CN207365823U - A kind of Free Modal pilot system under guided missile autorotation - Google Patents
A kind of Free Modal pilot system under guided missile autorotation Download PDFInfo
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Abstract
It the utility model is related to the Free Modal pilot system under a kind of guided missile autorotation, including suspension arrangement, exciting bank, equipment data acquisition analyzing, it is characterized in also setting up guided missile rotating driving device and rotary actuator, suspension arrangement includes hanger bracket, and hanger bracket is made of mounting bracket, anchor ear bearing and elastic threads；Guided missile rotating driving device includes variable-frequency motor and the frequency converter of 5Hz 20Hz；Rotary actuator includes transmission shaft, the universal connection variable-frequency motor shaft in transmission shaft one end, the clamping element of the universal connection guided missile test exemplar tail end of the other end；Equipment data acquisition analyzing includes acceleration transducer, force snesor, charge amplifier, data logger, wireless signal transmitter, wireless base station and terminal, acceleration transducer is arranged on guided missile test exemplar, pass through wireless signal transmitter wireless connection wireless base station, force snesor connects data logger by charge amplifier, and wireless base station is connected to terminal with data logger.
Description
Technical field
It the utility model is related to the free module under a kind of missile modality test system, more particularly to a kind of guided missile autorotation
State pilot system.
Background technology
Rotary missile due to cost is low, response quickly, beneficial to miniaturization and suitable dress property it is good the features such as, in guided weapon field
With huge development potentiality and application prospect.In order to improve rapidity, reduce flight resistance, rotary missile is commonly designed larger
Slenderness ratio, therefore the rigidity of structure is relatively low；At the same time as the raising of maneuverability requirement, missile flight overload are increasing.Big
Under the conditions of the angle of attack, body can produce serious elastic deformation.Exemplified by drawing nurse guided missile by the U.S., more than 20, maximum flies its slenderness ratio
Row overload more than 45g, longitudinal side are notable to elastic vibration.
Longitudinal side is that high mobile missile master-plan and Control System Design must take into consideration to elastic vibration, particularly with rotation
Transduction bullet, modal parameter of the body under rotation status will change, while suffered aerodynamic loading is also with speed cycle
Change, causes elastic movement to produce serious cross-couplings with rotary motion and acts on.One side cross-couplings reduce the dynamic of body
State stability, may cause occur the dynamic instability caused by elastic deformation in missile flight；On the other hand, power is coupled
The measurement output that response seriously affects control feedback transducer is learned, is caused according to the control system designed in the case of non-rotating in reality
Border, which in-flight controls, does not restrain, causes flight to fail.In order to solve rotary missile elastic vibration to master-plan and Guidance and control
The influence that system design is brought, the accurate modal parameter of guided missile in rotating condition that obtains is highly important.
At present, general Free Modal pilot system is (with reference to GJB 2706A-2008《Spacecraft Modal Experimental Method》) main
To include suspension arrangement, exciting bank, equipment data acquisition analyzing, the suspension arrangement for the tested guided missile of suspension mounting bracket and
Flexible strand, exciting bank are hammered into shape for power, and equipment data acquisition analyzing includes acceleration transducer, the force snesor on power hammer and data
Record and analyze device；Acceleration transducer is arranged on guided missile test exemplar, and is longitudinally uniformly arranged along guided missile test exemplar, will
Tested guided missile test exemplar is horizontally suspended on mounting bracket, and percussion excitation, acceleration are carried out to guided missile test exemplar using power hammer
The signal input data of sensor and force snesor records and analyzes device, you can obtains the modal parameter of guided missile, including mode frequency
Rate, modal damping and Mode Shape.
But existing Free Modal pilot system can not be fitted only for the Modal Parameter Identification of guided missile product under inactive state
For the situation under rotation status.Therefore Free Modal pilot system of the guided missile under autorotation how is developed, be obtained from
Turn changing rule of the missile modality parameter under state with rotating speed, become industry concerned issue.
