Pressing device for folding missile empennage

Abstract

The utility model relates to a press-fit device for folding a missile empennage, and belongs to the technical field of missile empennage folding equipment, the press-fit device comprises a rack, a mounting seat mounted on the top surface of the rack and used for arranging an inner wing, and press-fit mechanisms symmetrically arranged on the two sides of the mounting seat; the pressing mechanism comprises a supporting base, a pressing piece installed on the supporting base and a pressing handle used for driving the pressing piece to rotate, and a rotating shaft of the pressing piece coincides with a rotating shaft of the pressing handle. The missile empennage folding device has the effect of reducing the labor intensity of operators in the missile empennage folding process.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of missile tail folding device technology, in particular to a pressing device for missile tail folding. BACKGROUND

[0002] The missile needs to detect the unfolding time and unfolding angle of the tail wing during the production assembly and factory inspection process, so the tail wing of the missile needs to be folded before detection. The tail wing includes an inner wing connected with the body and an outer wing rotatably connected with the inner wing. A self-locking structure is arranged between the inner wing and the outer wing, and when the inner wing and the outer wing reach a certain folding angle, the inner wing and the outer wing will be automatically locked. At present, the folding between the inner wing and the outer wing mainly relies on manual force to fold the inner wing and the outer wing to a certain angle to enable the inner wing and the outer wing to be self-locked, but the above-mentioned method needs to consume a lot of manpower.

[0003] For the related technology in the above, the inventor believes that a pressing device is needed to assist the operator to fold the missile tail. CONTENT OF THE UTILITY MODEL

[0004] In order to reduce the labor intensity of the operator in the folding process of the missile tail, the present application provides a pressing device for folding the missile tail.

[0005] The pressing device for folding the missile tail provided by the present application adopts the following technical solution:

[0006] A pressing device for folding the missile tail, comprising a rack, a mounting seat mounted on the top surface of the rack and used for arranging the inner wing of the missile, and a pressing mechanism symmetrically arranged on both sides of the mounting seat; the pressing mechanism comprises a support seat, a pressing piece mounted on the support seat, and a pressing handle used for driving the pressing piece to rotate, the distance from one end of the pressing handle away from the support seat to the support seat is greater than the distance from one end of the pressing piece away from the support seat to the support seat, and the rotation axis of the pressing piece coincides with the rotation axis of the pressing handle.

[0007] By adopting the above technical solution, during the folding process of the missile tail, the outer wing of the missile is first folded to the height at which the pressing piece can be pressed by manual operation, and then the operator lifts the pressing handle to drive the pressing piece to continuously press the outer wing downward, so that when the outer wing and the inner wing reach a certain folding angle, the outer wing and the inner wing of the missile are self-locked, and then the operator presses the pressing handle downward to lift the pressing piece away from the missile tail, so that the pressing piece does not interfere with the subsequent movement of the missile tail. The length of the pressing handle in the above pressing mechanism is relatively long, and the pressing mechanism assists the operator to press the missile tail, which effectively reduces the labor intensity of the operator in the folding process of the missile tail.

[0008] Optionally, the pressing member comprises two pressing blocks arranged at intervals on the support base and a pressing roller connected to the two pressing blocks at the end away from the support base.

[0009] By adopting the above technical scheme, the structure of the pressing member is disclosed, and the arrangement of the pressing roller can provide uniform pressure during the pressing process of the missile tail wing, so as to prevent the missile tail wing from deviating or deforming and to ensure the pressing quality.

[0010] Optionally, the bottom of the pressing block away from the support base has a recess.

[0011] By adopting the above technical scheme, the arrangement of the recess enables the pressing block to better avoid the protruding or recessed part on the missile tail wing during the pressing process, so as to ensure the smooth progress of the pressing process and avoid damage to the missile tail wing.

[0012] Optionally, the support base comprises a support rod and a support plate symmetrically arranged at both ends of the support rod and used for supporting the support rod; the pressing block has a mounting ring portion for the support rod to pass through, and the pressing block and the support rod are connected through a locking structure, the locking structure comprising a first key groove opened in the mounting ring portion, a second key groove opened in the outer wall of the support rod, and a locking key arranged in the first key groove and the second key groove.

[0013] By adopting the above technical scheme, the pressing block and the support rod are connected through the locking structure, which reduces the probability of loosening or deviation of the pressing block during the pressing process, and ensures that the pressing handle can drive the pressing member to perform the pressing action.

[0014] Optionally, the support plate has a mounting through hole for the support rod to pass through, the two ends of the support rod have mounting protrusions arranged on the side of the support base away from the pressing member, the end of the mounting protrusion towards the support plate is provided with a guide protrusion, and the support plate has a guide sliding groove for the guide protrusion to slide.

