A spaceplane cabin test support tooling and its design method

Abstract

The present application provides a method for designing support tooling for a space plane cabin test, which includes: determining the outer contour curve of the support tooling barrel section; establishing a parametric CAD model of the support tooling, and determining the design variables of the support tooling; establishing a finite element simulation model of the support tooling, and performing force transmission simulation analysis together with the finite element model of the tested cabin section; giving initial values ​​of heat flux density and cooling medium flow rate based on the established finite element simulation model of the support tooling, and performing numerical heat transfer simulation analysis; determining the maximum stress boundary value, displacement judgment value and maximum positive and negative temperature rise rate judgment value of the support tooling; judging the design parameters of the support tooling based on the simulation results and the boundary values ​​and judgment values. If the requirements are not met, adjust the design parameter size and adjust the heat flux density and cooling medium flow rate, and re-judge until the support tooling meets the requirements, thereby obtaining the design parameters of the support tooling.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace planes, and in particular to a test support tooling for aerospace plane cabin and a design method thereof. Background Art

[0002] The space plane is a hypersonic aircraft that can perform both aviation and space travel. Since it needs to pass through the atmosphere, the fuselage of the space plane needs to withstand very high temperatures.

[0003] In order to verify the high-temperature resistance of the spaceplane fuselage, it is necessary to conduct ultra-high temperature thermal strength tests on the fuselage. In the ultra-high temperature thermal strength test, a heat load is applied to the surface of the tested cabin section, and the heat load has a large heating and cooling rate.

[0004] In existing thermal strength tests, the support fixture connecting one end of the tested module to the clamped support is designed as a reinforced cylinder. The thickness of the reinforced cylinder is typically designed solely for strength, ignoring stiffness matching requirements. Due to the influence of thermal loads, the force transmission path of the tested module under load differs from the actual flight state. Furthermore, the support fixture cannot achieve temperature matching with the tested module, resulting in additional thermal stresses in the tested module and the support fixture during heating that are inconsistent with actual flight conditions. This combination of factors leads to a certain deviation between the stress state of the tested module during testing and that during actual flight. Summary of the Invention

[0005] The purpose of this application is to provide a method for designing aerospace plane cabin test support tooling to solve or alleviate at least one problem in the background technology.

[0006] The technical solution of this application is: a method for designing aerospace plane cabin test support tooling, comprising:

[0007] Step 1: Determine the outer contour curve of the support tool barrel section;

[0008] Step 2: construct a parametric model of the support fixture and determine the design parameters of the support fixture, including the thickness of the docking plate connecting the support fixture and the tested compartment, the circumferential thickness of the support fixture barrel section, the diameter of the cooling pipes provided in the wall surface of the support fixture barrel section, and the spacing between the cooling pipes;

[0009] Step 3: Establish a finite element model of the support fixture based on the parameterized model of the support fixture, and couple it with the finite element model of the measured compartment to form a combined finite element model. Apply a force load to the heading front end of the measured compartment, and perform finite element simulation analysis on the combined finite element model.

[0010] Step 4: Add a heating unit finite element model to the combined finite element model, so that the heating unit applies a uniform heat flux density to the support tooling finite element model, use a radiation heat transfer mode to simulate the active heating process and influence of the heating unit on the support tooling, and apply forced convection heat transfer boundary conditions to the pipe wall of the cooling pipeline to simulate the influence of the cooling medium on the active cooling process of the support tooling by convection heat transfer, thereby completing the numerical heat transfer simulation analysis of the combined structure of the support tooling and the heating unit;

[0011] Step 5: Determine the maximum stress boundary value that the support tooling can withstand, the displacement judgment value of the interface between the support tooling and the tested compartment, and the judgment values ​​of the maximum positive temperature rise rate and the maximum negative temperature rise rate of the support tooling;

[0012] Determine whether the support tooling can meet the boundary value and the judgment value. If the support tooling cannot meet the boundary value and the judgment value, adjust the support tooling docking plate thickness, the support tooling barrel section circumferential wall thickness, the wall cooling pipe diameter and the cooling pipe spacing in the support tooling design parameters, update the parametric model of the support tooling according to the process in step 2, and increase the heat flux density of the heating unit and the cooling medium flow rate, repeat steps 3 and 4 and judge again until the support tooling meets the boundary value and the judgment value, thereby obtaining the final value of the design parameters of the support tooling.

