Adaptive vibration reduction method and system for launch system based on modal anti-node positioning

Abstract

The application discloses a launch system adaptive vibration reduction method and system based on modal anti-node positioning, and relates to the technical field of mechanical system vibration suppression.The application provides a system, which comprises the following steps: firstly, acquiring excitation force time domain signals under different set working conditions and ground boundary conditions and converting the signals into frequency domain to extract peak frequencies; then, performing modal analysis on a main structure of the launch system, and accurately positioning spatial modal anti-nodes of displacement amplitude maximum positions according to modal shapes; finally, arranging an adaptive vibration reduction device at the anti-node positions, and dynamically adjusting equivalent stiffness or damping of the device to perform matching tuning according to a real-time collected excitation response.The application arranges the vibration reduction device at a position with the highest energy consumption efficiency and assists with dynamic adjustment, so that the stability of the launch system is realized with a small system weight cost.

Description

Technical Field

[0001] This invention relates to the field of dynamic control of weapon launch platforms and vibration suppression technology of mechanical systems, and particularly to an adaptive vibration reduction method and system for launch systems based on modal anti-node positioning. Background Technology

[0002] The firing accuracy of a launch system (such as artillery or vehicle-mounted missile launch platforms) is one of the core indicators for evaluating its performance. At the moment of launch, the work done by the propellant gases and the movement of the projectile generate a huge instantaneous impact load (i.e., recoil). This broadband, high-energy impact excitation causes complex elastic vibrations in the load-bearing structures such as the launch pad, cradle, and base. This persistent structural residual vibration after launch can cause microscopic dynamic deviations in the barrel's orientation, affecting the density and accuracy of impact points in continuous fire.

[0003] To suppress such vibrations, traditional engineering solutions mainly focus on the following two directions:

[0004] The first approach is passive vibration suppression based on structural reinforcement. This involves identifying stress concentration areas or areas of excessive deformation through finite element analysis and improving the structure's impact resistance by adding stiffeners or thickening the walls. However, simply increasing stiffness leads to a significant increase in structural weight, affecting the launch system's maneuverability. Furthermore, this method only changes the structure's natural frequency and has limited ability to dissipate residual elastic vibrations within the system.

[0005] The second approach involves adding passive vibration damping devices to the structure, such as rubber damping pads or dynamic vibration absorbers with fixed parameters. However, in actual operating environments, the boundary conditions of the launching system are highly time-varying and complex. Changes in firing parameters (firing angle and azimuth angle) can lead to changes in the system's spatial mass and stiffness distribution; while differences in ground conditions (such as rigid concrete or soft mud) can cause extremely significant changes in foundation impedance. These factors cause the actual excitation force spectrum of the system to drift. The optimal operating frequency of traditional passive vibration dampers is fixed, and when faced with the above-mentioned changes in operating conditions, they are prone to reduced vibration damping effect or even failure due to frequency mismatch. In addition, the arrangement of vibration damping devices in existing technologies often relies on empirical settings and fails to fully incorporate the vibration energy distribution law of the structure, resulting in low energy absorption efficiency.

[0006] In summary, existing technologies lack a systematic solution that can effectively adapt to the dominant excitation characteristics under varying working conditions while strictly controlling the system weight, and can scientifically arrange and dynamically adjust the most sensitive areas of structural dynamics. Summary of the Invention

[0007] To address the shortcomings of existing technologies, such as simply increasing stiffness leading to increased weight, the inability of traditional passive vibration dampers to adapt to varying working conditions, and the lack of scientific quantitative analysis of the placement of vibration damping devices resulting in low energy absorption efficiency, this invention provides an adaptive vibration reduction method and system for a launch system based on modal anti-node positioning. The aim is to solve the technical problem of how to accurately locate and adaptively cancel transient impacts and structural residual vibrations under different environments and working conditions without significantly increasing the weight of the main system, thereby improving the stability of continuous firing.

[0008] To solve the above-mentioned technical problems, in a first aspect, the present invention provides the following technical solution:

[0009] An adaptive vibration reduction method for a launch system based on modal inverse node localization includes the following steps: acquiring the time-domain signal of the launch excitation force of the launch system under a set operating condition, and converting the time-domain signal of the launch excitation force into a frequency-domain signal to extract the peak frequency, wherein the peak frequency is the dominant frequency where the energy distribution is concentrated; performing modal analysis on the main structure of the launch system to obtain several natural frequencies and corresponding mode shapes of the main structure; for the natural frequency order that matches the peak frequency, determining the spatial location where the displacement amplitude reaches its maximum value according to the corresponding mode shape, and defining the spatial location as the modal inverse node; arranging an adaptive vibration reduction device at the modal inverse node of the main structure, and dynamically adjusting the dynamic parameters of the adaptive vibration reduction device according to the real-time acquired external excitation parameters during launch, so that the optimal vibration absorption frequency of the adaptive vibration reduction device matches the current external excitation parameters.

