Gliding wing separating and releasing mechanism

Abstract

The utility model discloses a hang glider separating and releasing mechanism. The mechanism comprises a hoop which is arranged outside an aircraft body in a sleeving mode and comprises a left half hoop and a right half hoop, the left half hoop is connected with a left side hang glider, and the right half hoop is connected with a right side hang glider; one ends of the left half hoop and the right half hoop are fixedly connected, and the other ends of the left half hoop and the right half hoop are inserted and elastically connected through a compressed first-stage separation spring; the piston cylinder is arranged in the aircraft body and is fixedly connected with the aircraft body; a memory alloy circular ring capable of being contracted by heating is arranged in the piston cylinder; a piston is arranged on the memory alloy circular ring; a compressed secondary separation spring is arranged on the periphery of the piston; the limiting stud is used for sequentially penetrating through the hoop and the aircraft body to be fixedly connected with the piston; when the memory alloy circular ring is heated and contracted, the piston drives the limiting stud to move downwards under the action of the second-stage separation spring to release connection between the left half hoop and the right half hoop, and the left half hoop and the right half hoop are opened under the action of the first-stage separation spring to be separated from the aircraft body.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of aircraft, specifically, a kind of glider separation release mechanism. BACKGROUND

[0002] The glider is used to carry out range-increasing propulsion, which is a kind of underwater vehicle propulsion mode, and generally used in zigzag navigation in a non-powered manner, which can realize long-distance long-time navigation task planning.For glider propulsion mode with special task planning, the glider needs to be separated and released at the end of the task to meet the requirements of low-resistance controllable vehicle.The existing separation mode mostly uses pyrotechnics (explosive bolts, etc.) as separation mechanism, which has the disadvantage of large noise;There is also a multi-stage steel ball mechanism, which has the disadvantage of low reliability of steel ball jamming action.

[0003] For the problems of large noise of using pyrotechnics as separation mechanism and low reliability of using multi-stage steel ball mechanism as separation mechanism in the prior art, no effective solution has been proposed so far. UTILITY MODEL CONTENT

[0004] The utility model embodiment provides a kind of glider separation release mechanism to solve the problems of large noise of using pyrotechnics as separation mechanism and low reliability of using multi-stage steel ball mechanism as separation mechanism in the prior art.

[0005] To achieve the above purpose, the utility model provides a kind of glider separation release mechanism, which comprises: a ring, which is used to be sleeved on the periphery of the vehicle body, comprising: left half ring and right half ring, left side glider is fixedly connected on the left half ring, right side glider is fixedly connected on the right half ring;One end of the left half ring and the right half ring is fixedly connected, the other end is inserted and elastically connected by compressed first-stage separation spring;Piston cylinder is arranged in the vehicle body and fixedly connected therewith;Memory alloy ring that can be contracted by heating is arranged in the piston cylinder;Piston is arranged on the memory alloy ring and located in the piston cylinder;Compressed second-stage separation spring is arranged on the periphery of the piston;Limiting stud is used to fixedly connect the left half ring and the right half ring by inserting one end of the left half ring and the right half ring, and then fixedly connected with the piston by penetrating the vehicle body;When the memory alloy ring is contracted by heating, the piston drives the limiting stud to move downward under the action of the second-stage separation spring, the connection between the left half ring and the right half ring is released, the left half ring and the right half ring are opened under the action of the first-stage separation spring, and the separation from the vehicle body is realized.

[0006] Optionally, one end of the left half ring and the right half ring is fixedly connected by a rotating shaft.

[0007] Optionally, a protrusion is arranged in the inner cavity of the piston cylinder for limiting the memory alloy ring.

[0008] Optionally, a heating medicine is arranged in the memory alloy ring; the heating medicine receives an external signal through an electric connector to cause combustion of the heating medicine.

[0009] Optionally, the piston comprises a first connecting part and a second connecting part fixedly connected; the second connecting part is below the first connecting part; the first connecting part is a circular ring body structure; the second connecting part is a cylindrical structure; the outer circle diameter of the first connecting part is smaller than the diameter of the second connecting part; the second separation spring is sleeved on the periphery of the first connecting part; one end of the second separation spring is in contact with the inside of the aircraft body, and the other end is in contact with the top surface of the second connecting part.

