CN104390529A - Half-free flight shrapnel dispersion separation wind tunnel testing system - Google Patents
Half-free flight shrapnel dispersion separation wind tunnel testing system Download PDFInfo
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Abstract
The invention provides a half-free flight shrapnel dispersion separation wind tunnel testing system which comprises a wind tunnel supporting mechanism, a locking mechanism, an unlocking mechanism, a high-speed camera and a multichannel precision synchronization control instrument, wherein the wind tunnel supporting mechanism is used for supporting a parent shell in a wind tunnel flow field windward; the locking mechanism comprises a locking wire and a spring; the locking wire radially passes across the inner part of the parent shell to bind a bomb on the outer periphery of the parent shell; the compressed spring is arranged between the bound parent shell and bomb; the unlocking mechanism comprises an unlocking wire, a cylinder and a piston; a hook is arranged at one end of the unlocking wire, and is positioned in front of the part, transversely arranged in the parent shell, of the locking wire; the other end of the unlocking wire is fixed on the piston; the high-speed camera is arranged outside the experiment flow field of a wind tunnel; the multichannel precision synchronization control instrument is also arranged outside the flow field. The half-free flight shrapnel dispersion separation wind tunnel testing system is used for researching a dynamic flying motion trail and dynamic separation aerodynamic characteristics in the process that the bomb is dispersed and separated from the parent shell so as to provide reference for dispersion optimization design of a shrapnel and dispersion distribution analysis of the bomb.
Description
Technical field
The present invention relates to and semi-freely fly shrapnel dispersion wind tunnel test system, be applied to and femalely in wind-tunnel play fixed support, and bullet sheds pilot system and the method for separation from female bullet.
Background technology
Shrapnel is used for tackling complex target, and as great depth, large-area Suppression Weapon, be configured at widely on shell, bomb, rocket projectile and guided missile, it is of a great variety, of many uses, and development rapidly, becomes the focus that countries in the world are extremely paid close attention to.Sub-munition separation aerodynamic characteristic, it is one of key technology in shrapnel development, be separated the state of flight (flight Mach number, the angle of attack, yaw angle etc.) of moment female bullet, and the ejection velocity of bullet, arrangement and impelling mode etc., all on the shape of bullet group's point distribution, shed size and uniformity coefficient thereof and there is impact, and and then affect the effect that target injured by shrapnel.Shrapnel separation gas dynamic characteristic is studied, realize to the dynamic flying movement locus of sub-munition separation process under sub-munition separation moment different state of flight and impelling state and dynamically dispersion characteristic predict, reference can be provided for the cast distribution analysis of shrapnel dispersion optimal design and bullet.Wind tunnel test is the main means of current pneumatic research, especially relates to the simulation of the dynamic process of sub-munition separation, adopts the authenticity of results of wind tunnel and reliability to be that numerical simulation is irreplaceable.Shrapnel dispersion separation is generally multiple bullet and is separated simultaneously, and the CTS technology for separating of aerodynamics problem research thus based on permanent pneumatic concept is more difficult to application.Combine the wind tunnel test of fixed support and this pilot system of wind tunnel model free flight test two kinds of test features, then can simulate by the dynamic process realized preferably multiple bullet is separated from female bullet, and the impact on projecting process such as the initial impelling parameter of the Study of the Realization and state of flight, realize studying shrapnel separation gas dynamic characteristic.
Summary of the invention
The problem that the technology of the present invention solves is: provide a kind of semi-free (female bullet is fixed on wind-tunnel knife rest) shrapnel that flies freely to shed separation wind tunnel test system, to realize the research of sub-munition separation aerodynamic characteristic, the dynamic process that multiple bullet is separated from female bullet is simultaneously simulated, and use high-speed camera to carry out shooting record to whole separation process with the flight path being separated rear bullet, thus the research that realization affects projecting process initial impelling parameter and state of flight, and to the dynamic flying movement locus of sub-munition separation process under sub-munition separation moment different state of flight and impelling state and dynamically dispersion characteristic predict, for the cast distribution analysis of shrapnel dispersion optimal design and bullet provides reference.
