Method and system for assembling complex aircraft power supply systems based on precision allocation

Abstract

The application provides an aircraft complex power system assembly method and system based on precision distribution, comprising the following steps: step 1, installing a flexible solar cell wing support, measuring the installation precision of the flexible solar cell wing support, and adjusting to a set interval; step 2, installing a sun-orienting device, measuring the installation precision of the sun-orienting device, and adjusting to a set interval; step 3, installing a truss assembly, measuring the installation precision of the truss assembly, and adjusting to a set interval; step 4, installing a flexible solar cell wing driving mechanism, measuring the installation precision of the driving mechanism, and adjusting to a set interval; and step 5, installing a flexible solar cell wing, measuring the installation precision of the flexible solar cell wing, and adjusting to a set interval. The application defines the technological process and related parameters of the aircraft complex power system assembly, and has a guiding effect on the assembly of the aircraft complex power system.

Description

Technical Field

[0001] This invention relates to the field of equipment manufacturing technology, and more specifically, to an assembly method and system for a complex power system of an aircraft based on precision allocation. Background Technology

[0002] The complex power system of an aircraft includes the aircraft structure, flexible solar panels, a solar orientation device, and truss assemblies. The flexible solar panels are installed across the aircraft structure, solar orientation device, and truss assemblies. The dimensional accuracy between the various mounting points of the flexible solar panels is ensured by the dimensional accuracy of the aircraft structure, the solar orientation device, and the truss assemblies themselves, as well as the final assembly accuracy of the aircraft.

[0003] To ensure that the installation accuracy of flexible solar cell wings meets the requirements, this invention proposes a method for allocating the accuracy of complex power system assembly requirements for aircraft. This method allocates the accuracy of aircraft structure, the dimensional accuracy of power system equipment, and the installation accuracy of power system equipment, so that after the equipment is assembled, the installation accuracy requirements of flexible solar cell wings can be met with the reserved adjustment margin.

[0004] Patent document CN113751981A discloses a spatial high-precision assembly method and system based on binocular vision servoing. The method includes: triggering left and right cameras to simultaneously detect targets in the parts to be assembled; extracting the pixel coordinates of current feature points in the target from the images captured by the cameras in real time; performing 3D reconstruction of the incomplete target captured by either camera based on linear constraints between feature points; establishing the relationship between feature points and camera velocities through the image Jacobian matrix according to the pixel errors of the feature points, obtaining the target velocity in the base coordinate system, and distributing the velocity under degree-of-freedom constraints between the upper and lower arm mechanisms. Although this patent mentions precision assembly, the object involved in the patent differs from that of this invention and cannot meet the requirements of this invention. Summary of the Invention

[0005] In view of the deficiencies in the prior art, the purpose of this invention is to provide an assembly method and system for complex power systems of aircraft based on precision allocation.

[0006] According to the assembly method of a complex power system for an aircraft based on precision allocation provided by the present invention, the complex power system for an aircraft includes: an aircraft structure, a flexible solar cell wing support, a flexible solar cell wing, a solar orientation device, a truss assembly, and a drive mechanism;

[0007] The flexible solar cell wing support is mounted on the aircraft structure;

[0008] A solar orientation device is installed on the end face of the aircraft structure;

[0009] A truss assembly is installed on the solar orientation device;

[0010] A drive mechanism is installed on the truss assembly;

[0011] The flexible solar cell wing is mounted on the flexible solar cell wing support and the drive mechanism.

[0012] The assembly method includes the following steps:

[0013] Step 1: Install the flexible solar cell wing support, measure the installation accuracy of the flexible solar cell wing support, and adjust the accuracy of the flexible solar cell wing support to the set range;

[0014] Step 2: Install the sun-aligning device, measure the installation accuracy of the sun-aligning device, and adjust the accuracy of the sun-aligning device to the set range;

[0015] Step 3: Install the truss assembly, measure the installation accuracy of the truss assembly, and adjust the accuracy of the truss assembly to the set range;

[0016] Step 4: Install the drive mechanism, measure the installation accuracy of the drive mechanism, and adjust the accuracy of the drive mechanism to the set range;

[0017] Step 5: Install the flexible solar cell wings, measure the installation accuracy of the flexible solar cell wings, and adjust the accuracy of the flexible solar cell wings to the set range.

