Method for internal and external heating test of solid rocket engine and vehicle

Abstract

The application relates to a method for simulating the internal and external heating of a solid engine, which comprises the following steps: using a quartz lamp to heat the inner and outer sides of an engine shell test piece to simulate the internal heat source condition Qn and the external heat source condition Qw of the engine shell; measuring the temperature of the engine shell test piece under the heating of the quartz lamp to form a simulated temperature history curve T, and providing a temperature boundary condition for the design of the engine shell according to the simulated temperature history curve T. The quartz lamp is used to simulate the heating history of the internal and external engine shells, and finally the temperature history of the shell under the combined action of the aerodynamic heating and the internal heating of the engine in the flight process is obtained, the temperature boundary condition is provided for the design of the engine shell, the design quality is improved, the heating weight is reduced, the overall performance of the aircraft is improved, and the range is expanded.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic thermal protection technology for aircraft, and in particular to a method for testing internal and external heating of a solid rocket motor and an aircraft thereof. Background Technology

[0002] The aircraft engine is not separated and flies at hypersonic speeds in the atmosphere for a long time. The solid rocket motor casing is subjected to the combined effects of internal combustion gas heating and external aerodynamic heat. The heat protection design is too conservative and cannot meet the requirements of the mission. Taking risks will bring great risks to the flight test. It is necessary to understand the working environment of the engine casing.

[0003] In related technologies, solid rocket motor casings use non-metallic shells, resulting in poor accuracy in predicting the inner wall temperature of combustion models. Theoretically, it's difficult to provide boundary conditions for internal heat sources, and the inner wall temperature cannot be directly measured during engine operation. Only the outer wall temperature measured after engine operation is used as a reference. In preliminary heat protection design, the outer wall temperature affected by the engine's internal heat is typically used as the initial temperature, and then the aerodynamic heating thermal response is calculated; or the aerodynamic heating response is directly calculated and then superimposed with the shell temperature affected by internal heat. However, using these temperatures as the basis for strength design is overly conservative and cannot meet the requirements of refined design. Summary of the Invention

[0004] This invention provides a method for testing the internal and external heating of a solid rocket motor and an aircraft, in order to solve the problem that the strength design of the solid rocket motor casing in related technologies is too conservative and cannot meet the requirements of refined design.

[0005] Firstly, a method for testing the internal and external heating of a solid rocket motor is provided, comprising the following steps: using a quartz lamp 2 to heat the inner and outer sides of the engine casing test piece 1, simulating the internal heat source conditions Q of the engine casing. n and external heat source conditions Q w The temperature of the engine housing test piece 1 under the heating of the quartz lamp 2 is measured to form a simulated temperature history curve T, and the simulated temperature history curve T is used to provide temperature boundary conditions for the design of the engine housing.

[0006] In some embodiments, before heating the inner and outer sides of the engine housing test piece 1 with the quartz lamp 2, the method further includes: calculating the internal heat source condition Q. n It includes the following steps: measuring the measured temperature history curve T of the engine casing through ground testing of the engine. n0 According to the measured temperature history curve T n0 By inversely deriving the internal heat source condition Q n .

[0007] In some embodiments, the step of basing the measured temperature history curve T n0 By inversely deriving the internal heat source condition Q n Includes: assuming a derivation of the internal heat source condition Q n The derived temperature history curve T0' of the engine casing was calculated using the heat conduction formula; T0' was compared with T n0 And correct the internal heat source condition Q. n ', until T0' and T n0 The difference between each moment does not exceed 5%, at which point the internal heat source condition Q is... n That is, the internal heat source condition Q. n .

[0008] In some embodiments, after obtaining the internal heat source condition Q n Following this, it also includes: verifying the internal heat source condition Q. n If it is reasonable, then the quartz lamp 2 shall be used for heating.

[0009] In some embodiments, the verification of the internal heat source condition Q n Whether it is reasonable includes: using the quartz lamp 2 to heat the inside of the engine housing test piece 1 to simulate the internal heat source condition Q. n ; Measure the temperature history curve T on the outer side of the engine housing test piece 1. w1 ; Comparison T w1 and T n0 If T w1 With T n0 If the difference between each moment does not exceed 5%, then the internal heat source condition Q is... n Reasonable.

[0010] In some embodiments, before heating the inner and outer sides of the engine housing test piece 1 with the quartz lamp 2, the method further includes: calculating the external heat source condition Q using the aerodynamic heat formula. w According to the external heat source condition Q w .

