CN106394945A - Solar wing flexible simulator - Google Patents
Solar wing flexible simulator Download PDFInfo
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- CN106394945A CN106394945A CN201610916201.5A CN201610916201A CN106394945A CN 106394945 A CN106394945 A CN 106394945A CN 201610916201 A CN201610916201 A CN 201610916201A CN 106394945 A CN106394945 A CN 106394945A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B23/00—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes
- G09B23/06—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes for physics
- G09B23/08—Models for scientific, medical, or mathematical purposes, e.g. full-sized devices for demonstration purposes for physics for statics or dynamics
Abstract
The invention discloses a solar wing flexible simulator. The solar wing flexible simulator comprises a base, a first simulating part, a second simulating part, a third simulating part and a torque sensor, wherein the first simulating part, the second simulating part and the third simulating part are sequentially connected and are installed on an air floating platform through the base connected with the first simulating part; the first simulating part is used for simulating the rotating inertia and the frequency of the first-order mode of a solar wing; the second simulating part is used for simulating the rotating inertia and the frequency of the sixth-order mode of the solar wing; the third simulating part is used for simulating the rotating inertia and the frequency of the twelfth-order mode of the solar wing; and the torque sensor is arranged at the position, close to the air floating platform, of the simulator and is used for measuring the torque output by the simulator to the air floating platform. The solar wing flexible simulator can analyze influences of different rotating inertias and different mode frequencies on a spacecraft body structure, and on the basis, the solar wing structure can be subjected to optimized design.
Description
Technical field
The present invention relates to space technology field, more particularly, to a kind of solar wing flexibility simulator.
Background technology
Modern spacecraft being continuously increased with function, complexity improves constantly, such as the flexibility such as large-sized solar windsurfing
Adnexa is also on the increase.When the light material manufacture, the therefore in-orbit flight of spacecraft of Low rigidity is adopted due to flexible appendage
Be highly susceptible to the effect of various propulsive forces and produce violent oscillatory motion, the vibration of flexible appendage and spacecraft body motion
Intercoupling and can produce impact to the attitude stabilization of spacecraft and orientation accuracy, or even damage instrument makes spacecraft lose efficacy.Therefore,
Design solar wing flexibility simulator carries out physical simulation experiment on ground, to study the shadow to spacecraft body construction for the flexible appendage
Sound is significant.
Solar wing has the characteristics that light weight, high flexible, is vulnerable to external disturbance and produces elastic vibration, special according to this
Point, the simulator in current ground simulation experimental system is broadly divided into active and two kinds of passive type.Wherein, active by adding
Plus exciting part carrys out produced elastic vibration after the simulated solar wing is interfered, and by the required generation of electric control system controls
Vibration mode；Passive type not by outside exciting, and by adjusting the structure of simulator come the mode of the simulated solar wing and rotation
Inertia.Existing solar wing simulator has following deficiency：
(1) vibration mode needed for active mode simulator passes through the generation of exciting part, and when vibrating change, its rotary inertia is several
Constant, therefore cannot Simulated Spacecraft solar wing different modalities corresponding difference rotary inertias feature, simulation reliability is relatively low.
(2) spacecraft solar wing rigidity is relatively low, and rank number of mode is high and low frequency is intensive, the general physical dimension of existing simulator
Less, model frequency higher it is difficult to realize the accurate simulation of frequency.In addition, space environment no extrernal resistance, solar wing each order mode state is shaken
Larger, existing simulator vibration weakens rapidly it is impossible to realize the true simulation of each order mode state amplitude with rank number of mode.
(3) in actual test, often it is not required to pay close attention to most of mode of solar wing, mode that only need to be larger to systematic influence
It is simulated, prior art cannot provide above-mentioned selective mode simulation.
(4) usually need in practical application the modal parameters such as torsion, bending are configured respectively, prior art cannot be real
Existing.
Therefore, the above-mentioned bottleneck of prior art make a kind of highly efficient, simulation precision is higher, can solve the above problems
Solar wing flexibility simulator become and need badly.
