CN207985243U - A kind of triangular truss flexible appendage simulator - Google Patents
A kind of triangular truss flexible appendage simulator Download PDFInfo
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- CN207985243U CN207985243U CN201820229261.4U CN201820229261U CN207985243U CN 207985243 U CN207985243 U CN 207985243U CN 201820229261 U CN201820229261 U CN 201820229261U CN 207985243 U CN207985243 U CN 207985243U
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- triangular truss
- flexible appendage
- simulator
- mounting base
- adjustable
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Abstract
The utility model is related to a kind of triangular truss flexible appendage simulators, including triangular truss, mounting base, adjustable pouring weight and constant force spring hanging frame；The mounting base is equipped with horizontal bottom plate and vertical side plate, and bottom plate with external air floating table for being fixedly connected, and side plate is for connecting triangular truss；Triangular truss is fixedly connected to form cantilever design as flexible appendage, one end with mounting base, and the other end sets adjustable pouring weight；Adjustable pouring weight is suspended in midair by constant force spring hanging frame to be supported.Simulator described in the utility model is used to be mounted on air floating table in the ground simulation test of spacecraft, it being capable of the larger flexible appendage of real simulation spacecraft rotary inertia, frequency span, with lower first-order flexure frequency, and fundamental frequency, rotary inertia are adjustable in wide range.
Description
Technical field
The utility model is related to spacecraft simulation experimental technique field more particularly to a kind of triangular truss flexible appendage moulds
Quasi- device.
Background technology
With comprehensive raising of information technology and industrial technology, space technology has the development advanced by leaps and bounds, space industry
It has been the competitive field that countries in the world are extremely paid attention to.Spacecraft structure just develops towards the direction of enlargement, flexibilityization, nowadays
Spacecraft structure it is complicated, with increasing for function, the quantity type of flexible appendage is also more and more；Flexible appendage is complicated
While, to consider cost, it is desirable that very light weight causes flexibility more obvious, to the performance of the attitude control system of spacecraft
It is required that being also continuously improved.
Spacecraft flexible part can be caused substantially to vibrate the flexible control deficiency of structure, and it is right after the coupling of spacecraft
The attitude stability and accuracy of spacecraft will produce influence, so far for having occurred and that repeatedly such space flight accident.
To avoid the generation of accident, when ground simulation test, will fully consider influence of the flexible part to spacecraft entirety, conventional means
It is the simulation realized by the flexible simulator on air floating table to flexible part.
Currently, when ground physical l-G simulation test, flexible appendage mostly uses greatly thin plate and Rigid Base is mounted on air floating table
It realizes, this simulator structure is simple, at low cost, but size is small, and intrinsic frequency is high, it is difficult to simulate that amount of deflection is increasing to scratch
Property attachment.Another kind of simulator is made of enough plurality of plates, flexible coupling and gas, and first natural frequency is low, but due to adopting
Cause cost higher enough with gas.
Invention content
The utility model provides a kind of triangular truss flexible appendage simulator, is tried for the ground simulation in spacecraft
Be mounted on air floating table when testing, can the larger flexible appendage of real simulation spacecraft rotary inertia, frequency span, have relatively low
First-order flexure frequency, and fundamental frequency, rotary inertia are adjustable in wide range.
In order to achieve the above object, the utility model is realized using following technical scheme：
A kind of triangular truss flexible appendage simulator, including triangular truss, mounting base, adjustable pouring weight and constant force bullet
Spring hanger；The mounting base is equipped with horizontal bottom plate and vertical side plate, and bottom plate, which is used to fix with external air floating table, to be connected
It connects, side plate is for connecting triangular truss；Triangular truss is fixedly connected to form outstanding as flexible appendage, one end with mounting base
Arm configuration, the other end set adjustable pouring weight；Adjustable pouring weight is suspended in midair by constant force spring hanging frame to be supported.
The adjustable pouring weight is made of the weight stack of multiple and different thickness.