[0010] Optionally, a first limiting hole is arranged at one end of the left half ring hoop and the right half ring hoop, a second limiting hole is arranged on the aircraft body, and a threaded hole is arranged on the second connecting part; the limiting stud is used for sequentially penetrating through the first limiting hole, the second limiting hole, the inner circle of the first connecting part and the threaded hole on the second connecting part and being screwed.

[0011] Optionally, a first limiting groove is arranged on the side surface of the second connecting part for mounting a first sealing ring.

[0012] Optionally, a second limiting groove is arranged on the top of the piston cylinder for mounting a second sealing ring.

[0013] Optionally, a third limiting groove is arranged on the aircraft body and located at the second limiting hole for mounting a third sealing ring.

[0014] Optionally, the piston cylinder and the aircraft body are fixedly connected through bolts.

[0015] The beneficial effects of the utility model are as follows:

[0016] The utility model provides a glider separation release mechanism, the mechanism adopts ring hoop plus limiting stud and can quickly realize glider installation, adopts memory alloy ring as secondary limiting device, its feature is that it contracts when hot, can contract deformation under the action of heating medicine, structural response speed is fast, and reliability is high, adopts compression spring as power element, does not have the noise of pyrotechnics action, effectively reduces action noise, adopts multiple sealing structure, can guarantee that the aircraft does not leak after structure action. DRAWINGS

[0017] Fig. 1 It is a perspective view of a glider separation release mechanism provided by the utility model embodiment;

[0018] Fig. 2 is a front view of a glider separation release mechanism provided by the embodiment of the utility model;

[0019] Fig. 3 is a partial sectional view of a glider separation release mechanism provided by the embodiment of the utility model.

[0020] Symbol explanation:

[0021] Vehicle body-1, left half hoop-2, right half hoop-3, left glider-4, right glider-5, first separation spring-6, piston cylinder-7, memory alloy ring-8, piston-9, second separation spring-10, limit stud-11, rotating shaft-12, heating medicine-13, electric connector-14, first sealing ring-15, second sealing ring-16, third sealing ring-17. Specific implementation

[0022] In order to make the utility model's purpose, technical scheme and advantage more clearly, below will combine with the drawing to the utility model make further detailed description, obviously, the described embodiment only is the utility model a part embodiment, is not all the embodiment. Based on the embodiment in the utility model, all other embodiments that the ordinary skill in the art person obtains under the premise of not making the creative labor belong to the scope of the utility model protection.

[0023] The existing separation mode adopts the initiating explosive device (explosive bolt) as the separation mechanism, and it has the defect of large noise; also adopts the multistage steel ball mechanism, and it has the defect of low action reliability of steel ball jam.

[0024] Therefore, the utility model provides a glider separation release structure based on memory alloy ring 8, aims at realizing the low-noise, high-reliability glider separation process.

[0025] Fig. 1 is a perspective view of a glider separation release mechanism provided by the embodiment of the utility model; Fig. 2 is a front view of a glider separation release mechanism provided by the embodiment of the utility model; Fig. 3 is a partial sectional view of a glider separation release mechanism provided by the embodiment of the utility model. As shown in Figs. 1-3 the glider separation release mechanism comprises:

[0026] 1, hoop, for being set in the periphery of vehicle body 1, it includes: left half hoop 2 and right half hoop 3, left glider 4 is fixedly connected on the left half hoop 2, right glider 5 is fixedly connected on the right half hoop 3;The left half hoop 2 and right half hoop 3 are fixedly connected at one end, and are elastically connected by the compression of first separation spring 6 at the other end.

[0027] In an alternative embodiment, the left half hoop 2 and the right half hoop 3 are both semi-circular structures, one end of the left half hoop 2 and the right half hoop 3 are fixedly connected through the rotating shaft 12, which can ensure the flexible rotation of the left half hoop 2 and the right half hoop 3 around the rotating shaft 12; the other end of the left half hoop 2 and the right half hoop 3 are both provided with a horizontal boss and a vertical boss, the two horizontal bosses are inserted, and the two vertical bosses are pressed against the first level separation spring 6.

[0028] The first level separation spring 6 is a compression spring, which provides the power to open the hoop when the glider separates, avoiding the noise problem of the pyrotechnic separation mechanism.