[0018] Preferably, the accuracy of the solar cell wing support includes: the distance between the geometric center of the solar wing mounting point assembly surface and the reference surface; the parallelism between the solar wing mounting point assembly surface and the reference surface; the flatness of the solar wing mounting points; the parallelism between the solar wing mounting point assembly surfaces; and the distance between the solar wing mounting point assembly axis and the reference point or reference surface.

[0019] Preferably, the accuracy of the sun-orienting device includes: the distance between the aircraft structure mounting surface and the truss support mounting surface; the accuracy of the mating surface with the truss structure support; the coaxiality of the mating surface with the truss support; the accuracy and position of the positioning pin holes connecting to the aircraft structure; the position of the connecting holes with the aircraft structure; the flatness of the connecting surface with the truss support; the flatness of the connecting surface with the aircraft structure; the parallelism of the truss support connecting surface relative to the cabin connecting surface; the angular deviation between the quadrant line markings of the sun-orienting device and the quadrant line of the aircraft structure; measuring the parallelism between the truss mounting surface on the sun-orienting device and the end face of the aircraft structure; and measuring the distance between the truss mounting surface on the sun-orienting device and the end face of the aircraft structure.

[0020] Preferably, the truss assembly precision includes: the distance from the center of the drive mechanism mounting hole to the truss mounting surface; the distance between the drive mechanism mounting surface and the centerline of the spacecraft structure; the precision of the mating surface between the foot support and the arc groove of the sun-orienting device; the coaxiality of the center axis of the drive mechanism mounting hole; the precision of the engraving lines in the outer quadrants of the drive mechanism mounting surface on the truss; the distance between the center of the drive mechanism mounting hole and the centerline of the spacecraft structure; the perpendicularity of the drive mechanism mounting surface relative to the truss foot support mounting surface; the flatness of the connection surface between the truss foot support and the sun-orienting device; the flatness of the drive mechanism mounting surface; the coaxiality of the truss centerline and the center axis of the spacecraft structure; and the angular deviation between the engraving lines on the truss structure and the engraving lines on the flange surface of the spacecraft structure end face.

[0021] Preferably, the accuracy of the drive mechanism includes: the flatness of the truss mounting surface of the drive mechanism; the parallelism between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the coaxiality between the truss mounting hole distribution circle of the drive mechanism and the solar panel mounting hole distribution circle; the distance between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the accuracy of the quadrant markings aligned with the truss on the truss mounting flange of the drive mechanism; the height value between the center of the flange surface of the drive mechanism and the rear end face of the cabin; and the distance between the drive mechanism and the solar panel mounting surface and quadrants I-III.

[0022] According to the precision allocation-based assembly system for complex power systems of aircraft provided by the present invention, the complex power system of aircraft includes: aircraft structure, flexible solar cell wing support, flexible solar cell wing, solar orientation device, truss assembly and drive mechanism;

[0023] The flexible solar cell wing support is mounted on the aircraft structure;

[0024] A solar orientation device is installed on the end face of the aircraft structure;

[0025] A truss assembly is installed on the solar orientation device;

[0026] A drive mechanism is installed on the truss assembly;

[0027] The flexible solar cell wing is mounted on the flexible solar cell wing support and the drive mechanism.

[0028] The assembly system includes the following modules:

[0029] Module M1: Install flexible solar cell wing support, measure the installation accuracy of the flexible solar cell wing support, and adjust the accuracy of the flexible solar cell wing support to the set range;

[0030] Module M2: Install the sun-aligning device, measure the installation accuracy of the sun-aligning device, and adjust the accuracy of the sun-aligning device to the set range;

[0031] Module M3: Install truss components, measure the installation accuracy of truss components, and adjust the accuracy of truss components to the set range;

[0032] Module M4: Install the drive mechanism, measure the installation accuracy of the drive mechanism, and adjust the accuracy of the drive mechanism to the set range;

[0033] Module M5: Install flexible solar cell wings, measure the installation accuracy of flexible solar cell wings, and adjust the accuracy of flexible solar cell wings to the set range.

