A method for rapid digital guidance and positioning of thermal protection components

Abstract

This invention provides a digital rapid guidance and positioning method for thermal protection components, belonging to the field of aerospace manufacturing engineering / aircraft assembly. The invention first uses digital measuring instruments to scan the fuselage surface to be bonded and the thermal protection components, forming a measurement point cloud dataset. Then, a three-dimensional model of the actual state is obtained through reverse modeling. Next, virtual assembly technology is used to correct the installation of the thermal protection components, obtaining a dataset of the actual assembly positions of each component. Finally, laser projection and digital measurement methods are used to guide and position the thermal protection components, achieving high-precision and rapid assembly of the thermal protection structure. This invention combines digital measurement and virtual assembly simulation technologies. During the assembly process, laser projection and digital measurement methods are used to guide and position the thermal protection components, ensuring a high first-time assembly success rate, reducing damage to the thermal protection components from repeated disassembly and assembly, improving assembly efficiency, and reducing production costs.

Description

Technical Field

[0001] This invention belongs to the field of aerospace manufacturing engineering / aircraft assembly, and relates to a digital rapid guidance and positioning method for thermal protection components, which is used to perform rapid and accurate assembly of thermal protection components by measuring and guiding their positioning using digital measurement methods. Background Technology

[0002] During high-speed flight, reusable high-Mach vehicles experience significant temperature rises on their surfaces due to aerodynamic loads. High-performance thermal protection systems are essential to maintain the structural temperature within permissible ranges. Oxide ceramic fiber rigid thermal insulation tiles and flexible felts, among other thermal protection components, are characterized by high temperature resistance, low density, low thermal conductivity, erosion resistance, and the ability to maintain aerodynamic shape. They are among the primary thermal protection materials for hypersonic vehicles, used on both the leading and leeward sides of the aircraft. However, large aircraft require a large quantity of thermal insulation tiles / flexible felts, and their shapes vary greatly depending on the curvature of the airframe, making universality insufficient. Therefore, eliminating the cumulative effects of errors and achieving precise and rapid installation onto the airframe surface has become a critical technical challenge that urgently needs to be addressed.

[0003] The United States has developed a series of ceramic thermal insulation tiles, which are important candidate materials for the design of thermal insulation structures for large areas and special parts of US hypersonic vehicles. These tiles are used in aerospace and civilian aircraft, advanced strategic air-launched missiles (ASALM), and other hypersonic vehicles, ensuring the integrity of the vehicle's structure and flight safety. European hypersonic vehicles also employ similar thermal insulation tile technology. For example, the German Aerospace Center (DLR) has developed two types of high-temperature resistant multilayer thermal insulation layers for large-area thermal protection systems of hypersonic vehicles (excluding the nose cone and wing leading edge). Domestically, the development of thermal insulation materials has been rapid and diversified, mainly focusing on traditional rigid thermal insulation tiles / flexible felts, aerogel materials, and adhesives. While domestic and international scholars have conducted extensive research on thermal insulation materials, there is very little technical literature or reports on the assembly of thermal protection components. The US Space Shuttle had tens of thousands of thermal insulation tiles on its surface, with varying shapes. The manual assembly method was time-consuming and labor-intensive, requiring a high level of operator experience and limiting the assembly accuracy of the thermal insulation tiles. The domestic thermal protection structure assembly industry is still in its developmental stage. In engineering applications, the cumulative errors in aircraft shape manufacturing and thermal protection component preparation lead to high rework rates and increased damage to thermal protection components. These components are valuable, especially the heat insulation tiles, whose preparation cycle can be as long as 3-6 months, significantly increasing manufacturing time and costs. In recent years, digital measurement technology has shown significant effectiveness in aircraft assembly, serving not only as a means of evaluating product assembly accuracy but also providing closed-loop control for the process, effectively improving the overall controllability and quality of key assembly and auxiliary processes. Aircraft assembly processes are long and susceptible to cumulative errors. By combining reverse modeling based on measured data and virtual assembly simulation technology, the fitting accuracy of key components can be verified on a computer, quality deviations affecting final assembly accuracy can be identified in advance, and timely process compensation measures can be formulated, improving the first-time success rate of assembly. Summary of the Invention