Of the present invention semi-free fly shrapnel freely shed be separated wind tunnel test system comprise wind-tunnel supporting mechanism, retaining mechanism, release mechanism, high-speed camera and multichannel precise synchronization controller, described wind-tunnel supporting mechanism is used for female bullet to be supported in the flow field of wind-tunnel to ground windward, described retaining mechanism comprises lock wire and spring, it is inner by the periphery of bullet tighten at described female bullet that described lock wire radial direction passes across described female bullet, be provided with by the described spring compressed between described female bullet of tighten and bullet, described release mechanism comprises unblock silk, cylinder and piston, described unblock silk front end is with hook, this hook is positioned at before described lock wire lies across the part of described female bullet, its other end is fixed on described piston, by described cylinder and described piston mating reaction, described unblock silk is pulled rearward dynamic, described hook can be hooked in described lock wire, and described lock wire is pulled apart, described high-speed camera is arranged at outside wind-tunnel, for the observation window from wind-tunnel, shooting record is carried out to the flight path of described bullet, described multichannel precise synchronization controller is also arranged at outside wind-tunnel, for controlling described cylinder and described high-speed camera simultaneously.
Preferred described spring is arranged at the barycenter place of described bullet, or before or after the barycenter being arranged at described bullet.
Preferred described wind-tunnel supporting mechanism is connected with wind-tunnel knife rest, can be changed the state of described female bullet by wind-tunnel knife rest.
Preferred described lock wire adopts molybdenum filament made.
Preferred described multichannel precise synchronization controller is by the described cylinder of control and described high-speed camera is synchronous or delayed startup, can realize carrying out shooting record to the flight path of described bullet within the scope of wind tunnel window after the time of releasing and separation.
Preferred described multichannel precise synchronization controller has 7 delay path.
The present invention's beneficial effect is compared with prior art:
1, present invention incorporates the wind tunnel test under fixed support and model free flight test two kinds of wind tunnel test modes, also namely adopt and semi-freely fly mode, be fixedly supported on by female bullet on wind-tunnel knife rest, bullet realizes under being then in free free flight state being separated with shedding of female bullet.The mode of the female bullet of fixed support can be accurately given or change the parameters such as the angle of attack of the female bullet of the time of releasing, yaw angle and rotary speed, is in investigate female bullet the impact that different flight state is separated shrapnel dispersion; When female bullet is fixing, moulded dimension contracting than desirable comparatively large (also namely contracting than after desirable larger of moulded dimension), thus can realize the separation test of shedding of smaller szie bullet; The mode that female bullet is fixed also can observe separation is shed in female change (as windward side, lee face, incoming flow M number size etc.) playing Flow Field or flow field parameter impact on bullet more comprehensively.This full free flight test being female bullet is also in free flight is comparatively difficult to accomplish, is also the comparatively outstanding feature of of this pilot system.
2, by the pretightning force of spring in change separating mechanism and the active position of relative bullet, and the arrangement mode of bullet, different ejection velocities, arrangement mode and impelling mode (size and Orientation of angular speed) can be realized, thus realize investigating and different shed separation parameter to bullet in the impact being separated moment and the dynamic flying movement locus after being separated and dynamic dispersion characteristic from female bullet.
Accompanying drawing explanation
Fig. 1 semi-freely flies shrapnel dispersion wind tunnel test system schematic diagram.
Fig. 2 is separated system for unlocking schematic diagram for shedding.
Detailed description of the invention
The present invention is set forth further below in conjunction with accompanying drawing.
The present invention freely sheds separation wind tunnel test system for a kind of semi-free shrapnel that flies, and comprises test model and sheds separation system for unlocking, high-speed camera 4, multichannel precise synchronization controller 5.Core is that separation system for unlocking is shed in examination, comprising: bullet 1, lock wire 7, spring 8, unblock silk 9, female bullet 2, wind-tunnel support system 3, cylinder 10, piston 11.