[0015] By adopting the above technical scheme, the cooperation between the guide protrusion and the guide sliding groove ensures the stable rotation of the pressing member mounted on the support rod, and reduces the probability of poor pressing effect caused by position deviation.

[0016] Optionally, the support plate is provided with a positioning groove at the guide sliding groove, the guide protrusion is provided with a plunger hole, and a ball head spring plunger is arranged in the plunger hole, when the pressing member is lifted to a certain height and does not interfere with the missile tail wing, the plunger ball head of the ball head spring plunger is clamped in the positioning groove.

[0017] By adopting the technical scheme, when the pressing handle is rotated clockwise by a certain angle, the plunger ball head of the ball head spring plunger is clamped in the positioning groove, at this time, the pressing piece does not interfere with the subsequent action of the missile tail wing, and the operator can stop rotating the pressing handle.

[0018] Optionally, one end of the pressing handle is provided with a plug-in protrusion, and a clamping protrusion is circumferentially arranged on the outer side wall of the plug-in protrusion; the support seat is provided with a mounting slot for inserting the plug-in protrusion, and a first clamping groove for inserting the clamping protrusion and arranged in the axial direction is arranged at the mounting slot, and a second clamping groove connected to the first clamping groove and arranged in the circumferential direction is arranged away from the one end of the pressing handle.

[0019] By adopting the technical scheme, the detachable connection between the pressing handle and the support seat is realized through the cooperation between the clamping protrusion and the first clamping groove and the second clamping groove, and the external occupied space of the pressing device for folding the missile tail wing when not in use is reduced.

[0020] Optionally, the bottom of the clamping protrusion is provided with a limiting protrusion, and the second clamping groove is provided with a limiting groove for clamping the limiting protrusion.

[0021] By adopting the technical scheme, the limiting protrusion of the clamping protrusion cooperates with the limiting groove on the second clamping groove, which helps to improve the stability of the clamping between the pressing handle and the support seat.

[0022] Optionally, the second connecting portion is provided with a rubber anti-skid sleeve away from one end of the support seat.

[0023] By adopting the technical scheme, the rubber anti-skid sleeve makes the operator hold the pressing handle more stably, reduces the probability of hand slipping, and improves the safety and reliability of operation. At the same time, the rubber anti-skid sleeve can also increase comfort and reduce the pressure on the hands during long-time operation.

[0024] In summary, the present application includes at least one of the following beneficial technical effects:

[0025] 1. A pressing device for folding a missile tail wing, in the folding process of the missile tail wing, first, the outer wing in the tail wing is folded to a height at which the pressing piece can be pressed by the operator, and then the pressing handle is lifted by the operator to realize the downward pressing of the pressing piece on the outer wing, which helps to reduce the labor intensity of the operator in the folding process of the missile tail wing.

[0026] 2. The arrangement of the recess groove on the pressing block helps to ensure the normal progress of the pressing process and reduce the probability of damage to the outer wing by the pressing block.

[0027] 3. The pressing handle is mounted on the support seat through the cooperation between the clamping protrusion and the first and second clamping grooves, which helps to reduce the external space occupied by the pressing device for missile tail folding when not in use. BRIEF DESCRIPTION OF DRAWINGS

[0028] Figure 1 is a schematic diagram of a pressing device for missile tail folding in the embodiment of the present application.

[0029] Figure 2 is a schematic diagram of a pressing mechanism in the embodiment of the present application.

[0030] Figure 3 is a schematic diagram of the cooperation between the pressing member and the support rod in the embodiment of the present application.

[0031] Figure 4 is a cross-sectional schematic diagram of the cooperation between the mounting protrusion and the support plate in the embodiment of the present application.

[0032] Figure 5 is a schematic diagram of the cooperation between the guide protrusion and the guide sliding groove in the embodiment of the present application.

[0033] Figure 6 is a cross-sectional schematic diagram of the cooperation between the mounting protrusion and the pressing handle in the embodiment of the present application.

[0034] Figure 7 is a cross-sectional schematic diagram of the cooperation between the clamping protrusion and the second clamping groove in the embodiment of the present application.

[0035] BRIEF DESCRIPTION OF DRAWINGS 1. frame; 2. mounting seat; 21. mounting portion; 22. sliding hole; 3. support seat; 31. support rod; 311. second key groove; 312. locking key; 313. mounting protrusion; 3131. guide protrusion; 31311. plunger hole; 31312. ball head spring plunger; 3132. mounting slot; 31321. first clamping groove; 31322. second clamping groove; 31323. limiting groove; 32. support plate; 321. mounting through hole; 322. guide sliding groove; 3221. positioning groove; 4. pressing member; 41. pressing block; 411. limiting groove; 412. mounting ring portion; 4121. first key groove; 42. pressing roller; 5. pressing handle; 51. plug-in protrusion; 511. clamping protrusion; 5111. limiting protrusion; 52. rubber anti-skid sleeve. DETAILED DESCRIPTION

[0036] The following will be described in detail in combination with the accompanying Figures 1-7 The present application will be further described in detail.

