CN212845108U

CN212845108U - Guided missile nondestructive testing system

Info

Publication number: CN212845108U
Application number: CN202020676724.9U
Authority: CN
Inventors: 宋祥君; 刘耀周; 刘海涛; 郭晓冉; 韩宁; 韩守红; 马飒飒; 方东兴; 耿斌; 刘占岭; 孙晶; 高润东; 康科
Original assignee: 32181 Troops of PLA
Current assignee: 32181 Troops of PLA
Priority date: 2020-04-28
Filing date: 2020-04-28
Publication date: 2021-03-30
Anticipated expiration: 2030-04-28

Abstract

The utility model relates to a guided missile nondestructive test system, it includes the main support, sets up the slip table that bears on the main support, sets up X ray source, imager slip table 4 and the control system of setting at the main support opposite side in main support one side. The utility model discloses can be under the condition that the guided missile did not disintegrate, to the inside real-time formation of image that carries on of guided missile, see internal defect and trouble directly perceivedly, carry out quality assessment to the guided missile.

Description

Guided missile nondestructive testing system

Technical Field

The utility model relates to a guided missile nondestructive test technical field, concretely relates to guided missile nondestructive test system.

Background

After the missiles of the train troops are transported and subjected to service treatment and stored for a long time, the problems of component parts translocation, breakage, debonding, corrosion, long whiskers and the like can occur inside the missiles, the missiles can fail to be launched in the future, and the missiles are delayed, even explode on a launching rack or in a launching tube, so that major safety accidents are caused, and therefore the missiles must be comprehensively detected in performance, and various defects and faults are accurately identified, so that quality evaluation is carried out.

At present, the detection of the missile is mainly based on electrical performance detection and surface visual inspection, and mechanical and physical defects and faults in the missile body cannot be found, so a device for visually seeing each component in the missile body under the conditions that the missile is not disassembled and damaged is designed, the problems and the severity of the missile to be detected are accurately found, and quality evaluation is carried out in time. In addition, in order to adapt to the characteristics of army standing training and field environment in wartime, the device has the advantages of small volume, light weight, easy disassembly and assembly, good universality and convenient vehicle-mounted transportation.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a can be under the condition that the guided missile did not disintegrate, carry out real-time imaging to the guided missile is inside, see internal defect and trouble directly perceivedly, carry out quality assessment's guided missile nondestructive test system to the guided missile.

The utility model adopts the following technical scheme:

the utility model provides a guided missile nondestructive test system, its includes the main support, sets up the slip table that bears on the main support, sets up the X ray source in main support one side, sets up imager slip table 4 and the control system in the main support opposite side.

The front end and the rear end of the main support are respectively provided with a first auxiliary support and a second auxiliary support, and the first auxiliary support and the second auxiliary support are connected with the main support through locking joints; the main bracket is provided with a guide rail, the first auxiliary bracket and the second auxiliary bracket are also provided with guide rails and are spliced with the guide rails on the main bracket to form a long rail, and the bottom of the bearing sliding table is provided with a sliding groove matched with the guide rails; be provided with the belt pulley on first auxiliary support and the second auxiliary support, two be provided with on the belt pulley and bear the weight of the slip table belt, bear the weight of slip table belt and bear slip table fixed connection, be provided with the bearing slip table motor that is used for the drive to bear the weight of the slip table belt on the main support.

The front end and the rear end of the bearing sliding table are both provided with a support frame and a roller group arranged on the support frame, and the roller group is provided with a clamp; the roller group comprises two rollers arranged in parallel and a belt guide wheel arranged between the two rollers, and the rollers and the belt guide wheel are connected with a roller motor through roller belts.

The imager sliding table is provided with an imager bracket, and the imager bracket is provided with a digital imager; the imager bracket is connected with the imager sliding table through a T-shaped groove, and the imager sliding table is provided with an imager motor for driving the imager bracket to move in a direction vertical to the guide rail.

