Rear-mounted mechanical magazine lock

Abstract

This invention provides a rear-mounted mechanical fixed missile device, comprising: a missile, a housing, a locking component, a clamping component, a connecting rod component, a pin component, a mounting bracket, a strip-shaped component, and a base; the housing includes: an inner top surface at the rear end of the housing; the mounting bracket is securely connected to the inner top surface at the rear end of the housing; the housing also includes: an inner bottom surface at the rear end of the housing; the base is securely connected to the inner bottom surface at the rear end of the housing; the locking component is disposed between the clamping component and the strip-shaped component; the connecting rod component and the locking component are mounted on the mounting bracket and the base via the pin component. This invention reduces the cross-section of the launch box, thereby lowering costs; this invention also improves the level of weapon system integration.

Description

Technical Field

[0001] This invention relates to the field of missile launch technology, specifically to a rear-mounted mechanical solid-propellant device, and more particularly to a rear-mounted purely mechanical solid-propellant device. Background Technology

[0002] In existing technologies, the ammunition fixing device for the launch box is mostly located on the side of the launch box and is unlocked using pyrotechnics, which results in a larger launch box cross-section, higher cost, and is not conducive to improving the level of weapon system integration.

[0003] Patent document CN205482628U discloses a dehumidification system for an anti-ship missile launch box, including a main outer shell with an inner cavity; it also includes an air inlet and an air outlet formed within the inner cavity; an internal ambient temperature control unit disposed outside the main outer shell; and a dehumidification air path formed within the main outer shell; wherein the dehumidification air path connects the air inlet and the air outlet; the internal ambient temperature control unit and the dehumidification air path are connected, forming a dehumidification airflow circulation within the dehumidification air path. An anti-ship missile launch box is also disclosed. This patent still has room for improvement in terms of weapon system integration. Summary of the Invention

[0004] In view of the deficiencies in the prior art, the purpose of this invention is to provide a rear-mounted mechanical fixed spring device.

[0005] A rear-mounted mechanical fixed missile device according to the present invention includes: a missile 1, a housing 2, a locking component, a clamping component, a connecting rod component, a pin component, a lifting base 4, a strip component, and a base 17; the housing 2 includes: an inner top surface at the rear end of the housing; the lifting base 4 is fastened to the inner top surface at the rear end of the housing; the housing 2 includes: an inner bottom surface at the rear end of the housing; the base 17 is fastened to the inner bottom surface at the rear end of the housing; the locking component is disposed between the clamping component and the strip component; the connecting rod component and the locking component are mounted on the lifting base 4 and the base 17 via the pin component.

[0006] Preferably, the locking component includes: a first pin 10, a second pin 12, and a locking cylinder 15; the first pin 10, the second pin 12, and the locking cylinder 15 are disposed between the clamping component and the strip component.

[0007] Preferably, the clamping components include: a first clamping member 8, a second clamping member 13, and a third clamping member 18; the locking component is disposed between the first clamping member 8, the second clamping member 13, the third clamping member 18, and the strip component.

[0008] Preferably, the strip component includes a magnesium strip 11; the locking component is disposed between the clamping component and the magnesium strip 11.

[0009] Preferably, the connecting rod assembly includes: a first connecting rod 5, a second connecting rod 7, and a third connecting rod 14; the first connecting rod 5, the second connecting rod 7, the third connecting rod 14, and the locking component are mounted on the hanger 4 and the base 17 via a pin assembly.

[0010] Preferably, the pin assembly includes: a first pin 3, a second pin 6, a third pin 9, a fourth pin 16, and a fifth pin 19; the connecting rod assembly and the locking assembly are mounted on the hanger 4 and the base 17 via the first pin 3, the second pin 6, the third pin 9, the fourth pin 16, and the fifth pin 19.

[0011] Preferably, the missile 1 includes: a missile rear end face; the mounting base 4 includes: a mounting base block; the missile rear end face rests against the mounting base block along the axial direction.

[0012] Preferably, the missile 1 further includes: a missile groove facet; the rear end facet of the missile, through a screw-locking cylinder 15, drives the first connecting rod 5 to rotate and hook onto the missile groove facet, thereby securing the missile 1 and realizing the locking function of the missile securing device. At this time, the magnesium strip is located directly behind the engine nozzle of the missile 1.