Utility model content
The main purpose of the utility model is that in view of the above-mentioned problems, being improved in prior art basis, there is provided one
Kind is simple in structure, the Free Modal pilot system under the low and easily operated guided missile autorotation of assembling maintenance cost, realization pair
The modal parameter of guided missile test exemplar with the changing rule of rotating speed test.
Technical solution is used by the utility model solves its technical problem：
A kind of Free Modal pilot system under guided missile autorotation, including suspension arrangement, exciting bank, data acquisition point
Analysis apparatus, it is characterised in that be also provided with guided missile rotating driving device and be connected to the guided missile rotating driving device and guided missile examination
Test the rotary actuator between exemplar tail end；The suspension arrangement includes at least two groups of hanger brackets, the hanger bracket mainly by
The anchor ear bearing of guided missile test exemplar and the bullet of the fixed anchor ear bearing of mounting bracket, support level set free rotation state
Property rope form；The frequency range that the guided missile rotating driving device includes variable-frequency motor and its connection is the frequency conversion of 5Hz-20Hz
Device；The rotary actuator includes a transmission shaft, the universal connection variable-frequency motor shaft of transmission shaft its one end, the other end ten thousand
It is fixedly clamped to connection in the clamping element of the guided missile test exemplar tail end；The equipment data acquisition analyzing is passed including acceleration
Force snesor, charge amplifier, data logger, wireless signal transmitter, wireless base station and progress on sensor, exciting bank
Data analysis is arranged on guided missile test exemplar with the terminal calculated, the acceleration transducer, acceleration transducer
Pass through wireless base station described in the wireless signal transmitter wireless connection that is correspondingly arranged on guided missile test exemplar, exciting bank
On force snesor data logger is connected by the charge amplifier, wireless base station and data logger are connected to computer
Terminal.
The exciting bank is hammered into shape for power.
The anchor ear bearing includes bearing and inner ring anchor ear and outer shroud anchor ear with its clearance fit, the inner ring anchor ear by
Two interior semicircle garter springs bound round on the outside of guided missile test exemplar and the interior ring fastener for being clamped and being connected as a single entity are formed；It is described
Outer shroud anchor ear is by two outer semicircle garter springs of the hoop on the outside of the bearing and is clamped the outer ring fastener being connected as a single entity and forms；
In the anchor ear bearing both ends of the surface, anti-channeling baffle is set.
The mounting bracket is by two vertical side frames, connection horizontal upper frame therebetween, and opposite with the horizontal upper frame is set
The supporting substrate put on the ground is formed, the bullet that four sides are respectively fixedly connected up and down that the anchor ear bearing passes through its outer shroud anchor ear
Property rope tense and tie up on the horizontal upper frame, supporting substrate and two vertical side frames, horizontal hanging set.
Along its longitudinally disposed multiple kidney slot on the two vertical side frame.
The clamping element is a tubular end cap for being sleeved on guided missile test exemplar tail end, its end face and the universal company of transmission shaft
Connect, its circumferential surface is fixed on guided missile test exemplar tail end by fastener.
Around the transmission shaft, door case type protective frame is set.
The beneficial effects of the utility model are：
(1) the utility model is in prior art basis, by adding guided missile rotating driving device, rotary actuator,
Suspension arrangement equipped with anchor ear bearing, and wireless signal transmitter and wireless base station, realize oneself under guided missile autorotation
Rule by modal parameter with rotation speed change；
(2) guided missile test exemplar is realized on request by the guided missile rotating driving device and rotary actuator added
Rotating speed rotates；
(3) mounting means of inner ring anchor ear+bearing+outer shroud anchor ear is used, is suitable for the diameter of different tests exemplar, and in fact
The decoupling for now rotating and hanging；
(4) exciting bank and equipment data acquisition analyzing, the vibration acceleration adapted under high centrifugal acceleration are wirelessly adopted
Collection, data result have preferable signal-to-noise ratio.The utility model is using IEPE acceleration transducers and wireless signal transmitter
Form, adapts to the working environment under high centrifugal acceleration；
(5) the utility model can adapt to different tests exemplar to Modal Parameter Identification by adjusting the length of transmission shaft
It is required that；
(6) Free Modal test system architecture under guided missile autorotation provided by the utility model is simple, it is easy to control,
It is easily installed maintenance；
(7) estimated modal frequency of the Integral modes frequency of the utility model whole system away from product, so as to avoid revolving
Turn influence of the drive system to guided missile Modal Parameter Identification itself.
