件的完 整性， 提高座舱透明件的抗冲击能力；
9、 座舱透明件加工后即实现预应力结构包边， 运输及安装使用过程中不会造成断面损 坏， 且座舱透明件始终为平面受力、 而非断面受力， 不产生破坏性内应力， 座舱透明件自身 安全性能得到了保障。
10、 本发明因为具有上述特点， 对座舱透明件稳定性的提高、 寿命的延长、 维修保养强 度的降低等都做出了积极的贡献；
11、本发明预应力紧固的实施过程是通过拧紧相关螺栓来压迫紧固组件而使其产生预应 力， 在具体操作时， 通过前期的设计模块中对各个组件原材料的选择及几何形状的设计， 后 期工人只需将相关螺栓拧紧到位即可得到预设的紧固力，无须受到操作力度等不确定因素的 影响， 大大降低了操作条件和技术要求。 附图说明
图 1为本发明直升机座舱透明件安装结构的直升机整体结构立体图；
图 2为本发明第一实施例带緩冲的座舱透明件与安装框体连接结构剖面图；
图 3为本发明第一实施例带緩冲的座舱透明件与安装框体连接结构立体图；
图 4为图 3的分解图；
图 5为本发明第一实施例带緩冲的座舱透明件与框体的连接结构立体图；
图 6为图 5的分解图；
图 7为本发明第一实施例带緩冲的座舱透明件与框体的连接结构平面图；
图 8为本发明紧固组件的平面示意图；
图 9为本发明第一实施例的第一压力条的立体图；
图 10为本发明第二压力条的立体图；
图 11为本发明直升机座舱透明件安装结构中框体与透明件紧固过程原理示意图； 图 12为本发明滑轮组件的结构示意图； 图 13-14为本发明座舱透明件受到冲击时的系统结构示意图；
图 15为本发明第二实施例的直升机座舱透明件安装结构的透明件与安装框体连接结构 剖面图；
图 16为本发明第二实施例的直升机座舱透明件安装结构的透明件与安装框体连接结构 立体图；
图 17为图 16的分解图；
图 18-20为本发明多种实施例的框体截面图。
图 21为本发明的直升机座舱透明件紧固结构中紧固组件的另一较佳实施例示意图。 具体实施方式
下面结合具体实施例对本发明作进一步说明。
请参阅图 1-2, 在本发明一种直升机座舱透明件安装结构的第一较佳实施例中， 包括一 安装框体 1和通过安装框体 1固定于直升机主体 5的座舱透明件 2 (可选用防爆玻璃或防弹 玻璃等、 并不限定） ； 安装框体 1形成有第一安装槽 10, 座舱透明件 2的侧边插设于第一 安装槽 10内； 且座舱透明件 2的侧边结合有一圏框体 3 , 框体 3与第一安装槽 10之间形成 有相互配合的安装结构， 框体 3包括一压迫组件 31和一紧固组件 32, 通过压迫组件 31和 座舱透明件 2的配合压迫紧固组件 32生成预应力进而紧固座舱透明件 2。 框体 3与安装框 体 1形成相互配合的限位部 3111、 111； 框体 3与安装框体 1之间设置有至少一弹性緩冲件 35。
且框体 3底部设置有滑动緩冲装置， 本实施例中滑动緩冲装置釆用滑轮组件 33; 安装 有框体 3的座舱透明件 2通过滑轮组件 33搁置于下部的框架 11上。 本实施例中， 限位部 3111、 111、 滑动緩冲装置以及弹性緩冲件 35共同形成安装结构。
结合图 12所示， 滑轮组件 33包括一滑轮座 331和设置于滑轮座 331内的滑轮 332; 其 中滑轮座 331通过螺栓紧固于第一压力条 311底部。
