CN106394945A - Solar wing flexible simulator - Google Patents
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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 invention relates to the technical field of spaceflight, in particular to a solar wing flexibility simulator.
Background
With the increasing functions of modern spacecrafts, the complexity of the spacecrafts is increased continuously, and flexible accessories such as large-scale solar sailboards are increased continuously. Because the flexible accessories are made of light materials with low rigidity, the spacecraft is easy to generate large-amplitude vibration under the action of various propelling forces when flying in orbit, the vibration of the flexible accessories and the motion of the spacecraft body are mutually coupled, the attitude stability and the orientation precision of the spacecraft can be influenced, and even instruments are damaged, so that the spacecraft fails. Therefore, the design of the solar wing flexible simulator for carrying out physical simulation experiments on the ground has great significance in researching the influence of the flexible accessories on the spacecraft body structure.
The solar wing has the characteristics of light weight and high flexibility, is easy to be interfered by the outside to generate elastic vibration, and the simulators in the prior ground simulation experiment system are mainly divided into an active simulator and a passive simulator according to the characteristic. The active mode simulates elastic vibration generated after the solar wing is interfered by adding an excitation part, and controls the vibration form required to be generated through an electric control system; the passive type does not rely on external excitation, but simulates the mode shape and the moment of inertia of the solar wing by adjusting the structure of the simulator. The existing solar wing simulator has the following defects:
(1) the active simulator generates a required vibration form through the excitation component, and the rotational inertia of the active simulator is almost unchanged when the vibration is changed, so that the characteristics of different modes of the solar wing of the spacecraft, which correspond to different rotational inertias, cannot be simulated, and the simulation reliability is low.
(2) The spacecraft solar wing has low rigidity, high modal order and dense low frequency, and the conventional simulator has small general geometric dimension and high modal frequency and is difficult to realize accurate simulation of frequency. In addition, the space environment has no external resistance, the modal amplitude of each order of the solar wing is large, the vibration of the existing simulator is rapidly weakened along with the modal order, and the real simulation of the modal amplitude of each order cannot be realized.
(3) In actual tests, most of the modes of the solar wing do not need to be concerned, and only the mode with larger influence on the system needs to be simulated, so that the selective mode simulation cannot be provided in the prior art.
(4) In practical application, mode parameters such as torsion and bending are required to be set respectively, and the prior art cannot realize the mode parameters.
Therefore, the above-mentioned bottleneck in the prior art makes a solar wing flexible simulator which is more efficient and has higher simulation precision and can solve the above-mentioned problems become a great need.
Disclosure of Invention
The invention provides a solar wing flexibility simulator, which adopts a shafting, a beam, a balancing weight, an elastic structure and a torque sensor to perform passive simulation, can truly present the characteristics of different modes of a spacecraft solar wing corresponding to different rotary inertias, and has higher simulation reliability; the first-order modes of different simulation components are used for simulating the first-order, sixth-order and twelfth-order modes of the solar wing, which have large influence on the attitude stability of the spacecraft, so that the characteristics of low modal frequency and strong amplitude of each order of the solar wing are accurately embodied; and the independent adjustment of the bending mode and the torsion mode is realized by arranging various adjusting parts, the simulation precision is greatly improved, and the method has wide application prospect in engineering application.