The present invention adopts and semi-freely flies mode, female bullet 2 is fixedly mounted in wind-tunnel support system 3, can be accurately given or change the parameters such as the angle of attack of the female bullet 2 of the time of releasing, yaw angle and rotary speed by the attitude controlling wind-tunnel knife rest, be in realize investigating female bullet 2 different flight state to shed separation impact on shrapnel 2.
Before separation test, need first bullet 1 to be locked on female bullet 2.By following manner locking bullet 1.Spring 8 between bullet 1 and female bullet 2 is compacted to design point, pass from the hole in the middle of the hole bullet 1 bomb body, spring 8 and the hole on female bullet 2 bomb body successively by lock wire 7, hole to the spring 8 and bullet 1 bomb body of opposite side passes rear locking, thus realizes the locking between bullet 1 and female bullet 2.As required, can arrange some groups of bullets 1 on female bullet 2 whole body, its arrangement mode can freely arrange.
Release mechanism is then realized by cylinder 10 system and unblock silk 9.After sending unlock command by multichannel precise synchronization controller 5, piston 11 in cylinder 10 starts accelerated motion to the right, thus drive the also accelerated motion to the right of unblock silk 9, when unlocking silk 9 accelerated motion to lock wire 7 place, the hook unlocked on silk 9 will hook lock wire 7, and lock wire 7 is broken by speed instantaneously that utilize it larger, thus retaining mechanism is unlocked.Lock wire 7 adopts thinner molybdenum filament, and its intensity can ensure both tighten bullets 1 just, is easy to again be pulled off under the effect of impulsive force.Owing between bullet 1 and female bullet 2 being the spring 8 of pre-pressing, therefore when retaining mechanism unlocks, bullet 1 flies out from female bullet 2 immediately by under the effect of spring 8 pretightning force, thus realizes shedding separation.Many group bullets 1 are locked to the situation on female bullet 2, because bullet 1 is equally distributed in same cross section circumference often, therefore many lines are also positioned at same cross section, and cross-shaped, therefore unlock silk 9 lock wire 7 to be broken simultaneously, realize many group bullets 1 and unlock simultaneously.
Separation parameter between bullet 1 with female bullet 2 is by realizing with the position changing spring 8 relative bullet 1 barycenter the designing and calculating of spring 8 parameter.Separation parameter generally comprises separating rate and angular speed, therefore design spring rate K by the parameter such as design wire diameter d, mean diameter of coil D, number of coils n, and compression deformation of the spring amount △ X makes bullet 1 obtain required separating rate.Spring 8, relative to the active position of bullet 1 barycenter, can make bullet 1 obtain corresponding angular speed.As spring 8 active position is positioned at the front of bullet 1 barycenter, then bullet 1 will obtain the angular speed turned clockwise; As acted on the rear of bullet 1 barycenter, then bullet 1 will obtain the angular speed be rotated counterclockwise; As acted on bullet 1 barycenter, then without angular speed, flat the flying of bullet 1 is separated with female bullet 2.
High-speed camera 4 is by taking in wind tunnel window 6 scope, realize to whole experimentation observation and record, therefore female bullet 2 scale model size should ensure that it is all in observation window 6, so that high-speed camera 4 can realize shooting to female bullet 2 Flow Field and record, and the impact of separation is shed in the change (as windward side, lee face, incoming flow M number size etc.) observing female bullet 2 Flow Field or flow field parameter on bullet 1; Should ensure that the size of the size after bullet 1 contracting ratio and observation window 6 is suitable simultaneously, bullet 1 undersized being difficult to observes its state of flight, and just leave observation window after should ensureing to still have certain flying distance after bullet 1 flies away from female bullet 2, to record the dynamic flight trajectories being separated rear bullet 1 and to observe.
Multichannel precise synchronization controller 5 controls to be arranged on shedding in wind-tunnel support system 3 simultaneously and is separated the cylinder 10 in system for unlocking and is in the outer high-speed camera 4 taken observation window 6 scope of wind-tunnel, make the two synchronous or delayed startup, thus realize to bullet 1 and the separation process of female bullet 2 and be separated rear bullet 1 dynamic flight trajectories and dynamically dispersion characteristic carry out shooting record.This instrument has 7 delay path, and can realize time delay and the maintenance of 7 road different times, its delay time and retention time all arbitrarily can set between 0 ~ 100 second, can be accurate to millisecond.
