Composite plug-in fixing mechanism and launching device

Abstract

The present invention provides a composite plug-in fixing mechanism and a launch device, relating to the technical field of launch devices. The composite plug-in fixing mechanism includes an axial fixing mechanism and a plug-in mechanism. The axial fixing mechanism includes two sets of elastic components and two connecting seats, with locking members installed in the connecting seats. The plug-in mechanism includes a limit support, a telescopic component, and a second combustible belt. The limit support is installed on the inner side wall of the launch tube, and a limit slot is provided on the limit support. An elastic member is provided in the limit slot. The first end of the telescopic component is installed on the inner side wall of the launch tube, and a limit pin is provided at the second end of the telescopic component. The limit pin is connected to a cable control plug via a pull cord. The telescopic component can be extended to limit the limit pin in the limit slot. The second combustible belt can limit the limit pin in the limit slot, while the limit pin compresses the elastic member. The composite plug-in fixing mechanism can solve the problems of axial fixing and unlocking of missiles, rockets, and other launchers, as well as the automatic removal of the cable control plug.

Description

Technical Field

[0001] The present invention relates to the technical field of engineering launch devices, and in particular to a composite plug-in and fixing mechanism and a launch device. Background Art

[0002] At present, missiles, rockets and other projectiles need to be fixed in the launch tube through an axial fixing mechanism before launch. When launch is required, the bolts are pulled off to unlock the fixation of the missiles, rockets and other projectiles. At the same time, missiles, rockets and other projectiles need to be connected to the launch control system through a cable control plug before launch. When launch is required, the cable control plug is disconnected from the launch control system to complete the launch of the missiles, rockets and other projectiles.

[0003] Existing axial securing mechanisms require precise design of the bolt weakening slots and high bolt material homogeneity, otherwise the required breaking force will be inconsistent. Alternatively, explosive bolts can be used to unlock the bolts, but this method requires additional electrical system design, reducing reliability, and the presence of pyrotechnics significantly increases safety risks. Existing launchers use actuator-powered cable control plugs for plugging and unplugging, but this method requires additional power to drive the actuator, requiring additional mechanical and electrical system design, and reducing reliability. Summary of the Invention

[0004] In response to the above-mentioned problems in the prior art, the present application proposes a composite plug-in and fixing mechanism and a launching device, which can solve the problems of axial fixing and unlocking of missiles, rockets and other launchers and automatic unplugging of cable control plugs.

[0005] One aspect of the present invention provides a composite plug-in fixing mechanism, which is installed in a launching tube and includes:

[0006] An axial fixing mechanism, comprising two groups of elastic components and two connecting seats, wherein the first ends of the two groups of elastic components are mounted on opposite radial sides of the inner side wall of the launch tube in a one-to-one correspondence, and the second ends of the two groups of elastic components are capable of extending and contracting along the radial direction of the launch tube, the first ends of the two connecting seats are connected to the second ends of the two groups of elastic components in a one-to-one correspondence, and the second ends of the two connecting seats are connected by a first combustible belt, and a locking member is installed in the connecting seat; and

[0007] The plug-in and pull-out mechanism includes a limit support, a telescopic assembly, and a second combustible belt. The limit support is installed on the inner side wall of the launch tube, and a limit groove is provided on the limit support. An elastic member is provided in the limit groove; the first end of the telescopic assembly is installed on the inner side wall of the launch tube, and the second end of the telescopic assembly is provided with a limit pin, and the limit pin is connected to the cable control plug through a pull rope. The telescopic assembly can be extended to limit the limit pin in the limit groove; the first end of the second combustible belt is connected to the first combustible belt, and the second end of the second combustible belt can limit the limit pin in the limit groove, and at the same time, the limit pin compresses the elastic member;

[0008] In which, the locking piece can be connected to the launch projectile to limit the axial position of the launch projectile in the launch tube, and when the first combustible belt is disconnected, the locking piece is disengaged from the launch projectile by the action of the elastic component and unlocks the launch projectile; at the same time, the second combustible belt is disconnected, and the elastic piece can drive the limit pin to disengage from the limit groove, and at the same time the telescopic component contracts to allow the pull rope to pull out the cable control plug.

[0009] As a further improvement of the above technical solution:

[0010] The above-mentioned composite plug-in and fixing mechanism, further, the connecting seat includes a first support seat connected to the second end of the elastic component and a second support seat connected to the first combustible belt, the first support seat and the second support seat are connected by a guide column, and the locking member is installed on the first support seat.

[0011] The above-mentioned composite plug-in and fixing mechanism further has a guide seat installed in the launching tube, the guide seat is provided in a guide groove extending radially along the launching tube, and the guide column is slidably arranged in the guide groove.