The invention provides a solar wing flexible simulator, which comprises a base, a first simulation component, a second simulation component, a third simulation component and a torque sensor, wherein the base is provided with a first end and a second end; the first simulation component, the second simulation component and the third simulation component are sequentially connected and are arranged on the air floatation platform through a base connected with the first simulation component;
the first simulation component comprises a first cross beam, a first rotating shaft, a first spring assembly and a lower balancing weight; the lower balancing weights are symmetrically arranged on two sides of the first cross beam and used for adjusting the moment of inertia of the first simulation component rotating around the first rotating shaft to serve as the simulation value of the first-order modal moment of inertia of the solar wing and primarily adjusting the first-order modal frequency of the first simulation component; the first spring assembly is arranged on the first rotating shaft and used for finely adjusting the first-order modal frequency of the first simulation component to serve as a simulation value of the first-order modal frequency of the solar wing;
the second simulation component comprises a second cross beam, a second rotating shaft, a second spring assembly and a middle balancing weight; the middle balancing weights are symmetrically arranged on two sides of the second cross beam and used for adjusting the moment of inertia of the second simulation component rotating around the second rotating shaft to serve as a simulation value of the sixth-order modal moment of inertia of the solar wing and primarily adjusting the first-order modal frequency of the second simulation component; the second spring assembly is arranged on the second rotating shaft and used for finely adjusting the first-order modal frequency of the second simulation component to serve as a simulation value of the sixth-order modal frequency of the solar wing;
the third simulation component comprises a third cross beam, a third rotating shaft, a third spring assembly and an upper balancing weight; the upper balancing weights are symmetrically arranged on two sides of the third cross beam and used for adjusting the rotational inertia of the third simulation component rotating around the third rotating shaft to serve as the simulation value of the twelfth-order modal rotational inertia of the solar wing and primarily adjusting the first-order modal frequency of the third simulation component; the third spring assembly is arranged on the third rotating shaft and used for finely adjusting the first-order modal frequency of the third simulation component to be used as a simulation value of the twelfth-order modal frequency of the solar wing;
the moment sensor is arranged at the position, close to the air floatation platform, of the first rotating shaft and used for measuring the moment output to the air floatation platform by the solar wing flexible simulator.
Preferably, the first rotating shaft, the second rotating shaft and the third rotating shaft are collinear and are perpendicular to the air floating platform.
Preferably, the lengths of the first beam, the second beam and the third beam are reduced in sequence.
Preferably, the simulator further comprises:
the first fastening part is arranged at the joint of the first cross beam and the first rotating shaft and used for adjusting the second-order modal frequency of the first analog component;
the second fastening part is arranged at the joint of the second cross beam and the second rotating shaft and used for adjusting the second-order modal frequency of the second analog component;
and the third fastening part is arranged at the joint of the third cross beam and the third rotating shaft and used for adjusting the second-order modal frequency of the third analog component.
Preferably, after the adjustment is completed, the second order modal frequency of the first analog component is greater than the first order modal frequencies of the second analog component and the third analog component, and the second order modal frequency of the second analog component is greater than the first order modal frequency of the third analog component.
Preferably, any one of the first spring assembly, the second spring assembly and the third spring assembly comprises: the assembly comprises an assembly main body and 8 springs, wherein the assembly main body is provided with 8 clamping holes and 2U-shaped grooves; the assembly comprises an assembly body, a spring and a spring, wherein the assembly body is a straight quadrangular prism, and two opposite surfaces of the assembly body are respectively provided with 4 springs; one end of the spring is fixed in the clamping hole, and the other end of the spring is movably connected with the U-shaped groove.
Preferably, the first rotating shaft, the second rotating shaft and the third rotating shaft are all angular contact ball bearings.
Preferably, the simulator further comprises:
the first bending mode adjusting part is arranged in the middle of the side face of the first cross beam, is elastically connected with two ends of the first cross beam and is used for adjusting third-order mode frequency of the first simulation component;
the second bending mode adjusting part is arranged in the middle of the side face of the second cross beam, is elastically connected with two ends of the second cross beam and is used for adjusting third-order mode frequency of the second simulation component;
and the third bending mode adjusting part is arranged in the middle of the side surface of the third cross beam, is elastically connected with two ends of the third cross beam and is used for adjusting the third-order mode frequency of the third simulation component.
Preferably, the simulator further comprises:
the first bending mode adjusting part is arranged in the middle of the upper surface of the first cross beam, is elastically connected with two ends of the first cross beam and is used for adjusting the fourth-order mode frequency of the first simulation component;
the second bending mode adjusting part is arranged in the middle of the upper surface of the second cross beam, is elastically connected with two ends of the second cross beam and is used for adjusting the fourth-order mode frequency of the second simulation component;
and the third bending mode adjusting part is arranged in the middle of the upper surface of the third cross beam, is elastically connected with two ends of the third cross beam and is used for adjusting the fourth-order mode frequency of the third simulation component.
