Expansion telescopic wing driven by gas gunpowder

Abstract

The utility model relates to an unfolding telescopic wing driven by fuel gas gunpowder, which comprises a wing comprising an inner wing and an outer wing; a first space is arranged in the outer wing, and the inner wing is axially sleeved in the first space; one end of the gas-driven telescopic device is connected with the inner wing, and the other end of the gas-driven telescopic device is connected with the outer wing; the gas-driven telescopic device stretches out and draws back in the length direction of the outer wing. The inner wing and the outer wing are connected in an axial sleeving mode, and a complete wing structure is formed when the inner wing and the outer wing are unfolded. The first space in the outer wing provides an installation space for the inner wing, and it is ensured that the inner wing can be axially connected into the outer wing in a sleeved mode. The gas-driven telescopic device is connected with the inner wing and the outer wing and can drive the outer wing to telescopically move in the length direction of the outer wing under driving of gas gunpowder, so that the telescopic form of the wing is changed, and the aircraft can automatically and dynamically adjust the form of the wing according to needs. Therefore, better flight performance and effect are realized.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft fixed wings, in particular to an unfoldable telescopic wing driven by gas and gunpowder. Background Art

[0002] There are many ways to fold existing fixed-wing aircraft. According to the different driving methods when the wings are unfolded, the common folding wing unfolding mechanisms are mainly classified into elastic drive and micro-motor drive according to the driving method. The elastic drive relies on a torsion spring or tension spring to drive. The characteristics of this mechanism are high reliability, but the wingspan length is limited. The micro-motor drive relies on a micro-motor to provide driving force. The characteristics of this mechanism are that the wing surface can be accurately adjusted to unfold, but the driving torque is small, the unfolding speed is slow, and the weight of the mechanism is large. The Chinese patent authorization number CN219037775U discloses a gas actuator driven folding wing unfolding device, which realizes the unfolding of two wing panels by the meshing rotation of the gas driven gear generated by the fuel, but the state of the wing cannot be further adjusted during the flight to realize the extension and retraction of the wing panel and change the length of the wingspan to change the lift of the aircraft. The maneuverability is poor and the structure is complex. Utility Model Content

[0003] The embodiment of the present application provides a deployable retractable wing driven by gas and gunpowder to solve the problem that the aircraft cannot flexibly change the wingspan length by gas and gunpowder driving during flight.

[0004] Provided is a deployable telescopic wing driven by gas and gunpowder, comprising: a wing, comprising an inner wing and an outer wing; a first space is provided in the outer wing, and the inner wing is axially sleeved in the first space; a gas-driven telescopic device is located in the wing, and one end is connected to the inner wing, and the other end is connected to the outer wing; the gas-driven telescopic device is telescopic along the length direction of the outer wing.

[0005] In some embodiments, the gas-driven telescopic device includes a cylinder assembly and a piston rod; a mounting groove for fixing the cylinder assembly is provided in the inner wing, one end of the piston rod is movably set in the cylinder assembly, and the other end is connected to the inner wall of the outer wing.

[0006] In some embodiments, the cylinder assembly includes a pipe sealed at both ends, and a movable seal is provided in the pipe to separate the pipe into a second space and a third space, and the movable seal is fixedly connected to one end of the piston rod extending into the cylinder assembly; the cylinder assembly includes a first gas source assembly for passing high-pressure gas into the second space, and a second gas source assembly for passing high-pressure gas into the third space.

[0007] In some embodiments, the first gas source assembly includes a first adapter connected to one end of the pipeline, the end of the first adapter away from the pipeline is connected to a first gunpowder placing tube, and the end of the first gunpowder placing tube away from the first adapter is provided with a first igniter; the second gas source assembly includes a second adapter connected to the other end of the pipeline, the end of the second adapter away from the pipeline is connected to a second gunpowder placing tube, and the end of the second gunpowder placing tube away from the second adapter is provided with a second igniter.

[0008] In some embodiments, the first gunpowder placing tube includes a bend; one end of the bend is connected to the first adapter, the other end of the bend is provided with a parallel portion parallel to the pipeline, and the other end of the parallel portion is provided with a first igniter; the second gunpowder placing tube also includes a bend; one end of the bend is connected to the second adapter, the other end of the bend is also provided with a parallel portion parallel to the pipeline, and the other end of the parallel portion is provided with a second igniter; the two parallel portions are located on the same straight line.

