阅读说明：本技术 一种长弦弹翼高超声速飞行器翼面折叠装置 (Wing surface folding device of long-chord missile wing hypersonic aircraft ) 是由 不公告发明人 于 2021-04-13 设计创作，主要内容包括：本申请提供一种长弦弹翼高超声速飞行器翼面折叠装置,包括底座、弹翼和整流罩；底座上对应弹翼设有安装座；弹翼可转动安装在安装座上,且与安装之间设有隔热密封组件；安装座上对应弹翼设有用于控制弹翼打开的扭转组件和用于限制弹翼转动的定位组件；整流罩安装在底座上,用于对安装座进行密封。根据本申请实施例提供的技术方案,通过扭转组件可实现将折叠的弹翼自动展开,配合定位组件,可对展开的弹翼进行定位限制,保证弹翼处于展开状态；因此,弹翼处于折叠状态时,可安装在发动机表面,并装入发射筒中,发射后,弹翼自动展开并固定；结合隔热密封组件和整流罩还能实现所需的隔热与密封,有效解决了现有技术中存在的缺陷。(The application provides a wing surface folding device of a long-chord missile wing hypersonic flight vehicle, which comprises a base, missile wings and a fairing; the base is provided with a mounting seat corresponding to the missile wing; the missile wing can be rotatably arranged on the mounting seat, and a heat insulation sealing assembly is arranged between the missile wing and the mounting seat; a torsion component for controlling the opening of the missile wing and a positioning component for limiting the rotation of the missile wing are arranged on the mounting seat corresponding to the missile wing; the fairing is installed on the base and used for sealing the installation seat. According to the technical scheme provided by the embodiment of the application, the folded missile wing can be automatically unfolded through the torsion assembly, and the unfolded missile wing can be positioned and limited by matching with the positioning assembly, so that the missile wing is ensured to be in an unfolded state; therefore, when the missile wing is in a folded state, the missile wing can be installed on the surface of an engine and is installed in a launching tube, and after being launched, the missile wing automatically unfolds and is fixed; the required heat insulation and sealing can be realized by combining the heat insulation sealing assembly and the fairing, and the defects in the prior art are effectively overcome.)

1. A wing surface folding device of a long-chord missile wing hypersonic aerocraft is characterized by comprising a base (100), a missile wing (200) and a fairing (300); the base (100) is provided with a mounting seat (110) corresponding to the missile wing (200); the missile wing (200) is rotatably arranged on the mounting seat (110), and a heat insulation sealing assembly is arranged between the missile wing and the mounting seat (110); a torsion assembly for controlling the opening of the missile wing (200) and a positioning assembly for limiting the rotation of the missile wing (200) are arranged on the mounting seat (110) corresponding to the missile wing (200); the fairing (300) is mounted on the base (100) for sealing the mount (110).

2. The airfoil folding device for the long-chord missile-wing hypersonic flight vehicle as claimed in claim 1, wherein the missile wing (200) is connected with the mounting base (110) through a rotating shaft (210); the rotating shaft (210) is rotatably arranged on the mounting base (110), and one end of the rotating shaft is connected with the missile wing (200) through threads.

3. The airfoil folding device for the long-chord missile-wing hypersonic flight vehicle as claimed in claim 2, wherein an auxiliary seat (120) is further arranged on the base (100) corresponding to the rotating shaft (210); the rotating shaft (210) penetrates through the mounting seat (110), and one end, far away from the missile wing (200), of the rotating shaft is rotatably mounted on the auxiliary seat (120).

4. The long-chord missile wing hypersonic aircraft airfoil folding device of claim 3, wherein the torsion assembly comprises a torsion spring (130); the torsion spring (130) is sleeved on the rotating shaft (210) and is positioned between the mounting seat (110) and the auxiliary seat (120); and two ends of the torsion spring (130) are respectively butted with the missile wing (200) and the auxiliary seat (120).

5. The airfoil folding device of the long-chord missile wing hypersonic flight vehicle as claimed in claim 4, wherein a torsion arm and a limit arm are respectively arranged at two ends of the torsion spring (130); the torsion arm is arranged along the axial direction of the torsion spring (130); the limiting arm is arranged along the tangential direction of the torsion spring (130).

6. The airfoil folding device for the long-chord missile-wing hypersonic flight vehicle as claimed in claim 5, wherein a limit pin (121) is arranged on the auxiliary seat (120) corresponding to the limit arm; the missile wing (200) is provided with a butt joint hole corresponding to the torsion arm; and the mounting seat (110) is provided with a through arc-shaped through hole corresponding to the torque arm.

7. The long-chord missile-wing hypersonic aircraft airfoil folding device according to claim 1, wherein the positioning assembly comprises a spring pin (140), a compression spring (141) and a compression nut (142); the mounting seat (110) is provided with corresponding mounting holes corresponding to the spring pins (140); the compression spring (141) is positioned in the through hole and is compressed at one end, far away from the missile wing (200), of the spring pin (140) through the compression nut (142).

