Missile Adapter

Abstract

This invention provides a missile adapter, comprising an adapter body and a spring mechanism, the spring mechanism being fixed to the adapter body. The spring mechanism includes two sets of circular leaf springs, one end of which is fixed to the adapter body, and the other end extending obliquely upwards to the top of the adapter body. Both sets of circular leaf springs are in a compressed state, fixed to opposite sides of the adapter's center of mass. By replacing ordinary springs with circular leaf springs, the adapter utilizes these springs as its power source, increasing the adapter's separation force, ensuring the initial separation speed, and reducing the risk of the adapter impacting onboard equipment after separation. Furthermore, the use of dual spring force points ensures a stable separation motion of the adapter, solving the problem of continuous flipping during separation.

Description

Technical Field

[0001] This invention relates to the field of missile adapter technology, specifically to a missile adapter. Background Technology

[0002] The adapter is a ring-shaped filling device that connects the storage and launch container (tube) to the missile, providing lateral support, centering, guidance, and shock absorption, and matching the clearance between them. The adapter exits the tube along with the missile during launch and separates from the missile under aerodynamic force and its own spring, falling back to the ground.

[0003] Using an adapter-guided launcher has the following significant advantages over a slider-rail launcher:

[0004] 1) It has a good weight reduction effect in transportation and combat readiness, which improves the missile's adaptability in harsh mechanical environments;

[0005] 2) The guide rail and its seat have been eliminated, making the storage and launch box (tube) compact, simple, lightweight and easy to manufacture;

[0006] 3) The missile slider was eliminated, reducing the missile's structural weight and aerodynamic drag;

[0007] When a missile is launched from a launch vehicle, it is necessary to prevent the adapter from falling onto the vehicle-mounted equipment after separating from the launch tube. Therefore, in addition to fulfilling the functions of supporting, damping and guiding the missile body, the adapter also needs to meet a certain initial separation speed.

[0008] Existing patent document CN106370056A discloses a simultaneous off-track launching device combining an adapter and a projectile belt support. The device includes an upper constraint guide rail, a lower high guide rail, a lower low guide rail, and an adapter. The rear half of the projectile's center of mass is constrained laterally by the upper constraint guide rail and the lower high guide rail via the projectile belt. The directional button on the projectile belt cooperates with the lower high guide rail to constrain the circumferential rotation of the projectile. The front half of the projectile's center of mass is supported by an adapter that is gap-fitted with the lower low guide rail. The adapter and the projectile move together along the projectile's axial direction during the launch constraint period. When the adapter separates from the lower low guide rail, it also disengages from the projectile, and the projectile belt simultaneously loses the constraint of the upper constraint guide rail and the lower high guide rail.

[0009] Currently, traditional missile adapters use ordinary springs as power sources and mainly consist of an adapter base, spring, locating pin seat, locating pin, and adapter layer. The adapter layer is mainly used for shock absorption and accommodating the gap between the missile and the launch tube. The spring, locating pin seat, and locating pin together form the adapter separation device, mainly used for positioning, movement with the missile during launch, and separation after exiting the launch tube. Traditional adapters have the following insurmountable drawbacks and risks in use:

[0010] 1. Low separation force

[0011] Due to the size limitations of the separation device, adapters powered by ordinary springs can only use slender springs. Slender springs have low separation force and can only meet the separation requirements of the adapter's cylinder outlet, but cannot meet the horizontal distance requirements of the cylinder outlet separation.

[0012] 2. Complex structural form

[0013] An adapter powered by a common spring requires a pair of relatively complex locating pin seats and locating pin structures for positioning, support, and spring mounting. Multiple screws are also needed for installation, making the structure quite complex. The use of locating pin seats and locating pins significantly increases the machining workload of the adapter, thus increasing its cost.