[0029] 2, the piston cylinder 7 is arranged in the aircraft body 1 and fixedly connected thereto; a heat-shrinkable memory alloy ring 8 is arranged in the piston cylinder 7; a piston 9 is arranged on the memory alloy ring 8 and located in the piston cylinder 7; a compressed second level separation spring 10 is arranged on the periphery of the piston 9;

[0030] In an alternative embodiment, the piston cylinder 7 is a cylindrical structure with a flange at one end; it is located in the aircraft body 1 and below the insertion end of the left half hoop 2 and the right half hoop 3, and the top of the piston cylinder 7 (the flange end) is fixedly connected to the aircraft body 1 by bolts.

[0031] A protrusion is arranged in the inner cavity of the piston cylinder 7 for limiting the memory alloy ring 8; the memory alloy ring 8 is a cylindrical structure; a heating agent 13 is arranged in the memory alloy ring 8; the heating agent 13 receives an external signal through an electrical connector 14 to ignite the combustion of the heating agent 13.

[0032] Specifically, the electrical connector 14 is a T-shaped structure, which includes a horizontal electrical connector 14 and a vertical electrical connector 14 fixedly connected; the heating agent 13 is arranged in the horizontal electrical connector 14; the horizontal electrical connector 14 is located in the memory alloy ring 8; the vertical electrical connector 14 passes through the bottom of the piston cylinder 7; when an electrical signal is given to the electrical connector 14, the heating agent 13 can be ignited, thereby heating the memory alloy ring 8; the memory alloy ring 8 shrinks when heated.

[0033] In an alternative embodiment, the material of the memory alloy ring 8 is nickel-titanium alloy, which has the characteristic of shrinking when heated.

[0034] A piston 9 is arranged on the memory alloy ring 8 and in the piston cylinder 7; the bottom of the piston 9 is in contact with the top of the memory alloy ring 8; the piston 9 comprises a first connecting part and a second connecting part fixedly connected; the second connecting part is below the first connecting part; the first connecting part is a ring body structure; the second connecting part is a cylindrical structure; the outer circle diameter of the first connecting part is smaller than the diameter of the second connecting part;

[0035] The second separation spring 10 is sleeved on the periphery of the first connecting part; one end of the second separation spring 10 is in contact with the inside of the vehicle body 1, and the other end is in contact with the top surface of the second connecting part; the second separation spring 10 is pressed (i.e. in a compressed state) by the vehicle body 1 and the top surface of the second connecting part of the piston 9.

[0036] After the memory alloy ring 8 shrinks due to heating, the memory alloy ring 8 is no longer limited by the protrusion of the inner cavity of the piston cylinder 7, and the piston 9 is pushed downward under the pushing force of the second separation spring 10.

[0037] 3. A limiting stud 11 is used to fixedly connect the left half ring 2 and the right half ring 3 by penetrating one end of the left half ring 2 and the right half ring 3, and is fixedly connected with the piston 9 by penetrating the vehicle body 1.

[0038] In an optional embodiment, a first limiting hole is arranged on one end of the left half ring 2 and the right half ring 3, a second limiting hole is arranged on the vehicle body 1, and a threaded hole is arranged on the second connecting part.

[0039] The limiting stud 11 is used to threadedly connect the first limiting hole, the second limiting hole, the inner circle of the first connecting part, and the threaded hole on the second connecting part in sequence.

[0040] In an optional embodiment, a first limiting groove is arranged on the side surface of the second connecting part for installing a first sealing ring 15, so as to realize the sealing effect of the piston cylinder 7 and the piston 9; a second limiting groove is arranged on the top of the piston cylinder 7 for installing a second sealing ring 16, so as to realize the sealing effect of the piston cylinder 7 and the vehicle body 1; a third limiting groove is arranged on the vehicle body 1 at the second limiting hole for installing a third sealing ring 17, so as to realize the sealing effect of the vehicle body 1 and the limiting stud 11.

[0041] In an optional embodiment, the ring, the limiting stud 11, the heating medicine 13, the first sealing ring 15, the second sealing ring 16, the third sealing ring 17, and other components are made of corrosion-resistant materials, which are suitable for long-term use of underwater vehicles.

[0042] When the memory alloy ring 8 is heated and shrinks, the piston 9 drives the limiting stud 11 to move downward under the action of the secondary separation spring 10, the connection of the left half hoop 2 and the right half hoop 3 is released, the left half hoop 2 and the right half hoop 3 are opened under the action of the primary separation spring 6, and the separation from the aircraft body 1 is realized.

