Solar wing configuration structure and working method thereof

Abstract

The present invention provides a solar wing configuration structure and a working method thereof in the field of aerospace technology, including a satellite body, a connecting frame and a base plate, wherein the satellite body includes a top plate and a side plate, and the side plate is vertically arranged with the top plate; one end of the connecting frame is arranged on the side plate, and the base plate is connected and arranged at the other end of the connecting frame; a remote sensing component for high-precision and high-stability tracking and observation of the sun is fixedly arranged on the connecting frame; when the base plate is in a locked state, the connecting frame is arranged in parallel with the side plate, the base plate is folded and arranged on the other side of the connecting frame, and the base plate is connected and arranged with the top plate through a connecting mechanism; when the base plate is in an unfolded state, the connecting mechanism is disconnected from the base plate, the base plate connecting frame rotates in a direction away from the satellite body to be vertical to the side plate, and the base plate rotates to be in the same horizontal plane as the connecting frame. The present invention is convenient and reliable to install, effectively reduces the mechanical response of the solar wing and the remote sensing instrument launching active segment, and the distributed unfolding has little influence on the center of mass of the satellite, which is conducive to the attitude stability of the satellite changing orbit.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a solar wing configuration structure and a working method thereof, and in particular to a solar wing configuration structure and a working method thereof for a geostationary orbit remote sensing satellite with solar imaging and detection requirements. Background Art

[0002] The configuration of the solar wing is an important part of the overall satellite design, especially the satellite configuration and layout design. The solar wing must first determine its required area based on its functional requirements (i.e., output power), and then consider the shape and size to decide how many substrates it is composed of. From the perspective of satellite energy, the solar wing can provide an installation basis for the entire satellite's solar cell patches, thereby ensuring the supply of satellite power energy. The traditional solar wing configuration is mainly designed around mission requirements such as satellite power, orbital characteristics, energy balance of the entire satellite, and in-orbit attitude control. It is only used to provide an installation surface for solar cell patches and to ensure the power supply of the satellite.

[0003] Through prior art search, it was found that the Chinese invention patent announcement number is CN105501468B, which discloses a flexible solar wing deployment mechanism for a space station. The mass limit of the rigid solar array has become a prominent problem. The present invention includes a bottom storage box, a storage cylinder, a storage cylinder cover, an extension arm deployment mechanism, a top storage box, a triangular prism extension arm, a wing surface and a wing surface tensioning mechanism; the bottom tripod of the triangular prism extension arm is fixedly connected to the boss in the storage cylinder, and the top tripod is fixedly connected to the barrel cover; the top storage box is fixedly connected to the storage cylinder cover, and the bottom storage box is fixedly connected to the storage cylinder; the extension arm deployment mechanism is fixed to the bottom of the storage cylinder to control the extension arm to deploy at a uniform speed; the wing surface tensioning mechanism is fixed in the top storage box to ensure the tension on the solar wing during the deployment process, and to tension the solar wing after deployment to maintain a certain rigidity. This patent technology has the above-mentioned related problems.

[0004] Through prior art search, it was found that the Chinese invention patent announcement number is CN105501468B, which discloses a flexible solar wing with a four-link deployment configuration. When the solar wing is deployed, the connecting rod is used as a two-force rod, as a rigid support component for the upper and lower box plates; the four-link mechanism is used to achieve the parallel arrangement of the box plate and the main deployment mechanism in the folded state; the traditional pin-type hinge is replaced by a spring mechanism in the connecting rod mechanism; and a quick locking mechanism is used in the upper connecting rod mechanism, so that the upper box plate can become a triangular stable system after being unlocked. However, the above patent has the following shortcomings: it only provides solar wings with different structural compositions, and does not involve the structural description of solar remote sensing instruments or even the solar wing configuration equipped with solar remote sensing instruments.

[0005] In combination with the characteristics of the orbital period of geostationary satellites and the real-time orientation of solar panels to the sun, the needs of continuous operation of remote sensing instruments for the sun and the mechanical response requirements of remote sensing instruments during the active phase of satellite launch are fully considered in the overall design and configuration layout of the satellite. Therefore, a solar panel configuration structure and its working method are proposed, which have the characteristics of good installation mechanical environment and stable operation in orbit, and can also meet the needs of remote sensing instruments for solar imaging and detection. However, there are no solar panels with such functions in China at present. Summary of the invention

[0006] In view of the defects in the prior art, an object of the present invention is to provide a solar wing configuration structure and a working method thereof.