[0014] 3. Unstable movement posture

[0015] Since the direction and magnitude of the aerodynamic force at the launch site are uncertain, it is difficult for the center of mass of the adapter and the centroid of the aerodynamic force to be aligned. When the adapter separates from the tube, only the spring below the positioning pin provides a single concentrated force. The line of action of the concentrated force does not coincide with the center of mass and the centroid of the aerodynamic force of the adapter, which will generate a rolling torque. This causes the adapter to continuously flip during the separation process, resulting in unstable motion and a significant reduction in the horizontal separation distance. Summary of the Invention

[0016] In view of the deficiencies in the prior art, the purpose of this invention is to provide a missile adapter.

[0017] According to the present invention, a missile adapter includes an adapter body and a spring mechanism, wherein the spring mechanism is fixed on the adapter body; the spring mechanism includes a circular leaf spring, one end of which is fixed on the adapter body, and the other end of which extends obliquely upward to the top of the adapter body; the circular leaf spring includes two sets, the two sets of circular leaf springs are respectively fixed on both sides of the adapter's center of mass, and both sets of circular leaf springs are in a compressed state.

[0018] Preferably, the adapter body includes a base, and a positioning pin is provided on the adapter body. The positioning pin and the base are integrally cured and formed. The positioning pin is located at the center of mass of the adapter, and two sets of circular leaf springs are respectively fixed on both sides of the positioning pin.

[0019] Preferably, one end of the circular spring plate extending above the adapter body is provided with a slot, which is connected to the positioning pin.

[0020] Preferably, the end of the circular spring plate is provided with a semi-circular hole, which is supported around the positioning pin.

[0021] Preferably, the spring mechanism further includes an arc-shaped base plate that supports the circular leaf springs; an arc-shaped base plate is provided under each set of circular leaf springs.

[0022] Preferably, the circular leaf spring comprises a single circular leaf spring or is composed of multiple circular leaf springs stacked together.

[0023] Preferably, the adapter body further includes a reinforcing plate, which is fixed to the base. One end of the circular leaf spring is fixed to the reinforcing plate, and the other end of the circular leaf spring extends obliquely upward to the top of the adapter body.

[0024] Preferably, the adapter body further includes an adapter layer, which is disposed on both sides of the adapter body. The adapter layer disposed on one side of the adapter body is connected to the missile, and the adapter layer disposed on the other side of the adapter body is connected to the launch tube.

[0025] Preferably, the front end of the adapter body that contacts the missile includes an acute-angled arc, and the acute-angled arc forms an acute-angled cavity with the missile.

[0026] Preferably, the adapter body is provided with an anti-spinning platform, which is disposed between the adapter and the launch tube.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. This invention replaces ordinary springs with circular leaf springs, and the adapter uses circular leaf springs as power, which increases the separation force of the adapter, ensures the initial separation speed of the adapter, and reduces the risk of the adapter hitting the vehicle equipment after separation;

[0029] 2. This invention assembles a circular leaf spring onto the outer surface of the adapter, simplifying the assembly process and making product inspection, disassembly, and maintenance convenient.

[0030] 3. By employing dual spring force points, this invention ensures a stable separation motion of the adapter, thus solving the problem of continuous flipping during adapter separation.

[0031] 4. By employing dual spring force points distributed on both sides of the center of mass and at a considerable distance from it, this invention reduces the requirement for the adapter's center of mass to coincide with the aerodynamic centroid.

[0032] 5. This invention uses a positioning pin and the base to be integrally cured and molded, eliminating the need for a positioning pin seat, which simplifies the structure, reduces the amount of machining work on the adapter, and reduces the cost of the adapter.

[0033] 6. By using multiple stacked circular leaf springs, this invention ensures low deformation stress while increasing separation speed;

[0034] 7. The present invention reduces the connection strength requirement between the positioning pin and the adapter base by setting a groove on the circular leaf spring that cooperates with the positioning pin, thereby dispersing the axial force of the projectile on the adapter when the adapter moves in and out of the cylinder with the projectile;

[0035] 8. This invention improves the load-bearing capacity of the adapter, simplifies the adapter structure, and enhances the safety of the inlet and outlet of the cylinder by using an arc-shaped base plate with a length similar to that of the adapter as the supporting base plate for the circular leaf spring. Attached Figure Description

[0036] 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:

[0037] Figure 1 This is a schematic diagram of the missile adapter.

