CN107084222B - A kind of aircraft gun buffer control method - Google Patents
A kind of aircraft gun buffer control method Download PDFInfo
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- CN107084222B CN107084222B CN201710339521.3A CN201710339521A CN107084222B CN 107084222 B CN107084222 B CN 107084222B CN 201710339521 A CN201710339521 A CN 201710339521A CN 107084222 B CN107084222 B CN 107084222B
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- aircraft gun
- recoil
- damper
- speed
- displacement
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F9/00—Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium
- F16F9/32—Details
- F16F9/53—Means for adjusting damping characteristics by varying fluid viscosity, e.g. electromagnetically
- F16F9/535—Magnetorheological [MR] fluid dampers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A25/00—Gun mountings permitting recoil or return to battery, e.g. gun cradles; Barrel buffers or brakes
Abstract
The invention discloses a kind of aircraft gun buffer control methods, comprising: obtains viscous damping coefficient c according to the MR damper for being set to aircraft gun back seat0The power bias term f generated with accumulator0, and rigidity k is obtained according to spring；The speed of aircraft gun barrel is calculated in the acceleration value according to detected by acceleration transducerAnd displacement x；Pass through preset recoil resultant force FB, viscous damping coefficient c0, accumulator generate power bias term f0, rigidity k, speedAnd displacement x, and according to formulaDamping force and current relationship item f is calculatedc；According to damping force and current relationship item fcBy tabling look-up to obtain the output current value corresponding to it, and output current value is applied to MR damper.The invention also discloses a kind of aircraft gun buffering control devices.The control to output size of current can be realized only by acceleration transducer in above-mentioned aircraft gun buffer control method, with the technical effect realizing recoil with significantly improving again into response speed when control.
Description
Technical field
The present invention relates to aircraft gun technical field, in particular to a kind of aircraft gun buffer control method.
Background technique
Aircraft gun buffering control device, mainly for aviation special equipment field, towards modern aircraft gun power big, lightweight,
The development need of mobility strong, Low Recoil Force.The big, rapid dynamic response speed, low in energy consumption using MR damper output resistance
Advantage solve the problems, such as aircraft gun transmitting when setback-impact and stability of vibration.
In the prior art, usually MR damper is mounted on barrel, is sensed according to recoil resistance, recoil velocity
Device feedback regulation recoil resultant force achievees the purpose that reduce recoil.However since force snesor installation site is harsh, velocity pick-up
The general volume of device is larger, is not suitable for aircraft gun recoil buffer unit.And aircraft gun requires running fire, needs to carry out barrel
It resets；In addition to this, there are also some scholars adjusts recoil according to recoil resistance, recoil velocity sensor inside loop and outside loop closed loop feedback
With joint efforts, achieve the purpose that reduce recoil.
Summary of the invention
The object of the present invention is to provide a kind of aircraft gun buffer control methods, and the aircraft gun buffer control method is only by acceleration
The control to output size of current can be realized in degree sensor, to realize that recoil and the multiple response speed into when control significantly improve
Technical effect.It is a further object of the present invention to provide a kind of aircraft gun buffering control devices.
To achieve the above object, the present invention provides a kind of aircraft gun buffer control method, comprising:
Viscous damping coefficient c is obtained according to the MR damper for being set to aircraft gun back seat0The power biasing generated with accumulator
Item f0, and rigidity k is obtained according to the spring for being sheathed on the MR damper surrounding；
Aircraft gun barrel is calculated according to acceleration value detected by the acceleration transducer for the guide rod for being set to aircraft gun
SpeedAnd displacement x；
Pass through preset recoil resultant force FB, the viscous damping coefficient c0, the power bias term f that generates of the accumulator0, institute
State rigidity k, the speedWith the displacement x, and according to formulaResistance is calculated
Buddhist nun's power and current relationship item fc；
Wherein,For sign symbol mark, recoil process is positive, and reseting procedure is negative；
According to the damping force and current relationship item fcBy tabling look-up to obtain the output current value corresponding to it, and will be described
Output current value is applied to MR damper.