[0007] A solar wing configuration structure provided by the present invention includes a satellite body, a connecting frame and a base plate, wherein the satellite body includes a top plate and a side plate, and the side plate is vertically arranged with respect to the top plate;

[0008] One end of the connecting frame is arranged on the side plate, and the base plate is connected to the other end of the connecting frame;

[0009] A remote sensing component for high-precision and high-stability tracking and observation of the sun is fixedly arranged on the connecting frame;

[0010] When the base plate is in a locked state, the connecting frame is arranged parallel to the side plate, the base plate is folded and arranged on the other side of the connecting frame, and the base plate is connected to the top plate through a connecting mechanism;

[0011] When the base plate is in the unfolded state, the connection mechanism is disconnected from the base plate, the base plate and the connecting frame are rotated in a direction away from the satellite body until they are perpendicular to the side plate, and the base plate is rotated until they are in the same horizontal plane as the connecting frame.

[0012] In some embodiments, one end of the connecting frame connected to the side panel is provided with a triangular plate structure, and the triangular plate structure end of the connecting frame is rotatably provided on the satellite body through a rotating member.

[0013] In some embodiments, the connection mechanism includes a fixing frame and a connecting member, wherein the fixing frame is fixedly disposed on the top plate, the connecting member is fixedly disposed on an upper end portion of the fixing frame, and the other end of the connecting member is connected to the base plate in a locked state.

[0014] In some embodiments, the remote sensing assembly includes a fixing plate, a snap groove and a solar remote sensing instrument, the fixing plate is fixedly disposed on the connecting frame, the solar remote sensing instrument is fixedly disposed on the fixing plate, and the snap grooves are provided on both sides of the fixing plate.

[0015] In some embodiments, a support frame is fixedly disposed on the top plate, and buckles are fixedly disposed on the support frame, and the buckles are respectively disposed corresponding to the buckle grooves.

[0016] In some embodiments, the connecting member and the substrate are connected via an unlocking member, and the buckling member and the buckling groove are connected via an unlocking member.

[0017] In some embodiments, one end of the base plate is hingedly connected to the connecting frame, and the other end of the base plate is connected to the connecting plate via an unlocking member.

[0018] In some implementations, the unlocking member is an explosive device.

[0019] In some implementations, the solar remote sensing instrument uses a solar imager and a flow meter.

[0020] The present invention also provides a working method of a solar wing configuration structure, comprising the following steps: Step 1. After the satellite launch and the rocket are separated, the pyrotechnics between the connecting member and the substrate and the pyrotechnics between the buckle member and the buckle groove are first detonated and unlocked;

[0021] Step 2. After receiving the telemetry command that the pyrotechnics between the connecting member and the base plate and the pyrotechnics between the buckle member and the buckle groove are successfully detonated and unlocked, the pyrotechnics pressing the base plate and the connecting plate are detonated and unlocked again;

[0022] Step 3. After the base plate is unlocked, the connecting frame and the remote sensing component installed on the connecting frame are unfolded first, and after the connecting frame and the remote sensing component are unfolded into place, the base plate is unfolded;

[0023] Step 4. After the satellite is positioned at the predetermined orbital position of the geostationary orbit, the substrate is roughly oriented toward the sun;

[0024] Step 5. The solar remote sensing instrument uses its own mechanism to accurately orient itself to the sun based on tracking and analysis of the sun's position, and completes continuous high-precision and high-stability tracking and observation of the sun.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] 1. The present invention sets a remote sensing component on the satellite body, sets a solar remote sensing instrument in the remote sensing component, and performs small-angle tracking rotation during high-precision tracking of the sun, thereby breaking through the functional limitations of traditional solar wings that are only used to provide a mounting surface for solar cell patches and ensure satellite power supply. The solar wing connecting frame provides a high-rigidity mounting foundation for the solar remote sensing instrument, thereby ensuring the installation accuracy of the remote sensing component;

[0027] 2. The present invention arranges a connecting frame on the satellite body, and arranges a base plate connected to the connecting frame, arranges a remote sensing component on the connecting frame, and adopts a method of respectively pressing the solar wing, the connecting frame and the remote sensing instrument, which not only makes the installation convenient and reliable, but also effectively reduces the mechanical response of the solar wing and the remote sensing instrument's active launch segment;

[0028] 3. The present invention provides an unlocking member between the other end of the base plate and the connecting plate, and in an unlocked state, the remote sensing component is provided on the support frame, so that the assembly operation is simple and there is sufficient operating space for the remote sensing component;

[0029] 4. The present invention first deploys the connecting frame and the remote sensing component installed on the connecting frame. After the connecting frame and the remote sensing component are deployed in place, the base plate is deployed. The distributed deployment of the solar panels and the remote sensing instrument has little impact on the satellite's center of mass, which is beneficial to the stability of the satellite's attitude during orbit change. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0031] Figure 1 It is a structural schematic diagram of the solar wing configuration structure of the present invention;

[0032] Figure 2 for Figure 1 A partial enlarged view of the

[0033] Figure 3 The structure of the solar wing configuration structure of the present invention is shown in FIG. Figure 1 ;

[0034] Figure 4 The structure of the solar wing configuration structure of the present invention is shown in FIG. Figure 2 ;

[0035] Figure 5 This is a schematic diagram of the precise directional detection of the sun by the satellite remote sensing instrument of the present invention;

[0036] Figure 6 The present invention is a schematic diagram of the satellite remote sensing instrument tracking, imaging and monitoring the sun within a one-year period.

[0037] DETAILED DESCRIPTION

[0038] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0039] Establish the satellite layout coordinate system (O-XYZ), which is defined as follows:

[0040] Coordinate origin O: center of the satellite-rocket separation plane;

[0041] OZ axis: perpendicular to the satellite-rocket separation plane, pointing to the direction of the satellite body along the coordinate origin;

[0042] OX axis: points to the direction of the satellite along the coordinate origin, consistent with the satellite's flight direction;

[0043] Y axis: forms a right-hand system with X and Z axes.

[0044] like Figure 1 The schematic diagram of the solar wing configuration is shown in FIG. Figure 2 Shown Figure 1 A partial enlarged view of Figure 3 The figure shows the structure of the solar wing configuration structure of the present invention. Figure 1 ,like Figure 4 The figure shows the structure of the solar wing configuration structure of the present invention. Figure 2 , including a satellite body 1, a connecting frame 3 and a base plate 7. The satellite body 1 includes a top plate 11 and a side plate 12. The side plate 12 is vertically arranged with the top plate 11. One end of the connecting frame 3 is arranged on the side plate 12, and the base plate 7 is connected and arranged on the other end of the connecting frame 3. The remote sensing component 6 for high-precision and high-stability tracking and observation of the sun is fixed on the connecting frame 3.

[0045] When the base plate 7 is in the locked state, the connecting frame 3 is arranged parallel to the side plate 12, the base plate 7 is folded and arranged on the other side of the connecting frame 3, and the base plate 7 is connected to the top plate 11 through the connecting mechanism. When the base plate 7 is in the unfolded state, the connecting mechanism is disconnected from the base plate 7, the base plate 7 connecting frame 3 is rotated in the direction away from the satellite body 1 until it is perpendicular to the side plate 12, and the base plate 7 is rotated to be in the same horizontal plane as the connecting frame 3.

[0046] One end of the connecting frame 3 connected to the side plate 12 is provided with a triangular plate structure, and the triangular plate structure end of the connecting frame 3 is rotatably provided on the satellite body 1 through the rotating member 2. The connecting mechanism includes a fixing frame 5 and a connecting member 51, the fixing frame 5 is fixedly provided on the top plate 11, the connecting member 51 is fixedly provided on the upper end of the fixing frame 5, and the other end of the connecting member 51 is connected to the base plate 7 in a locked state.

[0047] The remote sensing assembly 6 includes a fixing plate 61, a buckle slot 62 and a solar remote sensing instrument 63. The fixing plate 61 is fixedly arranged on the connecting frame 3, and the solar remote sensing instrument 63 is fixedly arranged on the fixing plate 61. The buckle slots 62 are provided on both sides of the fixing plate 61. In this embodiment, the solar remote sensing instrument 63 uses a solar imager and a flow meter to realize continuous imaging observation of the entire solar disk and the low corona region and monitoring of changes in solar spectrum distribution.

[0048] The support frame 4 is fixedly arranged on the top plate 11, and the buckle 41 is fixedly arranged on the support frame 4, and the buckle 41 is respectively arranged corresponding to the buckle groove 62. The connecting member 51 is connected to the base plate 7 through an unlocking member, and the buckle 41 is connected to the buckle groove 62 through an unlocking member. One end of the base plate 7 is hingedly connected to the connecting frame 3, and the other end of the base plate 7 is connected to the connecting plate through an unlocking member. In this embodiment, the unlocking member adopts an explosive device.

[0049] like Figure 5 FIG. 1 is a schematic diagram of the precise directional detection of the sun by the satellite remote sensing instrument of the present invention. Figure 6 The figure shows a schematic diagram of solar tracking, imaging and monitoring by the satellite remote sensing instrument of the present invention within a one-year period. The working method of the solar wing configuration structure includes the following steps: Step 1. After the satellite launch and the separation of the rocket and the satellite, the pyrotechnics between the connecting piece 51 and the base plate 7 and the pyrotechnics between the fastener 41 and the fastener groove 62 are first detonated and unlocked.

[0050] Step 2. After receiving the telemetry command of successful detonation and unlocking of the pyrotechnics between the connecting piece 51 and the base plate 7 and between the buckle 41 and the buckle groove 62, the ground presses the base plate 7 and the connecting plate and detonates and unlocks again.

[0051] Step 3. After the base plate 7 is unlocked, the connecting frame 3 and the remote sensing component 6 installed on the connecting frame 3 are unfolded first. After the connecting frame 3 and the remote sensing component 6 are unfolded to their proper positions, the base plate 7 is unfolded.

[0052] Step 4. After the satellite is positioned at the predetermined position in the geostationary orbit, the substrate 7 is roughly oriented toward the sun.

[0053] Step 5. The solar remote sensing instrument 63 completes precise solar orientation based on tracking and analyzing the solar position by its own mechanism, and completes continuous high-precision and high-stability tracking and observation of the solar system.

[0054] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0055] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A solar wing configuration structure, characterized in that: It comprises a satellite body (1), a connecting frame (3) and a base plate (7), wherein the satellite body (1) comprises a top plate (11) and a side plate (12), and the side plate (12) is arranged vertically to the top plate (11); One end of the connecting frame (3) is arranged on the side plate (12), and the base plate (7) is connected to the other end of the connecting frame (3); A remote sensing component (6) for high-precision and high-stability tracking and observation of the sun is fixedly arranged on the connecting frame (3); When the base plate (7) is in a locked state, the connecting frame (3) and the side plate (12) are arranged in parallel, the base plate (7) is folded and arranged on the other side of the connecting frame (3), and the base plate (7) and the top plate (11) are connected and arranged via a connecting mechanism; When the base plate (7) is in the unfolded state, the connection mechanism is disconnected from the base plate (7), the base plate (7) is rotated in a direction away from the satellite body (1) through the connecting frame (3) until it is perpendicular to the side plate (12), and the base plate (7) is rotated until it is in the same horizontal plane as the connecting frame (3); The remote sensing assembly (6) comprises a fixing plate (61) and a solar remote sensing instrument (63), wherein the fixing plate (61) is fixedly arranged on the connecting frame (3), and the solar remote sensing instrument (63) is fixedly arranged on the fixing plate (61); The connection mechanism comprises a fixing frame (5) and a connecting member (51), wherein the fixing frame (5) is fixedly arranged on the top plate (11), the connecting member (51) is fixedly arranged at the upper end of the fixing frame (5), and the other end of the connecting member (51) is connected to the base plate (7) in a locked state; The remote sensing component (6) comprises a buckle groove (62), and the buckle groove (62) is arranged on both sides of the fixing plate (61); A support frame (4) is fixedly arranged on the top plate (11), and a buckle member (41) is fixedly arranged on the support frame (4), and the buckle members (41) are respectively arranged corresponding to the buckle grooves (62); The connecting member (51) and the base plate (7) are connected via an unlocking member, and the buckling member (41) and the buckling groove (62) are connected via an unlocking member.

2. The solar wing configuration structure according to claim 1, characterized in that: One end of the connecting frame (3) connected to the side plate (12) is provided with a triangular plate structure, and the triangular plate structure end of the connecting frame (3) is rotatably provided on the satellite body (1) via a rotating member (2).

3. The solar wing configuration structure according to claim 1, characterized in that: One end of the base plate (7) is hingedly connected to the connecting frame (3), and the other end of the base plate (7) is connected to the connecting piece (51) via an unlocking piece.

4. The solar wing configuration structure according to claim 3, characterized in that: The unlocking piece is an explosive device.

5. The solar wing configuration structure according to claim 1, characterized in that: The solar remote sensing instrument (63) uses a solar imager and a flow meter.

6. A method for operating the solar wing configuration structure according to claim 1, characterized in that: The following steps are involved: Step 1. After the satellite launch and the rocket are separated, the pyrotechnics between the connecting piece (51) and the base plate (7) and the pyrotechnics between the buckle piece (41) and the buckle groove (62) are first detonated and unlocked; Step 2. After receiving the telemetry command that the pyrotechnics between the connecting piece (51) and the base plate (7) and the pyrotechnics between the buckle piece (41) and the buckle groove (62) have been successfully detonated and unlocked, the ground presses the pyrotechnics between the base plate (7) and the connecting piece (51) to detonate and unlock again; Step 3. After the base plate (7) is unlocked, the connecting frame (3) and the remote sensing component (6) mounted on the connecting frame (3) are unfolded first, and after the connecting frame (3) and the remote sensing component (6) are unfolded into place, the base plate (7) is unfolded; Step 4. After the satellite is positioned at a predetermined position in the geostationary orbit, the substrate (7) is roughly oriented toward the sun; Step 5. The solar remote sensing instrument (63) uses its own mechanism to accurately orient itself to the sun based on the tracking and analysis of the sun's position, and completes continuous high-precision and high-stability tracking and observation of the sun.

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