[0004] This invention proposes a digital rapid guidance and positioning method for thermal protection components. Combining digital measurement and virtual assembly simulation technology, it clarifies the actual state of the thermal protection components and the machine body surface and establishes an actual model. Based on virtual assembly technology, it formulates a dynamic and rapid adjustment scheme for the position of the thermal protection components. During the assembly process, laser projection and digital measurement are used to guide and position the thermal protection components, ensuring a high first-time assembly success rate, reducing damage to the thermal protection components from repeated disassembly and assembly, improving assembly efficiency, and reducing production costs.

[0005] Typically, thermal protection components are mounted on the surface of hypersonic vehicles, employing methods such as... Figure 1As shown, the thermal insulation tiles in the thermal protection assembly are aligned with the boundary of the aircraft structure, and the spaces between the tiles are filled with fiber insulation tape to compensate for thermal deformation while preventing hot air from entering. Due to the large area to be protected, and the influence of manufacturing errors in the aircraft parts and thermal protection components, incomplete surface coverage or the thermal protection components extending beyond the aircraft surface may occur if the assembly position of the thermal protection components is not corrected. This invention first uses a digital measuring instrument to scan the surface of the aircraft to be bonded and the thermal protection components, forming a measurement point cloud dataset. Then, a three-dimensional model of the actual state is obtained through reverse modeling. Next, virtual assembly technology is used to correct the installation of the thermal protection components, obtaining a dataset of the actual assembly positions of each thermal protection component. Finally, laser projection and digital measurement methods are used to guide and position the thermal protection components, achieving high-precision and rapid assembly of the thermal protection structure.

[0006] The technical solution adopted in this invention is as follows:

[0007] A digital rapid guidance and positioning method for a thermal protection component, comprising the following steps:

[0008] Step 1: Data Acquisition and Reverse Modeling;

[0009] A 3D scanner was used to measure the surface of the aircraft to be bonded and the thermal protection component 1, mainly the heat insulation tiles in the thermal protection component 1, to collect surface point cloud data. The surface point cloud data was then processed using commercial measurement and analysis software to remove measurement noise, repair point cloud defects, etc. Based on a theoretical model, a best-fit method was used for coordinate alignment, compressing the surface point cloud data size to obtain the point cloud dataset of the surface to be bonded and the thermal protection component 1. The point cloud acquisition principles are as follows:

[0010] (a) For areas with small surface curvature changes and large flat areas, uniform low-density sampling is used to compress point cloud density and reduce computational scale.

[0011] (b) For surfaces with large curvature changes, use chord deviation sampling and appropriately increase the point cloud density to improve the surface fitting accuracy;

[0012] (c) For the body structure boundary 3, high-density sampling of the boundary is adopted, that is, the highest point cloud density is adopted, and the point cloud spacing should not exceed 0.2mm.

[0013] Based on the above point cloud dataset, data analysis software was used to import the point cloud data and accurately model the surface of the aircraft to be pasted and the thermal protection component 1.

[0014] Step 2, conduct deviation analysis;

[0015] Due to errors in the processing, molding, and assembly of the surface to be bonded to the aircraft and thermal protection component 1, the actual assembly process should comprehensively consider these errors to eliminate the impact of error accumulation on the assembly accuracy of the thermal protection component, as detailed below:

[0016] Step 2.1, analyze the error of the surface to be pasted on the aircraft.

