Eversion non-ejectable cruise missile inlet cowl

Abstract

The application provides an everted non-throwing cruise missile air inlet port cover, comprising a cover, a torsion spring sheet, a mounting plate, a limiting mechanism and a locking mechanism, the cover is mounted on the mounting plate, and the mounting plate is mounted on the cruise missile; the cover comprises an unfolded state and a folded state; the cover comprises a mounting portion and a cover panel, when the cover is in the folded state, the cover panel completely covers an air inlet of the air inlet port, the mounting portion cooperates with the locking mechanism to lock the cover in the folded state; the torsion spring sheet is used for driving the cover to turn over in a direction away from the air inlet port; the limiting mechanism cooperates with the mounting portion to lock the cover in the unfolded state. The cover is locked in the folded state by the locking mechanism, which helps to protect the air inlet port of the air inlet port, the cover is driven to turn over by the torsion spring sheet, which helps to realize automatic unfolding, the cover is locked in the unfolded state by the limiting mechanism, which helps to reliably lock the cover, thereby helping to realize unfolding of the cover of the air inlet port and throwing out of no redundant objects in the process of launching and flying of the cruise missile.

Description

TECHNICAL FIELD

[0001] The present application relates to an air inlet port cover, in particular to an everted non-falling air inlet port cover of a loitering munition. BACKGROUND

[0002] At present, the air inlet port cover of an airborne loitering munition is usually designed with a falling cover device. The falling cover device generally uses a working dynamic form as a power source, and the separation process is prone to generate excess material. Once the excess material enters the air inlet, it will affect the working performance of the turbojet engine, and even cause the engine to fail. The movement trajectory of the falling cover after separation needs to be theoretically simulated and verified in a wind tunnel to ensure that it does not collide with the missile body. The process is complex and time-consuming. Cooperative combat is a typical combat model of loitering munitions or fighter jets, and the falling cover poses a safety hazard to cooperative loitering munitions or carrier aircraft, and even causes accidents.

[0003] The existing Chinese patent with publication number CN109595076B discloses an air inlet port cover. The air inlet port cover is installed at the air inlet of an exposed air inlet and has a boat-shaped structure composed of a head and a tail. The head includes upper and lower profiles. The upper profile is attached to the lower surface of the forebody. The tail is a cavity structure composed of a lower profile. The lower profile of the head smoothly transitions to the lower profile of the tail.

[0004] The present inventor believes that the existing falling loitering munition air inlet port cover has hidden dangers in terms of safety of the loitering munition engine itself and safety of cooperative combat loitering munitions or carrier aircraft in actual use, and needs to be improved. Therefore, it is necessary to provide an everted non-falling loitering munition air inlet port cover. SUMMARY

[0005] In view of the defects in the prior art, the purpose of the present application is to provide an everted non-falling loitering munition air inlet port cover.

[0006] According to the present application, an everted non-falling loitering munition air inlet port cover is provided, which comprises a cover, a torsional spring sheet, a mounting plate, a limiting mechanism, and a locking mechanism. The cover is installed on the mounting plate, and the mounting plate is installed on the loitering munition. The cover includes an unfolded state and a folded state. The cover includes a mounting portion and a cover panel. When the cover is in the folded state, the cover panel completely covers the air inlet of the air inlet. The mounting portion cooperates with the locking mechanism to lock the cover in the folded state. The torsional spring sheet is arranged in the mounting portion, and the torsional spring sheet is used to drive the cover to turn away from the air inlet. The limiting mechanism cooperates with the mounting portion to lock the cover in the unfolded state.

[0007] Preferably, a cover limiting hole is arranged on the mounting portion, the locking mechanism comprises a pin puller, and the cover limiting hole is inserted and matched with the pin puller.

[0008] Preferably, the pin puller is fastened and installed on the mounting plate, and the pin puller is electrically connected with the control system of the loitering munition.

[0009] Preferably, the mounting part is further provided with a mounting ring, the mounting ring comprises a first mounting ring and a second mounting ring, the first mounting ring is internally provided with a transmission shaft, and the mask can be turned along the axis of the transmission shaft.