[0034] Preferably, the accuracy of the solar cell wing support includes: the distance between the geometric center of the solar wing mounting point assembly surface and the reference surface; the parallelism between the solar wing mounting point assembly surface and the reference surface; the flatness of the solar wing mounting points; the parallelism between the solar wing mounting point assembly surfaces; and the distance between the solar wing mounting point assembly axis and the reference point or reference surface.

[0035] Preferably, the accuracy of the sun-orienting device includes: the distance between the aircraft structure mounting surface and the truss support mounting surface; the accuracy of the mating surface with the truss structure support; the coaxiality of the mating surface with the truss support; the accuracy and position of the positioning pin holes connecting to the aircraft structure; the position of the connecting holes with the aircraft structure; the flatness of the connecting surface with the truss support; the flatness of the connecting surface with the aircraft structure; the parallelism of the truss support connecting surface relative to the cabin connecting surface; the angular deviation between the quadrant line markings of the sun-orienting device and the quadrant line of the aircraft structure; measuring the parallelism between the truss mounting surface on the sun-orienting device and the end face of the aircraft structure; and measuring the distance between the truss mounting surface on the sun-orienting device and the end face of the aircraft structure.

[0036] Preferably, the truss assembly precision includes: the distance from the center of the drive mechanism mounting hole to the truss mounting surface; the distance between the drive mechanism mounting surface and the centerline of the spacecraft structure; the precision of the mating surface between the foot support and the arc groove of the sun-orienting device; the coaxiality of the center axis of the drive mechanism mounting hole; the precision of the engraving lines in the outer quadrants of the drive mechanism mounting surface on the truss; the distance between the center of the drive mechanism mounting hole and the centerline of the spacecraft structure; the perpendicularity of the drive mechanism mounting surface relative to the truss foot support mounting surface; the flatness of the connection surface between the truss foot support and the sun-orienting device; the flatness of the drive mechanism mounting surface; the coaxiality of the truss centerline and the center axis of the spacecraft structure; and the angular deviation between the engraving lines on the truss structure and the engraving lines on the flange surface of the spacecraft structure end face.

[0037] Preferably, the accuracy of the drive mechanism includes: the flatness of the truss mounting surface of the drive mechanism; the parallelism between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the coaxiality between the truss mounting hole distribution circle of the drive mechanism and the solar panel mounting hole distribution circle; the distance between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the accuracy of the quadrant markings aligned with the truss on the truss mounting flange of the drive mechanism; the height value between the center of the flange surface of the drive mechanism and the rear end face of the cabin; and the distance between the drive mechanism and the solar panel mounting surface and quadrants I-III.

[0038] Compared with the prior art, the present invention has the following beneficial effects:

[0039] The present invention proposes an assembly method for complex power systems of aircraft based on precision allocation, which allocates the precision of aircraft structure, the precision of power system equipment dimensions, and the precision of power system equipment installation, so that after the equipment is assembled, it can ultimately meet the installation precision requirements of flexible solar cell wings with the reserved adjustment margin. Attached Figure Description

[0040] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0041] Figure 1 An assembly flowchart provided for an embodiment of the present invention;

[0042] Figure 2 This is a schematic diagram of the complex power system structure of an aircraft provided in an embodiment of the present invention;

[0043] In the diagram: 1-Aircraft structure; 2-Flexible solar cell wing support; 3-Flexible solar cell wing; 4-Solar orientation device; 5-Truss assembly; 6-Drive mechanism. Detailed Implementation

[0044] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0045] Example 1

[0046] like Figure 2 As shown, the present invention provides a complex power system for an aircraft, including an aircraft structure 1, a flexible solar cell wing support 2, a flexible solar cell wing 3, a solar orientation device 4, a truss assembly 5, and a drive mechanism 6.

[0047] The flexible solar cell wing support 2 is mounted on the aircraft structure 1. The solar orientation device 4 is mounted on the end face of the aircraft structure 1. The truss assembly 5 is mounted on the solar orientation device 4. The drive mechanism 6 is mounted on the truss assembly 5. The flexible solar cell wing 3 is mounted on the flexible solar cell wing support 2 and the drive mechanism 6.

