Multi-mechanical parameter adjustable solar wing simulator capable of reflecting asymmetry

Abstract

The invention provides a multi-mechanical parameter adjustable solar wing simulator capable of reflecting asymmetry. The multi-mechanical parameter adjustable solar wing simulator comprises a main beam, a side beam, a shaft end mass block assembly, a side end mass block assembly and an offset adjusting block, the shaft end mass block assembly is installed at the end of the main beam, the two ends of the side beam are each provided with one side end mass block assembly, and the offset adjusting blocks are installed on the two sides of the side beam and used for connecting the main beam and the side beam. In an initial state, the two side end mass block assemblies and the two offset adjusting blocks are in central symmetry; the offset adjusting block can realize self position adjustment and is used for realizing adjustment of the asymmetry degree of the simulation piece; the mass of the shaft end mass block assembly can be adjusted, and the shaft end mass block assembly is used for adjusting the rotational inertia around the x axis and the z axis and the low-order mode of the simulation piece. And the position and the mass of the side end mass can be adjusted to realize the adjustment of the rotational inertia of the simulation piece. The problems that an existing simulation piece is insufficient in reaction to the dynamic characteristics of the solar wing, and asymmetry cannot be accurately reflected are solved.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace technology, and particularly relates to a multi-mechanical parameter adjustable solar wing simulation component that can reflect asymmetry. Background Art

[0002] To meet the energy requirements during on-orbit operation, spacecraft are usually equipped with solar wings to convert solar energy into electrical energy. During on-orbit operation, the solar wings will experience complex dynamic environments such as vibration and shock. The vibration generated will be transmitted to the spacecraft. Due to the special vacuum and micro-low gravity environment in space, once the structure vibrates, it is very difficult to attenuate, which may affect the normal operation of the spacecraft system, reduce the reliability of the entire system, and even cause structural damage. In addition, the vibration of the solar wings will also cause the control mechanism to work frequently, consume excessive energy, and affect the lifespan of the spacecraft. As the energy supply unit of the spacecraft, whether the solar wings can work normally is directly related to the success or failure of the space mission. Therefore, it is very necessary to carry out ground tests on the solar wings to study their dynamic characteristics.

[0003] Currently, the development of ground dynamic tests for solar wings has many limitations. On the one hand, to meet the increasing energy requirements of complex space missions such as deep space exploration and manned spaceflight, solar wings are gradually developing towards large-scale and flexible. If real solar wings are used for testing, the cost is too high and the product safety is difficult to guarantee. Considering the huge environmental differences from space, the development of ground tests requires the installation of devices such as vacuum chambers and gravity unloading. The complex structure of the solar wings means a complex gravity unloading system, and the cost of supporting facilities is also unacceptable. On the other hand, the existing solar wing simulation components are roughly divided into rigid and flexible types. The rigid simulation components can only simulate the inertia information of the solar wings. Although the existing flexible simulation components can reflect the inertia and low-order dynamic characteristics of the solar wings, no design that can simulate the asymmetry (geometric / stiffness / mass asymmetry) of the solar wings has been seen. Taking the American Ultraflex-175 type circular solar wing as an example, the out-of-plane first-order antisymmetric mode and the out-of-plane first-order symmetric mode frequencies are 1.29 Hz and 2.08 Hz respectively, with obvious asymmetry. Therefore, the solar wing simulation component should have the ability to reflect asymmetry. Summary of the Invention

[0004] In view of this, the present invention aims to propose a multi-mechanical parameter adjustable solar wing simulation component that can reflect asymmetry to solve the problem that the existing simulation components are insufficient in reflecting the dynamic characteristics of the solar wings and cannot accurately reflect asymmetry.

[0005] To achieve the above object, the technical solution of the present invention is realized as follows: A multi-mechanical parameter adjustable solar wing simulation component that can reflect asymmetry, including a main beam, side beams, shaft end mass block assemblies, side end mass block assemblies, and offset adjustment blocks; The main beam and the side beam are connected to form a T-shaped beam structure. The shaft-end mass block assembly is installed at the end of the main beam, and a side-end mass block assembly is installed at each end of the side beam. The offset adjustment blocks are installed on both sides of the side beam and are used to connect the main beam and the side beam. In the initial state, the two side-end mass block assemblies and the two offset adjustment blocks are centrosymmetric. The offset adjustment blocks can adjust their own positions to adjust the degree of asymmetry of the simulation component. The mass of the shaft-end mass block assembly can be adjusted to adjust the moment of inertia about the x-axis and the z-axis and the low-order modes of the simulation component. The position and mass of the side-end mass can be adjusted to adjust the moment of inertia of the simulation component.