[0012] The above-mentioned composite plug-in and fixing mechanism, further, the locking member is a locking pin, the locking pin extends radially along the launching tube, the tail of the launching bullet is provided with a connecting member, the connecting member is provided with a pin hole, and the locking pin can be passed through the pin hole.

[0013] The above-mentioned composite plug-in and fixing mechanism further has the following features: the limiting groove extends along the axial direction of the launching tube; a steering shaft is installed on the inner side wall of the launching tube; the second end of the second combustible belt bypasses the steering shaft so that the limiting pin is limited in the limiting groove.

[0014] The above-mentioned composite plug-in and fixing mechanism further has the following feature: the second end of the second combustible belt bypasses the limiting pin and is connected to the limiting support.

[0015] The above-mentioned composite plug-in and fixing mechanism further comprises: the telescopic assembly includes a telescopic spring and hinged seats respectively installed at both ends of the telescopic spring, one of the hinged seats is hinged to the inner wall of the launching tube, and the other hinged seat is installed with the limit pin.

[0016] The above-mentioned composite plug-in and fixing mechanism further has the following features: the limit support is also provided with a guide groove gradually inclined toward the inner side wall of the launch tube along the forward direction of the launch projectile; a rigid pull-out socket is installed at the tail of the launch projectile; the limit pin can be slidably installed on the rigid pull-out socket along the radial direction of the launch tube; the rigid pull-out socket can drive the limit pin to move along the guide groove so that the pull rope can pull out the cable control plug.

[0017] The above-mentioned composite plug-in and fixing mechanism, further, the first combustible belt and the second combustible belt are both made of magnesium material.

[0018] Another aspect of the present invention provides a launching device, which includes a launching tube and the composite plug-in and fixing mechanism as described above installed inside the launching tube.

[0019] The above technical features can be combined in various suitable ways or replaced by equivalent technical features, as long as the purpose of the present invention can be achieved.

[0020] The composite plug-in / fixture mechanism and launcher provided by the present invention, compared with existing technologies, have at least the following advantages: When a projectile, such as a missile or rocket, is to be transported, the projectile is placed in a launch tube, and a locking member is connected to the projectile to limit the projectile's axial position in the launch tube. When the projectile is to be launched, the projectile's gas generator is ignited. The jet ejected by the gas generator contains a high-pressure jet that directly impacts the first combustible band, causing it to break. The locking member, acting under the action of an elastic component, disengages and unlocks the projectile, allowing the projectile to move axially along the launch tube. Simultaneously, the second combustible band breaks, causing the elastic member to drive the limiting pin out of the limiting groove, and the telescopic assembly to retract, allowing the pull cord to unplug the cable control plug. The composite plug-in / fixture mechanism utilizes the gas generator to quickly fuse the combustible band, thereby axially unlocking the projectile. Simultaneously, the interlocking unlocking limiting pin disengages the limiting groove, and the telescopic assembly retracts, allowing the pull cord to unplug the cable control plug. The composite plug-in and fixing mechanism adopts the purely mechanical characteristics of the combustible belt, and there is no other external force to unlock it. It does not need to use traditional methods such as explosive bolts and electrical signals to unlock it, saving explosive bolts, unlocking mechanisms, multiple sets of connector combinations, cable networks, etc. The overall cost of the machine is low and the reliability and safety are high.

[0021] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments. It should be understood that the following drawings only illustrate certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying any creative work.

[0023] The present invention will be described in more detail below based on embodiments and with reference to the accompanying drawings, wherein:

[0024] Figure 1 Shows a structural schematic diagram of a composite plug-in and fixing mechanism provided by an embodiment of the present invention;

[0025] Figure 2 A schematic structural diagram of the axial fixing mechanism of the composite plug-in fixing mechanism provided by an embodiment of the present invention is shown;

[0026] Figure 3 A schematic structural diagram showing a connecting seat of an axial fixing mechanism of a composite plug-in fixing mechanism provided by an embodiment of the present invention;

[0027] Figure 4 A schematic diagram showing the structure of the connector of the axial fixing mechanism of the composite plug-in fixing mechanism provided by an embodiment of the present invention

[0028] Figure 5 A schematic structural diagram of a limit support of an insertion mechanism of a composite insertion and fixing mechanism provided by an embodiment of the present invention is shown;

[0029] Figure 6 A schematic diagram of the rigid plug socket installation structure of the plugging mechanism of the composite plugging and fixing mechanism provided by an embodiment of the present invention is shown.

[0030] In the drawings, like reference numerals are used for like parts, but the drawings are not necessarily true to scale.