Preferably, the first-order mode shape of the first analog component, the second analog component and the third analog component is torsion around the Y direction, the second-order mode shape is torsion around the Z direction, the third-order mode shape is bending around the Y direction, and the fourth-order mode shape is bending around the Z direction;
the Y direction is the direction of the first rotating shaft, and the Z direction is the direction perpendicular to the first rotating shaft and the first cross beam.
According to the technical scheme, the solar wing flexible simulator provided by the invention can realize accurate simulation of the solar wing of the spacecraft and perform targeted simulation on several concerned modes. The invention approaches to the solar wing in working state in the aspects of frequency, amplitude and the like, can independently adjust the torsional mode and the bending mode, and has stronger practicability.
Drawings
FIG. 1 is a schematic diagram of a solar wing flexibility simulator configuration of the present invention;
FIG. 2 is a schematic view of the counterweight of the present invention;
FIG. 3 is a schematic view of the spring assembly installation of the present invention;
FIG. 4 is a schematic diagram of the spring assembly of the present invention;
FIG. 5 is a schematic view of a first order mode shape of a first analog component of the present invention;
FIG. 6 is a second order mode shape schematic of the first analog component of the present invention;
FIG. 7 is a third order mode shape schematic of the first analog component of the present invention;
fig. 8 is a fourth order mode shape diagram of the first analog component of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings by way of examples of preferred embodiments. It should be noted, however, that the numerous details set forth in the description are merely for the purpose of providing the reader with a thorough understanding of one or more aspects of the present invention, which may be practiced without these specific details.
The inventor considers that the spacecraft is easy to generate large-amplitude vibration under the action of various propelling forces when flying in orbit, the vibration of the flexible accessory is mutually coupled with the motion of the spacecraft body, the attitude stability and the orientation precision of the spacecraft are influenced, and even instruments are damaged to cause the spacecraft to fail. Therefore, a solar wing flexible simulator needs to be designed to perform a physical simulation experiment on the ground to study the influence of the flexible accessories on the spacecraft body structure.
Currently, simulators in ground simulation experiment systems are mainly divided into an active simulator and a passive simulator. The active mode simulates elastic vibration generated after the solar wing is interfered by adding an excitation part, and controls the vibration mode required to be generated through an electric control system. The existing active simulator comprises the following methods:
(1) the flexible simulator generates high-frequency vibration by inputting the electric vibration exciter with controllable thrust, and data collection and processing are carried out by the accelerometer and the strain gauge.
(2) And an air injection device is arranged on the test bed, and the nozzle of the air injection device injects air to generate a reaction force to drive the satellite to generate angular motion, so that the flexible plate generates vibration, and the vibration mode of the flexible plate is measured in real time through a vibration measurement device to perform flexible dynamics simulation.
The passive type does not rely on external excitation, but simulates the mode shape and the moment of inertia of the solar wing by adjusting the structure of the simulator.
The existing solar wing simulator has the following defects:
(1) the active simulator generates a required vibration form through the excitation component, and the rotational inertia of the active simulator is almost unchanged when the vibration is changed, so that the characteristics of different modes of the solar wing of the spacecraft, which correspond to different rotational inertias, cannot be simulated, and the simulation reliability is low.
(2) The spacecraft solar wing has low rigidity, high modal order and dense low frequency, and the conventional simulator has small general geometric dimension and high modal frequency and is difficult to realize accurate simulation of frequency. In addition, the space environment has no external resistance, the modal amplitude of each order of the solar wing is large, the vibration of the existing simulator is rapidly weakened along with the modal order, and the real simulation of the modal amplitude of each order cannot be realized.
(3) In actual tests, most of the modes of the solar wing do not need to be concerned, and only the mode with larger influence on the system needs to be simulated. For example, in recent years, research on solar wing vibration indicates that 1, 6, and 12-order modes of the solar wing are easily coupled with a spacecraft body, thereby affecting the attitude stability and positioning accuracy of the spacecraft, and are not easily damped by an active vibration control method or a passive vibration control method, so that it is necessary to select the modes for targeted simulation, but the prior art cannot provide the selective simulation.
