CN104483089A - Full free flight cluster bomb dispersion separation testing system - Google Patents
Full free flight cluster bomb dispersion separation testing system Download PDFInfo
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- CN104483089A CN104483089A CN201410770767.2A CN201410770767A CN104483089A CN 104483089 A CN104483089 A CN 104483089A CN 201410770767 A CN201410770767 A CN 201410770767A CN 104483089 A CN104483089 A CN 104483089A
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Abstract
The invention provides a full free flight cluster bomb dispersion separation wind tunnel testing system which comprises a launching device, a locking mechanism, an unlocking mechanism, a high-speed camera and a multi-channel precise synchronization controller, wherein the launching device is fixed on a wind tunnel support system and is used for launching a primary bomb opposite to the wind direction; the locking mechanism comprises a locking line and springs; the locking line transversely penetrates through the primary bomb in the radial direction so as to tightly tie secondary bombs at the periphery of the primary bomb; the springs are used for exerting force to the secondary bombs to be dissociated from the primary bomb; the unlocking mechanism is a steel wire with a hook at the front end; the end, where the hook is arranged, of the unlocking mechanism is positioned before the part, which is transversely arranged inside the primary bomb, of the locking line; the other end of the unlocking mechanism is fixed on the launching device; the high-speed camera is arranged outside a wind tunnel; the multi-channel precise synchronization controller is also arranged outside the wind tunnel. The full free flight cluster bomb dispersion separation wind tunnel testing system is used for studying the dynamic flight movement tracks, the dynamic separation pneumatic characteristics and the mutual influence and interference of the secondary bombs and the primary bomb in the process that the secondary bombs are dispersed and dissociated from the primary bomb, and furthermore reference is provided for cluster bomb dispersion optimization design and dispersion distribution analysis on bombs.
Description
Technical field
The present invention relates to a kind of full free flight and shed separation wind tunnel test system, be applied to female in wind-tunnel bullet in the process of free flight, 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 gordian technique 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 degree of uniformity 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.Female bullet and bullet this pilot system before separation afterwards and under the state being all in free flight in detachment process is realized in wind-tunnel, can comparatively real sub-munition separation process under tunnel simulation actual flight state and influence each other and disturb, good realization is simulated the dynamic process that multiple bullet is separated from female bullet in wind-tunnel, and the impact on projecting process such as the initial impelling parameter of the Study of the Realization, 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 full free flight (female bullet and bullet before separation after and be all in free flight in detachment process state under) shrapnel dispersion is separated wind tunnel test system, to realize the research of sub-munition separation aerodynamic characteristic, the dynamic process that polylith bullet is separated from female bullet is at the same time simulated, and use high-speed camera to carry out shooting record to whole detachment process with the flight path being separated rear bullet, thus realization is predicted the dynamic flying movement locus of shrapnel detachment process and dynamic dispersion characteristic, for the cast distribution analysis of shrapnel dispersion optimal design and bullet provides reference.
Full free flight shrapnel dispersion of the present invention is separated wind tunnel test system and comprises emitter, latch mechanism, release mechanism, high-speed camera and hyperchannel precise synchronization controller, described emitter is fixed in wind-tunnel support system, for the female bullet of upwind transmitting, described latch 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, described spring is used for the power applying to depart from described female bullet to bullet, described release mechanism is the steel wire of front end buckle, one end of its buckle is positioned at before described lock wire lies across the part of described female bullet, its other end is fixed on described emitter, described female bullet is launched by triggering described emitter, 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, shooting record is carried out for the flight path of view window to described female bullet and described bullet from wind-tunnel, described hyperchannel precise synchronization controller is also arranged at outside wind-tunnel, for controlling described emitter and described high-speed camera simultaneously.
Preferred described bullet is two, the hole that described latch mechanism is played on bomb body from the hole in the middle of the hole described bullet bomb body, spring and described mother successively by described lock wire is passed, after hole to the described spring and described bullet bomb body of opposite side passes, described spring-compressed is locked to design point, thus realizes described bullet to be locked on described female bullet.
Preferred described bullet is multiple.
Preferred described hyperchannel precise synchronization controller is by the described emitter of control and described high-speed camera is synchronous or delayed startup, can realize carrying out shooting record to bullet and the flight path of female bullet within the scope of wind tunnel window after the time of releasing and separation.
Preferred described hyperchannel precise synchronization controller has 7 delay path.The present invention's beneficial effect is compared with prior art:
1, the present invention realize in wind-tunnel female bullet and bullet before separation after and be all in the state of free flight in detachment process, the sub-munition separation process under tunnel simulation actual flight state can be realized comparatively really and influence each other and disturb, realizing preferably simulating the dynamic process that multiple bullet is separated from female bullet in wind-tunnel.
