CN215006383U - Automatic tracking device for flying attitude of rocket - Google Patents
Automatic tracking device for flying attitude of rocket Download PDFInfo
- Publication number
- CN215006383U CN215006383U CN202121419000.7U CN202121419000U CN215006383U CN 215006383 U CN215006383 U CN 215006383U CN 202121419000 U CN202121419000 U CN 202121419000U CN 215006383 U CN215006383 U CN 215006383U
- Authority
- CN
- China
- Prior art keywords
- video recorder
- speed video
- speed
- driving mechanism
- servo motor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a bullet arrow flight gesture automatic tracking device, wherein, a bullet arrow flight gesture automatic tracking device, include: the high-speed video recorder comprises a high-speed video recorder, a driving mechanism, a control module and a fixed bracket; the bottom of the high-speed video recorder is connected with the driving mechanism for driving the high-speed video recorder to rotate; the control module is respectively connected with the high-speed video recorder and the driving mechanism through lines, and the high-speed video recorder and the driving mechanism are installed on the fixed support. To solve the problems. The method and the device solve the problems that in the prior art, when the flying postures of the projectile are tested, the testing cost is high, the experimental arrangement is complicated and strict by adopting a relay tracking mode of a plurality of high-speed video recorders, and when the nutation target is used for testing, the early preparation and the testing process are complicated.
Description
Technical Field
The utility model relates to a bullet arrow test field, a bullet arrow flight gesture automatic tracking device specifically says so.
Background
In the bullet arrow test project, the flight attitude of a bullet arrow is a very important research project, and the bullet arrow test project can directly reflect the flight stability of the bullet arrow after shooting and directly influence the range, precision and density of the bullet arrow. The currently adopted high-speed video test method is limited to a certain fixed point and limited by the visual field range of the high-speed video, and a plurality of high-speed video recorders perform relay tracking, so that the implementation cost is high, and the test arrangement is redundant and strict. The nutation target testing method has the disadvantages of more early preparation, complex testing process and incapability of real-time continuous measurement. The test methods have certain limitations on the research and development of products, and the test results are not intuitive.
Disclosure of Invention
In view of this, the utility model provides a bullet arrow flight gesture automatic tracking device to when solving in the past to bullet arrow flight gesture and testing, adopt a plurality of high-speed video cassette recorders relay tracking mode to carry out the test with high costs, the experiment is arranged loaded down with trivial details strictly, and when adopting nutation target test, prepare in earlier stage and the complicated problem of experimentation.
The utility model provides a bullet arrow flight gesture automatic tracking device, include: the high-speed video recorder comprises a high-speed video recorder, a driving mechanism, a control module and a fixed bracket;
the bottom of the high-speed video recorder is connected with the driving mechanism for driving the high-speed video recorder to rotate;
the control module is respectively connected with the high-speed video recorder and the driving mechanism through a circuit, and is used for controlling the starting or the closing of the high-speed video recorder and controlling the starting, the closing, the rotating speed and the rotating angle of the driving mechanism;
the high-speed video recorder and the driving mechanism are arranged on the fixed support.
Preferably, the drive mechanism comprises: a servo motor and a reducer;
the servo motor is connected with the speed reducer, and the speed reducer is connected with the high-speed video recorder;
the servo motor is connected with the control module through a line and is used for driving the high-speed video recorder to rotate through the speed reducer.
Preferably, the control module comprises: a servo controller, a delayer and a trigger switch;
the servo controller is respectively connected with the servo motor and the high-speed video recorder through a circuit and is used for controlling the rotating speed and the rotating angle of the servo motor and starting or closing the servo motor;
the line between the servo controller and the high-speed video recorder is connected with the delayer, and the delayer is used for setting the delayed start of the high-speed video recorder;
and the trigger switch is connected on a circuit between the servo controller and the high-speed video recorder and is used for controlling the high-speed video recorder and the servo controller to be started or closed.
Preferably, the fixed support is a tripod.
Preferably, the method further comprises the following steps: a tray;
the tray is arranged between the driving mechanism and the high-speed video recorder, and the bottom of the tray is connected with the driving mechanism.