Relative to above-mentioned background technique, aircraft gun buffer control method provided by the invention utilizes MR damper and bullet
Spring realizes the buffering to aircraft gun barrel jointly, avoids the recoil of aircraft gun barrel from being displaced excessive；At the same time, work as MR damper
After determining with the type of spring, viscous damping coefficient c could be aware that0, accumulator generate power bias term f0And rigidity k, and
The speed of aircraft gun barrel is calculated using acceleration value acquired in acceleration transducerAnd displacement x；For the recoil of barrel
Resultant force FB, can be preset based on practical experience, and according to formulaDamping is calculated
Power and current relationship item fc, for different MR damper types, damping force and current relationship item fcWith output current value thing
First statistics is table, namely damping force and current relationship item f is calculatedcLater you can learn that output current value, thus to magnetic
Rheological damper output achievees the purpose that reduce barrel recoil to control the damping force of MR damper.
Preferably, described according to the damping force and current relationship item fcBy tabling look-up to obtain the output electric current corresponding to it
Value, and after the step of output current value is applied to MR damper further include:
When describedWhen being negative and passing through preset time, preset reset recoil resultant force F is utilizedB 1, the energy storage
The power bias term f that device generates0, the rigidity k and the speed at current timeWith the displacement x at current time, and according to institute
State formulaDamping force and current relationship item f is calculatedc；
According to the damping force and current relationship item fcBy tabling look-up to obtain the output current value corresponding to it, and will be described
Output current value is applied to MR damper, remaining elastic potential energy is absorbed with for MR damper, to realize spring
It resets.
Preferably, the recoil resultant force FBAnd the reset recoil resultant force FB 1It is definite value.
Preferably, the acceleration value according to detected by the acceleration transducer for the guide rod for being set to aircraft gun is calculated
The speed of aircraft gun barrelAnd the step of displacement x, specifically includes:
The time is integrated according to the acceleration value to obtain the speedAccording to the speedIt is obtained with the time
The displacement x.
The present invention also provides a kind of aircraft gun buffering control devices, comprising:
Acceleration transducer: for detecting the acceleration value of aircraft gun barrel；
The signal conditioning unit being connected with the acceleration transducer: for aircraft gun to be calculated according to the acceleration value
The speed of barrelAnd displacement x；
The Operations Analysis being connected with the signal conditioning unit: for according to the magnetorheological damping for being set to aircraft gun back seat
The viscous damping coefficient c of device0The power bias term f generated with accumulator0, be sheathed on MR damper surrounding spring spring
Rigidity k, preset recoil resultant force FB, the speedWith the displacement x, and according to formula
Damping force and current relationship item f is calculatedc；Wherein,For sign symbol mark, recoil process is positive, and reseting procedure is
It is negative；And according to the damping force and current relationship item fcObtain the output current value corresponding to it；
Power output unit between the Operations Analysis and the MR damper: for according to
Output current value exports electric current to the MR damper.
Preferably, further includes:
Reset controller: for when describedWhen being negative and passing through preset time, preset reset recoil is utilized to close
Power FB 1, the power bias term f that generates of the accumulator0, the rigidity k and the speed at current timeWith current time
Displacement x, and according to the formulaDamping force and current relationship item f is calculatedc；
According to the damping force and current relationship item fcBy tabling look-up to obtain the output current value corresponding to it, and will be described
Output current value is applied to MR damper, remaining elastic potential energy is absorbed with for MR damper, to realize spring
It resets.
Preferably, further include the upper-level control system being connected with the Operations Analysis: being used for the viscous damping
Coefficient c0, the power bias term f that generates of the accumulator0, the rigidity k, the preset recoil resultant force FBAnd after resetting
Sit resultant force FB 1It exports to the Operations Analysis.
Preferably, there is communication unit between the Operations Analysis and the upper-level control system.