Brief description of the drawings
Fig. 1 is the general structure schematic diagram of the utility model；
Fig. 2 is the dimensional structure diagram that the utility model removes test device；
Fig. 3 is the structure diagram with anchor ear bearing；
Fig. 4 is the mounting structure schematic diagram of clamping piece.
In figure：
A suspension arrangements, B exciting banks, C data acquisition and analysis device, D rotary actuators, E guided missiles rotation driving dress
Put；
1 mounting bracket, the vertical side frames of 1a, the horizontal upper frames of 1b, 1c supporting substrates, 2 elastic threads, 3 anchor ear bearings, 30 bearings, 31
Outer shroud anchor ear, 32 inner ring anchor ears, 33-34 anti-channeling baffles, 4 guided missile test exemplars, 5 clamping pieces, 6 transmission shafts, 7 frequency converters, 8 frequency conversions
Motor, 81 motor support bases, 9 universal joints, 10 wireless signal transmitters, 11 acceleration transducers, 12 protective frames, 13 data records
Instrument, 14 charge amplifiers, 15 wireless base stations, 16-18 bolts, 19 terminals, 20 force snesors, 21 kidney slots, 22 excitations
Device.
The utility model is described in detail below in conjunction with drawings and examples.
Embodiment
Fig. 1-4 shows the Free Modal pilot system under a kind of guided missile autorotation, including suspension arrangement A, exciting bank
B, equipment data acquisition analyzing C, it is characterised in that be also provided with guided missile rotating driving device E and be connected to the guided missile rotation drive
Rotary actuator D between 4 tail ends of dynamic device E and guided missile test exemplar.The suspension arrangement A includes at least two groups of suspensions
Frame, this example, using two groups of hanger brackets.The hanger bracket is mainly by mounting bracket 1, the guided missile of support level set free rotation state
The elastic threads 2 of the anchor ear bearing 3 of tests exemplar 4 and the fixed anchor ear bearing 3 are formed；The guided missile rotating driving device E bags
The frequency range for including variable-frequency motor 8 and its connection is the frequency converter 7 of 5Hz-20Hz.In practice of construction, variable-frequency motor 8 is supported on height
Spend on adjustable motor support base 81.The function of variable-frequency motor 8 is the power source of rotation driving.The rotary actuator D includes
One transmission shaft 6, by the universal connection variable-frequency motor shaft of universal joint 9, the other end passes through another universal 6 its one end of transmission shaft
9 universal connections are saved to be fixedly clamped in the clamping element 5 of 4 tail end of guided missile test exemplar.
The clamping element 5 is a tubular end cap for being sleeved on 4 tail end of guided missile test exemplar, its end face is logical with transmission shaft 6
9 universal connection of universal joint is crossed, its circumferential surface is fixed on by fastener bolt 18 on the tail end of guided missile test exemplar 4.
The equipment data acquisition analyzing C includes acceleration transducer 11, the force snesor 20 on exciting bank, electric charge and puts
Big device 14, data logger 13, wireless signal transmitter 10, wireless base station 15 and the computer end for carrying out data analysis and calculating
End 19.The acceleration transducer 11 is arranged on guided missile test exemplar 4, and acceleration transducer 11 passes through in guided missile test exemplar
On wireless base station 15 described in 10 wireless connection of the wireless signal transmitter that is correspondingly arranged, the force snesor on exciting bank 22
20 connect data logger 13 by charge amplifier 14, and wireless base station 15 is connected to terminal with data logger 13
19.At this time, the signal of acceleration transducer 11 connects on the signal and guided missile test exemplar of the force snesor 20 of exciting bank 22
To terminal, model analysis calculating is carried out, obtains the modal parameter of guided missile test exemplar with the changing rule of rotating speed.