The utility model discloses following beneficial effect has:
the utility model provides a bullet arrow flight gesture automatic tracking device has solved in the past when testing bullet arrow flight gesture, adopts the test that carries out testing of a plurality of high-speed video cassette recorders relay tracking mode with high costs, experimental arrangement loaded down with trivial details strict to and when adopting nutation target test, prepare in earlier stage and the problem that the experimentation is complicated.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent from the following description of the embodiments of the present invention with reference to the accompanying drawings, in which:
fig. 1 is a schematic structural diagram of an automatic tracking device for flying postures of rocket in the embodiment of the present invention.
Fig. 2 is a circuit diagram of the servo controller, the delay device, the trigger switch and the high speed video recorder according to an embodiment of the present invention.
In the figure, 1-servo motor, 2-reducer, 3-tripod, 4-tray, 5-high speed video recorder, 6-servo controller, 7-time delay device, 8-trigger switch.
Detailed Description
The present invention will be described below based on examples, but it should be noted that the present invention is not limited to these examples. In the following detailed description of the present invention, certain specific details are set forth in detail. However, for parts not described in detail, those skilled in the art can fully understand the present invention.
Furthermore, those skilled in the art will appreciate that the drawings are provided for purposes of illustrating the objects, features, and advantages of the invention and are not necessarily drawn to scale.
Also, unless the context clearly requires otherwise, throughout the description and the claims, the words "comprise", "comprising", and the like are to be construed in an inclusive sense as opposed to an exclusive or exhaustive sense; that is, the meaning of "includes but is not limited to".
Fig. 1 is a schematic structural diagram of an automatic tracking device for flying postures of rocket in the embodiment of the present invention. Fig. 2 is a circuit diagram of the servo controller, the delay device, the trigger switch and the high speed video recorder according to an embodiment of the present invention. As shown in fig. 1 and 2, an automatic tracking device for a flying attitude of a rocket comprises: the high-speed video recorder comprises a high-speed video recorder 5, a driving mechanism, a control module and a fixed bracket; the bottom of the high-speed video recorder 5 is connected with a driving mechanism for driving the high-speed video recorder 5 to rotate; the control module is respectively connected with the high-speed video recorder 5 and the driving mechanism through a circuit, and is used for controlling the starting or the closing of the high-speed video recorder 5 and controlling the starting, the closing, the rotating speed and the rotating angle of the driving mechanism; the high-speed video recorder 5 and the driving mechanism are mounted on the fixed bracket.
The embodiment of the utility model provides an in, when the test, control module control high speed video recorder 5 and actuating mechanism start, start the video recording after high speed video recorder 5 starts, set up rotational speed and corner when actuating mechanism drives high speed video recorder 5 rotation through control module according to the flying speed of bullet arrow and the distance that needs the tracking in advance, control module control actuating mechanism starts and moves according to predetermined rotational speed and corner, actuating mechanism drives high speed video recorder 5 and uses the bottom to connect the position and rotate as axle horizontal direction, thereby its camera of high speed video recorder 5 follows bullet arrow flight direction when rotating and rotates the flight image of noting the bullet arrow. The high-speed video recorder 5 is connected with the display terminal, and testers can analyze the flying postures of the rocket according to the images recorded by the high-speed video recorder 5.
In the present invention and fig. 1, the driving mechanism includes: a servo motor 1 and a reducer 2; the servo motor 1 is connected with the speed reducer 2, and the speed reducer 2 is connected with the high-speed video recorder 5; the servo motor 1 is connected with the control module through a line, and the servo motor 1 is used for driving the high-speed video recorder 5 to rotate through the speed reducer 2.
In the embodiment of the present invention, one end of the speed reducer 2 is connected to the bottom of the high speed video recorder 5, and the other end is connected to the servo motor 1. When carrying out the bullet arrow flight test, control module control servo motor 1 starts, and servo motor 1 drives the drive mechanism rotation in the reduction gear 2, and drive mechanism connects high-speed video recorder 5 to drive high-speed video recorder 5 horizontal rotation, high-speed video recorder 5 is followed the bullet arrow flight direction and is shot when rotating. The control module controls the servo motor 1 to drive the speed reducer 2 to rotate, start or stop, so that the moving speed and the rotating angle of the high-speed video recorder 5 during shooting are adjusted.