The X-ray source device comprises a main bracket, a mobile power supply and a camera, wherein the main bracket is provided with the camera at one side of the X-ray source; an electric transfer box is arranged in the main bracket.

The control system comprises a control box, a movable wire coil, a ray source controller, a computer and an alarm; the control box is connected with the electric transfer box and the camera through cables; the mobile power supply supplies power to the control box, the ray source controller and the computer through the mobile wire coil; the X-ray source is connected with the ray source controller through a cable, and the ray source controller is connected with the alarm; the digital imager is connected with the computer through a cable.

Wherein, the bottom of the main bracket is provided with a caster.

Wherein, the guide rail is two parallel.

Wherein, the both ends of gyro wheel are provided with the anchor clamps stopper.

The beneficial effects of the utility model reside in that: (1) the utility model discloses a to the nondestructive test of guided missile, fix a position, the classification is judged, shape and size measurement to guided missile internal defect and trouble, in time carry out the quality to the guided missile and judge, avoid the emergence of guided missile launch failure and major incident. (2) The designed light combined tool can be quickly unfolded, folded, boxed and transported; the remote video monitoring and operation control mode is adopted, reliable ray radiation distance protection is realized, and a heavy fixed lead room is not needed; the system has small volume and light weight, is convenient for vehicle-mounted transportation, and is suitable for missile performance detection under field conditions.

Drawings

Fig. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a side view of fig. 1.

Fig. 3 is an electrical schematic diagram of the present invention.

Fig. 4 is a schematic sectional view of the jig.

Fig. 5 is a side view of the structure of fig. 4.

FIG. 6 is a schematic view of another length of the clip.

Wherein, 1 a main support, 2 a bearing sliding table, 3 an X-ray source, 4 an imager sliding table, 5 a first auxiliary support, 6 a second auxiliary support, 7 a locking joint, 8 a guide rail, 9 a sliding groove, 10 a belt pulley, 11 a bearing sliding table belt, 12 a bearing sliding table motor, 13 a support frame, 14 a clamp, 15 rollers, 16 belt guide wheels, 17 a roller belt, 18 a roller motor, 19 an imager support, 20 a digital imager, 21 an imager motor, 22 a camera, 23 a mobile power supply, 24 an electrical adapter box, 25 a control box, 26 a mobile wire coil, 27 a ray source controller, 28 a computer, 29 an alarm, 30 casters, 31 a clamp limiting block, 32 a tested missile, 14-1 an upper support ring, 14-2 a lower support ring, 14-3 a support clamping block, 14-4 screw grooves, 14-5 screw holes, 14-6 mating surfaces, 14-7 fixing screws, 14-7 a fixed screw, 14-8 fixture block fixing grooves, 14-9 lightening holes, 14-10 reinforcing blocks, 14-11 involutory grooves and 14-12 involutory bosses.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and examples.

As shown in fig. 1 and 2, a missile nondestructive testing system includes a main support 1, a bearing sliding table 2 disposed on the main support 1, an X-ray source 3 disposed on one side of the main support 1, an imager sliding table 4 disposed on the other side of the main support 1, and a control system.

The front end and the rear end of the main bracket 1 are respectively provided with a first auxiliary bracket 5 and a second auxiliary bracket 6, and the first auxiliary bracket 5 and the second auxiliary bracket 6 are connected with the main bracket 1 through a locking joint 7; the main support 1 is provided with a guide rail 8, the first auxiliary support 5 and the second auxiliary support 6 are also provided with guide rails 8 and are spliced with the guide rails 8 on the main support 1 to form a long rail, and the bottom of the bearing sliding table 2 is provided with a sliding groove 9 matched with the guide rails 8; be provided with belt pulley 10 on first auxiliary support 5 and the second auxiliary support 6, two be provided with on the belt pulley 10 and bear slip table belt 11, bear slip table belt 11 and bear slip table 2 fixed connection, be provided with on the main support 1 and be used for the drive to bear slip table motor 12 of bearing of slip table belt 11.