[0017] according to Figure 1 The position shown is defined as P, where the center point of the thermal protection component 1 in the j-th row and i-th column is defined as P. ji Selected via P ji cross section L i and W j , where the cross section L i (i = 1, 2, ..., n) The direction is parallel to the heading, and the cross section W j (j=1,2,…,m) The direction is parallel to the wingspan direction, n is the number of parallel heat insulation tile layers along the flight direction, and m is the number of heat insulation tile layers along the wingspan direction. Based on data analysis software, section L is used. i and W j Intersecting with both the theoretical and actual models of the surface to be pasted on the aircraft, the spatial curves of the cross-sections at the intersections are extracted, such as... Figure 2 As shown, cross section L is obtained respectively. i and W j Arc length of the spatial curve intersecting with the theoretical model of the surface to be pasted and and cross section L i and W j The arc length of the curve intersecting the actual model of the surface to be pasted and The change in the arc length of the curve between the actual model and the theoretical model, i.e., the error of the surface to be pasted on the aircraft, is defined as:

[0018]

[0019]

[0020] Based on formulas (1) and (2), we obtain the result that passes through all center points P. ji The change in arc length of the actual cross-section model compared to the theoretical model serves as one of the numerical bases for dynamically adjusting the assembly position of the thermal protection component 1.

[0021] Step 2.2, analyze the dimensional error of thermal protection component 1

[0022] Errors in the molding and coating thickness of thermal protection component 1 are mainly reflected in variations in side length, such as... Figure 3 As shown. Based on the theoretical model of the point cloud dataset of thermal protection component 1, the actual deviation values ​​of each side can be extracted by comparing it with the theoretical boundary 4 of thermal protection component 1. Define section L. i and Wj The tangents of the curves intersecting the surface to be pasted are in the x and y directions, respectively, and the normal direction is in the z direction. A coordinate system is established, and the center points of the theoretical model and the actual model of a certain thermal protection component 1 are aligned. The outer envelope curves of each side profile are taken as the fitting boundary 5 of the thermal protection component 1. The dimensional error of the thermal protection component 1 is then defined as:

[0023] Δl ji =x1+x2 (3)

[0024] Δh ji =y1+y2 (4)

[0025] In the formula, x1 and x2 are the errors of the two side boundaries in the x-direction, and Δl ji Let y1 and y2 be the cumulative error in the x-direction, and y1 and y2 be the errors at the two boundaries in the y-direction, Δh ji The cumulative error in the y-direction is defined as follows: when the fitting boundary 5 of the thermal protection component 1 is greater than the theoretical boundary 4, x1, x2, y1 and y2 are defined as positive, and otherwise as negative.

[0026] Step 3, Dynamic optimization of assembly position;

[0027] Currently, thermal protection component 1 mainly uses heat-insulating tiles and flexible felt. The flexible felt is located on the leeward side, has good elasticity, and is easy to assemble and attach. Therefore, the dynamic optimization of assembly gaps mainly considers the heat-insulating tiles. Because the surface to be attached on the aircraft is large (length can exceed 5m), manufacturing and assembly errors of the parts have the greatest impact on the thermal protection assembly. A detailed analysis follows:

[0028] An initial gap d (typically 1mm ± 0.5mm) is set between the heat insulation tiles to compensate for thermal deformation, prevent damage to the tiles, and ensure effective thermal protection. The elimination of manufacturing and assembly errors affecting the surface components is primarily achieved through dynamic adjustment of the gap between the heat insulation tiles. Given the large and relatively flat area of ​​the surface to be bonded, and the relatively small size of the thermal protection components, the dynamic adjustment of their position involves components in both the x and y directions.

[0029] Using the structural boundary 3 as a reference, the heat insulation tiles connected to the structural boundary 3 are aligned and remain stationary. The remaining heat insulation tiles are adjusted using a uniform distribution method. The interlayer position adjustment amounts for the heat insulation tiles are a. j / (n-1) and b i / (m-1). Therefore, the adjustment amount for the position of each heat insulation tile is:

[0030]

[0031]

[0032] Adjust the length and height of the insulation tiles, taking Δl for each side.ji / 2 and Δh ji / 2, Calculate the gap values ​​between the four sides of the heat insulation tile and the corresponding sides of each adjacent heat insulation tile:

[0033]

[0034]

[0035] Determine the two components of the gap. x and gap y Whether it is ≤0.5mm, if the condition is met, it is considered to meet the requirements. The adjustment value of the heat insulation tile in the j-th row and i-th column is determined as (Δx). i Δy j If the requirements are not met, such as if the gap component in the x-direction is greater than 0.5mm, then the excess value is defined as e, and the adjustment amounts for the corresponding sides of adjacent insulation tiles are -e / 2 and e / 2, respectively. After recalculating the boundary error of the heat insulation tile, judge according to formula (7). If it still does not meet the requirements, adjust the heat insulation tiles of the upper and lower layers until they meet the requirements; the same applies to the y direction.

