Aircraft design method and system based on mechanical load and mechanical environment

Abstract

The present application relates to the technical field of spacecraft design, and provides a spacecraft design method based on mechanical load and mechanical environment, comprising: S1: performing whole-vehicle level basic frequency design, by establishing a whole-vehicle level joint analysis model of a platform and a payload and optimizing stiffness and layout, the whole-vehicle mass is reduced while the whole-vehicle basic frequency is improved; S2: performing integrated design of load and mechanical environment conditions, according to the interface conditions of the carrier system, the mechanical environment conditions and the mechanical load conditions of each position of the payload are directly obtained from the whole-vehicle model, and the artificial boundary is eliminated to avoid multiple accumulations of safety margins; S3: optimizing the ground test process, after the basic mechanical environment identification test of the payload is completed, the whole-vehicle level ground environment test is directly performed, the development cycle is shortened and the cost is reduced. The mechanical conditions of the whole vehicle are directly transmitted to the mechanical conditions of the single machine, and multiple accumulations of safety margins caused by artificial division of the interface are avoided.

Description

Technical Field

[0001] This invention relates to the technical field of spacecraft design, and in particular to a spacecraft design method and system based on mechanical loads and mechanical environment. Background Technology

[0002] In aircraft design, various payloads are required to fulfill the target design functions. Payloads are generally composed of various individual units. Each payload is mounted on a platform, which serves as the foundation for payload installation. The payloads are the "organs" of the aircraft, while the platform is its "skeleton." Platforms and payloads are typically designed by different units; the platform is generally designed by the overall system, while the payloads are designed by their respective subsystems. To clarify the responsibility interface, from a mechanical perspective, the platform will impose fundamental frequency requirements, mechanical loads, and mechanical environment requirements on the payloads. These parameters are influenced by the platform, excitation, and payloads, and these requirements serve as important inputs for platform and payload design. In this paper, "payload" refers to the various individual units carried by the aircraft, collectively referred to as "payload." Mechanical loads refer to the mechanical conditions used in structural strength analysis; they are loads from a mechanical perspective.

[0003] The platform's fundamental frequency requirement for the payload is to avoid resonance damage caused by the payload's frequency being close to the platform's frequency. Frequency misalignment design is an important method in spacecraft dynamics design, especially for large payloads and critical equipment. Reasonably defining the fundamental frequency requirement for the payload is crucial for the entire spacecraft development, especially for large single-unit, heavy payloads. These payloads are generally large in size and weight; unreasonable fundamental frequency specifications can cause a surge in payload weight, severely restricting the improvement of the spacecraft's payload ratio and wasting valuable carrying capacity.

[0004] The platform's requirements for the mechanical environment of the payload stem from the fact that spacecraft undergo various mechanical environmental conditions during ascent and other operational phases. It is essential to ensure that the payload can withstand the mechanical environmental conditions required throughout the spacecraft's entire lifespan, preventing structural or functional failures caused by dynamic environments. Accurate prediction of mechanical environmental conditions is crucial for the development of the payload and its components, effectively avoiding additional weight design costs. Accurately and reasonably predicting the payload's mechanical environment is a vital aspect of spacecraft design. Inappropriate mechanical environmental conditions can lead to significant cost increases during payload design, especially for large payloads, and may even negatively impact the platform's dynamic characteristics.

[0005] The mechanical load requirements of the payload on the platform. During ascent, on-orbit, and reentry, the spacecraft's payload exerts certain mechanical loads on the platform, which are crucial inputs for spacecraft platform design. Simultaneously, the platform also exerts loads on the payload. Accurately and reasonably defining these conditions can optimize platform design parameters and reduce structural weight. For large payloads, the mechanical load conditions on the platform are closely related to the dynamic characteristics of their structure. If the dynamic characteristics of the payload change during the early design phase, the previously predicted mechanical load conditions must also change accordingly, thus affecting the spacecraft platform design and requiring revisions.

