Flexible projectile holding protection mechanism during transportation of rocket projectiles or guided missiles

Abstract

The invention discloses a flexible bomb holding protection mechanism during rocket bomb or missile transportation. The flexible bomb holding protection mechanism comprises a supporting plate; one end of the connecting rod is connected with the supporting plate, the other end is connected with the dome-shaped shell at the bottom, and a supporting ball is arranged in the middle; the shell is used for guiding the connecting rod and mounting the dome-shaped shell, and an air chamber is formed between the shell and the dome-shaped shell, so that the dome-shaped shell is inflated and deflated, and switching of two steady states of the dome-shaped shell is realized; four dome-shaped shells are arranged at the side ends, and one dome-shaped shell is arranged at the bottom; the dome-shaped shell at the side end and the bottom forms a throat structure and is sealed by the shell; when the air chamber is in an inflated state, the throat structure is in contact with the supporting ball, and axial movement of the connecting rod is supported through elasticity of the dome-shaped shell, so that the bomb holding protection mechanism is in an elastic holding state; when the air chamber is in a negative pressure state, the four dome-shaped shells at the side ends turn over and are separated from the supporting balls, and the dome-shaped shell at the bottom drives the connecting rods to contract, so that the bomb holding protection mechanism is in an open state. Transportation protection is provided, meanwhile, quick opening can be achieved, and launching is not affected.

Description

Technical Field

[0001] The invention belongs to the field of rocket and missile transportation safety protection, and specifically relates to a rocket or missile protection mechanism. Background Art

[0002] Large-caliber, long-range rockets and missiles are equipped with separate storage and transportation launch boxes (tubes) to achieve the purpose of long-term storage and rapid loading and launching. At present, there are two ways to match the bomb box (tube), one is the guide rail and the other is the adapter. Both methods are to constrain the projectile and guide it. Among them, the adapter is made of elastomer and filled between the bomb barrels. It can provide overload protection for rockets and missiles during transportation. It moves with the projectile during launch and separates from the projectile after leaving the tube. It is more common in vertical launch systems. However, for the inclined launch system, the effect of gravity causes the adapter made of elastic material to be severely squeezed, and due to the large friction coefficient, the friction resistance between the adapter and the launch tube during the launch process is too large, affecting the launch safety and initial disturbance of the missile. Therefore, the inclined launch system mostly uses metal guide rails with better rigidity and smaller friction coefficient for orientation.

[0003] In order to avoid blockage of the projectile during the launching process, the guide rail and the projectile slider are matched with clearance. This causes the projectile to collide with the guide rail repeatedly due to overload and bumps during transportation and lifting. Under long-term action, the projectile slider is very likely to be damaged by fatigue, posing a safety hazard that may cause the projectile to break away from the constraints of the guide rail. Summary of the invention

[0004] The object of the present invention is to provide a flexible projectile holding and protection mechanism during the transportation of rockets or missiles, which can not only reliably hold the projectile body and provide transportation protection, but also can be opened quickly without affecting the launch.

[0005] The technical solution to achieve the purpose of the present invention is:

[0006] A flexible rocket or missile protection mechanism during transportation, comprising:

[0007] A support plate, used for contacting with the projectile to support the projectile;

[0008] A connecting rod, one end of which is connected to the support plate and the other end is connected to the dome-shaped shell at the bottom, and can be telescopic relative to the shell; a supporting ball is provided in the middle, and its diameter is larger than the size of the throat structure;

[0009] The shell is used to guide the connecting rod and to install the dome-shaped shell, and to form an air chamber between the shell and the dome-shaped shell to inflate and deflate the dome-shaped shell, thereby realizing the switching of the two stable states of the dome-shaped shell;

[0010] A dome-shaped shell made of elastic material is provided with four on the side ends and one on the bottom; the inner walls of the dome-shaped shells at the side ends and the bottom form a throat structure with the shell body and are closed by the shell body; the dome-shaped shell has two stable structures: in the positive pressure state of the air chamber, the dome-shaped shell is in the first stable state, and the formed throat structure contacts the supporting ball to elastically support the axial movement of the connecting rod, so that the bullet holding protection mechanism is in an elastic clamping state; in the negative pressure state of the air chamber, the dome-shaped shell flips over under the action of the negative pressure to form a second stable state, and the four dome-shaped shells at the side ends are separated from the supporting balls due to the flipping, and the dome-shaped shell at the bottom drives the connecting rod to contract, so that the bullet holding protection mechanism is in the open state.