(4) In practical application, mode parameters such as torsion and bending are required to be set respectively, and the prior art cannot realize the mode parameters.
Aiming at the problems, the inventor of the invention adopts a plurality of simulation components consisting of the cross beam, the rotating shaft, the spring component and the counterweight block to respectively simulate each mode of the solar wing, and simulates the high-order mode of the solar wing by the low-order mode of each component, thereby realizing the real reproduction of the frequency and the amplitude of the solar wing. And the torsion and bending modes can be freely adjusted through different adjusting devices, so that the adjusting precision of the parameters of the simulator is greatly improved. Meanwhile, the solar wing simulator can truly simulate the characteristics of different modes of the solar wing corresponding to different rotational inertia.
It will be understood that the terms "first," "second," and the like, as used herein, are used herein to describe various elements, but these elements are not limited by the above terms. The above terms are only used to distinguish one element from another. For example, without departing from the scope of the invention, a first analog component may be referred to as a second analog component, or a second analog component may be referred to as a first analog component, both the first analog component and the second analog component being analog components, but not the same analog component.
In addition, the terminology used to refer to an orientation is conventionally dependent upon the orientation in which it is used in its operating state. For example, the upper, middle and lower counterweights are described in terms of relative positions in operation, and the lateral and upper surfaces of the beam are also referred to the beam in operation. Particularly, the three components, namely the direction of the rotating shaft, the direction of the cross beam and the direction perpendicular to the rotating shaft and the cross beam, form a three-dimensional rectangular coordinate system.
Fig. 1 shows a solar wing flexible simulator structure of the present invention, and referring to fig. 1, the solar wing flexible simulator includes a base 4, a first simulation member 1, a second simulation member 2, a third simulation member 3, and a moment sensor (not shown in the figure).
Specifically, the first simulation member 1, the second simulation member 2, and the third simulation member 3 are sequentially stacked from bottom to top, and each of them is independently rotatable around an axis. The first simulation element 1 is connected to the base 4 at the lowermost position. Typically, the base 4 is made of cast aluminum, which is relatively light in weight. The solar wing flexible simulator is mounted on the single-shaft air floatation platform through the base 4 in a common bolt connection mode.
The three analog components are similar in structure. The first simulation member 1 includes a first beam 11, a first rotating shaft, a first spring assembly, and a lower weight 12. A first rotating shaft is arranged in the middle of the first cross beam 11, lower balancing weights 12 are symmetrically arranged on two sides of the first cross beam 11, and a first spring assembly is arranged on the first rotating shaft. The spring assemblies are mounted as shown in fig. 3 (three spring assemblies are mounted in a similar manner). The lower counterweight 12 is made of thin metal sheet, the middle part is positioned by bolts, the periphery is fixed by bolts, the installation mode is shown in figure 2, and the materials and the installation mode of the upper counterweight, the middle counterweight and the lower counterweight are similar.
The moment of inertia of the first simulation member 1 about the first axis of rotation can be adjusted by changing the number of the lower counter weights 12, and the first-order modal frequency of the first simulation member 1 is preliminarily adjusted. The first spring assembly is used to fine tune the first order modal frequency of the first analogue component 1. The moment of inertia and the first-order modal frequency of the first simulation component 1 are used for simulating the moment of inertia and the frequency of the first-order modal of the solar wing, respectively.
The second simulation part 2 includes a second beam 21, a second rotating shaft, a second spring assembly, and a middle weight 22. The middle part of the second beam 21 is provided with a second rotating shaft, the middle balancing weights 22 are symmetrically arranged at two sides of the second beam 21, and the second spring assembly is arranged at the second rotating shaft. The middle counter weight 22 is used to adjust the moment of inertia of the second analog component 2 about the second rotation axis, and primarily adjust the first-order modal frequency of the second analog component 2. The second spring assembly is used to fine tune the first order modal frequency of the second analogue component 2. The moment of inertia and the first-order modal frequency of the second simulation component 2 are respectively used for simulating the moment of inertia and the frequency of the sixth-order modal of the solar wing.
