Design method of single-machine mechanical environment test conditions for attitude control power system

Abstract

The application provides a kind of attitude control power system single machine mechanical environment test condition design method, including model stage, initial sample stage and positive sample stage, the mechanical response of each single machine support pasted vibration sensor position node in the mechanical environment prediction process is analyzed respectively in each stage;The mechanical response of each single machine support pasted vibration sensor position node in the mechanical environment prediction process is enveloped by using Matlab program;And compared with the data of last stage, the mechanical environment test condition of each single machine in this stage is formulated.The method used in the application runs through the whole stage of attitude control power system single machine development, improves the safety and reliability of attitude control power system single machine design;The mechanical response of single machine is enveloped by Matlab program, the mechanical environment test condition of single machine is formulated, the design time is saved, the single machine mechanical environment test condition design level is improved, and the design precision of single machine mechanical environment test condition is improved.

Description

Technical Field

[0001] This invention belongs to the field of attitude control power system testing technology, and specifically relates to a method for designing mechanical environment test conditions for a single attitude control power system. Background Technology

[0002] An attitude control system, also known as an attitude control system, is a system for controlling the attitude of an aircraft. Its basic task is to ensure good stability and maneuverability during free flight. The main function of the attitude control system is to maintain the aircraft's attitude stability during flight while implementing trajectory control commands generated by the navigation or guidance system. The attitude control system receives control information from two sources: first, information from attitude sensors, which arises when the aircraft's attitude deviates from its original state due to disturbances. This attitude sensor information is processed by the automatic stabilization device (controller) to generate control signals, which are then used by servo mechanisms to generate control forces. These control forces act on the aircraft body, returning it to its original attitude position, thus forming a negative feedback closed-loop control circuit to ensure attitude stability. The other source of control information comes from the navigation or guidance system, which provides guidance commands for maneuvering and turning.

[0003] To ensure the attitude control propulsion system can withstand potential mechanical environments, corresponding mechanical environment tests must be conducted at key stages of its development. These tests include sinusoidal vibration tests, impact tests, and random vibration tests. The test conditions directly determine the design performance of the attitude control propulsion system. Insufficiently low mechanical environment conditions will prevent effective verification of the system, failing to expose potential defects and potentially leading to flight defects. Conversely, excessively high conditions may render even a reasonable design unacceptable, while excessively high environmental conditions will increase the investment required for the system. Current technical solutions for designing mechanical environment test conditions lack sufficient precision, failing to reflect the actual mechanical loads during product operation. Furthermore, these designed test conditions are not implemented throughout the entire product development process, failing to expose potential breakage or failure under harsh dynamic conditions, thus increasing safety risks.

[0004] In order to fully expose the potential defects of the attitude control power system in ground mechanical environment tests and verify the rationality of the design, without causing structural damage, it is necessary to accurately design the mechanical environment test conditions of the attitude control power system. Summary of the Invention

[0005] The technical problem solved by this invention is to provide a design method for mechanical environment test conditions of a single machine for attitude control power system, which simulates real mechanical environment test loads and solves the problem that mechanical environment test conditions cannot be implemented throughout the entire product development process and increase the safety hazards of the product.

[0006] The technical solution adopted in this invention is: a method for designing test conditions for the mechanical environment of a single-machine attitude control power system, comprising the following steps:

[0007] Step 1: Prototype Stage;

[0008] Step 1.1 Establish a nonlinear model of the entire attitude control power system. Based on the mechanical environment test conditions of the overall input, apply mechanical environment excitation to the nonlinear model of the entire system to predict the mechanical environment.

[0009] Step 1.2: Analyze the mechanical response of the nodes at the locations where vibration sensors are attached to each individual bracket during the mechanical environment prediction process;

[0010] Step 1.3: Use Matlab to envelop the mechanical response of the nodes at the locations where vibration sensors are attached to each stand during the mechanical environment prediction process;

[0011] Step 1.4: Develop the mechanical environment test conditions for each unit during the prototype stage;

[0012] Step 2: Prototype Stage;

[0013] Step 2.1: Based on the overall input test sequence, the attitude control power system conducts a hot test and obtains the vibration data of the hot test.