[0013] Preferably, the missile 1 further includes a missile engine; when the missile engine is ignited, the engine gas scours, ablates, and weakens the strip-shaped component. When the thrust of the missile engine increases to the point of breaking the magnesium strip 11, the first connecting rod 5 flips over, disengages from the vertical surface of the missile groove, releases the fixation on the missile 1, and realizes the function of unlocking the fixed missile device.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] 1. The present invention has a reasonable structure and is easy to use, and can overcome the defects of the prior art;

[0016] 2. This invention reduces the cross-section of the launch box, thereby lowering costs;

[0017] 3. This invention improves the level of weapon system integration. Attached Figure Description

[0018] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0019] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0020] In the picture:

[0021] Missile 1 Magnesium Belt 11

[0022] Box 2 Second pin 12

[0023] First pin 3; Second clamping element 13

[0024] Hanger 4, Third Link 14

[0025] First link 5, locking cylinder 15

[0026] Second pin 6, Fourth pin 16

[0027] Second link 7, base 17

[0028] First clamping component 8; Third clamping component 18

[0029] Third pin 9, Fifth pin 19

[0030] First pin 10 Detailed Implementation

[0031] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0032] like Figure 1 As shown, a rear-mounted mechanical fixed missile device according to the present invention includes: a missile 1, a housing 2, a locking component, a clamping component, a connecting rod component, a pin component, a lifting base 4, a strip component, and a base 17; the housing 2 includes: an inner top surface at the rear end of the housing; the lifting base 4 is fastened to the inner top surface at the rear end of the housing; the housing 2 includes: an inner bottom surface at the rear end of the housing; the base 17 is fastened to the inner bottom surface at the rear end of the housing; the locking component is disposed between the clamping component and the strip component; the connecting rod component and the locking component are mounted on the lifting base 4 and the base 17 via the pin component.

[0033] Preferably, the locking component includes: a first pin 10, a second pin 12, and a locking cylinder 15; the first pin 10, the second pin 12, and the locking cylinder 15 are disposed between the clamping component and the strip component.

[0034] Preferably, the clamping components include: a first clamping member 8, a second clamping member 13, and a third clamping member 18; the locking component is disposed between the first clamping member 8, the second clamping member 13, the third clamping member 18, and the strip component.

[0035] Preferably, the strip component includes a magnesium strip 11; the locking component is disposed between the clamping component and the magnesium strip 11.

[0036] Preferably, the connecting rod assembly includes: a first connecting rod 5, a second connecting rod 7, and a third connecting rod 14; the first connecting rod 5, the second connecting rod 7, the third connecting rod 14, and the locking component are mounted on the hanger 4 and the base 17 via a pin assembly.

[0037] Preferably, the pin assembly includes: a first pin 3, a second pin 6, a third pin 9, a fourth pin 16, and a fifth pin 19; the connecting rod assembly and the locking assembly are mounted on the hanger 4 and the base 17 via the first pin 3, the second pin 6, the third pin 9, the fourth pin 16, and the fifth pin 19.

[0038] Preferably, the missile 1 includes: a missile rear end face; the mounting base 4 includes: a mounting base block; the missile rear end face rests against the mounting base block along the axial direction.

[0039] Preferably, the missile 1 further includes: a missile groove facet; the rear end facet of the missile, through a screw-locking cylinder 15, drives the first connecting rod 5 to rotate and hook onto the missile groove facet, thereby securing the missile 1 and realizing the locking function of the missile securing device. At this time, the magnesium strip is located directly behind the engine nozzle of the missile 1.

[0040] Preferably, the missile 1 further includes a missile engine; when the missile engine is ignited, the engine gas scours, ablates, and weakens the strip-shaped component. When the thrust of the missile engine increases to the point of breaking the magnesium strip 11, the first connecting rod 5 flips over, disengages from the vertical surface of the missile groove, releases the fixation on the missile 1, and realizes the function of unlocking the fixed missile device.

[0041] Specifically, in one embodiment, a rear-mounted purely mechanical fixed missile device includes: a missile, a housing, a first pin, a mounting base, a first connecting rod, a second pin, a second connecting rod, a first clamping member, a third pin, a first pin, a magnesium strip, a second pin, a second clamping member, a third connecting rod, a locking cylinder, a fourth pin, a base, a third clamping member, and a fifth pin. The mounting bracket and base are respectively fixed to the inner top and bottom surfaces of the rear end of the housing; the first clamping member, the second clamping member, the third clamping member, and the magnesium strip are connected by a first pin, a second pin, and a locking cylinder to form a locking component; the first connecting rod, the second connecting rod, the third connecting rod, and the locking component are connected by a first pin, a second pin, a third pin, a fourth pin, and a fifth pin and mounted on the mounting bracket and base; the rear end face of the missile rests axially against the mounting bracket block, and by turning the locking cylinder, the first connecting rod is rotated to hook the vertical surface of the missile groove, thereby securing the missile and realizing the locking function of the missile fixing device. At this time, the magnesium strip is located directly behind the missile engine nozzle.

[0042] Furthermore, when the missile engine ignites, the engine gas washes, ablates, and weakens the magnesium strip. When the engine thrust increases to the point of breaking the magnesium strip, the first connecting rod flips and disengages from the missile groove surface, releasing the missile from its fastening and realizing the missile fastening device unlocking function.