[0036] Finally, the position adjustment amount of each heat insulation tile was obtained and converted into the machine coordinate system, resulting in the coordinates of the center point of the heat insulation tile after adjustment as P. ji (x, y).

[0037] Step 4, Digital Guidance and Positioning;

[0038] Based on the position coordinates P of each heat insulation tile ji Using (x, y) and the fitted actual boundary of the insulation tile, laser projection is used to map the installation position of each insulation tile onto the surface to be pasted. After the insulation tiles are installed in their respective positions, digital measurement technology is used to accurately correct their positions, achieving rapid guidance and positioning.

[0039] The beneficial effects of this invention are as follows:

[0040] Thermal protection components such as heat insulation tiles have long manufacturing cycles, low strength, and high prices, significantly impacting manufacturing costs and timelines. This invention combines digital measurement, reverse modeling, and virtual simulation technologies to clearly identify the actual manufacturing deviations between the thermal protection components and the machine body surface in virtual space. It then develops a dynamic and rapid adjustment scheme for the assembly position of the thermal protection components and uses laser projection and digital measurement to guide and position them, ensuring a high first-time assembly success rate, reducing damage from repeated disassembly and reassembly, improving assembly efficiency, and lowering production costs. Attached Figure Description

[0041] Figure 1 Schematic diagram of thermal protection component installation;

[0042] Figure 2 Coordinate definition diagram of thermal protection components;

[0043] Figure 3 Schematic diagram of digital modeling of thermal protection components;

[0044] Figure 4 Implementation flowchart

[0045] In the figure: 1 Thermal protection component; 2 Fiber insulation strip; 3 Body structure boundary; 4 Theoretical boundary; 5 Fitting boundary. Detailed Implementation

[0046] The technical solution of the present invention will now be clearly and completely described. Obviously, the described embodiments are merely some embodiments of the present invention, and not all embodiments. All other embodiments derived by those skilled in the art based on the embodiments of the present invention through modifications or adjustments are within the protection scope of the present invention.

[0047] A method for rapid digital guidance and positioning of thermal protection components, the specific implementation process of which is as follows: Figure 4 As shown, it includes the following steps:

[0048] (1) Constructing a high-precision digital measurement field

[0049] Based on the process requirements for digital measurement and guidance of thermal protection component 1, a measurement field was built and high-precision calibration was performed. A working coordinate system was established, with a tracking measurement accuracy of not less than 0.02 mm / m and a single-scan measurement accuracy of not less than 0.03 mm.

[0050] (2) Data Acquisition and Reverse Modeling

[0051] After establishing the working coordinate system, measurements were performed on the surface to be pasted and all thermal protection components 1 of the aircraft using a tracking measuring instrument and a 3D scanner, collecting point cloud data. The point cloud data was then processed using commercial measurement and analysis software (such as Polyworks) to remove measurement noise, repair point cloud defects, etc. Based on the theoretical model, a best-fit method was used for coordinate alignment, compressing the surface point cloud data size to obtain the point cloud dataset of the surface to be pasted and thermal protection components 1. The point cloud acquisition principles are as follows:

[0052] (a) For areas with small surface curvature changes and large flat areas, uniform low-density sampling is used to compress point cloud density and reduce computational scale.

[0053] (b) For surfaces with large curvature changes, use chord deviation sampling and appropriately increase the point cloud density to improve the surface fitting accuracy;

[0054] (c) For the body structure boundary 3, high-density sampling of the boundary is adopted, that is, the highest point cloud density is adopted, and the point cloud spacing should not exceed 0.2mm.