Content of the invention
The present invention provides a kind of solar wing flexibility simulator, is passed using shafting, crossbeam, balancing weight, elastic construction and moment
Sensor carries out passive type simulation, can truly assume the feature of spacecraft solar wing different modalities corresponding difference rotary inertia, tool
There is higher simulation reliability；With the first-order modal simulated solar wing of different analog components, spacecraft attitude stabilization is affected larger
One, six, ten second-order modals, accurately embody the feature that solar wing each rank model frequency is relatively low, amplitude is stronger；And it is each by setting
Class adjustment part achieves the independence adjustment of mode of flexural vibration and torsion mode, substantially increases simulation precision, in engineer applied
Have broad application prospects.
The present invention provides a kind of solar wing flexibility simulator, including pedestal, the first analog component, the second analog component, the
Three analog components and torque sensor；Wherein, the first analog component, the second analog component, the 3rd analog component are sequentially connected, and
Air floating platform is installed on by the pedestal being connected with the first analog component；
First analog component includes first crossbeam, first rotating shaft, the first spring assembly and end plate block；End plate block
It is symmetrically arranged on first crossbeam both sides, for adjusting the rotary inertia that the first analog component rotates around first rotating shaft as solar wing
The analogue value of first step mode rotary inertia, and tentatively adjust the first step mode frequency of the first analog component；First groups of springs
Part is arranged on first rotating shaft, for the first step mode frequency of accurate adjustment first analog component, as solar wing first step mode frequency
The analogue value of rate；
Second analog component includes second cross beam, the second rotating shaft, second spring assembly and middle part balancing weight；Middle part balancing weight
It is symmetrically arranged on second cross beam both sides, for adjusting the rotary inertia that the second analog component rotates around the second rotating shaft as solar wing
The analogue value of the 6th order mode state rotary inertia, and tentatively adjust the first step mode frequency of the second analog component；Second spring group
Part is arranged on the second rotating shaft, for the first step mode frequency of accurate adjustment second analog component, as solar wing the 6th order mode state frequency
The analogue value of rate；
3rd analog component includes the 3rd crossbeam, the 3rd rotating shaft, the 3rd spring assembly and top balancing weight；Top balancing weight
It is symmetrically mounted on the 3rd crossbeam both sides, for adjusting the rotary inertia that the 3rd analog component rotates around the 3rd rotating shaft as solar wing
The analogue value of the tenth second-order modal rotary inertia, and tentatively adjust the first step mode frequency of the 3rd analog component；3rd spring
Assembly is arranged on the 3rd rotating shaft, for the first step mode frequency of accurate adjustment the 3rd analog component, as solar wing the tenth second order mode
The analogue value of state frequency；
Torque sensor is arranged at first rotating shaft and is bordering at air floating platform, for measuring solar wing flexibility simulator to air supporting
The moment of platform output.
Preferably, first rotating shaft, the second rotating shaft and the 3rd rotating shaft are conllinear, and vertical with air floating platform.
Preferably, first crossbeam, second cross beam, the length of the 3rd crossbeam are sequentially reduced.
Preferably, described simulator also includes：
First fastening part, is installed on first crossbeam and first rotating shaft junction, for adjusting the second of the first analog component
Rank model frequency；
Second fastening part, is installed on second cross beam and the second rotating shaft junction, for adjusting the second of the second analog component
Rank model frequency；
3rd fastening part, is installed on the 3rd crossbeam and the 3rd rotating shaft junction, for adjusting the second of the 3rd analog component
Rank model frequency.
Preferably, after the completion of regulation, the second-order model frequency of the first analog component is more than the second analog component and the 3rd
The first step mode frequency of analog component, the second-order model frequency of the second analog component is more than the first rank of the 3rd analog component
Model frequency.
Preferably, the first spring assembly, second spring assembly, arbitrary in the 3rd spring assembly all include：It is provided with 8 folders
Hold the module body of hole and 2 U-lags, 8 springs；Wherein, module body is straight quadrangular, and its two relative surface respectively sets
Put 4 springs；Spring one end is fixed on clamping hole, and the other end is movably connected to U-lag.
Preferably, first rotating shaft, the second rotating shaft, the 3rd rotating shaft are all using angular contact ball bearing.
Preferably, described simulator also includes：
Be arranged at the first mode of flexural vibration adjustment portion in the middle part of first crossbeam side, its with first crossbeam two ends elastic connection,
For adjusting the 3rd rank model frequency of the first analog component；
Be arranged at the second mode of flexural vibration adjustment portion in the middle part of second cross beam side, its with second cross beam two ends elastic connection,
For adjusting the 3rd rank model frequency of the second analog component；
Be arranged at the 3rd mode of flexural vibration adjustment portion in the middle part of the 3rd crossbeam side, its with the 3rd crossbeam two ends elastic connection,
For adjusting the 3rd rank model frequency of the 3rd analog component.