The third simulation member 3 includes a third beam 31, a third rotation shaft, a third spring assembly, and an upper weight 32. The middle part of the third beam 31 is provided with a third rotating shaft, the upper balancing weights 32 are symmetrically arranged at two sides of the third beam 31, and the third spring assembly is arranged at the third rotating shaft. The upper balancing weight 32 is used to adjust the moment of inertia of the third analog component 3 about the third rotation axis, and primarily adjust the first-order modal frequency of the third analog component 3. The third spring assembly is used to fine tune the first order modal frequency of the third analogue component 3. The moment of inertia and the first-order modal frequency of the third simulation component 3 are respectively used for simulating the moment of inertia and the frequency of the twelfth-order modal of the solar wing.
The shafting provides the support to superstructure, considers the requirement of bearing capacity and coefficient of friction, and first pivot, second pivot, third pivot all adopt angular contact ball bearing. Furthermore, the bearing in the embodiment of the invention is an angular contact ball bearing with the model number 7208B, the inner diameter D is 40mm, the outer diameter D is 80mm, the width B is 18mm, the rated dynamic load is 32500N, and the rated static load is 23500N. The first rotating shaft, the second rotating shaft and the third rotating shaft are collinear and are vertical to the air floating platform.
Preferably, the first spring assembly, the second spring assembly and the third spring assembly are similar in structure, wherein each spring assembly comprises an assembly body and 8 springs. The spring assembly structure is as shown in fig. 4, referring to fig. 4, the assembly body is a straight quadrangular prism, 8 clamping holes and 2U-shaped grooves are arranged, and 4 springs are respectively arranged on two opposite surfaces. One end of the spring is fixed in the clamping hole, and the other end of the spring is movably connected with the U-shaped groove. The clamping manner shown in the figure can ensure that the mounting position of the spring is accurate and convenient to adjust. When the frequency-adjustable frequency converter works, the length of the spring is changed through the U-shaped groove, so that the mode frequency is finely adjusted.
The moment sensor is arranged at the position, close to the air floatation platform, of the first rotating shaft, is generally not more than 100mm away from the air floatation platform, and is used for measuring the moment output to the air floatation platform by the solar wing flexible simulator.
During the use, at first adjust the balancing weight and satisfy inertia's requirement, realize the preliminary regulation of simulation part first order frequency simultaneously, later realize the fine tuning of first order frequency through spring assembly.
Through the arrangement, the solar wing flexible simulator disclosed by the invention achieves the following technical effects:
(1) the passive simulation is adopted to embody the characteristics that different modes of the solar wing correspond to different rotational inertia.
(2) Three independent simulation components are adopted to realize respective simulation of 1, 6 and 12-order modes which seriously affect the attitude of the spacecraft.
(3) The high-order mode of the solar wing is simulated by the first-order mode of the simulation component, so that the mode amplitude and the natural frequency are consistent with the actual value, and the defects that the natural frequency of a simulator in the prior art is too high, the amplitude is small and the simulator is deviated from real data are overcome.
In the preferred embodiment of the present invention, the lengths of the first beam 11, the second beam 21 and the third beam 31 are sequentially reduced, so that the natural frequencies of the three are sequentially increased, thereby facilitating the adjustment of the modal frequency.
In practical application, for the convenience of follow-up modal frequency regulation through balancing weight and spring assembly, the length of first crossbeam, second crossbeam, third crossbeam needs to be rationally set up to reduce modal parameter regulation time, increase system's practicality. Therefore, the method comprises the steps of firstly, obtaining the relationship between the length of a cross beam with the cross section of 120mm x 120mm and the first-order modal frequency by utilizing a finite element analysis technology; then, 1, 6 and 12 order modal frequencies of various solar wings are counted to obtain universal data, for example, the 1, 6 and 12 order modal frequencies of a representative solar wing are 0.0679Hz, 0.124Hz and 0.1825Hz respectively; and then obtaining the optimal beam length relation of the fitting result by adopting an iterative regression algorithm. The invention provides the following formula, which can be suitable for 1, 6 and 12-order modal simulation of various solar wings, and realizes that each modal frequency of the cross beam is close to a simulation value, so that the subsequent fine adjustment difficulty is reduced, and the adjustment process of a simulator is accelerated.