请参阅图 7-8 , 紧固组件 32包括两个对称夹持于座舱透明件 2两侧的弓形臂 321 , 其材 料应选用具有相当强度， 同时兼具一定弹性与韧性的材料， 如金属、 工程塑料、 高分子材料 等； 两弓形臂 321之间夹设形成一围合空间 320, 弓形臂 321 包括一第一力臂 3211与一连 接第一力臂 3211 的第二力臂 3212, 第一力臂 3211与第二力臂 3212的连接处形成滑移端 3213 , 该滑移端 3213呈圆弧面或斜面可以在保证在滑移过程中产生的阻力更小； 第一力臂 3211于远离第二力臂 3212的一侧形成受压端 3214, 该受压端 3214向下延伸形成有旋转定 位棱 3217; 第二力臂 3212于远离第一力臂 3211的一侧形成紧固端 3215 , 紧固端 3215上结 合有压板 3216, 且压板 3216与第二力臂 3212的连接区域向内凹陷形成一压板位置调节区 3218 , 通过该压板位置调节区 3218可在紧固过程中实现压板 3216微小的自身位置调节， 以 使其更平整地贴附座舱透明件 2, 第一力臂 3211的受压端 3214接受压迫组件 31的压迫并 配合座舱透明件 2驱使第一力臂 3211与第二力臂 3212生成预应力。在本实施例中第一力臂 3211为一短直臂， 第二力臂 3212为一弧形臂， 且第二力臂 3212的厚度自滑移端 3213至紧 固端 3215形成一由厚至薄的渐变， 该种结构可以保证整个弧形臂充分和均匀形变， 不易折 断。 紧固组件 32的两受压端 3214之间配合形成有复数个螺栓孔。 压板 3216与座舱透明件 2之间可涂抹粘结胶（如 UV胶）或夹设双面胶（如 3M胶）或塾设緩冲垫（如橡胶片） 。
请参阅图 3-10, 为便于描述现在该实施例中作以下定义： 以图 4中座舱透明件 2的通长 延伸方向作为 X轴方向， 以座舱透明件 2的厚度方向作为 Y轴方向， 以座舱透明件 2的高 度方向作为 Z轴方向， 且 X轴垂直于 Y轴， Z轴垂直于 X轴与 Y轴构成的平面。
安装框体 1包括框架 11和固定于框架 11上的盖板 12, 框架 11和盖板 12配合形成第 一安装槽 10。
压迫组件 31 包括一第一压力条 311和一第二压力条 312。 其中第一压力条 311翻折形 成限位部 3111 , 第一压力条 311截面呈 " ， 型； 第二压力条 312的表面中部沿 X轴方向 配合旋转定位棱 3217设置了两条通长的旋转定位槽 3121 , 该旋转定位槽 3121的半径等于 或略大于旋转定位棱 3217的半径， 这样当系统分别处于预紧固与紧固状态时， 旋转定位棱 3217可以有效地在旋转定位槽 3121 内定位与进行转动， 两滑移端 3213才会在固定板 1211 内侧表面仅沿 Y轴方向位移。
弓形臂 321的两滑移端 3213抵靠于第一压力条 311的表面；弓形臂 321的两受压端 3214 抵靠于第二压力条 312的表面， 弓形臂 321的两紧固端 3215抵靠于座舱透明件 2两侧面。
通过螺栓紧固第一压力条 311与第二压力条 312, 第二压力条 312压迫弓形臂 321的两 受压端 3214向第一压力条 311方向位移， 弓形臂 321的两滑移端 3213于第一压力条 311表 面发生相互远离的位移， 弓形臂 321的两紧固端 3215受到座舱透明件 2的限位， 从而驱使 第一力臂 3211与第二力臂 3212生成预应力紧固座舱透明件 2; 座舱透明件 2通过围合空间 320进行 X轴方向与 Z轴方向的位置调整。