[0011] In some embodiments, after obtaining the external heat source condition Q w Following this, it also includes: verifying the external heat source condition Q. w Is this reasonable? If so, then use quartz lamp 2 for heating.

[0012] In some embodiments, the verification of the external heat source condition Q w Whether it is reasonable includes: based on the external heat source condition Q w The measured temperature history curve T of the engine casing was calculated using the heat conduction formula. w0A quartz lamp 2 is used to heat the outside of the engine housing test piece 1 to simulate the external heat source condition Q. w ; Measure the temperature history curve T on the outer side of the engine housing test piece 1. w2 ; Comparison T w2 and T w0 If T w2 With T w0 If the difference between each moment does not exceed 5%, then the external heat source condition Q w Reasonable.

[0013] In some embodiments, the testing method further includes: verifying through flight tests whether the actual flight temperature of the engine casing can be simulated.

[0014] Secondly, an aircraft is provided, comprising an engine manufactured using the aforementioned solid rocket motor internal and external heating test method.

[0015] The beneficial effects of the technical solution provided by this invention include:

[0016] This invention provides a solid rocket motor internal and external heating test method and an aircraft. By using a quartz lamp to simulate the heating process of the internal and external engine casing, the temperature history of the casing under the combined action of aerodynamic heating and internal engine heat during flight is finally obtained. This provides temperature boundary conditions for engine casing design, improves design quality, reduces heat-generating weight, enhances the overall performance of the aircraft, and extends its range. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 A schematic diagram of the structure of a test apparatus for a solid rocket motor internal and external heating test method provided in an embodiment of the present invention;

[0019] Figure 2 This is a schematic diagram of the structure of an engine casing test piece for a solid rocket motor internal and external heating test method provided in an embodiment of the present invention.

[0020] Numbering on the map:

[0021] 1. Engine housing test piece; 11. Outer heat shield layer; 12. Carbon fiber housing; 13. Inner heat insulation layer; 14. Front; 15. Front middle; 16. Rear middle; 17. Back; 2. Quartz lamp; 3. Test piece mounting plate. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] This invention provides a method for testing the internal and external heating of a solid rocket motor and an aircraft, which can solve the problem that the strength design of the solid rocket motor casing in related technologies is too conservative and cannot meet the requirements of refined design.

[0024] See Figure 1 As shown, this invention provides a method for testing the internal and external heating of a solid rocket motor, which includes the following steps:

[0025] Step 1: Use quartz lamp 2 to heat the inner and outer sides of the engine housing test piece 1 to simulate the internal heat source conditions Q of the engine housing. n and external heat source conditions Q w Specifically, the engine housing test piece 1 is mounted on the test piece mounting plate 3, which is water-cooled. Quartz lamps 2 are placed on opposite sides of the engine housing test piece 1 and are set parallel to and spaced apart from the test piece mounting plate 3.

[0026] Step two: Measure the temperature of the engine housing test piece 1 under the heating of the quartz lamp 2 to form a simulated temperature history curve T. Based on this simulated temperature history curve T, temperature boundary conditions are provided for the design of the engine housing. Specifically, this is achieved by measuring the temperature history curve T of the outer wall of the engine housing. w and the inner wall temperature history curve T n As a temperature environment condition for engine design, the heating process of the inner and outer engine casing is simulated by heating with quartz lamp 2. Finally, the casing temperature process under the combined action of aerodynamic heating and internal engine heat during flight is obtained, which provides temperature boundary conditions for engine casing design, improves design quality, reduces heat-generating weight, improves the overall performance of the aircraft, and extends the range.

[0027] Furthermore, before heating the inner and outer sides of the engine housing test piece 1 using the quartz lamp 2, the process may further include: calculating the internal heat source condition Q. n It includes the following steps: measuring the measured temperature history curve T of the engine casing through ground testing of the engine. n0 According to the measured temperature history curve T n0By inversely deriving the internal heat source condition Q n In this embodiment, during the engine ground test, the engine casing is only subjected to internal engine heat and not to aerodynamic heating. After the engine ground test, the measured temperature history curve T of the outer wall of the engine casing under the action of internal heat is measured. n0 The internal heat source conditions Q of the engine can be deduced from this. n This allows control over the heating power Q of the quartz lamp 2. kn Simulated internal heat source conditions Q n This provides a basis for controlling the heating power of the quartz lamp 2.

