CN106483872A - The flexible solar wing of simulation drives the precision judge method of dynamics simulation testing stand - Google Patents
The flexible solar wing of simulation drives the precision judge method of dynamics simulation testing stand Download PDFInfo
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- CN106483872A CN106483872A CN201510531727.7A CN201510531727A CN106483872A CN 106483872 A CN106483872 A CN 106483872A CN 201510531727 A CN201510531727 A CN 201510531727A CN 106483872 A CN106483872 A CN 106483872A
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
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Abstract
The invention discloses a kind of pass judgment on the precision methods that the flexible solar wing of simulation drives dynamics simulation testing stand.Main inclusion torsional oscillation device, the realization of torsion frequency, flexible solar wing drive simulation, pass judgment on the quantization of precision.Present invention inertia disc is vibrated with the kinetics during torsion bar simulation flexible solar wing driving, realize different torsion frequencies by adjusting inertia disc quality from torsion bar torsional rigidity, applying step velocity drives simulated solar wing Direct to the sun to rotate, with torque sensor measurement dynamic load moment as theoretical value, to quantify to pass judgment on the precision of simulation test stand with frequency departure with the amplitude of theoretical value with the moment that simulation test stand loads.The present invention devises the precision judge method that the flexible solar wing of simulation drives dynamics simulation testing stand, economical, efficiently achieve the precision judge that the flexible solar wing of simulation drives dynamics simulation testing stand, achieve economy, implement easily, the high beneficial effect of accuracy.
Description
Technical field
The present invention relates to semi-physical system precision judge, specifically simulate the precision judge method that flexible solar wing drives dynamics simulation testing stand.
Technical background
It is to be realized by Direct to the sun device driving mechanism semi-physical simulation platform that the flexible solar wing of simulation drives dynamic process, it is the testing equipment evaluating Direct to the sun device performance that flexible solar wing drives kinetics semi-physical simulation platform, during Direct to the sun device drives flexible solar wing drive control performance test, the problems such as flexible solar wing drive control can be caused unstable because of the factor such as testing equipment performance and loading deviation is it is therefore necessary to flexible solar wing drives the precision of dynamics simulation testing stand to make accurate judge to simulation.And actual solar energy sailboard characteristic is extremely complex, is multiple degrees of freedom flexible system, its characteristic is difficult to recognize clear.Therefore the method that need to design economical and efficient accurately to pass judgment on the precision that the flexible solar wing of simulation drives dynamics simulation testing stand.Solar battery array grand movement moment of reaction Research of Solving Method, Zhao Zhen, 2010, vibrate and impact；Describe the method for solving of the flexible solar wing kinetics moment of reaction.
The evaluation method of dynamics simulation testing stand precision is driven to yet there are no open source information about the flexible solar wing of simulation at present.
Content of the invention
Inventing problem to be solved is the accurate precision passing judgment on simulation flexible solar wing driving dynamics simulation testing stand, and the present invention proposes the precision judge method that a kind of flexible solar wing of simulation drives dynamics simulation testing stand.The method is achieved by the steps of：
Step 1, setting inertia disc and the load of the torsion bar arrangement simulated solar wing, are supported by air-bearing, eliminate frictional force；Described torsional oscillation device includes inertia disc [1], air-bearing [2] and torsion bar [3], described motor [7] is arranged on pedestal [6], torque sensor [5] is arranged on motor [7] axle head, and shaft coupling [4] connects torsion bar [3] and torque sensor [5]；
Step 2, adjustment inertia disc quality realize different torsion frequencies from torsion bar torsional rigidity；
Step 3, motor carry out the simulated solar wing by Velocity Step Technique and drive；
Step 4, measure disturbance moment of torsion by torque sensor and be used as theoretical value, the amplitude of the moment and the theoretical value that are loaded with simulation test stand under identical operating mode and frequency departure to quantify to pass judgment on the precision of simulation test stand.
Compared with prior art, it is an advantage of the current invention that：
Effectively pass judgment on the flexible solar wing of simulation using the inventive method and drive dynamics simulation testing stand precision capability, and economy, enforcement are easily, accuracy is high.Can be widely applied to simulate flexible solar wing driving dynamics simulation testing stand precision judge.
Brief description
Fig. 1 simulates flexible solar wing for the present invention and drives dynamics simulation testing stand precision judge method sketch；
Fig. 2 is that simulated solar wing actuating speed instruction of the present invention is illustrated；
Fig. 3 adjusts schematic diagram for torsion frequency of the present invention；
Fig. 4 is that disturbance moment of torsion loaded value is carried out quantified precision and illustrated with the amplitude of theoretical value and frequency departure.