Wherein L is1、L2、L3Respectively a first beam and a second beamAnd the length of the third beam, wherein the cross section shapes and the areas of the first beam, the second beam and the third beam are required to be the same by a formula.
In the preferred embodiment of the present invention, the lengths of the first beam, the second beam and the third beam are 6 meters, 5.841 meters and 1.5 meters in sequence, which is in accordance with formula 1.
The first-order mode shapes of the first, second, and third simulation members are twisted around the Y direction, and simulate the 1 st, 6 th, and 12 th-order modes of the solar wing. In order to adjust the second order modal frequency of the first, second and third analog components, the invention is provided with a first, second and third fastening parts.
Specifically, the first fastening portion is installed at a position where the first beam 11 is connected to the first rotating shaft, and is used for adjusting the second-order modal frequency of the first analog component 1. The second fastening portion is mounted at a joint of the second beam 21 and the second rotating shaft, and is used for adjusting the second-order modal frequency of the second analog component 2. The third fastening portion is mounted at a joint of the third beam 31 and the third rotating shaft, and is used for adjusting the second-order modal frequency of the third analog component 3.
Generally, the second order mode modes of the first, second and third simulation components are torsional around the Z direction, and corresponding torsional mode modes of the solar wing are simulated.
Through the arrangement, the independent adjustment of the second-order modal frequency of the simulator is realized, and the simulation precision of the solar wing modal is improved.
In engineering application, in order to prevent interference among the three analog components, the second-order modal frequency of the first analog component 1 is adjusted to be greater than the first-order modal frequencies of the second analog component 2 and the third analog component 3, and the second-order modal frequency of the second analog component 2 is adjusted to be greater than the first-order modal frequency of the third analog component 3.
Preferably, the solar wing flexible simulator is further provided with a first bending mode adjusting part, a second bending mode adjusting part and a third bending mode adjusting part so as to adjust the third-order modal frequency of each simulation component.
Specifically, the first bending mode adjusting part, the second bending mode adjusting part and the third bending mode adjusting part are elastic structures with adjustable rigidity. The first bending mode adjusting part is arranged in the middle of the side face of the first cross beam 11, is elastically connected with two ends of the first cross beam 11, and is used for adjusting third-order mode frequency of the first simulation component 1. The second bending mode adjusting part is arranged in the middle of the side face of the second cross beam 21, is elastically connected with two ends of the second cross beam 21, and is used for adjusting third-order mode frequency of the second simulation component 2. The third bending mode adjusting part is arranged in the middle of the side face of the third cross beam 31, is elastically connected with two ends of the third cross beam 31, and is used for adjusting the third-order mode frequency of the third analog component 3.
In a preferred embodiment of the invention, the third-order mode shape of the analog component is curved around the Y-direction, i.e. the direction of the bending deformation is perpendicular to the Y-direction. And the third-order modal frequency of each simulation component is used for simulating the corresponding mode of the bending mode of the solar wing.
Through the arrangement, the third-order modal frequency of the simulator is independently adjusted, so that the simulation of the torsional mode and the simulation of the bending mode are separated, and the decoupling torsional mode and the decoupling bending mode of the solar wing are accurately simulated respectively.
In a preferred embodiment of the present invention, the solar wing flexible simulator further includes a first bending mode adjusting portion disposed in the middle of the upper surface of the first beam 11, a second bending mode adjusting portion disposed in the middle of the upper surface of the second beam 21, and a third bending mode adjusting portion disposed in the middle of the upper surface of the third beam 31, which are respectively used for adjusting the fourth-order modal frequency of the corresponding simulation component.