[0048] like Figure 1 As shown, this invention provides an assembly method for a complex power system of an aircraft based on precision allocation, comprising the following steps:

[0049] Step 1: Install the flexible solar cell wing support 2.

[0050] Furthermore, the installation accuracy of the flexible solar cell wing support 2 is measured, including but not limited to: the distance between the geometric center of the solar wing mounting point assembly surface and the reference surface; the parallelism between the solar wing mounting point assembly surface and the reference surface; the flatness of the solar wing mounting points; the parallelism between the solar wing mounting point assembly surfaces; and the distance between the solar wing mounting point assembly axis and the reference point or reference surface.

[0051] Furthermore, the precision of the flexible solar cell wing support 2 was adjusted to the set range.

[0052] Step 2: Place the sun-oriented device 4 stably on the mounting surface of the aircraft structure 1 and secure it with fasteners.

[0053] Furthermore, the installation accuracy of the sun-orienting device 4 is measured. This includes using a theodolite to observe the angular deviation between the quadrant lines of the sun-orienting device 4 and the quadrant lines of the aircraft structure, measuring the parallelism between the truss mounting surface of the sun-orienting device 4 and the end face of the aircraft structure, and measuring the distance between the truss mounting surface of the sun-orienting device 4 and the end face of the aircraft structure.

[0054] Furthermore, the accuracy of the sun-orientation device 4 is adjusted to the set range by adjusting the shims. The parallelism between the truss mounting surface on the sun-orientation device and the end face of the aircraft structure is adjusted to be no greater than 0.5.

[0055] Step 3: Place the truss assembly 5 stably on the mounting surface of the sun-oriented device 4 and secure it with fasteners.

[0056] Furthermore, the installation accuracy of truss assembly 5 is measured. This includes precise measurement of the coaxiality between the truss centerline and the central axis of the aircraft structure 1, and the angular deviation between the truss structure engraving and the flange surface engraving on the end face of the aircraft structure 1.

[0057] Furthermore, the accuracy of the day-orientation device is adjusted to the set range by adjusting the mounting shims of truss assembly 5.

[0058] Step 4: Install the flexible solar cell wing drive mechanism 6.

[0059] Furthermore, the installation accuracy of the drive mechanism 6 is measured, including the actual height value between the center of the flange face of the drive mechanism 6 and the rear end face of the cabin, and the distance between the drive mechanism 6 and the solar cell wing mounting surface and quadrants I-III.

[0060] Furthermore, the accuracy requirements are ensured by adjusting the drive mechanism 6 and placing shims on the truss assembly 5 and the sun-oriented device 4.

[0061] Step 5: Install the flexible solar cell wing 3.

[0062] Furthermore, the installation accuracy of the flexible solar cell wing 3 was measured, and the accuracy of the flexible solar cell wing 3 was adjusted to the set range.

[0063] Example 2

[0064] The present invention also provides an assembly system for complex power systems of aircraft based on precision allocation. The assembly system for complex power systems of aircraft based on precision allocation can be implemented by executing the process steps of the assembly method for complex power systems of aircraft based on precision allocation. That is, those skilled in the art can understand the assembly method for complex power systems of aircraft based on precision allocation as a preferred embodiment of the assembly system for complex power systems of aircraft based on precision allocation.

[0065] This invention provides an assembly system for a complex power system of an aircraft based on precision allocation. The complex power system of the aircraft includes: an aircraft structure 1, a flexible solar cell wing support 2, a flexible solar cell wing 3, a solar orientation device 4, a truss assembly 5, and a drive mechanism 6.

[0066] The flexible solar cell wing support 2 is mounted on the aircraft structure 1; a solar orientation device 4 is mounted on the end face of the aircraft structure 1; a truss assembly 5 is mounted on the solar orientation device 4; a drive mechanism 6 is mounted on the truss assembly 5; and the flexible solar cell wing 3 is mounted on the flexible solar cell wing support 2 and the drive mechanism 6.