座舱透明件 2的侧边凹陷形成第二安装槽 21并结合有一 T型件 22; T型件 22包括一背 板 221和形成于背板 221的凸条 222, 凸条 222嵌设并通过结构胶 25固定于第二安装槽 21 内， 背板 221抵靠第二压力条 312, 且背板 221与座舱透明件 2之间垫设有垫片 24; 第一压 力条 311、 紧固组件 32和第二压力条 312形成相互配合的复数个通孔， 背板 221与凸条 222 形成与该通孔配合的复数个螺孔； 通过螺栓贯穿紧固第一压力条 311、 紧固组件 32、 第二压 力条 312以及 T型件 22, 从而驱使紧固组件 32的第一力臂 3211与第二力臂 3212生成预应 力紧固座舱透明件 2。 通过螺栓的紧固， 第二压力条 312压迫紧固组件 32的弓形臂 321的 两受压端 3214向第一压力条 311方向位移， 紧固组件 32的弓形臂 321的两滑移端 3213于 第一压力条 311表面发生相互远离的位移， 紧固组件 32的弓形臂 321的两紧固端 3215受到 座舱透明件 2的限位， 从而驱使紧固组件 32的第一力臂 3211与第二力臂 3212生成预应力 紧固座舱透明件 2。
由于 T型件 22的凸条 222通过结构胶 25结合于第二安装槽 21内增大了 T型件 22与座 舱透明件 2的连接面积， 从而加大了框体 3与座舱透明件 2的整体连接强度， 同时 T型件 22为穿设于第一压力条 311、 紧固组件 32和第二压力条 312之间的螺栓增加了螺孔长度， 使得该螺栓拥有更长的螺距，增强了第一压力条 311与第二压力条 312之间螺接的强度及可 靠性， 进一步保证了框体 3与座舱透明件 2的稳定牢固连接。
在座舱透明件 2出厂前， 先通过结构胶将 T型件 22结合于座舱透明件 2各侧边的第二 安装槽 21 , 接着安装框体 3 , 将第一压力条 311设置于紧固组件 32第一力臂 3211的外侧； 第二压力条 312设置于紧固组件 32第一力臂 3211和 T型件 22背板 221之间， 紧固组件 32 弓形臂 321的两紧固端 3215抵靠于座舱透明件 2的两侧面； 然后通过依次穿设于第一压力 条 311、 紧固组件 32、 第二压力条 312和 T型件 22的螺栓紧固第一压力条 311和第二压力 条 312, 第二压力条 312压迫紧固组弓形臂 321的两受压端 3214向第一压力条方向位移， 紧弓形臂 321的两滑移端 3213于第一压力条的表面发生相互远离的位移， 弓形臂 321的两 紧固端 3215受到座舱透明件 2的限位， 从而驱使弓形臂 321生成预应力紧固座舱透明件 2。 在座舱透明件 2底部的框体 3上安装滑动緩冲装置， 本实施例为滑轮组件 33。 然后将已安 装有框体 3的座舱透明件 2设置于第一安装槽 10内 , 并使得限位部 3111、 111相互配合， 然后将弹性緩冲件 35设置于框体 3和框架 11之间； 再将盖板 12安装固定于框架 11上， 形 成槽口； 此时弹性緩冲件 35位于框体 3、 框架 11和盖板 12围成的空间内； 将座舱透明件 2 调整到预设位置后， 在槽口设置橡胶条 14密封。
下面配合图 7、 11来进一步说明整个紧固过程的工作原理， 弓形臂 321的两受压端 3214 在第二压力条 312的压迫作用下向第一压力条 311方向位移， 通过旋转定位棱 3217与旋转 定位槽 3121的配合保证了受压端 3214在移动过程中不发生 X、 Y轴方向上的偏移， 两个弓 形臂受压端 3214之间的距离在紧固过程中是可控（不变）的， 同时两滑移端 3213抵靠于第 一压力条 311表面沿 Y轴方向发生相互远离的位移， 而两紧固端 3215沿 Y轴方向发生相互 靠近的位移直至抵靠于座舱透明件 2的侧面， 因此两紧固端 3215的压板 3216间的距离也是 可控的， 其在座舱透明件 2上的紧固位置点也是可控的； 进一步通过第二压力条 312压迫两 受压端 3214向第一压力条 311方向位移，进而驱使两滑移端 3213沿 Y轴方向继续相互远离， 而两紧固端 3215此时抵靠于座舱透明件 2的侧面并由此受到限位，第一力臂 3211及第二力 臂 3212由此发生形变并生成预应力， 至此具有稳定预应力结构的座舱透明件 2与框体 3达 到紧固状态，座舱透明件 2获得紧固。 