The bending mode adjusting parts are elastic structures with adjustable rigidity and are elastically connected with the two sides of the beam. Preferably, the fourth-order mode shape of the analog component is curved around the Z-direction, i.e. the direction of the bending deformation is perpendicular to the Z-direction. The fourth order modal frequency of each simulation component is used for simulating the corresponding mode of the bending mode of the solar wing.
After the solar wing flexibility simulator is adjusted, modal analysis is carried out on the solar wing flexibility simulator, and specific data of each order of modes can be obtained. Figures 5-8 show the first, second, third and fourth order mode shapes, respectively, of the first analogue component, from which the respective mode shapes can be seen as described above, with the horizontal direction being the X-direction and the vertical direction being the Y-direction. The second and third analog components have similar vibration modes as the first analog component.
Through the arrangement, the fourth-order modal frequency of the simulator is independently adjusted, so that the simulation of the torsional mode and the simulation of the bending mode are separated, and the decoupling torsional mode and the decoupling bending mode of the solar wing are accurately simulated respectively.
In practical application, the torque generated by the spring to the shaft can be calculated through the following formula to judge whether the torque meets the requirement:
f ═ Δ L × K equation 2
M ═ F × R formula 3
Wherein M is torque, F is tension generated by the spring, R is turning radius, K is spring stiffness, and Delta L is spring deformation.
Calculating the friction torque through a formula 4, and judging whether the requirements are met:
wherein M is1Mu is friction torque, d is bearing inner diameter, and f is bearing capacity.
The modal damping ratio can be calculated from equation 5:
where ζ is the damping ratio, and a1 and a2 are the periodic amplitudes.
According to the solar wing flexible simulator provided by the invention, three simulation parts are stacked in the center of the single-shaft air bearing table, and the torque sensor is arranged between the simulation parts and the single-shaft air bearing table and used for measuring the torque of the simulator on the rotary table, so that the influence of the solar wing on the spacecraft body is simulated. When the single-shaft air bearing table simulates the spacecraft body to move, the flexible simulation structure can be disturbed to generate vibration, the magnitude of the moment is calculated through the output signal of the moment sensor, and the influence of different rotational inertia and different modal frequencies of the simulator on the spacecraft body structure can be analyzed. On the basis, the solar wing structure can be optimally designed to reduce the interference of the solar wing structure on the spacecraft body. In addition, the invention does not need to design a control system and a power system, and compared with the prior art, the invention is simpler and more convenient and easier and has lower cost.
Those skilled in the art will appreciate that all or part of the steps in the method for implementing the above embodiments may be implemented by relevant hardware instructed by a program, and the program may be stored in a computer readable storage medium, such as: ROM/RAM, magnetic disk, optical disk, etc.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that those skilled in the art can make various improvements and modifications without departing from the principle of the present invention, and these improvements and modifications should also be construed as the protection scope of the present invention.
Claims (10)
1. A solar wing flexible simulator is characterized by comprising a base, a first simulation component, a second simulation component, a third simulation component and a torque sensor; wherein,
the first simulation component, the second simulation component and the third simulation component are sequentially connected and are arranged on the air floatation platform through a base connected with the first simulation component;
the first simulation component comprises a first cross beam, a first rotating shaft, a first spring assembly and a lower balancing weight; the lower balancing weights are symmetrically arranged on two sides of the first cross beam and used for adjusting the moment of inertia of the first simulation component rotating around the first rotating shaft to serve as the simulation value of the first-order modal moment of inertia of the solar wing and primarily adjusting the first-order modal frequency of the first simulation component; the first spring assembly is arranged on the first rotating shaft and used for finely adjusting the first-order modal frequency of the first simulation component to serve as a simulation value of the first-order modal frequency of the solar wing;
the second simulation component comprises a second cross beam, a second rotating shaft, a second spring assembly and a middle balancing weight; the middle balancing weights are symmetrically arranged on two sides of the second cross beam and used for adjusting the moment of inertia of the second simulation component rotating around the second rotating shaft to serve as a simulation value of the sixth-order modal moment of inertia of the solar wing and primarily adjusting the first-order modal frequency of the second simulation component; the second spring assembly is arranged on the second rotating shaft and used for finely adjusting the first-order modal frequency of the second simulation component to serve as a simulation value of the sixth-order modal frequency of the solar wing;
the third simulation component comprises a third cross beam, a third rotating shaft, a third spring assembly and an upper balancing weight; the upper balancing weights are symmetrically arranged on two sides of the third cross beam and used for adjusting the rotational inertia of the third simulation component rotating around the third rotating shaft to serve as the simulation value of the twelfth-order modal rotational inertia of the solar wing and primarily adjusting the first-order modal frequency of the third simulation component; the third spring assembly is arranged on the third rotating shaft and used for finely adjusting the first-order modal frequency of the third simulation component to be used as a simulation value of the twelfth-order modal frequency of the solar wing;
the moment sensor is arranged at the position, close to the air floatation platform, of the first rotating shaft and used for measuring the moment output to the air floatation platform by the solar wing flexible simulator.
