Support model and model construction method of rocket engine strong dynamic load test device

Abstract

The present invention discloses a support model of a rocket engine strong dynamic load test device and a model construction method. The weak positions of the rocket engine strong dynamic load test model are discovered through calculation and assessment; a support structure is arranged at the weak position, and the support points of the support structure are arranged according to the stress characteristics and structural strength distribution characteristics of the combustion chamber and nozzle of the rocket engine under a strong dynamic load environment; the structural performance of the support structure formed by the selected support points is evaluated, the deformation resistance of the entire support structure, the structural natural vibration frequency of the support structure and the rocket engine, and the internal force of the structural rods are calculated, and the contribution of the support structure to the structural stiffness and the ultimate bearing capacity are determined; the present invention comprehensively considers multiple factors such as the support point position, the space skeleton form, and the multi-point connection method, breaks through the limitations of traditional single-dimensional design, improves the comprehensive performance and survivability under extreme strong dynamic loads, and provides a stable and reliable platform for test measurement.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engines, and in particular to a support model of a rocket engine strong dynamic load test device and a model construction method. Background Art

[0002] The performance verification of the rocket engine combustion chamber and nozzle is crucial. The strong dynamic load test is one of the key links in the technology research and development process. The strong dynamic load environment is extremely complex and has a strong energy impact. There are usually strong energy release processes such as detonation, explosion, high-speed impact, and rapid flight, which instantly produce extremely high pressure, temperature or speed changes.

[0003] Under strong dynamic load environment, the instantaneous burst of energy will be converted into huge force exerted on the rocket engine combustion chamber, nozzle and surrounding objects. The magnitude and direction of this force are highly uncertain and complex. It may come from impacts in multiple directions, which is enough to cause plastic deformation or even fracture of the structural materials of the rocket engine combustion chamber, nozzle and surrounding objects, far exceeding the design bearing limit under conventional static loads. In order to reduce damage to the structural materials of the rocket engine combustion chamber, nozzle and surrounding objects, the existing treatment method for insufficient stiffness of the tail support structure is centralized support methods such as tail support and belly support.

[0004] However, the tail and belly of the above-mentioned strong dynamic load test model for rocket engines adopt a centralized support method, resulting in the load being mainly concentrated on a few support points, causing these support points to bear great pressure and stress. In the strong dynamic load test model of the rocket engine combustion chamber and nozzle, the structure near the support point of the test model is prone to local damage under the impact of strong dynamic loads, and the load cannot be effectively evenly distributed to the entire structure. Summary of the invention

[0005] The purpose of the present invention is to provide a support model for a rocket engine strong dynamic load test device and a model construction method, so as to solve the technical problem in the prior art that due to the local stress concentration at the concentrated support point, the structure near the support point is prone to local damage and the load cannot be effectively and evenly distributed to the entire structure.

[0006] In order to solve the above technical problems, the present invention specifically provides the following technical solutions:

[0007] A rocket engine strong dynamic load test device support model, the strong dynamic load test model includes a driving section and a combustion chamber connected to the driving section through a connecting section, the combustion chamber is connected to a nozzle through a throat, and includes:

[0008] A supporting platform is provided at the lower end of the strong dynamic load test model, and a three-dimensional skeleton with a three-dimensional structure is provided between the combustion chamber, the throat and the nozzle and the supporting platform, wherein a plurality of connection points are provided between the three-dimensional skeleton and the combustion chamber, the throat and the nozzle respectively.

[0009] As a preferred solution of the present invention, the three-dimensional skeleton includes a plurality of rods, and all the rods are connected by hinges, so that the three-dimensional skeleton forms a stable frame structure.

[0010] As a preferred solution of the present invention, a plurality of connection points are respectively arranged at the connection position between the combustion chamber and the throat, the connection position between the nozzle and the throat, and the ends of the combustion chamber and the nozzle, and the rods of the three-dimensional skeleton are installed inside the strong dynamic load test model through the plurality of connection points, and the rods of the three-dimensional skeleton connected by the connection points form a torque path;

[0011] The aerodynamic load and impact load generated by the driving section can be evenly dispersed to the surfaces of the combustion chamber and the nozzle along the different torque paths.

