CN214470419U - Missile testing device - Google Patents
Missile testing device Download PDFInfo
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- CN214470419U CN214470419U CN202023182794.8U CN202023182794U CN214470419U CN 214470419 U CN214470419 U CN 214470419U CN 202023182794 U CN202023182794 U CN 202023182794U CN 214470419 U CN214470419 U CN 214470419U
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Abstract
Missile testing arrangement, testing arrangement includes the supporting bench body, the light source, clamping device, light source biax rotating assembly and controller, the one end of supporting bench body is located to clamping device detachably, clamping device's axial sets up along the horizontal direction for the centre gripping is tested the missile, the other end of supporting bench body is located to the light source, light source biax rotating assembly locates on the supporting bench body, the switch of controller control light source, and control light source biax rotating assembly drive light source along driftage direction and/or the motion of every single move. The utility model relates to a guided missile testing arrangement, through the clamping device who changes different models with the guided missile that is tested of different models of test, improved the test commonality, improve the efficiency of software testing at driftage and every single move direction through light source biax rotating assembly.
Description
Technical Field
The utility model belongs to the technical field of measure, more specifically relates to a guided missile testing arrangement.
Background
The missile test is an important work item in the process of missile development, production and use, is used for checking and verifying the function and main technical performance of a missile system, positioning faults, adjusting unqualified parameters or replacing faulty components under the necessary and allowable conditions, and ensures that the technical state and the functional performance of the missiles produced in factories meet requirements so as to ensure that the delivered missiles are in a good standby state. The missile testing support device is necessary equipment for a missile in the final assembly testing process, but the existing missile testing tool mainly has the following defects: 1. the main body supporting equipment is large and inconvenient to transport; 2. when the equipment clamping and supporting tool clamps the missile, the surface of the missile is scratched and the paint skin is damaged frequently, and the cabin section is possibly scrapped seriously; 3. the equipment is not strong in universality, and different types of missiles cannot be shared at the same time; 4. the equipment test is unstable, the performance test precision is not high, and the support is unstable and inconvenient; 5. the equipment testing efficiency is low, and the joint test of the pitching and heading direction target simulation cannot be realized. Therefore, it is necessary to develop a missile testing device, which can at least solve the problem of weak universality in the prior art.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a guided missile testing arrangement can solve the not strong problem of general type among the prior art at least.
In order to realize the above-mentioned purpose, the utility model provides a missile testing arrangement, testing arrangement includes the supporting bench body, light source, clamping device, light source biax rotating assembly and controller, clamping device detachably locates the one end of the supporting bench body, clamping device's axial is along the horizontal direction setting for the centre gripping is tested the missile, the light source is located the other end of the supporting bench body, light source biax rotating assembly locates on the supporting bench body, the controller control the switch of light source, and control light source biax rotating assembly drive yaw direction and/or pitch direction motion are followed to the light source.
Preferably, the clamping device comprises a rear section supporting clamp, a middle section supporting clamp and a front section supporting clamp which are sequentially arranged from one end of the supporting table body to the other end in parallel and are coaxial, and the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are detachably connected with the supporting table body through bases.
Preferably, the rear section supporting clamp and the front section supporting clamp are circular ring structures spliced by two semicircular ring structures, each semicircular ring structure is hinged to one end of the other semicircular ring structure, the other end of the semicircular ring structure is locked by a lock catch, and the middle section supporting clamp is of a semicircular ring structure.
Preferably, the inner wall of the front section supporting clamp is provided with a rotatable annular slide rail, one side of the annular slide rail is provided with a handle, and the annular slide rail and the front section supporting clamp are provided with alignment marks.
Preferably, the inner wall of the annular slide rail is provided with a silica gel pad, and the inner wall of the rear section supporting clamp and the inner wall of the middle section supporting clamp are provided with rollers.
Preferably, the device further comprises three fine adjustment mechanisms, wherein each fine adjustment mechanism comprises an installation platform, a fine adjustment bracket, a hand wheel, a screw rod assembly and an instrument, and the screw rod assembly and the instrument are arranged in the fine adjustment bracket;
the fine adjustment support is arranged on the supporting platform body, the mounting platform is connected to the top of the fine adjustment support in a sliding mode and is connected to the lead screw assembly, the hand wheel is arranged on the outer side of the fine adjustment support, the hand wheel is rotated to drive a lead screw of the lead screw assembly to rotate, so that a lead screw nut of the lead screw assembly drives the mounting platform to move linearly along the lead screw, and the instrument is used for displaying adjustment measurement of the lead screw assembly;
the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are respectively arranged on one mounting platform of the fine adjustment mechanism.
Preferably, the missile launching device further comprises a plurality of laser positioning devices, the plurality of laser positioning devices are arranged on the supporting table body, and laser emitted by each laser positioning device is used for aligning with a reference point on the missile.