It preferably, further include to the communication unit, the Operations Analysis, the power output unit and institute
It states signal conditioning unit and the power supply unit of electric energy is provided.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 is a kind of flow chart of aircraft gun buffer control method provided by the embodiment of the present invention；
Fig. 2 is a kind of structural block diagram of aircraft gun buffering control device provided by the embodiment of the present invention；
Fig. 3 is the structure chart of barrel tail portion in a kind of aircraft gun buffering control device provided by the embodiment of the present invention；
Fig. 4 is the recoil and recoil displacement curve figure of aircraft gun.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
In order to make those skilled in the art more fully understand the present invention program, with reference to the accompanying drawing and it is embodied
The present invention is described in further detail for mode.
Fig. 1, Fig. 2, Fig. 3 and Fig. 4 are please referred to, Fig. 1 is a kind of aircraft gun buffer control method provided by the embodiment of the present invention
Flow chart；Fig. 2 is a kind of structural block diagram of aircraft gun buffering control device provided by the embodiment of the present invention；Fig. 3 is the present invention
The structure chart of barrel tail portion in a kind of aircraft gun buffering control device provided by embodiment；Fig. 4 is recoil and the recoil of aircraft gun
Displacement curve figure.
A kind of aircraft gun buffer control method provided by the invention, as shown in Figure of description 1, comprising:
S1, viscous damping coefficient c is obtained according to the MR damper for being set to aircraft gun back seat0The power generated with accumulator is inclined
Set a f0, and rigidity k is obtained according to the spring for being sheathed on the MR damper surrounding；
Aircraft gun barrel is calculated in S2, the acceleration value according to detected by the acceleration transducer for the guide rod for being set to aircraft gun
SpeedAnd displacement x；
S3, pass through preset recoil resultant force FB, the viscous damping coefficient c0, the power bias term f that generates of the accumulator0、
The rigidity k, the speedWith the displacement x, and according to formulaIt is calculated
Damping force and current relationship item fc；Wherein,For sign symbol mark, recoil process is positive, and reseting procedure is negative；
S4, according to the damping force and current relationship item fcBy tabling look-up to obtain the output current value corresponding to it, and will
The output current value is applied to MR damper.
First as shown in Figure of description 3, setting of the present invention by the way of the additional connecting tooling of MR damper 2
Mode is separately mounted to aircraft gun barrel two sides by two buffer units.Acceleration transducer 1 is mounted at the top of guide rod, sliding branch
Guide rod 4 is supportted to limit by caging bolt.Buffer unit includes MR damper 2 and steel spring 3；Namely it is magnetorheological by two
The mode of 3 parallel connection of damper 2 plus steel spring replaces the original buffer unit without recoil damping of aircraft gun system.When system recoil
With it is multiple into when, steel spring 3 provide recoil rigidity and it is multiple into power, wanted with meeting recoil displacement and the recoil size of system
It asks.The MR damper of MR damper 2 provides damping force according to damping force characteristic curve, and damping force size is by applying
Operating current control.And operating current can be controlled by the voltage variety of application, to reach required damping force
Characteristic curve.
And it is well known that aircraft gun single shot and burst-firing required precision aircraft gun recoil buffer unit must be smaller
Recoil stroke under meet recoil resistance minimum.And total work caused by recoil is used to offset the energy for shellbursting generation,
Meet following formula:
From attached drawing 4 as can be seen that when one timing of recoil displacement, FBWhen for constant, the peak value of recoil can achieve minimum,
Therefore it needs to guarantee that recoil resulting force curve is approximately constant by controlling variable damping force.
In step sl, it after MR damper 2 is similar with spring 3 to be determined, can be obtained by MR damper 2
Know the viscous damping coefficient c of MR damper 20The power bias term f generated with accumulator0, spring could be aware that by spring 3
Rigidity k；
In step s 2, the speed of aircraft gun barrel is calculated by acceleration value detected by acceleration transducer 1And displacement x；
In step s3, recoil resultant force with speed, displacement, electric current relational expression can are as follows:
In formula: fcFor damping force and current relationship item；c0For viscous damping coefficient；f0The power bias term generated for accumulator.