[0014] Step 2.2: Analyze the vibration data of the hot-run test using the Matlab program to obtain the mechanical response of the vibration sensor positions of each single unit bracket during the hot-run test;

[0015] Step 2.3: Use Matlab to envelop the mechanical response of the vibration sensor locations on each individual support during the hot-run test;

[0016] Step 2.4: Develop the mechanical environment test conditions for each unit in the prototype stage;

[0017] Step 2.5: Compare the mechanical environment test conditions of each unit in the prototype stage, and adopt the larger mechanical environment test conditions as the mechanical environment test conditions for the final prototype stage of each unit.

[0018] Step 3: Prototype Development Stage;

[0019] Step 3.1: Conduct flight tests on the attitude control propulsion system and acquire vibration data from the flight tests;

[0020] Step 3.2: Analyze the vibration data from the flight test using the Matlab program to obtain the mechanical response of the vibration sensor positions attached to each individual support during the flight test;

[0021] Step 3.3: Use Matlab to envelop the mechanical response of the vibration sensor locations on each individual support during the flight test;

[0022] Step 3.4: Develop the mechanical environment test conditions for each unit during the prototype stage;

[0023] Step 3.5: Compare the mechanical environment test conditions of each unit in the prototype stage, and adopt the larger mechanical environment test conditions as the mechanical environment test conditions for the final prototype stage of each unit.

[0024] Preferably, the mechanical environment prediction in step 1 is performed using the commercial finite element software MSC.Nastran.

[0025] Preferably, the mechanical environment test conditions for the prototyping stage, the initial prototype stage, and the final prototype stage include sinusoidal vibration test conditions, impact test conditions, and random vibration test conditions.

[0026] Preferably, in the prototype stage, initial prototype stage, and final prototype stage, the rising slope and falling slope of the single-machine sinusoidal vibration and random vibration test conditions are determined based on the numerical values ​​of the envelope curves of sinusoidal vibration and random vibration response. Then, the rising spectrum, flat spectrum, and falling spectrum of the single-machine sinusoidal vibration and random vibration test conditions are designed based on the rising slope and falling slope of the single-machine sinusoidal vibration and random vibration test conditions, and the sinusoidal vibration and random vibration test conditions corresponding to the current test stage are formulated. A comparative analysis is then performed with the single-machine sinusoidal vibration and random vibration test conditions of the previous test stage to determine the energy... The larger values ​​represent the sinusoidal and random vibration test conditions in the final stage of single-machine testing. Then, based on the values ​​of the impact response envelope curve in the current test stage, the rising slope of the single-machine impact test conditions is determined. The rising spectrum and flat spectrum of the single-machine impact test conditions are designed based on the rising slope of the single-machine impact test conditions in the current test stage. The impact test conditions for the current stage of single-machine testing are formulated and compared with the single-machine impact test conditions of the previous test stage. The impact test conditions with larger energy are the impact test conditions for the final stage of single-machine testing. The above process is repeated until the impact test conditions for the prototype stage are determined.

[0027] The beneficial effects of this invention are:

[0028] 1. The mechanical environment prediction of the attitude control propulsion system, the vibration data of the attitude control propulsion system hot test, and the vibration data of the attitude control propulsion system flight test are used to analyze the sinusoidal vibration, impact, and random vibration response of the vibration sensor positions on the single-unit support of the attitude control propulsion system. This method runs through the entire development stage of the attitude control propulsion system single unit and improves the safety and reliability of the attitude control propulsion system single unit design.

[0029] 2. The response envelopes of sinusoidal vibration, impact, and random vibration at the sensor mounting position on the single-unit bracket were obtained by using the Matlab program. The mechanical environment test conditions for the single unit were established, which saved design time, improved the design level of the mechanical environment test conditions for the single unit, and enhanced the design accuracy of the mechanical environment test conditions for the single unit. Attached Figure Description

[0030] Figure 1 A flowchart illustrating the design method for single-machine mechanical environment test conditions of the invented attitude control power system.