[0006] Furthermore, a first mating through-hole is provided at the first end of the main beam and is used as an interface to connect to a spacecraft or a simulation boundary during the test. A rectangular through-hole is provided at the second end of the main beam. The side beam passes through the rectangular through-hole to form a fit with the main beam. A second mating through-hole is also provided at the second end of the main beam. The shaft-end mass block assembly is installed in the second mating through-hole through bolts.

[0007] Furthermore, two end adjustment holes are symmetrically provided at both ends of the side beam, and two middle adjustment holes are symmetrically provided at a position near the middle of the side beam. The side-end mass block assembly is installed in the end adjustment holes through bolts to adjust the position of the side-end mass block assembly. The offset adjustment blocks are installed in the middle adjustment holes through bolts to adjust the positions of the offset adjustment blocks.

[0008] Furthermore, the offset adjustment blocks are in an L-shaped structure and are provided with a horizontal hole and a vertical hole. Bolts pass through the vertical hole, the end adjustment hole and are connected to nuts. Auxiliary adjustment holes are also provided on the main beam. Bolts pass through the horizontal hole, the auxiliary adjustment hole and are connected to nuts to adjust the positions of the offset adjustment blocks.

[0009] Furthermore, the side-end mass block assembly includes a side-end mass block body and a plurality of side-end mass sheet bodies. Through-holes for the side beam to pass through are provided in the middle of the side-end mass block body and the side-end mass sheet bodies. Bolts pass through the side-end mass block body, the end adjustment hole and are connected to nuts to connect the side-end mass block body and the side beam. Bolts pass through the side-end mass sheet bodies and are connected to the side-end mass block body to connect the side-end mass sheet bodies and the side-end mass block body. The overall mass of the side-end mass block assembly can be controlled by increasing or decreasing the number of side-end mass block bodies.

[0010] Furthermore, the shaft-end mass block assembly includes a shaft-end mass block body and a plurality of shaft-end mass block bodies; The shaft-end mass block body is provided with a clamping groove for cooperating with the end of the main beam. A bolt passes through the clamping groove of the shaft-end mass block body, the main beam and is connected with a nut, so as to realize the connection between the shaft-end mass block body and the main beam; The bolt passes through the shaft-end mass block body and is connected with the shaft-end mass block body, so as to realize the connection between the shaft-end mass block body and the shaft-end mass block body; The overall mass of the shaft-end mass block assembly can be controlled by increasing or decreasing the number of shaft-end mass block bodies.

[0011] Compared with the prior art, the multi-mechanical parameter adjustable solar wing simulator capable of reflecting asymmetry of the present invention has the following advantages: (1) The multi-mechanical parameter adjustable solar wing simulator capable of reflecting asymmetry of the present invention has the function of adjustable asymmetry, and can adjust the degree of structural asymmetry on the premise of hardly changing the position of the structural centroid. The centroid position is always on the main beam axis, which is convenient for applying gravity unloading during ground tests.

[0012] (2) For the multi-mechanical parameter adjustable solar wing simulator capable of reflecting asymmetry of the present invention, the mass and position of the shaft-end mass block assembly and the side-end mass block assembly are both easily adjustable, which is convenient for adjusting multi-mechanical parameters such as the moment of inertia and low-order modes.

[0013] (3) The multi-mechanical parameter adjustable solar wing simulator capable of reflecting asymmetry of the present invention adopts a T-shaped beam structure as a whole, which greatly reduces the contact area between the structure and the air, and can carry out ground tests in the atmospheric environment, avoiding the high cost required for a vacuum chamber. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 Schematic diagram of a multi-mechanical parameter adjustable solar wing simulator capable of reflecting asymmetry according to an embodiment of the present invention Figure 1 ; Figure 2 Schematic diagram of a multi-mechanical parameter adjustable solar wing simulator capable of reflecting asymmetry according to an embodiment of the present invention Figure 2 ; Figure 3 Front view of the main beam according to an embodiment of the present invention; Figure 4 Front view of the side beam according to the embodiment of the present invention; Figure 5 According to the embodiment of the present invention Figure 2 Enlarged schematic diagram of the annotation A; Figure 6 According to the embodiment of the present invention Figure 2 Enlarged schematic diagram of the annotation B; Figure 7 Schematic diagram of the first three-order modal vibration modes of a multi-mechanical parameter adjustable solar wing simulation component that can reflect asymmetry according to the embodiment of the present invention.

[0015] Explanation of reference numerals: 1, main beam; 11, first mating through hole; 12, second mating through hole; 13, rectangular through hole; 2, side beam; 21, end adjustment hole; 22, middle adjustment hole; 3, shaft end mass block assembly; 31, shaft end mass block body; 32, shaft end mass sheet body; 4, side end mass block assembly; 41, side end mass block body; 42, side end mass sheet body; 5, offset adjustment block. Detailed implementation manners

[0016] It should be noted that, without conflict, the embodiments in the present invention and the features in the embodiments may be combined with each other.