Preferably, described simulator also includes：
It is arranged at the first mode of flexural vibration adjustment portion of first crossbeam upper surface middle part, it is with first crossbeam two ends elasticity even
Connect, for adjusting the fourth order model frequency of the first analog component；
It is arranged at the second mode of flexural vibration adjustment portion of second cross beam upper surface middle part, it is with second cross beam two ends elasticity even
Connect, for adjusting the fourth order model frequency of the second analog component；
It is arranged at the 3rd mode of flexural vibration adjustment portion in the middle part of the 3rd beam surface upper, it is with the 3rd crossbeam two ends elasticity even
Connect, for adjusting the fourth order model frequency of the 3rd analog component.
Preferably, the first step mode vibration shape of the first analog component, the second analog component and the 3rd analog component is around Y side
To torsion, second-order Mode Shape is to reverse around Z-direction, and the 3rd rank Mode Shape is around Y-direction bending, fourth order Mode Shape
It is around Z-direction bending；
Wherein, Y-direction is first rotating shaft place direction, and Z-direction is perpendicular to the direction of first rotating shaft and first crossbeam.
From above technical scheme, the solar wing flexibility simulator that the present invention provides, it is capable of spacecraft solar wing
Accurate simulation, and specific aim emulation is carried out to the several mode receiving publicity.The present invention the aspects such as frequency, amplitude all with place
Solar wing in working condition approaches, and can independent regulation torsion mode and mode of flexural vibration, there is stronger practicality.
Brief description
Fig. 1 is the solar wing flexibility simulator structural representation of the present invention；
Fig. 2 is the balancing weight scheme of installation of the present invention；
Fig. 3 is the spring assembly scheme of installation of the present invention；
Fig. 4 is the spring assembly structural representation of the present invention；
Fig. 5 is the first analog component first step mode vibration shape schematic diagram of the present invention；
Fig. 6 is the first analog component second-order Mode Shape schematic diagram of the present invention；
Fig. 7 is the first analog component the 3rd rank Mode Shape schematic diagram of the present invention；
Fig. 8 is the first analog component fourth order Mode Shape schematic diagram of the present invention.
Specific embodiment
For making the objects, technical solutions and advantages of the present invention become more apparent, referring to the drawings and enumerate preferred reality
Apply example, the present invention is described in more detail.However, it is necessary to illustrate, the many details listed in description are only
The reader is made to have a thorough explanation to one or more aspects of the present invention, can also even without these specific details
Realize the aspects of the invention.
The present inventor it is considered that be highly susceptible to when spacecraft in-orbit flight various propulsive forces effect and
Produce violent oscillatory motion, the vibration of flexible appendage and spacecraft body motion intercouple can attitude stabilization to spacecraft
And orientation accuracy produces impact, or even damage instrument makes spacecraft lose efficacy.Accordingly, it would be desirable to design solar wing flexibility simulator is on ground
Face carries out physical simulation experiment, to study the impact to spacecraft body construction for the flexible appendage.
Simulator in ground simulation experimental system is broadly divided into active and two kinds of passive type at present.Wherein, active
Produced elastic vibration after being interfered come the simulated solar wing by interpolation exciting part, and by needed for electric control system controls
The vibration mode producing.Existing active mode simulator includes following methods：
(1) pass through the controlled electric activator of input pushing force, make flexible simulator produce dither, and pass through acceleration
Meter and strain gauge carry out data collection and process.
(2) air jet system is installed on testing stand, its jet produces counteracting force, drives satellite to produce angular movement,
So that flex plate produces vibration, record the vibration shape of flex plate by vibration detecting device in real time, carry out flexible dynamics emulation.
Passive type is not by outside exciting, and come the mode of the simulated solar wing and rotates used by the structure adjusting simulator
Amount.
Existing solar wing simulator has following deficiency：
(1) vibration mode needed for active mode simulator passes through the generation of exciting part, and when vibrating change, its rotary inertia is several
Constant, therefore cannot Simulated Spacecraft solar wing different modalities corresponding difference rotary inertias feature, simulation reliability is relatively low.