[0013] Furthermore, the cross-sectional outer contour curve of the supporting tool barrel section is taken from the outer contour curve of the rear end face of the measured cabin section.

[0014] Furthermore, the support tool barrel segment is divided into multiple segments along the circumferential direction, and the thickness of the support tool barrel segment along the circumferential direction in step 2 includes the wall thickness of multiple segments of the support tool barrel segment along the circumferential direction.

[0015] Furthermore, the positions of the multiple sections into which the support tool barrel section is divided along the circumferential direction are determined according to the spacing and positions of the grid ribs inside the measured compartment section.

[0016] Furthermore, the maximum stress boundary value that the supporting tooling can withstand is determined according to the material selected for the supporting tooling.

[0017] Furthermore, the wall thickness displacement of the front end face of the supporting tooling along the circumferential direction is in proportional correspondence with the wall thickness displacement of the rear end face of the measured compartment along the circumferential direction, and the displacement judgment value of the docking surface between the supporting tooling and the measured compartment is determined based on the wall thickness displacement of the rear end face of the measured compartment along the circumferential direction.

[0018] Furthermore, the judgment values ​​of the maximum positive temperature rise rate and the maximum negative temperature rise rate of the supporting tooling are not less than the maximum positive temperature rise rate and the maximum negative temperature rise rate in the temperature curve of the rear end face of the measured compartment.

[0019] In addition, the present application also provides an aerospace plane cabin section test support tooling, the support tooling comprising a support tooling barrel section and a support tooling docking plate, one end of the support tooling barrel section is fixed to the support platform, and the other end of the support tooling barrel section is fixedly connected to the support tooling docking plate, the support tooling barrel section and the support tooling docking plate have the same contour curve, a plurality of connection holes are provided on the support tooling docking plate, the tested cabin section is fixedly connected to the connection holes via a connector, and a plurality of parallel cooling pipes are provided in the wall surface of the support tooling barrel section;

[0020] The design parameters of the support tooling include the thickness of the support tooling docking plate, the circumferential thickness of the support tooling barrel section, the diameter of the cooling pipe, and the spacing between adjacent cooling pipes;

[0021] The design parameters of the support tooling are determined by any of the design methods described above.

[0022] Furthermore, the supporting tooling barrel section and the supporting tooling docking plate have flush outer end surfaces, and the inner end surface of the supporting tooling docking plate protrudes toward the center from the inner end surface of the supporting tooling barrel section.

[0023] The design method of this application realizes the dual simulation design of the stiffness boundary and thermal boundary of the support tooling in the ultra-high temperature strength test, so that the force transmission path and the thermal stress state generated in the test compartment during the test loading and heating process are as consistent as possible with the actual flight state. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0025] Figure 1 The following is a flow chart of the supporting tooling design method for this application.

[0026] Figure 2 Schematic diagram of a typical aerospace plane in this application.

[0027] Figure 3 This is a schematic diagram of the supporting tooling structure for this application.

[0028] Figure 4 This is a vertical section view of the supporting tooling for this application.

[0029] Figure 5 This is a cross-sectional view of the supporting tooling for this application.

[0030] Figure 6 This is the temperature curve of the rear end surface of the measured compartment in one embodiment of the present application. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0032] In order to overcome the problems raised in the prior art, the present application provides an aerospace plane cabin test support tooling and a design method thereof to meet the requirement that the tested cabin must be consistent with the actual flight process state during the ultra-high temperature test.

[0033] like Figure 1 As shown, the support work design method provided by this application mainly includes the following steps:

[0034] Step 1: Determine the outer contour curve of the support tooling barrel segment.

[0035] like Figure 2 In the typical aerospace plane 10 shown, the central fuselage section 11 of the aerospace plane 10 is the module being tested. The rear side of the module being tested (near the tail of the aerospace plane along the flight path) is the support module 12. Support module 12 is connected to the module being tested and used to support it. The support fixture is used to replace support module 12 to support the module being tested. Therefore, the outer contour curve of the rear end face of the module being tested is used as the cross-sectional outer contour curve of the support fixture barrel section.