In this example, using IEPE acceleration transducers and the data collection form of wireless signal transmitter, adapt to it is high from
Working environment under heart acceleration.
In the present embodiment, the exciting bank 22 is hammered into shape for power.
The anchor ear bearing 3 includes bearing 30 and inner ring anchor ear 32 and outer shroud anchor ear 31 with its clearance fit, described interior
Hoop 32 is encircled to be fastened in the interior semicircle garter spring in the outside of guided missile test exemplar 4 and the inner ring for being clamped and being connected as a single entity by two hoops
Part is formed, and the outer shroud anchor ear 31 in the outer semicircle garter spring in the outside of bearing 30 and is clamped what is be connected as a single entity by two hoops
Outer ring fastener is formed, as shown in figure 3, in this example, two interior semicircle garter springs are clamped and are connected as a single entity by bolt 17；Two outer
Semicircle garter spring is clamped and is connected as a single entity by bolt 16.Anti-channeling baffle is set in the both ends of the surface of the anchor ear bearing 3, such as Fig. 3 institutes
Show, anti-channeling baffle 33 is fixed on outer shroud anchor ear between outer shroud anchor ear 31 and bearing 30, and anti-channeling baffle 34 is located at inner ring
Between anchor ear 32 and bearing 30, and it is fixed on inner ring anchor ear, so effectively prevents bearing 30 with respect to outer shroud anchor ear 31, interior encircles
The play of hoop 32.
In this example, the mounting bracket be by two vertical side frame 1a, connection horizontal upper frame 1b therebetween, and with the level
Upper frame is oppositely arranged supporting substrate 1c on the ground and forms, the anchor ear bearing 3 by its outer shroud anchor ear 31 up and down
The elastic threads 2 that four sides are respectively fixedly connected tense the waist-shaped hole 21 tied up on the vertical side frame 1a of horizontal upper frame 1b, supporting substrate 1c and two
It is interior, horizontal hanging set.Along its longitudinally disposed multiple kidney slot 21 on described two vertical side frame 1a, facilitate elastic threads 2 different
The installation of position.
In the utility model, door case type protective frame 12 is provided with around the transmission shaft.Protective frame 12 is used for
Occurs security protection during unexpected significantly whirling motion in debugging process of uniting.
The structural principle of the utility model and operation：
In conclusion guided missile rotating driving device E, rotation is realized for being provided for guided missile test exemplar with desired frequency
Power；Rotary actuator D, for connecting variable-frequency motor and missile tail, carries out rotary drive, and is avoided that itself is additional
The influence that quality and additional stiffness identify missile modality parameter；Suspension arrangement A be used for guided missile test exemplar free suspension and
Rotation decoupling；Exciting bank B is used for the application of exciting force in modal test；Equipment data acquisition analyzing C, for guided missile test sample
The data acquisition and analysis of part response calculate.Result inputs terminal 19 after collection, final acquisition guided missile test exemplar
Modal parameter with rotating speed changing rule.
Rotary actuator D includes transmission shaft 4 and clamping piece 5.4 both ends of the transmission shaft universal joint by each connecting respectively
9 with the 5 universal connection of variable-frequency electric arbor and clamping piece.Transmission shaft is used for the rotation for exporting variable-frequency motor 1, passes to guided missile test
Exemplar 4.Clamping piece 5 is used for gripping for guided missile test exemplar afterbody.
During actual fabrication, by suitably designing and simulation analysis, it can be adapted to by adjusting the diameter of transmission shaft, length
Requirement of the different guided missile test exemplars to Modal Parameter Identification, ensures that the dynamic characteristic of transmission shaft 4 does not interfere with tests exemplar mode
Identification, and the modal frequency of integrated model will not be caused larger whirling motion occur because being in the range of 5Hz-20Hz.System
System selects the design of elongated steel round bar by transmission shaft, can avoid rotary drive system to guided missile Modal Parameter Identification itself
Influence, and the tests exemplar of different low order mode of flexural vibration frequencies conveniently by the transmission shaft for replacing different length, can be adapted to.