(2) spacecraft solar wing rigidity is relatively low, and rank number of mode is high and low frequency is intensive, the general physical dimension of existing simulator
Less, model frequency higher it is difficult to realize the accurate simulation of frequency.In addition, space environment no extrernal resistance, solar wing each order mode state is shaken
Larger, existing simulator vibration weakens rapidly it is impossible to realize the true simulation of each order mode state amplitude with rank number of mode.
(3) in actual test, often it is not required to pay close attention to most of mode of solar wing, mode that only need to be larger to systematic influence
It is simulated.Such as, the research to solar wing vibration shows, 1,6,12 order mode states of solar wing are easy to and space flight in recent years
Device body couples, and then affects spacecraft attitude stabilization and positioning precision, and not easily passs through Vibration Active Control, passive vibration control
Method vibration damping processed, it is therefore necessary to choosing above-mentioned mode to carry out specific aim simulation, but prior art cannot provide above-mentioned selection
The simulation of property.
(4) usually need in practical application the modal parameters such as torsion, bending are configured respectively, prior art cannot be real
Existing.
For the problems referred to above, the present inventor is made up of crossbeam, rotating shaft, spring members, balancing weight using multiple
Each mode of the analog component respectively simulated solar wing, with the high order mode of the lower mode simulated solar wing of each part it is achieved that
Solar wing frequency and the true reappearance of amplitude.And by different adjusting meanss, torsion, mode of flexural vibration can be adjusted freely,
Greatly improve the degree of regulation of simulator parameter.Meanwhile, the solar wing simulator of the present invention can truly the simulated solar wing different
The feature of mode corresponding difference rotary inertia.
It is appreciated that term " first " used in the present invention, " second " etc. are herein used for describing various elements, but
These elements are not limited by above-mentioned term.Above-mentioned term is only used for distinguishing an element with another element.For example, exist
Without departing from the present invention, the first analog component can be referred to as the second analog component it is also possible to simulate second
Part is referred to as the first analog component, and the first analog component and the second analog component are all analog components, but the two is not same mould
Intend part.
In addition, refer to the noun in orientation traditionally according in running order when the orientation that is located.Such as, upper, middle and lower
Portion's balancing weight is to be described with residing relative position in working, and crossbeam side, upper surface are also for crossbeam during work
Speech.Particularly, Y herein is rotating shaft place direction, and X is crossbeam place direction, and Z is perpendicular to the direction of rotating shaft and crossbeam,
Three constitutes the three-dimensional cartesian coordinate system of this paper.
Fig. 1 shows the solar wing flexibility simulator structure of the present invention, and referring to Fig. 1, solar wing flexibility simulator includes base
Seat the 4, first analog component 1, the second analog component 2, the 3rd analog component 3 and torque sensor (not shown).
Specifically, the first analog component 1, the second analog component 2, the 3rd analog component 3 are sequentially overlapped, often from down to up
One all can independent pivoting.First analog component 1 is in bottom and is connected with pedestal 4.Usually, pedestal 4 adopts weight
Lighter cast aluminium.Solar wing flexibility simulator is installed on single shaft air floating platform by pedestal 4, and mounting means can be common spiral shell
Tether and connect.
Above three analog component structure is similar to.First analog component 1 includes first crossbeam 11, first rotating shaft, the first bullet
Spring assembly and end plate block 12.First crossbeam 11 middle part setting first rotating shaft, it is horizontal that end plate block 12 is symmetrically arranged on first
Beam 11 both sides, the first spring assembly is arranged on first rotating shaft.The installation of the spring assembly (peace of three spring assemblies as shown in Figure 3
Dress mode is similar).End plate block 12 is foil, and middle bolt positions, and surrounding bolt is fixed, and its mounting means is such as
Shown in Fig. 2, top balancing weight, middle part balancing weight are similar with the material of end plate block and mounting means.
The first analog component 1 can be adjusted by the quantity changing end plate block 12 to be used to around the rotation that first rotating shaft rotates
Amount and the preliminary first step mode frequency adjusting the first analog component 1.First spring assembly is used for accurate adjustment the first analog component 1
First step mode frequency.The rotary inertia of above-mentioned first analog component 1, first step mode frequency are respectively used to the simulated solar wing
The rotary inertia of first step mode and frequency.