[0012] As a preferred solution of the present invention, the rods of the three-dimensional skeleton are movably connected to the corresponding connection points, so that the three-dimensional skeleton can be displaced under the action of the aerodynamic load and the impact load.

[0013] In addition, the present invention also provides a method for simulating and setting support parameters in a support model of a rocket engine strong dynamic load test device, comprising the following steps:

[0014] Step 100, determining the weak position: determining the weak position of the strong dynamic load test model by calculating the operating parameters of the rocket engine;

[0015] Step 200, numerical simulation: arranging the support structure at the weak position, and arranging the support points of the support structure according to the stress characteristics and structural strength distribution characteristics of the combustion chamber and nozzle of the rocket engine under the strong dynamic load environment;

[0016] Step 300, test evaluation and verification: evaluate the structural performance of the support structure formed by the selected support points, calculate the deformation resistance of the entire support structure, the structural natural vibration frequency of the support structure and the rocket engine, and the internal forces of the structural members, and determine the contribution of the support structure to the structural stiffness and the ultimate bearing capacity.

[0017] As a preferred solution of the present invention, in step 100, the weak position of the rocket engine strong dynamic load test model is determined by:

[0018] The weak parts of the strong dynamic load test model are confirmed by calculating the operating parameters of the engine. Specifically, the locations where deformation, vibration and explosion occur in the strong dynamic load test model during the test are defined as the weak parts of the strong dynamic load test model.

[0019] As a preferred solution of the present invention, in step 200, the test method for arranging the support points of the support structure is:

[0020] Finite element analysis was used to perform numerical simulation and to conduct detailed analysis of the stress distribution and deformation of the strong dynamic load test model under different support point layout schemes;

[0021] According to the analysis results, determine the number, position, spacing parameters of the support points of the support structure, as well as the rod material and rod structure of the support structure;

[0022] A support structure is formed on the outside of the strong dynamic load test model according to the number, position and spacing parameters of the support points.

[0023] As a preferred solution of the present invention, different rod materials of the support structure are selected as test objects, and the stress distribution of the support structure composed of each rod material under different strong dynamic load conditions is analyzed by combining numerical simulation and experimental verification to find out the weak links in the strength of the rocket engine strong dynamic load test model formed by different rod materials;

[0024] The strength differences corresponding to different rod materials are counted respectively to determine the rod material selected for the supporting structure.

[0025] As a preferred solution of the present invention, rod structures with different supporting structures are selected as test objects, and the stress distribution of the supporting structure composed of each rod structure under different strong dynamic load conditions is analyzed by combining numerical simulation and experimental verification. The rod size and rod connection method of the supporting structure are optimized based on the stress analysis results to improve the stiffness of the strong dynamic load test model.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] (2) The spatial skeleton structure provided by the present invention and the multi-point support of the spatial skeleton structure for the strong dynamic load test model can effectively distribute the load under the strong dynamic load environment evenly to the entire model and support system, greatly reducing the risk of local stress concentration, thereby significantly improving the safety and reliability of the structure;

[0028] (3) The present invention comprehensively considers multiple factors such as the support point position, spatial skeleton form, and multi-point connection method, and uses a combination of numerical simulation and experimental verification to comprehensively optimize the strength and stiffness of the model and supporting structure, including material selection, structural design, and balanced stiffness design in all directions. It breaks through the limitations of traditional single-dimensional design, improves the comprehensive performance and survivability under extremely strong dynamic loads, and provides a stable and reliable platform for experimental measurement. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the implementation methods of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the implementation methods or the description of the prior art. Obviously, the drawings in the following description are only exemplary, and for ordinary technicians in this field, other implementation drawings can be derived from the provided drawings without creative work.