[0010] Preferably, the torsional spring piece is arranged inside the transmission shaft, and one end of the torsional spring piece is fastened and connected with the transmission shaft through a spring piece pin.

[0011] Preferably, the second mounting ring is provided with a torsional head matched with the torsional spring piece, and the torsional head is fastened and connected with the second mounting ring through a torsional head locking screw.

[0012] Preferably, when the mask is in a folded state, the torsional spring piece is in a torsional force storage state.

[0013] Preferably, the transmission shaft extends from the first mounting ring to the second mounting ring, the outer side of the part of the transmission shaft extending out of the first mounting ring is sleeved with a support, and the transmission shaft is fastened and connected with the support through a movable shaft locking screw.

[0014] Preferably, the side of the support away from the mask is provided with a mounting hole, and the support is fastened and connected with the mounting plate through the mounting hole.

[0015] Preferably, the limiting mechanism comprises a compression spring and a locking pin, the locking pin is provided with a limiting block, the inside of the support and the second mounting ring is provided with a rectangular groove matched with the limiting block, when the mask is in a folded state, the limiting block of the locking pin is located in the rectangular groove of the support, and when the mask is in an unfolded state, the limiting block of the locking pin is moved into the rectangular groove of the second mounting ring through the compression spring.

[0016] Compared with the prior art, the present application has the following beneficial effects:

[0017] 1、The locking mechanism of the present application can lock the mask in a folded state, which helps to protect the air inlet of the air inlet channel, the torsional spring piece can drive the mask to turn, which helps to realize automatic unfolding, the limiting mechanism can lock the mask in an unfolded state, which helps to reliably lock the mask, and thus helps to realize the unfolding of the mask of the air inlet channel during the launching and flying process of the loitering munition without throwing out any redundant objects.

[0018] 2、The application is helpful to realize the automatic unfolding of the mask by adopting the unlocking of the puller controlled by the power on the elastic, and the cooperation of the torsional spring sheet in the torsional force storage state, and the torsional spring sheet is designed by combining multiple torsional spring sheets, which is helpful to the inlet mask unfolding of the cruise missile flying at the same Mach number, so as to expand the application range.

[0019] 3、The application is helpful to guarantee the reliability of the mask locking by the limiting block, the support and the rectangular slot of the mask matched with the limiting block, and the locking pin embedded into the limiting slot of the mask, so as to guarantee that the inlet mask does not interfere with the work of the inlet after being unfolded. BRIEF DESCRIPTION OF DRAWINGS

[0020] Other features, objects and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0021] Figure 1 It is a sectional view of the folded state of the everted non-parachute cruise missile inlet mask.

[0022] Figure 2 It is a rear view of the folded state of the everted non-parachute cruise missile inlet mask.

[0023] Figure 3 It is a structural schematic view of the folded state of the everted non-parachute cruise missile inlet mask after installation.

[0024] Figure 4 It is a structural schematic view of the unfolded state of the everted non-parachute cruise missile inlet mask.

[0025] Figure 5 It is a structural schematic view of the mask.

[0026] Figure 6 It is a structural schematic view of the puller.

[0027] Figure 7 It is a structural schematic view of the force transmission shaft.

[0028] Figure 8 It is a structural schematic view of the torsional head.

[0029] Figure 9 It is a structural schematic view of the support.

[0030] Figure 10 It is a structural schematic view of the locking pin.

[0031] In the drawings:

[0032] Pin puller 1 torsion spring 2 force transmission shaft 3

[0033] spring leaf pin 4 mounting plate 5 support 6

[0034] mask 7 compression spring 8 lock pin 9

[0035] twist head 10 force transmission shaft locking screw 11 twist head locking screw 12

[0036] intake passage 13 fuel tank 1414 DETAILED DESCRIPTION

[0037] The application will be described in detail below with specific embodiments. The following examples will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be noted that for those skilled in the art, without departing from the concept of the application, a number of changes and improvements can be made. These are within the scope of the present application.