Second analog component 2 includes second cross beam 21, the second rotating shaft, second spring assembly and middle part balancing weight 22.Second
Crossbeam 21 middle part setting the second rotating shaft, middle part balancing weight 22 is symmetrically arranged on second cross beam 21 both sides, and second spring assembly is installed
In the second rotating shaft.Middle part balancing weight 22 is used for adjusting the rotary inertia that the second analog component 2 rotates around the second rotating shaft, and first step
Save the first step mode frequency of the second analog component 2.Second spring assembly is used for the first step mode of accurate adjustment the second analog component 2
Frequency.The rotary inertia of above-mentioned second analog component 2, first step mode frequency are respectively used to the simulated solar wing the 6th order mode state
Rotary inertia and frequency.
3rd analog component 3 includes the 3rd crossbeam 31, the 3rd rotating shaft, the 3rd spring assembly and top balancing weight 32.3rd
Crossbeam 31 middle part setting the 3rd rotating shaft, top balancing weight 32 is symmetrically arranged on the 3rd crossbeam 31 both sides, and the 3rd spring assembly is installed
In the 3rd rotating shaft.Top balancing weight 32 is used for adjusting the rotary inertia that the 3rd analog component 3 rotates around the 3rd rotating shaft, and first step
Save the first step mode frequency of the 3rd analog component 3.3rd spring assembly is used for the first step mode of accurate adjustment the 3rd analog component 3
Frequency.The rotary inertia of above-mentioned 3rd analog component 3, first step mode frequency are respectively used to the simulated solar wing the tenth second-order modal
Rotary inertia and frequency.
Shafting provides to the support of superstructure it is contemplated that the requirement of bearing capacity and coefficient of friction, first rotating shaft, second
Rotating shaft, the 3rd rotating shaft are all using angular contact ball bearing.Further, the bearing in the embodiment of the present invention is 7208B for model
Angular contact ball bearing, internal diameter d=40mm, outer diameter D=80mm, width B=18mm, its dynamic load rating is 32500N, specified quiet
Load is 23500N.First rotating shaft, the second rotating shaft and the 3rd rotating shaft are conllinear, and vertical with air floating platform.
It is preferred that the structure of the first spring assembly, second spring assembly, the 3rd spring assembly is similar to, any of which is all wrapped
Include module body and 8 springs.Spring assembly structure is as shown in figure 4, referring to Fig. 4, module body is straight quadrangular, is provided with 8
Individual clamping hole and 2 U-lags, two relative surfaces respectively arrange 4 springs.Spring one end is fixed on clamping hole, and the other end can
It is connected to U-lag dynamicly.Method of clamping shown in figure ensure that spring attachment positions accurately and is conveniently adjusted.During work,
Its length is changed thus realizing the accurate adjustment of model frequency by U-lag.
Torque sensor is arranged at first rotating shaft and is bordering at air floating platform, is typically less than 100mm away from air floating platform, is used for
The moment that measurement solar wing flexibility simulator exports to air floating platform.
During use, adjustment balancing weight meets the requirement of rotary inertia first, realizes analog component first order frequency simultaneously
Preliminary regulation, realizes the accurate adjustment of the first order frequency afterwards by spring assembly.
By above-mentioned setting, the solar wing flexibility simulator of the present invention achieves following technique effect：
(1) feature of solar wing different modalities corresponding difference rotary inertia is embodied using passive type simulation.
(2) 1,6,12 order modes more serious for impact spacecraft attitude are achieved using three independent analog components
The simulation respectively of state.
(3) with the high order mode of the first-order modal simulated solar wing of analog component so that mode amplitude, natural frequency and reality
Actual value is coincide, the defect that the natural frequency overcoming simulator in prior art is too high, amplitude is less and truthful data deviates.
In a preferred embodiment of the invention, first crossbeam 11, second cross beam 21, the length of the 3rd crossbeam 31 are sequentially reduced,
So that the natural frequency of three raises successively, it is easy to the regulation of model frequency.
In practical application, for the ease of adjusting model frequency subsequently through balancing weight, spring assembly, need horizontal to first
Beam, second cross beam, the length of the 3rd crossbeam are rationally arranged, and to reduce modal parameter regulating time, increase system availability.
