CN104483089B - Full free flight shrapnel dispersion separation test system - Google Patents
Full free flight shrapnel dispersion separation test system Download PDFInfo
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- CN104483089B CN104483089B CN201410770767.2A CN201410770767A CN104483089B CN 104483089 B CN104483089 B CN 104483089B CN 201410770767 A CN201410770767 A CN 201410770767A CN 104483089 B CN104483089 B CN 104483089B
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Abstract
The invention provides a kind of full free flight is shed separates wind tunnel test system, including emitter, retaining mechanism, unlocking mechanism, high-speed camera and multichannel precise synchronization controller, emitter is fixed in wind-tunnel support system, for the female bullet of upwind transmitting, retaining mechanism includes lock wire and spring, lock wire is diametrically cross inside excessively female bullet tightening bullet in the periphery of female bullet, spring is used for the power for applying the female bullet of disengaging to bullet, steel wire of the unlocking mechanism for front end buckle, before the part that one end of its buckle lies across in female bullet positioned at lock wire, its other end end is fixed on emitter, high-speed camera is arranged at outside wind-tunnel, multichannel precise synchronization controller is also disposed on outside wind-tunnel.The present invention is for studying bullet and shedding the dynamic flying movement locus of bullet in separation process and female bullet, Dynamic Separation aerodynamic characteristic from female bullet and its influence each other and disturb, and then the cast distribution analysis for shrapnel dispersion optimization design and bullet provides reference.
Description
Technical field
The present invention relates to a kind of full free flight is shed separates wind tunnel test system, female bullet free flight in wind-tunnel is applied to
During, bullet sheds detached pilot system and method from female bullet.
Background technology
Shrapnel is used for tackling complex target, as great depth, large-area Suppression Weapon, has widely been configured at big gun
On bullet, bomb, rocket projectile and guided missile, its species is various, of many uses, quickly grows, and becomes the heat that countries in the world are extremely paid close attention to
Point.Sub-munition separation aerodynamic characteristic, is one of key technology during shrapnel is developed, and the state of flight for separating moment mother's bullet (flies
Row Mach number, the angle of attack, yaw angle etc.), and the ejection velocity of bullet, arrangement and projectile mode etc., all to bullet group point minute
The shape of cloth, shed size and its uniformity coefficient and exist and affect, and and then affect shrapnel to injure the effect of target.Antithetical phrase
Female bullet separates aerodynamic characteristic and is studied, and realizes shrapnel under the state of flights different to the sub-munition separation moment and projectile state
The dynamic flying movement locus of separation process and dynamic dispersion characteristic are predicted, and can be shrapnel dispersion optimization design and bullet
Cast distribution analysis provide reference.Wind tunnel test is the main means of currently pneumatic research, more particularly, to shrapnel point
From dynamic process simulation, be that numerical simulation is irreplaceable using the authenticity and reliability of results of wind tunnel.In wind
Being completely in this test in the state of free flight after realizing female bullet and bullet before separation in hole and in separation process is
System, sub-munition separation process that can more really under tunnel simulation actual flight state and its influences each other and does
Disturb, preferably realize detached dynamic process simulation being played to multiple bullets from female in wind-tunnel, and realization is initial
The impact to projecting process such as parameter is cast, realizes studying sub-munition separation aerodynamic characteristic.
Content of the invention：
The technology of the present invention solve problem be：(female bullet and bullet are rear before separation and separate to provide a kind of full free flight
In the state of being completely in free flight in journey) shrapnel dispersion separation wind tunnel test system, to realize sub-munition separation gas
The research of dynamic characteristic, plays detached dynamic process simulation from female at the same time to polylith bullet, and uses high-speed camera pair
After whole separation process and separation, the flight path of bullet carries out shooting record, so as to realize the dynamic to shrapnel separation process
Sporting flying track and dynamic dispersion characteristic are predicted, and are that the cast distribution analysis of shrapnel dispersion optimization design and bullet is carried
For reference.