[0031] Figure 2 This study describes the sinusoidal vibration response at the location of the vibration sensor attached to a single unit support during the mechanical environment prediction process of an attitude control power system, as well as the sinusoidal vibration test conditions during the prototype stage of a single unit.

[0032] Figure 3 This study describes the impact response at the location of the vibration sensor attached to a single unit bracket during the mechanical environment prediction process of an attitude control power system, as well as the impact test conditions during the prototype stage of a single unit.

[0033] Figure 4 This study describes the random vibration response at the location of the vibration sensor attached to a single unit bracket during the mechanical environment prediction process of an attitude control power system, as well as the random vibration test conditions during the prototype stage of a single unit.

[0034] Figure 5 This study describes the sinusoidal vibration response at the location of the vibration sensor attached to the bracket of a single unit during the hot test of the attitude control power system, as well as the sinusoidal vibration test conditions during the prototype stage of a single unit.

[0035] Figure 6 This study describes the impact response at the location of the vibration sensor attached to the bracket of a single unit during the hot test of the attitude control power system, as well as the impact test conditions during the prototype stage of a single unit.

[0036] Figure 7 This study describes the random vibration response at the location of the vibration sensor attached to the bracket of a single unit during the hot test of the attitude control power system, as well as the random vibration test conditions during the prototype stage of a single unit.

[0037] Figure 8 This study describes the sinusoidal vibration response at the location of the vibration sensor attached to the support of a single unit during flight testing of the attitude control power system, as well as the sinusoidal vibration test conditions during the prototype stage of a single unit.

[0038] Figure 9 This study describes the random vibration response at the location of the vibration sensor attached to the support of a single unit during flight testing of the attitude control power system, as well as the random vibration test conditions during the prototype stage of a single unit.

[0039] Figure 10 This study describes the impact response of a vibration sensor attached to a single unit's support structure during flight testing of the attitude control propulsion system, as well as the impact test conditions during the prototype stage of a single unit. Detailed Implementation

[0040] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0041] like Figures 1 to 10 As shown, a method for designing mechanical environment test conditions for a single unit of an attitude control propulsion system is carried out in three stages: prototype stage, preliminary prototype stage, and final prototype stage. The mechanical response of the vibration sensor positions on the single unit support is analyzed by using vibration data from the mechanical environment prediction of the attitude control propulsion system, the vibration data from the hot test of the attitude control propulsion system, and the vibration data from the flight test of the attitude control propulsion system. At the same time, the mechanical response of the vibration sensor positions on each single unit support is enveloped by the Matlab program to design the mechanical environment test conditions at different stages of the development of each single unit.

[0042] like Figure 1 As shown, the specific steps are as follows:

[0043] Step 1: Modeling Stage: such as Figures 2 to 4 As shown, a nonlinear model of the entire attitude control power system is established. Based on the sinusoidal vibration, shock and random vibration test conditions of the overall input, sinusoidal vibration, shock and random vibration loads are applied to the nonlinear model of the entire attitude control power system in MSC.Nastran software to predict the mechanical environment.

[0044] The sinusoidal vibration, impact, and random vibration responses of nodes at the sensor attachment locations on a single support during the mechanical environment prediction process of the attitude control dynamic system were analyzed.

[0045] The Matlab program was used to encapsulate the sinusoidal vibration, impact, and random vibration responses of nodes at the sensor locations on a single support during the mechanical environment prediction process of the attitude control dynamic system.

[0046] The rising and falling slopes of the single-machine sinusoidal vibration and random vibration test conditions are determined based on the numerical values ​​of the envelope curves of the sinusoidal and random vibration responses predicted by the mechanical environment.