For this reason, the present invention obtains length and first order mode of the crossbeam that section is 120mm*120mm first with finite element analysis technology
The relation of state frequency；Then count 1,6,12 rank model frequencies of all kinds of solar wing, obtain universality data, such as, Yi Zhongdai
Solar wing 1,6, the 12 rank model frequency of table is respectively 0.0679Hz, 0.124Hz, 0.1825Hz；Adopt iterative regression afterwards
Algorithm obtains the optimum crossbeam length relation of fitting result.The present invention proposes equation below, can be applied to all kinds of solar wing
1st, 6,12 order mode morphotypes are intended, and each model frequency realizing crossbeam is close with the analogue value, to reduce follow-up fine setting difficulty, accelerate simulation
The regulation process of device.
Wherein, L1、L2、L3Respectively first crossbeam, second cross beam, the length of the 3rd crossbeam, formula requirement first crossbeam,
Second cross beam, the 3rd crossbeam shape of cross section identical with area.
In a preferred embodiment of the invention, first crossbeam, second cross beam, the length of the 3rd crossbeam be followed successively by 6 meters, 5.841
Rice, 1.5 meters, coincidence formula 1.
It should be noted that the first step mode vibration shape of first, second and third analog component is to reverse around Y-direction, simulated solar
The 1st of the wing, 6,12 order mode states.In order to adjust the second-order model frequency of first, second and third analog component, present invention setting first,
2nd, three fastening part.
Specifically, the first fastening part is installed on first crossbeam 11 and first rotating shaft junction, for adjusting the first simulation part
The second-order model frequency of part 1.Second fastening part is installed on second cross beam 21 and the second rotating shaft junction, for adjusting the second mould
Intend the second-order model frequency of part 2.3rd fastening part is installed on the 3rd crossbeam 31 and the 3rd rotating shaft junction, for adjusting the
The second-order model frequency of three analog components 3.
Usually, the second-order Mode Shape of first, second and third analog component is to reverse around Z-direction, and the simulated solar wing is corresponding
Torsion vibration mode mode.
By above-mentioned setting, present invention achieves the independent regulation of simulator second-order model frequency, improve solar wing
The simulation precision of mode.
In engineer applied, in order to prevent the interference between three analog components, make the of the first analog component 1 by adjusting
Second-order modal frequency is more than the first step mode frequency of the second analog component 2 and the 3rd analog component 3, the second analog component 2
Second-order model frequency is more than the first step mode frequency of the 3rd analog component 3.
As a preferred version, solar wing flexibility simulator also sets up the first mode of flexural vibration adjustment portion, the second bending die
State adjustment portion, the 3rd mode of flexural vibration adjustment portion are to adjust the 3rd rank model frequency of each analog component.
Specifically, first, second and third mode of flexural vibration adjustment portion is the adjustable elastic construction of rigidity.First mode of flexural vibration is adjusted
Section portion is arranged in the middle part of first crossbeam 11 side, and first crossbeam 11 two ends elastic connection, for adjusting the first analog component 1
3rd rank model frequency.Second mode of flexural vibration adjustment portion is arranged in the middle part of second cross beam 21 side, with second cross beam 21 two ends bullet
Property connect, for adjusting the 3rd rank model frequency of the second analog component 2.3rd mode of flexural vibration adjustment portion is arranged at the 3rd crossbeam
In the middle part of 31 sides, and the 3rd crossbeam 31 two ends elastic connection, for adjusting the 3rd rank model frequency of the 3rd analog component 3.
In a preferred embodiment of the invention, the 3rd rank Mode Shape of analog component is around Y-direction bending, i.e. Bending Deformation
Direction is vertical with Y-direction.3rd rank model frequency of each analog component is used for the corresponding mode that the simulated solar wing bends the vibration shape.
By above-mentioned setting, present invention achieves the independent regulation of simulator the 3rd rank model frequency is so that torsion mode
Separated with the simulation of mode of flexural vibration, accurately simulated respectively beneficial to the torsion decoupling, mode of flexural vibration to solar wing.
In a preferred embodiment of the invention, solar wing flexibility simulator also includes being arranged at first crossbeam 11 upper surface middle part
The first mode of flexural vibration adjustment portion, be arranged at the second mode of flexural vibration adjustment portion of second cross beam 21 upper surface middle part, be arranged at
3rd mode of flexural vibration adjustment portion of three crossbeam 31 upper surface middle part, is respectively used to adjust the fourth order mode frequency of corresponding analog component
Rate.