Preferably, the light source double-shaft rotating assembly comprises an arc-shaped sliding rail, a mounting disc, a yaw motor assembly, a pitching motor assembly, a moving part and a supporting frame;
the supporting frame is connected to the other end of the supporting table body, the mounting disc and the pitching motor assembly are connected to the top end of the supporting frame, the arc-shaped sliding rail is arranged at one end, extending beyond the clamping device, of the mounting disc, the moving part is connected to the arc-shaped sliding rail in a sliding mode, the light source is arranged on the moving part, the yawing motor assembly is connected to the moving part, the pitching motor assembly is used for driving the mounting disc to swing in the pitching direction, and the yawing motor assembly is used for driving the moving part to slide in the arc-shaped sliding rail in the yawing direction;
the controller controls the start, stop and running speed of the yaw motor assembly to drive the moving piece to move along the arc-shaped sliding rail, so that the light source is driven to move along the yaw direction, and the controller controls the start, stop and running speed of the pitch motor assembly to enable the mounting plate to swing along the pitch direction, so that the light source is driven to move along the pitch direction.
Preferably, the moving angle range of the moving part along the yaw direction is +/-35 degrees, and the moving angle range of the mounting disc along the pitch direction is-10 degrees to 55 degrees.
Preferably, the light source double-shaft rotating assembly is arranged on the supporting table body, is electrically connected with the light source double-shaft rotating assembly and is in communication connection with the controller, so as to receive a control command sent by the controller and control the light source double-shaft rotating assembly according to the control command.
The utility model relates to a guided missile testing arrangement, its beneficial effect lies in: the device has the advantages that the device can be used for testing the tested missiles of different models by replacing the clamping devices of different models, the testing universality is improved, and the testing efficiency in the yaw and pitch directions is improved through the light source double-shaft rotating assembly.
Other features and advantages of the present invention will be described in detail in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout the exemplary embodiments of the present invention.
Fig. 1 shows a schematic structural diagram of a missile testing device according to an exemplary embodiment of the present invention;
FIG. 2 shows a schematic view of the range of rotation of the pitch angle in a missile testing unit in accordance with an exemplary embodiment of the present invention;
fig. 3 shows a schematic view of the rotation range of the yaw angle in the missile testing device according to an exemplary embodiment of the present invention.
Description of reference numerals:
1 back end support anchor clamps, 2 middle sections support anchor clamps, 3 laser positioning device, 4 anterior segments support anchor clamps, 5 annular slide rails, 6 arc slide rails, 7 mounting discs, 8 yaw motor components, 9 light sources, 10 emergency stop buttons, 11 operation pilot lamps, 12 electric cabinets, 13 electric cabinet interfaces, 14 support stage bodies, 15 pitch motor components, 16 motion, 17 support frames, 18 drawers, 19 fine-tuning, 20 universal wheels, 21 rings.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
For solving the problem that prior art exists, the utility model provides a guided missile testing arrangement, testing arrangement includes the supporting bench body, the light source, clamping device, light source biax rotating assembly and controller, the one end of supporting bench body is located to clamping device detachably, clamping device's axial is along the horizontal direction setting, be used for the centre gripping by the test guided missile, the other end of supporting bench body is located to the light source, light source biax rotating assembly locates on the supporting bench body, the switch of controller control light source, and control light source biax rotating assembly drive light source along yaw direction and/or pitch direction motion.
The utility model relates to a guided missile testing arrangement, through the clamping device who changes different models with the guided missile that is tested of different models of test, improved the test commonality, improve the efficiency of software testing at driftage and every single move direction through light source biax rotating assembly.
The controller controls the light source double-shaft rotating assembly to drive the light source to move along a preset track, the tested guided missile captures and tracks the light source and transmits a tracking signal to the controller, and the controller compares the light source tracking signal fed back by the tested guided missile with the preset track signal and judges whether the product is qualified or not according to a comparison result.
Preferably, the clamping device comprises a rear section supporting clamp, a middle section supporting clamp and a front section supporting clamp which are sequentially arranged from one end of the supporting table body to the other end in parallel and are coaxial, and the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are detachably connected with the supporting table body through bases.
The supporting table body adopts a missile course layout, the arrangement modes of the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are set according to the course of the tested missile, and the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are fixed on the supporting table body through quick locking bolts and pins which penetrate through the base; the front section supporting clamp is used for fixing and rotating the head of the tested guided missile, and the middle section supporting clamp and the rear section supporting clamp are used for supporting and clamping the tail of the tested guided missile. The internal diameters of the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are adapted to the missile diameter of a tested missile of a certain type, and the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp of different internal diameter types are replaced to be suitable for tested missiles of different missile diameters, so that the universality is strong, and the operation is easy.
Preferably, the rear section supporting clamp and the front section supporting clamp are circular ring structures spliced by two semicircular ring structures, each semicircular ring structure is hinged to one end of the other semicircular ring structure, the other end of each semicircular ring structure is locked by a lock catch, and the middle section supporting clamp is of a semicircular ring structure.
The rear section supporting clamp and the front end supporting clamp are used for clamping the tested guided missile, the two semicircular ring structures spliced into the annular structure can be opened and closed, the tested guided missile can be conveniently placed into the annular structure, the annular structure can be locked through the lock catch after the annular structure is placed into the annular structure, the lock catch structure is a common locking mode, and therefore the specific structure is not repeated. The middle section supporting clamp is used for supporting the projectile body.
Preferably, the inner wall of the front section supporting clamp is provided with a rotatable annular slide rail, one side of the annular slide rail is provided with a handle, and the annular slide rail and the front section supporting clamp are provided with alignment marks.
The annular slide rail is used for driving the tested guided missile to rotate by 90 degrees when the tested guided missile is in a clamping state, and the rotation angle is quickly realized through the alignment mark, so that the polarity test of an inertia measurement unit in the tested guided missile is met.