[0031] Reference numerals:

[0032] 100- axial fixing mechanism, 110- elastic component, 120- connecting seat, 121- first support seat, 122- second support seat, 123- guide column, 130- first combustible belt, 140- locking member, 141- weakening groove, 150- guide seat, 160- connecting member, 161- axial bolt, 162- pin shaft hole, 200- plug-in and pull-out mechanism, 210- limiting support, 211- limiting groove, 212- guide groove, 220- elastic member, 230- telescopic component, 231- telescopic spring, 232- hinged seat, 240- limiting pin, 250- cable control plug, 260- pull rope, 270- second combustible belt, 280- steering shaft, 290- rigid pull-out socket, 300- launching tube. DETAILED DESCRIPTION

[0033] The following describes embodiments of the present invention in detail. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended only to explain the present invention and are not to be construed as limiting the present invention.

[0034] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to 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 invention 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 should not be understood as limiting the present invention.

[0035] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature identified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0036] In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "connect," "fixed," etc. should be understood broadly. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0037] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0038] The present invention will be further described below with reference to the accompanying drawings.

[0039] The embodiment of the present invention provides a composite plug-in fixing mechanism and a launching device, which can solve the problems of axial fixing and unlocking of missiles, rockets and other launching projects and automatic unplugging of the cable control plug 250.

[0040] See also Figure 1 and Figure 2 The composite plug-in fixing mechanism provided by an embodiment of the present invention is installed in a launching tube 300 , and the composite plug-in fixing mechanism includes an axial fixing mechanism 100 and a plug-in mechanism 200 .

[0041] The axial fixing mechanism 100 includes two groups of elastic components 110 and two connecting seats 120. The first ends of the two groups of elastic components 110 are installed one-to-one on the radially opposite sides of the inner wall of the launch tube 300, and the second ends of the two groups of elastic components 110 can be extended and retracted along the radial direction of the launch tube 300. The first ends of the two connecting seats 120 are connected one-to-one to the second ends of the two groups of elastic components 110, and the second ends of the two connecting seats 120 are connected through the first combustible belt 130. A locking piece 140 is installed in the connecting seat 120.

[0042] The plug-in and pull-out mechanism 200 includes a limit support 210, a telescopic assembly 230, and a second combustible belt 270. The limit support 210 is installed on the inner wall of the launch tube 300. A limit groove 211 is provided on the limit support 210, and an elastic member 220 is provided in the limit groove 211; the first end of the telescopic assembly 230 is installed on the inner wall of the launch tube 300, and the second end of the telescopic assembly 230 is provided with a limit pin 240. The limit pin 240 is connected to the cable control plug 250 through a pull rope 260, and the telescopic assembly 230 can be extended to limit the limit pin 240 in the limit groove 211; the first end of the second combustible belt 270 is connected to the first combustible belt 130, and the second end of the second combustible belt 270 can limit the limit pin 240 in the limit groove 211, and at the same time, the limit pin 240 compresses the elastic member 220.

[0043] Among them, the locking piece 140 can be connected to the launch projectile to limit the axial position of the launch projectile in the launch tube 300, and when the first combustible belt 130 is disconnected, the locking piece 140 is disengaged from the unlocked launch projectile under the action of the elastic component 110; at the same time, the second combustible belt 270 is disconnected, and the elastic component 220 can drive the limiting pin 240 to disengage from the limiting groove 211, and at the same time the telescopic component 230 contracts to allow the pull rope 260 to pull out the cable control plug 250.

[0044] When a projectile, such as a missile or rocket, is to be transported, it is placed in the launch tube 300. The locking member 140 is connected to the projectile to limit the projectile's axial position in the launch tube 300. When the projectile is to be launched, the gas generator of the projectile is ignited. The jet ejected by the gas generator contains a high-pressure jet, which directly impacts the first combustible band 130, causing it to break. The locking member 140, under the action of the elastic assembly 110, disengages and unlocks the projectile, allowing the projectile to move axially along the launch tube 300. Simultaneously, the second combustible band 270 breaks, and the elastic member 220 drives the limiting pin 240 out of the limiting groove 211. Simultaneously, the telescopic assembly 230 contracts, allowing the pull cord 260 to unplug the cable control plug 250.

[0045] The composite plug-in and fixing mechanism provided in an embodiment of the present invention utilizes a gas generator to quickly fuse the combustible belt, thereby completing the axial unlocking of the projectile. At the same time, the interlocking unlocking limit pin 240 disengages from the limit groove 211, and the telescopic assembly 230 contracts to allow the pull rope 260 to pull out the cable control plug 250.