[0006] In traditional spacecraft design, the launch vehicle team typically sets the fundamental frequency requirements, mechanical loads, and mechanical environment requirements for the entire spacecraft. The spacecraft platform is then designed based on mission requirements, and the platform sets its own fundamental frequency and mechanical environment requirements for the payload, as well as the mechanical load requirements exerted by the payload on the platform. Since the platform and payload are designed by different units, this design model uses the interface between the payload and the spacecraft platform as a dividing line, with the mechanical environment at this dividing line acting as the transmission mechanism. This model is widely adopted due to its clear interface and well-defined division of responsibilities. The payload designer conducts relevant designs based on the overall design requirements. However, in the decomposition and transmission of these indicators, there is a cumulative safety margin introduced by the human interface. During the preliminary design of the payload, its functional design is completed first, followed by meeting the frequency requirements of the spacecraft platform. Small payloads generally have higher frequencies, but some large payloads have lower frequencies. If the fundamental frequency requirements set by the spacecraft for the payload are inaccurate, the payload may have to be designed with increased rigidity to achieve the higher frequency, leading to increased structural mass and potentially altering the platform's dynamic characteristics. Secondly, the mechanical environment requirements of the platform for the payload must be met. The payload side conducts dynamic simulations and experiments, applies mechanical environmental conditions, and tests whether the payload passes the mechanical environment test. If problems are found, the design needs to be revised back to the design stage until the payload passes the mechanical environment test. For the aircraft platform, the dynamic impact of the payload on the entire system needs to be predicted, including frequency, mechanical load, and mechanical environment. After the payload's preliminary design is completed, these indicators of the aircraft need to be re-estimated to ensure that the aircraft platform can withstand the dynamic impact of the payload in actual operation. If the mechanical load imposed by the payload on the platform exceeds the initial design value, the platform design needs to be improved, such as through local reinforcement or structural modifications; in severe cases, significant structural modifications may be required. This process is highly complex and iterative, involving the joint participation and repeated iterations of multiple systems. In particular, the accumulation of safety margins due to artificially segmented interfaces results in significant redundancy in the final weight of the aircraft, wasting valuable carrying capacity. Summary of the Invention

[0007] To address the aforementioned problems, the present invention aims to provide a spacecraft design method and system based on mechanical loads and mechanical environment. It overcomes the shortcomings of existing spacecraft or aircraft whole-vehicle dynamics design processes, achieving direct transfer of whole-vehicle mechanical conditions to individual-vehicle mechanical conditions. This avoids the repeated accumulation of safety margins caused by artificially segmented interfaces, effectively reducing the overall structural weight of the spacecraft.

[0008] The above-mentioned objective of this invention is achieved through the following technical solutions: An aircraft design method based on mechanical loads and mechanical environment includes the following steps: S1: Perform overall fundamental frequency design. By establishing an overall joint analysis model of the platform and the payload and optimizing stiffness and layout, the overall fundamental frequency can be improved while reducing the overall mass. S2: Perform integrated design of load and mechanical environment conditions. Based on the interface conditions of the rocket provided by the launch system, directly obtain the mechanical environment conditions and mechanical load conditions of each position of the effective load from the whole model, and eliminate artificial boundaries to avoid multiple accumulations of safety margin. S3: Optimize the ground testing process. After the payload completes the basic mechanical environment qualification test at the single-unit level, directly conduct the ground environment test at the whole-device level, shortening the development cycle and reducing costs.

[0009] Furthermore, step S1 specifically includes: Based on the requirements of the launch frequency index, an integrated fundamental frequency design is proposed for the platform-payload integrated system. At the same time, a joint analysis model of the platform and payload is established, eliminating the need for a separate fundamental frequency requirement for the payload. The flexibility of the platform, the flexibility of the payload, and the stiffness characteristics of the platform-payload connection surface are fully considered to reduce stiffness discontinuities caused by interface decomposition. This approach aims to reduce the overall mass of the aircraft while maximizing the overall fundamental frequency.

[0010] Furthermore, step S1 also includes: By combining integrated structure and layout optimization, the overall mass of the aircraft is reduced while the fundamental frequency of the aircraft is increased; after the payload design is completed, an integrated dynamic analysis model is directly constructed with the platform to give the modal frequencies of the entire aircraft, thereby answering the requirements of the launch vehicle. Based on the lateral and longitudinal fundamental frequency requirements provided in the launch vehicle user manual, the overall lateral and longitudinal modal frequencies of the spacecraft platform-payload assembly are designed to meet launch requirements. Frequency design requirements are only proposed for the entire spacecraft, without separately proposing frequency requirements for each payload. The payload dynamics model and the platform model are integrated into a unified model to obtain the natural frequencies and mode shapes of the unified model, which are then used as the design parameters for the spacecraft. If the frequency parameters of the unified model do not meet the requirements, the platform and payload are redesigned, and the stiffness of weak points is improved until the combined model meets the frequency parameters required for launch. This effectively reduces the difficulties caused by fundamental frequency design for various complex payloads and effectively reduces structural weight.

[0011] Furthermore, step S2 specifically includes: Based on the mechanical environment conditions of the rocket-device interface provided by the launch system, the effective load and mechanical environment conditions of each individual unit are obtained directly from the platform-payload assembly model, eliminating the artificial dividing boundary between the platform and the payload, realizing direct transfer from the whole system to the individual units, and avoiding multiple accumulations of safety margins. The integrated analysis model directly provides the mechanical environment conditions and mechanical load conditions at each position of the payload, where the mechanical environment conditions are used for the design of the payload, and the mechanical loads are used for the structural strength design of the platform and the payload. Based on the mechanical input conditions of the rocket-device interface provided by the launch system, the load and mechanical environment conditions of each individual unit are obtained directly from the platform-payload assembly model, eliminating the artificial boundary between the platform and the payload, and carrying out joint design in aspects including mechanical loads and environmental conditions, realizing direct transfer from the whole system to the individual units, and avoiding multiple accumulations of safety margins.