[0037] The embodiment of the present application discloses a pressing device for missile tail folding. Referring to Figure 1The utility model provides a kind of pressing device for missile tail wing folding, including frame 1, mounting seat 2 mounted on the top surface of frame 1 and the pressing mechanism for pressing outer wing symmetrically arranged in mounting seat 2 two sides.

[0038] Referring to Figure 1 And Figure 2 , pressing mechanism includes support seat 3, pressing piece 4 mounted on support seat 3 and pressing handle 5 mounted on support seat 3 and used to drive the rotation of pressing piece 4.The rotation axis of pressing piece 4 coincides with the rotation axis of pressing handle 5, and the distance from the end of pressing handle 5 away from support seat 3 to support seat 3 is greater than the distance from the end of pressing piece 4 away from support seat 3 to support seat 3, so that the operator can press the outer wing more labor-saving. Support seat 3 includes support rod 31 and support plate 32 symmetrically arranged at both ends of support rod 31 and used to support support rod 31. Wherein, support plate 32 is fixed on the top surface of frame 1 by screw.Pressing piece 4 is fixedly arranged on support rod 31, and pressing piece 4 includes two pressing blocks 41 spaced apart mounted on support rod 31 and pressing roller 42 connected two pressing blocks 41 and located at the end of two pressing blocks 41 away from support rod 31. Wherein, in order to reduce the probability of damage to missile outer wing by pressing roller 42, pressing roller 42 is made of rubber material, and the end of pressing block 41 close to mounting seat 2 has a circular corner structure. In order to reduce the probability of interference of pressing block 41 to inner wing and outer wing folding process, the bottom of pressing block 41 at the end away from support rod 31 also has a recess 411.

[0039] Referring to Figure 2 And Figure 3 , in order to fix pressing block 41 on support rod 31, so that pressing piece 4 can realize synchronous rotation with pressing handle 5, pressing block 41 and support rod 31 are connected by locking structure. Pressing block 41 has mounting ring part 412 for support rod 31 to pass through, and locking structure includes first key groove 4121 opened at mounting ring part 412 of pressing block 41, second key groove 311 opened at the outer side wall of support rod 31 and locking key 312 arranged in first key groove 4121 and second key groove 311. Wherein, locking key 312 is interference fit with first key groove 4121 and second key groove 311.

[0040] Referring to Figure 2 And Figure 4 , support plate 32 has mounting through hole 321 for support rod 31 to pass through, and both ends of support rod 31 also have mounting protrusion 313 arranged on the side of support plate 32 away from pressing piece 4. The end of mounting protrusion 313 towards support plate 32 is provided with guide boss 3131, and support plate 32 is provided with circumferentially arranged guide sliding groove 322 for guide boss 3131 to slide. Wherein, guide boss 3131 has a circular corner.

[0041] With reference to Figure 5 , in order to facilitate the operator to determine that the pressing member 4 is lifted to a height without interfering with the missile tail wing, the support plate 32 is provided with a positioning groove 3221 at the guide sliding groove 322, the guide protrusion 3131 is provided with a plunger hole 31311 at one end facing the guide sliding groove 322, and a ball head spring plunger 31312 is arranged in the plunger hole 31311, when the pressing member 4 is lifted to a height without interference to the subsequent action of the missile tail wing, the plunger ball head of the ball head spring plunger 31312 is clamped in the positioning groove 3221.

[0042] With reference to Figure 6 and Figure 7 , in order to reduce the external space occupied by the pressing device for folding the missile tail wing when not in use, the pressing handle 5 is detachably mounted on the mounting protrusion 313 of the support rod 31. One end of the pressing handle 5 has a plug-in protrusion 51, and the outer side wall of the plug-in protrusion 51 is circumferentially spaced apart from the clamping protrusion 511, the mounting protrusion 313 has a mounting slot 3132 for inserting the plug-in protrusion 51, and the mounting protrusion 313 is provided with a first clamping groove 31321 for inserting the clamping protrusion 511 and axially arranged at the mounting slot 3132, and a second clamping groove 31322 connected to the first clamping groove 31321 and circumferentially arranged away from one end of the pressing handle 5. In order to further improve the locking effect between the pressing handle 5 and the mounting protrusion 313, the bottom of the clamping protrusion 511 is further provided with a limiting protrusion 5111, and the second clamping groove 31322 has a limiting groove 31323 for arranging the limiting protrusion 5111. In this embodiment, the number of clamping protrusions 511 on the outer side wall of the plug-in protrusion 51 is two.