[0011] Compared with the prior art, the present invention has the following significant advantages:

[0012] (1) The contact between the missile-carrying mechanism of the present invention and the rocket or missile is flexible, which can achieve buffering and avoid rigid impact. The principle of buffering achieved by the flexible missile-carrying mechanism is that when the metal connecting rod of the missile-carrying mechanism is hit by the projectile, the rigid sphere on it will squeeze the elastic dome-shaped shell on the side, and the elastic dome-shaped shell connected to the connecting rod at the bottom will also be compressed, and the dome-shaped shell will deform to provide elastic force to achieve buffering;

[0013] (2) The realization of the opening and closing function of the bullet holding mechanism of the present invention utilizes the bistable characteristics of the dome-shaped shell, and does not require an additional opening mechanism. The side dome-shaped shell can quickly flip inward under the action of the driving load. During the flipping process, the side dome-shaped shell no longer hinders the movement of the metal ball on the connecting rod, and the connecting rod is opened as the bottom dome-shaped shell flips. All dome-shaped shells can remain stable after flipping, so that the metal connecting rod does not rebound. Therefore, the bullet holding mechanism of the present invention does not require continuous power supply;

[0014] (3) A closed air chamber is formed between the metal shell and the dome-shaped shell of the bullet-holding mechanism of the present invention. By controlling the pressure in the air chamber, the dome-shaped shell can be controlled to flip, thereby realizing the opening and closing of the bullet-holding mechanism. Adjusting the pressure in the air chamber can also play a role in adjusting the rigidity of the structure, thereby adjusting the load-bearing capacity of the bullet-holding mechanism. Using gas as a drive does not require a complex drive mechanism, and has the advantages of being simple, reliable, and easy to control. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is a schematic diagram of the closed working condition of the missile holding mechanism;

[0016] Figure 2 This is a schematic diagram of the working condition of the bomb holding mechanism being opened;

[0017] Figure 3 This is the overall axonometric drawing of the missile holding mechanism;

[0018] Figure 4 This is the internal axonometric view of the missile holding mechanism;

[0019] Figure 5 This is a cross-sectional view of the closed state of the bullet holding mechanism;

[0020] Figure 6 This is a cross-sectional view of the missile holding mechanism in the open state;

[0021] Figure 7 Axonometric view of the dome-shaped bistable shell.

[0022] As shown in the figure: a projectile holding mechanism 1; a rocket or missile body 2; a slider 3; a guide rail 4; a buffer pad 1-1; a metal support plate 1-2; a metal shell 1-3; a metal connecting rod 1-4; a dome-shaped shell 1-5; a metal support ball 1-6; a metal support frame 1-7; a connecting air hole 1-8; a guide hole 1-9; an air inlet 1-10; and air chambers 1-11 and 1-12. DETAILED DESCRIPTION

[0023] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments.

[0024] The present invention provides a projectile holding mechanism for a large-caliber rocket or missile directed by a guide rail, which provides protection for the projectile body during transportation and prevents repeated collisions between the projectile body slide block and the guide rail.

[0025] The projectile holding mechanism 1 is installed in pairs between the projectile body 2 and the launch box, with one end fixed to the side wall of the launch box and the other end in contact with the projectile body 2. Figure 1 The schematic diagram shows the working condition of the rocket or missile during storage and transportation, when the rocket holding mechanism 1 is closed and the missile body 2 is tightly held. Figure 2 The figure shows the working condition of the rocket or missile when the missile holding mechanism 1 is opened and disengaged from the missile body 2 before the rocket or missile is launched.