[0030] Figure 1 This is a schematic diagram of the single-point support structure of the traditional strong dynamic load test model;

[0031] Figure 2 It is a structural schematic diagram of a multi-point support structure of a strong dynamic load test model according to an embodiment of the present invention. DETAILED DESCRIPTION

[0032] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0033] The present invention provides a support model of a rocket engine strong dynamic load test device, the strong dynamic load test model comprises a driving section and a combustion chamber connected to the driving section through a connecting section, the combustion chamber is connected to a nozzle through a throat, and comprises:

[0034] A supporting platform is provided at the lower end of the strong dynamic load test model, and a three-dimensional skeleton with a three-dimensional structure is provided between the combustion chamber, throat and nozzle and the supporting platform, wherein a plurality of connection points are respectively provided between the three-dimensional skeleton and the combustion chamber, throat and nozzle.

[0035] The three-dimensional skeleton includes a plurality of rods, and all the rods are connected by hinges, so that the three-dimensional skeleton forms a stable frame structure.

[0036] A plurality of connection points are respectively arranged at the connection position between the combustion chamber and the throat, the connection position between the nozzle and the throat, and the ends of the combustion chamber and the nozzle. The rods of the three-dimensional skeleton are installed inside the strong dynamic load test model through the plurality of connection points. The rods of the three-dimensional skeleton connected by the connection points form a torque path. The aerodynamic load and impact load generated by the driving section can be evenly dispersed to the surface of the combustion chamber and the nozzle along different torque paths.

[0037] The supporting structure adopts the form of a space skeleton, which has a complex and orderly three-dimensional structure. The space skeleton is composed of multiple high-strength rods through a reasonable hinged method to form a stable frame system.

[0038] The materials of these rods are alloy materials with high strength, high toughness and good impact resistance, such as titanium alloy or high-strength alloy steel. The shape and layout of the space skeleton are customized according to the appearance of the aircraft and test requirements to ensure that it can provide effective support for the aircraft model at different parts.

[0039] like Figure 1 As shown, the existing solution to the insufficient rigidity of the tail support structure is centralized support methods such as tail support and belly support. However, the tail and belly of the strong dynamic load test model of the rocket engine adopt centralized support methods, which causes the load to be mainly concentrated on a few support points, causing these support points to be subjected to great pressure and stress.

[0040] In this embodiment, the space frame is connected to the base of the strong dynamic load test device through a multi-point connection method, such as Figure 2 As shown, multiple supporting points are reasonably distributed on the surface of the rocket engine combustion chamber and nozzle model. These connection points are evenly distributed at different positions of the base. The installation method of the space frame and the base can be reliably connected by high-strength bolt connection or welding connection to ensure the firmness and stability of the connection. Through this multi-point connection method, the load generated under the strong dynamic load environment can be evenly transferred to the base of the test device, avoiding the load concentration on a few connection points, and improving the bearing capacity and reliability of the entire support system.

[0041] These support points are optimally arranged according to the stress characteristics and structural strength distribution of the rocket engine combustion chamber and nozzle under strong dynamic load conditions. Specifically, in order to achieve the best load sharing effect, the layout of the support points is systematically optimized, and advanced numerical simulation methods such as finite element analysis are used to conduct detailed analysis of the stress distribution and deformation of the model under different support point layout schemes. Based on the analysis results, the number, position, spacing and other parameters of the support points are determined.

[0042] When strong dynamic loads act on the surface of the model, the loads can be evenly distributed to the entire model structure through these multiple support points, rather than concentrated in a certain local area. For example, multiple support points are set at the main stress-bearing parts such as the rocket engine combustion chamber and nozzle connection, inlet, and outlet, so that aerodynamic loads, impact loads, etc. can be dispersed to the internal structure of the model along different force transmission paths, effectively reducing the risk of local stress concentration.