The full free flight shrapnel dispersion of the present invention separates wind tunnel test system includes emitter, retaining mechanism, unblock
Mechanism, high-speed camera and multichannel precise synchronization controller, the emitter are fixed in wind-tunnel support system, for inverse
The female bullet of wind direction transmitting, the retaining mechanism include that lock wire and spring, the lock wire are incited somebody to action diametrically cross inside excessively described female bullet
Bullet is tightened in the periphery of female bullet, and the spring is used for the power for applying disengaging female bullet to bullet, the unlocking mechanism
For the steel wire of front end buckle, before one end of its buckle lies across the part in female bullet positioned at the lock wire, its other end
It is fixed on the emitter, launches female bullet by triggering the emitter, the hook can be hooked on described
In lock wire, and the lock wire is pulled apart, the high-speed camera is arranged at outside wind-tunnel, for the observation window pair from wind-tunnel
The flight path of female bullet and the bullet carries out shooting record, and the multichannel precise synchronization controller is also disposed on wind-tunnel
Outside, for controlling the emitter and the high-speed camera simultaneously.
It is preferred that the bullet is two, the retaining mechanism is by the lock wire successively from a bullet bomb body
Hole, the hole in the middle of spring and female hole played on bomb body pass through, to the spring and another described bullet of opposite side
After hole on bomb body passes, the spring-compressed is locked to design point, so as to realize for the bullet being locked at institute
State on female bullet.
It is preferred that the bullet is multiple.
It is preferred that the multichannel precise synchronization controller is by controlling the emitter and the high-speed camera synchronization
Or delayed startup, can realize entering bullet after the time of releasing and separation and female flight path of the bullet in the range of wind tunnel window
Row shoots record.
It is preferred that the multichannel precise synchronization controller has 7 delay paths.The present invention having compared with prior art
Beneficial effect is：
1st, after the present invention realizes female bullet and bullet before separation in wind-tunnel and in separation process, free flight is completely in
Capable state, more can really realize sub-munition separation process under tunnel simulation actual flight state and its mutually
Affect and disturb, preferably realize that in wind-tunnel detached dynamic process is played to multiple bullets from mother is simulated.
2nd, the full free flight mode that the present invention is adopted so that before transmission in emitter, this will play female bullet
The female bullet of effect protection prevents bullet before unlocking mechanism startup i.e. by wind not by the startup load impacting during Flow Field in Wind Tunnel foundation
Hole starts load and blows away or cause retaining mechanism to loosen, so as to affect the simulation effect of separation process.Therefore at need not be as female bullet
In as the semi-free winged test under stationary state, needing to take the measure for preventing aerodynamic loading from impacting, this is this pilot system
Full free flight mode compared to semi-free winged test advantage.
Description of the drawings
Fig. 1 is the structural representation that wind tunnel test system is shed in full free flight.
Fig. 2 sheds for full free flight and separates unlocking mechanism schematic diagram.
Symbol description
1- bullets, 2- mother's bullets, 3- model emitters, 4- wind-tunnel support systems, 5- high-speed cameras, 6- multichannels are accurate
Synchronization Control instrument, 7- wind tunnel windows, 8- lock wires, 9- springs, 10- unblock silks
Specific embodiment
The present invention separates wind tunnel test system for a kind of full free flight shrapnel dispersion, sheds including full free flight and separates solution
Lock system, high-speed camera 5, multichannel precise synchronization controller 6.Core is shed for full free flight and separates system for unlocking,
Which includes：Bullet 1, lock wire 8, spring 9, unblock silk 10 and female bullet 2.
The present invention adopts full free flight mode, i.e., cause the rear and separation process before separation of female bullet 2 and bullet 1 in wind-tunnel
In be completely in the state of free flight such that it is able to more really realize under tunnel simulation actual flight state
Sub-munition separation process and its influence each other and disturb, preferably realize detached dynamic from female bullet 2 to multiple bullets 1 in wind-tunnel
State process simulation.
