A modular and reconfigurable aircraft structural strength design method

Abstract

The present application provides a modular and reconfigurable aircraft structural strength design method, the method comprising: determining various single-purpose aircraft structural configuration design schemes according to usage requirements, calculating the equivalent structural strength design weight according to a single configuration design method; determining whether the difference in equivalent structural strength design weight under various single configuration design schemes meets a predetermined gap; when the difference in equivalent structural strength design weight of two or more configurations is within the predetermined gap, the aircraft structures of the two or more configurations can be combined for design, thereby forming a modular or reconfigurable aircraft structural overall plan; dividing common modules and dedicated modules according to overall aerodynamic layout requirements, and realizing aircraft configuration changes through rapid reorganization of common modules and dedicated modules. The method of the present application not only meets the user's usage requirements, but also can achieve the optimized structural aerodynamic layout for each mission, thereby reducing overall mission costs.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft structure design, and in particular relates to a modular and reconfigurable aircraft structure strength design method. Background Art

[0002] As aircraft economics and cost control become increasingly important in aircraft design, low-cost, multi-purpose aircraft have become the trend in future aircraft design. Currently, the structural strength design of series aircraft platforms, both domestically and internationally, generally evolves from a single model to multiple models. This involves gradually evolving a basic model to meet the diverse needs of different users, forming an aircraft family. However, each aircraft within a family has its own independent design specifications, and its missions are limited to a fixed overall structural layout. Structural components share only a limited degree of commonality during design and manufacturing, with little consideration given to the economic benefits of commonality in operation. When developing a new generation of aircraft, the substantial investment and time required necessitate even higher requirements for cost control, multi-configuration, and advanced features. Designs that only fulfill a single mission type or are adaptable to a single operating environment or conditions clearly fail to meet the low-cost design requirements of the new generation.

[0003] Therefore, it is necessary to adopt an aircraft structural strength design method based on modular and reconfigurable design ideas. In the scheme design stage, the overall aerodynamic shape and structural layout of the series aircraft can be determined according to multiple mission requirements or technical status requirements in multiple configurations, and the aircraft body structure can be divided into general modules and exclusive modules. Through module selection and combination, the aircraft product structure and function are analyzed and reorganized, and a series of products with different functions are derived, so that the aircraft structure platform can be quickly and economically changed according to the mission, reducing the mission cost of the aircraft, increasing the flexibility of user use, and meeting the user's uncertainty needs. Summary of the Invention

[0004] The purpose of this application is to provide an aircraft structural strength design method based on modularity and reconfigurability to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of this application is: a modular and reconfigurable aircraft structural strength design method, the method comprising:

[0006] According to the use requirements, various single-purpose aircraft structure configuration design schemes are determined, and the equivalent structural strength design weight is calculated according to the single configuration design method. The calculation method of the equivalent structural strength design weight is: G 当量 =n·f·G, where n is the maximum overload, f is the uncertainty coefficient, and G is the basic structural strength design weight;

[0007] Determine whether the difference in equivalent structural strength design weight under various single configuration design schemes meets the predetermined gap;

[0008] When the difference in equivalent structural strength design weights of two or more configurations is within a predetermined range, the aircraft structures of the two or more configurations can be combined for design, thereby forming a modular or reconfigurable overall aircraft structure plan;

[0009] General modules and exclusive modules are divided according to the overall aerodynamic layout requirements, and the aircraft configuration can be changed through the rapid reorganization of general modules and exclusive modules.

[0010] Furthermore, the predetermined gap is 10%.

[0011] Furthermore, the universal module is a module that can be used in two or more configurations;

[0012] The exclusive module is a module that can only be used in a single configuration or is designed as a general module, which results in increased weight or unsatisfactory performance.

[0013] Furthermore, the static strength of the universal module is determined according to all design load conditions in two or more configurations;

[0014] The fatigue strength of the universal module is determined according to the sum of the full life cycle design indicators of the aircraft structure in two or more configurations.

[0015] Furthermore, when the weight increase of the universal module causes the basic technical and tactical performance indicators to fail to meet the requirements, the maximum value of the life indicators of each single configuration of the aircraft structure in more than two configurations shall be used.