[0038] Figure 2 This is a mid-section view of the missile adapter.

[0039] As shown in the figure:

[0040] Base 1, Slot 5

[0041] Circular leaf spring 2, adapter layer 6

[0042] Reinforcing plate 3, anti-spinning platform 7

[0043] Positioning pin 4 Detailed Implementation

[0044] 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.

[0045] This invention provides an adapter that uses a circular leaf spring as the power source, has two spring force points, provides stable motion posture, and can adapt to various separation speeds and various medium and large missiles.

[0046] like Figure 1 and 2 As shown, a missile adapter according to the present invention includes an adapter body and a spring mechanism, the spring mechanism being fixed on the adapter body; the spring mechanism includes a circular leaf spring 2, one end of the circular leaf spring 2 being fixed on the adapter body, and the other end of the circular leaf spring 2 extending obliquely upward to the top of the adapter body; the circular leaf spring 2 includes two sets, the two sets of circular leaf spring 2 being fixed on both sides of the adapter's center of mass, and both sets of circular leaf spring 2 being in a compressed state.

[0047] When the missile is stored in the launch tube, the adapter acts as a buffer and adaptor for the missile body. After the missile leaves the tube, the adapter has a certain initial vertical velocity. The elastic potential energy of the two sets of circular leaf springs 2 is released, providing the adapter with horizontal separation force and horizontal separation velocity. The adapter flies away from the combat weapon system in a parabolic trajectory, completing the launch mission.

[0048] This invention employs a circular leaf spring 2 as the power source, increasing the adapter's separation force, ensuring the initial separation speed, and reducing the risk of the adapter hitting the vehicle-mounted equipment after separation. Two sets of circular leaf springs 2 are fixed on both sides of the adapter's center of mass. A preferred embodiment is that the two sets of circular leaf springs 2 are symmetrically fixed on both sides of the adapter's center of mass, and are relatively far from the center of mass, reducing the requirement for the adapter's center of mass to coincide with the aerodynamic centroid. The fixing points of the circular leaf springs 2 are also the spring's force application points. The adapter's use of dual spring force application points ensures a stable separation motion, solving the problem of continuous flipping during adapter separation.

[0049] Furthermore, the adapter body includes a base 1, on which a positioning pin 4 is provided. The positioning pin 4 and the base 1 are integrally formed. The positioning pin 4 is located at the center of mass of the adapter, and two sets of circular leaf springs 2 are respectively fixed on both sides of the positioning pin 4. When the missile enters or exits the tube, the adapter is installed on the missile body through the positioning pin 4. The circular leaf springs 2 are pre-compressed, and the end of the circular spring plate is provided with a semi-circular hole, which supports the positioning pin 4 and disperses the load on the adapter when the missile enters or exits the tube. One end of the circular spring plate extending to the top of the adapter body is provided with a groove 5, which is connected to the positioning pin 4. The groove 5 disperses the axial force of the missile body on the adapter when the adapter enters or exits the tube with the missile body, reducing the strength requirement of the connection between the positioning pin 4 and the adapter base 1. The adapter body also includes a reinforcing plate 3, which is fixed to the base 1. One end of the circular leaf spring 2 is fixed to the reinforcing plate 3, and the other end of the circular leaf spring 2 extends obliquely upward to the top of the adapter body. The reinforcing plate 3 is fixed on the base 1, and the reinforcing plate 3 and the base 1 are integrally cured and formed. The bottom of the circular leaf spring 2 is installed on the reinforcing plate 3 by two screws. The width of the reinforcing plate 3 can be set to be the same as the width of the circular leaf spring 2. The setting of the reinforcing plate 3 makes the circular leaf spring 2 more stably installed on the base 1. The circular leaf spring 2 is assembled on the outside of the adapter. The assembly relationship is simple, and the product inspection, disassembly and maintenance are convenient.