[0036] like Figure 3 Shown is a schematic diagram of the support tooling 20 in one embodiment of the present application. The outer contour curve of the support tooling 20 is an excellent semicircle (i.e., larger than a semicircle). It can be understood that the outer contour curve of the support tooling 20 is not limited to an excellent semicircle, and it can also be a circle, an ellipse, or the like, which depends on the rear end face contour of the compartment being measured.

[0037] Step 2: Create a parametric CAD model of the support tooling 20 and determine the design parameters of the support tooling 20. The design parameters include the thickness A of the docking plate 23 connecting the support tooling 20 and the measured compartment, the circumferential thickness B of the support tooling barrel section 21, the diameter C of the cooling pipe set in the wall of the support tooling barrel section 21, and the spacing D of the cooling pipes. The parametric model is adjusted through programming tools to automatically generate a new CAD model.

[0038] like Figure 3As shown, the support fixture 20 includes a support fixture barrel section 21 and a support fixture docking plate 23. One end of the support fixture barrel section 21 is fixed to the support platform 22, and the other end of the support fixture barrel section 21 is fixedly connected to the support fixture docking plate 23 by welding. The support fixture barrel section 21 and the support fixture docking plate 23 have the same contour curve, and the support fixture barrel section 21 and the support fixture docking plate 23 have flush outer end surfaces, and the inner end surface of the support fixture docking plate 23 protrudes centrally from the inner end surface of the support fixture barrel section 21. A plurality of connection holes 24 are provided in the support fixture docking plate 23, and the tested cabin section is fixed to these connection holes 24 via connectors.

[0039] like Figure 4 As shown in the cross-sectional view of the support tooling in the height direction, a plurality of parallel cooling pipes are arranged in the wall of the support tooling barrel section 21 , and a cooling medium (for example, the cooling medium can be water) can flow through the cooling pipes to cool the support tooling 20 .

[0040] In this application, according to the spacing and position of the grid ribs inside the tested compartment, the support tool barrel section 21 is divided into multiple sections along the circumferential direction, and the thickness B of the design parameter includes the wall thickness of the multiple sections. Figure 5 In the top view embodiment of the supporting tooling shown, the supporting tooling barrel section 21 is divided into 9 sections B1 to B9 along the circumferential direction, and the thickness B of the supporting tooling barrel section 21 along the circumferential direction includes B1-B9.

[0041] Step 3: Finite element force transmission simulation analysis of loads:

[0042] For the support fixture CAD model obtained in step 2, a finite element simulation model of the support fixture 20 is established, and the finite element model of the tested cabin section is added. The docking surface of the tested cabin section and the support fixture docking plate is connected by bolts. A fixed support constraint is added to the lower end face of the support fixture 20 and the test platform. A force load is applied to the front end of the tested cabin section, and a finite element simulation analysis is performed.

[0043] Step 4: Finite element heat transfer simulation analysis of thermal load:

[0044] The given finite element model of the heating unit is added to the finite element simulation model obtained in step 3, and a uniform heat flux density E is applied to the heating unit (the type and power of the heating unit are determined by the heat flux density E). The radiation heat transfer mode is used to simulate the active heating process and influence of the heating unit on the support tooling. Forced convection heat transfer boundary conditions are applied to the pipe walls of the cooling pipes in the support tooling. The corresponding convection heat transfer coefficient on the pipe walls of the cooling pipes is determined by the cooling medium flow rate F in the pipes, which is used to simulate the influence of the cooling medium on the active cooling process of the support tooling 20 during convection heat transfer. Numerical heat transfer simulation analysis is performed on the combined structure of the support tooling and the heating unit.

[0045] Step 5: Support tooling optimization and iteration:

[0046] Determine the maximum stress boundary value that the support tooling 20 can withstand. The maximum stress boundary value is determined by the material selected for the support tooling 20. Generally, the maximum stress boundary value is 1 / 3 of the maximum tensile strength of the material selected for the support tooling 20.