[0028] Furthermore, the step of basing the measured temperature history curve T... n0 By inversely deriving the internal heat source condition Q n This may include: assuming a derivation of an internal heat source condition Q n The derived temperature history curve T0' of the engine casing was calculated using the heat conduction formula; T0' was compared with T n0 And correct the internal heat source condition Q. n ', until T0' and T n0 The difference between each moment does not exceed 5%, at which point the internal heat source condition Q is... n That is, the internal heat source condition Q. n In this embodiment, the heat conduction formula Q = -kAdt / dx is used, based on the assumed internal heat source condition Q. n 'Calculate the actual temperature history curve T0', then compare T0' with the measured temperature history curve T n0 Comparison to correct Q n That is, the actual internal heat source conditions Q can be deduced. n It is easy to calculate and the results are accurate.

[0029] Furthermore, after obtaining the internal heat source condition Q... n Subsequently, it may also include: verifying the internal heat source condition Q. n If it is reasonable, then the quartz lamp 2 is used for heating. In this embodiment, when verifying the derived internal heat source condition Q... n After determining the appropriate conditions, a quartz lamp 2 is used to simulate the internal heat source conditions Q. n Heating the engine housing test piece 1 can further ensure the accuracy of the test and make the test results closer to the actual situation.

[0030] Furthermore, the verification of the internal heat source condition Q n Whether it is reasonable can include: using the quartz lamp 2 to heat the inside of the engine housing test piece 1 to simulate the internal heat source condition Q. n; Measure the temperature history curve T on the outer side of the engine housing test piece 1. w1 ; Comparison T w1 and T n0 If T w1 With T n0 If the difference between each moment does not exceed 5%, then the internal heat source condition Q is... n Reasonably, in this embodiment, a quartz lamp 2 is used to simulate the internal heat source condition Q. n Heating the inside of the engine casing test piece 1 yields the simulated internal heat source condition Q obtained by the quartz lamp 2. n Temperature history curve T w1 By comparing T w1 and T n0 This can verify the use of the measured temperature history curve T during the engine ground test. n0 The derived internal heat source condition Q n Whether it is reasonable can further ensure the accuracy of the experiment and make the test results closer to the actual situation.

[0031] Furthermore, before heating the inner and outer sides of the engine housing test piece 1 using the quartz lamp 2, the process may further include: calculating the external heat source condition Q using the aerodynamic heat formula. w In this embodiment, the aerodynamic heat formula Q = k(hr - hw) is used, where h r To restore enthalpy, h w Given the wall enthalpy, calculate the external heat source condition Q. w This allows control over the heating power Q of the quartz lamp 2. kw Simulated external heat source conditions Q w This provides a basis for controlling the heating power of the quartz lamp 2.

[0032] Furthermore, after obtaining the external heat source condition Q... w Subsequently, it may also include: verifying the external heat source condition Q. w If the conditions are reasonable, then quartz lamp 2 will be used for heating. In this embodiment, when verifying the derived external heat source condition Q... w After determining the appropriate conditions, a quartz lamp 2 is used to simulate the external heat source condition Q. w Heating the engine housing test piece 1 can further ensure the accuracy of the test and make the test results closer to the actual situation.

[0033] Furthermore, the verification of the external heat source condition Q w Whether it is reasonable may include: based on the external heat source condition Q w The measured temperature history curve T of the engine casing was calculated using the heat conduction formula. w0A quartz lamp 2 is used to heat the outside of the engine housing test piece 1 to simulate the external heat source condition Q. w ; Measure the temperature history curve T on the outer side of the engine housing test piece 1. w2 ; Comparison T w2 and T w0 If T w2 With T w0 If the difference between each moment does not exceed 5%, then the external heat source condition Q w Reasonably, in this embodiment, a quartz lamp 2 is used to simulate the external heat source condition Q. w Heating the outside of the engine housing test piece 1 yields the external heat source condition Q simulated by the quartz lamp 2. w Temperature history curve T w2 By comparing T w2 and T w0 This can verify the external heat source condition Q. w Whether it is reasonable can further ensure the accuracy of the experiment and make the test results closer to the actual situation.

[0034] Furthermore, the test method may also include: verifying whether the actual flight temperature of the engine casing can be simulated through flight tests. In this embodiment, after verification through flight tests, it can be shown whether the test method can more accurately simulate the actual flight temperature of the engine casing.

[0035] The engine housing design of this invention is as follows: Figure 2 As shown, its heat protection structure includes an outer heat protection layer 11, a carbon fiber shell 12, and an inner heat insulation layer 13.