The design principle of the utility model is：
(1) the low order mode of flexural vibration frequency of whole guided missile test exemplar-transmission shaft-elastic threads system is as small as possible, ensures
At least below the 1/5 of the 1st rank intrinsic frequency of guided missile test exemplar, to reduce the free boundary of elastic system simulation to guided missile test
The influence of exemplar mode；
(2) the low order mode of flexural vibration frequency of whole guided missile test exemplar-transmission shaft-elastic threads system is as small as possible, ensures
Largely it is less than the frequency 5Hz-20Hz of rotary drive system, to prevent from occurring by a relatively large margin in variable-frequency motor start-up course
Whirling motion；
(3) consider that steel round bar can be selected in structural strength and actual installation, transmission shaft, and leave in test certain peace
Full surplus；
(4) by the length and diameter design to transmission shaft, to ensure whole guided missile test exemplar-transmission shaft-elastic threads
Modal parameter (mainly frequency and the vibration shape) of the modal parameter of system with guided missile test exemplar in a non-rotatable state is approximate.
In the present embodiment：
(1) guided missile test exemplar length is 2.7m, and the preceding 3 rank modal frequency under non-rotating state is 82.7Hz, 205.4Hz
And 425.5Hz.
(2) considering structural strength and actual installation, select a diameter of 12mm, length is respectively 200mm, 300mm, 400mm,
The transmission shaft of 500mm, 600mm, 700mm, carry out simulation analysis using finite element analysis softwares such as MSC.Patran, obtain guided missile
The modal frequency of tests exemplar and whole guided missile test exemplar-transmission shaft-elastic threads system, is shown in Table 1：
Guided missile test exemplar and total system modal frequency table 1
(3) 1/5 propeller shaft length 400mm, the 500mm less than the 1st rank intrinsic frequency of guided missile test exemplar is selected,
600mm, 700mm；And then the length of reselection transmission shaft, ensure modal parameter and guided missile that corresponding simulation result is presented
The approximate 600mm of the modal parameter of tests exemplar in a non-rotatable state, 700mm transmission shafts, and preferentially select the biography of length length
Moving axis 700mm；
(4) for analyzing definite propeller shaft length L=700mm, to avoid emulating caused error, while L- is used
The transmission shaft of 3 kinds of specifications of 50mm, L and L+50mm, and during trial test before the test, most suitable transmission shaft is selected,
To obtain more accurately result.
Suspension arrangement A includes two groups of hanger brackets, and hanger bracket includes elastic threads 2, anchor ear bearing 3 and mounting bracket 1.Actually should
Elastic string is selected with middle elastic threads.Bearing 30 in anchor ear bearing 3 selects single-groove grooved ball bearing, and bearing 30 is tried with guided missile
Test exemplar 4 to fix by inner ring anchor ear 32, Bearing outer is fixed by outer shroud anchor ear 31, bearing 30 and inner and outer rings anchor ear 32,31
It is clearance fit, realization is freely rotated.Both sides are fixed by anti-channeling baffle 33,34, prevent interstructural axial float.Anti-channeling
Baffle 33,34 uses thin-slab structure, is respectively used to compress edge and outer in the bearing of bearing.It is suitable for not using anchor ear bearing 3
With the diameter of guided missile test exemplar, and realize the decoupling of rotation and suspension.
Since suspension arrangement A includes two groups of hanger brackets, guided missile test exemplar 4 is supported by front and rear anchor ear bearing 3 respectively, should
Used time, the levelness of guided missile test exemplar is adjusted by adjusting the relative altitude of elastic threads 2.Elastic threads 2 are from 4 directions
Anchor ear bearing 3 provides elastic bearing, while as the simulating boundary of Free Modal.During actual fabrication, 31 4 side of outer shroud anchor ear can
Hanging ring is installed, for fixing elastic threads 2.Along its longitudinally disposed multiple kidney slot 21 on two vertical side frame 1a, facilitate elastic threads 2
The installation of diverse location.In application, two elastic threads 2 in an opposite direction should try one's best and ensure identical rigidity.