[0047] Determine the displacement determination value for the interface between the support fixture 20 and the tested compartment. The determination process requires that the maximum stress generated by the support fixture 20 under a given load is less than the boundary value, and that the displacement Wb of the front face of the support fixture 20 at each circumferential wall thickness position is proportional to the displacement Wt of the rear face of the tested compartment at each circumferential wall thickness position (the displacement of the tested compartment is known data), i.e., Wb = K * Wt. Considering the limited number of circumferential segments during finite element analysis, the coefficient K at each corresponding point on the wall thickness of the support fixture and the tested compartment cannot be completely consistent. Therefore, the coefficient K should be set within a reasonable range: |Km-Kn| / Kmax≤0.2 (Km and Kn are the coefficients K of any point, and Kmax is the maximum coefficient K among all wall thickness points). Meeting this range satisfies the determination requirement.

[0048] Determine the maximum positive temperature rise rate and the maximum negative temperature rise rate judgment value of the support tooling 20. For example, in this embodiment, the temperature rise rate judgment value is consistent with the maximum positive temperature rise rate and the maximum negative temperature rise rate in the temperature curve of the rear end face of the measured compartment. The judgment process is that the absolute values ​​of the maximum positive temperature rise rate and the maximum negative temperature rise rate on the inner and outer surfaces of the support tooling 20 are both greater than the absolute values ​​of the corresponding temperature rise rate judgment values;

[0049] If the support tooling 20 cannot meet the above boundary values ​​and judgment values, adjust the support tooling docking plate thickness A, the support tooling barrel section circumferential wall thickness B, the wall cooling pipe diameter C and the cooling pipe spacing D in the design parameters, update the CAD model of the support tooling according to the process in step 2, and increase the heat flux density E of the heating unit and the cooling medium flow F. Repeat steps 3 and 4 and judge again until the support tooling meets the boundary values ​​and all judgment values, and obtain the final value of the design parameters of the support tooling.

[0050] like Figure 5The figure shows the temperature curve of the rear end face of the measured compartment in an embodiment of the present application, wherein the maximum positive temperature rise rate is 8°C / s and the maximum negative temperature rise rate is -6°C / s. By adjusting the thickness A of the supporting tooling docking plate, the circumferential wall thickness B of the supporting tooling barrel section, the diameter C of the wall cooling pipe and the cooling pipe spacing D, the supporting tooling CAD model is updated according to the process of step 2, and the heat flux density E of the heating unit and the cooling medium flow rate F are increased. Steps 3 and 4 are repeated, and the iterations are repeated. Finally, the thickness A of the supporting tooling docking plate is obtained as 17 mm, the circumferential wall thickness B1, B5 of the supporting tooling barrel section is obtained as 11 mm, B2, B4 is obtained as 12.5 mm, B as 14.5 mm, B6, B9 as 13.2 mm, B7, B8 as 14.1 mm, C as 8 mm, D as 50 mm, the heat flux density E of the heating unit is obtained as 520 kW / m2, and the cooling medium flow rate F as 20 L / min. The supporting tooling can meet the dual simulation of the test stiffness boundary and the thermal boundary.

[0051] The design method of this application realizes the dual simulation design of the stiffness boundary and thermal boundary of the support tooling in the ultra-high temperature strength test, so that the force transmission path and the thermal stress state generated in the test compartment during the test loading and heating process are as consistent as possible with the actual flight state.