Specific embodiment
With example, the present invention is described in further detail below in conjunction with the accompanying drawings.
The technology of the present invention method is made up of following part：
Torsional oscillation device is made up of inertia disc 1, air-bearing 2 and torsion bar 3 as shown in Figure 1, and described motor 7 is arranged on pedestal 6, and torque sensor 5 is arranged on motor 7 axle head, and shaft coupling 4 connects torsion bar 3 and torque sensor 5.With inertia disc torsion bar arrangement alternate test platform loading motor, test starts, motor 7 is pressed speed command and is started, drive torsional oscillation device, due to inertia disc inertia and torsion bar elastic reaction, torsional oscillation device is while rotating, rock by certain frequency, measure the disturbing moment of torsional oscillation device by torque sensor 5, this disturbing moment and the flexible solar wing of simulation are driven identical operating mode loading moment contrast on dynamics simulation testing stand, from wherein reading disturbing moment amplitude to quantify testing stand loading accuracy with frequency departure.
Instruct to drive motor 7 by step velocity as shown in Figure 2, the simulated solar wing is followed the tracks of to day and driven.
When adjusting different torsion frequency as shown in Figure 3, load equivalent inertia being adjusted by the distance of adjustment inertia disc quality, inertia disc power central shaft, adjusting torsion bar equivalent stiffness by adjusting torsion bar end face interfacial area, thus realizing simulating different torsion frequencies.
Measure disturbing moment value as shown in Figure 4 from torque sensor 5, flexible to this disturbing moment and simulation solar wing is driven identical operating mode loading moment contrast on dynamics simulation testing stand, reads disturbing moment amplitude to quantify testing stand loading accuracy with frequency departure.
Its discriminating step is as follows：
Step 1, setting inertia disc and the load of the torsion bar arrangement simulated solar wing, are supported by air-bearing, eliminate frictional force；
Step 2, adjustment inertia disc quality realize different torsion frequencies from torsion bar torsional rigidity；
Step 3, motor carry out the simulated solar wing by Velocity Step Technique and drive；
Step 4, measure disturbance moment of torsion by torque sensor between shaft coupling and motor axle and be used as theoretical value, disturbance moment of torsion is measured by torque sensor and is used as theoretical value, to quantify to pass judgment on the precision of simulation test stand with frequency departure with the amplitude of theoretical value with the moment that simulation test stand under identical operating mode loads.
Torsional oscillation in order to realize different frequency drives process, and by adjusting inertia disc quality, inertia disc to adjust load equivalent inertia with a distance from central shaft, adjusts torsion bar equivalent stiffness by adjusting torsion bar end face sectional area, thus realizing simulating different torsion frequencies.
Simulating flexible solar wing driving thermodynamic nature characteristic is：
, wherein m is inertia disc quality, and l is inertia disc distance center wheelbase from G is torsion bar material modulus of shearing, and L is torsion bar length, and D is torsion bar sectional area.Flexible solar wing is made up of multi-modes, examine one by one by unifrequency during examination, measure disturbance moment of torsion from torque sensor, the deviation of analysis disturbance torque value, disturbance moment of torsion frequency and theoretical value simulates flexible solar wing driving kinetics semi-physical simulation platform precision to pass judgment on.
The inventive method can be used for passing judgment in simulation flexible solar wing driving kinetics or the semi-physical system of various simulated dynamics process.
Claims (3)
1. a kind of simulation flexibility solar wing drives the precision judge method of dynamics simulation testing stand：It is characterized in that, the method is achieved by the steps of：
Step 1, setting inertia disc and the load of the torsion bar arrangement simulated solar wing, are supported by air-bearing, eliminate frictional force；Described torsional oscillation device includes inertia disc [1], air-bearing [2] and torsion bar [3], motor [7] is arranged on pedestal [6], torque sensor [5] is arranged on motor [7] axle head, and shaft coupling [4] connects torsion bar [3] and torque sensor [5]；
Step 2, adjustment inertia disc quality realize different torsion frequencies from torsion bar torsional rigidity；
Step 3, motor carry out the simulated solar wing by Velocity Step Technique and drive；
Step 4, measure disturbance moment of torsion by torque sensor between shaft coupling and motor axle and be used as theoretical value, to quantify to pass judgment on the precision of simulation test stand with frequency departure with the amplitude of theoretical value with the moment that simulation test stand under identical operating mode loads.