8. The airfoil folding device for the long-chord missile-wing hypersonic flight vehicle as claimed in claim 7, wherein the missile wing (200) is provided with a corresponding spring pin hole (201) corresponding to the spring pin (140).

9. The long-chord missile-wing hypersonic aircraft airfoil folding device of claim 1, wherein the heat-insulating seal assembly comprises a dynamic seal ring (220); the missile wing (200) is provided with a mounting groove (202) corresponding to the dynamic seal ring (220).

Technical Field

The application relates to the technical field of hypersonic aircrafts, in particular to a wing surface folding device of a long-chord missile wing hypersonic aircraft.

Background

The folding device of the existing aircraft has various forms, but is mostly used for the low-Mach aircraft with low requirements on aerodynamic appearance and heat insulation, most parts of the folding device of the existing aircraft are exposed outside, and the folding device is not suitable for the hypersonic aircraft due to the problem of heat insulation sealing. The wing folding device of part of the fighter plane solves the problem of heat insulation and sealing, but the wing surface of the wing is generally thicker, so that the folding device is suitable for being arranged at the opposite position of the wing surface, and under the condition of the elastic wing with the thinner part of the wing surface, the adoption of the folding device has very strict requirements on the strength and the rigidity of a rotating shaft, and even the problem that the folding device cannot be realized under the existing material and process technical conditions can be caused.

Disclosure of Invention

In view of the above-identified deficiencies or inadequacies in the prior art, it would be desirable to provide a long-chord missile wing hypersonic aircraft airfoil folding device.

The application provides a wing surface folding device of a long-chord missile wing hypersonic flight vehicle, which comprises a base, missile wings and a fairing; the base is provided with a mounting seat corresponding to the missile wing; the missile wing can be rotatably arranged on the mounting seat, and a heat insulation sealing assembly is arranged between the missile wing and the mounting seat; a torsion component for controlling the opening of the missile wing and a positioning component for limiting the rotation of the missile wing are arranged on the mounting seat corresponding to the missile wing; the fairing is installed on the base and used for sealing the installation seat.

Furthermore, the missile wing is connected with the mounting seat through a rotating shaft; the pivot is rotatable to be installed on the mount pad, and one end passes through threaded connection with the missile wing.

Furthermore, an auxiliary seat is arranged on the base corresponding to the rotating shaft; the pivot runs through the mount pad, keeps away from the rotatable installation of one end of missile wing on supplementary seat.

Further, the torsion assembly includes a torsion spring; the torsional spring is sleeved on the rotating shaft and is positioned between the mounting seat and the auxiliary seat; two ends of the torsion spring are respectively butted with the elastic wing and the auxiliary seat.

Furthermore, both ends of the torsion spring are respectively provided with a torsion arm and a limiting arm; the torsion arm is arranged along the axial direction of the torsion spring; the limiting arm is arranged along the tangential direction of the torsion spring.

Furthermore, a limiting pin is arranged on the auxiliary seat corresponding to the limiting arm; the missile wing is provided with a butt joint hole corresponding to the torsion arm; the mounting seat is provided with a through arc-shaped through hole corresponding to the torque arm.

Furthermore, the positioning assembly comprises a spring pin, a pressure spring and a compression nut; the mounting seat is provided with corresponding mounting holes corresponding to the spring pins; the pressure spring is located the through-hole, compresses tightly at the spring catch keep away from the one end department of missile wing through gland nut.

Furthermore, the missile wing is provided with a corresponding spring pin hole corresponding to the spring pin.

Further, the heat insulation sealing assembly comprises a dynamic sealing ring; the missile wing is provided with a mounting groove corresponding to the movable sealing ring.

The application has the advantages and positive effects that:

according to the technical scheme, the folded missile wing can be automatically unfolded through the torsion assembly, and the unfolded missile wing can be positioned and limited by matching with the positioning assembly, so that the missile wing is ensured to be in an unfolded state; therefore, when the missile wing is in a folded state, the missile wing can be installed on the surface of an engine and is installed in a launching tube, and after being launched, the missile wing automatically unfolds and is fixed; the required heat insulation and sealing can be realized by combining the heat insulation sealing assembly and the fairing, and the defects in the prior art are effectively overcome.

Drawings

FIG. 1 is a schematic structural diagram of a folding device for an airfoil of a long-chord missile-wing hypersonic flight vehicle according to an embodiment of the present application;

fig. 2 is an assembled structural schematic diagram of the airfoil folding device of the long-chord missile wing hypersonic flight vehicle according to the embodiment of the present application.