[0043] It is further explained that the model is connected to the space skeleton support at multiple points, abandoning the traditional centralized connection method. The rods of the three-dimensional skeleton are movably connected to their corresponding connection points so that the three-dimensional skeleton can be displaced under the action of aerodynamic loads and impact loads, such as ball joint connections or elastic connection elements, which can adapt to the deformation and displacement of the model under strong dynamic loads to a certain extent, while effectively transmitting the load.

[0044] This multi-point connection method makes the strong dynamic load test model and the supporting structure form an organic whole, improving the collaborative working ability and stability of the entire system. The multi-point connection method between the strong dynamic load test model and the space skeleton has a positive impact on the design and layout of the strong dynamic load test model structure.

[0045] Since the load can be evenly distributed inside the model during the strong dynamic load test, the design of the internal structure can be more flexible and optimized. For example, the position of internal components such as instruments and equipment and fuel tanks can be arranged more reasonably, reducing the space waste and unreasonable layout problems caused by the limitation of the support structure. At the same time, the multi-point connection method is also conducive to improving the overall strength and rigidity of the internal structure of the model and enhancing its anti-destruction ability under strong dynamic load environment.

[0046] In order to determine the number, position, spacing and other parameters of the support points of the support structure on the strong dynamic load test model, as well as the materials used for the support structure, and to achieve system optimization of the entire strong dynamic load test model, this embodiment also discloses a support parameter simulation setting method in the above-mentioned strong dynamic load test model, comprising the following steps:

[0047] Step 100, determine the weak position: determine the weak position of the strong dynamic load test model by calculating the operating parameters of the rocket engine, and then install the support structure at the weak position in a targeted manner, so as to improve the strength and stiffness of the weak position of the strong dynamic load test model.

[0048] The strong dynamic load test is mainly to assess the strength, stiffness, and load-bearing capacity of the engine in the dynamic process. Therefore, the relevant information of the engine can be calculated to obtain preliminary results and confirm the weak parts that may cause deformation, vibration, or even explosion.

[0049] Step 200, numerical simulation: Arrange the support structure at the weak position, and arrange the support points of the support structure according to the stress characteristics and structural strength distribution characteristics of the combustion chamber and nozzle of the rocket engine under the strong dynamic load environment.

[0050] In step 200, the test method for arranging the support points of the support structure is:

[0051] Finite element analysis was used to perform numerical simulation and to conduct detailed analysis of the stress distribution and deformation of the strong dynamic load test model under different support point layout schemes;

[0052] According to the analysis results, determine the number, position and spacing parameters of the supporting points of the supporting structure, as well as the rod material and rod structure of the supporting structure;

[0053] A support structure is formed outside the strong dynamic load test model according to the number, position, spacing parameters of the support points and the rod structure of the support structure.

[0054] Among them, the number, position and spacing are determined according to the degree of freedom requirements. Generally, an over-static structure is adopted, that is, the number of constraints is greater than the number of degrees of freedom; the support strength is further considered, that is, the supporting steel structure should be able to withstand strong dynamic load impact; the structural stiffness is further considered, that is, the vibration frequency requirements must be met, and generally the first-order vibration frequency is guaranteed to be higher than 30Hz.

[0055] The connection method of the rod structure of the supporting structure is hinged connection, and the rod size: the diameter is generally 0.5~5cm, and the aspect ratio is generally greater than 10.

[0056] The specific method for selecting the rod material of the support structure is as follows: different rod materials of the support structure are selected as test objects, and the stress distribution of the support structure composed of each rod material under different strong dynamic load conditions is analyzed by combining numerical simulation and experimental verification to find out the weak links in the strength of the rocket engine strong dynamic load test model formed by different rod materials; the strength difference corresponding to different rod materials is counted respectively to determine the rod material selected for the support structure.

