Active separation device for missile-borne loitering pods

Abstract

This invention provides an active separation device for a missile-borne loitering munition, relating to the field of missile-borne loitering munition separation technology. The device includes a loitering munition, a guide rail, a separation guide mechanism, and a linkage mechanism. The loitering munition is equipped with the linkage mechanism, with both ends connected to the separation guide mechanism. The separation guide mechanism is connected to the guide rail, which is connected to the loitering munition. The linkage mechanism controls the locking and unlocking of the separation guide mechanism. This invention provides an active separation device for a missile-borne loitering munition, enabling rapid, safe, and reliable separation of the missile-borne loitering munition from its payload compartment under high altitude and high dynamic pressure conditions. It features simple engineering implementation, high separation reliability, and good controllability during the separation and transition to cruising phase. Explosive bolts are used to lock and unlock the separation linkage mechanism, controlling the start time of separation. Combined with loitering munition attitude control, this ensures that the loitering munition separates at a suitable speed and attitude.

Description

Technical Field

[0001] This invention relates to the field of missile-borne loitering munitions separation technology, and more specifically, to an active missile-borne loitering munitions separation device. Background Technology

[0002] Loitering munitions are a new concept of munitions that integrate missiles and loitering vehicles, deploying them above target areas to perform a variety of combat missions. Loitering munitions combine the characteristics of cruise missiles and drones. Compared to cruise missiles, loitering munitions have a longer loiter time, allowing them to hover over targets and search for and engage various hidden targets. Compared to drones, loitering munitions offer advantages such as supersonic missile delivery, compatibility with multiple platform launch systems, and rapid, concentrated launch capabilities.

[0003] During combat, the missile-borne loitering munition needs to safely and reliably separate from the high-speed loitering munition, and perform a series of maneuvers including wing and control surface deployment, engine start-up, and transition to cruise flight. This invention mainly relates to a device for achieving highly dynamic active separation of the loitering munition from the loitering munition payload compartment under high altitude and high dynamic pressure conditions. Summary of the Invention

[0004] In view of the deficiencies in the prior art, the purpose of this invention is to provide an active separation device for missiles and loitering munitions.

[0005] According to the present invention, an active separation device for a missile-borne loitering pod includes a loitering pod, a guide rail, a separation guide mechanism, and a linkage mechanism. The loitering pod is provided with a linkage mechanism, and the two ends of the linkage mechanism are respectively connected to the separation guide mechanism. The separation guide mechanism is connected to the guide rail, and the guide rail is connected to the loitering pod. The linkage mechanism controls the locking and unlocking of the separation guide mechanism.

[0006] Preferably, the separation guide mechanism includes a guide rod, a guide wheel bracket, and a guide wheel. The guide wheel contacts the guide rail, the guide wheel is connected to the guide wheel bracket, and multiple guide wheel brackets are connected to the guide rod.

[0007] In the initial state, the guide rods are located on both sides of the loitering device, the guide wheels are stuck in the guide rails, and the guide rails press the guide wheels tightly. The guide wheel brackets are deformed by radial pressure.

[0008] Preferably, the guide rod is provided with a protrusion, which is adapted to connect with the groove on the outer wall of the loitering device.

[0009] Preferably, the protrusion is in the shape of an isosceles trapezoid.

[0010] Preferably, the ratio of the number of guide wheel brackets to the number of guide wheels is 1:2.

[0011] Preferably, it also includes a guide rack and a rack slider. The separation guide mechanism achieves locking through the meshing of the guide rack and the rack slider. The linkage mechanism controls the locking and unlocking of the separation guide mechanism through the meshing of the guide rack and the rack slider.

[0012] Preferably, the linkage mechanism includes a slider connecting rod, a slider guide shaft, a separation bracket, a force transmission connecting rod, a connecting pin, and a parachute compartment connector. The slider guide shaft is fixedly connected to the separation bracket, the rack slider slides axially along the slider guide shaft, the slider connecting rod is fixedly connected to the rack slider, the force transmission connecting rod is connected to the slider connecting rod through a hinge, and the lower end connecting hole of the force transmission connecting rod, the connecting hole of the parachute compartment connector, and the slide groove of the separation bracket are connected by a connecting pin, which is slidably connected in the slide groove of the separation bracket.

[0013] Preferably, the linkage mechanism further includes an explosive bolt, one end of which is connected to the separation bracket, and the other end of which is connected to a connecting pin.

[0014] Preferably, when the explosive bolts are not detonated, the linkage mechanism is in a locked state and cannot be deformed;

[0015] After the explosive bolts detonate, the linkage mechanism is unlocked and deformed under the pulling force of the deceleration chute, thereby releasing the lock of the separation device.