The annular slide rail is formed by splicing two semicircular structures matched with the front section supporting clamp, the two semicircular structures of the front section supporting clamp correspond to each other up and down, when the two semicircular structures of the front section supporting clamp are closed, the handle of the annular slide rail is rotated, the annular slide rail rotates along the circumferential direction, and the farthest rotating distance is not more than the connecting distance between the annular slide rail and the semicircular structures of the front section supporting clamp.
The annular slide rail is sliding connection with anterior segment support fixture inner wall, and its connected mode is common slider joint mode, and concrete structure is no longer repeated.
Preferably, the inner wall of the annular slide rail is provided with a silica gel pad, and the inner walls of the rear section supporting clamp and the middle section supporting clamp are provided with rollers. The silica gel pad can realize flexible contact, guarantees the fastness of centre gripping guided missile, can not produce the scratch to the lacquer painting of guided missile simultaneously, and the gyro wheel then is used for providing the sliding force when being tested the guided missile is rotatory, and the axial of gyro wheel is the same with the axial of being tested the guided missile, makes to be tested guided missile produce relative slip when front end support fixture drives the rotation between back end support fixture, the middle section support fixture.
Preferably, the device also comprises three fine adjustment mechanisms, wherein each fine adjustment mechanism comprises a mounting platform, a fine adjustment bracket, a hand wheel, a screw rod assembly and an instrument, wherein the screw rod assembly and the instrument are arranged in the fine adjustment bracket;
the fine adjustment support is arranged on the supporting platform body, the mounting platform is connected to the top of the fine adjustment support in a sliding mode and is connected to the lead screw assembly, the hand wheel is arranged on the outer side of the fine adjustment support, the hand wheel can be rotated to drive a lead screw of the lead screw assembly to rotate, so that a lead screw nut of the lead screw assembly drives the mounting platform to move linearly along the lead screw, and the instrument is used for displaying adjustment measurement of the lead screw assembly, namely the movement distance of the lead screw nut along the lead screw which is arranged in the axial direction of the tested missile;
the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are respectively arranged on a mounting platform of a fine adjustment mechanism.
The screw component is a common trapezoidal screw component in the market, and the instrument is a mechanical digital display instrument and is used for displaying the measurement of the adjustment of the trapezoidal screw component. The fine setting support top both sides are equipped with the slide rail, and mounting platform is through connecting in the slider sliding connection in the slide rail in support top, and fixed connection in screw nut, and hand wheel department can set up locking structure and lock, avoids the mistake to bump the hand wheel and leads to mounting platform's position drunkenness.
The rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are positioned on the same axis through the fine adjustment mechanism, namely the position of the central shaft of the guided missile is horizontally adjusted in the sailing direction, so that the guided missile and the light source are positioned on the same axis. When the clamping device is used, the axis positions of the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are adjusted in advance through the fine adjustment mechanism, the fine adjustment mechanism is locked after data are recorded, mistaken touch is avoided, and when the clamping devices of different bullet diameter models are replaced, the position of the clamping device can be quickly adjusted to meet the initial preset position of the bullet diameter model by adjusting the screw rod assembly to the preset value.
The fine adjustment mechanism can transversely adjust the clamping device, improve the precision of performance test, ensure the stability of support and facilitate the position adjustment.
Preferably, the missile launching device further comprises a plurality of laser positioning devices, the plurality of laser positioning devices are arranged on the supporting table body, and laser emitted by each laser positioning device is used for aligning with the datum point on the missile.
The laser positioning devices are laser generators existing in the market, each laser positioning device is used for aligning the guided missile to be tested in different assembly states, such as a cabin section state, a cabin section general assembly state and datum points of guided missiles with different missile diameters, so that the guided missiles are guaranteed to be accurately placed at each time when being manually carried and clamped, the whole guided missiles can be stably and accurately aligned to the rotating datum points, the tested indexes are guaranteed to be accurate and effective, and the testing requirements are met.
Preferably, the light source double-shaft rotating assembly comprises an arc-shaped sliding rail, a mounting disc, a yaw motor assembly, a pitching motor assembly, a moving part and a supporting frame;
the support frame is connected to the other end of the support table body, the mounting disc and the pitching motor assembly are connected to the top end of the support frame, the arc-shaped slide rail is arranged at one end, facing the clamping device, of the mounting disc, the moving part is connected to the arc-shaped slide rail in a sliding mode, the light source is arranged on the moving part, the yawing motor assembly is connected to the moving part, the pitching motor assembly is used for driving the mounting disc to swing in the pitching direction, and the yawing motor assembly is used for driving the moving part to slide in the arc-shaped slide rail in the yawing direction;
the controller controls the start, stop and running speed of the yaw motor assembly to drive the moving piece to move along the arc-shaped sliding rail, so that the light source is driven to move along the yaw direction, and the controller controls the start, stop and running speed of the pitch motor assembly to enable the mounting disc to swing in the pitch direction, so that the light source is driven to move in the vertical direction along the pitch direction.
The light source double-shaft rotating assembly is used for simulating target motion in the yaw direction and the pitch direction, namely the motion trail of the light source, so as to test the capture and tracking capacity of the missile.