[0009] In some embodiments, a connecting piece is provided at one end of the inner wing away from the outer wing, and a tension spring connecting portion is provided on the connecting piece; a tension spring is provided on the tension spring connecting portion, and the other end of the tension spring is connected to the frame; the connecting pieces of the two wings are hingedly connected by a hinge assembly, and the hinge assembly is used to be fixedly connected to the frame.

[0010] In some embodiments, the hinge assembly includes a first swivel, a second swivel, a fixing plate and a limiting nut; the fixing plate is fixedly connected to the frame, and a protruding shaft is provided on the upper middle portion thereof, the first swivel and the second swivel are stacked on the protruding shaft, and the limiting nut is provided on the protruding shaft and abuts against the second swivel located on the outside; the connecting parts of the two inner wings are rotatably connected to the first swivel and the second swivel respectively.

[0011] In some embodiments, the first rotating ring is a cylinder with an opening in the middle, which is arranged on the protruding shaft and contacts the fixed plate; the second rotating ring includes a cylinder portion and a ring portion; the cylinder portion is penetrated by the protruding shaft and abuts against a side of the first rotating ring away from the fixed plate; the ring portion is arranged on the circumference of the cylinder portion, and an annular groove is formed between the first rotating ring and the cylinder portion; a bearing is arranged in the annular groove. The cylinder portion penetrates the protruding shaft and abuts against the first rotating ring, the ring portion is arranged on the circumference of the cylinder portion and an annular groove is formed between the first rotating ring and the cylinder portion, a bearing is arranged in the annular groove, a limit nut is arranged on the protruding shaft and abuts against the second rotating ring; the two inner wing connecting pieces are rotatably connected to the first rotating ring and the second rotating ring respectively.

[0012] In some embodiments, when the inner wings of the two wings are completely located in the first space and rotated to the same axial direction, the total length of the wings is 2L.

[0013] In some embodiments, when the inner wings of the two wings are completely located outside the first space and rotated to the same axial direction, the total length of the wings is 3.5L.

[0014] The beneficial effects of the technical solution provided by this application include:

[0015] The embodiment of the present application provides an expandable and retractable wing driven by gas and gunpowder, wherein the inner wing and the outer wing constitute the structure of the entire wing, and the inner wing and the outer wing are connected together by axial sleeve connection, so that a complete wing structure can be formed when expanded. The first space inside the outer wing provides an installation space for the inner wing, ensuring that the inner wing can be axially sleeved inside the outer wing. The gas-driven retractable device is a key device for controlling the extension and retraction of the outer wing. By being connected to the inner wing and the outer wing respectively, and driven by gas and gunpowder, the gas-driven retractable device can drive the outer wing to retract and move along its length direction, thereby changing the retractable state of the wing, so that the aircraft can autonomously and dynamically adjust the wing shape as needed to achieve better flight performance and effects. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0017] Figure 1 A schematic diagram of a structure in which the wings provided in an embodiment of the present application are unfolded and the outer wings are extended;

[0018] Figure 2 A schematic diagram of a structure in which the wings are unfolded and the outer wings are retracted provided in an embodiment of the present application;

[0019] Figure 3 A schematic diagram of the structure of folded wings provided in an embodiment of the present application;

[0020] Figure 4 A schematic diagram of the structure of a gas-driven telescopic device provided in an embodiment of the present application;

[0021] Figure 5 A partial structural schematic diagram of a cylinder assembly provided in an embodiment of the present application;

[0022] Figure 6 A schematic diagram of the peripheral structure of the hinge assembly provided in an embodiment of the present application;

[0023] Figure 7 A schematic diagram of the cross-sectional structure of the hinge assembly and its surrounding side provided in an embodiment of the present application.

[0024] In the figure: 1. wing; 11. outer wing; 12. inner wing; 13. connecting part; 14. tension spring connecting part; 2. gas-driven telescopic device; 3. piston rod; 31. moving seal; 32. second space; 33. third space; 4. cylinder assembly; 41. first gas source assembly; 411. first gunpowder placing tube; 412. first adapter; 413. first igniter; 42. second gas source assembly; 421. second gunpowder placing tube; 422. second adapter; 423. second igniter; 43. pipeline; 5. hinge assembly; 51. protruding shaft rod; 52. fixing plate; 6. limit nut; 7. bearing; 8. tension spring; 9. first swivel; 10. second swivel. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application.

[0026] The embodiment of the present application provides a deployable retractable wing driven by gas and gunpowder, which can solve the problem that the aircraft cannot flexibly change the wingspan length by gas and gunpowder driving during flight.