[0046] The composite plug-in and fixing mechanism provided in the embodiment of the present invention adopts the purely mechanical characteristics of the combustible belt, and there is no other external force to unlock it. There is no need to use traditional methods such as explosive bolts and electrical signals to unlock it, which saves explosive bolts, unlocking mechanisms, multiple sets of connector combinations, cable networks, etc. The cost of the whole machine is low and the reliability and safety are high.

[0047] The composite plug-in fixing mechanism provided by the embodiment of the present invention is specifically Figure 3 The connecting base 120 includes a first support base 121 connected to the second end of the elastic component 110 and a second support base 122 connected to the first combustible belt 130. The first support base 121 and the second support base 122 are connected by a guide post 123, and the locking member 140 is mounted on the first support base 121. A guide base 150 is installed in the launch tube 300. The guide base 150 is provided in a guide groove 212 extending radially along the launch tube 300. The guide post 123 slides in the guide groove 212. The guide base 150 allows the guide post 123 to move radially along the launch tube 300 when the first combustible belt 130 breaks, thereby causing the connecting base 120 to move radially along the launch tube 300 and preventing the connecting base 120 from moving in other directions.

[0048] Specifically, the locking member 140 is a locking pin, which extends radially along the launch tube 300. A connecting member 160 is provided at the tail of the launcher, and a pin hole 162 is provided on the connecting member 160. The locking pin can be inserted into the pin hole 162. Figure 4 The first end of the connector 160 is provided with an axial bolt 161, which is used to be threadedly connected to the tail of the projectile. A pin hole 162 is provided at the second end of the connector 160. A weakening groove 141 is formed along the circumference of the end of the locking pin near the first support seat 121. When the projectile is ignited and moves upward, the first combustible band 130 is not broken due to the three effects of the elastic component 110 pulling, the gas blowing, and the high-temperature burning. The upward axial force of the projectile pulls the locking pin along the weakening groove 141, thereby unlocking the projectile.

[0049] The composite plug-in fixing mechanism provided by the embodiment of the present invention is specifically Figure 5 The limiting groove 211 extends axially along the launch tube 300. A steering shaft 280 is mounted on the inner sidewall of the launch tube 300. The second end of the second combustible belt 270 passes around the steering shaft 280, allowing the limiting pin 240 to be retained in the limiting groove 211. The second end of the second combustible belt 270 passes around the limiting pin 240 and is connected to the limiting support 210. The steering shaft 280 is used to redirect the tension of the second combustible belt 270, ensuring that the tension direction of the second combustible belt 270 is consistent with the extension direction of the limiting groove 211.

[0050] The composite plug-in and fixation mechanism provided by the embodiment of the present invention specifically comprises a telescopic assembly 230 comprising a telescopic spring 231 and hinged seats 232 mounted on either end of the telescopic spring 231. One hinged seat 232 is hingedly connected to the inner wall of the launch tube 300, and the other hinged seat 232 is mounted with a limit pin 240. Because the limit pin 240 is limited in movement between being in and out of the limit slot 211, the hinged connection between the telescopic assembly 230 and the inner wall of the launch tube 300 prevents the movement of the limit pin 240 from being affected by the connection method between the telescopic assembly 230 and the inner wall of the launch tube 300.

[0051] The composite plug-in fixing mechanism provided by the embodiment of the present invention further has a guide groove 212 which is gradually inclined toward the inner wall of the launch tube 300 along the forward direction of the launch projectile. Figure 6 A rigid extraction socket 290 is mounted at the rear of the projectile. A stop pin 240 is mounted on the rigid extraction socket 290 and can slide radially along the launch tube 300. The rigid extraction socket 290 drives the stop pin 240 along the guide slot 212, allowing the pull cord 260 to disconnect from the cable control plug 250. When the projectile ignites and moves upward, the second combustible band 270 remains intact due to the push of the elastic member 220, the blowing of the gas generator, and the high-temperature combustion. The axial force of the projectile's upward motion drives the rigid extraction socket along the oblique guide slot 212, allowing the pull cord 260 to disconnect from the cable control plug 250.

[0052] In this embodiment, the first combustible belt 130 and the second combustible belt 270 are both made of magnesium, which has high mechanical properties and a low melting point.

[0053] An embodiment of the present invention further provides a launcher, comprising a launch tube 300 and a composite plug-in / fixing mechanism, such as provided in any of the aforementioned embodiments, mounted within the launch tube 300. The specific structure of the composite plug-in / fixing mechanism is similar to that of the aforementioned embodiments. Since the present launcher utilizes all of the technical solutions of all of the aforementioned embodiments, it possesses at least all of the beneficial effects of the technical solutions of the aforementioned embodiments, and therefore will not be further detailed here.