In the present invention, fig. 1 and 2, the control module includes: a servo controller 6, a delayer 7 and a trigger switch 8; the servo controller 6 is respectively connected with the servo motor 1 and the high-speed video recorder 5 through circuits, and the servo controller 6 is used for controlling the rotating speed and the rotating angle of the servo motor 1 and starting or closing the servo motor; a delay 7 is connected on a line between the servo controller 6 and the high-speed video recorder 5, and the delay 7 is used for setting the delayed start of the high-speed video recorder 5; a trigger switch 8 is connected on a line between the servo controller 6 and the high-speed video recorder 5, and the trigger switch 8 is used for controlling the start or stop of the high-speed video recorder 5 and the servo controller 6.
In the embodiment of the present invention, the servo controller 6 is connected to the servo motor 1 through a circuit, and the servo controller 6 presets the rotating speed and the rotating angle of the servo motor 1 according to the shooting requirement of the high speed video recorder 5. The servo controller 6 is connected with the high-speed video recorder 5 through a parallel circuit, the servo controller 6 is used for providing a power supply for the high-speed video recorder 5, a trigger switch 8 is installed on the parallel circuit between the servo controller 6 and the high-speed video recorder 5, the trigger switch 8 is an on-off switch and used for enabling a circuit parallel circuit between the servo controller 6 and the high-speed video recorder 5 to be connected or disconnected, and the on-off switch is connected with a trigger of a cannon. A time delay 7 is connected between the on-off switch and the high-speed video recorder 5.
When testing, the trigger of bullet arrow starts, because of the trigger connects on-off switch, tears on-off switch interconnecting link when the trigger starts, will send step signal when on-off switch breaks off, transmits simultaneously for high-speed video recorder 5 and servo controller 6 to control high-speed video recorder 5 and servo controller 6 and start. Because the delayer 7 is arranged between the high-speed video recorder 5 and the on-off switch, a signal sent by the on-off switch is delayed by the delayer 7 and then transmitted to the high-speed video recorder 5, and the high-speed video recorder 5 starts to record after the delay.
The effect of the delayer 7 is that, when transmitting, in order to ensure the synchronism of transmission and test, the trigger switch 8 and the trigger of the artillery are started simultaneously, the high-speed video recorder 5 and the servo controller 6 are also started simultaneously according to the signal sent by the trigger switch 8, the high-speed video recorder 5 starts shooting instantly, but the launched rocket still moves in the artillery barrel, the high-speed video recorder 5 shoots useless pictures, when analyzing the flying posture of the rocket, the useless pictures can increase the analysis time, and the time for storing and transmitting the videos in the high-speed video recorder 5 can be occupied. The time delay 7 is arranged between the trigger switch 8 and the high-speed video recorder 5, so that the starting time of the high-speed video recorder 5 is delayed, shooting is started after the shooting arrow moves out of the chamber, and useless pictures are prevented from being shot by the high-speed video recorder 5. The specific delay time of the delayer 7 is calculated according to the length, the caliber, the launching speed and the like of the gun body tube of the rocket gun through the knowledge of the ammunition in the gun and the actual launching requirement.
In the present invention and fig. 1, the fixing bracket is a tripod 3.
In the embodiment of the present invention, the tripod 3 is used to support the speed reducer 2, the servo motor 1, and the high-speed video recorder 5. The outside lateral wall of reduction gear 2 is connected with the fixing base at 3 tops of tripod, when using, opens the three-leg pipe brace of tripod 3 and arranges subaerial support high-speed video recorder 5 in, and after the use, tripod 3 also conveniently removes and deposits.
The utility model discloses and in fig. 1, still include: a tray 4; a tray 4 is provided between the driving mechanism and the high-speed video recorder 5, and the bottom of the tray 4 is connected with the driving mechanism.