[0027] Since the wingspan of the aircraft can only be realized on the wing 1 to realize the rotation of the wing 1 to improve the space utilization and change the wingspan length of the wing 1, the wing 1 is changed into two parts, and the two parts of the wing 1 are connected, one part of the wing 1 is used to connect with the frame to realize the rotation of the wing 1 to improve the space utilization, and the other part of the wing 1 is sleeved on the first part of the wing 1, and a gas-fired gunpowder driving device is used to connect with the two parts of the wing 1 respectively, providing a power source for the part of the wing 1 located on the outside, so that it can be telescopically moved along its length direction, thereby changing the telescopic state of the wing 1, so that the aircraft can dynamically adjust the wing shape autonomously as needed to achieve better flight performance and effect. This solves the problem that the aircraft cannot flexibly change the wingspan length by gas-fired gunpowder driving during flight.

[0028] refer to Figure 1-4 A deployable telescopic wing driven by gas and explosives, comprising: a wing 1, comprising an inner wing 12 and an outer wing 11; a first space is provided in the outer wing 11, and the inner wing 12 is axially sleeved in the first space; a gas-driven telescopic device 2 is located in the wing 1, and one end is connected to the inner wing 12, and the other end is connected to the outer wing 11; the gas-driven telescopic device 2 is telescopic along the length direction of the outer wing 11.

[0029] Through the above structure, the inner wing 12 and the outer wing 11 form the structure of the entire wing 1. The inner wing 12 and the outer wing 11 are connected together by axial sleeve connection, and a complete wing 1 structure can be formed when unfolded. The first space inside the outer wing 11 provides an installation space for the inner wing 12, ensuring that the inner wing 12 can be axially sleeved in the outer wing 11. The gas-driven telescopic device 2 is a key device for controlling the extension and retraction of the outer wing 11. By being connected to the inner wing 12 and the outer wing 11 respectively, the gas-driven telescopic device 2 can drive the outer wing 11 to telescopically move along its length direction under the drive of gas gunpowder, thereby changing the telescopic state of the wing 1, so that the aircraft can autonomously and dynamically adjust the wing shape as needed to achieve better flight performance and effect.

[0030] In some preferred embodiments, the gas-driven telescopic device 2 includes a cylinder assembly 4 and a piston rod 3; a mounting groove for fixing the cylinder assembly 4 is provided in the inner wing 12, one end of the piston rod 3 is movably arranged in the cylinder assembly 4, and the other end is connected to the inner wall of the outer wing 11. Through this structural setting, the cylinder assembly 4 is an important part of the gas-driven telescopic device 2, which is usually composed of a cylinder and related components. The function of the cylinder assembly 4 is to accommodate the piston rod 3 and generate a driving force. The piston rod 3 is a component in the gas-driven telescopic device 2 that cooperates with the cylinder assembly 4. One end of the piston rod 3 is arranged in the cylinder assembly 4, and the other end is connected to the inner wall of the outer wing 11. Through the action of gas pressure, the piston rod 3 can move in the cylinder, thereby pushing the outer wing 11 to telescope. The inner wing 12 is provided with a mounting groove for fixing the cylinder assembly 4, so that the cylinder assembly 4 can be ensured to be firmly installed in the inner wing 12. One end of the piston rod 3 is movably arranged in the cylinder assembly 4, and the other end is connected to the inner wall of the outer wing 11, so that the gas-driven telescopic device 2 can effectively transmit force when it is working. Through such a configuration, the gas-driven retractable device 2 can effectively transmit power between the inner wing 12 and the outer wing 11, realize the function of extending and retracting the wing 1, and thus realize dynamic adjustment of the shape of the aircraft wing 1.

[0031] In some preferred embodiments, the cylinder assembly 4 includes a pipeline 43 sealed at both ends, and a movable seal 31 is provided in the pipeline 43 to separate it into a second space 32 and a third space 33, and the movable seal 31 is fixedly connected to one end of the piston rod 3 extending into the cylinder assembly 4; the cylinder assembly 4 includes a first gas source assembly 41 for passing high-pressure gas into the second space 32, and a second gas source assembly 42 for passing high-pressure gas into the third space 33. In such a preferred embodiment, the cylinder assembly 4 adopts a special structural design, which specifically includes the following parts: the cylinder assembly 4 includes a pipeline 43 sealed at both ends, and a movable seal 31 is provided in the pipeline 43 to separate the pipeline into the second space 32 and the third space 33. Such a design can effectively control the direction of gas flow and pressure distribution. The movable seal 31 is fixedly connected to the piston rod 3, located inside the pipeline 43, and separates the pipeline 43 into the second space 32 and the third space 33. When high-pressure gas is passed into the second space 32 and the third space 33, the high-pressure gas will push the movable seal 31 and then drive the piston rod 3 connected thereto to expand and contract. The cylinder assembly 4 also includes a first gas source assembly 41 for supplying high-pressure gas to the second space 32 and a second gas source assembly 42 for supplying high-pressure gas to the third space 33. Such a design can realize the movement of the piston rod 3 and the operation of the cylinder assembly 4 by controlling the pressure of the gas in the two spaces. The cylinder assembly 4 of such a structural design plays a key role in the gas-driven telescopic device 2, and can realize the movement of the piston rod 3 by controlling the high-pressure gas, thereby pushing the outer wing 11 to expand or contract, and realizing the dynamic adjustment of the shape of the wing 1.

[0032] In some preferred embodiments, the first gas source assembly 41 includes a first adapter 412 connected to one end of the pipeline 43, the end of the first adapter 412 away from the pipeline 43 is connected to a first gunpowder placement tube 411, and the end of the first gunpowder placement tube 411 away from the first adapter 412 is provided with a first igniter 413; the second gas source assembly 42 includes a second adapter 422 connected to the other end of the pipeline 43, the end of the second adapter 422 away from the pipeline 43 is connected to a second gunpowder placement tube 421, and the end of the second gunpowder placement tube 421 away from the second adapter 422 is provided with a second igniter 423. Specifically, the first gas source assembly 41 and the second gas source assembly 42 respectively include adapters connected to both ends of the pipeline 43, gunpowder placement tubes and igniters. When it is necessary to pneumatically control the pipeline 43, the gunpowder can be ignited by the igniter to generate high-pressure gas, thereby realizing the supply of gas source. The first gas source assembly 41 and the second gas source assembly 42 play a key role in the driving system, igniting the gunpowder through the igniter and releasing high-pressure gas, thereby realizing the control and operation of the driving device. This design structure can effectively realize the supply and control of the gas source, so that the performance and stability of the gas gunpowder drive are improved.

[0033] In some excellent embodiments, the first gunpowder placing tube 411 includes a bend; one end of the bend is connected to the first adapter 412, the other end of the bend is provided with a parallel portion parallel to the pipeline 43, and the other end of the parallel portion is provided with a first igniter 413; the second gunpowder placing tube 421 also includes a bend; one end of the bend is connected to the second adapter 422, the other end of the bend is also provided with a parallel portion parallel to the pipeline 43, and the other end of the parallel portion is provided with a second igniter 423; the two parallel portions are located on the same straight line. This design scheme improves the placing tube in the above scheme, and such a design structure makes the igniter of the gunpowder placing tube parallel to the pipeline 43, and facilitates the connection between the igniter and the pipeline 43. Through the ignition effect of the igniter, the gunpowder can be ignited when needed, thereby generating high-pressure gas for controlling the drive system. This design can improve the reliability and flexibility of the gas source component and ensure that the system can perform pneumatic control operations efficiently.

[0034] In some preferred embodiments, a connector 13 is provided at one end of the inner wing 12 away from the outer wing 11, and a tension spring connector 14 is provided on the connector 13; a tension spring 8 is provided on the tension spring connector 14, and the other end of the tension spring 8 is connected to the frame; the connectors 13 of the two wings 1 are hinged by a hinge assembly 5, and the hinge assembly 5 is used to be fixedly connected to the frame. In these preferred embodiments, a relatively complex design is adopted for the connection between the wing 1 and the frame. Specifically, a connector 13 is provided at one end of the inner wing 12, and a tension spring connector 14 is provided on the connector 13. A tension spring 8 is installed on the tension spring connector 14, and the other end is connected to the frame. Such a design allows the inner wing 12 to move relative to the outer wing 11 to a certain extent under certain conditions, and a certain reset force can be provided by the tension spring 8 to ensure that the inner wing 12 can return to its original position within a suitable time, thereby realizing the rotation of the wing 1. In addition, the connectors 13 of the two wings 1 are hinged by a hinge assembly 5, and the hinge assembly 5 is fixedly connected to the frame. This design allows the inner wings 12 to rotate with the frame, and the stability and reliability of the inner wings 12 can be ensured through the connection of the hinge assembly 5 .