Exciting bank 22 is hammered into shape using power, and equipment data acquisition analyzing includes acceleration transducer 11, force snesor 20, electric charge
Amplifier 14, data logger 13, wireless signal transmitter 10, wireless base station 15 and the computer for carrying out data analysis and calculating
Terminal 19.This example employs IEPE acceleration transducers.During experiment, anchor ear bearing is encouraged with by the way of tapping at random using power hammer
At 3 outer shroud anchor ear, power hammer is equipped with force snesor 20, and is connected by charge amplifier 14 with data logger 13.
In addition, in this example, guided missile test exemplar 4 2.7 meters long corresponding, using 10 acceleration transducers 11 and 4 three
Channel wireless signals transmitter 10 is uniformly installed on guided missile test exemplar 4 along guided missile test exemplar longitudinal direction, acceleration transducer
11 points are 4 groups, are connected respectively with corresponding set to the wireless signal transmitter 10 in this group of region, each wireless signal transmitter 10
Wireless signal is received by wireless base station 15, realizes the collection of acceleration responsive signal.Wireless base station 15 and data logger 13
Terminal 19 is connected to, at this time, acceleration passes on the signal and guided missile test exemplar of the force snesor 20 of exciting bank 22
The signal of sensor 11 is transferred to terminal, carries out model analysis calculating, obtain the modal parameter of guided missile test exemplar with
The changing rule of rotating speed.
The specific installation and debugging step of Free Modal pilot system under guided missile autorotation provided by the utility model is such as
Under：
(1) anchor ear bearing 3 is installed to before and after guided missile test exemplar 4 on 2 positions, while clamping piece 5 is installed to and is led
Play the afterbody of tests exemplar 4；
(2) variable-frequency motor 8 is installed on adjustable for height motor mount 81, motor mount 81, which first adjusts, to be designed
Default height；
(3) mounting bracket 1 is installed, and is connected to by elastic threads 2 on anchor ear bearing 3.The length of elastic threads 2 is adjusted, is ensured
Guided missile test exemplar 4 keeps horizontality, while whole height is in the height adjustable extent of variable-frequency motor；
(4) by the transmission shaft 6 of above-mentioned setting, variable-frequency motor 8 and clamping piece 5 are connected；
(5) connect on guided missile test exemplar 4 along its longitudinally mounted acceleration transducer and 11 and wireless signal transmitter 10
Whether logical data logger 13, wireless base station 15 and terminal 19, detection signal are normal；
(6) power supply of frequency converter 7 is opened, sets the rotating speed of test requirements document；
(8) it is whether normal that variable-frequency motor 1, the rotation of inspection guided missile test exemplar 4, and each signal are opened；
(9) using power hammer to carrying out random percussion excitation at the outer layer anchor ear 31 of anchor ear bearing 3；
(10) feedback signal of acceleration responsive signal and internal components is gathered, modal idenlification is carried out and signal confirms.
In conclusion the Free Modal pilot system under guided missile autorotation provided by the utility model, passes through what is added
Guided missile rotating driving device and rotary actuator realize the rotating speed rotation of guided missile test exemplar on request；By using inner ring
The frame mode of anchor ear, bearing and outer shroud anchor ear, adapts to the diameter of different guided missile test exemplars, and realizes the solution of rotation and suspension
Coupling；Exciting bank and equipment data acquisition analyzing, adapt to the vibration acceleration wireless collection under high centrifugal acceleration, data knot
Fruit has preferable signal-to-noise ratio；Especially system assembles are simple, and maintenance cost is low, easily operated, can be by adjusting the length of transmission shaft
Degree, adapts to requirement of the different tests exemplar to Modal Parameter Identification；Rotating driving device can be avoided to guided missile modal parameter itself
The influence of identification；Test system architecture is simple, and mechanical boundary is clear；Can accurately it be emulated for different tests exemplar
Prerun.