[0012] Furthermore, step S2 also includes: In general design, after the mechanical environmental conditions are given to each payload in the overall design, each payload will undergo relevant environmental tests. Because the mechanical impedance of its boundary is inconsistent with the actual state, the amplification caused by each payload during environmental tests is much greater than the actual state on the whole device. This will cause each payload to strengthen the structure, resulting in additional weight and cost. Response analysis is performed on the platform-payload assembly under various given excitations to obtain the mechanical environment conditions and mechanical load indicators of the payload, and related design and verification are carried out. If the payload and platform cannot be completed or the cost is too high, the platform and payload are redesigned and the process returns to step S1. Based on the integrated analysis model, the mechanical environment conditions and mechanical load conditions of each payload are directly given, and the single-machine dynamics calculation results are optimized to make them closer to the actual state of the product, and to minimize the layer amplification and layer accumulation caused by artificially dividing the interface.

[0013] Furthermore, step S3 specifically includes: During ground testing, after completing its basic mechanical environment qualification test at the unit level, the payload directly conducts various mechanical environment tests on the platform-payload assembly, shortening the development and testing time and reducing development costs. After completing their respective qualification tests, each unit of the payload participates in the assembly-level mechanical environment test along with the assembly, optimizing the entire aircraft development process, accelerating the development progress, and saving development funds.

[0014] Furthermore, step S3 also includes: The conventional process requires each individual payload to undergo its own mechanical tests, followed by subsystem-level mechanical environment tests along with each payload. Since the mechanical boundaries differ significantly from those on the actual aircraft, ground tests may result in overtesting, increasing the development cycle, time, and costs. If problems are found during the aircraft-level testing, i.e., the test fails, the process returns to step S1 or S2 for redesign. By rationally extracting the mechanical environment conditions of individual payloads, after each payload completes its relevant qualification-level mechanical tests, it can directly undergo relevant mechanical testing verification along with the entire aircraft, accelerating the development speed and optimizing the entire aircraft development process. This avoids the overtesting, multiple rounds of iterative design, and additional development process steps and testing costs caused by the ground test boundary impedance of each payload exceeding the actual aircraft state, which is common in traditional processes.

[0015] A mechanical load and mechanical environment-based aircraft design system for performing the above-described mechanical load and mechanical environment-based aircraft design method includes: The fundamental frequency design module is used for overall fundamental frequency design. By establishing an overall joint analysis model of the platform and the payload and optimizing stiffness and layout, the overall fundamental frequency is increased while reducing the overall mass. The load environment module is used for integrated design of load and mechanical environment conditions. Based on the rocket interface conditions provided by the launch system, it directly obtains the mechanical environment conditions and mechanical load conditions at each position of the effective load from the whole model, eliminating artificial boundaries to avoid multiple accumulations of safety margin. The test optimization module is used to optimize the ground test process, allowing the entire device to be tested directly after the payload has completed the basic mechanical environment qualification test at the single-unit level, thus shortening the development cycle and reducing costs.

[0016] A computer device, characterized in that it includes a memory and one or more processors, wherein the memory stores computer code, and when the computer code is executed by the one or more processors, causes the one or more processors to perform the method as described above.

[0017] A computer-readable storage medium, characterized in that the computer-readable storage medium stores computer code, which, when executed, is performed as described above.

[0018] Compared with existing technologies, this invention discloses an integrated spacecraft design method based on optimization of mechanical loads and mechanical environmental conditions. It weakens the concept of the payload's fundamental frequency and directly provides the mechanical environmental and load conditions of the payload through a complete platform payload model. It performs joint design in terms of mechanical loads, environmental conditions, and ground testing, achieving direct transfer of overall spacecraft conditions to individual spacecraft conditions and avoiding multiple accumulations of safety margins. Compared with existing technologies, this invention has the following beneficial effects: (1) Significantly reduce the structural weight of the aircraft and improve the payload ratio. By designing the fundamental frequency at the whole-vehicle level, a joint analysis model of the platform and the payload is established. The fundamental frequency requirement for the payload is no longer proposed separately. The flexibility of the platform, the flexibility of the payload, and the stiffness characteristics of the connection surface are fully considered. Combined with the optimization of the integrated structure and layout, the fundamental frequency of the whole vehicle is significantly improved while reducing the overall weight. This design avoids the structural redundancy caused by the layer-by-layer decomposition of frequency indicators, the discontinuity of stiffness at the artificial interface, and the repeated accumulation of safety margins in traditional methods. Especially for large and complex payloads, it can effectively alleviate the problem of weight surge caused by unreasonable fundamental frequency requirements, thereby saving valuable carrying capacity.