2. the flexible solar wing of simulation as claimed in claim 1 drive dynamics simulation testing stand precision judge method it is characterised in that：Simulate the vibration characteristics of different frequency when flexible solar wing drives with inertia disc torsion bar arrangement in described step 2, by adjusting inertia disc quality, the excentric distance of inertia disc adjusts load inertia, adjust torsion bar rigidity by adjusting torsion bar sectional area, thus realizing the adjustment of different torsion frequencies.
3. the flexible solar wing of simulation as claimed in claim 1 drive dynamics simulation testing stand precision judge method it is characterised in that：Motor step velocity instruction simulation solar wing actuating speed is given in described step 3, disturbance moment of torsion is measured by torque sensor and is used as theoretical value, to quantify to pass judgment on the precision of simulation test stand with frequency departure with the amplitude of theoretical value with the moment that simulation test stand under identical operating mode loads.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106970573A (en) * | 2017-05-22 | 2017-07-21 | 上海航天控制技术研究所 | A kind of spacecraft solar wing drive control system of permanent magnet synchronous motor |
| CN107144409A (en) * | 2017-06-15 | 2017-09-08 | 重庆大学 | Rotating flexible beam Coupling System of Flexible Structures And Rigid Body vibration measurement control device and method |
| CN107389364A (en) * | 2017-06-12 | 2017-11-24 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of inertia load weighted platform |
| CN109466809A (en) * | 2018-11-28 | 2019-03-15 | 北京控制工程研究所 | One kind can configure assemblnig flexible simulator |
| CN110263413A (en) * | 2019-06-14 | 2019-09-20 | 庆安集团有限公司 | A kind of optimum design method of torsion-bar spring |
| CN110703588A (en) * | 2019-11-15 | 2020-01-17 | 上海航天控制技术研究所 | Space station solar wing reliable redundancy control system and method based on multi-instruction input |
| CN112444365A (en) * | 2020-11-30 | 2021-03-05 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency modal testing method based on force hammer swing method and laser Doppler method |
| CN114088375A (en) * | 2021-11-25 | 2022-02-25 | 长光卫星技术有限公司 | Solar wing load simulation device |
| 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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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106970573B (en) * | 2017-05-22 | 2019-03-15 | 上海航天控制技术研究所 | A kind of spacecraft solar wing drive control system of permanent magnet synchronous motor |
| CN106970573A (en) * | 2017-05-22 | 2017-07-21 | 上海航天控制技术研究所 | A kind of spacecraft solar wing drive control system of permanent magnet synchronous motor |
| CN107389364B (en) * | 2017-06-12 | 2020-04-07 | 中国航空工业集团公司西安飞行自动控制研究所 | Inertial load loading platform |
| CN107389364A (en) * | 2017-06-12 | 2017-11-24 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of inertia load weighted platform |
| CN107144409A (en) * | 2017-06-15 | 2017-09-08 | 重庆大学 | Rotating flexible beam Coupling System of Flexible Structures And Rigid Body vibration measurement control device and method |
| CN107144409B (en) * | 2017-06-15 | 2019-02-15 | 重庆大学 | Rotating flexible beam Coupling System of Flexible Structures And Rigid Body vibration measurement control device and 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 |
| CN110263413A (en) * | 2019-06-14 | 2019-09-20 | 庆安集团有限公司 | A kind of optimum design method of torsion-bar spring |
| CN110703588A (en) * | 2019-11-15 | 2020-01-17 | 上海航天控制技术研究所 | Space station solar wing reliable redundancy control system and method based on multi-instruction input |
| CN112444365A (en) * | 2020-11-30 | 2021-03-05 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency modal testing method based on force hammer swing method and laser Doppler method |
| CN112444365B (en) * | 2020-11-30 | 2023-08-29 | 哈尔滨工业大学 | Satellite solar wing substrate unfolding low-frequency mode testing method |
| CN114088375A (en) * | 2021-11-25 | 2022-02-25 | 长光卫星技术有限公司 | Solar wing load simulation device |
| 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 |
| CN114414145B (en) * | 2021-12-21 | 2024-03-12 | 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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Inventor after: Meng Guang Inventor after: Zhang Chongfeng Inventor after: Zou Huaiwu Inventor after: Shi Junwei Inventor after: Zhang Lingxuan Inventor after: Gao Songtao Inventor after: Qian Zhiyuan Inventor after: Wang Zhiyi Inventor after: Chen Baodong Inventor before: Zou Huaiwu Inventor before: Shi Junwei Inventor before: Zhang Lingxuan Inventor before: Qian Zhiyuan Inventor before: Wang Zhiyi Inventor before: Chen Baodong |
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