[0038] As Figures 1-4 shown, according to the everted non-throwing patrol missile intake port mask provided by the application, comprising: mask 7, torsion spring 2, mounting plate 5, limiting mechanism and locking mechanism, mask 7 is installed on mounting plate 5, mounting plate 5 is installed on the patrol missile; mask 7 includes an expanded state and a folded state; mask 7 includes a mounting portion and a mask panel, when mask 7 is in a folded state, the mask panel completely covers the air inlet of intake passage 13, the mounting portion cooperates with the locking mechanism to lock mask 7 in a folded state; torsion spring 2 is arranged in the mounting portion, and torsion spring 2 is used to drive mask 7 to turn over in the direction away from intake passage 13; limiting mechanism cooperates with mounting portion to lock mask 7 in an expanded state.

[0039] When mask 7 of the present application is in a folded state, the mask panel of mask 7 is attached to the air inlet position of intake passage 13, realizing that the missile air inlet of intake passage 13 bears aerodynamic load during missile flight, avoiding damage to intake passage 13 due to the inner surface or lip of intake passage 13, while taking into account the protection of rain and dust prevention. Further, during combat, the present application is fixed by 5 screws on both sides of mounting plate 5 and fuel tank 14, so that the present application is installed at the bottom of fuel tank 14, mask 7 is expanded but not thrown, providing a protection for the patrol missile itself and the safety of the carrier.

[0040] As Figure 5 and 6As shown, the mounting portion of the mask 7 is provided with a mask limiting hole, and the locking mechanism includes a puller 1, and the mask limiting hole is in plug-in cooperation with the puller 1. The puller 1 is fastened and installed on the mounting plate 5 through a screw, and the puller 1 is electrically connected with the control system of the loitering munition. When the mask 7 is in a folded state, the puller 1 locks the mask 7. After the loitering munition is launched from the carrier, the missile comprehensive electronic equipment gives an air inlet mask unfolding instruction according to a predetermined program, and then supplies power to the puller 1 through the on-board power supply and activates the puller 1. The pin shaft of the puller 1 is retracted to release the constraint on the mask 7, so that the mask 7 can be unfolded.

[0041] As shown in Figure 7 As shown, the mounting portion of the mask 7 is further provided with a mounting ring, and the mounting ring includes a first mounting ring and a second mounting ring. The first mounting ring is internally provided with a force transmission shaft 3. When the mask 7 is unfolded, it is flipped away from the air inlet 13 along the axis of the force transmission shaft 3.

[0042] As shown in Figure 8 As shown, a torsion spring piece 2 is arranged inside the force transmission shaft 3, and one end of the torsion spring piece 2 is fastened and connected with the force transmission shaft 3 through a spring piece pin 4. A torsion head 10 matched with the torsion spring piece 2 is mounted on the second mounting ring, and the torsion head 10 is fastened and connected with the second mounting ring through a torsion head locking screw 12.

[0043] The torsion spring piece 2 is designed in combination of multiple torsion spring pieces, and can be adjusted according to actual use. When the mask 7 is in a folded state, the torsion spring piece 2 is rotated by a certain angle and is in a torsion energy storage state. When the mask 7 is unfolded, the torsion spring piece 2 has a large unfolding torque.

[0044] As shown in Figure 9 As shown, the force transmission shaft 3 extends from the first mounting ring to the second mounting ring, and the outside of the part of the force transmission shaft 3 extending out of the first mounting ring is sleeved with a support 6, and the force transmission shaft 3 is fastened and connected with the support 6 through a movable shaft locking screw 11. The side of the support 6 away from the mask 7 is provided with a mounting hole, and the support 6 is fastened and connected with the mounting plate 5 through the mounting hole.

[0045] Since the torsion spring piece 2 is in a torsion energy storage state, the pin shaft of the puller 1 is retracted to release the constraint on the mask 7, and at the same time, the constraint of the mask 7 on the torsion spring piece 2 is released. The torsion spring piece 2 starts to rotate, so that the torsion head 10 and the mask 7 are rotated under the driving of the torsion spring piece 2. The mask 7 starts to flip away from the air inlet 13 along the axis of the force transmission shaft 3 and is unfolded.