[0035] In some preferred embodiments, the hinge assembly 5 includes a first swivel 9, a second swivel 10, a fixing plate 52 and a limiting nut 6; the fixing plate 52 is fixedly connected to the frame, and a protruding shaft 51 is provided in the middle of the fixing plate 52, the first swivel 9 and the second swivel 10 are stacked on the protruding shaft 51, and the limiting nut 6 is provided on the protruding shaft 51 and abuts against the second swivel 10 located on the outside; the connecting pieces 13 of the two inner wings 12 are rotatably connected to the first swivel 9 and the second swivel 10 respectively. The setting of the protruding shaft 51 provides a suitable support point for the first swivel 9 and the second swivel 10, ensuring that they can rotate stably on the fixing plate 52. At the same time, the limiting nut 6 can limit the second swivel 10 to ensure stable rotation. The design of the hinge assembly 5 strengthens the coordination between the internal components, improves the connection with the frame and the rotation stability, and provides important support for the movement and stability of the system.

[0036] In some preferred embodiments, the first rotating ring 9 is a cylinder with an opening in the middle, which is arranged on the protruding shaft 51 and contacts the fixed plate 52; the second rotating ring 10 includes a cylinder portion and a ring portion; the cylinder portion is penetrated by the protruding shaft 51 and abuts against the side of the first rotating ring 9 away from the fixed plate 52; the ring portion is arranged on the circumference of the cylinder portion, and an annular groove is formed between the first rotating ring 9 and the cylinder portion; a bearing 7 is arranged in the annular groove. Based on the previous implementation scheme, this design scheme reasonably arranges the bearing 7 between the first rotating ring 9 and the second rotating ring 10, which can reduce the friction of rotation, thereby improving the operating efficiency and stability of the inner wing 12 and the hinge assembly 5. The function of the bearing 7 is to support the rotating parts, reduce friction and reduce energy loss, and effectively extend the service life of the hinge assembly 5.

[0037] In some preferred embodiments, when the inner wings 12 of the two wings 1 are completely located in the first space and rotated to the same axial direction, the total length of the wing 1 is 2L. By completely folding the inner wings 12 of the two wings 1 and rotating them to the same axial direction, the length of the wing 1 can be minimized and the maneuverability of the aircraft can be improved. Such a design can reduce the resistance of the aircraft and set the length to match the length of other components in order to achieve the best flight effect.

[0038] In some preferred embodiments, when the inner wings 12 of the two wings 1 are completely outside the first space and rotated to the same axial direction, the total length of the wings 1 is 3.5L. The length is limited here mainly to reasonably design the lengths of the outer wings 11 and the inner wings 12 in order to obtain better performance in specific aspects.

[0039] The beneficial effects brought by the utility model include:

[0040] The lift is controllable and the maneuverability is high. The outer wing 11 of the utility model can be extended and retracted once. When launching out of the tube, the outer wing 11 is extended to increase the wingspan and improve the lift, thereby ensuring the low-speed endurance of the aircraft. When diving, the outer wing 11 is retracted to reduce the wingspan and reduce the lift, thereby increasing the diving speed and achieving high maneuverability.

[0041] Compared with the conventional wings which are driven to fold by torsion springs or coil springs, the utility model adopts an external tension spring 8 and uses a hinge to connect the two inner wings 12, which has a simple structure; compared with the conventional wings which are driven to retract by a motor with a gear rack or a spiral screw, the gas gunpowder structure is simple and not prone to failure;

[0042] The utility model is convenient to transport and carry, and occupies little space. The wings of the utility model can be folded and loaded into a launching tube, and are convenient to carry and transport during field patrols or single-soldier combat.

[0043] In the description of the present application, it should be noted that the terms "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0044] It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0045] The above description is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

Claims

1. A deployable retractable wing driven by gas and explosives, characterized in that: It includes: A wing (1) comprises an inner wing (12) and an outer wing (11); a first space is provided in the outer wing (11), and the inner wing (12) is axially sleeved in the first space; A gas-driven telescopic device (2) is located inside the wing (1), one end of which is connected to the inner wing (12) and the other end of which is connected to the outer wing (11); the gas-driven telescopic device (2) is telescopic along the length direction of the outer wing (11).

2. The deployable retractable wing driven by gas and explosives as claimed in claim 1, characterized in that: The gas-driven telescopic device (2) comprises a cylinder assembly (4) and a piston rod (3); The inner wing (12) is provided with a mounting groove for fixing the cylinder assembly (4); one end of the piston rod (3) is movably arranged in the cylinder assembly (4), and the other end is connected to the inner wall of the outer wing (11).