[0047] By predicting the rising and falling slopes of the single-machine sinusoidal vibration and random vibration test conditions in the mechanical environment, the rising spectrum, flat spectrum, and falling spectrum of the single-machine sinusoidal vibration and random vibration test conditions are designed, and the sinusoidal vibration and random vibration test conditions of the single-machine prototype stage are formulated.

[0048] The ramp rate of the single-machine impact test conditions is determined based on the numerical value of the impact response envelope curve predicted by the mechanical environment.

[0049] By designing the rise slope of the single-machine impact test conditions in the mechanical environment prediction, the rise spectrum and flat spectrum of the single-machine impact test conditions are determined, and the impact test conditions for the single-machine prototype stage are formulated.

[0050] Step 2: Prototype Stage: such as Figures 5 to 7 As shown, the attitude control power system undergoes a hot test based on the overall input test sequence, and the vibration test data of the hot test is obtained.

[0051] The vibration data from the hot-run test were processed using the Matlab program, and the sinusoidal vibration, impact, and random vibration responses of the sensor positions on the single-unit bracket of the attitude control power system during the hot-run test were analyzed.

[0052] The envelope of sinusoidal vibration, shock, and random vibration responses at the sensor locations on a single support during a hot-roller test of the attitude control power system was determined using a Matlab program.

[0053] The rising and falling slopes of the single-machine sinusoidal vibration and random vibration test conditions are determined based on the numerical values ​​of the envelope curves of the sinusoidal and random vibration responses during the hot-run test.

[0054] By designing the rising and falling slopes of the single-unit sinusoidal vibration and random vibration test conditions during hot commissioning tests, the rising, flat, and falling spectra of the single-unit sinusoidal vibration and random vibration test conditions are determined, thus establishing the sinusoidal vibration and random vibration test conditions for the initial prototype stage of the single unit.

[0055] A comparative analysis of the single-machine sinusoidal vibration and random vibration test conditions at the prototype stage revealed that the sinusoidal vibration and random vibration test conditions at the final prototype stage of the single machine had higher energy levels.

[0056] The ramp rate of the single-machine impact test conditions is determined based on the numerical value of the impact response envelope curve during the hot-run test.

[0057] By designing the rise slope of the single-unit impact test conditions during hot commissioning, the rise spectrum and flat spectrum of the single-unit impact test conditions are determined, and the impact test conditions for the initial prototype stage of the single unit are established.

[0058] A comparative analysis of the single-unit impact test conditions at the prototype stage revealed that the impact test conditions at the final prototype stage had higher energy levels.

[0059] Step 3: Prototype Stage: such as Figures 8 to 10 As shown, the attitude control propulsion system underwent flight testing to obtain flight test vibration data.

[0060] The vibration data from the flight test were processed using a Matlab program to analyze the sinusoidal vibration, shock, and random vibration responses of the sensor positions on the single-unit support of the attitude control power system during the on-orbit process.

[0061] The envelope of sinusoidal vibration, shock, and random vibration responses at the sensor locations on a single support during flight tests of the attitude control propulsion system was determined using a Matlab program.

[0062] The rising and falling slopes of the single-aircraft sinusoidal vibration and random vibration test conditions are determined based on the numerical values ​​of the envelope curves of the sinusoidal and random vibration responses during flight tests.

[0063] By designing the rising and falling slopes of the single-aircraft sinusoidal vibration and random vibration test conditions during flight testing, the rising, level, and falling spectra of the single-aircraft sinusoidal vibration and random vibration test conditions are established, thus defining the sinusoidal vibration and random vibration test conditions for the single-aircraft prototype stage.

[0064] A comparative analysis of the single-machine sinusoidal vibration and random vibration test conditions in the prototype stage revealed that the conditions with higher energy were those in the final prototype stage.

[0065] The ramp rate of the single-aircraft impact test conditions is determined based on the values ​​of the impact response envelope curve during flight testing.

[0066] By designing the rise and flat spectrum of the single-aircraft impact test conditions based on the rise slope of the single-aircraft impact test conditions during flight testing, the impact test conditions for the single-aircraft prototype stage are formulated.

