Auxiliary supporting device for tail end of missile warhead

Abstract

The invention discloses an auxiliary supporting device for the tail end of a missile warhead. The auxiliary supporting device comprises a cabin, the warhead, a supporting frame, a supporting ring, a nut and a bolt. The supporting ring is a circular ring with an L-shaped section, the supporting frames are evenly distributed and installed in the annular direction, the supporting frames are trapezoid pieces with ribs, one ends of the supporting frames are fixedly connected with the supporting ring, and the other ends of the supporting frames are fixedly connected with the end face of a cabin. The tail end of the warhead is sleeved with the supporting ring, the supporting frame and the supporting ring form a claw-like connecting structure, and the connecting structure is good in openness, light in weight and convenient to install. A plurality of radial threaded holes are formed in the axial side edge of the supporting ring, bolts and nuts are installed in the radial threaded holes, so that the bolts can vertically abut against the surface of the tail end of the warhead, pre-tightening force is formed, radial constraint rigidity is provided, and meanwhile the nuts are screwed to prevent looseness; for the axial constraint rigidity of the warhead, the axial constraint rigidity can be adjusted by adjusting the pretightening force of the radial bolt. The device can adapt to warheads in various shapes, and radial constraint is achieved by installing screws in different threaded holes.

Description

Technical Field

[0001] The invention belongs to the field of navigation technology, and in particular relates to a missile warhead tail end auxiliary support device. Background Art

[0002] For the installation and connection of heavy warheads in the cabin, it is necessary to consider the strength and reliability of the connection structure, as well as the deformation matching problem caused by the elongation and deformation of the warhead cabin under the action of thermal load during the flight of the missile. In conventional ballistic design, there will be a special warhead cabin to carry the warhead. The warhead is a mass-concentrated and large component in the missile structure. It needs to be connected to the warhead cabin through specially designed connectors to fix the missile to prevent sliding, shaking, swinging, etc. that affect the missile's flight attitude and shooting angle. There are also many ways to connect the warhead to the cabin, mainly three-point connection method, two-point connection method, and also directly fix the warhead to the instrument cabin of the next level, and only use the warhead cabin as a rectifier. Among them, the three-point connection method requires a large structural weight, and there will also be over-constraint; the method of fixed connection in the instrument compartment requires high structural strength of the instrument compartment, which is not conducive to the use of the warhead compartment; in the two-point connection method, the center of gravity of the warhead is the main load-bearing connection point, but when the missile turns and maneuvers, the weight of the front and rear ends of the warhead will form a large bending moment on the connection point at the center of gravity, which poses a greater risk. Therefore, it is necessary to use the front or rear end as an auxiliary connection point to eliminate the bending moment of the connection point at the center of gravity. In this regard, the auxiliary connection point mainly provides radial constraint stiffness to eliminate the bending moment, and the axial load is still borne by the connection point at the center of gravity. For the front and rear auxiliary connection methods, generally a flange-like structure is used to connect with the warhead tail end by threaded adaptation, threaded holes are drilled for connection, and the warhead tail end is clamped or clamped. These methods can generally achieve the purpose of connection and fixation, but will bring some other problems as follows, and are not the optimal connection methods.

[0003] 1) For many uniform or standard warheads, the tail end is not equipped with threads or threaded holes for connection, making it difficult to use;

[0004] 2) A flange-like structure is used, with one end connected to the warhead thread or with a drilled threaded hole, and the other end connected to the cabin bolt. It has no adjustment capability. When there is a slight deviation in the installation of the warhead, the flange connection structure will be unable to be installed.