[0026] The overall structure of the bullet holding mechanism 1 is as follows Figure 3 The buffer pad 1-1 made of elastic material is attached to the metal support plate 1-2 at the upper end of the connecting rod of the missile holding mechanism, and its function is to prevent the missile holding mechanism 1 from rigidly contacting with the missile body 2; after removing the metal shell 1-3 of the missile holding mechanism 1, the internal structure of the missile holding mechanism 1 is as shown in FIG. Figure 4As shown; the interior of the bomb holding mechanism 1 is composed of four side and one bottom square dome-shaped shells 1-5 interconnected to form a cubic structure with a narrow throat; the square dome-shaped shell 1-5 is also made of elastic material and has two stable states; the metal frame 1-7 arranged around and at the bottom wraps the cubic structure formed by the dome-shaped shell to enhance the rigidity of the edge of the dome-shaped shell 1-5; the dome-shaped shell 1-5 at the bottom is connected to the connecting rod 1-4, and a metal supporting ball 1-6 with a diameter larger than the throat size is designed in the middle of the connecting rod and is in contact with the dome-shaped shell 1-5 on the side; the metal shell 1-3 closes the internal structure and forms two air chambers 1-11 and 1-12 on the side and bottom, and the air chambers are connected through four connecting air holes 1-8 located at the bottom. The cross-sectional view of the closed state of the bomb holding mechanism 1 is shown in FIG. Figure 5 As shown, the bottom of the metal shell 1-3 is provided with an air inlet 1-10 for gas flow, thereby changing the pressure in the air chamber. The upper cover plate of the metal shell 1-3 is provided with a connecting rod guide hole 1-9 to provide guidance for the connecting rod 1-4. When the air chamber is inflated, the internal pressure is positive, and the bomb holding mechanism is in a clamped state. When the air chamber is deflated, the internal pressure becomes negative (relative to the ambient pressure), the dome-shaped shell flips over, and the bomb holding mechanism is in an open state.

[0027] Since the mass of large-caliber bullets is large, in order to withstand the large inertial impact from the bullet body 2 during transportation overload, multiple pairs of bullet holding mechanisms can be used to carry the load together. In addition, the bullet body 2 can move a limited distance under the constraint of the guide rail 4. In order to increase the reaction force generated by the bullet holding mechanism 1 within the limited stroke, the bullet holding mechanism 1 needs to be pre-compressed during installation, and the structural rigidity is increased by increasing the air chamber pressure. The installation process of the bullet holding mechanism 1 is described in detail below.

[0028] Step 1: Position 6 positions at equal intervals between the front and rear slide blocks of the rocket and missile, and install 6 pairs of missile holding mechanisms 1 on both sides of the launch box. The missile holding mechanisms 1 have a certain angle with the horizontal direction to protect the missile body from lateral and longitudinal overloads at the same time.

[0029] Step 2: The air in the air chamber of the spring-holding mechanism is pumped back by an air pump, so that the bistable shell 1-5 contracts under the action of the internal and external pressure difference, and drives the connecting rod 1-4 to contract until the contraction stroke of the connecting rod 1-4 reaches the designed pre-compression amount.

[0030] Step 3: Install rockets and missiles in place.

[0031] Step 4: Readjust the air chamber pressure to the ambient pressure, so that the connecting rod 1-4 of the projectile holding mechanism extends out under the elastic restoring force of the dome-shaped shell 1-5 and contacts the projectile body 2 in place.

[0032] Step 5: Use an air pump to inflate the air chamber to increase the pressure in the air chamber until the pressure in the air chamber reaches the design pressure.

[0033] Through the above steps, the missile holding mechanism 1 is installed in place and in a clamped state. When the launch box is overloaded during transportation, the rocket or missile hits the missile holding mechanism under the action of inertia, the connecting rod 1-4 of the missile holding mechanism shrinks, and the metal support ball 1-6 in the middle of the connecting rod squeezes the elastic dome-shaped shell 1-5 on the side, and the dome-shaped shell connected to the connecting rod at the bottom is also compressed. The bistable elastic dome-shaped shell 1-5 generates an elastic reaction force under the action of its own deformation and the air chamber pressure, and is transmitted to the projectile 2 through the connecting rod 1-4, limiting the movement of the rocket or missile, thereby preventing the projectile slide 3 from hitting the guide rail 4, and at the same time playing a buffering role.