3. The deployable retractable wing driven by gas and explosives as claimed in claim 2, characterized in that: The cylinder assembly (4) comprises a pipe (43) sealed at both ends, wherein a movable seal member (31) is arranged in the pipe (43) to separate the pipe into a second space (32) and a third space (33), and the movable seal member (31) is fixedly connected to one end of the piston rod (3) extending into the cylinder assembly (4); The cylinder assembly (4) comprises a first gas source assembly (41) for introducing high-pressure gas into the second space (32), and a second gas source assembly (42) for introducing high-pressure gas into the third space (33).

4. The deployable retractable wing driven by gas and explosives as claimed in claim 3, characterized in that: The first gas source component (41) comprises a first adapter (412) connected to one end of the pipeline (43); the end of the first adapter (412) away from the pipeline (43) is connected to a first gunpowder placing tube (411); the end of the first gunpowder placing tube (411) away from the first adapter (412) is provided with a first igniter (413); The second gas source component (42) comprises a second adapter (422) connected to the other end of the pipeline (43); the end of the second adapter (422) away from the pipeline (43) is connected to a second gunpowder placing tube (421); the end of the second gunpowder placing tube (421) away from the second adapter (422) is provided with a second igniter (423).

5. The deployable and retractable wing driven by gas and explosives as claimed in claim 4, characterized in that: The first gunpowder placing tube (411) comprises a bend; one end of the bend is connected to the first adapter (412), the other end of the bend is provided with a parallel portion parallel to the pipeline (43), and the other end of the parallel portion is provided with the first igniter (413); The second gunpowder placing tube (421) also includes the bend; one end of the bend is connected to the second adapter (422), the other end of the bend is also provided with the parallel portion parallel to the pipeline (43), and the other end of the parallel portion is provided with the second igniter (423); The two parallel portions are located on the same straight line.

6. The deployable and retractable wing driven by gas and explosives as claimed in claim 1, characterized in that: A connecting piece (13) is provided at one end of the inner wing (12) away from the outer wing (11), and a tension spring connecting portion (14) is provided on the connecting piece (13); a tension spring (8) is provided on the tension spring connecting portion (14), and the other end of the tension spring (8) is connected to the frame; The connecting parts (13) of the two wings (1) are hingedly connected via a hinge assembly (5), and the hinge assembly (5) is used for fixedly connecting to the frame.

7. The deployable and retractable wing driven by gas and explosives as claimed in claim 6, characterized in that: The hinge assembly (5) comprises a first rotating ring (9), a second rotating ring (10), a fixing plate (52) and a limiting nut (6); the fixing plate (52) is fixedly connected to the frame, and a protruding shaft (51) is provided at the middle part of the fixing plate (52); the first rotating ring (9) and the second rotating ring (10) are stacked on the protruding shaft (51) from top to bottom, and the limiting nut (6) is provided on the protruding shaft (51) and abuts against the second rotating ring (10) located on the outside; The connecting parts (13) of the two inner wings (12) are rotatably connected to the first swivel (9) and the second swivel (10) respectively.

8. The deployable and retractable wing driven by gas and explosives as claimed in claim 7, characterized in that: The first rotating ring (9) is a cylinder with an opening in the middle, which is arranged on the protruding shaft (51) and contacts the fixing plate (52); The second rotating ring (10) comprises a barrel portion and a ring portion; the barrel portion is penetrated by the protruding shaft (51) and abuts against a surface of the first rotating ring (9) away from the fixing plate (52); the ring portion is arranged on the circumference of the barrel portion and forms an annular groove between the first rotating ring (9) and the barrel portion; a bearing (7) is arranged in the annular groove; The barrel portion passes through the protruding shaft (51) and abuts against the first rotating ring (9); the ring portion is arranged on the circumference of the barrel portion and forms an annular groove with the first rotating ring (9); a bearing (7) is arranged in the annular groove; the limiting nut (6) is arranged on the protruding shaft (51) and abuts against the second rotating ring (10).

9. The deployable and retractable wing driven by gas and explosives as claimed in claim 6, characterized in that: When the inner wings (12) of the two wings (1) are completely located in the first space and rotated to the same axial direction, the total length of the wings (1) is 2L.

10. The deployable and retractable wing driven by gas and explosives as claimed in claim 6, characterized in that: When the inner wings (12) of the two wings (1) are completely located outside the first space and rotated to the same axial direction, the total length of the wings (1) is 3.5L.

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