The front end and the rear end of the bearing sliding table 2 are both provided with a support frame 13 and a roller group arranged on the support frame 13, and the roller group is provided with a clamp 14; the roller group comprises two rollers 15 arranged in parallel and a belt guide wheel 16 arranged between the two rollers 15, and the rollers 15 and the belt guide wheel 16 are connected with a roller motor 18 through roller belts 17.

An imager bracket 19 is arranged on the imager sliding table 4, and a digital imager 20 is arranged on the imager bracket 19; the imager bracket 19 is connected with the imager sliding table 4 through a T-shaped groove, and an imager motor 21 for driving the imager bracket 19 to move in a direction perpendicular to the guide rail is arranged on the imager sliding table 4.

The system further comprises a mobile power supply 23; a camera 22 is arranged on one side of the main bracket 1, which is positioned on the X-ray source 3; an electrical junction box 24 is arranged in the main support 1.

The bottom of the main bracket 1 is provided with a caster 30. The guide rails 8 are two parallel rails. And two ends of the roller 15 are provided with clamp limiting blocks 31.

As shown in fig. 3, the control system comprises a control box 25, a movable wire coil 26, a ray source controller 27, a computer 28 and an alarm 29; the control box 25 is connected with the electric junction box 24 and the camera 22 through cables; the mobile power supply 23 supplies power to the control box 25, the ray source controller 27 and the computer 28 through the mobile wire coil 26; the X-ray source 3 is connected with a ray source controller 27 through a cable, and the ray source controller 27 is connected with an alarm 29; the digital imager 20 is connected to a computer 28 by a cable.

As shown in fig. 4 and 5, the clamp comprises an upper support ring 14-1, a lower support ring 14-2 and a support fixture block 3; the upper support ring 14-1 and the lower support ring 14-2 are combined to form a closed ring shape, the outer side walls of two ends of the upper support ring 14-1 are provided with screw grooves 14-4 perpendicular to the bottom edge of the upper support ring 14-1, the bottom of the screw grooves 14-4 and the upper end surface of the lower support ring are provided with corresponding screw holes 14-5, and fixing screws 14-7 for connecting the combined surface 14-6 of the upper support ring 14-1 and the lower support ring 14-2 are arranged in the screw holes 14-5 in a penetrating manner; fixture block fixing grooves 14-8 are uniformly formed in the inner side walls of the upper supporting ring 14-1 and the lower supporting ring 14-2 along the circumferential direction, and supporting fixture blocks 14-3 are arranged in the fixture block fixing grooves 14-8.

The cross section of the supporting fixture block 14-3 is trapezoidal, the supporting fixture block 14-3 is embedded in the fixture block fixing groove 14-8, the top of the supporting fixture block 14-3 is arc-shaped, and the tops of the supporting fixture blocks 14-3 are surrounded to form a circumference; the support fixture block 14-3 is provided with a lightening hole 14-9. The length of the supporting fixture block can be selected according to the diameters of workpieces of different models.

The upper support ring 14-1, the lower support ring 14-2, the support clamping blocks 14-3, the fixing screws 14-7 and the reinforcing blocks 14-10 are all made of nylon.

As shown in figure 6, in order to clamp a missile with a smaller diameter, the length of the supporting fixture block is longer, the top of the supporting fixture block is provided with a reinforcing block 14-10, the top of the reinforcing block 14-10 is arc-shaped, and the tops of a plurality of reinforcing blocks surround to form a circumference. For the supporting clamping block with longer length, the reinforcing block can increase the contact area of the supporting clamping block and the missile to be measured, so that the supporting clamping block and the missile are fixed more firmly.

When the clamp is used, firstly, the supporting clamping block is inserted into the clamping block fixing groove, the upper supporting ring and the lower supporting ring clamp the tested missile 32, so that the supporting clamping block is in close contact with the tested missile, the weight of the whole clamp is reduced by the lightening hole, the upper supporting ring and the lower supporting ring are aligned, and the left and right screw grooves of the upper supporting ring and the left and right screw holes of the lower supporting ring are aligned; in order to be more easily involuted, involution grooves 14-11 and involution bosses 14-12 which are matched with each other can be arranged at involution parts of the upper support ring and the lower support ring, so that the positioning is more convenient; the two fixing screws are respectively inserted into the two screw grooves and screwed down, so that the tested missile is firmly clamped; two clamps can be arranged at appropriate positions at both ends according to the length of the missile 32 to be measured.