[0016] Furthermore, the static strength of the dedicated module is determined according to the single configuration design load condition used;

[0017] The fatigue strength of the dedicated module is designed and determined according to the single configuration life index used.

[0018] In addition, the present application also provides an aircraft structure, which is obtained by any of the above-mentioned modular and reconfigurable aircraft structure strength design methods.

[0019] The method of the present application not only meets the user's usage needs, but also can achieve the optimal structural aerodynamic layout of each task and reduce the overall task cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] 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.

[0021] Figure 1This is a flow chart of the aircraft structure strength design method of this application.

[0022] Figure 2 Schematic diagram of an aircraft in a ground attack configuration and a long-endurance reconnaissance configuration in one embodiment of the present application.

[0023] Figure 3 This is a schematic diagram of a general module in an embodiment of the present application.

[0024] Figure 4 Schematic diagram of a dedicated module for ground attack configuration in one embodiment of the present application.

[0025] Figure 5 This is a schematic diagram of a dedicated module for a long-endurance reconnaissance configuration in one embodiment of the present application. DETAILED DESCRIPTION

[0026] 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.

[0027] In order to solve the problems of poor versatility, long design cycle and high development cost of current serialized aircraft structural platforms, this application proposes an aircraft structural strength design method based on modular or reconfigurable design ideas to meet the low-cost and multi-configuration design requirements of the future new generation of aircraft and adapt to the rapidly changing needs of future battlefields.

[0028] The aircraft structural strength design method based on modular or reconfigurable design concepts in this application includes the following steps:

[0029] S1. Overall design of modular or reconfigurable aircraft structures

[0030] According to user needs, determine the structural configuration design schemes of various single-purpose aircraft, and calculate the equivalent structural strength design weight according to the design method: G 当量 =n·f·G;

[0031] Where n is the maximum overload, f is the uncertainty coefficient, and G is the basic structural strength design weight.

[0032] When the difference in equivalent structural strength design weight between two or more configurations is within a predetermined gap (for example, 10%), the two or more configurations can be combined to form a modular or reconfigurable aircraft structure overall plan. Common modules and dedicated modules can be divided according to the overall aerodynamic layout requirements, and the aircraft configuration can be changed through the rapid reorganization of common modules and dedicated modules.

[0033] like Figure 2Shown are two configurations of a certain type of aircraft provided in this embodiment of the present application, which perform daily tasks mainly as ground attack (Figure a) and long-endurance reconnaissance (Figure b). The equivalent structural strength design weight under the ground attack configuration is 30,000 kg, the basic structural strength design weight G = 6,000 kg, the maximum overload n = 4, the uncertainty coefficient f = 1.25, and the life index under this configuration is 3,000 flight hours.

[0034] The equivalent structural strength design weight in the long-endurance reconnaissance configuration is 30,000 kg, the basic structural strength design weight G = 8,000 kg, the maximum overload n = 2.5, and the uncertainty factor f = 1.5. The service life target in this configuration is 8,000 flight hours.

[0035] The equivalent structural strength design weights of the two configurations are essentially equivalent, less than a predetermined value, allowing them to be combined. Based on the overall aerodynamic layout requirements, the wing utilizes a platform combination of a universal root module and dedicated outer wing box modules, ultimately achieving a multifunctional, serialized UAV platform capable of both unmanned ground attack and long-endurance reconnaissance missions.

[0036] S2. General module design

[0037] Modules that can be used in two or more configurations should be designed as universal modules, and their static strength should be designed for all design load conditions in the multi-configuration schemes in which they are used. As support for dedicated modules, their design requires sufficient design space and support stiffness, and they should generally be designed as multi-load transmission structures. Their fatigue strength should, in principle, be designed based on the sum of the full life cycle design indicators of the multi-configuration airframe structural platform. If structural weight increases prevent basic technical and tactical performance requirements from being met, the design should be based on no less than the maximum life cycle indicator of each single configuration in the multi-configuration structural platform.

[0038] For example, in the above two configurations, the universal module is composed of two parts, such as Figure 3 As shown in the figure, the fuselage universal module 11 and the wing root universal module 12. The finished mission and other systems are installed in the universal fuselage module, using a modular docking method, and the corresponding mission module is installed according to the mission requirements.