The text labels in the figures are represented as: 100-a base; 110-a mount; 120-an auxiliary seat; 121-a spacing pin; 130-torsion spring; 140-a spring pin; 141-a pressure spring; 142-a compression nut; 200-missile wing; 201-spring pin hole; 202-mounting grooves; 210-a rotating shaft; 220-moving a sealing ring; 300-fairing.

Detailed Description

The following detailed description of the present application is given for the purpose of enabling those skilled in the art to better understand the technical solutions of the present application, and the description in this section is only exemplary and explanatory, and should not be taken as limiting the scope of the present application in any way.

Referring to fig. 1-2, the present embodiment provides a wing surface folding device for a long-chord missile wing hypersonic flight vehicle, which includes a base 100 and a missile wing 200; the missile wing 200 can be folded and installed on the base 100, and can be automatically unfolded and fixed through the twisting component and the positioning component. The missile wing 200 in a folded state is installed on the surface of an engine through the base 100 and is loaded into a launch canister, and is automatically unfolded and fixed by using a twisting assembly and a positioning assembly after being launched.

In a preferred embodiment, the missile wing 200 is rotatably mounted on the base 100 through a rotating shaft 210; the base 100 is provided with a mounting seat 110 and an auxiliary seat 120 corresponding to the rotating shaft 210; the rotating shaft 210 is bridged between the mounting seat 110 and the auxiliary seat 120, and is respectively rotatably connected with the mounting seat 110 and the auxiliary seat 120; the hinge 210 is more stable by two-point support.

Preferably, one end of the rotating shaft 210 near the mounting base 110 penetrates through the mounting base 110 and is connected with the missile wing 200 through a screw thread. Thereby realizing the relative rotation of the missile wing 200 and the base 100.

In a preferred embodiment, the torsion assembly includes a torsion spring 130; the torsion spring 130 is sleeved on the rotating shaft 210 and located between the mounting base 110 and the auxiliary base 120, and two ends of the torsion spring are respectively connected with the missile wing 200 and the auxiliary base 120; when the missile wing 200 is in a folded state, the torsion spring 130 is in a stressed state, so that after being launched, the missile wing 200 is separated from the launching tube and is not under a constraint force, and the automatic opening action is realized.

Preferably, both ends of the torsion spring 130 are respectively provided with a torsion arm and a limit arm corresponding to the missile wing 200 and the auxiliary seat 120; the torsion arm is arranged along the axial direction of the torsion spring 130; the limiting arm is arranged along the tangential direction of the torsion spring 130.

Preferably, the auxiliary seat 120 is provided with a limit pin 121 corresponding to the limit arm; the limiting pin 121 is disposed along the axial direction of the torsion spring 130, and is perpendicular to the limiting arm, so as to effectively limit the torsion spring 130 to rotate relatively on the rotating shaft 210.

Preferably, the mounting base 110 is provided with a through arc-shaped through hole corresponding to the torsion arm; the torque arm passes the arc through-hole and docks with the bullet wing 200, and the bullet wing 200 turns over a in-process, and the torque arm can rotate in step, and the arc through-hole can not cause the influence to the rotation of torque arm.

Preferably, the missile wing 200 is provided with a butt hole corresponding to the torsion arm, and the torsion spring 130 is connected with the missile wing 200 in a plugging manner through the torsion arm.

In a preferred embodiment, the positioning assembly includes a spring pin 140; the mounting seat 110 is provided with mounting holes corresponding to the spring pins 140, and the missile wing 200 is provided with spring pin holes 201 corresponding to the spring pins 140; the spring pin 140 is slidably installed in the installation hole, and the missile wing 200 and the installation base 110 can be relatively fixed after sliding into the spring pin hole 201.

Preferably, a pressure spring 141 is further arranged in the mounting hole; the pressure spring 141 is positioned at one end of the spring pin 140 far away from the missile wing 200 and is blocked in the mounting hole through a compression nut 142; the compression nut 142 is threadedly coupled to the mounting hole.

In a preferred embodiment, a dynamic seal ring 220 is further arranged between the missile wing 200 and the mounting seat 110; the missile wing 200 is provided with a matching mounting groove 202 corresponding to the dynamic seal ring 220.

In a preferred embodiment, a fairing 300 is also mounted on the base 100; fairing 300 is used to seal and insulate mount 110 and the torsion and locating assemblies.

The principles and embodiments of the present application are explained herein using specific examples, which are provided only to help understand the method and the core idea of the present application. The foregoing is only a preferred embodiment of the present application, and it should be noted that there are objectively infinite specific structures due to the limited character expressions, and it will be apparent to those skilled in the art that a plurality of modifications, decorations or changes may be made without departing from the principle of the present invention, and the technical features described above may be combined in a suitable manner; such modifications, variations, combinations, or adaptations of the invention in other contexts without modification may be viewed as within the scope of the present application.