[0019] Optimizing mechanical loads and environmental conditions reduces unit design costs. Based on the mechanical input conditions of the launch vehicle interface provided by the launch system, the mechanical loads and environmental conditions of each unit are directly obtained from the platform-payload integrated model, eliminating the artificial separation boundary between the platform and the payload. This integrated design ensures that the mechanical boundaries are highly consistent with the actual flight conditions, avoiding the problems of boundary impedance mismatch, environmental test amplification effects, and multiple accumulation of safety margins in traditional segmented designs. The payload does not need additional structural reinforcement to meet excessively harsh environmental conditions, thus significantly reducing the unit design weight and development cost.

[0020] (3) Shortened development cycle and reduced testing costs. The ground testing process has been optimized: After the payload completes the basic mechanical environment qualification test at the single-unit level, it can directly conduct various environmental tests at the platform-payload assembly level without having to conduct separate subsystem-level mechanical tests. This process significantly shortens the development cycle, reduces the number of repeated design and iteration tests, and lowers testing costs. At the same time, since the boundaries of the assembly-level tests are closer to the actual flight conditions, the overtesting problem caused by differences in mechanical boundaries in the traditional process is effectively avoided, further improving the effectiveness of the tests and the reliability of the product. Attached Figure Description

[0021] Figure 1 A flowchart illustrating the steps involved in designing the mechanical load and environmental interface for traditional spacecraft. Figure 2 This is an overall flowchart of the aircraft design method based on mechanical load and mechanical environment of the present invention. Detailed Implementation

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

[0023] Those skilled in the art will understand that, unless specifically stated otherwise, the singular forms “a,” “an,” “the,” and “the” used herein may also include the plural forms. It should be further understood that the term “comprising” as used in this specification means the presence of the stated features, integers, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0024] like Figure 1 As shown, the specific process of the traditional design scheme is as follows: After clarifying the overall mission requirements of the aircraft, the traditional design method first involves platform design and payload design. The "platform-payload" interface serves as the dividing line between the two, with a clear division of responsibilities. The platform designer, based on the launch system's fundamental frequency requirements for the entire aircraft, sets separate fundamental frequency requirements for the payload to avoid resonance damage caused by the payload's frequency approaching the platform's frequency. The payload designer, in turn, must meet the fundamental frequency specifications set by the platform. Especially for large payloads, higher frequencies often necessitate a more rigid design, leading to a significant increase in structural mass. After the frequency requirements are met, the platform designator further sets mechanical environment requirements (such as vibration and shock conditions) for the payload, while the payload designator must provide feedback on the mechanical load conditions it exerts on the platform. Subsequently, the payload designator conducts single-aircraft-level mechanical environment adaptability verification based on the platform's provided mechanical environment conditions and structural strength verification based on the given mechanical load conditions. The platform designator, in turn, verifies the platform's structural strength based on the mechanical load conditions fed back by the payload. Only when the payload's mechanical environment adaptability, structural strength, and platform design all meet the relevant requirements can the entire aircraft-level ground testing commence. The overall design of an aircraft is only considered complete after successful ground testing at the whole-vehicle level. In this traditional process, because the platform and payload are designed by different units, the artificial separation of interfaces leads to the accumulation of safety margins at each level. Furthermore, the boundary mechanical impedance of the payload during ground testing is inconsistent with the actual state of the entire aircraft, easily resulting in over-testing and structural reinforcement, causing additional weight and cost. The entire design process is complex and iterative, involving multiple iterations, which severely restricts the improvement of the aircraft's payload ratio and development efficiency.

[0025] Based on the problems in traditional design methods, this invention discloses an aircraft design method based on mechanical loads and mechanical environment, including: (1) Aircraft fundamental frequency design, while establishing an integrated analysis model for the payload and platform. The platform no longer proposes separate fundamental frequency requirements for the payload. Through integrated design, the fundamental frequency of the entire aircraft is increased as much as possible while reducing the structural mass of the aircraft platform and payload. (2) Formulation of mechanical loads and mechanical environment conditions. Based on the mechanical environment conditions of the launch vehicle interface provided by the launch system, the mechanical loads and mechanical environment conditions of the payload are obtained directly from the analysis model of the "platform-payload" combination, eliminating the influence of the artificial boundary between the platform and the payload. The mechanical characteristics are directly transferred from the entire aircraft to the single unit, avoiding the multiple accumulation of safety margins caused by the division of interface responsibilities, and reducing the design weight of the payload. (3) Optimization of ground test process. During the ground test, after completing the basic mechanical environment identification test at the single unit level and the static strength test of the platform structure, various environmental tests at the entire "platform-payload" combination level can be carried out directly, shortening the development time and reducing the development cost. The method described in this invention can effectively design load conditions during the active phase of a spacecraft and other operating cycles, effectively balance and optimize mechanical environmental conditions, optimize the fundamental frequency of the entire spacecraft, and reduce the weight of the payload and platform structure.