同样的， 当预应力需要解除时， 只要将相应螺栓松开， 弓形臂 321的形变会恢复到之前未紧固状态， 此时预应力自动消失， 整个直升机座舱透明件 安装结构的部件都是无损耗的和可重复使用的， 不仅节约了成本， 同时也非常环保。
请参阅图 13 , 当本发明的座舱透明件 2受到冲击时， 若冲击力较小， 座舱透明件 2不 发生形变并在冲击力的作用下产生冲击方向的位移，压迫弹性緩冲件 35和橡胶条 14起到緩 冲的效果， 冲击力消失后座舱透明件 2可在弹性緩冲件 35的作用下复位。
请参阅图 14, 当本发明的座舱透明件 2受到的冲击较大， 由于座舱透明件 2釆用防弹 或防爆玻璃等夹胶玻璃， 所以座舱透明件破碎后仍靠胶片粘接为一整体， 此时虽然座舱透明 件 2的中部受到冲击发生形变，但是由于框体 3的存在保证了座舱透明件 2的周边基本未产 生形变收缩， 从而防止了初步的逃逸； 当座舱透明件 2发生的形变较大， 从而带动其周边发 生逃逸出第一安装槽 10的位移时， 座舱透明件 2的周边又进一步通过框体 3上的限位结构 3111配合槽口进行限位； 进而防止了座舱透明件 2受到冲击后的整块脱出。
请参阅图 18-20, 本实施例中第二压力条 312与座舱透明件 2的连接结构如图 18所示； 另外也可如图 19所示， 在第二压力条 312本身的中部形成凸条， 此时无需 T型件 22, 可直 接将第二压力条 312的凸条通过结构胶 25固定于第二安装槽 21内， 此时垫片 24塾设于第 二压力条 312与座舱透明件 2之间。 也可如图 20所示， 座舱透明件 2的侧边不开设第二安 装槽 21 , 也无需 T型件 22, 只通过预应力结构对座舱透明件 2进行紧固。
请参阅图 15-17, 在本发明的第二较佳实施例中， 本发明的一种直升机座舱透明件安装 结构其主要结构与第一实施例相同， 区别在于： 不具备第一实施例中的緩冲结构， 且安装框 体 1形成第一压力条 311 , 通过螺栓紧固所述第一压力条 311与第二压力条 312形成安装结 构进而将座舱透明件 2安装于第一安装槽内 10。
进一步参阅图 21所示， 当座舱透明件 2边缘呈圆弧面时， 紧固组件 32的第二力臂 3212 可以分裂成多个夹爪， 以更贴合于座舱透明件 2的圆弧面， 使紧固组件在不破坏座舱透明件 2自身内应力的前提下， 更牢固与稳定地紧固座舱透明件 2。
以上结合附图实施例对本发明进行了详细说明，本领域普通技术人员可根据上述说明对 本发明做出种种变化例。 因而， 实施例中的某些细节不应构成对本发明的限定， 本发明将以 所附权利要求书界定的范围作为本发明的保护范围。

Claims

权 利 要 求 书
1. 一种具防爆緩冲功能的武装直升机透明件紧固结构， 包括一安装框体和通过所述安 装框体固定于直升机主体的座舱透明件； 其特征在于， 所述安装框体形成有第一安装槽， 所 述座舱透明件的侧边插设于所述第一安装槽内； 所述座舱透明件的侧边结合有一圏框体， 所 述框体与所述第一安装槽之间形成有相互配合的安装结构，所述框体包括一压迫组件和一紧 固组件，通过所述压迫组件和座舱透明件的配合压迫所述紧固组件生成预应力进而紧固所述 座舱透明件。