[0054] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0055] Although the present invention is described herein with reference to specific embodiments, it should be understood that these embodiments are merely illustrative of the principles and applications of the invention. It should be understood that many modifications may be made to the illustrative embodiments, and that other arrangements may be devised, without departing from the spirit and scope of the invention as defined by the appended claims. It should be understood that the various dependent claims and features described herein may be combined in ways other than those described in the original claims. It should also be understood that features described in conjunction with individual embodiments may be employed in conjunction with other described embodiments.

Claims

1. A composite plug-in fixing mechanism, characterized in that: The composite plug-in fixing mechanism is installed in the launching tube, and the composite plug-in fixing mechanism includes: An axial fixing mechanism, comprising two groups of elastic components and two connecting seats, wherein the first ends of the two groups of elastic components are mounted on opposite radial sides of the inner side wall of the launch tube in a one-to-one correspondence, and the second ends of the two groups of elastic components are capable of extending and contracting along the radial direction of the launch tube, the first ends of the two connecting seats are connected to the second ends of the two groups of elastic components in a one-to-one correspondence, and the second ends of the two connecting seats are connected by a first combustible belt, and a locking member is installed in the connecting seat; and The plug-in and pull-out mechanism includes a limit support, a telescopic assembly, and a second combustible belt. The limit support is installed on the inner side wall of the launch tube, and a limit groove is provided on the limit support. An elastic member is provided in the limit groove; the first end of the telescopic assembly is installed on the inner side wall of the launch tube, and the second end of the telescopic assembly is provided with a limit pin, and the limit pin is connected to the cable control plug through a pull rope. The telescopic assembly can be extended to limit the limit pin in the limit groove; the first end of the second combustible belt is connected to the first combustible belt, and the second end of the second combustible belt can limit the limit pin in the limit groove, and at the same time, the limit pin compresses the elastic member; In which, the locking piece can be connected to the launch projectile to limit the axial position of the launch projectile in the launch tube, and when the first combustible belt is disconnected, the locking piece is disengaged from the launch projectile by the action of the elastic component and unlocks the launch projectile; at the same time, the second combustible belt is disconnected, and the elastic piece can drive the limit pin to disengage from the limit groove, and at the same time the telescopic component contracts to allow the pull rope to pull out the cable control plug.

2. The composite plug-in and fixing mechanism according to claim 1, characterized in that: The connecting seat includes a first support seat connected to the second end of the elastic component and a second support seat connected to the first combustible belt. The first support seat and the second support seat are connected through a guide column, and the locking member is installed on the first support seat.

3. The composite plug-in and fixing mechanism according to claim 2, characterized in that: A guide seat is installed in the launching tube, and the guide seat is opened in a guide groove extending along the radial direction of the launching tube. The guide column is slidably arranged in the guide groove.

4. The composite plug-in and fixing mechanism according to claim 2, characterized in that: The locking piece is a locking pin, which extends radially along the launching tube. A connecting piece is provided at the tail of the launching bullet, and a pin hole is provided on the connecting piece. The locking pin can be inserted into the pin hole.

5. The composite plug-in and fixing mechanism according to claim 1, characterized in that: The limiting groove extends along the axial direction of the launching tube, and a steering shaft is installed on the inner side wall of the launching tube. The second end of the second combustible belt passes around the steering shaft so that the limiting pin is limited in the limiting groove.

6. The composite plug-in and fixing mechanism according to claim 5, characterized in that: The second end of the second combustible belt bypasses the limiting pin and is connected to the limiting support.

7. The composite plug-in and fixing mechanism according to claim 1, characterized in that: The telescopic assembly includes a telescopic spring and hinged seats respectively installed on both ends of the telescopic spring, one of the hinged seats is hinged to the inner side wall of the launching tube, and the other hinged seat is installed with the limit pin.

8. The composite plug-in and fixing mechanism according to claim 1, characterized in that: The limit support is also provided with a guide groove which is gradually inclined toward the inner side wall of the launch tube along the forward direction of the launch projectile. A rigid pull-out socket is installed at the tail of the launch projectile. The limit pin can be slidably installed on the rigid pull-out socket along the radial direction of the launch tube. The rigid pull-out socket can drive the limit pin to move along the guide groove so that the pull rope can pull out the cable control plug.

9. The composite plug-in and fixing mechanism according to claim 1, characterized in that: The first combustible belt and the second combustible belt are both made of magnesium.

10. A launching device, characterized in that: The launching device includes a launching tube and a composite plug-in and fixing mechanism as claimed in any one of claims 1 to 9 installed inside the launching tube.

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