It is positioned and is fixed by positioning plate between the adjustable pouring weight and triangular truss.
Disc spring is set in the constant force spring hanging frame as elastic element, point of suspension is located at the top center of adjustable pouring weight.
Composition is bolted using steel spring plate in the triangular truss.
Multiple reinforcing ribs are equipped between the bottom plate and side plate of the mounting base.
Compared with prior art, the utility model has the beneficial effects that：
1) flexible appendage uses triangular truss structure, low manufacture cost；Agent structure is using narrow and thin steel spring plate
Composition is bolted, required flexibility can be provided, the gusset of cross-sectional direction is used to improve the rigidity of vertical direction；
2) mounting base is equipped with reinforcing rib structure, to balance the tilting moment caused by simulator structure bias, reduces
Deformation at the adjustable pouring weight in simulator end, enhances integrally-built stability；
3) adjustable pouring weight is suspended in midair by constant force spring hanging frame and is supported, small, the spring tension output of constant force spring hanging frame
Stablize, the displacement stress of simulator free end can be reduced, offset the deformation of vertical direction, to reduce caused by suspention
The vibration of simulator；
4) adjustable pouring weight is made of the weight stack of multiple and different thickness, when debugging and using simulator, can pass through increasing
Subtract the frequency and rotary inertia of weight stack adjustment simulator.
Description of the drawings
Fig. 1 is a kind of structural schematic diagram of triangular truss flexible appendage simulator described in the utility model.
Fig. 2 is a kind of dimensional structure diagram (constant force of triangular truss flexible appendage simulator described in the utility model
Spring hanger is not shown).
Fig. 3 is the 2D curved line relations of optimum results design point and structure first natural frequency in the utility model embodiment
Figure.
Fig. 4 is the 3D curved line relations of optimum results design point and structure first natural frequency in the utility model embodiment
Figure.
Fig. 5 is the static analysis Aberration nephogram of the utility model embodiment intermediate cam shape truss flexible appendage simulator.
Fig. 6 is the static analysis Stress Map of the utility model embodiment intermediate cam shape truss flexible appendage simulator.
Fig. 7 is the buckling analysis first-order bending vibation mode picture of the utility model embodiment intermediate cam shape truss flexible appendage simulator.
Fig. 8 is the model analysis first-order bending vibation mode picture of the utility model embodiment intermediate cam shape truss flexible appendage simulator.
In figure：1. 2. triangular truss of mounting base, 3. positioning plate, 4. constant force spring hanging frame, 5. adjustable pouring weight
Specific implementation mode
Specific embodiment of the present utility model is described further below in conjunction with the accompanying drawings：
As shown in Figure 1 and Figure 2, a kind of triangular truss flexible appendage simulator described in the utility model, including triangle purlin
Frame 2, mounting base 1, adjustable pouring weight 5 and constant force spring hanging frame 4；The mounting base 1 is equipped with horizontal bottom plate and vertical side
Plate, bottom plate with external air floating table for being fixedly connected, and side plate is for connecting triangular truss 2；Triangular truss 2 is used as and scratches
Property attachment, one end and mounting base 1 be fixedly connected to form cantilever design, and the other end sets adjustable pouring weight 5；Adjustable pouring weight 5 by
The suspention support of constant force spring hanging frame 4.
The adjustable pouring weight 5 is made of the weight stack of multiple and different thickness.
It is positioned and is fixed by positioning plate 3 between the adjustable pouring weight 5 and triangular truss 2.
Disc spring is set in the constant force spring hanging frame 4 as elastic element, point of suspension is located in the top of adjustable pouring weight 5
The heart.
Composition is bolted using steel spring plate in the triangular truss 2.
Multiple reinforcing ribs are equipped between the bottom plate and side plate of the mounting base 1.