The utility model has the following advantages that than the prior art：
(1) the utility model is in prior art basis, by adding guided missile rotating driving device, rotary actuator,
Suspension arrangement equipped with anchor ear bearing, and wireless signal transmitter and wireless base station, realize oneself under guided missile autorotation
Rule by modal parameter with rotation speed change；
(2) guided missile test exemplar is realized on request by the guided missile rotating driving device and rotary actuator added
Rotating speed rotates；
(3) mounting means of inner ring anchor ear+bearing+outer shroud anchor ear is used, adapts to the diameter of different tests exemplar, and is realized
Rotation and the decoupling of suspension；
(4) exciting bank and equipment data acquisition analyzing, the vibration acceleration adapted under high centrifugal acceleration are wirelessly adopted
Collection, data result have preferable signal-to-noise ratio.The utility model is using IEPE acceleration transducers and wireless signal transmitter
Form, adapts to the working environment under high centrifugal acceleration；
(5) the utility model can adapt to different tests exemplar to Modal Parameter Identification by adjusting the length of transmission shaft
It is required that；
(6) Free Modal test system architecture under guided missile autorotation provided by the utility model is simple, it is easy to control,
It is easily installed maintenance；
(7) estimated modal frequency of the Integral modes frequency of the utility model whole system away from product, so as to avoid revolving
Turn influence of the drive system to guided missile Modal Parameter Identification itself.
The above, is only the preferred embodiment of the utility model, not to the structure and shape of the utility model
Make limitation in any form, it is every any simply to be repaiied according to what the technical essence of the utility model made above example
Change, equivalent variations and modification, in the range of still falling within technical solutions of the utility model.
Claims (10)
1. the Free Modal pilot system under a kind of guided missile autorotation, including suspension arrangement, exciting bank, data collection and analysis
Device, it is characterised in that be also provided with guided missile rotating driving device and be connected to the guided missile rotating driving device and guided missile test
Rotary actuator between exemplar tail end；The suspension arrangement includes at least two groups of hanger brackets, and the hanger bracket is mainly by pacifying
Shelve, the elasticity of the anchor ear bearing of the guided missile test exemplar of support level set free rotation state and the fixed anchor ear bearing
Rope is formed；The frequency range that the guided missile rotating driving device includes variable-frequency motor and its connection is the frequency converter of 5Hz-20Hz；
The rotary actuator includes a transmission shaft, and the transmission shaft its one end is universal to connect variable-frequency motor shaft, and the other end is universal
Connection is fixedly clamped in the clamping element of the guided missile test exemplar tail end；The equipment data acquisition analyzing includes acceleration sensing
Force snesor, charge amplifier, data logger, wireless signal transmitter, wireless base station on device, exciting bank and into line number
According to the terminal of analysis and calculating, the acceleration transducer is arranged on guided missile test exemplar, and acceleration transducer leads to
Wireless base station described in the wireless signal transmitter wireless connection being correspondingly arranged crossed on guided missile test exemplar, on exciting bank
Force snesor data logger is connected by the charge amplifier, wireless base station and data logger are connected to computer end
End.
2. the Free Modal pilot system under a kind of guided missile autorotation according to claim 1, it is characterised in that described
Exciting bank is hammered into shape for power.
3. the Free Modal pilot system under a kind of guided missile autorotation according to claim 1 or 2, it is characterised in that institute
Stating anchor ear bearing includes bearing and inner ring anchor ear and outer shroud anchor ear with its clearance fit, and the inner ring anchor ear is being led by two hoops
Play the interior semicircle garter spring on the outside of tests exemplar and the interior ring fastener for being clamped and being connected as a single entity is formed；The outer shroud anchor ear by
Two outer semicircle garter springs of the hoop on the outside of the bearing and is clamped the outer ring fastener composition being connected as a single entity；In the anchor ear
Bearing both ends of the surface set anti-channeling baffle.