[0026] The following is an illustration through specific examples: First Embodiment like Figure 2 As shown in the figure, this embodiment presents an aircraft design method based on mechanical loads and mechanical environment, which includes the following steps: S1: Perform overall fundamental frequency design. By establishing an overall joint analysis model of the platform and payload and optimizing stiffness and layout, the overall fundamental frequency can be increased while reducing the overall mass.

[0027] Step S1 specifically includes: Based on the requirements of the launch frequency index, an integrated fundamental frequency design is proposed for the platform-payload integrated system. At the same time, a joint analysis model of the platform and payload is established, eliminating the need for a separate fundamental frequency requirement for the payload. The flexibility of the platform, the flexibility of the payload, and the stiffness characteristics of the platform-payload connection surface are fully considered to reduce stiffness discontinuities caused by interface decomposition. This approach aims to reduce the overall mass of the aircraft while maximizing the overall fundamental frequency.

[0028] Step S1 also includes: By combining integrated structure and layout optimization, the overall mass of the aircraft is reduced while the fundamental frequency of the aircraft is increased; after the payload design is completed, an integrated dynamic analysis model is directly constructed with the platform to give the modal frequencies of the entire aircraft, thereby answering the requirements of the launch vehicle. Based on the lateral and longitudinal fundamental frequency requirements provided in the launch vehicle user manual, the overall lateral and longitudinal modal frequencies of the spacecraft platform-payload assembly are designed to meet launch requirements. Frequency design requirements are only proposed for the entire spacecraft, without separately proposing frequency requirements for each payload. The payload dynamics model and the platform model are integrated into a unified model to obtain the natural frequencies and mode shapes of the unified model, which are then used as the design parameters for the spacecraft. If the frequency parameters of the unified model do not meet the requirements, the platform and payload are redesigned, and the stiffness of weak points is improved until the combined model meets the frequency parameters required for launch. This effectively reduces the difficulties caused by fundamental frequency design for various complex payloads and effectively reduces structural weight.

[0029] In this embodiment, frequency requirements for the entire spacecraft "platform-payload" assembly are proposed based on the launch vehicle's fundamental frequency requirements. For example, according to a launch vehicle user manual, the launch vehicle's lateral fundamental frequency requirement is ≥10Hz, and its longitudinal fundamental frequency requirement is ≥10Hz. Therefore, the overall lateral modal frequency of the designed spacecraft "platform-payload" assembly needs to be ≥10Hz, and its longitudinal modal fundamental frequency needs to be ≥10Hz. This design method only proposes frequency design requirements for the entire spacecraft, rather than separately proposing frequency requirements for each payload. Instead, it integrates the payload dynamics model with the platform model to form an integrated "platform-payload" model, obtaining the natural frequencies and mode shapes of the integrated model, which are then used as the spacecraft's design parameters. If the frequency parameters of the integrated model do not meet the requirements, the platform and payload need to be redesigned, with stiffness improvements made to address weak points, until the integrated model meets the launch vehicle's required frequency parameters. In conventional design methods, after obtaining the launch vehicle's fundamental frequency requirements for the entire assembly, the platform also proposes fundamental frequency requirements for each payload, typically requiring each payload to avoid the platform's dominant frequencies. When the payload is small in size or has low mass, its natural frequency is generally high. However, when the payload is large in size and mass, especially for some large payloads, increasing the fundamental frequency comes at a high cost, significantly increasing its overall mass. When the payload mass increases significantly, it in turn greatly reduces the platform's fundamental frequency performance, forcing the platform to be designed with increased stiffness to increase the frequency, thus increasing the platform's weight. Overall, this results in a cumulative effect of mass accumulation, severely wasting valuable carrying capacity and causing unnecessary waste.

[0030] S2: Perform integrated design of load and mechanical environment conditions. Based on the interface conditions of the rocket provided by the launch system, directly obtain the mechanical environment conditions and mechanical load conditions of each position of the effective load from the whole model, eliminate artificial boundaries to avoid multiple accumulations of safety margin.