[0043] With reference to Figure 2 , the end of the pressing handle 5 away from the support seat 3 is also provided with a rubber anti-skid sleeve 52, so that the operator can hold the pressing handle 5 more stably, and has a certain comfort.

[0044] The implementation principle of the folding device for the missile tail wing is as follows: in the folding process of the missile tail wing, first, the operator lowers the outer wing to the height at which the pressing member 4 can press the outer wing, then the operator lifts the pressing handle 5, so that the pressing member 4 presses the outer wing until the folding angle between the outer wing and the inner wing reaches a certain value, then the outer wing and the inner wing are self-locked, the folding of the missile tail wing is completed, then the operator lowers the pressing handle 5, so that the pressing member 4 rises, when the plunger ball head of the ball head spring plunger 31312 on the mounting convex part 313 is clamped in the positioning groove 3221 on the support plate 32, the height of the pressing member 4 does not interfere with the subsequent operation of the missile tail wing, so that the unfolding time and the unfolding angle of the missile tail wing are detected, the operator presses and folds the missile tail wing with the aid of the pressing mechanism, and the labor intensity of the operator in the folding process of the missile tail wing is effectively reduced.

[0045] The above are preferred embodiments of the present application, and are not intended to limit the protection scope of the present application, therefore: any equivalent changes made on the structure, shape and principle of the present application shall be covered within the protection scope of the present application.

Claims

1. A pressing device for folding missile tail fins, characterized in that, The device includes a frame (1), a mounting base (2) mounted on the top surface of the frame (1) for arranging the inner wing, and pressing mechanisms symmetrically arranged on both sides of the mounting base (2). The pressing mechanism includes a support base (3), a pressing component (4) mounted on the support base (3), and a pressing handle (5) for driving the pressing component (4) to rotate. The distance from the end of the pressing handle (5) away from the support base (3) to the support base (3) is greater than the distance from the end of the pressing component (4) away from the support base (3) to the support base (3). The rotation axis of the pressing component (4) coincides with the rotation axis of the pressing handle (5).

2. The pressing device for folding missile tail fins according to claim 1, characterized in that, The pressing component (4) includes two pressing blocks (41) spaced apart from the support base (3) and a pressing roller (42) connected to one end of the two pressing blocks (41) away from the support base (3).

3. The pressing device for folding missile tail fins according to claim 2, characterized in that, The bottom of the pressing block (41) has a relief groove (411) at the end away from the support base (3).

4. A pressing device for folding missile tail fins according to claim 2, characterized in that, The support base (3) includes a support rod (31) and a support plate (32) symmetrically arranged at both ends of the support rod (31) for supporting the support rod (31); the pressing block (41) has a mounting ring (412) for the support rod (31) to pass through, and the pressing block (41) and the support rod (31) are connected by a locking structure, which includes a first keyway (4121) formed in the mounting ring (412), a second keyway (311) formed in the outer wall of the support rod (31), and a locking key (312) arranged in the first keyway (4121) and the second keyway (311).

5. A pressing device for folding missile tail fins according to claim 4, characterized in that, The support plate (32) has a mounting through hole (321) for the support rod (31) to pass through. The two ends of the support rod (31) have mounting protrusions (313) arranged on the side of the support base (3) facing away from the pressing member (4). The mounting protrusions (313) facing the support plate (32) are provided with guide protrusions (3131). The support plate (32) has guide grooves (322) for the guide protrusions (3131) to slide.

6. A pressing device for folding missile tail fins according to claim 5, characterized in that, The support plate (32) has a positioning groove (3221) at the guide slide (322), and the guide protrusion (3131) has a plunger hole (31311) and a ball spring plunger (31312) is provided in the plunger hole (31311). When the pressing part (4) is raised to a certain height and does not interfere with the missile tail fin, the plunger ball of the ball spring plunger (31312) is engaged with the positioning groove (3221).

7. A pressing device for folding missile tail fins according to claim 1, characterized in that, One end of the pressing handle (5) has a plug-in protrusion (51) and the outer side wall of the plug-in protrusion (51) is circumferentially spaced with snap-fit ​​protrusions (511); the support base (3) has a mounting slot (3132) for inserting the plug-in protrusion (51), and the mounting slot (3132) is provided with a first slot (31321) for inserting the snap-fit ​​protrusion (511) and arranged axially, and a second slot (31322) connected to the first slot (31321) away from the end of the pressing handle (5) and arranged circumferentially.

8. A pressing device for folding missile tail fins according to claim 7, characterized in that, The bottom of the snap-fit ​​protrusion (511) is provided with a limiting protrusion (5111), and the second snap-fit ​​groove (31322) has a limiting groove (31323) for the limiting protrusion (5111) to be snapped into.

9. A pressing device for folding missile tail fins according to claim 7, characterized in that, A rubber anti-slip sleeve (52) is provided at the end of the pressing handle (5) away from the support base (3).

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