[0067] The assembly system includes the following modules: Module M1: Installs the flexible solar cell wing support, measures the installation accuracy of the flexible solar cell wing support, and adjusts the accuracy of the flexible solar cell wing support to a set range; Module M2: Installs the solar orientation device, measures the installation accuracy of the solar orientation device, and adjusts the accuracy of the solar orientation device to a set range; Module M3: Installs the truss assembly, measures the installation accuracy of the truss assembly, and adjusts the accuracy of the truss assembly to a set range; Module M4: Installs the drive mechanism, measures the installation accuracy of the drive mechanism, and adjusts the accuracy of the drive mechanism to a set range; Module M5: Installs the flexible solar cell wing, measures the installation accuracy of the flexible solar cell wing, and adjusts the accuracy of the flexible solar cell wing to a set range.

[0068] The accuracy of solar cell fin support includes: the distance between the geometric center of the solar fin mounting point assembly surface and the reference surface; the parallelism between the solar fin mounting point assembly surface and the reference surface; the flatness of the solar fin mounting points; the parallelism between the solar fin mounting point assembly surfaces; and the distance between the solar fin mounting point assembly axis and the reference point or reference surface.

[0069] The accuracy of the solar orientation device includes: the distance between the aircraft structure mounting surface and the truss support mounting surface; the accuracy of the mating surface with the truss support; the coaxiality of the mating surface with the truss support; the accuracy and position of the positioning pin holes connecting to the aircraft structure; the position of the connecting holes with the aircraft structure; the flatness of the connecting surface with the truss support; the flatness of the connecting surface with the aircraft structure; the parallelism of the truss support connecting surface relative to the cabin connecting surface; the angular deviation between the quadrant lines of the solar orientation device and the quadrant lines of the aircraft structure; the parallelism between the truss mounting surface on the solar orientation device and the end face of the aircraft structure; and the distance between the truss mounting surface on the solar orientation device and the end face of the aircraft structure.

[0070] The truss assembly precision includes: the distance from the center of the drive mechanism mounting hole to the truss mounting surface; the distance between the drive mechanism mounting surface and the centerline of the spacecraft structure; the precision of the mating surface between the foot support and the arc groove of the sun-orienting device; the coaxiality of the center axis of the drive mechanism mounting hole; the precision of the engraving lines in the outer quadrants of the drive mechanism mounting surface on the truss; the distance between the center of the drive mechanism mounting hole and the centerline of the spacecraft structure; the perpendicularity of the drive mechanism mounting surface relative to the truss foot support mounting surface; the flatness of the connection surface between the truss foot support and the sun-orienting device; the flatness of the drive mechanism mounting surface; the coaxiality of the truss centerline and the center axis of the spacecraft structure; and the angular deviation between the engraving lines on the truss structure and the engraving lines on the flange surface of the spacecraft structure end face.

[0071] The accuracy of the drive mechanism includes: the flatness of the truss mounting surface of the drive mechanism; the parallelism between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the coaxiality between the truss mounting hole distribution circle of the drive mechanism and the solar panel mounting hole distribution circle; the distance between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the accuracy of the quadrant markings on the truss mounting flange of the drive mechanism that are aligned with the truss; the height value between the center of the flange surface of the drive mechanism and the rear end face of the cabin; and the distance between the drive mechanism and the solar panel mounting surface and quadrants I-III.

[0072] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0073] Those skilled in the art will understand that, in addition to implementing the system, apparatus, and their modules provided by this invention in purely computer-readable program code, the same program can be implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system, apparatus, and their modules provided by this invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; alternatively, modules for implementing various functions can be considered both software programs implementing the method and structures within the hardware component.