[0031] Step S2 specifically includes: Based on the mechanical environment conditions of the rocket-device interface provided by the launch system, the effective load and mechanical environment conditions of each individual unit are obtained directly from the platform-payload assembly model, eliminating the artificial dividing boundary between the platform and the payload, realizing direct transfer from the whole system to the individual units, and avoiding multiple accumulations of safety margins. The integrated analysis model directly provides the mechanical environment conditions and mechanical load conditions at each position of the payload, where the mechanical environment conditions are used for the design of the payload, and the mechanical loads are used for the structural strength design of the platform and the payload. Based on the mechanical input conditions of the rocket-device interface provided by the launch system, the load and mechanical environment conditions of each individual unit are obtained directly from the platform-payload assembly model, eliminating the artificial boundary between the platform and the payload, and carrying out joint design in aspects including mechanical loads and environmental conditions, realizing direct transfer from the whole system to the individual units, and avoiding multiple accumulations of safety margins.

[0032] Step S2 also includes: In general design, after the mechanical environmental conditions are given to each payload in the overall design, each payload will undergo relevant environmental tests. Because the mechanical impedance of its boundary is inconsistent with the actual state, the amplification caused by each payload during environmental tests is much greater than the actual state on the whole device. This will cause each payload to strengthen the structure, resulting in additional weight and cost. Response analysis is performed on the platform-payload assembly under various given excitations to obtain the mechanical environment conditions and mechanical load indicators of the payload, and related design and verification are carried out. If the payload and platform cannot be completed or the cost is too high, the platform and payload are redesigned and the process returns to step S1. Based on the integrated analysis model, the mechanical environment conditions and mechanical load conditions of each payload are directly given, and the single-machine dynamics calculation results are optimized to make them closer to the actual state of the product, and to minimize the layer amplification and layer accumulation caused by artificially dividing the interface.

[0033] In this embodiment, step S2, based on the established "platform-payload" model, proposes the mechanical environment conditions and mechanical load conditions at the payload installation location. The mechanical environment conditions are used for payload design, while the mechanical load conditions are used for structural strength design of the platform and payload. In this embodiment, the response analysis of the "platform-payload" assembly exemplified in step S1 under various given excitations can be performed to obtain the mechanical environment conditions and mechanical load indices of the payload, and related design and verification can be carried out. If the payload and platform cannot be completed or the cost is too high, then the platform and payload need to be redesigned, and the process returns to step S1. The platform structure and payload are redesigned, and the mechanical environment conditions and mechanical load conditions of the payload are reduced by means of response prediction under various excitations. Based on the integrated analysis model, the mechanical environment conditions and mechanical load conditions of each payload are directly given. The mechanical environment conditions are used for anti-mechanical environment design of each payload, while the mechanical load conditions are used for structural strength design of the platform and each payload. As an integrated analysis model, it can directly provide the single-machine-level mechanical environment and mechanical loads down to the payload, greatly optimizing the single-machine dynamics calculation results. Its mechanical boundaries have been significantly optimized compared to the hierarchical verification in traditional methods, and are closer to the actual state of the product. It minimizes the layered amplification and accumulation caused by artificially segmented interfaces. This can significantly reduce the design weight of the single machine, reduce the design weight of the payload, and thus reduce the overall structural design weight of the device.

[0034] S3: Optimize the ground testing process. After the payload completes the basic mechanical environment qualification test at the single-unit level, directly conduct the ground environment test at the whole-device level, shortening the development cycle and reducing costs.

[0035] Step S3 specifically includes: During ground testing, after completing its basic mechanical environment qualification test at the unit level, the payload directly conducts various mechanical environment tests on the platform-payload assembly, shortening the development and testing time and reducing development costs. After completing their respective qualification tests, each unit of the payload participates in the assembly-level mechanical environment test along with the assembly, optimizing the entire aircraft development process, accelerating the development progress, and saving development funds.

[0036] Step S3 also includes: The conventional process requires each individual payload to undergo its own mechanical tests, followed by subsystem-level mechanical environment tests along with each payload. Since the mechanical boundaries differ significantly from those on the actual aircraft, ground tests may result in overtesting, increasing the development cycle, time, and costs. If problems are found during the aircraft-level testing, i.e., the test fails, the process returns to step S1 or S2 for redesign. By rationally extracting the mechanical environment conditions of individual payloads, after each payload completes its relevant qualification-level mechanical tests, it can directly undergo relevant mechanical testing verification along with the entire aircraft, accelerating the development speed and optimizing the entire aircraft development process. This avoids the overtesting, multiple rounds of iterative design, and additional development process steps and testing costs caused by the ground test boundary impedance of each payload exceeding the actual aircraft state, which is common in traditional processes.