Above the preferred embodiment of the present invention is illustrated, but the present invention is not limited to above-described embodiment.To one skilled in the art, in the category described in claims, various modification or fixed case can be expected apparently, certainly also belong to technology category of the present invention.
Claims (6)
1. separation wind tunnel test system freely shed by the semi-free shrapnel that flies, it is characterized in that: comprise wind-tunnel supporting mechanism, retaining mechanism, release mechanism, high-speed camera and multichannel precise synchronization controller, described wind-tunnel supporting mechanism is used for female bullet to be supported in the flow field of wind-tunnel to ground windward, described retaining mechanism comprises lock wire and spring, it is inner by the periphery of bullet tighten at described female bullet that described lock wire radial direction passes across described female bullet, be provided with by the described spring compressed between described female bullet of tighten and bullet, described release mechanism comprises unblock silk, cylinder and piston, described unblock silk one end is with hook, this hook is positioned at before described lock wire lies across the part of described female bullet, its other end is fixed on described piston, by described cylinder and described piston mating reaction, described unblock silk is pulled rearward dynamic, described hook can be hooked in described lock wire, and described lock wire is pulled apart, described high-speed camera is arranged at outside wind-tunnel, for the observation window from wind-tunnel, shooting record is carried out to the flight path of described bullet, described multichannel precise synchronization controller is also arranged at outside wind-tunnel, for controlling described cylinder and described high-speed camera simultaneously.
2. the semi-free shrapnel dispersion that flies according to claim 1 is separated wind tunnel test system, it is characterized in that: described spring is arranged at the barycenter place of described bullet, or before or after the barycenter being arranged at described bullet.
3. the semi-free shrapnel dispersion that flies according to claim 1 is separated wind tunnel test system, it is characterized in that: described wind-tunnel supporting mechanism is connected with wind-tunnel knife rest, can be changed the state of described female bullet by wind-tunnel knife rest.
4. the semi-free shrapnel dispersion that flies according to claim 1 is separated wind tunnel test system, it is characterized in that: described lock wire adopts molybdenum filament made.
5. the semi-free shrapnel dispersion that flies according to claim 1 is separated wind tunnel test system, it is characterized in that: described multichannel precise synchronization controller is by the described cylinder of control and described high-speed camera is synchronous or delayed startup, can realize carrying out shooting record to the flight path of described bullet within the scope of wind tunnel window after the time of releasing and separation.
6. the semi-free shrapnel dispersion that flies according to any one of Claims 1 to 5 is separated wind tunnel test system, it is characterized in that: described multichannel precise synchronization controller has 7 delay path.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104949588A (en) * | 2015-07-10 | 2015-09-30 | 中国航天空气动力技术研究院 | Shell and dispenser separating and dispensing mechanism |
| CN105444982A (en) * | 2015-11-24 | 2016-03-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Monocular video measurement method for external store separating locus wind tunnel test |
| CN107782526A (en) * | 2017-11-07 | 2018-03-09 | 中国航天空气动力技术研究院 | Barycenter is located at separation free flight flow tunnel testing device between the parallel level at interface |
| CN108680330A (en) * | 2018-08-06 | 2018-10-19 | 中国航天空气动力技术研究院 | The full free flight wind tunnel experimental rig of drive parallel connection stage separation |