In the specific implementation process of the detection system, the main support is pushed to a specified position by using the trundles, and the first auxiliary support and the second auxiliary support are respectively fixed at the front end and the rear end of the main support through the locking joints to form a basic bearing frame of the tool; can pull down first auxiliary support and second auxiliary support when withdrawing, nest in an organic whole with the main support, reduced the system volume, be convenient for case.

The guide rails are respectively fixed on the main support, the first auxiliary support and the second auxiliary support and are kept horizontally aligned to form long guide rails spanning the main support, the first auxiliary support and the second auxiliary support, and 1 guide rail is respectively arranged on two sides of each support. The bearing sliding table is connected with the guide rail, the bearing sliding table belt is connected with the bearing sliding table, and the bearing sliding table motor drives the bearing sliding table belt to rotate and drives the bearing sliding table to move back and forth along the guide rail, so that the tested guided missile 32 can be translated back and forth, and the tested guided missile 32 can be scanned and detected from beginning to end. 2 rollers are fixed on the bearing sliding table and connected with a roller belt, and a roller motor drives the roller belt to drive the rollers to rotate; two ends of the missile to be tested are respectively clamped by the clamps, the clamps are placed on the rollers and can be driven by the rotation of the rollers to rotate, and 360-degree rotation scanning detection on the missile to be tested 32 is realized. The clamp limiters are fixed on two sides of the roller to prevent the clamp from sliding off when rotating.

The X ray source is fixed in one side of main support, and the opposite side at the main support is fixed to the imager slip table, and digital imager fixes on the imager support, and the imager support passes through T-slot connection with the imager slip table, and the imager motor drives the imager support along imager slip table translation, realizes examining the focus adjustment of time measuring to the quilt guided missile of different diameters. The center of a ray emitting port of the X-ray source is opposite to the center of the digital imager, and the center of the X-ray source and the center of the clamp, namely the axis of the missile to be measured, are at the same horizontal height, so that the complete coverage scanning of the missile to be measured and the full utilization of the digital imager are ensured; the electric junction box is arranged in the main bracket to improve the compactness of the system.

As shown in fig. 3, the control and acquisition circuit of the utility model comprises an electrical transfer box, a control box, a ray source controller, an alarm, a mobile power supply, a mobile wire coil and a computer; the connection relationship among the circuits is as follows: the control box is connected with the electrical junction box through a 50-meter control cable to send a control instruction, and is connected with the camera through a 50-meter video cable to receive video monitoring information; the ray source controller is connected with the X-ray source through a 50-meter ray control cable to control the X-ray source and is connected with the alarm to send an alarm signal; the computer is connected with the digital imager through a 50-meter network cable to acquire the information of the radiographic image; the mobile power supply supplies power to the control box, the ray source controller and the computer through the mobile wire coil and supplies power to the electrical junction box; the electric transfer box respectively supplies power to the camera, the digital imager, the bearing sliding table motor, the roller motor and the imager motor and controls the actions of the above 3 motors.

The utility model discloses a control box sends control command to electric transfer box to the corresponding motor action of drive: and the whole missile is scanned by 360 degrees from the beginning to the end by the X-ray. And a display on the control box receives the field video transmitted by the camera in real time, so that the field real-time monitoring is realized. And the computer receives the radiation image signal transmitted by the digital imager in real time, and the radiation image signal is subjected to image processing and then is checked by a user for fault identification. The radiation intensity of the X-ray source is adjusted by the ray source controller, and proper radiation intensity can be set according to different positions of the missile to be detected until the optimal image is obtained. After the tested missiles with different diameters are replaced, the position of the digital imager is adjusted through the control box to focus, and the proper focal distance can be set through observing the image definition on the computer.