[0057] The specific method for selecting the number, position and spacing of the supporting structures is as follows: rod structures using different supporting structures are selected as test objects, and the stress distribution of the supporting structures composed of each rod structure under different strong dynamic load conditions is analyzed by combining numerical simulation and experimental verification; based on the stress analysis results, the rod size and rod connection method of the supporting structure are optimized to improve the stiffness of the strong dynamic load test model.

[0058] In terms of materials, the inherent strength of the structure is improved through material selection and structural design, and high-strength, low-density advanced materials such as carbon fiber composites are selected to reduce the weight of the structure while improving its load-bearing capacity.

[0059] In structural design, reasonable cross-sectional shapes, reinforcement arrangements and other measures are adopted to enhance the structure's ability to resist bending, shearing and compression.

[0060] By combining numerical simulation with experimental verification, the stress distribution of the supporting structure under different strong dynamic load conditions is analyzed to identify the weak links in strength, and targeted optimization and improvement are carried out to ensure that the entire structure will not be damaged under the impact of strong dynamic loads. For example, the stiffness of the entire system can be improved by optimizing parameters such as the rod size, connection method, and wall thickness of the model structure of the supporting structure.

[0061] Step 300, test evaluation and verification: evaluate the structural performance of the support structure formed by the selected support points, calculate the deformation resistance of the entire support structure, the structural natural vibration frequency of the support structure and the rocket engine, and the internal forces of the structural members, and determine the contribution of the support structure to the structural stiffness and the ultimate bearing capacity.

[0062] The ultimate bearing capacity of the supporting structure for the structural stiffness is determined by performing a static analysis using CAE software, taking the first damaged support point as the limit, and calculating the overall bearing capacity, i.e., the ultimate bearing capacity.

[0063] The contribution of the support structure to the structural stiffness is determined by performing dynamic analysis using CAE software to obtain the free vibration frequency. The higher the frequency, the greater the stiffness contribution.

[0064] The spatial skeleton structure provided in this embodiment, and the multi-point support of the spatial skeleton structure for the strong dynamic load test model can effectively and evenly disperse the load under the strong dynamic load environment to the entire model and support system, greatly reducing the risk of local stress concentration, thereby significantly improving the safety and reliability of the structure, and optimizing the layout of the model surface support points based on the strong dynamic load force characteristics and structural strength distribution. Compared with the traditional uniform or random arrangement method, it can accurately adapt to complex stress conditions, distribute the surface load along multiple force transmission paths, and reduce the risk of local stress concentration. Different from traditional plane or simple frame supports, it can disperse loads in multiple dimensions, enhance overall stability and bearing capacity, effectively transfer loads to the base, and improve anti-overturning and anti-destruction capabilities.

[0065] Taking into account multiple factors such as the support points, spatial skeleton form, and multi-point connection methods, the strength and stiffness of the model and supporting structure are comprehensively optimized using a combination of numerical simulation and experimental verification, including material selection, structural design, and balanced stiffness design in all directions. This breaks through the limitations of traditional single-dimensional design, improves the comprehensive performance and survivability under extremely strong dynamic loads, and provides a stable and reliable platform for experimental measurement.

[0066] And because the strong dynamic load test model and supporting structure have high stability and small deformation under strong dynamic load environment, they provide a reliable platform for test measurement. The measurement sensors inside the strong dynamic load test model can collect test data more accurately, reducing measurement errors caused by factors such as structural deformation and vibration. In actual experiments, the accuracy and reliability of measurement data have been significantly improved, providing strong data support for in-depth research on the performance changes of rocket engine combustion chambers and nozzles under strong dynamic load environments.

[0067] The above embodiments are only exemplary embodiments of the present application and are not intended to limit the present application. The protection scope of the present application is defined by the claims. Those skilled in the art may make various modifications or equivalent substitutions to the present application within the essence and protection scope of the present application, and such modifications or equivalent substitutions shall also be deemed to fall within the protection scope of the present application.