Above-mentioned mode of flexural vibration adjustment portion is the adjustable elastic construction of rigidity, is connected with place crossbeam two-side elastic.Preferably
Ground, the fourth order Mode Shape of analog component is that is, Bending Deformation direction is vertical with Z-direction around Z-direction bending.Each analog component
Fourth order model frequency be used for the simulated solar wing bend the vibration shape corresponding mode.
After the completion of solar wing flexibility simulator is adjusted, model analyses are carried out to it, the concrete number of each order mode state can be obtained
According to.Fig. 5-8 respectively illustrates first, second, third and fourth rank Mode Shape of the first analog component, therefrom can see as mentioned above
Each vibration shape, the horizontal direction of in figure is X-direction, and vertical direction is Y-direction.The vibration shape of second and third analog component and first
Analog component is similar to.
By above-mentioned setting, present invention achieves the independent regulation of simulator fourth order model frequency is so that torsion mode
Separated with the simulation of mode of flexural vibration, accurately simulated respectively beneficial to the torsion decoupling, mode of flexural vibration to solar wing.
The moment of torsion of the countershaft generation of spring in practical application, can be calculated by following equation, judge whether to meet the requirements：
F=Δ L × K formula 2
M=F × R formula 3
Wherein, M is moment of torsion, the pulling force that F produces for spring, and R is the radius of gyration, and K is spring rate, and Δ L is spring deformation.
Moment of friction is calculated by formula 4, judges whether to meet requirement：
Wherein, M1For moment of friction, μ is coefficient of friction, and d is bearing bore diameter, and f is bearing capacity.
Each damping ratios can be calculated by formula 5：
Wherein, ζ is damping ratio, and A1, A2 are each cycle amplitude.
The solar wing flexibility simulator being provided according to the present invention, is stacked in single-axle air bearing table using three analog components
The heart, between analog component and single-axle air bearing table, mounting torque sensor is used for measure analog device for the moment size of turntable, enters
And the simulated solar wing is for the impact of spacecraft body.When single-axle air bearing table Simulated Spacecraft body moves, flexible simulation knot
Structure also can be disturbed and produce vibration, calculate the size of moment by torque sensor output signal, you can analysis mode device
Different rotary inertias, the impact to spacecraft body construction for the different modalities frequency.Sun wing structure can be entered on this basis
Row optimization design, to weaken its interference to spacecraft body.In addition, the present invention does not need to design control system and dynamical system
System, compared with prior art more simple and easy to do, cost is relatively low.
One of ordinary skill in the art will appreciate that it is permissible for realizing all or part of step in above-described embodiment method
Instruct related hardware to complete by program, this program can be stored in a computer read/write memory medium, such as：
ROM/RAM, magnetic disc, CD etc..
The above is only the preferred embodiment of the present invention it is noted that ordinary skill people for the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (10)
1. a kind of solar wing flexibility simulator it is characterised in that include pedestal, the first analog component, the second analog component, the 3rd
Analog component and torque sensor；Wherein,
First analog component, the second analog component, the 3rd analog component are sequentially connected, and by being connected with the first analog component
Pedestal is installed on air floating platform；
First analog component includes first crossbeam, first rotating shaft, the first spring assembly and end plate block；End plate block is symmetrical
It is installed on first crossbeam both sides, for adjusting the rotary inertia that the first analog component rotates around first rotating shaft as solar wing first
The analogue value of order mode state rotary inertia, and tentatively adjust the first step mode frequency of the first analog component；First spring assembly peace
It is contained in first rotating shaft, for the first step mode frequency of accurate adjustment first analog component, as solar wing first step mode frequency
The analogue value；
Second analog component includes second cross beam, the second rotating shaft, second spring assembly and middle part balancing weight；Middle part balancing weight is symmetrical
It is installed on second cross beam both sides, for adjusting the rotary inertia that the second analog component rotates around the second rotating shaft as solar wing the 6th
The analogue value of order mode state rotary inertia, and tentatively adjust the first step mode frequency of the second analog component；Second spring assembly is pacified
It is contained in the second rotating shaft, for the first step mode frequency of accurate adjustment second analog component, as solar wing the 6th rank model frequency
The analogue value；
3rd analog component includes the 3rd crossbeam, the 3rd rotating shaft, the 3rd spring assembly and top balancing weight；Top balancing weight is symmetrical
It is arranged on the 3rd crossbeam both sides, for adjusting the rotary inertia that the 3rd analog component rotates around the 3rd rotating shaft as solar wing the tenth
The analogue value of second-order modal rotary inertia, and tentatively adjust the first step mode frequency of the 3rd analog component；3rd spring assembly
It is arranged on the 3rd rotating shaft, for the first step mode frequency of accurate adjustment the 3rd analog component, as solar wing the tenth second-order modal frequency
The analogue value of rate；
Torque sensor is arranged at first rotating shaft and is bordering at air floating platform, for measuring solar wing flexibility simulator to air floating platform
The moment of output.