[0074] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for assembling a complex power system for an aircraft based on precision allocation, characterized in that, The complex power system of the aircraft includes: aircraft structure (1), flexible solar cell wing support (2), flexible solar cell wing (3), solar orientation device (4), truss assembly (5) and drive mechanism (6). The flexible solar cell wing support (2) is mounted on the aircraft structure (1); The end face of the aircraft structure (1) is equipped with a solar orientation device (4); A truss assembly (5) is installed on the sun-oriented device (4); A drive mechanism (6) is installed on the truss assembly (5); The flexible solar cell wing (3) is mounted on the flexible solar cell wing support (2) and the drive mechanism (6); The assembly method includes the following steps: Step 1: Install the flexible solar cell wing support, measure the installation accuracy of the flexible solar cell wing support, and adjust the accuracy of the flexible solar cell wing support to the set range; Step 2: Install the sun-aligning device, measure the installation accuracy of the sun-aligning device, and adjust the accuracy of the sun-aligning device to the set range; The measurement of the installation accuracy of the sun-orienting device includes: measuring the parallelism between the truss mounting surface on the sun-orienting device and the end face of the aircraft structure; Step 3: Install the truss assembly, measure the installation accuracy of the truss assembly, and adjust the accuracy of the truss assembly to the set range; The measurement of the installation accuracy of the truss assembly includes: measuring the coaxiality between the centerline of the truss and the center axis of the aircraft structure; Step 4: Install the drive mechanism, measure the installation accuracy of the drive mechanism, and adjust the accuracy of the drive mechanism to the set range; Step 5: Install the flexible solar cell wings, measure the installation accuracy of the flexible solar cell wings, and adjust the accuracy of the flexible solar cell wings to the set range.

2. The assembly method for complex aircraft power systems based on precision allocation according to claim 1, characterized in that, The accuracy of solar cell fin support includes: the distance between the geometric center of the solar fin mounting point assembly surface and the reference surface; the parallelism between the solar fin mounting point assembly surface and the reference surface; the flatness of the solar fin mounting points; the parallelism between the solar fin mounting point assembly surfaces; and the distance between the solar fin mounting point assembly axis and the reference point or reference surface.

3. The assembly method for complex aircraft power systems based on precision allocation according to claim 1, characterized in that, The accuracy of the sun orientation device includes: the distance between the aircraft structure mounting surface and the truss support mounting surface; the accuracy of the mating surface with the truss support; the coaxiality of the mating surface with the truss support; the accuracy and position of the positioning pin holes connecting to the aircraft structure; the position of the connecting holes with the aircraft structure; the flatness of the connecting surface with the truss support; the flatness of the connecting surface with the aircraft structure; the parallelism of the truss support connecting surface relative to the cabin connecting surface; the angular deviation between the quadrant lines of the sun orientation device and the quadrant lines of the aircraft structure; and the measurement of the distance between the truss mounting surface on the sun orientation device and the end face of the aircraft structure.

4. The assembly method for complex aircraft power systems based on precision allocation according to claim 1, characterized in that, The truss assembly precision includes: the distance from the center of the drive mechanism mounting hole to the truss mounting surface; the distance between the drive mechanism mounting surface and the centerline of the spacecraft structure; the precision of the mating surface between the foot support and the arc groove of the sun-orienting device; the coaxiality of the center axis of the drive mechanism mounting hole; the precision of the engraving lines in the outer quadrants of the drive mechanism mounting surface on the truss; the distance between the center of the drive mechanism mounting hole and the centerline of the spacecraft structure; the perpendicularity of the drive mechanism mounting surface relative to the truss foot support mounting surface; the flatness of the connection surface between the truss foot support and the sun-orienting device; the flatness of the drive mechanism mounting surface; and the angular deviation between the engraving lines on the truss structure and the engraving lines on the flange surface on the end face of the spacecraft structure.

5. The assembly method for complex aircraft power systems based on precision allocation according to claim 1, characterized in that, The accuracy of the drive mechanism includes: the flatness of the truss mounting surface of the drive mechanism; the parallelism between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the coaxiality between the truss mounting hole distribution circle of the drive mechanism and the solar panel mounting hole distribution circle; the distance between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the accuracy of the quadrant markings on the truss mounting flange of the drive mechanism that are aligned with the truss; the height value between the center of the flange surface of the drive mechanism and the rear end face of the cabin; and the distance between the drive mechanism and the solar panel mounting surface and quadrants I-III.