A kind of design method of triangular truss flexible appendage simulator described in the utility model is as follows：
1) using fundamental frequency and rotary inertia as design parameter, the structure of simulator is carried out using dynamic flexibility method theoretical
It calculates；For convenience of calculating, Modal truncation is calculated into the low degree-of-freedom differential equation；
Simulator is reduced to the restraining structure with resilient support boundary, when it does simple harmonic oscillation with natural frequency ω
When, internal force R will be generated by being supported at it on boundaryb(ω)；Corresponding free structure be equivalent to the position of corresponding restrained boundary by
To exciting force Rb(ω) is acted on and is carried out forced vibration；Its diriven motion equation is：
Corresponding characteristic equation is：
Only consider support system stiffness characteristics k, ignores the quality m of simulator, support system does letter in restraining structure with ω
Equilibrium equation when harmonic motion can be written as：
It is through being derived from characteristic equation：
[κ(ω)-ω2μ(ω)]qt=0
The natural frequency ω and q of restraining structure can be obtained by solving above formulaiModal matrix in space；
2) after the intrinsic frequency for finding out fixed constraint structure, using FInite Element, using the APDL of ANSYS Workbench
Module and Design Exploration modules are designed and adjust to each portion's size of simulator, and verify overall structure
Intensity, rigidity and stability；
Static analysis is carried out first, and then proof strength, rigidity carry out buckling analysis in safe range, verification is stablized
Property；Since simulator carries out suspention support using constant force spring hanging frame to adjustable pouring weight, the load of preceding two ranks buckling mode because
Son is higher, and the stability of simulator is made to greatly improve；
3) after the intensity, rigidity and stability of simulator are all verified, prestressed mode point has been carried out to simulator
Analysis；The intrinsic frequency of calculating simulation device optimizes the key dimension for influencing frequency further according to the first-order flexure frequency of setting,
Obtain the specific size in each portion of simulator；
4) it during debugging and use, when frequency needs a wide range of adjustment, is required for excellent by finite element analysis, size
After change, the thickness of adjustable pouring weight is calculated, then adjustable pouring weight is formed by adjusting weight stack.
In use, a kind of triangular truss flexible appendage simulator described in the utility model is mounted on by mounting base 1
On air floating table.Air floating table Simulated Spacecraft main body, triangular truss 2 described in the utility model simulate space flight as flexible appendage
The related solar array of device main body, satellite antenna or mechanical arm, for verifying when spacecraft moves, the flexibility of flexible appendage is shaken
The influence of dynamic interference and the coupling of flexible appendage and spacecraft ontology to control system performance, is attitude control system
Design improves and verification provides support.
Following embodiment is implemented under premised on technical solutions of the utility model, gives detailed embodiment
With specific operating process, but the scope of protection of the utility model is not limited to following embodiments.Side used in following embodiments
Method is conventional method unless otherwise instructed.
【Embodiment】
In the present embodiment, after theoretical calculation, primary Calculation goes out the size range of each portion's structure of simulator, by limited
After meta analysis verifies the intensity, rigidity and stability of structure, the fundamental frequency of structure is calculated, it is excellent then to carry out size
Change.
For example, the size of adjustable pouring weight 5 that can be larger to frequency influence optimizes；As shown in figure 3, adjustable counter balance
When the length 100-300mm of block 5, the fundamental frequency of simulator changes within the scope of 0.53944Hz-0.303Hz；To adjustable counter balance
After two sizes of 5 length of block and thickness optimize, response surface design such as Fig. 4 institutes of optimum results design point and two design objects
Show, after optimization, the accurate dimension of required structure, the size and thickness of adjustable pouring weight 5 can be obtained.
In the present embodiment, after optimized, the length of simulator intermediate cam shape truss 2 is 2.01m, and fundamental frequency is
0.35Hz-3.3Hz, rotary inertia is in 804kgm2-5.95kgm2It is adjustable in range；In use, what frequency needs adjusted, it can basis
Above-mentioned result of calculation determines the combination of adjustable pouring weight.