[0055] Based on the above point cloud dataset, precise models were created for the surface of the aircraft to be pasted and the thermal protection component 1, with each thermal protection component 1 modeled separately.

[0056] (3) Fit Deviation Analysis

[0057] Due to errors in the processing, molding, and assembly of the surface to be bonded to the aircraft and thermal protection component 1, the actual assembly process should comprehensively consider these errors to eliminate the impact of error accumulation on the assembly accuracy of the thermal protection component, as detailed below:

[0058] ①Analyze the surface error of the aircraft to be pasted

[0059] according to Figure 1 The position shown is defined as P, where the center point of the thermal protection component 1 in the j-th row and i-th column is defined as P. ji Selected via P ji cross section L i and W j , where the cross section L i (i = 1, 2, ..., n) The direction is parallel to the heading, and the cross section W j (j=1,2,…,m) The direction is parallel to the wingspan direction, n is the number of parallel heat insulation tile layers along the flight direction, and m is the number of heat insulation tile layers along the wingspan direction. Based on data analysis software, section L is used. i and W j Intersecting with both the theoretical and actual models of the surface to be pasted on the aircraft, the spatial curves of the cross-sections at the intersections are extracted, such as... Figure 2 As shown, cross section L is obtained respectively. i and W j Arc length of the spatial curve intersecting with the theoretical model of the surface to be pasted and and cross section L i and W j The arc length of the curve intersecting the actual model of the surface to be pasted and The change in curve arc length between the actual model and the theoretical model, as shown in formulas (1) and (2), is obtained by passing through all center points P. ji The change in arc length of the actual cross-section model compared to the theoretical model serves as one of the numerical bases for dynamically adjusting the assembly position of the thermal protection component 1.

[0060] ②Analysis of dimensional errors in thermal protection component 1

[0061] Errors in the molding and coating thickness of thermal protection component 1 are mainly reflected in variations in side length, such as... Figure 3As shown. Based on the theoretical model of the point cloud dataset of thermal protection component 1, the actual deviation values ​​of each side can be extracted by comparing it with the theoretical boundary 4 of thermal protection component 1. Define section L. i and W j The tangents of the curves intersecting the surface to be pasted are x and y, respectively, and the normal direction is z. A coordinate system is established, and the center point of the theoretical model and the actual model of a certain thermal protection component 1 are aligned. The outer envelope curve of each side contour surface is taken as the fitting boundary 5 of the thermal protection component 1. Then the size error of the thermal protection component 1 is as shown in formulas (3) and (4).

[0062] (4) Setting the assembly position adjustment value

[0063] An initial gap d (typically 1mm ± 0.5mm) is set between the heat insulation tiles to compensate for thermal deformation, prevent damage to the tiles, and ensure effective thermal protection. The elimination of manufacturing and assembly errors affecting the surface components is primarily achieved through dynamic adjustment of the gap between the heat insulation tiles. Given the large and relatively flat area of ​​the surface to be bonded, and the relatively small size of the thermal protection components, the dynamic adjustment of their position involves components in both the x and y directions.

[0064] Using the structural boundary 3 as a reference, the heat insulation tiles connected to the structural boundary 3 are aligned and remain stationary. The remaining heat insulation tiles are adjusted using a uniform distribution method. The interlayer position adjustment amounts for the heat insulation tiles are a. j / (n-1) and b i / (m-1). Therefore, the adjustment amount of each heat insulation tile position is as shown in formulas (5) and (6).