[0016] Preferably, a preload spring or torsion spring is installed between the guide rod and the loitering device;

[0017] After the guide rod and the loitering munition are completely detached from the loitering munition payload compartment, the guide rod automatically detaches via a preloaded spring or torsion spring.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] (1) The active separation device for missile-borne loitering munitions provided by the present invention can realize the rapid, safe and reliable separation of the missile-borne loitering munition from the loitering munition payload compartment under high altitude and high dynamic pressure conditions. It has significant features such as simple engineering implementation, high separation reliability and good controllability of the loitering munition separation and cruise process.

[0020] (2) The present invention uses explosive bolts to lock and unlock the separation linkage mechanism, control the separation start time, and combined with the attitude control of the loitering munition, can ensure that the loitering munition can separate at a suitable speed and attitude. Attached Figure Description

[0021] 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:

[0022] Figure 1 This is a schematic diagram of the structure of the present invention;

[0023] Figure 2 This is a schematic cross-sectional view of the rack and pinion in the engaged and locked state.

[0024] Figure 3 This is a schematic diagram of the cross-section of the structure in its initial state after separation.

[0025] Figure 4 This is a schematic diagram of the structural cross-section during the separation process;

[0026] Figure 5 This is a schematic diagram of a partial assembly of the separation support;

[0027] Figure 6 This is a schematic cross-sectional view of a partial assembly of the bump and slider guide shaft.

[0028] Numbering on the map:

[0029] Loitering device 1, guide rail 2, separation guide mechanism 3, guide rod 301, guide wheel bracket 302, guide wheel 303, guide rail rack 304, rack slider 305, protrusion 306, linkage mechanism 4, slider connecting rod 401, slider guide shaft 402, separation bracket 403, force transmission connecting rod 404, explosion bolt 405, connecting pin 406, parachute compartment connector 407. Detailed Implementation

[0030] 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.

[0031] Example

[0032] This invention provides an active separation device for missile-borne loitering munitions, such as... Figure 1-6 As shown, the device includes a loitering device 1, a guide rail 2, a separation guide mechanism 3, and a linkage mechanism 4. The loitering device 1 is equipped with the linkage mechanism 4, with both ends of the linkage mechanism 4 connected to the separation guide mechanism 3. The separation guide mechanism 3 is connected to the guide rail 2, which is connected to the loitering device 1. The linkage mechanism 4 controls the locking and unlocking of the separation guide mechanism 3. The active separation device for the projectile has a symmetrical configuration in all directions; therefore, this embodiment only describes the connection method of the mechanism on the upper left side, and the other identical mechanisms will not be described in detail.

[0033] The separation guide mechanism 3 includes a guide rod 301, a guide wheel bracket 302, and a guide wheel 303. The guide wheel 303 contacts the guide rail 2. The guide wheel 303 and the guide wheel bracket 302 are connected by a hinge. The guide wheel bracket 302 and the guide rod 301 are fixedly connected by bolts. The number of guide wheel brackets 302 mounted on the guide rod 301 is determined by the length of the guide rod 301 and the length of the guide rail 2. In this embodiment, there are sixteen guide wheel brackets 302. Multiple protrusions 306 are installed on the guide rod 301. The shape of the protrusions 306 matches multiple grooves on the outer wall of the loitering device 1. In this embodiment, there are two protrusions 306, and the shape of the protrusions 306 is an isosceles trapezoidal block. Figure 6 As shown; four slider guide shafts 402 are fixedly connected to the separation bracket 403, as... Figure 5 As shown; the rack and pinion slider 305 can slide axially along the slider guide shaft 402. In this embodiment, the slider guide shaft 402 has a circular cross-section and two shafts on each side; the slider connecting rod 401 is fixedly connected to the rack and pinion slider 305 by bolts; the force transmission connecting rod 404 is connected to the slider connecting rod 401 by a hinge; the connecting pin 406 connects the lower end connecting hole of the force transmission connecting rod 404, the connecting hole of the parachute connecting piece 407, and the slide groove of the separation bracket 403 together. The connecting pin 406 can slide within the slide groove of the separation bracket 403, such as... Figure 5 As shown; one end of the explosion bolt 405 is fixed to the separation bracket 403 by a thread, and the other end is connected to the connecting pin 406; the part of the slider guide shaft 402 extending out of the rack slider 305 contacts the cylindrical groove of the guide rod 301, as shown. Figure 6 As shown; the guide rail rack 304 is fixed to the guide rail 2 by bolts. In the initial state, the guide rail rack 304 is engaged with the rack part on the rack slider 305.