6. An assembly system for a complex power system of an aircraft based on precision allocation, characterized in that, The complex power system of the aircraft includes: aircraft structure (1), flexible solar cell wing support (2), flexible solar cell wing (3), solar orientation device (4), truss assembly (5) and drive mechanism (6). The flexible solar cell wing support (2) is mounted on the aircraft structure (1); The end face of the aircraft structure (1) is equipped with a solar orientation device (4); A truss assembly (5) is installed on the sun-oriented device (4); A drive mechanism (6) is installed on the truss assembly (5); The flexible solar cell wing (3) is mounted on the flexible solar cell wing support (2) and the drive mechanism (6); The assembly system includes the following modules: Module M1: Install flexible solar cell wing support, measure the installation accuracy of the flexible solar cell wing support, and adjust the accuracy of the flexible solar cell wing support to the set range; Module M2: Install the sun-aligning device, measure the installation accuracy of the sun-aligning device, and adjust the accuracy of the sun-aligning device to the set range; The measurement of the installation accuracy of the sun-orienting device includes: measuring the parallelism between the truss mounting surface on the sun-orienting device and the end face of the aircraft structure; Module M3: Install truss components, measure the installation accuracy of truss components, and adjust the accuracy of truss components to the set range; The measurement of the installation accuracy of the truss assembly includes: measuring the coaxiality between the centerline of the truss and the center axis of the aircraft structure; Module M4: Install the drive mechanism, measure the installation accuracy of the drive mechanism, and adjust the accuracy of the drive mechanism to the set range; Module M5: Install flexible solar cell wings, measure the installation accuracy of flexible solar cell wings, and adjust the accuracy of flexible solar cell wings to the set range.

7. The assembly system for complex aircraft power systems based on precision allocation according to claim 6, characterized in that, The accuracy of solar cell fin support includes: the distance between the geometric center of the solar fin mounting point assembly surface and the reference surface; the parallelism between the solar fin mounting point assembly surface and the reference surface; the flatness of the solar fin mounting points; the parallelism between the solar fin mounting point assembly surfaces; and the distance between the solar fin mounting point assembly axis and the reference point or reference surface.

8. The assembly system for complex aircraft power systems based on precision allocation according to claim 6, characterized in that, The accuracy of the sun orientation device includes: the distance between the aircraft structure mounting surface and the truss support mounting surface; the accuracy of the mating surface with the truss support; the coaxiality of the mating surface with the truss support; the accuracy and position of the positioning pin holes connecting to the aircraft structure; the position of the connecting holes with the aircraft structure; the flatness of the connecting surface with the truss support; the flatness of the connecting surface with the aircraft structure; the parallelism of the truss support connecting surface relative to the cabin connecting surface; the angular deviation between the quadrant lines of the sun orientation device and the quadrant lines of the aircraft structure; and the measurement of the distance between the truss mounting surface on the sun orientation device and the end face of the aircraft structure.

9. The assembly system for complex aircraft power systems based on precision allocation according to claim 6, characterized in that, The truss assembly precision includes: the distance from the center of the drive mechanism mounting hole to the truss mounting surface; the distance between the drive mechanism mounting surface and the centerline of the spacecraft structure; the precision of the mating surface between the foot support and the arc groove of the sun-orienting device; the coaxiality of the center axis of the drive mechanism mounting hole; the precision of the engraving lines in the outer quadrants of the drive mechanism mounting surface on the truss; the distance between the center of the drive mechanism mounting hole and the centerline of the spacecraft structure; the perpendicularity of the drive mechanism mounting surface relative to the truss foot support mounting surface; the flatness of the connection surface between the truss foot support and the sun-orienting device; the flatness of the drive mechanism mounting surface; and the angular deviation between the engraving lines on the truss structure and the engraving lines on the flange surface on the end face of the spacecraft structure.

10. The assembly system for complex aircraft power systems based on precision allocation according to claim 6, characterized in that, The accuracy of the drive mechanism includes: the flatness of the truss mounting surface of the drive mechanism; the parallelism between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the coaxiality between the truss mounting hole distribution circle of the drive mechanism and the solar panel mounting hole distribution circle; the distance between the truss mounting surface of the drive mechanism and the solar panel mounting surface; the accuracy of the quadrant markings on the truss mounting flange of the drive mechanism that are aligned with the truss; the height value between the center of the flange surface of the drive mechanism and the rear end face of the cabin; and the distance between the drive mechanism and the solar panel mounting surface and quadrants I-III.

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