[0043] This invention has a reasonable structure, is easy to use, and can overcome the defects of the prior art; this invention reduces the cross-section of the launch box and lowers the cost; this invention improves the level of weapon system integration.

[0044] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0045] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A rear-mounted mechanical spring-loaded device, characterized in that, include: Missile (1), housing (2), locking components, clamping components, connecting rod components, pin components, lifting base (4), strip components and base (17); The box body (2) includes: the inner top surface at the rear end of the box body; The hanging bracket (4) is fastened to the inner top surface of the rear end of the box; The box body (2) includes: the inner bottom surface at the rear end of the box body; The base (17) is fastened to the inner bottom surface of the rear end of the box; the locking component includes: a first pin (10), a second pin (12) and a locking cylinder; the strip component includes: a magnesium strip (11); the clamping component includes: a first clamping member (8), a second clamping member (13) and a third clamping member (18); the first pin is disposed between the first clamping member and the magnesium strip, the second pin is disposed between the magnesium strip and the second clamping member, and the locking cylinder is disposed between the second clamping member and the third clamping member; the connecting rod component and the clamping component are connected by a pin component, the connecting rod component and the clamping component are mounted on the base by a pin component, and the connecting rod component is mounted on the hanger by a pin component; The linkage assembly includes: a first linkage (5), a second linkage (7), and a third linkage (14); the first linkage (5), the second linkage (7), and the third linkage (14) are connected in sequence by a pin assembly, and the first linkage and the third linkage are respectively mounted on the hanger and the base by the pin assembly; The missile (1) also includes: a missile groove facet; the rear end facet of the missile rotates to hook the first connecting rod (5) by rotating the locking cylinder (15) to hook the missile groove facet.

2. The rear-mounted mechanical spring-loaded device according to claim 1, characterized in that, The pin assembly includes: a first pin (3), a second pin (6), a third pin (9), a fourth pin (16), and a fifth pin (19); the first connecting rod is mounted on the hanger via the first pin, the first connecting rod and the second connecting rod are connected via the second pin, the second connecting rod and the third connecting rod are connected via the third pin, and the third connecting rod and the third clamping member are mounted on the base via the fourth pin and the fifth pin, respectively.

3. The rear-mounted mechanical spring-loaded device according to claim 1, characterized in that... , The suspension base (4) includes: a suspension base support block; The rear end face of the missile rests axially against the mounting block.

4. The rear-mounted mechanical spring-loaded device according to claim 3, characterized in that, The missile (1) also includes: a missile engine; When the missile engine thrust increases to the point that the magnesium strip (11) breaks, the first connecting rod (5) flips over, disengages from the missile groove surface, and releases the missile (1) from its fastening.

5. A rear-mounted mechanical spring-loaded device, characterized in that, include: Missile (1), housing (2), locking components, clamping components, connecting rod components, pin components, lifting base (4), strip components and base (17); The box body (2) includes: the inner top surface at the rear end of the box body; The hanging bracket (4) is fastened to the inner top surface of the rear end of the box; The box body (2) includes: the inner bottom surface at the rear end of the box body; The base (17) is fastened to the inner bottom surface of the rear end of the box; the locking component includes: a first pin (10), a second pin (12) and a locking cylinder; the strip component includes: a magnesium strip (11); the clamping component includes: a first clamping member (8), a second clamping member (13) and a third clamping member (18); the first pin is disposed between the first clamping member and the magnesium strip, the second pin is disposed between the magnesium strip and the second clamping member, and the locking cylinder is disposed between the second clamping member and the third clamping member; the connecting rod component and the clamping component are connected by a pin component, the connecting rod component and the clamping component are mounted on the base by a pin component, and the connecting rod component is mounted on the hanger by a pin component; The linkage assembly includes: a first linkage (5), a second linkage (7), and a third linkage (14); the first linkage (5), the second linkage (7), and the third linkage (14) are connected in sequence by a pin assembly, and the first linkage and the third linkage are respectively mounted on the hanger and the base by the pin assembly; The missile (1) also includes: a missile groove facet; the rear end facet of the missile rotates to hook the first connecting rod (5) by rotating the locking cylinder (15); The pin assembly includes: a first pin (3), a second pin (6), a third pin (9), a fourth pin (16), and a fifth pin (19); The first link is mounted on the hanger via the first pin, the first link and the second link are connected via the second pin, the second link and the third link are connected via the third pin, and the third link and the third clamping member are mounted on the base via the fourth pin and the fifth pin, respectively. The suspension base (4) includes: a suspension base support block; The rear end face of the missile rests axially against the mounting block; The missile (1) also includes: a missile engine; When the missile engine thrust increases to the point that the magnesium strip (11) breaks, the first connecting rod (5) flips over, disengages from the missile groove surface, and releases the missile (1) from its fastening.

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