[0037] In this embodiment, step S3 involves whole-system level testing and verification. After completing their respective qualification tests, each individual payload component can participate in whole-system level mechanical environment testing along with the entire system. This optimizes the entire aircraft development process, accelerates the development progress, and saves development costs. In this embodiment, if each individual payload component passes its respective mechanical environment adaptability verification and structural strength verification, and the platform passes the structural strength verification, then whole-system level testing and verification can proceed. If problems are found during whole-system level testing and verification, i.e., the test fails, then it is necessary to return to step S1 or step S2 and redesign. In the traditional design process, each payload undergoes its own ground tests. The biggest drawback is that the mechanical boundaries cannot be consistent with the actual flight conditions. The mechanical boundary impedance of the ground tests is much greater than that of the actual on-board conditions. This leads to significant over-testing issues in the ground mechanical tests, and in severe cases, it can lead to multiple rounds of iterative design for each payload and its individual components. It also increases the corresponding development process steps and testing costs, seriously restricting the progress of development, especially in the current environment of tight aircraft development schedules, where it is necessary to improve the overall development speed. By rationally extracting the mechanical environment conditions of the payload unit, after the unit completes the relevant qualification-level mechanical tests, it can be directly subjected to relevant mechanical tests and verifications along with the whole aircraft, which greatly accelerates the relevant development speed and optimizes the entire aircraft development process.

[0038] The integrated aircraft design method based on mechanical load and mechanical environment optimization described in this invention has been successfully applied to the development of a certain aircraft, providing an important reference for reducing structural design weight and improving the design of effective load environmental conditions.

[0039] Second Embodiment This embodiment provides a mechanical load and mechanical environment-based aircraft design system for executing the mechanical load and mechanical environment-based aircraft design method as described in the first embodiment, comprising: The fundamental frequency design module is used for overall fundamental frequency design. By establishing an overall joint analysis model of the platform and the payload and optimizing stiffness and layout, the overall fundamental frequency is increased while reducing the overall mass. The load environment module is used for integrated design of load and mechanical environment conditions. Based on the rocket interface conditions provided by the launch system, it directly obtains the mechanical environment conditions and mechanical load conditions at each position of the effective load from the whole model, eliminating artificial boundaries to avoid multiple accumulations of safety margin. The test optimization module is used to optimize the ground test process, allowing the entire device to be tested directly after the payload has completed the basic mechanical environment qualification test at the single-unit level, thus shortening the development cycle and reducing costs.

[0040] A computer-readable storage medium stores computer code that, when executed, performs the methods described above. Those skilled in the art will understand that all or part of the steps in the various methods of the above embodiments can be implemented by a program instructing related hardware. This program can be stored in a computer-readable storage medium, which may include: read-only memory (ROM), random access memory (RAM), a magnetic disk, or an optical disk, etc.

[0041] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

[0042] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0043] It should be noted that the above embodiments can be freely combined as needed. The above description is only a preferred embodiment of the present invention. It should be pointed out that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. An aircraft design method based on mechanical loads and mechanical environment, characterized in that, Includes the following steps: S1: Perform overall fundamental frequency design. By establishing an overall joint analysis model of the platform and the payload and optimizing stiffness and layout, the overall fundamental frequency can be improved while reducing the overall mass. S2: Perform integrated design of load and mechanical environment conditions. Based on the interface conditions of the rocket provided by the launch system, directly obtain the mechanical environment conditions and mechanical load conditions of each position of the effective load from the whole model, and eliminate artificial boundaries to avoid multiple accumulations of safety margin. S3: Optimize the ground testing process. After the payload completes the basic mechanical environment qualification test at the single-unit level, directly conduct the ground environment test at the whole-device level, shortening the development cycle and reducing costs.

2. The aircraft design method based on mechanical load and mechanical environment according to claim 1, characterized in that, Step S1 specifically includes: Based on the requirements of the launch frequency index, an integrated fundamental frequency design is proposed for the platform-payload integrated system. At the same time, a joint analysis model of the platform and payload is established, eliminating the need for a separate fundamental frequency requirement for the payload. The flexibility of the platform, the flexibility of the payload, and the stiffness characteristics of the platform-payload connection surface are fully considered to reduce stiffness discontinuities caused by interface decomposition. This approach aims to reduce the overall mass of the aircraft while maximizing the overall fundamental frequency.

3. The aircraft design method based on mechanical load and mechanical environment according to claim 1, characterized in that, Step S1 also includes: By combining integrated structure and layout optimization, the overall mass of the aircraft is reduced while the fundamental frequency of the aircraft is increased; after the payload design is completed, an integrated dynamic analysis model is directly constructed with the platform to give the modal frequencies of the entire aircraft, thereby answering the requirements of the launch vehicle. Based on the lateral and longitudinal fundamental frequency requirements provided in the launch vehicle user manual, the overall lateral and longitudinal modal frequencies of the spacecraft platform-payload assembly are designed to meet launch requirements. Frequency design requirements are only proposed for the entire spacecraft, without separately proposing frequency requirements for each payload. The payload dynamics model and the platform model are integrated into a unified model to obtain the natural frequencies and mode shapes of the unified model, which are then used as the design parameters for the spacecraft. If the frequency parameters of the unified model do not meet the requirements, the platform and payload are redesigned, and the stiffness of weak points is improved until the combined model meets the frequency parameters required for launch. This effectively reduces the difficulties caused by fundamental frequency design for various complex payloads and effectively reduces structural weight.