[0005] 3) Regardless of the method or connection structure, factors such as light weight and low cost should be considered as much as possible;

[0006] 4) The tail auxiliary support connection should have as large an opening as possible to facilitate observation of the cabin or wiring;

[0007] 5. Conventional tail connection methods are generally strong connection methods such as threads and bolts. For the tail auxiliary connection point, due to its distance from the center of gravity, only a strong radial constraint stiffness needs to be provided, and the axial constraint stiffness is mainly provided by the connection at the center of gravity. The auxiliary connection at the rear end should minimize the axial constraint stiffness to prevent the auxiliary connection structure from being damaged prematurely due to excessive axial load. At the same time, reducing stiffness is conducive to reducing the weight of the structure. Summary of the invention

[0008] In order to overcome the shortcomings of the prior art, the present invention provides an auxiliary support device for the tail end of a missile warhead, including a cabin, a warhead, a support frame, a support ring, nuts, and bolts; the support ring is a circular ring with an L-shaped cross-section, and the support frame is evenly installed along the annular direction. The support frame is a trapezoidal member with ribs, one end of which is fixedly connected to the support ring, and the other end is fixedly connected to the end face of the cabin. The support ring is inserted into the tail end of the warhead, and the support frame and the support ring form a connection structure similar to a "claw", which has good openness, light weight, and easy installation. The support ring is provided with a plurality of radial threaded holes along the axial side, and bolts and nuts are installed in the radial threaded holes so that the bolts can vertically support the surface of the tail end of the warhead to form a preload, provide radial constraint stiffness, and tighten the nuts to prevent loosening; for the axial constraint stiffness of the warhead, the axial constraint stiffness can be adjusted by adjusting the radial bolt preload. The present invention can be adapted to warheads of various shapes, and radial constraint can be achieved by installing screws in different threaded holes.

[0009] The technical solution adopted by the present invention to solve the technical problem is as follows:

[0010] A missile warhead tail end auxiliary support device, comprising a cabin, a warhead, a support frame, a support ring, nuts and bolts;

[0011] The warhead is installed inside the cabin, and the tail end of the warhead extends out of the rear end surface of the cabin;

[0012] The support ring is a circular ring with an L-shaped cross-section, the inner diameter of which is larger than the outer diameter of the tail end of the warhead, and is inserted into the tail end of the warhead;

[0013] The support frame is a trapezoidal member with ribs, one end of the long side is an arc surface, fixedly connected to the support ring, and one end of the short side is fixedly connected to the rear end surface of the cabin;

[0014] The support frames are evenly distributed along the circumference of the support ring, and the number is greater than 3;

[0015] The support ring is provided with a plurality of radial threaded holes along the axial side, and bolts and nuts are installed in the radial threaded holes so that the bolts can vertically support the surface of the tail end of the warhead to form a pre-tightening force, provide radial constraint stiffness, and tighten the nuts to prevent loosening.

[0016] Preferably, the axial constraint stiffness of the warhead can be adjusted by adjusting the radial bolt preload to avoid damage to the auxiliary support device due to excessive axial constraint stiffness.

[0017] Preferably, each quadrant of the support ring has at least one threaded hole, and the bolts installed in the threaded holes can vertically support the non-recessed surface of the tail end of the warhead to prevent the bolts from tilting.

[0018] Preferably, the number of the supporting frames is 4.

[0019] The beneficial effects of the present invention are as follows:

[0020] 1) The present invention can be adapted to warheads of various shapes, whether they have a smooth surface or a regular concave-convex shape, and radial constraints can be achieved by installing screws in different threaded holes;

[0021] 2) A certain gap is left between the inner side of the support ring of the present invention and the surface of the tail end of the warhead, so as to avoid the situation that the installation cannot be caused by the installation deviation of the warhead axis, and the invention has a certain degree of adaptability and adjustable space, and also brings convenience to the installation;

[0022] 3) The support ring and support frame of the present invention have simple structures and are easy to install, further reducing the weight and cost of the structure;

[0023] 4) The present invention provides a large opening at the rear end of the warhead cabin, which is convenient for observing the situation inside the cabin and for wiring;

[0024] 5) While providing strong radial constraint stiffness, the present invention can adjust the axial constraint stiffness according to the bolt preload to obtain a lower axial constraint stiffness, thereby avoiding damage to the auxiliary support structure due to excessive load. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a structural schematic diagram of the auxiliary supporting device of the present invention.

[0026] Figure 2 It is a top view of the auxiliary support device of the present invention.