[0067] A comparative analysis of the single-unit impact test conditions at the prototype stage revealed that the impact test conditions at the final prototype stage had higher energy levels.

[0068] The above describes specific embodiments of the present invention and the technical principles employed. Any modifications or equivalent transformations based on the technical solutions of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for designing mechanical environment test conditions for a single-machine attitude control dynamic system, characterized in that, Includes the following steps: Step 1: Prototype Stage; Step 1.1 Establish a nonlinear model of the entire attitude control power system. Based on the mechanical environment test conditions of the overall input, apply mechanical environment excitation to the nonlinear model of the entire system to predict the mechanical environment. Step 1.2: Analyze the mechanical response of the nodes at the locations where vibration sensors are attached to each individual bracket during the mechanical environment prediction process; Step 1.3: Use Matlab to envelop the mechanical response of the nodes at the locations where vibration sensors are attached to each stand during the mechanical environment prediction process; Step 1.4: Develop the mechanical environment test conditions for each unit during the prototype stage; Step 2: Prototype Stage; Step 2.1: Based on the overall input test sequence, the attitude control power system conducts a hot test and obtains the vibration data of the hot test. Step 2.2: Analyze the vibration data of the hot-run test using the Matlab program to obtain the mechanical response of the vibration sensor positions of each single unit bracket during the hot-run test; Step 2.3: Use Matlab to envelop the mechanical response of the vibration sensor locations on each individual support during the hot-run test; Step 2.4: Develop the mechanical environment test conditions for each unit in the prototype stage; Step 2.5: Compare the mechanical environment test conditions of each unit in the prototype stage, and adopt the larger mechanical environment test conditions as the mechanical environment test conditions for the final prototype stage of each unit. Step 3: Prototype Development Stage; Step 3.1: Conduct flight tests on the attitude control propulsion system and acquire vibration data from the flight tests; Step 3.2: Analyze the vibration data from the flight test using the Matlab program to obtain the mechanical response of the vibration sensor positions attached to each individual support during the flight test; Step 3.3: Use Matlab to envelop the mechanical response of the vibration sensor locations on each individual support during the flight test; Step 3.4: Develop the mechanical environment test conditions for each unit during the prototype stage; Step 3.5: Compare the mechanical environment test conditions of each unit in the prototype stage, and adopt the larger mechanical environment test conditions as the mechanical environment test conditions for the final prototype stage of each unit. The prototype, initial prototype, and final prototype stages all determine the rising and falling slopes of the single-machine sinusoidal and random vibration test conditions based on the numerical values ​​of the sinusoidal and random vibration response envelope curves. Then, using these rising and falling slopes, the rising, flat, and falling spectra of the single-machine sinusoidal and random vibration test conditions are designed to establish the sinusoidal and random vibration test conditions for the current test stage. These conditions are then compared with the single-machine sinusoidal and random vibration test conditions from the previous test stage; the one with the higher energy is selected as the final sinusoidal and random vibration test condition for the current test stage. Next, the rising slope of the single-machine impact test conditions is determined based on the numerical values ​​of the impact response envelope curve in the current test stage. Using this rising slope, the rising and flat spectra of the single-machine impact test conditions are designed to establish the impact test conditions for the current test stage. These conditions are then compared with the single-machine impact test conditions from the previous test stage; the one with the higher energy is selected as the final impact test condition for the current test stage. This process is repeated until the impact test conditions for the final prototype stage are determined.

2. The method for designing single-machine mechanical environment test conditions for the attitude control power system according to claim 1, characterized in that: The mechanical environment prediction described in step 1 was performed using the commercial finite element software MSC.Nastran.

3. The method for designing single-machine mechanical environment test conditions for the attitude control power system according to claim 1, characterized in that: The mechanical environment test conditions for the prototype stage, initial prototype stage, and final prototype stage include sinusoidal vibration test conditions, impact test conditions, and random vibration test conditions.

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