[0065] (5) Dynamic optimization of assembly position

[0066] Considering the variations in the length and height of the insulation tile, each side is taken as Δl. ij / 2 and Δh ij / 2, calculate the gap values ​​between the four sides of the insulation tile and the corresponding sides of each adjacent insulation tile according to equations (7) and (8). Determine the two components of gap. x and gap y Whether it is ≤0.5mm, if the condition is met, it is considered to meet the requirements. The adjustment value of the heat insulation tile in the j-th row and i-th column is determined as (Δx). i Δy j If the requirements are not met, such as if the gap component in the x-direction is greater than 0.5mm, then the excess value is defined as e, and the adjustment amounts for the corresponding sides of adjacent insulation tiles are -e / 2 and e / 2, respectively. After recalculating the boundary error of the heat insulation tile, judge according to formula (7). If it still does not meet the requirements, adjust the heat insulation tiles of the upper and lower layers until they meet the requirements; the same applies to the y item.

[0067] Finally, the position adjustment amount of each heat insulation tile was obtained and converted into the machine coordinate system, resulting in the coordinates of the center point of the heat insulation tile after adjustment as P. ji (x, y).

[0068] (6) Digital guidance and positioning

[0069] Based on the position coordinates P of each heat insulation tile ji (x, y), and according to Figure 3 The actual boundaries of the fitted insulation tiles are projected onto the surface to be pasted using laser projection. After the insulation tiles are installed in their respective positions, digital measurement technology is used to precisely correct their positions, enabling rapid guidance and positioning.

[0070] The above-described embodiments are merely illustrative of the implementation methods of the present invention, but should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the protection scope of the present invention.

Claims

1. A method for rapid digital guidance and positioning of a thermal protection component, characterized in that, The digital rapid guidance and positioning method includes the following steps: Step 1: Build the measurement system, collect data, and perform reverse modeling; The surface to be pasted and the thermal protection component (1) of the aircraft were measured to collect surface point cloud data; the surface point cloud data was lightened and the best fitting method was used to align the coordinates based on the theoretical model to compress the scale of the surface point cloud data, so as to obtain the point cloud dataset of the surface to be pasted and the thermal protection component (1). Based on the above point cloud dataset, data analysis software was used to import the point cloud data and to accurately model the surface to be pasted on the aircraft and the thermal protection components (1) respectively. Step 2, conduct deviation analysis; Step 2.1, analyze the error of the surface to be pasted on the aircraft. Define the center point of the thermal protection component (1) in row j and column i as P. ji Selected via P ji cross section L i and W j , where the cross section L i (i=1,2,…,n) The direction is parallel to the heading, and the cross section W j (j=1,2,…,m) The direction is parallel to the wingspan direction, n is the number of parallel heat insulation tile layers along the flight direction, and m is the number of heat insulation tile layers along the wingspan direction; using section L i and W j Intersecting with both the theoretical and actual models of the surface to be pasted on the aircraft, the spatial curves of the cross-sections at the intersection points are extracted, yielding the cross-section L. i and W j Arc length of the spatial curve intersecting with the theoretical model of the surface to be pasted and and cross section L i and W j The arc length of the curve intersecting the actual model of the surface to be pasted and Calculate the surface error 'a' of the aircraft to be pasted. j and b i Obtain the path through all center points P ji The change in arc length of the actual cross-section model compared to the theoretical model; Step 2.2, analyze the dimensional error of the thermal protection component (1). Define section L i and W j The tangents of the curves intersecting the surface to be pasted are x and y, respectively, and the normal direction is z. A coordinate system is established. Based on the theoretical model of the point cloud dataset of the thermal protection component (1), the actual deviation values ​​of each side are extracted by comparing with the theoretical boundary 4 of the thermal protection component (1), which is the size error Δl of the thermal protection component (1). ji and Δh ji , Δl ji The cumulative error in the x-direction, Δh ji This represents the cumulative error in the y-direction; Step 3, Dynamic optimization of assembly position; The dynamic optimization of assembly gap mainly considers the heat insulation tiles. An initial gap d is set between the heat insulation tiles. The elimination of the influence of manufacturing and assembly errors of the parts on the machine body surface is achieved by dynamically adjusting the gap value between the heat insulation tiles. The dynamic adjustment of the position is divided into components in the x and y directions. Based on the boundary (3) of the body structure, the heat insulation tiles connected to the boundary (3) of the body structure are aligned with the boundary (3) and remain stationary, while the remaining heat insulation tiles are adjusted using a uniform distribution method; the interlayer position adjustment amounts of the heat insulation tiles are a j / (n-1) and b i / (m-1); Therefore, the adjustment amount for the position of each heat insulation tile is: (i=1,2,…,n),(j=1,2,…,m) (5) (j=1,2,…,m),(i=1,2,…,n) (6) Next, calculate the gap value between the four sides of the insulation tile and the corresponding sides of each adjacent insulation tile. x and gap y Determine the two components of gap. x and gap y Whether the set conditions are met or not, if the conditions are met, it is considered to meet the requirements. The adjustment value of the heat insulation tile in the j-th row and i-th column is determined as ( , If the requirements are not met, such as if the gap component in the x-direction is greater than 0.5mm, then the excess value is defined as e, and the adjustment amounts for the corresponding sides of adjacent insulation tiles are -e / 2 and e / 2, respectively. , After recalculating the boundary error of the insulation tiles, a new judgment is made. If it still does not meet the requirements, the insulation tiles of the upper and lower layers are adjusted until they meet the requirements; the same applies to the y-direction. Finally, the position adjustment amount of each heat insulation tile was obtained and converted into the machine coordinate system, resulting in the coordinates of the center point of the heat insulation tile after adjustment as P. ji (x, y); Step 4, Digital Guidance and Positioning; Based on the position coordinates P of each heat insulation tile ji (x, y), and the fitted actual boundary of the heat insulation tile, the installation position of each heat insulation tile is projected onto the surface to be pasted using laser projection; after the heat insulation tile is installed in the corresponding position, its position is precisely corrected using digital measurement technology.