Both sides of the arc-shaped slide rail are V-shaped guide rail surfaces, one end of the moving part is provided with a pair of pulleys which are respectively clamped on the V-shaped guide rail surfaces on both sides, the other end of the moving part is a plate type, and the light source and the yaw motor assembly are connected to the plate type end of the moving part through the motor bracket;
the bottom surface of arc slide rail is equipped with the arc rack, and the yaw motor subassembly includes yaw motor and yaw motor gear, and yaw motor gear engagement connects in the arc rack, and the other end fixed connection that the output shaft of yaw motor passed the moving part is in the yaw motor gear, and the operation of controller control yaw motor to make the yaw motor gear rotate along the arc rack, thereby provide thrust and slide along the arc slide rail with the drive moving part.
The junction on the light source motor support is equipped with along a plurality of fine setting holes of vertical top setting, and the light source back is equipped with the installation notch, through connecting the installation notch in the position of different fine setting holes in order to adjust the light source.
The other end of the mounting disc, namely the bottom of the arc-shaped outer edge end of the mounting disc, is rotatably connected to the support frame through a bearing;
the pitching motor assembly comprises a pitching motor, a coupler and a connecting shaft, the connecting shaft is fixedly connected to the arc-shaped outer edge end of the mounting disc, the connecting shaft and a bearing at the bottom of the mounting disc are coaxial, the axis of the connecting shaft is arranged along the radial direction of the missile to be tested, the connecting shaft is connected with an output shaft of the pitching motor through the coupler, and the controller controls the pitching motor to operate, so that the connecting shaft rotates, the mounting disc is driven to swing up and down by taking the joint of the mounting disc and the supporting frame as the axis, namely, the pitching motor moves, and the light source is driven to move along the pitching direction.
The supporting frame is provided with a limit switch for limiting the maximum pitching angle of the mounting disc, and the controller controls the pitching motor to stop running according to a signal of the limit switch.
Preferably, the range of angular movement of the moving member in the yaw direction is ± 35 °, and the range of angular movement of the mounting plate in the pitch direction is-10 ° -55 °.
Preferably, the electric cabinet is arranged on the supporting table body, is electrically connected with the light source double-shaft rotating assembly and is in communication connection with the controller so as to receive a control instruction sent by the controller and control the light source double-shaft rotating assembly according to the control instruction.
The yaw motor assembly and the pitch motor assembly comprise motor encoders, and the electric cabinet comprises a box body, and a motor driver, a power supply and a signal adapter plate which are arranged in the box body; the box body is connected with the supporting platform body, the signal adapter plate receives an electric signal fed back by the motor encoder, and simultaneously receives an electric control signal of the controller, and controls the starting, stopping and moving speeds of the yaw motor and the pitching motor through the motor driver;
the electric cabinet is still including locating scram button, operation pilot lamp and the electric cabinet interface on the box, and the guided missile under test passes through cable electric connection with the electric cabinet interface, and the signal keysets receives the test signal information of guided missile under test and transmits for the controller, and the scram button is used for controlling motor drive and stops the operation.
The light source moves at a preset speed in the yaw direction and the pitch direction according to preset position information, a target tracking device is arranged in the head of the tested missile and used for tracking light source signals, namely, the target capturing and tracking capacity of the tested missile is measured, a signal adapter plate transmits received tracking signals to a controller, and the controller compares the tracking signals with the preset light source position and speed, namely, a preset motion track:
and when the tracking signal is not matched with the preset light source track, judging the tested missile to be a qualified product.
Preferably, at least one drawer is arranged on the side surface of the supporting table body, is used for accommodating clamping devices with different spring diameters and is locked through a locking structure; the bottom four corners of the supporting table body are provided with lockable universal wheels, the supporting table body is convenient to move and fixed when the test is not influenced, the top four corners of the supporting table body are provided with hanging rings, and the two sides of the supporting table body are provided with handles, so that the supporting table body is convenient to move.
The utility model relates to a guided missile testing arrangement adopts the aluminum alloy to make.
According to the utility model discloses a method that guided missile testing arrangement carries out guided missile test as follows:
step 3, the controller controls the light source rotating assembly to operate to enable the light source to move according to a preset speed and a preset position, namely, the light source moves along a preset track, the controller compares a tracking signal fed back by the tested missile with a preset motion track signal and judges whether the tracking signal meets the requirement or not so as to test performance parameters of the missile, such as a search range, a search period, a target search speed and the like;
step 4, rotating the tested missile by 90 degrees along the annular slide rail by utilizing the handle of the front section supporting clamp, feeding the inertia information back to the controller by using an inertia measuring unit in the tested missile, comparing the inertia measuring signal of the tested missile with preset information by using the controller, and judging whether the polarity of the tested missile meets the requirement or not;
and 5, disconnecting each line after the test is finished, and processing the tested missile according to the comparison result of the controller.
And after the test is finished, placing the qualified missile product to be tested in a qualified product area, placing the unqualified missile product in an unqualified product area, and finishing the test.
When missiles with other types and missile diameters need to be tested, the rear section supporting clamp, the middle section supporting clamp and the front section supporting clamp are disassembled, the clamping devices corresponding to the missile diameters are taken out from the drawer and are installed on the installation platform of the fine adjustment mechanism, and the steps are repeated to realize the test of the missiles.