2, the full free flight mode of the present invention's employing; female bullet is in emitter before transmission; this will play the female bullet of available protecting not by the startup load impacting in Flow Field in Wind Tunnel process of establishing; prevent bullet from namely being blown away by starting load of wind tunnel before release mechanism starts or causing latch mechanism to loosen, thus affect the simulate effect of detachment process.Therefore fly test without the need to be under stationary state as female bullet semi-free the same, need the measure taking to prevent aerodynamic loading from impacting, this is that the full free flight mode of this pilot system is compared to the semi-free advantage flying test.
Accompanying drawing explanation
Fig. 1 is the structural representation that wind tunnel test system is shed in full free flight.
Fig. 2 is that separation release mechanism schematic diagram is shed in full free flight.
Symbol description
The female bullet of 1-bullet, 2-, 3-model emitter, 4-wind-tunnel support system, 5-high-speed camera, 6-hyperchannel precise synchronization controller, 7-wind tunnel window, 8-lock wire, 9-spring, 10-unlock silk
Embodiment
The present invention is that a kind of full free flight shrapnel dispersion is separated wind tunnel test system, comprises full free flight and sheds separation system for unlocking, high-speed camera 5, hyperchannel precise synchronization controller 6.Core is that separation system for unlocking is shed in full free flight, and it comprises: bullet 1, lock wire 8, spring 9, unblock silk 10 and female bullet 2.
The present invention adopts full free flight mode, namely the state of free flight is all in after making female bullet 2 and bullet 1 before separation in wind-tunnel and in detachment process, thus the sub-munition separation process that can realize comparatively really under tunnel simulation actual flight state and influence each other and disturb, realize preferably simulating the dynamic process that multiple bullet 1 is separated from female bullet 2 in wind-tunnel.
Before separation test, need first to be fixed in wind-tunnel support system 4 by model emitter 3, bullet 1 also needs to be locked in advance on female bullet 2.By following manner locking bullet 1: by the spring compression between bullet 1 and female bullet 2 to design point, pass from the hole in the middle of the hole bullet 1 bomb body, spring 9 and the hole on female bullet 2 bomb body successively by lock wire, hole to the spring 9 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.
Unlock and then realized by unblock silk 10.Unlock the steel wire that silk 10 is one end hooks, before one end of its buckle is positioned at the lock wire 8 of female bullet 2 body internal locking mechanism, tail end is then fixed on model emitter 3, after hyperchannel precise synchronization controller 6 sends firing order, female bullet 2 accelerates to launch influent stream field from model emitter 3, impact release silk 10 when latch mechanism accelerates to certain speed, lock wire 8 is broken by the reacting force being unlocked silk 10, thus latch mechanism is unlocked, owing between bullet and female bullet being the spring 9 of pre-pressing, therefore when latch mechanism unlocks, bullet flies out from female bullet 2 immediately by under the effect of spring 9 pretightning force, thus realize shedding separation.Emitter 3 is fixed in wind-tunnel support system 4, for the female bullet of upwind transmitting.Separation parameter between bullet 1 with female bullet 2 is by realizing with the position changing spring 9 relative bullet 1 barycenter the designing and calculating of spring 9 parameter.Separation parameter generally comprises velocity of separation and angular velocity, 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 Δ X makes the velocity of separation needed for bullet acquisition.Spring 9, relative to the active position of bullet 1 barycenter, can make bullet 1 obtain corresponding angular velocity.As spring 9 active position is positioned at the front of bullet 1 barycenter, then bullet 1 will obtain the angular velocity turned clockwise; As acted on the rear of bullet 1 barycenter, then bullet 1 will obtain the angular velocity be rotated counterclockwise; As acted on bullet 1 barycenter, then without angular velocity, flat the flying of bullet 1 is separated with female bullet 2.