The displacement of x expression aircraft gun barrel.The speed for indicating aircraft gun barrel, when numerical value is that timing indicates recoil process, when numerical value is negative
Indicate multiple into process.For sign symbol mark, recoil process is positive, and reseting procedure is negative.It can be counted by above-mentioned formula
Calculation obtains damping force and current relationship item fc；
In step s 4, for different types of MR damper 2, damping force and current relationship item fcWith output electricity
It is corresponded between flow valuve, and table is made, there is the table in the prior art, therefore using look-up table you can learn that output electricity
Flow valuve, to control MR damper 2, to reduce the displacement of barrel recoil.
The above-mentioned barrel that gives is in the control mode in recoil stage, when the directional velocity of barrel changes namely barrel
When into reseting stage, it can be controlled in the following way.
When describedWhen being negative and passing through preset time, preset reset recoil resultant force F is utilizedB 1, the accumulator
The power bias term f of generation0, the rigidity k and the speed at current timeWith the displacement x at current time, and according to described
FormulaDamping force and current relationship item f is calculatedc；
According to the damping force and current relationship item fcBy tabling look-up to obtain the output current value corresponding to it, and will be described
Output current value is applied to MR damper, remaining elastic potential energy is absorbed with for MR damper, to realize spring
It resets.
That is, when the positive negative direction of the speed of barrel changes, and after preset time, surface barrel enters
Cannon enters reseting stage after reseting stage, i.e. steel spring reach maximum compressibility, utilizes the reset recoil resultant force F of settingB 1, storage
The power bias term f that energy device generates0, rigidity k and the speed at current timeWith the displacement x at current time, and according to above-mentioned
Updated damping force and current relationship item f is calculated in formulac；Wherein, recoil resultant force F is resettedB 1F as in formulaB,
I.e. updated FB, utilize updated damping force and current relationship item fcTable look-up to obtain to corresponding output current value, utilize
The elastic potential of spring achievees the effect that multiple into and controlling MR damper and consume extra elastic potential energy, maintain barrel vibration
Dynamic stability is unlikely to overshoot.
In above process, it can use acceleration transducer 1 and judge whether the positive negative direction of the speed of barrel changes,
Reset recoil resultant force F is utilized to triggerB 1Updated damping force and current relationship item f is calculatedc, and execute subsequent step
Suddenly.Certainly, as described above, recoil resultant force FBAnd reset recoil resultant force FB 1It is definite value, to reduce the recoil displacement of barrel.
For above-mentioned steps S2, calculated according to acceleration value detected by the acceleration transducer for the guide rod for being set to aircraft gun
Obtain the speed of aircraft gun barrelAnd the step of displacement x, specifically includes:
The time is integrated according to the acceleration value to obtain the speedAccording to the speedIt is obtained with the time
The displacement x.The above process can refer to the prior art, and the present invention will not be described in great detail.
The invention also discloses a kind of aircraft gun buffering control devices, as shown in Figure of description 2, comprising:
Acceleration transducer 1: for detecting the acceleration value of aircraft gun barrel；
The signal conditioning unit 600 being connected with the acceleration transducer 1: for being calculated according to the acceleration value
The speed of aircraft gun barrelAnd displacement x；
The Operations Analysis 400 being connected with the signal conditioning unit 600: for according to the magnetic current for being set to aircraft gun back seat
The viscous damping coefficient c of variable damping device 20The power bias term f generated with accumulator0, be sheathed on the spring of MR damper surrounding
3 rigidity k, preset recoil resultant force FB, the speedWith the displacement x, and according to formulaDamping force and current relationship item f is calculatedc；Wherein,For sign symbol mark,
Recoil process is positive, and reseting procedure is negative；And according to the damping force and current relationship item fcObtain the output electricity corresponding to it
Flow valuve；
Power output unit 500 between the Operations Analysis 400 and the MR damper 2: it is used for
Electric current is exported to the MR damper 2 according to the output current value.
Preferably, further includes:
Reset controller: for when describedWhen being negative and passing through preset time, preset reset recoil is utilized to close
Power FB 1, the power bias term f that generates of the accumulator0, the rigidity k and the speed at current timeWith current time
Displacement x, and according to the formulaDamping force and current relationship item f is calculatedc；
According to the damping force and current relationship item fcBy tabling look-up to obtain the output current value corresponding to it, and will be described
Output current value is applied to MR damper, remaining elastic potential energy is absorbed with for MR damper, to realize spring
It resets.