[0046] As shown in Figure 10 As shown, the limiting mechanism includes a compression spring 8 and a locking pin 9, and the locking pin 9 is provided with a limiting block. The inside of the support 6 and the second mounting ring are both provided with a rectangular groove matched with the limiting block.

[0047] When the mask 7 is in the folded state, the locking block of the locking pin 9 is located in the rectangular groove of the support 6. When installing here, a tool is inserted into the hole of the locking pin 9, and the locking pin 9 is pushed to move axially along the rectangular groove of the support 6, so that the bottom locking block of the locking pin 9 is completely retracted in the inner hole of the support 6.

[0048] When the mask 7 is in the unfolded state, the locking block of the locking pin 9 is moved into the rectangular groove of the second mounting ring by the compression spring 8. The mask 7 starts to turn and unfold until the rectangular groove of the second mounting ring is turned to communicate with the rectangular groove of the support 6, at which time the bottom locking block of the locking pin 9 is partially inserted into the mask 7 under the action of the compression spring 8, realizing the unfolding locking.

[0049] The air inlet mask is usually in the folded state at this time, the mask 7 is rotated by 90° relative to the support 6, the locking pin 9 is retracted in the rectangular groove of the support 6, and the torsional spring piece 2 is in the torsional force storage state, and finally the pin shaft of the pin extractor 1 cooperates with the mask limiting hole to realize reliable locking of the mask 7.

[0050] When the cruise missile is launched from the carrier, the missile integrated electronic equipment gives the air inlet mask unfolding instruction according to the predetermined program, and then supplies power to the pin extractor 1 of the air inlet mask through the missile on-board power supply and activates it, the pin shaft of the pin extractor 1 is retracted to release the constraint on the mask 7, and the mask 7 together with the torsional head 10 is rotated and folded outward along the force transmission shaft 3 in the support 6 under the action of the torsional spring piece 2. When the mask 7 and the internal limiting groove of the support 6 are aligned, the locking pin 9 moves along the internal limiting groove of the support 6 under the action of the compression spring 8, one end is embedded into the limiting groove of the mask 7, thereby realizing the unfolding and falling locking of the air inlet mask.

[0051] The application realizes that the air inlet of the missile air inlet 13 can bear the aerodynamic load during the flight of the missile, avoids damaging the air inlet 13 due to the internal surface or lip of the air inlet 13, and also considers the protection against rain and dust. The application adopts the design of multiple torsional spring pieces, has a large unfolding torque, and can adapt to the air inlet mask unfolding of the cruise missile at different Mach numbers. The application uses the electrical pin extractor 1 to unlock the mask 7, the mask 7 is automatically unfolded and reliably locked under the action of the torsional spring piece 2, realizes the unfolding of the air inlet mask of the cruise missile during the launch and flight process, and no extra objects are thrown out, thereby providing protection for the cruise missile itself and the carrier.

[0052] Working principle

[0053] The air inlet port cover is normally in a folded state, at this time the cover 7 is rotated 90° relative to the support 6, the locking pin 9 is retracted in the rectangular slot of the support 6, the torsion spring piece 2 is in a torsion storage state, and finally the reliable locking of the cover 7 is realized through the cooperation of the pin shaft of the pin extractor 1 and the cover limiting hole. After the cruise missile is launched from the carrier aircraft, the missile comprehensive electronic equipment gives the air inlet port cover a deployment command according to the predetermined program, then the pin extractor 1 is powered and activated through the power supply on the missile, the pin shaft of the pin extractor 1 is retracted to release the constraint on the cover 7, and the cover 7 together with the torsion head 10 is rotated and folded outside the air inlet 13 under the action of the torsion spring piece 2 around the force transmission shaft 3 in the support 6. When the cover 7 and the internal limiting slot of the support 6 are aligned, the locking pin 9 moves along the internal limiting slot of the support 6 under the action of the compression spring 8, one end of the locking pin 9 is embedded in the limiting slot of the cover 7, so that the air inlet port cover is deployed and not thrown and locked.

[0054] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0055] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict.