2. 如权利要求 1 所述的武装直升机座舱透明件紧固结构， 其特征在于， 所述紧固组件 包括两个对称夹持于所述座舱透明件两侧的弓形臂， 两弓形臂之间夹设形成一围合空间， 所 述弓形臂包括第一力臂与连接所述第一力臂的第二力臂，所述第一力臂与所述第二力臂的连 接处形成滑移端， 所述第一力臂于远离所述第二力臂的一侧形成受压端， 所述第二力臂于远 离所述第一力臂的一侧形成紧固端，所述第一力臂的受压端接受所述压迫组件的压迫并配合 所述座舱透明件驱使所述第一力臂与第二力臂生成预应力。
3. 如权利要求 2 所述的武装直升机座舱透明件紧固结构， 其特征在于， 所述压迫组件 包括一第一压力条和一第二压力条；
所述弓形臂的两滑移端抵靠于所述第一压力条表面；所述弓形臂的两受压端抵靠于所述 第二压力条的外侧表面， 所述弓形臂的两紧固端^ I氏靠于所述座舱透明件两侧面；
通过螺栓紧固所述第一压力条与所述第二压力条，所述第二压力条压迫所述弓形臂的两 受压端向所述第一压力条方向位移，所述弓形臂的两滑移端于所述第一压力条的表面发生相 互远离的位移， 所述弓形臂的两紧固端受到所述座舱透明件的限位， 从而驱使所述第一力臂 与所述第二力臂生成预应力紧固所述座舱透明件。
4. 如权利要求 3 所述的武装直升机座舱透明件紧固结构， 其特征在于， 所述座舱透明 件通过所述围合空间进行一第一方向与一第二方向的位置调整。
5. 如权利要求 4 所述的武装直升机座舱透明件紧固结构， 其特征在于， 所述安装框体 形成所述第一压力条，通过螺栓紧固所述第一压力条与所述第二压力条形成所述紧固结构进 而将所述座舱透明件安装于所述第一安装槽内。
6. 如权利要求 4 所述的武装直升机座舱透明件紧固结构， 其特征在于， 所述第一压力 条与所述安装框体形成相互配合的限位部；所述框体与所述安装框体之间设置有至少一弹性 緩冲件。
7. 如权利要求 6所述的武装直升机座舱透明件紧固结构， 其特征在于： 所述框体的底 部设置有滑动緩冲装置。
8. 如权利要求 1~7 中任一项所述的武装直升机座舱透明件紧固结构， 其特征在于， 所 述安装框体包括框架和固定于所述框架上的盖板，所述框架和所述盖板配合形成所述第一安 装槽。
9. 如权利要求 8所述的武装直升机座舱透明件紧固结构， 其特征在于： 所述座舱透明 件的侧边凹陷形成第二安装槽并结合有一 T型件；所述 T型件包括一背板和形成于所述背板 的凸条， 所述凸条嵌设于所述第二安装槽内， 所述背板抵靠所述第二压力条， 通过螺栓贯穿 紧固所述第一压力条、所述第二压力条以及所述 τ型件的背板与凸条，从而驱使所述紧固组 件的第一力臂与第二力臂生成预应力紧固所述座舱透明件。
10. 如权利要求 9所述的武装直升机座舱透明件紧固结构， 其特征在于所述座舱透明件 和所述背板之间设有一垫片。
11. 如权利要求 2~7中任一项所述的武装直升机座舱透明件紧固结构， 其特征在于： 所 述弓形臂的滑移端呈圆弧面或斜面。
12. 如权利要求 2~7中任一项所述的武装直升机座舱透明件紧固结构， 其特征在于所述 第二力臂的厚度自所述滑移端至所述紧固端形成一由厚至薄的渐变。
13. 如权利要求 2~7中任一项所述的武装直升机座舱透明件紧固结构， 其特征在于： 所 述紧固组件的弓形臂的受压端向下延伸形成有一旋转定位棱，所述第二压力条对应所述紧固 组件的所述旋转定位棱形成有旋转定位槽。
14. 一种应用权利要求 1~7中任一项的紧固结构对武装直升机座舱透明件进行紧固的方 法。
PCT/CN2014/077243 2013-05-16 2014-05-12 具防爆缓冲功能的武装直升机透明件紧固结构及紧固方法 WO2014183614A1 (zh)

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