| CN108827593A (en) * | 2018-06-27 | 2018-11-16 | 北京理工大学 | A kind of experimental provision that high-speed liquid is shed |
| CN109372886A (en) * | 2018-11-06 | 2019-02-22 | 中国航天空气动力技术研究院 | A kind of hinged fixed structure of rotary shaft model and rotating shaft support method |
| CN111175063A (en) * | 2020-01-07 | 2020-05-19 | 湖北三江航天红峰控制有限公司 | Throwing test device |
| CN111289212A (en) * | 2020-04-01 | 2020-06-16 | 中国空气动力研究与发展中心超高速空气动力研究所 | Dynamic separation device applied to model interstage dynamic separation wind tunnel test |
| CN113551563A (en) * | 2021-08-11 | 2021-10-26 | 天津恒匠数字装备有限公司 | Repeated scattering device |
| CN114018099A (en) * | 2021-11-15 | 2022-02-08 | 重庆零壹空间航天科技有限公司 | Device is shed to shrapnel |
| CN114964693A (en) * | 2022-05-20 | 2022-08-30 | 中国科学院力学研究所 | Shock tunnel simulation test device and method based on high-speed pneumatic ejection technology |
| CN114993598A (en) * | 2022-05-20 | 2022-09-02 | 中国科学院力学研究所 | Time calibration method and device for shock tunnel dynamic test |
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Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104949588A (en) * | 2015-07-10 | 2015-09-30 | 中国航天空气动力技术研究院 | Shell and dispenser separating and dispensing mechanism |
| CN105444982A (en) * | 2015-11-24 | 2016-03-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Monocular video measurement method for external store separating locus wind tunnel test |
| CN105444982B (en) * | 2015-11-24 | 2017-12-19 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of monocular video measuring method of Halo vest track wind tunnel test |
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| CN107782526B (en) * | 2017-11-07 | 2019-05-24 | 中国航天空气动力技术研究院 | Mass center is located at separation free flight flow tunnel testing device between the parallel level at interface |
| CN108827593A (en) * | 2018-06-27 | 2018-11-16 | 北京理工大学 | A kind of experimental provision that high-speed liquid is shed |
| CN108827593B (en) * | 2018-06-27 | 2020-03-13 | 北京理工大学 | Experimental device for high-speed liquid is shed |
| CN108680330A (en) * | 2018-08-06 | 2018-10-19 | 中国航天空气动力技术研究院 | The full free flight wind tunnel experimental rig of drive parallel connection stage separation |
| CN108680330B (en) * | 2018-08-06 | 2020-05-12 | 中国航天空气动力技术研究院 | Full-free flight wind tunnel test device with power parallel interstage separation and method |
| CN109372886B (en) * | 2018-11-06 | 2020-12-18 | 中国航天空气动力技术研究院 | Rotating shaft type model hinging and fixing structure and rotating shaft supporting method |
| CN109372886A (en) * | 2018-11-06 | 2019-02-22 | 中国航天空气动力技术研究院 | A kind of hinged fixed structure of rotary shaft model and rotating shaft support method |
| CN111175063A (en) * | 2020-01-07 | 2020-05-19 | 湖北三江航天红峰控制有限公司 | Throwing test device |
| CN111175063B (en) * | 2020-01-07 | 2021-07-23 | 湖北三江航天红峰控制有限公司 | Throwing test device |
| CN111289212A (en) * | 2020-04-01 | 2020-06-16 | 中国空气动力研究与发展中心超高速空气动力研究所 | Dynamic separation device applied to model interstage dynamic separation wind tunnel test |
| CN111289212B (en) * | 2020-04-01 | 2024-03-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Dynamic separation device applied to model interstage dynamic separation wind tunnel test |
| CN113551563A (en) * | 2021-08-11 | 2021-10-26 | 天津恒匠数字装备有限公司 | Repeated scattering device |
| CN113551563B (en) * | 2021-08-11 | 2023-02-17 | 天津恒匠数字装备有限公司 | Repeated scattering device |
| CN114018099A (en) * | 2021-11-15 | 2022-02-08 | 重庆零壹空间航天科技有限公司 | Device is shed to shrapnel |
| CN114018099B (en) * | 2021-11-15 | 2023-04-11 | 重庆零壹空间航天科技有限公司 | Device is shed to shrapnel |
| CN114964693A (en) * | 2022-05-20 | 2022-08-30 | 中国科学院力学研究所 | Shock tunnel simulation test device and method based on high-speed pneumatic ejection technology |
| CN114993598A (en) * | 2022-05-20 | 2022-09-02 | 中国科学院力学研究所 | Time calibration method and device for shock tunnel dynamic test |
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