[0027] Among them, 1-cabin, 2-warhead, 3-support frame, 4-support ring, 5-nut, 6-bolt. DETAILED DESCRIPTION

[0028] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0029] Based on the above application background, the present invention mainly proposes a tail end auxiliary support device for a missile warhead in the tail end auxiliary support connection scheme in the two-point connection mode between the heavy warhead and the cabin, which mainly solves 1) being adaptable to the connection of warheads of various shapes; 2) having a certain structural installation adjustment capability to facilitate the installation of the warhead; 3) further reducing the structural weight and cost; 4) making the rear end of the warhead cabin have a large opening to facilitate observation of the situation inside the cabin and wiring; 5) reducing the axial constraint stiffness while maintaining the radial constraint stiffness.

[0030] The technical solution of the present invention is based on the two-point connection mode of the warhead. The front point is at the center of gravity of the warhead and is the main load-bearing connection point, and the rear point is at the tail end of the warhead and is the auxiliary support point. In order to solve the requirements of large radial connection stiffness, small axial connection stiffness, small structural weight and convenient installation required by the auxiliary support connection structure of the tail end of the heavy warhead, the present invention proposes an auxiliary support device for the tail end of the missile warhead, including a cabin, a warhead, a support frame, a support ring, bolts and other components. The support ring is a circular ring with an L-shaped cross-section, and the support frame is evenly installed along the annular direction. The support frame is a trapezoidal member with ribs, one end is fixedly connected to the support ring, and the other end is fixedly connected to the end face of the cabin, and the number is greater than 3 (4 in the embodiment of the present invention). During installation, the support ring is inserted into the tail end of the warhead. The inner diameter of the support ring is larger than the outer diameter of the warhead to avoid the situation where the warhead cannot be inserted due to the axial installation deviation. The support frame and the support ring form a connection structure similar to a "claw", which has good openness, light weight and convenient installation; at this time, the support ring is not in contact with the tail end of the warhead and cannot play a supporting role. Several threaded holes are arranged radially on the side of the support ring. The radial screws are installed in the threaded holes to tighten the tail end of the warhead through the pre-tightening force to obtain radial support stiffness. Since the axial constraint of the support ring on the tail end of the warhead is achieved through the friction force converted from the pre-tightening force of the radial screws, the axial support stiffness can be adjusted according to the size of the screw pre-tightening force. The threaded holes can be evenly distributed in a certain number to adapt to the shape of the tail end of the warhead or the state after installation, that is, as long as one threaded hole is available in one area, it can be used.

[0031] A missile warhead tail end auxiliary support device, comprising a cabin 1, a warhead 2, a support frame 3, a support ring 4, a nut 5 and a bolt 6;

[0032] The warhead 2 is installed inside the cabin 1, and the tail end of the warhead 2 extends out of the rear end surface of the cabin 1;

[0033] The support ring 4 is a circular ring with an L-shaped cross section, the inner diameter of which is larger than the outer diameter of the tail end of the warhead 2, and is inserted into the tail end of the warhead 2;

[0034] The support frame 3 is a trapezoidal member with ribs, one end of the long side is an arc surface, fixedly connected to the support ring 4, and one end of the short side is fixedly connected to the rear end surface of the cabin body 1;

[0035] The support frames 3 are evenly distributed along the circumference of the support ring 4, and the number is greater than 3;

[0036] The support ring 4 is provided with a plurality of radial threaded holes along the axial side, and bolts 6 and nuts 5 are installed in the radial threaded holes so that the bolts 6 can vertically support the tail end surface of the warhead 2 to form a pre-tightening force, provide radial constraint stiffness, and tighten the nuts 5 to prevent loosening.

[0037] The axial constraint stiffness of the warhead 2 can be adjusted by adjusting the radial pre-tightening force of the bolt 6 to avoid damage to the auxiliary support device caused by excessive axial constraint stiffness.

[0038] Each quadrant of the support ring 4 has at least one threaded hole, and the bolts 6 installed in the threaded holes can vertically support the non-concave surface of the tail end of the warhead 2 to prevent the bolts from tilting.

[0039] The number of the supporting frames 3 is four.