It preferably, further include the upper-level control system 100 being connected with the Operations Analysis 400: for that described will glue
Stagnant damped coefficient c0, the power bias term f that generates of the accumulator0, the rigidity k, the preset recoil resultant force FBAnd
Reset recoil resultant force FB 1It exports to the Operations Analysis.
Preferably, there is communication unit 200 between the Operations Analysis 400 and the upper-level control system 100.
It preferably, further include to the communication unit 200, the Operations Analysis 400, the power output list
Member 500 and the signal conditioning unit 600 provide the power supply unit 300 of electric energy.
It should be noted that in the present specification, such as first and second etc relational terms are used merely to one
Entity is distinguished with other several entities, and without necessarily requiring or implying between these entities, there are any this actual
Relationship or sequence.
Aircraft gun buffer control method provided by the present invention and device are described in detail above.It is used herein
A specific example illustrates the principle and implementation of the invention, and the above embodiments are only used to help understand originally
The method and its core concept of invention.It should be pointed out that for those skilled in the art, not departing from this hair
, can be with several improvements and modifications are made to the present invention under the premise of bright principle, these improvement and modification also fall into power of the present invention
In the protection scope that benefit requires.
Claims (4)
1. a kind of aircraft gun buffer control method characterized by comprising
Viscous damping coefficient c is obtained according to the MR damper for being set to aircraft gun back seat0The power bias term f generated with accumulator0,
And rigidity k is obtained according to the spring for being sheathed on the MR damper surrounding；
The speed of aircraft gun barrel is calculated according to acceleration value detected by the acceleration transducer for the guide rod for being set to aircraft gun
And displacement x；
Pass through preset recoil resultant force FB, the viscous damping coefficient c0, the power bias term f that generates of the accumulator0, the bullet
Spring rigidity k, the speedWith the displacement x, and according to formulaDamping force is calculated
With current relationship item fc；
Wherein,For sign symbol mark, recoil process is positive, and reseting procedure is negative；
According to the damping force and current relationship item fcBy tabling look-up to obtain the output current value corresponding to it, and by the output
Current value is applied to MR damper.
2. aircraft gun buffer control method according to claim 1, which is characterized in that described according to the damping force and electric current
Relational term fcBy tabling look-up to obtain the output current value corresponding to it, and the output current value is applied to MR damper
The step of after further include:
When describedWhen being negative and passing through preset time, preset reset recoil resultant force F is utilizedB 1, the accumulator generates
Power bias term f0, the rigidity k and the speed at current timeWith the displacement x at current time, and according to the formulaDamping force and current relationship item f is calculatedc；
According to the damping force and current relationship item fcBy tabling look-up to obtain the output current value corresponding to it, and by the output
Current value is applied to MR damper, remaining elastic potential energy is absorbed with for MR damper, to realize spring reset.
3. aircraft gun buffer control method according to claim 2, which is characterized in that the recoil resultant force FBAnd it is described multiple
Position recoil resultant force FB 1It is definite value.
4. aircraft gun buffer control method according to any one of claims 1 to 3, which is characterized in that the basis is set to
The speed of aircraft gun barrel is calculated in acceleration value detected by the acceleration transducer of the guide rod of aircraft gunWith the step of displacement x
Suddenly it specifically includes:
The time is integrated according to the acceleration value to obtain the speedAccording to the speedIt is obtained with the time described
Displacement x.
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| CN111102315B (en) * | 2018-10-25 | 2021-08-10 | 中车株洲电力机车研究所有限公司 | Control method of catapult recoil buffer device based on magnetorheological damper |
| CN114441130B (en) * | 2021-12-31 | 2023-11-10 | 中国航空工业集团公司北京长城计量测试技术研究所 | Multi-impact waveform generating device and method |
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| CN2147184Y (en) * | 1993-04-09 | 1993-11-24 | 国营庆安宇航设备公司 | Air cannon dumper |
| US6694856B1 (en) * | 2001-02-22 | 2004-02-24 | The University Of Maryland | Magnetorheological damper and energy dissipation method |
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