[0050] Furthermore, the adapter body also includes an adaptation layer 6, which is disposed on both sides of the adapter body. The adaptation layer 6 on one side of the adapter body connects with the missile, while the adaptation layer 6 on the other side connects with the launch tube. When the missile is stored and transported inside the launch tube, the adaptation layer 6 provides a buffering and adaptation function for the missile body. An anti-spin platform 7 is provided on the adapter body, positioned between the adapter and the launch tube. The anti-spin platform 7 prevents the missile body from rotating inside the tube when entering or exiting it. The front end of the adapter body that contacts the missile includes an acute-angled arc, which forms an acute-angled cavity with the missile, increasing the aerodynamic separation force during separation.

[0051] A preferred embodiment is as follows: the spring mechanism further includes an arc-shaped base plate, which supports the circular leaf spring 2; each set of circular leaf springs 2 is provided with an arc-shaped base plate, and the adapter uses an arc-shaped base plate with a length similar to that of the adapter as the supporting base plate of the circular leaf spring 2, which improves the load-bearing capacity of the adapter, simplifies the adapter structure, and improves the safety of entering and exiting the cylinder.

[0052] Specifically, the circular leaf spring 2 includes one circular leaf spring 2 or multiple circular leaf springs 2 stacked together. The adapter can adapt to different initial separation speeds by changing the size and number of circular leaf springs 2. The adapter uses multiple circular leaf springs 2 stacked together, which ensures low deformation stress and increases separation speed.

[0053] 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.

[0054] 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 missile adapter, characterized in that, It includes an adapter body and a spring mechanism, wherein the spring mechanism is fixed to the adapter body; The spring mechanism includes a circular leaf spring (2), one end of which is fixed to the adapter body, and the other end of which extends obliquely upward to the top of the adapter body; The circular leaf spring (2) includes two sets, and the two sets of circular leaf springs (2) are respectively fixed on both sides of the center of mass of the adapter, and both sets of circular leaf springs (2) are in a compressed state; The adapter body includes a base (1), and a positioning pin (4) is provided on the adapter body. The positioning pin (4) and the base (1) are integrally solidified. The positioning pin (4) is located at the center of mass of the adapter, and the two sets of circular leaf springs (2) are respectively fixed on both sides of the positioning pin (4); One end of the circular leaf spring extending above the adapter body is provided with a slot (5), which is connected to the positioning pin (4).

2. The missile adapter as described in claim 1, characterized in that, The end of the circular leaf spring is provided with a semi-circular hole, which is supported around the positioning pin (4).

3. The missile adapter as described in claim 1, characterized in that, The spring mechanism also includes an arc-shaped base plate, which supports a circular leaf spring (2); Each set of circular leaf springs (2) is provided with a set of arc-shaped bottom plates.

4. The missile adapter as described in claim 1, characterized in that, The adapter body also includes a reinforcing plate (3), which is fixed on the base (1). One end of the circular leaf spring (2) is fixed on the reinforcing plate (3), and the other end of the circular leaf spring (2) extends obliquely upward to the top of the adapter body.

5. The missile adapter as described in claim 1, characterized in that, The adapter body also includes an adapter layer (6), which is disposed on both sides of the adapter body. The adapter layer (6) disposed on one side of the adapter body is connected to the missile, and the adapter layer (6) disposed on the other side of the adapter body is connected to the launch tube.

6. The missile adapter as claimed in claim 1, characterized in that, The front end of the adapter body that contacts the missile includes an acute-angled arc, which forms an acute-angled cavity with the missile.

7. The missile adapter as claimed in claim 1, characterized in that, The adapter body is provided with an anti-spin platform (7), which is located between the adapter and the launch tube.

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