[0052] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A method for designing aerospace plane cabin test support tooling, characterized in that: include: Step 1: Determine the outer contour curve of the support tool barrel section; Step 2: construct a parametric model of the support fixture and determine the design parameters of the support fixture, including the thickness of the docking plate connecting the support fixture and the tested compartment, the circumferential thickness of the support fixture barrel section, the diameter of the cooling pipes provided in the wall surface of the support fixture barrel section, and the spacing between the cooling pipes; Step 3: Establish a finite element model of the support fixture based on the parameterized model of the support fixture, and couple it with the finite element model of the measured compartment to form a combined finite element model. Apply a force load to the heading front end of the measured compartment, and perform finite element simulation analysis on the combined finite element model. Step 4: Add a heating unit finite element model to the combined finite element model, so that the heating unit applies a uniform heat flux density to the support tooling finite element model, use a radiation heat transfer mode to simulate the active heating process and influence of the heating unit on the support tooling, and apply forced convection heat transfer boundary conditions to the pipe wall of the cooling pipeline to simulate the influence of the cooling medium on the active cooling process of the support tooling by convection heat transfer, thereby completing the numerical heat transfer simulation analysis of the combined structure of the support tooling and the heating unit; Step 5: Determine the maximum stress boundary value that the support tooling can withstand, the displacement judgment value of the interface between the support tooling and the tested compartment, and the judgment values ​​of the maximum positive temperature rise rate and the maximum negative temperature rise rate of the support tooling; Determine whether the support tooling can meet the boundary value and the judgment value. If the support tooling cannot meet the boundary value and the judgment value, adjust the support tooling docking plate thickness, the support tooling barrel section circumferential wall thickness, the wall cooling pipe diameter and the cooling pipe spacing in the support tooling design parameters, update the parametric model of the support tooling according to the process in step 2, and increase the heat flux density of the heating unit and the cooling medium flow rate, repeat steps 3 and 4 and judge again until the support tooling meets the boundary value and the judgment value, thereby obtaining the final value of the design parameters of the support tooling.

2. The spaceplane cabin test support tooling design method according to claim 1, characterized in that: The cross-sectional outer contour curve of the support tool barrel section is taken from the outer contour curve of the rear end face of the measured cabin section.

3. The spaceplane cabin test support tooling design method according to claim 1, characterized in that: The supporting tool barrel segment is divided into multiple segments along the circumferential direction, and the thickness of the supporting tool barrel segment along the circumferential direction in step 2 includes the wall thickness of the supporting tool barrel segment along the circumferential direction.

4. The spaceplane cabin test support tooling design method according to claim 3, characterized in that: The positions of the multiple sections into which the support tool barrel section is divided along the circumferential direction are determined according to the spacing and positions of the grid ribs inside the measured compartment section.

5. The spaceplane cabin test support tooling design method according to claim 1, characterized in that: The maximum stress boundary value that the supporting tool can withstand is determined according to the material selected for the supporting tool.

6. The spaceplane cabin test support tooling design method according to claim 1, characterized in that: The wall thickness displacement of the front end face of the supporting tooling along the circumferential direction is in proportional correspondence with the wall thickness displacement of the rear end face of the measured compartment section along the circumferential direction, and the displacement judgment value of the docking surface between the supporting tooling and the measured compartment section is determined based on the wall thickness displacement of the rear end face of the measured compartment section along the circumferential direction.

7. The spaceplane cabin test support tooling design method according to claim 1, characterized in that: The judgment values ​​of the maximum positive temperature rise rate and the maximum negative temperature rise rate of the supporting tooling are not less than the maximum positive temperature rise rate and the maximum negative temperature rise rate in the temperature curve of the rear end face of the measured compartment section.

8. A spaceplane cabin test support tooling obtained by using the spaceplane cabin test support tooling design method according to any one of claims 1 to 7, characterized in that: The support tooling (20) comprises a support tooling barrel section (21) and a support tooling docking plate (23); one end of the support tooling barrel section (21) is fixed on the support platform (22); the other end of the support tooling barrel section (21) is fixedly connected to the support tooling docking plate (23); the support tooling barrel section (21) and the support tooling docking plate (23) have the same contour curve; a plurality of connection holes (24) are provided on the support tooling docking plate (23); the measured cabin section is fixedly connected to the connection holes (24) via a connector; a plurality of cooling pipes parallel to each other are provided in the wall surface of the support tooling barrel section (21); The design parameters of the supporting tool (20) include the thickness of the supporting tool butt joint plate (A), the circumferential thickness of the supporting tool barrel section (B), the diameter of the cooling pipeline (C), and the spacing between adjacent cooling pipelines (D); The design parameters of the support tool (20) are determined by the design method according to any one of claims 1 to 7.

9. The space plane cabin test support tooling according to claim 8, characterized in that: The supporting tool barrel section (21) and the supporting tool docking plate (23) have flush outer end surfaces, and the inner end surface of the supporting tool docking plate (23) protrudes toward the center from the inner end surface of the supporting tool barrel section (21).

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