[0040] Example:

[0041] Reference Figure 1 and Figure 2 The present invention provides a missile warhead tail end auxiliary support device, including a cabin 1, a warhead 2, a support frame 3, a support ring 4, a nut 5, a bolt 6 and other components.

[0042] The warhead 2 is installed inside the cabin 1, and the tail end of the warhead 2 extends out of the rear end surface of the cabin 1 by a certain dimension, leaving space for the installation of the auxiliary support device;

[0043] The support ring 4 is a circular ring with an L-shaped cross section, the inner diameter of which is larger than the outer diameter of the tail end of the warhead 2, and the support frame 3 is installed along the circumferential direction;

[0044] As a preferred solution, the support frames 3 are evenly distributed along the circumference of the support ring 4, with a number greater than 3, preferably 4, to form a regular or symmetrical quadrant;

[0045] The support frame 3 is a trapezoidal member with ribs, one end of the long side is an arc surface, which is assembled and connected with the support ring 4, and one end of the short side is connected to the rear end surface of the cabin body 1; the support frame 3 is fixedly connected to the rear end surface of the cabin body 1 and cannot be adjusted. The support frame 3 mainly provides radial constraint stiffness;

[0046] The support ring 4 and the support frame 3 are installed on the rear end surface of the cabin 1, and the support ring 4 is inserted into the tail end of the warhead 2. A certain gap is left between the inner side of the support ring 4 and the outer surface of the tail end of the warhead 2 to avoid the situation where the warhead 2 cannot be inserted due to the installation deviation of the axis of the warhead 2. It has a certain degree of adaptability and adjustable space, and also brings convenience to installation;

[0047] The support ring 4 is provided with a plurality of radial threaded holes along the axial side, and the positions and number of the threaded holes are designed according to the concave-convex shape of the tail end of the warhead 2, so that after the warhead 2 and the support ring 4 are installed, at least one threaded hole can be found in each quadrant, and the bolts installed in the threaded holes can just vertically support the non-concave surface of the tail end of the warhead to prevent the bolts from tilting;

[0048] After the support ring 4 and the support frame 3 are fixedly installed, bolts 6 and nuts 5 are installed in the radial threaded holes according to the installed state, so that the bolts 6 can vertically support the surface of the tail end of the warhead to form a pre-tightening force and provide radial constraint stiffness, and at the same time, the nuts 5 are tightened to prevent loosening;

[0049] The axial constraint stiffness of the warhead 2 can be adjusted by adjusting the pre-tightening force of the radial bolt 6 to avoid premature damage to the auxiliary support device caused by excessive axial constraint stiffness.

Claims

1. A missile warhead tail end auxiliary support device, characterized in that: Includes cabin, warhead, support frame, support ring, nuts and bolts; The warhead is installed inside the cabin, and the tail end of the warhead extends out of the rear end surface of the cabin; The support ring is a circular ring with an L-shaped cross-section, the inner diameter of which is larger than the outer diameter of the tail end of the warhead, and is inserted into the tail end of the warhead; The support frame is a trapezoidal member with ribs, one end of the long side is an arc surface, fixedly connected to the support ring, and one end of the short side is fixedly connected to the rear end surface of the cabin; The support frames are evenly distributed along the circumference of the support ring, and the number is greater than 3; The support ring is provided with a plurality of radial threaded holes along the axial side, and bolts and nuts are installed in the radial threaded holes so that the bolts can vertically support the surface of the tail end of the warhead to form a pre-tightening force, provide radial constraint stiffness, and tighten the nuts to prevent loosening.

2. A missile warhead tail end auxiliary support device according to claim 1, characterized in that: The axial constraint stiffness of the warhead can be adjusted by adjusting the radial bolt preload force to avoid damage to the auxiliary support device caused by excessive axial constraint stiffness.

3. The missile warhead tail end auxiliary support device according to claim 1, characterized in that: Each quadrant of the support ring has at least one threaded hole, and the bolts installed in the threaded holes can vertically support the non-concave surface of the tail end of the warhead to prevent the bolts from tilting.

4. The missile warhead tail end auxiliary support device according to claim 1, characterized in that: The number of the support frames is 4.

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