Claims

1. A support model of a rocket engine strong dynamic load test device, the strong dynamic load test model comprising a driving section and a combustion chamber connected to the driving section via a connecting section, the combustion chamber being connected to a nozzle via a throat, characterized in that: include: A support platform is provided at the lower end of the strong dynamic load test model, and a three-dimensional skeleton with a three-dimensional structure is provided between the combustion chamber, the throat and the nozzle and the support platform, wherein a plurality of connection points are provided between the three-dimensional skeleton and the combustion chamber, the throat and the nozzle respectively; The plurality of connection points are respectively arranged at the connection position between the combustion chamber and the throat, the connection position between the nozzle and the throat, and the ends of the combustion chamber and the nozzle. The rods of the three-dimensional skeleton are installed inside the strong dynamic load test model through the plurality of connection points. The rods of the three-dimensional skeleton connected by the connection points form a moment path. The aerodynamic load and impact load generated by the driving section can be evenly distributed to the surfaces of the combustion chamber and the nozzle along different torque paths; The rods of the three-dimensional framework are movably connected to the corresponding connection points, so that the three-dimensional framework can be displaced under the action of the pneumatic load and the impact load.

2. The rocket engine strong dynamic load test device support model according to claim 1 is characterized in that: The three-dimensional skeleton includes a plurality of rods, all of which are connected by hinges, and the three-dimensional skeleton forms a stable frame structure.

3. A model construction method for a rocket engine strong dynamic load test device support model based on any one of claims 1-2, characterized in that: The following steps are involved: Step 100, determining the weak position: determining the weak position of the strong dynamic load test model by calculating the operating parameters of the rocket engine; Step 200, numerical simulation: arranging the support structure at the weak position, and arranging the support points of the support structure according to the stress characteristics and structural strength distribution characteristics of the combustion chamber and nozzle of the rocket engine under the strong dynamic load environment; Step 300, test evaluation and verification: evaluate the structural performance of the support structure formed by the selected support points, calculate the deformation resistance of the entire support structure, the structural natural vibration frequency of the support structure and the rocket engine, and the internal forces of the structural members, and determine the contribution of the support structure to the structural stiffness and the ultimate bearing capacity.

4. The model construction method of the rocket engine strong dynamic load test device support model according to claim 3 is characterized in that: In step 100, the weak position of the rocket engine strong dynamic load test model is determined by: The weak parts of the strong dynamic load test model are confirmed by calculating the operating parameters of the engine. Specifically, the locations where deformation, vibration and explosion occur in the strong dynamic load test model during the test are defined as the weak parts of the strong dynamic load test model.

5. The model construction method of the rocket engine strong dynamic load test device support model according to claim 3 is characterized in that: In step 200, the test method for arranging the support points of the support structure is: Finite element analysis was used to perform numerical simulation and to conduct detailed analysis of the stress distribution and deformation of the strong dynamic load test model under different support point layout schemes; According to the analysis results, determine the number, position, spacing parameters of the support points of the support structure, as well as the rod material and rod structure of the support structure; A support structure is formed on the outside of the strong dynamic load test model according to the number, position and spacing parameters of the support points.

6. The model construction method of the rocket engine strong dynamic load test device support model according to claim 5 is characterized in that: Different rod materials of the supporting structure are selected as test objects respectively, and the stress distribution of the supporting structure composed of each rod material under different strong dynamic load conditions is analyzed by combining numerical simulation and test verification, so as to find out the weak links of the strength of the rocket engine strong dynamic load test model formed by different rod materials; The strength differences corresponding to different rod materials are counted respectively to determine the rod material selected for the supporting structure.

7. The model construction method of the rocket engine strong dynamic load test device support model according to claim 5 is characterized in that: Rod structures using different supporting structures were selected as test objects. The stress distribution of the supporting structure composed of each rod structure under different strong dynamic load conditions was analyzed by combining numerical simulation and experimental verification. The rod size and rod connection method of the supporting structure were optimized based on the stress analysis results to improve the stiffness of the strong dynamic load test model.

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