[0017] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation to the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first", "second", etc. may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise specified, the meaning of "a plurality" is two or more.

[0018] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "installation", "connection", and "coupling" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0019] The present invention will be described in detail below with reference to the drawings and in conjunction with embodiments.

[0020] A multi-mechanical parameter adjustable solar wing simulation component capable of reflecting asymmetry, as Figures 1-6 shown, includes a main beam 1, side beams 2, shaft-end mass block assemblies 3, side-end mass block assemblies 4, and offset adjustment blocks 5; The main beam 1 is connected to the side beams 2 to form a T-shaped beam structure. The shaft-end mass block assemblies 3 are installed at the ends of the main beam 1, and one side-end mass block assembly 4 is installed at each end of the side beams 2. The offset adjustment blocks 5 are installed on both sides of the side beams 2 and are used to connect the main beam 1 and the side beams 2; In the initial state, the two side-end mass block assemblies 4 and the two offset adjustment blocks 5 are centrosymmetric; The offset adjustment blocks 5 can adjust their own positions to adjust the degree of asymmetry of the simulation component; The mass of the shaft-end mass block assemblies 3 can be adjusted to adjust the moments of inertia about the x-axis and z-axis and the low-order modes of the simulation component; The positions and masses of the side-end masses can be adjusted to adjust the moment of inertia of the simulation component.

[0021] Preferably, a first mating through-hole 11 is provided at the first end of the main beam 1 for connection to a spacecraft (or a wall) during testing; A rectangular through-hole 13 is provided at the second end of the main beam 1, and the side beam 2 passes through the rectangular through-hole to form a fit with the main beam 1; A second mating through-hole 12 is further provided at the second end of the main beam 1, and the shaft-end mass block assemblies 3 are installed in the second mating through-hole 12 by bolts.

[0022] Preferably, two end adjustment holes 21 are symmetrically provided at both ends of the side beam 2, and two middle adjustment holes 22 are symmetrically provided at positions close to the middle of the side beam 2; The side-end mass block assemblies 4 are installed in the end adjustment holes 21 by bolts to adjust the positions of the side-end mass block assemblies 4; The offset adjustment blocks 5 are installed in the middle adjustment holes 22 by bolts to adjust the positions of the offset adjustment blocks 5.

[0023] Preferably, the bias adjustment block 5 is in an L-shaped structure, provided with a horizontal hole and a vertical hole, and the bolt passes through the vertical hole, the end adjustment hole 21 and is connected with a nut; The main beam 1 is also provided with an auxiliary adjustment hole; the bolt passes through the horizontal hole and the auxiliary adjustment hole and is connected with a nut; to realize the adjustment of the position of the bias adjustment block 5, and the horizontal hole and the vertical hole cooperate with each other to improve the stability of the bias adjustment block 5.

[0024] Preferably, the side-end mass block assembly 4 includes a side-end mass block body 41 and a plurality of side-end mass sheet bodies 42; A through hole for the side beam 2 to pass through is provided in the middle of the side-end mass block body 41 and the side-end mass sheet body 42; The bolt passes through the side-end mass block body 41, the end adjustment hole 21 and is connected with a nut to realize the connection between the side-end mass block body 41 and the side beam 2; The bolt passes through the side-end mass sheet body 42 and is connected with the side-end mass block body 41 to realize the connection between the side-end mass sheet body 42 and the side-end mass block body 41; By increasing or decreasing the number of the side-end mass sheet bodies 42, the overall mass of the side-end mass block assembly 4 can be controlled.

[0025] Preferably, the shaft-end mass block assembly 3 includes a shaft-end mass block body 31 and a plurality of shaft-end mass sheet bodies 32; The shaft-end mass block body 31 is provided with a clamping groove for cooperating with the end of the main beam 1, and the bolt passes through the clamping groove of the shaft-end mass block body 31, the main beam 1 and is connected with a nut to realize the connection between the shaft-end mass block body 31 and the main beam 1; The bolt passes through the shaft-end mass sheet body 32 and is connected with the shaft-end mass block body 31 to realize the connection between the shaft-end mass sheet body 32 and the shaft-end mass block body 31; By increasing or decreasing the number of the shaft-end mass sheet bodies 32, the overall mass of the shaft-end mass block assembly 3 can be controlled.

[0026] Since the mechanical parameters of different configurations of solar wings, such as the moment of inertia and the low-order modal characteristics, may vary greatly, before designing the simulation part, first determine the lengths of the main beam 1 and the side beam 2 of the simulation part according to the mechanical parameters of the target solar wing and the size limit of the simulation part, and then adjust the masses of the shaft-end mass block and the side-end mass block until the simulation effect is achieved.

[0027] For different configurations of solar wings, such as traditional multi-panel deployed rigid or semi-rigid solar wings or new circular solar wings, the degree of asymmetry is different, and the bias adjustment block 5 is adjusted to simulate different degrees of asymmetry of the solar wing.