High-speed camera 5 is by taking within the scope of wind tunnel window, realize observation and the record of the flight course within the scope of view window to bullet 1 and female bullet 2, therefore female bullet 2 scale model size should ensure that it can not fly out within the scope of view window before detachment process completes, so that high-speed camera 5 can realize taking and record whole detachment process; Should ensure that the size of the size after bullet 1 contracting ratio and view window is suitable, bullet 1 undersized being difficult to observes its state of flight simultaneously.Hyperchannel precise synchronization controller 6 and high-speed camera 5 are all arranged on outside flow field.Hyperchannel precise synchronization controller 6 controls to be arranged on the model emitter 3 in the support system 4 in wind-tunnel simultaneously and is in the outer high-speed camera 5 taken view window scope of wind-tunnel, make the two synchronous or delayed startup, thus realize to bullet 1 and the detachment 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 (5)
1. a full free flight shrapnel dispersion is separated wind tunnel test system, it is characterized in that: comprise emitter, latch mechanism, release mechanism, high-speed camera and hyperchannel precise synchronization controller, described emitter is fixed in wind-tunnel support system, for the female bullet of upwind transmitting, described latch 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, described spring is used for the power applying to depart from described female bullet to bullet, described release mechanism is the steel wire of front end buckle, one end of its buckle is positioned at before described lock wire lies across the part of described female bullet, its other end is fixed on described emitter, described female bullet is launched by triggering described emitter, 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, shooting record is carried out for the flight path of view window to described female bullet and described bullet from wind-tunnel, described hyperchannel precise synchronization controller is also arranged at outside wind-tunnel, for controlling described emitter and described high-speed camera simultaneously.
2. full free flight shrapnel dispersion according to claim 1 is separated wind tunnel test system, it is characterized in that: described bullet is two, the hole that described latch mechanism is played on bomb body from the hole in the middle of the hole described bullet bomb body, spring and described mother successively by described lock wire is passed, after hole to the described spring and described bullet bomb body of opposite side passes, described spring-compressed is locked to design point, thus realizes described bullet to be locked on described female bullet.
3. full free flight shrapnel dispersion according to claim 1 is separated wind tunnel test system, it is characterized in that: described bullet is multiple.
4. full free flight shrapnel dispersion according to claim 1 is separated wind tunnel test system, it is characterized in that: described hyperchannel precise synchronization controller is by the described emitter of control and described high-speed camera is synchronous or delayed startup, can realize carrying out shooting record to bullet and the flight path of female bullet within the scope of wind tunnel window after the time of releasing and separation.
5. be separated wind tunnel test system according to the full free flight shrapnel dispersion in Claims 1 to 4 described in any one, it is characterized in that: described hyperchannel precise synchronization controller has 7 delay path.
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| CN201410770767.2A CN104483089B (en) | 2014-12-11 | 2014-12-11 | Full free flight shrapnel dispersion separation test system |
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| CN201410770767.2A CN104483089B (en) | 2014-12-11 | 2014-12-11 | Full free flight shrapnel dispersion separation test system |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN105550467A (en) * | 2016-01-12 | 2016-05-04 | 南京航空航天大学 | Building method of wall surface flowing model of high-speed wind tunnel inclined hole wall |
| CN107228750A (en) * | 2017-05-12 | 2017-10-03 | 中国航天空气动力技术研究院 | Free flight model control surface deflection device |
| CN107830772A (en) * | 2017-12-01 | 2018-03-23 | 西安工业大学 | One kind plus wind resistance formula shell speed measuring device and its application method |
| 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 |
| CN111272027A (en) * | 2020-01-23 | 2020-06-12 | 西安现代控制技术研究所 | On-missile dynamics data test system |
| CN114061383A (en) * | 2021-10-29 | 2022-02-18 | 上海机电工程研究所 | Test simulation method and system for vibration separation of shrapnel under overload condition |
| 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 |
| CN117073964A (en) * | 2023-10-16 | 2023-11-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel model free flight test mass block scattering device and scattering method |
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Cited By (15)
| 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 |
| CN105550467B (en) * | 2016-01-12 | 2018-11-09 | 南京航空航天大学 | The method for building up of high-speed wind tunnel inclined hole wall wall surface flow model |
| CN105550467A (en) * | 2016-01-12 | 2016-05-04 | 南京航空航天大学 | Building method of wall surface flowing model of high-speed wind tunnel inclined hole wall |
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| 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 |
| CN111272027A (en) * | 2020-01-23 | 2020-06-12 | 西安现代控制技术研究所 | On-missile dynamics data test system |
| CN111272027B (en) * | 2020-01-23 | 2022-07-05 | 西安现代控制技术研究所 | Dynamic data test system on bullet |
| CN114061383A (en) * | 2021-10-29 | 2022-02-18 | 上海机电工程研究所 | Test simulation method and system for vibration separation of shrapnel under overload condition |
| 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 |
| CN117073964A (en) * | 2023-10-16 | 2023-11-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel model free flight test mass block scattering device and scattering method |
| CN117073964B (en) * | 2023-10-16 | 2023-12-15 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel model free flight test mass block scattering device and scattering method |
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