The utility model discloses a distance carries out the X ray protection, divide into test area and operating area with the test site, and the test area contains test fixture, quilt survey guided missile, camera and portable power source, and personnel's operating area contains control box, ray source controller, alarm, removal drum and computer, and the operating area sets up in the rear of X ray source ray transmission mouth, and two regions are about 50 meters apart from, can effectively avoid the injury of X ray radiation to the human body.

The utility model discloses in, the X ray source adopts 300KV little focus X ray source, and digital imager adopts 3025 dull and stereotyped digital imager, bears the slip table motor and adopts 110BYG350 type step motor, and roller motor, imager motor adopt 56BYG250 type step motor, and portable power source adopts single-phase 220V5KW gasoline engine generator, and anchor clamps are the nylon material. The control box is a PLC or single chip microcomputer control system with a display. Electrical junction boxes are a routine choice in the art.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention should be covered by the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. The missile nondestructive testing system is characterized by comprising a main support (1), a bearing sliding table (2) arranged on the main support (1), an X-ray source (3) arranged on one side of the main support (1), an imager sliding table (4) arranged on the other side of the main support (1) and a control system;

the front end and the rear end of the main support (1) are respectively provided with a first auxiliary support (5) and a second auxiliary support (6), and the first auxiliary support (5) and the second auxiliary support (6) are connected with the main support (1) through locking joints (7); a guide rail (8) is arranged on the main support (1), the guide rails (8) are also arranged on the first auxiliary support (5) and the second auxiliary support (6) and are spliced with the guide rail (8) on the main support (1) to form a long rail, and a sliding groove (9) matched with the guide rail (8) is arranged at the bottom of the bearing sliding table (2); the first auxiliary support (5) and the second auxiliary support (6) are provided with belt pulleys (10), two belt pulleys (10) are provided with bearing sliding table belts (11), the bearing sliding table belts (11) are fixedly connected with the bearing sliding table (2), and the main support (1) is provided with a bearing sliding table motor (12) for driving the bearing sliding table belts (11);

the front end and the rear end of the bearing sliding table (2) are respectively provided with a support frame (13) and a roller group arranged on the support frame (13), and the roller group is provided with a clamp (14); the roller group comprises two rollers (15) arranged in parallel and a belt guide wheel (16) arranged between the two rollers (15), and the rollers (15) and the belt guide wheel (16) are connected with a roller motor (18) through roller belts (17).

2. The missile nondestructive testing system of claim 1, wherein the imager slide (4) is provided with an imager bracket (19), and the imager bracket (19) is provided with a digital imager (20); the imaging device is characterized in that the imaging device support (19) is connected with the imaging device sliding table (4) through a T-shaped groove, and an imaging device motor (21) for driving the imaging device support (19) to move in the direction perpendicular to the guide rail is arranged on the imaging device sliding table (4).

3. The missile nondestructive testing system of claim 1, further comprising a mobile power source (23); a camera (22) is arranged on one side of the X-ray source (3) of the main support (1); an electric transfer box (24) is arranged in the main bracket (1).

4. Missile nondestructive testing system according to claim 3, characterized in that the control system comprises a control box (25), a moving coil (26), a radiation source controller (27), a computer (28) and an alarm (29); the control box (25) is connected with the electric junction box (24) and the camera (22) through cables; the mobile power supply (23) supplies power to the control box (25), the ray source controller (27) and the computer (28) through a mobile wire coil (26); the X-ray source (3) is connected with a ray source controller (27) through a cable, and the ray source controller (27) is connected with an alarm (29); the digital imager (20) is connected to a computer (28) by a cable.

5. Missile nondestructive testing system according to claim 1, characterized in that the bottom of the main support (1) is provided with casters (30).

6. Missile nondestructive testing system according to claim 1, characterized in that the guide rails (8) are two parallel.

7. Missile nondestructive testing system according to claim 1, characterized in that the rollers (15) are provided with clamp stoppers (31) at both ends.