The utility model relates to a missile testing device, which can lead the tracking target, namely the light source to carry out double-shaft motion, can simultaneously test a plurality of directions and a plurality of models for the tested missile, and is not limited to small-sized missiles;
the integrated level is high, the clamping device, the light source double-shaft rotating assembly, the laser positioning device, the electric cabinet and the supporting table body are effectively integrated together, and devices such as lifting lugs and handles are designed, so that the portability of transportation is fully considered;
through reasonable design clamping device, guarantee to be flexible connection between guided missile and the frock, can not make guided missile surface produce the damage. In addition, in a clamping state, the missile can rotate through the front section supporting clamp, so that the exchange of course and pitching direction is realized, and the omnibearing test of the locking and tracking performance of the missile is met;
the device has high testing precision and is suitable for the bullet types with different bullet diameters. The positions of the central line of the guided missile and the laser testing instrument can be conveniently adjusted to the optimal position through the knob on the fine-tuning trapezoidal lead screw component supported by the clamping. In addition, by designing a clamping tool with various bullet diameters, the device is ensured to meet the clamping and testing requirements of bullets of other types;
the device can realize the simultaneous control of pitching and heading directions, so that the test of a user is more efficient, and the means are richer.
Example 1
As shown in fig. 1 to 3, the utility model provides a missile testing arrangement, testing arrangement includes the supporting bench body 14, the light source 9, clamping device, light source biax rotating assembly and controller, clamping device detachably locates the one end of supporting bench body 14, clamping device's axial is along the horizontal direction setting, be used for the centre gripping by the test guided missile, the other end of supporting bench body 14 is located to light source 9, light source biax rotating assembly locates on the supporting bench body 14, the switch of controller control light source 9, and control light source biax rotating assembly drive light source 9 along yaw direction and/or pitch direction motion.
The controller controls the light source double-shaft rotating assembly to drive the light source 9 to move along a preset track, the tested guided missile captures and tracks the light source 9 and transmits a tracking signal to the controller, and the controller compares the light source tracking signal fed back by the tested guided missile with the preset track signal and judges whether the product is qualified or not according to a comparison result.
In this embodiment, the clamping device includes rear section supporting jig 1, middle section supporting jig 2 and anterior section supporting jig 4 which are sequentially arranged in parallel and coaxial from one end of the supporting table body 14 to the other end, and the rear section supporting jig 1, the middle section supporting jig 2 and the anterior section supporting jig 4 are detachably connected to the supporting table body 14 through the base.
The supporting table body 14 adopts a missile course layout, the arrangement modes of the rear section supporting clamp 1, the middle section supporting clamp 2 and the front section supporting clamp 4 are set according to the course of the tested missile, and the supporting table body 14 is fixed through a quick locking bolt and a pin which are arranged on the base in a penetrating mode; the front section supporting clamp 4 is used for fixing and rotating the head of the tested missile, and the middle section supporting clamp 2 and the rear section supporting clamp 1 are used for supporting and clamping the tail of the tested missile. The inner diameters of the rear section supporting clamp 1, the middle section supporting clamp 2 and the front section supporting clamp 4 are adapted to the missile diameter of the tested missile of a certain type, and the rear section supporting clamp 1, the middle section supporting clamp 2 and the front section supporting clamp 4 of different inner diameter types are replaced to be suitable for the tested missiles of different missile diameters.
The rear section supporting clamp 1 and the front section supporting clamp 4 are circular ring structures spliced by two semicircular ring structures, each semicircular ring structure is hinged to one end of the other semicircular ring structure, the other end of each semicircular ring structure is locked by a lock catch, and the middle section supporting clamp 2 is of a semicircular ring structure.
The rear section supporting clamp 1 and the front end supporting clamp are used for clamping the tested guided missile, the two semicircular ring structures spliced into the annular structure can be opened and closed, the tested guided missile can be conveniently placed into the annular structure, and the annular structure can be locked through the lock catch after the guided missile is placed into the annular structure. The middle section support jig 2 is used for supporting the projectile body.
The inner wall of the front section supporting clamp 4 is provided with a rotatable annular slide rail, one side of the annular slide rail 5 is provided with a handle, and the annular slide rail 5 and the front section supporting clamp 4 are provided with alignment marks.
The annular slide rail 5 is used for driving the tested guided missile to rotate by 90 degrees when the tested guided missile is in a clamping state, and the rotation angle is quickly realized through the alignment mark, so that the polarity test of the internal inertia measurement unit of the tested guided missile is met.
Annular slide rail 5 forms for two semicircle loop configuration concatenations with anterior segment support fixture 4 adaptation, and corresponds from top to bottom with two semicircle loop configuration of anterior segment support fixture 4, and when two semicircle loop configuration closure of current segment support fixture 4, rotates the handle of annular slide rail 5, makes annular slide rail 5 follow rotation in a circumferential direction, and the furthest distance of pivoted is no longer than annular slide rail 5 and anterior segment support fixture 4's semicircle loop configuration's distance of being connected.
The inner walls of the annular slide rail 5 and the front section supporting clamp 4 are in sliding connection, the connection mode is a common slide block clamping mode, and the specific structure is not repeated.
The inner wall of the annular slide rail 5 is provided with a silica gel pad, and the inner walls of the rear section supporting clamp 1 and the middle section supporting clamp 2 are provided with idler wheels. The axial direction of the roller is the same as that of the tested missile, so that the tested missile slides relatively between the rear section supporting clamp 1 and the middle section supporting clamp 2 when being driven to rotate by the front section supporting clamp 4.
In this embodiment, the system further includes three fine adjustment mechanisms 19, and each fine adjustment mechanism 19 includes a mounting platform, a fine adjustment bracket, a hand wheel, and a screw assembly and an instrument which are arranged in the fine adjustment bracket;
the fine adjustment support is arranged on the supporting table body 14, the mounting platform is connected to the top of the fine adjustment support in a sliding mode and is connected to the lead screw assembly, the hand wheel is arranged on the outer side of the fine adjustment support, the hand wheel can be rotated to drive a lead screw of the lead screw assembly to rotate, so that a lead screw nut of the lead screw assembly drives the mounting platform to move linearly along the lead screw, and the instrument is used for displaying adjustment measurement of the lead screw assembly, namely the movement distance of the lead screw nut along the lead screw which is arranged in the axial direction of the tested missile;
the rear section supporting clamp 1, the middle section supporting clamp 2 and the front section supporting clamp 4 are respectively arranged on a mounting platform of a fine adjustment mechanism.
The screw component is a common trapezoidal screw component in the market, and the instrument is a mechanical digital display instrument and is used for displaying the measurement of the adjustment of the trapezoidal screw component. The fine setting support top both sides are equipped with the slide rail, and mounting platform is through connecting in the slider sliding connection in the slide rail in support top, and fixed connection in screw nut, and hand wheel department can set up locking structure and lock, avoids the mistake to bump the hand wheel and leads to mounting platform's position drunkenness.
The rear section supporting clamp 1, the middle section supporting clamp 2 and the front section supporting clamp 4 are positioned on the same axis through the fine adjustment mechanism 19, namely the position of the central shaft of the guided missile is horizontally adjusted in the sailing direction, and the guided missile and the light source 9 are positioned on the same axis. When the device is used, the axis positions of the rear section supporting clamp 1, the middle section supporting clamp 2 and the front section supporting clamp 4 are adjusted in advance through the fine adjustment mechanism 19, the fine adjustment mechanism 19 is locked after data recording, mistaken collision is avoided, and when clamping devices of different bullet diameter models are replaced, the position of the clamping device can be quickly adjusted to meet the initial preset position of the bullet diameter model by adjusting the screw rod assembly to the preset value.
In the embodiment, a plurality of laser positioning devices 3 are further included, the plurality of laser positioning devices 3 are arranged on the supporting table body 14, and the laser emitted by each laser positioning device 3 is used for aligning with the datum point on the missile.
The laser positioning devices 3 are laser generators existing in the market, and each laser positioning device 3 is used for aligning the tested missile in different assembly states, such as a cabin section state, a cabin section final assembly state and datum points of missiles with different missile diameters.
In the present embodiment, the number of the laser positioning devices 3 is three.
The light source double-shaft rotating assembly comprises an arc-shaped sliding rail 6, a mounting disc 7, a yaw motor assembly 8, a pitching motor 15 assembly, a moving part 16 and a supporting frame 17;
the supporting frame 17 is connected to the other end of the supporting table body 14, the mounting disc 7 and the pitching motor assembly 15 are connected to the top end of the supporting frame 17, the arc-shaped slide rail 6 is arranged at one end, facing the clamping device, of the mounting disc 7, the moving part 16 is connected to the arc-shaped slide rail 6 in a sliding manner, the light source 9 is arranged on the moving part 16, the yawing motor assembly 8 is connected to the moving part 16, the pitching motor assembly 15 is used for driving the mounting disc 7 to swing in the pitching direction, and the yawing motor assembly 8 is used for driving the moving part 16 to slide in the yawing direction along the arc-shaped slide rail 6;
the controller controls the start, stop and running speed of the yaw motor assembly 8 to drive the moving part 16 to move along the arc-shaped sliding rail 6 so as to drive the light source 9 to move along the yaw direction, and controls the start, stop and running speed of the pitch motor 15 assembly so as to enable the mounting disc 7 to swing in the pitch direction, so as to drive the light source 9 to move along the pitch direction.
The light source double-shaft rotating assembly is used for simulating target motion in the yaw direction and the pitch direction, namely the motion trail of the light source 9, so as to test the capture and tracking capacity of the missile.
Both sides of the arc-shaped slide rail 6 are V-shaped guide surfaces, one end of the moving part 16 is provided with a pair of pulleys which are respectively clamped on the V-shaped guide surfaces on both sides, the other end of the moving part is a plate type, and the light source 9 and the yaw motor assembly 8 are connected to the plate type end of the moving part 16 through a motor bracket;
the bottom surface of arc slide rail 6 is equipped with the arc rack, and yaw motor subassembly 8 includes yaw motor and yaw motor gear, and yaw motor gear engagement connects in the arc rack, and the other end fixed connection in yaw motor gear that the output shaft of yaw motor passed the moving part 16, and the controller controls the yaw motor operation to make the yaw motor gear rotate along the arc rack, thereby provide thrust and slide along arc slide rail 6 with driving moving part 16.
The junction on the 9 motor supports of light source is equipped with along a plurality of fine setting holes of vertical top setting, and the 9 backs of light source are equipped with the installation notch, through connecting the installation notch in the position of the fine setting hole of difference in order to adjust light source 9.
The other end of the mounting disc 7, namely the bottom of the arc-shaped outer edge end of the mounting disc 7, is rotatably connected to a support frame 17 through a bearing;
the pitching motor 15 component comprises a pitching motor 15, a coupler and a connecting shaft, the connecting shaft is fixedly connected to the arc-shaped outer edge end of the mounting disc 7, the connecting shaft is coaxial with a bearing at the bottom of the mounting disc 7, the axis of the connecting shaft is arranged along the radial direction of the tested missile, the connecting shaft is connected with an output shaft of the pitching motor 15 through the coupler, and the controller controls the pitching motor 15 to operate, so that the connecting shaft rotates, the mounting disc 7 is driven to swing up and down by taking the joint with the supporting frame 17 as the axis, namely, the pitching direction movement is carried out, and the light source 9 is driven to move along the pitching direction.
And a limit switch is arranged on the support frame 17 and used for limiting the maximum pitching angle of the mounting disc 7, and the controller controls the pitching motor 15 to stop running according to a signal of the limit switch.
In the present embodiment, the moving angle range of the moving member 16 in the yaw direction is ± 35 °, and the moving angle range of the mounting plate 7 in the pitch direction is-10 ° to 55 °.
In this embodiment, the light source double-shaft rotating assembly further comprises an electric cabinet 12, wherein the electric cabinet 12 is arranged on the supporting table body 14, electrically connected with the light source double-shaft rotating assembly, and in communication connection with the controller, so as to receive a control instruction sent by the controller and control the light source double-shaft rotating assembly according to the control instruction.
The yaw motor assembly 8 and the pitching motor assembly 15 both comprise motor encoders, and the electric cabinet 12 comprises a box body, and a motor driver, a power supply and a signal adapter plate which are arranged in the box body; the box body is connected with the supporting platform body 14, the signal adapter plate receives an electric signal fed back by the motor encoder, and simultaneously receives an electric control signal of the controller, and controls the starting, stopping and moving speeds of the yaw motor and the pitching motor through the motor driver;
the electric cabinet 12 further comprises an emergency stop button 10, an operation indicator light 11 and an electric cabinet interface 13 which are arranged on the cabinet body, the tested guided missile is electrically connected with the electric cabinet interface 13 through a cable, the signal adapter plate receives test signal information of the tested guided missile and transmits the test signal information to the controller, and the emergency stop button 10 is used for controlling the motor driver to stop running.
The light source 9 moves at a preset speed in the yaw direction and the pitch direction according to preset position information, a target tracking device is arranged in the head of the tested missile and used for tracking a light source 9 signal, namely, the target capturing and tracking capacity of the tested missile is measured, a signal adapter plate transmits a received tracking signal to a controller, and the controller compares the tracking signal with the preset light source 9 position and speed, namely, a preset movement track:
when the tracking signal is matched with the preset light source 9 motion track, the tested missile is judged to be a qualified product, and when the tracking signal is not matched with the preset light source 9 track, the tested missile is judged to be an unqualified product.
In the present embodiment, two drawers 18 are provided on the side of the supporting table 14 for accommodating the clamping devices with different spring diameters and locked by a locking structure; lockable universal wheels 20 are arranged at four corners of the bottom of the supporting table body 14, so that the supporting table body is convenient to move and fixed when the test is not influenced, hanging rings 21 are arranged at four corners of the top of the supporting table body 14, and handles are arranged at two sides of the supporting table body, so that the supporting table body is convenient to move.
The utility model relates to a guided missile testing arrangement adopts the aluminum alloy to make.
According to the utility model discloses a method that guided missile testing arrangement carries out guided missile test as follows:
step 3, the controller controls the light source double-shaft rotating assembly to operate so that the light source 9 moves according to a preset speed and position, namely, moves along a preset track, and the controller compares a tracking signal fed back by the tested missile with a preset motion track signal and judges whether the tracking signal meets the requirement or not so as to test performance parameters of the missile, such as a search range, a search period, a target search speed and the like;
step 4, rotating the tested missile by 90 degrees along the annular slide rail 5 by using a handle of the front section supporting clamp 4, feeding the inertia information back to the controller by using an inertia measuring unit in the tested missile, comparing the inertia measuring signal of the tested missile with preset information by using the controller, and judging whether the polarity of the tested missile meets the requirement or not;
and 5, disconnecting each line after the test is finished, and processing the tested missile according to the comparison result of the controller.
And after the test is finished, placing the qualified missile product to be tested in a qualified product area, placing the unqualified missile product in an unqualified product area, and finishing the test.
When missiles with different missile diameters need to be tested, the rear section supporting clamp 1, the middle section supporting clamp 2 and the front section supporting clamp 4 are disassembled, the clamping devices corresponding to the missile diameters are taken out from the drawer 18 and are installed on the installation platform of the fine adjustment mechanism 19, and the steps are repeated to realize the test of the missiles.
While various embodiments of the present invention have been described above, the above description is intended to be illustrative, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (10)
1. The missile testing device is characterized by comprising a supporting table body (14), a light source (9), a clamping device, a light source double-shaft rotating assembly and a controller, wherein the clamping device is detachably arranged at one end of the supporting table body (14), the axial direction of the clamping device is arranged along the horizontal direction and is used for clamping a tested missile, the light source (9) is arranged at the other end of the supporting table body (14), the light source double-shaft rotating assembly is arranged on the supporting table body (14), and the controller controls the light source double-shaft rotating assembly to be switched on and switched off and controls the light source double-shaft rotating assembly to drive the light source (9) to move along the yaw direction and/or the pitch direction.