2. The simulator of claim 1, wherein the first axis, the second axis and the third axis are collinear and perpendicular to the air bearing platform.
3. The simulator of claim 2 wherein the first, second and third beams decrease in length in sequence.
4. The simulator of claim 3, further comprising:
the first fastening part is arranged at the joint of the first cross beam and the first rotating shaft and used for adjusting the second-order modal frequency of the first analog component;
the second fastening part is arranged at the joint of the second cross beam and the second rotating shaft and used for adjusting the second-order modal frequency of the second analog component;
and the third fastening part is arranged at the joint of the third cross beam and the third rotating shaft and used for adjusting the second-order modal frequency of the third analog component.
5. The simulator of claim 4, wherein after tuning is complete, the second order modal frequency of the first simulation component is greater than the first order modal frequencies of the second and third simulation components, and the second order modal frequency of the second simulation component is greater than the first order modal frequency of the third simulation component.
6. The simulator of claim 5, any of the first spring assembly, the second spring assembly, and the third spring assembly comprising: the assembly comprises an assembly main body and 8 springs, wherein the assembly main body is provided with 8 clamping holes and 2U-shaped grooves; the assembly comprises an assembly body, a spring and a spring, wherein the assembly body is a straight quadrangular prism, and two opposite surfaces of the assembly body are respectively provided with 4 springs; one end of the spring is fixed in the clamping hole, and the other end of the spring is movably connected with the U-shaped groove.
7. The simulator as claimed in any one of claims 1 to 6, wherein the first, second and third shafts each employ angular contact ball bearings.
8. The simulator of claim 7, further comprising:
the first bending mode adjusting part is arranged in the middle of the side face of the first cross beam, is elastically connected with two ends of the first cross beam and is used for adjusting third-order mode frequency of the first simulation component;
the second bending mode adjusting part is arranged in the middle of the side face of the second cross beam, is elastically connected with two ends of the second cross beam and is used for adjusting third-order mode frequency of the second simulation component;
and the third bending mode adjusting part is arranged in the middle of the side surface of the third cross beam, is elastically connected with two ends of the third cross beam and is used for adjusting the third-order mode frequency of the third simulation component.
9. The simulator of claim 8, further comprising:
the first bending mode adjusting part is arranged in the middle of the upper surface of the first cross beam, is elastically connected with two ends of the first cross beam and is used for adjusting the fourth-order mode frequency of the first simulation component;
the second bending mode adjusting part is arranged in the middle of the upper surface of the second cross beam, is elastically connected with two ends of the second cross beam and is used for adjusting the fourth-order mode frequency of the second simulation component;
and the third bending mode adjusting part is arranged in the middle of the upper surface of the third cross beam, is elastically connected with two ends of the third cross beam and is used for adjusting the fourth-order mode frequency of the third simulation component.
10. The simulator of claim 9, wherein the first order mode shape of the first, second and third simulation components is torsional about the Y direction, the second order mode shape is torsional about the Z direction, the third order mode shape is bending about the Y direction, and the fourth order mode shape is bending about the Z direction;
the Y direction is the direction of the first rotating shaft, and the Z direction is the direction perpendicular to the first rotating shaft and the first cross beam.
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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 |
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