Before separation test, need first model emitter 3 is fixed in wind-tunnel support system 4, bullet 1 also needs thing
First it is locked on female bullet 2.Bullet 1 is locked by following manner：By the spring compression between bullet 1 and female bullet 2 to design point,
Passed through with the hole on the lock wire successively hole from 1 bomb body of bullet, 2 bomb body of the hole in the middle of spring 9 and female bullet, to opposite side
Hole on 1 bomb body of spring 9 and bullet is locked after passing, so as to realize the locking between bullet 1 and female bullet 2.As needed, can be
Arrange that some groups of bullets 1, its arrangement mode freely can be arranged in 2 whole body of female bullet.
Unblock is then realized by unblock silk 10.Unblock silk 10 is the steel wire of one end hook, and one end of its buckle is located at mother
Before the lock wire 8 of 2 body internal locking mechanism of bullet, tail end is then fixed on model emitter 3, treats multichannel precise synchronization control
After instrument processed 6 sends firing order, female bullet 2 accelerates to be emitted into flow field from model emitter 3, and retaining mechanism accelerates to a constant speed
Lock wire 8 is broken by impact release silk 10 when spending, the reaction force for being unlocked silk 10, so as to unlock retaining mechanism, due to son
It is the spring 9 of pre-pressing between bullet and female bullet, therefore in the case of retaining mechanism unblock, bullet is by 9 pretightning force of spring
Flown out from female bullet 2 under effect immediately, so as to realize shedding separation.Emitter 3 is fixed in wind-tunnel support system 4, is used for
Upwind transmitting mother bullet.Separation parameter between bullet 1 and female bullet 2 can be calculated by the design to 9 parameter of spring and change bullet
The position of 1 barycenter of relative bullet of spring 9 is realizing.Separation parameter generally comprises separating rate and angular speed, therefore by designing bullet
The parameters such as spring silk diameter d, mean diameter of coil D, number of coils n are designing spring rate K, and compression deformation of the spring amount △ X
Separating rate needed for obtaining bullet.Active position of the spring 9 relative to 1 barycenter of bullet, can make bullet 1 obtain corresponding angle
Speed.As 9 active position of spring is located at the front of 1 barycenter of bullet, then bullet 1 will obtain the angular speed for turning clockwise；As made
For the rear of 1 barycenter of bullet, then bullet 1 will obtain the angular speed of rotate counterclockwise；Such as act on 1 barycenter of bullet, then without
Angular speed, bullet 1 is flat to fly to separate with female bullet 2.
High-speed camera 5 is by shooting in the range of wind tunnel window, realizing to bullet 1 and female bullet 2 in observation window
In the range of flight course observation and record, therefore female 2 scale model size of bullet should ensure which completes it in separation process
Before can not fly out in the range of observation window, so that high-speed camera 5 can be realized shooting whole separation process and being recorded；With
When should ensure that the size of size and observation window of the contracting of bullet 1 than after is appropriate, bullet 1 is undersized will to be difficult to observe which and fly
State.Multichannel precise synchronization controller 6 and high-speed camera 5 are arranged at outside flow field.Multichannel precise synchronization controller 6
Model emitter 3 and observation window scope is carried out outside wind-tunnel that control simultaneously is arranged in the support system 4 in wind-tunnel
The high-speed camera 5 of shooting, makes the two synchronization or delayed startup, so as to realize to bullet 1 with 2 separation process of female bullet and separate after
The dynamic flight trajectories of bullet 1 and dynamic dispersion characteristic carry out shooting record.The instrument has 7 delay paths, it is possible to achieve 7
The time delay and holding of road different time, its delay time and retention time can be arbitrarily set between 0～100 second, can be accurate
Arrive millisecond.
Above the preferred embodiment of the present invention is illustrated, but the present invention is not limited to above-described embodiment.Right
For those skilled in the art, in the category described in claims, it should be apparent that it is conceivable that various modifications
Or fixed case, fall within certainly the technology category of the present invention.