Claims

1. An everted non-ejecting cruise missile inlet cowl, characterized by, The utility model relates to a kind of air filter for unmanned aerial vehicle, including: Mask (7), torsion spring piece (2), mounting plate (5), limiting mechanism and locking mechanism, the mask (7) is installed on the mounting plate (5), and the mounting plate (5) is installed on the patrol missile; The mask (7) includes an unfolded state and a folded state; The mask (7) includes a mounting portion and a mask panel, when the mask (7) is in the folded state, the mask panel completely covers the air inlet of the air inlet (13), and the mounting portion cooperates with the locking mechanism to lock the mask (7) in the folded state; The torsion spring piece (2) is arranged in the mounting portion, and the torsion spring piece (2) is used to drive the mask (7) to overturn in the direction away from the air inlet (13); The limiting mechanism cooperates with the mounting portion to lock the mask (7) in the unfolded state; The mounting portion is provided with a mask limiting hole, and the locking mechanism includes a pin puller (1), and the mask limiting hole is inserted and matched with the pin puller (1); The mounting portion is also provided with a mounting ring, and the mounting ring includes a first mounting ring and a second mounting ring, the first mounting ring is provided with a transmission shaft (3) inside, and the mask (7) can overturn along the axis of the transmission shaft (3); The transmission shaft (3) extends from the first mounting ring to the second mounting ring, and the outside of the part of the transmission shaft (3) extending out of the first mounting ring is sleeved with a support (6), and the transmission shaft (3) is fastened and connected with the support (6) through a movable shaft locking screw (11); The side of the support (6) away from the mask (7) is provided with a mounting hole, and the support (6) is fastened and connected with the mounting plate (5) through the mounting hole; The limiting mechanism includes a compression spring (8) and a lock pin (9), the lock pin (9) is provided with a limiting block, and the inside of the support (6) and the second mounting ring is provided with a rectangular groove matched with the limiting block; When the mask (7) is in the folded state, the limiting block of the lock pin (9) is located in the rectangular groove of the support (6); When the mask (7) is in the unfolded state, the limiting block of the lock pin (9) is moved into the rectangular groove of the second mounting ring by the compression spring (8). The air inlet port cover is in a folded state, at this time, the cover (7) is rotated 90° relative to the support (6), the locking pin (9) is retracted in the rectangular slot of the support (6), the torsion spring sheet (2) is in a torsion energy storage state, and finally the reliable locking of the cover (7) is realized through the cooperation of the pin shaft of the pin puller (1) and the cover limiting hole; after the cruise missile is launched from the carrier, the missile comprehensive electronic equipment gives the air inlet port cover deployment instruction according to the established program, then the pin puller (1) of the air inlet port cover is powered and activated through the missile power supply, the pin shaft of the pin puller (1) is retracted to release the constraint on the cover (7), the cover (7) and the torsion head (10) are rotated and folded outside the air inlet (13) under the action of the torsion spring sheet (2) around the transmission shaft (3) in the support (6); when the cover (7) and the internal limiting slot of the support (6) are aligned, the locking pin (9) moves along the internal limiting slot of the support (6) under the action of the compression spring (8), one end is embedded into the limiting slot of the cover (7), so that the air inlet port cover is deployed and not thrown and locked.

2. The everted non-spinning loitering munition inlet cowl of claim 1, wherein, The pin puller (1) is tightly installed on the mounting plate (5), and the pin puller (1) is electrically connected with the control system of the cruise missile.

3. The everted non-spinning loitering munition inlet cowl of claim 1, wherein, The torsion spring sheet (2) is arranged in the transmission shaft (3), and one end of the torsion spring sheet (2) is tightly connected with the transmission shaft (3) through the spring sheet pin (4).

4. The everted non-spinning loitering munition inlet cowl of claim 1, wherein, The second mounting ring is provided with a torsion head (10) matched with the torsion spring sheet (2), and the torsion head (10) is tightly connected with the second mounting ring through a torsion head locking screw (12).

5. The everted non-spinning loitering munition inlet cowl of claim 1, wherein, When the cover (7) is in a folded state, the torsion spring sheet (2) is in a torsion energy storage state.

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