[0034] The separation process of the active separation device for projectiles of the present invention includes three stages:

[0035] In the first stage, all components are placed inside the loitering munition payload compartment. Two guide rods 301 are placed on both sides of the fuselage of the loitering munition 1, and the protrusions 306 on the guide rods 301 are embedded in the grooves on the outer wall of the loitering munition 1. The guide wheels 303 are all locked in the guide rails 2, and the guide rails 2 press the guide wheels 303, so that the guide wheel brackets 302 are subjected to radial pressure and have a certain deformation. The explosive bolts 405 lock the relative position of the connecting pins 406 and the separation brackets 403, and the linkage mechanism 4 is locked. In the locked state, the rack and pinion slider 305 and the guide rail rack 304 are engaged through the tooth structure, so that the separation guide mechanism 3 is locked and cannot slide along the axial direction of the loitering munition payload compartment. The parachute compartment connector 407 directly pulls the entire loitering munition payload compartment to decelerate under the action of the deceleration parachute. When the overall speed drops to an acceptable value, the next separation stage begins.

[0036] In the second stage, the explosive bolt 405 is detonated, releasing the locking of the linkage structure; under the pulling force of the deceleration chute, the linkage mechanism 4 deforms, the rack and pinion slider 305 slides radially, disengaging from the guide rack 304, thus unlocking the separation guide mechanism 3. Figure 3 As shown; guide rod 301 engages and locks, separation bracket 403 pulls guide rod 301 outward from the loitering munition payload compartment via slider guide shaft 402 fixed thereon, thus causing loitering munition 1 to move outward together, as shown. Figure 4 As shown.

[0037] In the third stage, after the guide rod 301 and the loitering device 1 are completely detached from the loitering munition payload compartment, the guide rods 301 on both sides separate under the action of the compression torsion spring force between them and the loitering device 1, thus realizing the automatic detachment of the guide rods 301.

[0038] 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.

[0039] 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. An active separation device for missile-borne loitering munitions, characterized in that, The system includes a loitering device (1), a guide rail (2), a separation guide mechanism (3), and a linkage mechanism (4). The loitering device (1) is equipped with the linkage mechanism (4). The two ends of the linkage mechanism (4) are respectively connected to the separation guide mechanism (3). The separation guide mechanism (3) is connected to the guide rail (2). The guide rail (2) is connected to the loitering device (1). The linkage mechanism (4) controls the locking and unlocking of the separation guide mechanism (3). The separation guide mechanism (3) includes a guide rod (301), a guide wheel bracket (302), and a guide wheel (303). The guide wheel (303) contacts the guide rail (2), and the guide wheel (303) is connected to the guide wheel bracket (302). Multiple guide wheel brackets (302) are connected to the guide rod (301). In the initial state, the guide rod (301) is located on both sides of the loitering device (1), the guide wheel (303) is stuck in the guide rail (2), and the guide rail (2) presses the guide wheel (303) tightly. The guide wheel bracket (302) is deformed by radial pressure. It also includes a guide rack (304) and a rack slider (305). The separation guide mechanism (3) locks through the meshing of the guide rack (304) and the rack slider (305). The linkage mechanism (4) controls the locking and unlocking of the separation guide mechanism (3) through the meshing of the guide rack (304) and the rack slider (305). The linkage mechanism (4) includes a slider link (401), a slider guide shaft (402), a separation bracket (403), a force transmission link (404), a connecting pin (406), and a parachute compartment connector (407). The slider guide shaft (402) is fixedly connected to the separation bracket (403). The rack slider (305) slides axially along the slider guide shaft (402). The slider link (401) is fixedly connected to the rack slider (305). The force transmission link (404) is connected to the slider link (401) via a hinge. The lower end connection hole of the force transmission link (404), the connection hole of the parachute compartment connector (407), and the slide groove of the separation bracket (403) are connected by the connecting pin (406). The connecting pin (406) is slidably connected in the slide groove of the separation bracket (403).

2. The active separation device for missile-borne loitering munitions according to claim 1, characterized in that, The guide rod (301) is provided with a protrusion (306), which is adapted to be connected to the groove on the outer wall of the loitering device (1).

3. The active separation device for missile-borne loitering pods according to claim 2, characterized in that, The protrusion (306) is in the shape of an isosceles trapezoid.

4. The active separation device for missile-borne loitering pods according to claim 1, characterized in that, The ratio of the number of guide wheel brackets (302) to the number of guide wheels (303) is 1:

2.

5. The active separation device for missile-borne loitering pods according to claim 4, characterized in that, The linkage mechanism (4) further includes an explosive bolt (405), one end of which is connected to the separation bracket (403), and the other end of which is connected to the connecting pin (406).

6. The active separation device for missile-borne loitering munitions according to claim 5, characterized in that, When the explosive bolt (405) is not detonated, the linkage mechanism (4) is in a locked state and cannot be deformed; After the explosive bolt (405) is detonated, the linkage mechanism (4) is unlocked and deformed under the pulling force of the deceleration parachute, thereby releasing the lock of the separation device.

7. The active separation device for missile-borne loitering pods according to claim 1, characterized in that, A preload spring or torsion spring is installed between the guide rod (301) and the loitering device (1); After the guide rod (301) and the loitering munition (1) are completely detached from the loitering munition payload compartment, the guide rod (301) automatically detaches via a pre-tension spring or torsion spring.

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