In the embodiment of the present invention, the bottom of the tray 4 is connected to the top of the speed reducer 2, and the tray 4 is used for holding the high-speed video recorder 5. When the servo motor 1 drives the speed reducer 2 to rotate, the tray 4 rotates together with the speed reducer 2 and the high-speed video recorder 5.
The embodiment of the utility model provides an in, before the test, set up servo motor 1's rotational speed and corner in servo controller 6 according to the parameter and the requirement of transmission bullet arrow, set up the delay time of delayer 7, erect the tripod 3 of fixing reduction gear 2, servo motor 1 and high-speed video recorder 5 in the shooting position, the shooting direction is aimed at to high-speed video recorder 5 camera lens. During testing, a trigger is started to launch the rocket, the trigger switch 8 sends out signals to control the servo controller 6 to start at the same time, and the servo controller 6 controls the servo motor 1 to start and drives the high-speed video recorder 5 to rotate through the speed reducer 2; the signal sent by the trigger switch 8 is delayed by the delayer 7 and then transmitted to the high-speed video recorder 5, and the high-speed video recorder 5 is controlled to start recording. The high-speed video recorder 5 is driven by the speed reducer 2 to horizontally rotate according to a preset rotating speed and a preset rotating angle, shooting the flying rocket attitude in the rotating process, transmitting the shot picture to the display terminal, and analyzing the flying rocket attitude by the user according to the shot picture.
The utility model discloses an only use a high-speed video recording equipment, connect servo motor 1, reduction gear 2 and servo controller 6, drive high-speed video recorder 5 and rotate, can accurately trail the flight gesture in the certain distance behind the test bullet arrow straight angle shooting, test method is simple, the flexible operation. The servo motor 1 and the speed reducer 2 can greatly improve the response speed of the system, and can ensure the synchronism of rocket tracking. Before the test, different rotating speeds and rotating angles are set, so that the rocket and the tracking distance at different speeds can be measured. The high-speed video recorder 5 starts to shoot pictures more accurately by arranging the delayer 7. The utility model discloses under the prerequisite that does not influence original high-speed video recording test performance and result, extended test method, solved the difficult problem of dynamic test, fine satisfying test operation requirement. Reasonable in design, use reliably, test result are directly perceived, have filled the blank of single high-speed video recorder 5 tracking test bullet arrow flight gesture, simple structure, novelty, convenient operation and practicality are strong. The utility model discloses pass through experimental verification, the result shows, the utility model discloses the test result is reliable, can reflect the flight gesture of bullet arrow faithfully, and the test result is directly perceived, provides valuable experimental data for the product scientific research stage. The utility model discloses a servo motor 1 model LCMT-18L02-110M06030 be the corner type, also can change into upright type according to actual conditions, and the power and the torque of motor also can change according to actual test condition, and the big effect of power and torque is better, carries out reasonable matching according to actual test condition and can reach the optimal test effect.
The above embodiments are merely embodiments for expressing the invention, and the description thereof is more specific and detailed, but not to be construed as limiting the scope of the invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several changes, substitutions, modifications, etc. can be made without departing from the spirit of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.
Claims (5)
1. The utility model provides a bullet arrow flight attitude automatic tracking device which characterized in that includes: the high-speed video recorder comprises a high-speed video recorder (5), a driving mechanism, a control module and a fixed bracket;
the bottom of the high-speed video recorder (5) is connected with the driving mechanism for driving the high-speed video recorder (5) to rotate;
the control module is respectively connected with the high-speed video recorder (5) and the driving mechanism through a circuit, and is used for controlling the starting or the closing of the high-speed video recorder (5) and controlling the starting, the closing, the rotating speed and the rotating angle of the driving mechanism;
the high-speed video recorder (5) and the driving mechanism are arranged on the fixed support.
2. The automatic projectile attitude tracking device of claim 1, wherein said drive mechanism comprises: a servo motor (1) and a speed reducer (2);
the servo motor (1) is connected with the speed reducer (2), and the speed reducer (2) is connected with the high-speed video recorder (5);
the servo motor (1) is connected with the control module through a line, and the servo motor (1) is used for driving the high-speed video recorder (5) to rotate through the speed reducer (2).