Claims (5)
1. a kind of full free flight shrapnel dispersion separates wind tunnel test system, it is characterised in that：Including emitter, locking machine
Structure, unlocking mechanism, high-speed camera and multichannel precise synchronization controller, the emitter are fixed on wind-tunnel support system
On, for the female bullet of upwind transmitting, the retaining mechanism includes lock wire and spring, and the lock wire is diametrically cross excessively described mother
Bullet is tightened in the periphery of female bullet inside bullet, the spring is used for the power for applying disengaging female bullet to bullet, described
Steel wire of the unlocking mechanism for front end buckle, before one end of its buckle lies across the part in female bullet positioned at the lock wire,
Its other end is fixed on the emitter, launches female bullet by triggering the emitter, and the hook being capable of hook
Hang in the lock wire, and the lock wire is pulled apart, the high-speed camera is arranged at outside wind-tunnel, for from wind-tunnel
Observation window carries out shooting record to the flight path of female bullet and the bullet, and the multichannel precise synchronization controller also sets
It is placed in outside wind-tunnel, for controlling the emitter and the high-speed camera simultaneously.
2. full free flight shrapnel dispersion according to claim 1 separates wind tunnel test system, it is characterised in that：The son
Bullet is two, and the retaining mechanism is by lock wire hole successively from a bullet bomb body, the hole in the middle of spring
Pass through with the hole on female bullet bomb body, after the hole to the spring and another described bullet bomb body of opposite side passes,
The spring-compressed is locked to design point, so as to realize that the bullet is locked on female bullet.
3. full free flight shrapnel dispersion according to claim 1 separates wind tunnel test system, it is characterised in that：The son
Bullet is multiple.
4. full free flight shrapnel dispersion according to claim 1 separates wind tunnel test system, it is characterised in that：Described many
Passage precise synchronization controller can be realized by controlling the emitter and the high-speed camera synchronization or delayed startup
Shooting record is carried out to bullet after the time of releasing and separation and female flight path of the bullet in the range of wind tunnel window.
5. the full free flight shrapnel dispersion according to any one in Claims 1 to 4 separates wind tunnel test system, and which is special
Levy and be：The multichannel precise synchronization controller has 7 delay paths.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| CN104483089A CN104483089A (en) | 2015-04-01 |
| CN104483089B true CN104483089B (en) | 2017-03-15 |
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| CN201410770767.2A Active CN104483089B (en) | 2014-12-11 | 2014-12-11 | Full free flight shrapnel dispersion separation test system |
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| CN104949588B (en) * | 2015-07-10 | 2017-02-01 | 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 |
| CN107228750B (en) * | 2017-05-12 | 2019-05-24 | 中国航天空气动力技术研究院 | Free flight model control surface deflection device |
| CN107830772B (en) * | 2017-12-01 | 2023-06-23 | 西安工业大学 | Wind resistance type shell speed measuring device and application method thereof |
| CN108827593B (en) * | 2018-06-27 | 2020-03-13 | 北京理工大学 | Experimental device for high-speed liquid is shed |
| 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 |
| 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 |
| CN114061383B (en) * | 2021-10-29 | 2023-07-04 | 上海机电工程研究所 | Test simulation method and system for vibration separation under overload condition of primary and secondary bullets |
| CN114993598B (en) * | 2022-05-20 | 2023-07-21 | 中国科学院力学研究所 | Time calibration method and device for shock tunnel dynamic test |
| 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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| JPS60205230A (en) * | 1984-03-30 | 1985-10-16 | Mitsubishi Heavy Ind Ltd | Smoke diffusion testing method |
| EP0262617A1 (en) * | 1986-09-30 | 1988-04-06 | Industrias Cardoen Limitada | Cluster bomb |
| EP0559560A1 (en) * | 1992-03-06 | 1993-09-08 | AEROSPATIALE Société Nationale Industrielle | Structure for positioning and stabilizing an objekt in a threedimensional referencespace |
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| CN104483089A (en) | 2015-04-01 |
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