[0036] The initial temperature boundary theory analysis indicates a maximum casing temperature of 350℃, while the direct superposition method theoretically predicts a maximum casing temperature of 300℃. The experimental method of this invention verifies that the maximum casing temperature is 250℃. These analyses demonstrate that this experimental method can more accurately simulate the actual flight temperature of the engine casing, and flight tests have verified a maximum casing temperature of 220℃. This method effectively simulates flight conditions with internal and external heating, accurately verifying the actual flight operating temperature of the engine. It provides temperature boundaries for engine design, improves design quality, reduces heat-generating weight, enhances overall aircraft performance, and extends range.

[0037] This invention also provides an aircraft that may include an engine manufactured using the aforementioned solid rocket motor internal and external heating test method.

[0038] The principle of the solid rocket motor internal and external heating test method provided in this embodiment of the invention is as follows:

[0039] Using the outer wall temperature of the solid rocket motor casing as a condition, an initial value for an internal heat source is theoretically derived. Based on the actual measured outer wall temperature of the engine, the boundary conditions for simulating the internal heat source of the engine are obtained through repeated corrections via quartz lamp 2 heating experiments. The external aerodynamic heating conditions are obtained through aerodynamic thermal maturity calculation model. Then, the internal and external heating processes are simulated through quartz lamp heating. Finally, the casing temperature process under the combined action of aerodynamic heating and internal engine heat during flight is obtained, providing temperature boundaries for the design of the engine casing.

[0040] In the description of this invention, it should be noted that the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention 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, and therefore should not be construed as a limitation of the invention. Unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this invention can be understood according to the specific circumstances.

[0041] It should be noted that in this invention, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0042] The above description is merely a specific embodiment of the present invention, enabling those skilled in the art to understand or implement the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features claimed herein.

Claims

1. A method for testing internal and external heating of a solid rocket motor, characterized in that, It includes the following steps: A quartz lamp (2) was used to heat the inner and outer sides of the engine housing test piece (1) to simulate the internal heat source conditions Q of the engine housing. n and external heat source conditions Q w ; The temperature of the engine housing test piece (1) under the heating of the quartz lamp (2) is measured to form a simulated temperature history curve T, and the simulated temperature history curve T is used to provide temperature boundary conditions for the design of the engine housing. Before heating the inner and outer sides of the engine housing test piece (1) with a quartz lamp (2), the method further includes: Calculate the internal heat source condition Q n It includes the following steps: The measured temperature history curve T of the engine casing was obtained through ground testing of the engine. n0 ; According to the measured temperature history curve T n0 By inversely deriving the internal heat source condition Q n ; The measured temperature history curve T n0 By inversely deriving the internal heat source condition Q n include: Assume a derivation of the internal heat source condition Q n The derived temperature history curve T0 of the engine casing is calculated using the heat conduction formula. Compare T0' and T n0 And correct the internal heat source condition Q. n ', until T0' and T n0 The difference between each moment does not exceed 5%, at which point the internal heat source condition Q is... n That is, the internal heat source condition Q. n ; After obtaining the internal heat source condition Q n Following that, it also includes: Verify the internal heat source condition Q n Whether it is reasonable, if so, then the quartz lamp (2) shall be used for heating; The verification of the internal heat source condition Q n Whether it is reasonable includes: The quartz lamp (2) is used to heat the inside of the engine housing test piece (1) to simulate the internal heat source condition Q. n ; The temperature history curve T on the outside of the engine housing test piece (1) was measured. w1 ; Comparison T w1 and T n0 If T w1 With T n0 If the difference between each moment does not exceed 5%, then the internal heat source condition Q is... n Reasonable; Before heating the inner and outer sides of the engine housing test piece (1) with a quartz lamp (2), the method further includes: The external heat source condition Q is calculated using the aerodynamic heat formula. w ; After obtaining the external heat source condition Q w Following that, it also includes: Verify the external heat source condition Q w Is it reasonable? If so, then use a quartz lamp (2) for heating; The verification of the external heat source condition Q w Whether it is reasonable includes: According to the external heat source condition Q w The measured temperature history curve T of the engine casing was calculated using the heat conduction formula. w0 ; A quartz lamp (2) is used to heat the outside of the engine housing test piece (1) to simulate the external heat source condition Q. w ; The temperature history curve T on the outside of the engine housing test piece (1) was measured. w2 ; Comparison T w2 and T w0 If T w2 With T w0 If the difference between each moment does not exceed 5%, then the external heat source condition Q w Reasonable.

2. The solid rocket motor internal and external heating test method as described in claim 1, characterized in that, The test method also includes: Flight tests were conducted to verify whether the actual flight temperature of the engine casing could be simulated.

3. An aircraft, characterized in that, It includes engines manufactured using the solid rocket motor internal and external heating test method as described in claim 1 or 2.

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