3. The apparatus according to claim 2, wherein the control module comprises: a servo controller (6), a delayer (7) and a trigger switch (8);
the servo controller (6) is respectively connected with the servo motor (1) and the high-speed video recorder (5) through a circuit, and the servo controller (6) is used for controlling the rotating speed and the rotating angle of the servo motor (1) and starting or closing the servo motor;
the delayer (7) is connected on a line between the servo controller (6) and the high-speed video recorder (5), and the delayer (7) is used for setting the delayed start of the high-speed video recorder (5);
the trigger switch (8) is connected to a line between the servo controller (6) and the high-speed video recorder (5), and the trigger switch (8) is used for controlling the high-speed video recorder (5) and the servo controller (6) to be started or closed.
4. The automatic projectile attitude tracking device according to claim 1, wherein said fixed support is a tripod (3).
5. The automatic missile and rocket flight attitude tracking device according to any one of claims 1 to 4, further comprising: a tray (4);
the tray (4) is arranged between the driving mechanism and the high-speed video recorder (5), and the bottom of the tray (4) is connected with the driving mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121419000.7U CN215006383U (en) | 2021-06-22 | 2021-06-22 | Automatic tracking device for flying attitude of rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121419000.7U CN215006383U (en) | 2021-06-22 | 2021-06-22 | Automatic tracking device for flying attitude of rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215006383U true CN215006383U (en) | 2021-12-03 |
Family
ID=79082881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121419000.7U Active CN215006383U (en) | 2021-06-22 | 2021-06-22 | Automatic tracking device for flying attitude of rocket |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215006383U (en) |
-
2021
- 2021-06-22 CN CN202121419000.7U patent/CN215006383U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111521370B (en) | Specific phase bit flow field testing device and method suitable for pulse wind tunnel rotation model | |
| US7694973B1 (en) | System, apparatus, and method for rapidly displacing an object | |
| CN109506875B (en) | Experimental system for coupling loading of non-explosive underwater explosion shock waves and high-speed fragments | |
| US3422808A (en) | Pneumatic accelerating device with frangible diaphragm release means | |
| CN215006383U (en) | Automatic tracking device for flying attitude of rocket | |
| CN106297524A (en) | A kind of rocket launching analog device and method of work thereof | |
| CN210603808U (en) | High overload experimental device based on reverse ballistic impact loading | |
| CN112698580A (en) | Semi-physical simulation system and method suitable for infrared accurate guidance bomb | |
| CN113375501B (en) | Rocket launching training system and method | |
| CN108644030A (en) | A kind of device and measurement method measuring hypergolic propellant liquid phase firing delay | |
| KR101330213B1 (en) | Device for assembling and testing portable guided missile | |
| CN114754637B (en) | Generalized attitude control ground test system | |
| JP2012007876A (en) | Electronic programming system for detonating fuse | |
| CN111521366A (en) | Flow display device applied to trailing vortex of control surface of supersonic rotary aircraft | |
| CN215676668U (en) | Spring-hinge-driven sliding-port-passing ejection holder | |
| CN109334981A (en) | A kind of unmanned plane equipped with fire extinguishing bullet launching device | |
| CN113686202B (en) | Tripod head spring passing mechanism based on spring hinge driving sliding port | |
| CN112954182A (en) | Device and method for synchronously shooting and recording explosion crushing by using high-speed camera | |
| CN213363560U (en) | Novel fire engine locking force detection device | |
| CN107600449A (en) | A kind of unmanned aerial vehicle ejecting device | |
| CN110986665B (en) | Method for detecting motion rule of projectile in hearth | |
| CN114132506A (en) | Target capture device and method of airborne anti-unmanned aerial vehicle | |
| CN212567110U (en) | Novel gun barrel structure of launching device | |
| CN113347351A (en) | Scenic spot along-the-way shooting method | |
| CN208031688U (en) | Extinguishing device and unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |