Ground simulation on-orbit satellite high-speed spinning and solar wing unfolding test device

Abstract

The invention provides a ground simulation on-orbit satellite high-speed spinning and solar wing unfolding test device which comprises a mechanical arm, an unfolding type solar wing, a locking device, a satellite body, an adapter, a simulation operation end face, an inclined support and a fixed type solar wing. The unfolding type solar wing and the fixed type solar wing are installed on the side face of the satellite body through inclined supports, the simulation operation end face is further installed on the side face of the satellite body, and the locking device is further installed at the joint of the satellite body and the unfolding type solar wing. The device has the advantages that high-speed spinning motion of a simulated satellite is achieved, the solar wing sailboard can simulate the 0-90-degree (not limited to the angle range) unfolding process after the locking pin is pulled out from the initial locking state, and reference is provided for design of solar wings of the same type.

Description

Technical Field

[0001] The present invention belongs to the field of full-physics simulation test equipment, and in particular relates to a ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of a solar wing. Background Art

[0002] Since the beginning of the 21st century, my country's aerospace industry has developed rapidly and is at the forefront of the world in satellite research. Satellite engineering is a high-risk, high-investment, and highly complex system engineering. Therefore, domestic research institutions attach great importance to satellite ground simulation and testing, and have conducted various satellite ground simulation tests on the ground to simulate high-reliability satellite simulations and verify various satellite motion parameters.

[0003] At present, most of the research on satellites by various research institutions is carried out through digital simulation. There is a big difference between the digital simulation results and the actual satellite motion process. Therefore, the present invention proposes a ground-based simulation test device for high-speed rotation of in-orbit satellites and deployment of solar wings, which can simulate the motion state of satellite high-speed rotation and deployment of solar wings. The obtained simulation parameters can provide a more realistic reference for space attack and defense research and satellite stability control, and the structure of satellite solar wing deployment can also be used as a reference for studying new solar wings. Summary of the invention

[0004] In view of this, the present invention aims to propose a ground-based test device for simulating the high-speed rotation of an on-orbit satellite and the deployment of solar panels, so as to solve at least one problem existing in the above-mentioned prior art.

[0005] To achieve the above object, the technical solution of the present invention is achieved as follows: A ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of a solar wing comprises a mechanical arm, an deployable solar wing, a locking device, a satellite body, an adapter, a simulated operation end face, an inclined support and a fixed solar wing. The satellite body is connected to the mechanical arm via the adapter, the deployable solar wing and the fixed solar wing are respectively installed on the side of the satellite body via the inclined support, the simulated operation end face is also installed on the side of the satellite body, and the locking device is also installed at the connection between the satellite body and the deployable solar wing.

[0006] Furthermore, the robotic arm is installed on a three-dimensional translation device, and is carried by the three-dimensional translation device to achieve translational movement in three directions.

[0007] Furthermore, the deployable solar wing includes a solar wing sailboard, a root hinge, an upper hinge, a lower hinge and a nitrogen spring. The solar wing sailboard is connected to the satellite body through the root hinge, and the solar wing sailboard is also connected to one end of the nitrogen spring through the upper hinge. The other end of the nitrogen spring is connected to the satellite body through the lower hinge, one end of the oblique support is connected to the solar wing sailboard, and the other end of the oblique support is connected to the satellite body.

[0008] Furthermore, the root hinge includes a root seat, a locking nut, an intermediate rotating shaft, a connecting seat, a small shaft sleeve and a bearing. One end of the root hinge is connected to the satellite body, and the other end of the root hinge is connected to the solar wing sailboard. The solar wing sailboard can rotate around the axis system of the root hinge. The bearing is installed in the bearing hole of the connecting seat, the intermediate rotating shaft cooperates with the inner ring of the bearing, the root seat cooperates with the intermediate rotating shaft, the intermediate rotating shaft is locked by the locking nut, and the small shaft sleeve cooperates with the intermediate rotating shaft.

[0009] Furthermore, the lower hinge includes a lower hinge seat, a lower pin, a lower sleeve and a lower cotter pin. The lower hinge seat is screwed to the satellite body, the lower pin passes through the lower hinge seat and the lower sleeve and is connected to the lower cotter pin respectively, and the outer ring of the lower sleeve cooperates with the nitrogen spring.

[0010] Furthermore, the upper hinge includes an upper hinge seat, an upper pin, an upper sleeve and an upper cotter pin. The upper hinge seat is screwed to the solar wing sailboard, the upper pin passes through the upper hinge seat and the upper sleeve and is connected to the upper cotter pin respectively, and the outer ring of the upper sleeve cooperates with the nitrogen spring.

[0011] Furthermore, the locking device includes a locking frame, a locking seat and a locking pin. The locking seat is installed on the solar wing sailboard, and the locking frame is screwed to the satellite body. When the unfolded solar wing is in the zero position, the locking pin passes through the through holes of the locking seat and the locking frame to lock the unfolded solar wing. When the unfolded solar wing unfolding test is required, the locking pin is pulled out, the unfolded solar wing is unfolded, and the locking pin is connected to the satellite body.

[0012] Furthermore, the simulated operation end face is screwed to the satellite body, and satellite operation simulation components can be installed on the simulated operation end face as required to provide operation and identification tests.

[0013] Furthermore, the fixed solar wing is screwed to the two side surfaces of the satellite body through oblique supports.

[0014] Compared with the prior art, the ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar wings described in the present invention has the following advantages: (1) The present invention discloses a ground-based test device for simulating the high-speed rotation of an on-orbit satellite and the deployment of a solar wing. The present invention realizes the simulation of the high-speed rotation of a satellite. The solar wing sailboard can simulate the deployment process of 0-90° (not limited to this angle range) after the locking pin is pulled out from the initial locked state, providing a reference for the design of the same type of solar wings.

[0015] (2) The present invention discloses a ground-based test device for simulating the high-speed rotation of an on-orbit satellite and the deployment of a solar wing. The deployable solar wing of the present invention is designed with a locking device, so that the solar wing has a locked and freely deployable state. The locking device is easy to open. When the locking device is opened, the solar wing can be deployed. When the next test is conducted, the solar wing can be folded back to its original position and the locking device can be locked.

[0016] (3) The present invention discloses a ground-based test device for simulating the high-speed rotation of an on-orbit satellite and the deployment of solar wings. The present invention is designed with a detachable inclined support for auxiliary support of the fixed solar wings and the deployed solar wings, thereby ensuring the stability and safety of the device during high-speed rotation.

[0017] (4) The present invention discloses a ground-based test device for simulating the high-speed rotation of an on-orbit satellite and the deployment of solar wings. The present invention adopts a nitrogen spring as the drive for the deployment of the solar wings. The driving force is relatively large, and the ground deployment test can be carried out without the assistance of zero-gravity unloading equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 It is a schematic axial view of the overall structure according to an embodiment of the present invention; Figure 2 It is a schematic diagram of the overall structure unfolding process according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the root hinge axis side according to an embodiment of the present invention; Figure 4 This is a schematic axial view of a deployable solar wing according to an embodiment of the present invention; Figure 5 for Figure 1 An enlarged schematic diagram of Figure 6 It is a schematic axial view of the high-speed spinning state described in an embodiment of the present invention.

[0019] Description of reference numerals: 1. Mechanical arm; 2. Expandable solar wing; 2.1. Solar wing sailboard; 2.2. Root hinge; 2.2.1. Root seat; 2.2.2. Locking nut; 2.2.3. Intermediate shaft; 2.2.4. Connecting seat; 2.2.5. Small bushing; 2.2.6. Bearing; 2.3. Upper hinge; 2.3.1. Upper hinge seat; 2.3.2. Upper pin; 2.3.3. Upper bushing; 2. 3.4, upper cotter pin; 2.4, lower hinge; 2.4.1, lower hinge seat; 2.4.2, lower pin; 2.4.3, lower bushing; 2.4.4, lower cotter pin; 2.5, nitrogen spring; 3, locking device; 3.1, locking frame; 3.2, locking seat; 3.3, locking pin; 4, satellite body; 5, adapter; 6, simulated operation end face; 7, inclined support; 8, fixed solar wing. DETAILED DESCRIPTION

[0020] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0021] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are 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 limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0022] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" 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 it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0023] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0024] like Figures 1 to 6As shown, a ground-based test device for simulating the high-speed rotation of an in-orbit satellite and the deployment of a solar wing comprises a robotic arm 1, an deployable solar wing 2, a locking device 3, a satellite body 4, an adapter 5, a simulated operating end face 6, an inclined support 7 and a fixed solar wing 8. Compared with the current test simulation system, the present invention is carried by a robotic arm and can simulate the high-speed rotation motion of a certain type of in-orbit satellite and the deployment process of a single-sided solar wing.

[0025] In a preferred embodiment of the present invention, the robot arm 1 is installed on a three-dimensional translation device, and is carried by the three-dimensional translation device to realize translational motion in three directions.

[0026] In a preferred embodiment of the present invention, the satellite body 4 is connected to the robotic arm 1 via an adapter 5, and is carried by the robotic arm to realize flight movements such as rotation and translation.

[0027] In a preferred embodiment of the present invention, one end of the deployable solar wing 2 is connected to the satellite body 4 through a root hinge 2.2, and the other end is connected to the satellite body 4 through a nitrogen spring 2.5 and an upper hinge 2.3 and a lower hinge 2.4. The deployable solar wing 2 mainly includes a solar wing sailboard 2.1, a root hinge 2.2, an upper hinge 2.3, a lower hinge 2.4, and a nitrogen spring 2.5. The thrust of the nitrogen spring 2.5 can deploy the deployable solar wing 2. When performing a high-speed spin test, one end of the inclined support 7 is connected to the solar wing sailboard 2.1, and the other end is connected to the satellite body 4, playing the role of fixed support.

[0028] In a preferred embodiment of the present invention, the root hinge 2.2 mainly includes a root seat 2.2.1, a locking nut 2.2.2, an intermediate shaft 2.2.3, a connecting seat 2.2.4, a small shaft sleeve 2.2.5, and a bearing 2.2.6. One end of the root hinge 2.2 is connected to the satellite body 4 and the other end is connected to the solar wing sailboard 2.1. The solar wing sailboard 2.1 can rotate around the axis of the root hinge 2.2. The bearing 2.2.6 is installed in the bearing hole of the connecting seat 2.2.4. The intermediate shaft 2.2.3 cooperates with the inner ring of the bearing 2.2.6. The root seat 2.2.1 cooperates with the intermediate shaft 2.2.3. The intermediate shaft 2.2.3 is locked by the locking nut 2.2.2. The small shaft sleeve 2.2.5 cooperates with the intermediate shaft 2.2.3. The root hinge 2.2 mainly realizes the rotational freedom, but is not limited to this rotational method.

[0029] In a preferred embodiment of the present invention, the lower hinge 2.4 mainly includes a lower hinge seat 2.4.1, a lower pin 2.4.2, a lower sleeve 2.4.3, and a lower cotter pin 2.4.4. The lower hinge seat 2.4.1 is screwed with the satellite body 4, the lower pin 2.4.2 passes through the lower hinge seat 2.4.1 and the lower sleeve 2.4.3 respectively, the outer ring of the lower sleeve 2.4.3 cooperates with the nitrogen spring 2.5, and the lower cotter pin 2.4.4 passes through the hole of the lower pin 2.4.2 to prevent the lower pin 2.4.2 from coming out. The lower hinge 2.4 mainly realizes the rotational freedom, but is not limited to this rotational realization method.

[0030] In a preferred embodiment of the present invention, the upper hinge 2.3 mainly includes an upper hinge seat 2.3.1, an upper pin 2.3.2, an upper sleeve 2.3.3, and an upper cotter pin 2.3.4. The upper hinge seat 2.3.1 is screwed with the solar wing sailboard 2.1, the upper pin 2.3.2 passes through the upper hinge seat 2.3.1 and the upper sleeve 2.3.3 respectively, the outer ring of the upper sleeve 2.3.3 cooperates with the nitrogen spring 2.5, and the upper cotter pin 2.3.4 passes through the hole of the upper pin 2.3.2 to prevent the upper pin 2.3.2 from coming out. The upper hinge 2.3 mainly realizes the rotational freedom, but is not limited to this rotational realization method.

[0031] In a preferred embodiment of the present invention, the locking device 3 mainly includes a locking frame 3.1, a locking seat 3.2, and a locking pin 3.3. The locking seat 3.2 is installed on the solar wing sailboard 2.1 of the unfolded solar wing 2, and the locking frame 3.1 is screwed on the satellite body 4. When the unfolded solar wing 2 is in the zero position, the locking pin 3.3 passes through the through holes of the locking seat 3.2 and the locking frame 3.1 to lock the unfolded solar wing 2. When the unfolded solar wing 2 needs to be unfolded, the locking pin 3.3 is pulled out, and the unfolded solar wing 2 is unfolded. The locking pin 3.3 is connected to the satellite body 4 with a rope and will not fall off after the locking pin is pulled out.

[0032] In a preferred embodiment of the present invention, the simulated operation end face 6 is screwed onto the satellite body 4, on which a satellite operation simulation component can be installed as required for operation, identification and other tests.

[0033] In a preferred embodiment of the present invention, the fixed solar wing 8 is screwed onto the two side surfaces of the satellite body 4 and fixedly connected to the satellite body 4 via the inclined support 7 to ensure the rigidity and strength of the device when performing high-speed spinning motion.

[0034] The present invention realizes the simulation of high-speed spinning motion of satellites. The solar wing sailboard can simulate the 0-90° (not limited to this angle range) unfolding process after the locking pin is pulled out from the initial locked state, providing a reference for the design of similar solar wings.

[0035] The deployable solar wing of the present invention is designed with a locking device, so that the solar wing has a locked and freely deployable state. The locking device is easy to open. When the locking device is opened, the solar wing can be deployed. When conducting the next test, the solar wing can be folded back to its original position and the locking device can be locked.

[0036] The present invention is designed with a detachable oblique support for auxiliary support of the fixed solar wing and the unfolded solar wing, thereby ensuring the stability and safety of the device during high-speed rotation.

[0037] The present invention adopts a nitrogen spring as a drive for unfolding the solar wing, which has a relatively large driving force and can be used for ground unfolding tests without the assistance of zero-gravity unloading equipment.

[0038] Working principle of a ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels: The mechanical arm 1 and the satellite body 4 are connected through an adapter 5, and the mechanical arm 1 drives the satellite to perform translation and high-speed spin motion. When performing high-speed spin motion, all inclined supports 7 are installed to ensure the stability of the satellite's high-speed spin motion.

[0039] Deployment process of deployable solar wing: After the test preparation begins, the locking pin 3.3 is pulled out by a mechanical arm or a tester, the locking frame 3.1 and the locking seat 3.2 are released from the locking relationship, and the push rod of the nitrogen spring 2.5 is pushed out to push the solar wing sailboard 2.1 to rotate and unfold around the root hinge 2.2. During the unfolding process, the angle between the nitrogen spring 2.5 and the satellite body is constantly changing. At this time, the pin holes at both ends of the nitrogen spring 2.5 rotate around the upper hinge 2.3 and the lower hinge 2.4 respectively to adapt to the angle change. After the solar wing is unfolded, a limiter can be designed to set the solar wing to a specified unfolding angle. When conducting the next unfolding test, the solar wing sailboard 2.1 can be manually rotated along the root hinge 2.2 until the locking seat 3.2 is aligned with the pin hole of the locking frame 3.1. After the pin holes are aligned, the locking pin 3.3 is inserted, and the unfolded solar wing 2 is locked at this time.

[0040] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels, characterized in that: The invention comprises a mechanical arm (1), an unfolded solar wing (2), a locking device (3), a satellite body (4), an adapter (5), a simulated operation end face (6), an inclined support (7) and a fixed solar wing (8), wherein the satellite body (4) is connected to the mechanical arm (1) via the adapter (5), the unfolded solar wing (2) and the fixed solar wing (8) are respectively installed on the side of the satellite body (4) via the inclined support (7), the simulated operation end face (6) is also installed on the side of the satellite body (4), and the locking device (3) is also installed at the connection between the satellite body (4) and the unfolded solar wing (2).

2. A ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels according to claim 1, characterized in that: The mechanical arm (1) is mounted on a three-dimensional translation device and is carried by the three-dimensional translation device to achieve translational motion in three directions.

3. A ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels according to claim 1, characterized in that: The deployable solar wing (2) comprises a solar wing sailboard (2.1), a root hinge (2.2), an upper hinge (2.3), a lower hinge (2.4) and a nitrogen spring (2.5); the solar wing sailboard (2.1) is connected to a satellite body (4) via the root hinge (2.2); the solar wing sailboard (2.1) is also connected to one end of the nitrogen spring (2.5) via the upper hinge (2.3); the other end of the nitrogen spring (2.5) is connected to the satellite body (4) via the lower hinge (2.4); one end of an inclined support (7) is connected to the solar wing sailboard (2.1); and the other end of the inclined support (7) is connected to the satellite body (4).

4. A ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels according to claim 3, characterized in that: The root hinge (2.2) comprises a root seat (2.2.1), a locking nut (2.2.2), an intermediate rotating shaft (2.2.3), a connecting seat (2.2.4), a small shaft sleeve (2.2.5) and a bearing (2.2.6). One end of the root hinge (2.2) is connected to the satellite body (4), and the other end of the root hinge (2.2) is connected to the solar wing sailboard (2.1). The solar wing sailboard (2.1) can be rotated around the root The shaft system of the hinge (2.2) rotates, the bearing (2.2.6) is installed in the bearing hole of the connecting seat (2.2.4), the intermediate rotating shaft (2.2.3) cooperates with the inner ring of the bearing (2.2.6), the root seat (2.2.1) cooperates with the intermediate rotating shaft (2.2.3), the intermediate rotating shaft (2.2.3) is locked by a locking nut (2.2.2), and the small shaft sleeve (2.2.5) cooperates with the intermediate rotating shaft (2.2.3).

5. The ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels according to claim 1, characterized in that: The lower hinge (2.4) comprises a lower hinge seat (2.4.1), a lower pin (2.4.2), a lower shaft sleeve (2.4.3) and a lower cotter pin (2.4.4); the lower hinge seat (2.4.1) is screwed to the satellite body (4); the lower pin (2.4.2) passes through the lower hinge seat (2.4.1) and the lower shaft sleeve (2.4.3) and is connected to the lower cotter pin (2.4.4); and the outer ring of the lower shaft sleeve (2.4.3) cooperates with the nitrogen spring (2.5).

6. The ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels according to claim 3, characterized in that: The upper hinge (2.3) comprises an upper hinge seat (2.3.1), an upper pin (2.3.2), an upper shaft sleeve (2.3.3) and an upper cotter pin (2.3.4); the upper hinge seat (2.3.1) is screwed to the solar wing sailboard (2.1); the upper pin (2.3.2) passes through the upper hinge seat (2.3.1) and the upper shaft sleeve (2.3.3) and is connected to the upper cotter pin (2.3.4); and the outer ring of the upper shaft sleeve (2.3.3) cooperates with the nitrogen spring (2.5).

7. The ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels according to claim 3, characterized in that: The locking device (3) comprises a locking frame (3.1), a locking seat (3.2) and a locking pin (3.3); the locking seat (3.2) is mounted on the solar wing sailboard (2.1); the locking frame (3.1) is screwed to the satellite body (4); when the unfolded solar wing (2) is in a zero position, the locking pin (3.3) passes through the through holes of the locking seat (3.2) and the locking frame (3.1) to lock the unfolded solar wing (2); when the unfolded solar wing (2) needs to be unfolded, the locking pin (3.3) is pulled out, the unfolded solar wing (2) is unfolded, and the locking pin (3.3) is connected to the satellite body (4).

8. The ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels according to claim 1, characterized in that: The simulated operation end surface (6) is screwed to the satellite body (4), and a satellite operation simulation component can be installed on the simulated operation end surface (6) as required to provide operation and identification tests.

9. The ground-based test device for simulating high-speed rotation of an on-orbit satellite and deployment of solar panels according to claim 1, characterized in that: The fixed solar wing (8) is screwed to the two side surfaces of the satellite body (4) via the oblique support (7).

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