2. The missile testing device according to claim 1, wherein the clamping device comprises a rear section supporting clamp (1), a middle section supporting clamp (2) and a front section supporting clamp (4) which are coaxially arranged in parallel from the one end to the other end of the supporting platform body (14), and the rear section supporting clamp (1), the middle section supporting clamp (2) and the front section supporting clamp (4) are detachably connected with the supporting platform body (14) through a base.
3. Missile testing device according to claim 2, wherein the rear section support fixture (1) and the front section support fixture (4) are both circular ring structures formed by splicing two semicircular ring structures, each semicircular ring structure is hinged with one end of the other semicircular ring structure, the other end of each semicircular ring structure is locked by a lock catch, and the middle section support fixture (2) is a semicircular ring structure.
4. Missile testing device according to claim 3, wherein the inner wall of the front section support clamp (4) is provided with a rotatable annular slide rail (5), one side of the annular slide rail (5) is provided with a handle, and the annular slide rail (5) and the front section support clamp (4) are provided with alignment marks.
5. Missile testing device according to claim 4, characterized in that the inner walls of the ring-shaped slide rails (5) are provided with silica gel pads, and the inner walls of the rear section supporting clamp (1) and the middle section supporting clamp (2) are provided with rollers.
6. A missile testing device according to claim 3, further comprising three fine adjustment mechanisms (19), wherein each fine adjustment mechanism (19) comprises a mounting platform, a fine adjustment bracket, a hand wheel, a lead screw assembly and a meter, and the lead screw assembly and the meter are arranged in the fine adjustment bracket;
the fine adjustment support is arranged on the supporting table body (14), the mounting platform is connected to the top of the fine adjustment support in a sliding mode and is connected to the lead screw assembly, the hand wheel is arranged on the outer side of the fine adjustment support, the hand wheel is rotated to drive a lead screw of the lead screw assembly to rotate, a lead screw nut of the lead screw assembly drives the mounting platform to move linearly along the lead screw, and the instrument is used for displaying adjustment measurement of the lead screw assembly;
the rear section supporting clamp (1), the middle section supporting clamp (2) and the front section supporting clamp (4) are respectively arranged on one mounting platform of the fine adjustment mechanism.
7. Missile testing device according to claim 3, further comprising a plurality of laser positioning devices (3), wherein a plurality of laser positioning devices (3) are arranged on the supporting table body (14), and the laser emitted by each laser positioning device (3) is used for aligning with a reference point on the missile.
8. The missile testing device according to claim 3, wherein the light source double-shaft rotating assembly comprises an arc-shaped slide rail (6), a mounting plate (7), a yaw motor assembly (8), a pitching motor assembly (15), a moving part (16) and a supporting frame (17);
the supporting frame (17) is connected to the other end of the supporting table body (14), the mounting disc (7) and the pitching motor assembly (15) are connected to the top end of the supporting frame (17), the arc-shaped sliding rail (6) is arranged at one end, facing the clamping device, of the mounting disc (7), the moving part (16) is slidably connected to the arc-shaped sliding rail (6), the light source (9) is arranged on the moving part (16), the yawing motor assembly (8) is connected to the moving part (16), the pitching motor assembly (15) is used for driving the mounting disc (7) to swing in a pitching direction, and the yawing motor assembly (8) is used for driving the moving part (16) to slide in the yaw direction along the arc-shaped sliding rail (6);
the controller controls the starting, stopping and running speed of the yaw motor assembly (8) to drive the moving piece (16) to move along the arc-shaped sliding rail (6), so that the light source (9) is driven to move along the yaw direction, and the controller controls the starting, stopping and running speed of the pitch motor assembly (15) to enable the mounting disc (7) to swing along the pitch direction, so that the light source (9) is driven to move along the pitch direction.
9. Missile testing device according to claim 8, characterized in that the range of angles of movement of the moving part (16) in the yaw direction is ± 35 °, and the range of angles of movement of the mounting plate (7) in the pitch direction is-10 ° -55 °.
10. The missile testing device according to claim 1, further comprising an electric cabinet (12), wherein the electric cabinet (12) is arranged on the supporting table body (14), is electrically connected with the light source double-shaft rotating assembly, and is in communication connection with the controller so as to receive a control command sent by the controller and control the light source double-shaft rotating assembly according to the control command.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023182794.8U CN214470419U (en) | 2020-12-25 | 2020-12-25 | Missile testing device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023182794.8U CN214470419U (en) | 2020-12-25 | 2020-12-25 | Missile testing device |
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| CN214470419U true CN214470419U (en) | 2021-10-22 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112611272A (en) * | 2020-12-25 | 2021-04-06 | 中国航天空气动力技术研究院 | Missile testing device |
| CN112611272B (en) * | 2020-12-25 | 2024-07-09 | 中国航天空气动力技术研究院 | Missile testing device |
-
2020
- 2020-12-25 CN CN202023182794.8U patent/CN214470419U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112611272A (en) * | 2020-12-25 | 2021-04-06 | 中国航天空气动力技术研究院 | Missile testing device |
| CN112611272B (en) * | 2020-12-25 | 2024-07-09 | 中国航天空气动力技术研究院 | Missile testing device |
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