2. simulator as claimed in claim 1, first rotating shaft, the second rotating shaft and the 3rd rotating shaft are conllinear, and hang down with air floating platform
Directly.
3. simulator as claimed in claim 2, first crossbeam, second cross beam, the length of the 3rd crossbeam are sequentially reduced.
4. simulator as claimed in claim 3, also includes：
First fastening part, is installed on first crossbeam and first rotating shaft junction, for adjusting the second order mode of the first analog component
State frequency；
Second fastening part, is installed on second cross beam and the second rotating shaft junction, for adjusting the second order mode of the second analog component
State frequency；
3rd fastening part, is installed on the 3rd crossbeam and the 3rd rotating shaft junction, for adjusting the second order mode of the 3rd analog component
State frequency.
5. simulator as claimed in claim 4, after the completion of regulation, the second-order model frequency of the first analog component is more than second
Analog component and the first step mode frequency of the 3rd analog component, the second-order model frequency of the second analog component is more than the 3rd mould
Intend the first step mode frequency of part.
6. simulator as claimed in claim 5, arbitrary equal in the first spring assembly, second spring assembly, the 3rd spring assembly
Including：It is provided with the module body of 8 clampings holes and 2 U-lags, 8 springs；Wherein, module body is straight quadrangular, its phase
To two surfaces 4 springs are respectively set；Spring one end is fixed on clamping hole, and the other end is movably connected to U-lag.
7. described simulator as arbitrary in claim 1-6, first rotating shaft, the second rotating shaft, the 3rd rotating shaft are all using angular contact ball
Bearing.
8. simulator as claimed in claim 7, also includes：
It is arranged at the first mode of flexural vibration adjustment portion in the middle part of first crossbeam side, it is used for first crossbeam two ends elastic connection
Adjust the 3rd rank model frequency of the first analog component；
It is arranged at the second mode of flexural vibration adjustment portion in the middle part of second cross beam side, it is used for second cross beam two ends elastic connection
Adjust the 3rd rank model frequency of the second analog component；
It is arranged at the 3rd mode of flexural vibration adjustment portion in the middle part of the 3rd crossbeam side, it is used for the 3rd crossbeam two ends elastic connection
Adjust the 3rd rank model frequency of the 3rd analog component.
9. simulator as claimed in claim 8, also includes：
It is arranged at the first mode of flexural vibration adjustment portion of first crossbeam upper surface middle part, it is used with first crossbeam two ends elastic connection
In the fourth order model frequency adjusting the first analog component；
It is arranged at the second mode of flexural vibration adjustment portion of second cross beam upper surface middle part, it is used with second cross beam two ends elastic connection
In the fourth order model frequency adjusting the second analog component；
It is arranged at the 3rd mode of flexural vibration adjustment portion in the middle part of the 3rd beam surface upper, it is used with the 3rd crossbeam two ends elastic connection
In the fourth order model frequency adjusting the 3rd analog component.
10. simulator as claimed in claim 9, the first of the first analog component, the second analog component and the 3rd analog component
Rank Mode Shape is to reverse around Y-direction, and second-order Mode Shape is to reverse around Z-direction, and the 3rd rank Mode Shape is curved around Y-direction
Song, fourth order Mode Shape is around Z-direction bending；
Wherein, Y-direction is first rotating shaft place direction, and Z-direction is perpendicular to the direction of first rotating shaft and first crossbeam.
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| CN113879573A (en) * | 2021-09-18 | 2022-01-04 | 长光卫星技术有限公司 | Fundamental frequency and rotational inertia adjustable solar wing ground simulation system |
| CN114414145A (en) * | 2021-12-21 | 2022-04-29 | 上海利正卫星应用技术有限公司 | Rotational inertia simulation device of sailboard driving mechanism |
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