[0043] Specifically, when the aircraft is ready to separate and release the glider wing, an electric signal is given to ignite the heating agent 13, the heat makes the memory alloy ring 8 shrink, the limiting constraint of the memory alloy ring 8 and the convex of the inner cavity of the piston cylinder 7 is released, the piston 9 moves downward together with the limiting stud 11 under the action of the pushing force of the secondary separation spring 10, the transverse limiting of the left and right hoops is released, the left and right hoops rotate and open around the rotating shaft 12 under the action of the primary separation spring 6, and the separation from the aircraft is realized.

[0044] The utility model discloses the beneficial effects of:

[0045] The utility model provides a glider wing separation release mechanism, this mechanism adopts hoop and limiting stud 11 to be able to realize glider wing installation fast, adopts memory alloy ring 8 as secondary limiting device, its feature is to meet the heat shrinkage, can contract deformation under the action of heating agent 13, and the structural response speed is fast, and the reliability is high, adopts compression spring as power element, does not exist the noise of pyrotechnics action, effectively reduces the action noise, adopts multiple sealing structure, can guarantee that the aircraft will not leak after the structure action.

[0046] Finally, it should be noted that: the above examples are only used to illustrate the technical scheme of the utility model, and not to limit it; although the utility model has been described in detail with reference to the foregoing examples, those skilled in the art should understand that: it still can modify the technical scheme recorded in the foregoing each embodiment, or make equivalent replacement to part of technical features; and these modifications or replacements do not make the essence of the corresponding technical scheme deviate from the spirit and scope of the technical scheme of each embodiment of the utility model.

Claims

1. A gliding wing separation release mechanism, characterized by, The utility model relates to a kind of mechanism for separating aircraft body and aircraft body, comprising: Ring, for being set in the periphery of aircraft body, comprising: left half ring and right half ring, left side glider is fixedly connected on the left half ring, right side glider is fixedly connected on the right half ring;The one end of the left half ring and right half ring is fixedly connected, the other end is inserted and is elastically connected by the compression of one level separation spring; Piston cylinder, be located in the aircraft body and is fixedly connected;Heating contractile memory alloy ring is arranged in the piston cylinder;Piston is arranged on the memory alloy ring and located in the piston cylinder;Compression secondary separation spring is arranged on the periphery of the piston; Limiting stud, for the one end inserted through left half ring and right half ring and the left half ring and right half ring fixedly connected, and again through aircraft body and the piston fixedly connected; When the memory alloy ring is heated and shrinks, under the action of the secondary separation spring, piston drives limiting stud to move downward, the connection of left half ring and right half ring is released, under the action of the one level separation spring, left half ring and right half ring open, realize the separation with aircraft body.

2. The mechanism according to claim 1, wherein: The one end of the left half ring and right half ring is fixedly connected through a rotating shaft.

3. The mechanism according to claim 1, wherein: A protrusion is arranged in the inner cavity of the piston cylinder for limiting the memory alloy ring.

4. The mechanism according to claim 3, wherein: A heating medicine is arranged in the memory alloy ring; the heating medicine receives external signal through an electric connector to cause the combustion of the heating medicine.

5. The mechanism according to claim 1, wherein: The piston comprises a first connecting part and a second connecting part fixedly connected; the second connecting part is located below the first connecting part; the first connecting part is a circular ring structure; the second connecting part is a cylindrical structure; the outer diameter of the first connecting part is smaller than the diameter of the second connecting part; The secondary separation spring is sleeved on the periphery of the first connecting part; one end of the secondary separation spring is in contact with the inside of the aircraft body, and the other end is in contact with the top surface of the second connecting part.

6. The mechanism according to claim 5, wherein: A first limiting hole is arranged at the one end inserted through the left half ring and right half ring, a second limiting hole is arranged on the aircraft body, and a threaded hole is arranged on the second connecting part; The limiting stud is used to pass through the first limiting hole, the second limiting hole, the inner circle of the first connecting part, and the threaded hole on the second connecting part in sequence and be screwed.

7. The mechanism according to claim 5, wherein: A first limiting groove is arranged on the side surface of the second connecting part for mounting a first sealing ring.

8. The mechanism according to claim 1, wherein: A second limiting groove is arranged on the top of the piston cylinder for mounting a second sealing ring.

9. The mechanism according to claim 1, wherein: A third limiting groove is arranged on the aircraft body at the second limiting hole for mounting a third sealing ring.

10. The mechanism of claim 1, wherein: the piston cylinder is fixedly connected to the vehicle body by bolts.

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