In the present embodiment, the simulator for being 0.35Hz is required fundamental frequency, after optimized size, has carried out intensity, just
The verification of degree, stability and intrinsic frequency calculates；As shown in Figure 5, Figure 6, it is from the Aberration nephogram of heavy load static analysis and to answer
The maximum distortion of power cloud atlas, simulator is 1.8582mm, maximum stress 34.165MPa.Fig. 7 is the single order buckling of buckling analysis
Bending vibation mode picture, the single order buckling factor are 17.401.Fig. 8 is to have prestressed model analysis first step mode bending vibation mode picture, the vibration shape one
Rank is bent, and the first order frequency is 0.35221Hz.
In the present embodiment, when 5 overall thickness 200mm of adjustable pouring weight after optimization, fundamental frequency 0.35022Hz, rotation
Inertia 804kgm2。
The preferable specific implementation mode of the above, only the utility model, but the scope of protection of the utility model is not
Be confined to this, any one skilled in the art within the technical scope disclosed by the utility model, according to this practicality
Novel technical solution and its utility model design are subject to equivalent substitution or change, should all cover the protection model in the utility model
Within enclosing.
Claims (6)
1. a kind of triangular truss flexible appendage simulator, which is characterized in that including triangular truss, mounting base, adjustable counter balance
Block and constant force spring hanging frame；The mounting base is equipped with horizontal bottom plate and vertical side plate, and bottom plate is used for and external gas
Floating platform is fixedly connected, and side plate is for connecting triangular truss；Triangular truss is fixed as flexible appendage, one end with mounting base
Connection forms cantilever design, and the other end sets adjustable pouring weight；Adjustable pouring weight is suspended in midair by constant force spring hanging frame to be supported.
2. a kind of triangular truss flexible appendage simulator according to claim 1, which is characterized in that the adjustable counter balance
Block is made of the weight stack of multiple and different thickness.
3. a kind of triangular truss flexible appendage simulator according to claim 1, which is characterized in that the adjustable counter balance
It is positioned and is fixed by positioning plate between block and triangular truss.
4. a kind of triangular truss flexible appendage simulator according to claim 1, which is characterized in that the constant force spring
Disc spring is set in hanger as elastic element, point of suspension is located at the top center of adjustable pouring weight.
5. a kind of triangular truss flexible appendage simulator according to claim 1, which is characterized in that the triangle purlin
Composition is bolted using steel spring plate in frame.
6. a kind of triangular truss flexible appendage simulator according to claim 1, which is characterized in that the mounting base
Multiple reinforcing ribs are equipped between bottom plate and side plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201820229261.4U CN207985243U (en) | 2018-02-09 | 2018-02-09 | A kind of triangular truss flexible appendage simulator |
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| CN201820229261.4U CN207985243U (en) | 2018-02-09 | 2018-02-09 | A kind of triangular truss flexible appendage simulator |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108190053A (en) * | 2018-02-09 | 2018-06-22 | 哈工大鞍山工业技术研究院有限公司 | A kind of triangular truss flexible appendage simulator and its design method |
| CN109466809A (en) * | 2018-11-28 | 2019-03-15 | 北京控制工程研究所 | One kind can configure assemblnig flexible simulator |
| CN113465856A (en) * | 2021-08-31 | 2021-10-01 | 中国航天空气动力技术研究院 | Cabin body frequency modulation tool |
-
2018
- 2018-02-09 CN CN201820229261.4U patent/CN207985243U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108190053A (en) * | 2018-02-09 | 2018-06-22 | 哈工大鞍山工业技术研究院有限公司 | A kind of triangular truss flexible appendage simulator and its design method |
| CN109466809A (en) * | 2018-11-28 | 2019-03-15 | 北京控制工程研究所 | One kind can configure assemblnig flexible simulator |
| CN113465856A (en) * | 2021-08-31 | 2021-10-01 | 中国航天空气动力技术研究院 | Cabin body frequency modulation tool |
| CN113465856B (en) * | 2021-08-31 | 2022-01-04 | 中国航天空气动力技术研究院 | Cabin body frequency modulation tool |
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