[0034] During launch, in order to avoid large friction resistance between the projectile holding mechanism 1 and the projectile body 2, which affects the initial disturbance and launch safety, it is necessary to disengage the projectile holding mechanism 1 from the projectile body 2. The gas in the air chamber of the projectile holding mechanism 1 is pumped back by an air pump, so that the dome-shaped shell 1-5 is concave (convex relative to the shell body) under the action of the internal and external pressure difference. As the side dome-shaped shell is concave, the movement of the metal support ball 1-6 is no longer hindered, and the connecting rod 1-4 is driven by the bottom dome-shaped shell to shrink until the dome-shaped shell flips to the second stable state, and the projectile holding mechanism is opened.

[0035] The principle of the bistable state of the dome-shaped shell is that the shell surface bends and deforms during the concave process. As the deformation increases, the accumulated bending deformation energy is gradually released inward (outward for the convex surface) until the internal energy of the dome-shaped shell reaches stability and the dome-shaped shell reaches another stable state. The process is similar to turning half of an elastic spherical shell inside out. This characteristic is determined by the shell's own geometry and does not depend on external factors. Figure 6 A cross-sectional view of the open state of the bomb holding mechanism 1 is shown after the air chamber pressure returns to the ambient pressure. The dome-shaped shell is in the second stable state and can maintain stability without continuous external drive.

[0036] When it is necessary to reload the ammunition, after the ammunition is loaded in place, the ammunition holding mechanism air chamber can be inflated to restore the ammunition holding mechanism 1 to the closed and tightened state.

Claims

1. A flexible protection mechanism for rockets or missiles during transportation, characterized in that: include: A support plate, used for contacting with the projectile to support the projectile; A connecting rod, one end of which is connected to the support plate and the other end is connected to the dome-shaped shell at the bottom, and can be telescopic relative to the shell; a supporting ball is provided in the middle, and its diameter is larger than the size of the throat structure; The shell is used to guide the connecting rod and to install the dome-shaped shell, and to form an air chamber between the shell and the dome-shaped shell to inflate and deflate the dome-shaped shell, thereby realizing the switching of the two stable states of the dome-shaped shell; The dome-shaped shell is made of elastic material, with four side ends and one bottom end. The inner walls of the dome-shaped shell at the side ends and the bottom end form a throat structure with the shell body and are closed by the shell body. The dome-shaped shell has two stable structures: in the positive pressure state of the air chamber, the dome-shaped shell is in the first stable state, and the throat structure formed contacts the support ball to elastically support the axial movement of the connecting rod, so that the bullet-holding protection mechanism is in an elastically tightened state. In the negative pressure state of the air chamber, the dome-shaped shell flips over under the action of negative pressure to form a second stable state. The four dome-shaped shells at the side ends are separated from the supporting balls due to the flipping, and the bottom dome-shaped shell drives the connecting rod to contract, so that the bullet protection mechanism is in the open state.

2. The flexible rocket or missile protection mechanism during transportation according to claim 1, characterized in that: The two air chambers are connected via a plurality of connecting air holes at the bottom.

3. The flexible rocket or missile protection mechanism during transportation according to claim 1, characterized in that: A frame is provided at the edge of the dome-shaped shell to wrap the cubic structure formed by the dome-shaped shell.

4. The flexible rocket or missile protection mechanism during transportation according to claim 1, characterized in that: A buffer pad is arranged on the support plate.

5. The flexible rocket or missile protection mechanism during transportation according to claim 1, characterized in that: They are installed in pairs between the projectile body and the launch box, with an angle to the horizontal direction, so as to protect the projectile body from lateral and longitudinal overloads at the same time.

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