[0028] In an embodiment of the present invention, when the bias adjustment block 5 is not provided in the finite element simulation analysis model, the centroid position is (0 m, 2.64 m, 0 m), and the first three natural frequencies are 0.59 Hz, 1.12 Hz, and 1.49 Hz respectively; when the bias adjustment block 5 is added and the distance between the bias adjustment block 5 and the main beam 1 is 50 mm, the centroid position of the model is (0 m, 2.65 m, 0 m), and the first three natural frequencies are 0.59 Hz, 1.19 Hz, and 1.66 Hz respectively. As Figure 7 shown, if the plane formed by the model is used as the reference plane, the first three natural frequencies are in-plane swing mode, out-of-plane first-order antisymmetric mode, and out-of-plane first-order symmetric mode in sequence. It can be seen that after adding the bias adjustment block 5, the centroid position of the system hardly changes, and the frequency intervals between the symmetric mode and the asymmetric mode are adjusted.

[0029] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A solar wing simulation component with adjustable multiple mechanical parameters that can reflect asymmetry, characterized by: It includes a main beam, a side beam, an axle end mass block assembly, a side end mass block assembly and an offset adjustment block; The main beam and the side beam are connected to form a T-beam structure. The axle-end mass block assembly is installed at the end of the main beam, and a side-end mass block assembly is installed at each end of the side beam. The offset adjustment blocks are mounted on both sides of the side beams and are used to connect the main beam and the side beams; In the initial state, the two side mass block assemblies and the two offset adjustment blocks are centrally symmetrical; The offset adjustment block can realize its own position adjustment, and is used to adjust the asymmetry degree of the simulation component; The mass of the shaft end mass block assembly can be adjusted to adjust the rotational inertia and low-order modes of the simulation component around the x-axis and the z-axis; The position and mass of the side end mass can be adjusted to adjust the rotational inertia of the simulation part.

2. The solar wing simulation component with adjustable multiple mechanical parameters that can reflect asymmetry according to claim 1, characterized in that: The first end of the main beam is provided with a No. 1 mating through hole, which serves as an interface for connection with the spacecraft or the simulated boundary during the test; The second end of the main beam is provided with a rectangular through hole, and the side beam passes through the rectangular through hole to form a match with the main beam; The second end of the main beam is also provided with a No. 2 matching through hole, and the shaft end mass block assembly is installed to the No. 2 matching through hole by bolts.

3. The solar wing simulation component with adjustable multiple mechanical parameters capable of reflecting asymmetry according to claim 1, characterized in that: Two end adjustment holes are symmetrically arranged at both ends of the side beam, and two middle adjustment holes are symmetrically arranged near the middle of the side beam; The side mass block assembly is installed to the end adjustment hole by bolts to adjust the position of the side mass block assembly; The offset adjustment block is installed to the middle adjustment hole by means of bolts to adjust the position of the offset adjustment block.

4. The solar wing simulation component with adjustable multiple mechanical parameters capable of reflecting asymmetry according to claim 3, characterized in that: The offset adjustment block is in an L-shaped structure, and is provided with a horizontal hole and a vertical hole, and a bolt passes through the vertical hole, the end adjustment hole and is connected with a nut; The main beam is also provided with an auxiliary adjustment hole; the bolt passes through the horizontal hole, the auxiliary adjustment hole and is connected with the nut; and the position of the offset adjustment block is adjusted.

5. The solar wing simulation component with adjustable multiple mechanical parameters capable of reflecting asymmetry according to claim 3, characterized in that: The side mass block assembly comprises a side mass block body and a plurality of side mass sheet bodies; The middle parts of the side mass block body and the side mass sheet body are provided with through holes for the side beam to pass through; The bolt passes through the side end mass block body, the end adjustment hole and is connected with the nut to realize the connection between the side end mass block body and the side beam; The bolt passes through the side mass piece body and is connected to the side mass block body, so as to realize the connection between the side mass piece body and the side mass block body; The overall mass of the side-end mass block assembly can be controlled by increasing or decreasing the number of the side-end mass piece bodies.

6. The solar wing simulation component with adjustable multiple mechanical parameters capable of reflecting asymmetry according to claim 3, characterized in that: The shaft end mass block assembly comprises a shaft end mass block body and a plurality of shaft end mass sheet bodies; The shaft end mass block body is provided with a slot matched with the end of the main beam, and the bolt passes through the slot of the shaft end mass block body, the main beam and the nut to achieve the connection between the shaft end mass block body and the main beam; The bolt passes through the shaft end mass piece body and is connected to the shaft end mass block body, so as to realize the connection between the shaft end mass piece body and the shaft end mass block body; By increasing or decreasing the number of shaft end mass pieces, the overall mass of the shaft end mass block assembly can be controlled.

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