2. The method for rapid digital guidance and positioning of a thermal protection component according to claim 1, characterized in that, In step 1, the point cloud acquisition principles are as follows: (a) For areas with small surface curvature changes and large flat areas, uniform low-density sampling is used; (b) For surfaces with large curvature variations, chord deviation sampling is used; (c) For the body structure boundary (3), high-density sampling of the boundary is adopted, and the point cloud spacing should not exceed 0.2 mm.

3. The method for rapid digital guidance and positioning of a thermal protection component according to claim 1, characterized in that, In step 2.1, the error of the surface to be pasted on the aircraft is the change in the arc length of the curve between the actual model and the theoretical model. a j = (1) b i = (2)。 4. The method for rapid digital guidance and positioning of a thermal protection component according to claim 1, characterized in that, In step 2.2, Δl ji and Δh ji The calculation process is as follows: Align the center point of the theoretical model of a certain thermal protection component (1) with the center point of the actual model, take the outer envelope curve of each side contour surface as the fitting boundary (5) of the thermal protection component (1), and calculate the dimensional error of the thermal protection component (1): Δl ji =x1+x2 (3) Δh ji =y1+y2 (4) In the formula, x1 and x2 are the errors of the two side boundaries in the x direction, and y1 and y2 are the errors of the two side boundaries in the y direction; wherein, when the fitting boundary (5) of the thermal protection component (1) is greater than the theoretical boundary (4) of the thermal protection component, x 1、 x 2、 y1 and y2 are positive, and vice versa.

5. The method for rapid digital guidance and positioning of a thermal protection component according to claim 1, characterized in that, In step 3, d is 1mm ± 0.5mm.

6. The method for rapid digital guidance and positioning of a thermal protection component according to claim 1, characterized in that, In step 3, the gap value between the four sides of the heat insulation tile and the corresponding sides of each adjacent heat insulation tile is... x and gap y The calculation process is as follows: Adjust the length and height of the insulation tile, and take Δl for each side. ji / 2 and Δh ji / 2, calculate the gap values ​​between the four sides of the heat insulation tile and the corresponding sides of each adjacent heat insulation tile according to equations (7) and (8): gap x =gap x = (7) gap y = (8)。 7. The method for rapid digital guidance and positioning of a thermal protection component according to claim 1, characterized in that, In step 3, gap x and gap y The setting condition is ≤0.5mm.

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