4. the Free Modal pilot system under a kind of guided missile autorotation according to claim 1 or 2, it is characterised in that institute
Stating mounting bracket is oppositely arranged on the ground by two vertical side frames, the horizontal upper frame of connection therebetween, and with the horizontal upper frame
Supporting substrate form, the anchor ear bearing tenses system by the elastic threads that four sides are respectively fixedly connected up and down of its outer shroud anchor ear
On the horizontal upper frame, supporting substrate and two vertical side frames, horizontal hanging set.
5. the Free Modal pilot system under a kind of guided missile autorotation according to claim 4, it is characterised in that in institute
State on two vertical side frames along its longitudinally disposed multiple kidney slot.
6. the Free Modal pilot system under a kind of guided missile autorotation according to claim 3, it is characterised in that described
Mounting bracket is oppositely arranged on the ground by two vertical side frames, the horizontal upper frame of connection therebetween, and with the horizontal upper frame
Supporting substrate is formed, and the anchor ear bearing is tensed by the elastic threads that four sides are respectively fixedly connected up and down of its outer shroud anchor ear and tied up to
On horizontal upper frame, supporting substrate and two vertical side frames, horizontal hanging set.
7. the Free Modal pilot system under a kind of guided missile autorotation according to claim 1 or 2, it is characterised in that institute
Clamping element is stated as a tubular end cap for being sleeved on guided missile test exemplar tail end, its end face and the universal connection of transmission shaft, its ring
Side face is fixed on guided missile test exemplar tail end by fastener.
8. the Free Modal pilot system under a kind of guided missile autorotation according to claim 6, it is characterised in that described
Clamping element is a tubular end cap for being sleeved on guided missile test exemplar tail end, its end face and the universal connection of transmission shaft, its ring week
Face is fixed on guided missile test exemplar tail end by fastener.
9. the Free Modal pilot system under a kind of guided missile autorotation according to claim 1 or 2, it is characterised in that ring
Around the transmission shaft, door case type protective frame is set.
10. the Free Modal pilot system under a kind of guided missile autorotation according to claim 8, it is characterised in that surround
The transmission shaft sets door case type protective frame.
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| CN201721059779.XU CN207365823U (en) | 2017-08-22 | 2017-08-22 | A kind of Free Modal pilot system under guided missile autorotation |
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| CN201721059779.XU CN207365823U (en) | 2017-08-22 | 2017-08-22 | A kind of Free Modal pilot system under guided missile autorotation |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107388907A (en) * | 2017-08-22 | 2017-11-24 | 天津航天瑞莱科技有限公司 | A kind of Free Modal pilot system under guided missile autorotation |
| CN108845553A (en) * | 2018-06-15 | 2018-11-20 | 上海航天控制技术研究所 | A kind of servo elastic vibration inhibition comprehensive test method for elongated aircraft |
| CN109186974A (en) * | 2018-08-22 | 2019-01-11 | 清华大学 | One kind being fixedly connected with assembly performance and stablizes accelerated method |
| CN110542356A (en) * | 2019-09-03 | 2019-12-06 | 中国空空导弹研究院 | Guided missile hanging device |
-
2017
- 2017-08-22 CN CN201721059779.XU patent/CN207365823U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107388907A (en) * | 2017-08-22 | 2017-11-24 | 天津航天瑞莱科技有限公司 | A kind of Free Modal pilot system under guided missile autorotation |
| CN108845553A (en) * | 2018-06-15 | 2018-11-20 | 上海航天控制技术研究所 | A kind of servo elastic vibration inhibition comprehensive test method for elongated aircraft |
| CN108845553B (en) * | 2018-06-15 | 2021-03-09 | 上海航天控制技术研究所 | Servo elastic vibration suppression comprehensive inspection method for slender aircraft |
| CN109186974A (en) * | 2018-08-22 | 2019-01-11 | 清华大学 | One kind being fixedly connected with assembly performance and stablizes accelerated method |
| CN110542356A (en) * | 2019-09-03 | 2019-12-06 | 中国空空导弹研究院 | Guided missile hanging device |
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