[0039] The static strength of the fuselage universal module 11 and the wing root universal module 12 is designed according to all design load conditions of unmanned ground attack and long-endurance reconnaissance, and the fatigue strength is designed according to the life index of 10,000 flight hours.

[0040] S3, exclusive module design

[0041] Modules used only in a single mission configuration, where a general module design would increase weight or fail to meet performance requirements, are designed as dedicated modules with relatively independent and clear process interfaces, enabling rapid assembly and disassembly. Structural static strength design is conducted according to the design load conditions of the single configuration scheme used by the dedicated module. Fatigue strength design is conducted according to the lifespan design indicators of the single configuration scheme used.

[0042] In the above two configuration embodiments, corresponding outer wing dedicated modules are designed according to the mission requirements of ground attack and long-endurance reconnaissance, such as Figure 4 and Figure 5 The modules shown are specific to the ground attack configuration and the modules specific to the long-endurance reconnaissance configuration.

[0043] The static strength of the ground attack configuration-specific module is designed according to the ground attack configuration design load condition, and the fatigue strength is designed according to the 3,000 flight hour life index.

[0044] The static strength of the dedicated module for the long-endurance reconnaissance configuration is designed according to the design load conditions of the long-endurance reconnaissance configuration, and the fatigue strength is designed according to the life index of 8,000 flight hours.

[0045] For example, suppose that according to the organizational structure and mission requirements, the user needs to equip 5 ground attack drones and 3 long-flight ground surveillance drones. The number of drones dispatched during the mission shall not exceed 5, the number of long-flight ground surveillance drones shall not exceed 3, and the number of ground attack drones shall not exceed 2.

[0046] If the existing technology is used, a total of 8 drones need to be manufactured and provided. However, if the method of the present application is used to design the aircraft structure, it is only necessary to manufacture and provide 5 universal fuselage and wing modules, 3 long-endurance ground integrated surveillance configuration outer wing dedicated modules and 2 ground attack configuration outer wing dedicated modules.

[0047] It can be seen that the method of the present application not only meets the user's usage needs, but also can achieve the optimal structural aerodynamic layout of each task and reduce the overall task cost.

[0048] 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 modular and reconfigurable aircraft structural strength design method, characterized in that: The method comprises: According to the use requirements, various single-purpose aircraft structure configuration design schemes are determined, and the equivalent structural strength design weight is calculated according to the single configuration design method. The calculation method of the equivalent structural strength design weight is: G 当量 =n·f·G, where n is the maximum overload, f is the uncertainty coefficient, and G is the basic structural strength design weight; Determine whether the difference in equivalent structural strength design weight under various single configuration design schemes meets the predetermined gap; When the difference in equivalent structural strength design weights of two or more configurations is within a predetermined range, the aircraft structures of the two or more configurations can be combined for design, thereby forming a modular or reconfigurable overall aircraft structure plan; General modules and exclusive modules are divided according to the overall aerodynamic layout requirements, and the aircraft configuration can be changed through the rapid reorganization of general modules and exclusive modules.

2. The modular and reconfigurable aircraft structure strength design method according to claim 1, wherein: The predetermined difference is 10%.

3. The modular and reconfigurable aircraft structure strength design method according to claim 1, wherein: The universal module is a module that can be used in two or more configurations; The exclusive module is a module that can only be used in a single configuration or is designed as a general module, which results in increased weight or unsatisfactory performance.

4. The modular and reconfigurable aircraft structure strength design method according to claim 3, wherein: The static strength of the universal module is determined according to all design load conditions in two or more configurations; The fatigue strength of the universal module is determined according to the sum of the full life cycle design indicators of the aircraft structure in two or more configurations.

5. The modular and reconfigurable aircraft structure strength design method according to claim 4, characterized in that: When the weight increase of the common module causes the basic technical and tactical performance indicators to be unable to meet the requirements, the maximum value of the life indicators of each single configuration of the aircraft structure in more than two configurations shall be used.

6. The modular and reconfigurable aircraft structure strength design method according to claim 3, wherein: The static strength of the dedicated module is determined according to the single configuration design load condition used; The fatigue strength of the dedicated module is designed and determined according to the single configuration life index used.

7. An aircraft structure, characterized in that The aircraft structure is obtained by the modular and reconfigurable aircraft structure strength design method according to any one of claims 1 to 6.

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