4. The aircraft design method based on mechanical load and mechanical environment according to claim 1, characterized in that, Step S2 specifically includes: Based on the mechanical environment conditions of the rocket-device interface provided by the launch system, the effective load and mechanical environment conditions of each individual unit are obtained directly from the platform-payload assembly model, eliminating the artificial dividing boundary between the platform and the payload, realizing direct transfer from the whole system to the individual units, and avoiding multiple accumulations of safety margins. The integrated analysis model directly provides the mechanical environment conditions and mechanical load conditions at each position of the payload, where the mechanical environment conditions are used for the design of the payload, and the mechanical loads are used for the structural strength design of the platform and the payload. Based on the mechanical input conditions of the rocket-device interface provided by the launch system, the load and mechanical environment conditions of each individual unit are obtained directly from the platform-payload assembly model, eliminating the artificial boundary between the platform and the payload, and carrying out joint design in aspects including mechanical loads and environmental conditions, realizing direct transfer from the whole system to the individual units, and avoiding multiple accumulations of safety margins.

5. The aircraft design method based on mechanical load and mechanical environment according to claim 1, characterized in that, Step S2 also includes: In general design, after the mechanical environmental conditions are given to each payload in the overall design, each payload will undergo relevant environmental tests. Because the mechanical impedance of its boundary is inconsistent with the actual state, the amplification caused by each payload during environmental tests is much greater than the actual state on the whole device. This will cause each payload to strengthen the structure, resulting in additional weight and cost. Response analysis is performed on the platform-payload assembly under various given excitations to obtain the mechanical environment conditions and mechanical load indicators of the payload, and related design and verification are carried out. If the payload and platform cannot be completed or the cost is too high, the platform and payload are redesigned and the process returns to step S1. Based on the integrated analysis model, the mechanical environment conditions and mechanical load conditions of each payload are directly given, and the single-machine dynamics calculation results are optimized to make them closer to the actual state of the product, and to minimize the layer amplification and layer accumulation caused by artificially dividing the interface.

6. The aircraft design method based on mechanical load and mechanical environment according to claim 1, characterized in that, Step S3 specifically includes: During ground testing, after completing its basic mechanical environment qualification test at the unit level, the payload directly conducts various mechanical environment tests on the platform-payload assembly, shortening the development and testing time and reducing development costs. After completing their respective qualification tests, each unit of the payload participates in the assembly-level mechanical environment test along with the assembly, optimizing the entire aircraft development process, accelerating the development progress, and saving development funds.

7. The aircraft design method based on mechanical load and mechanical environment according to claim 1, characterized in that, Step S3 also includes: The conventional process requires each individual payload to undergo its own mechanical tests, followed by subsystem-level mechanical environment tests along with each payload. Since the mechanical boundaries differ significantly from those on the actual aircraft, ground tests may result in overtesting, increasing the development cycle, time, and costs. If problems are found during the aircraft-level testing, i.e., the test fails, the process returns to step S1 or S2 for redesign. By rationally extracting the mechanical environment conditions of individual payloads, after each payload completes its relevant qualification-level mechanical tests, it can directly undergo relevant mechanical testing verification along with the entire aircraft, accelerating the development speed and optimizing the entire aircraft development process. This avoids the overtesting, multiple rounds of iterative design, and additional development process steps and testing costs caused by the ground test boundary impedance of each payload exceeding the actual aircraft state, which is common in traditional processes.

8. A mechanical load and mechanical environment-based aircraft design system for executing the aircraft design method based on mechanical load and mechanical environment as described in any one of claims 1-7, characterized in that, include: The fundamental frequency design module is used for overall fundamental frequency design. By establishing an overall joint analysis model of the platform and the payload and optimizing stiffness and layout, the overall fundamental frequency is increased while reducing the overall mass. The load environment module is used for integrated design of load and mechanical environment conditions. Based on the rocket interface conditions provided by the launch system, it directly obtains the mechanical environment conditions and mechanical load conditions at each position of the effective load from the whole model, eliminating artificial boundaries to avoid multiple accumulations of safety margin. The test optimization module is used to optimize the ground test process, allowing the entire device to be tested directly after the payload has completed the basic mechanical environment qualification test at the single-unit level, thus shortening the development cycle and reducing costs.

9. A computer device, characterized in that, The device includes a memory and one or more processors, wherein the memory stores computer code that, when executed by the one or more processors, causes the one or more processors to perform the method as described in any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer code, and when the computer code is executed, the method as described in any one of claims 1 to 7 is performed.

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