[0010] The adaptive vibration damping device is arranged at the modal inverse node of the main structure of the launching system. The modal inverse node is the spatial location where the displacement amplitude reaches its maximum value, determined according to the corresponding mode shape, for the natural frequency order of the main structure that matches the peak frequency of the excitation force where the energy distribution of the launching system is concentrated under a set operating condition. By employing a technique that integrates the frequency domain characteristic analysis of external loads with the dynamic characteristics of the internal structure, accurately locates the modal inverse node, and applies the adaptively adjusted vibration damping device, this invention can achieve precise and efficient vibration suppression. Because the modal inverse node is the region where the vibration displacement is maximum and the energy is most concentrated at that natural frequency, arranging a vibration absorption device at this location can effectively dissipate a large amount of vibration energy with relatively small working force; at the same time, the dynamic adjustment parameters allow the vibration damping system to adapt to changes in excitation frequency under different operating conditions and maintain optimal tuning.

[0011] As a preferred embodiment of the present invention, before acquiring the time-domain signal of the launch excitation force of the launch system under set operating conditions, a pre-optimization step is included: establishing a three-dimensional finite element model of the main structure; setting multiple sets of analysis conditions, which include the attitude combinations of the launch system under different rotation angles and different elevation angles; performing static strength analysis and deformation stiffness analysis under the multiple sets of analysis conditions respectively; when the maximum stress exceeds the allowable stress threshold or the maximum deformation displacement exceeds the set accuracy threshold, structural optimization is performed on the three-dimensional finite element model until the preset basic safety and mechanical performance conditions are met. By further adopting the pre-optimized multi-condition strength and stiffness optimization technology, the present invention can also improve the basic stability of the launch platform's main structure. This step constructs a reliable underlying mechanical platform for the safe operation of the system, avoids safety hazards caused by insufficient strength of the main load-bearing structure, and reserves reasonable operational margins for subsequent lightweight design and local efficient vibration reduction.

[0012] In a preferred embodiment of the present invention, the set operating conditions include variations in ground boundary conditions; the method for obtaining the time-domain signal of the launch excitation force includes: obtaining excitation force data by conducting launch tests on a physical prototype under different ground impedance boundary conditions; or, obtaining excitation force data by inputting the internal ballistic recoil curve as a load into a dynamic simulation system. By further employing measured or simulated calculation techniques that incorporate ground boundary condition variables, the present invention can also achieve broad-spectrum coverage of excitation data. It fully considers the influence of ground medium differences on the dynamic response of the coupled system, ensuring that the obtained dominant frequency characteristics are closer to the complex actual operating environment.

[0013] In a preferred embodiment of the present invention, the dynamic adjustment of the dynamic parameters of the adaptive vibration damping device based on the real-time acquired external excitation parameters includes: real-time acquisition of the current excitation force frequency or system vibration response signal by a sensor network arranged on the launching system; the control unit generating adjustment commands based on the excitation force frequency or system vibration response signal using an adaptive filtering algorithm, a fuzzy logic control algorithm, or a predictive control algorithm based on an artificial neural network; and the adaptive vibration damping device changing its internal equivalent stiffness coefficient or equivalent damping coefficient based on the adjustment commands to suppress the vibration energy transmitted to the main structure. By further employing the closed-loop feedback control technology of a sensor network based on advanced algorithms, the present invention can also achieve real-time tracking response to transient and non-stationary loads. This enables the actuator to continuously and smoothly output the corresponding anti-vibration impedance, keeping the system response in a convergent state.

[0014] As a preferred embodiment of the present invention, the adaptive vibration reduction device includes a hydraulic spring composite vibration absorber, a magnetorheological fluid damper, an electrorheological fluid damper, an electromagnetic active actuator, or a pneumatic adjustable spring. By further employing specific types of semi-active or fully active intelligent actuating elements, the present invention can also achieve efficient matching of vibrations of different frequency bands and magnitudes. The wide variety of actuator types expands the engineering applicability of the solution, allowing for flexible selection based on load requirements.

[0015] To solve the above-mentioned technical problems, in a second aspect, the present invention provides the following technical solution:

[0016] An adaptive vibration reduction system for a launch system includes: a signal processing module for acquiring the time-domain signal of the launch excitation force of the launch system under set operating conditions, and performing time-frequency domain conversion to extract the peak frequency of the concentrated energy distribution; a modal analysis and positioning module for analyzing and solving the main structure of the launch system to obtain the mode shape, and selecting the position coordinates of the inverse node of the mode with the largest displacement amplitude based on the mode shape; an adaptive vibration reduction device arranged at the position of the inverse node of the mode corresponding to the main structure, the adaptive vibration reduction device having adjustable stiffness or damping characteristics; and a control unit communicatively connected to the adaptive vibration reduction device for receiving real-time excitation signal characteristics under multiple operating conditions and outputting control commands to drive the adaptive vibration reduction device to perform real-time matching and tuning of dynamic parameters.

[0017] By employing a technique that organically integrates theoretical calculation modules, signal processing modules, and physical execution devices, this invention enables the realization of a complete intelligent closed-loop vibration reduction engineering system. It establishes a link from numerical simulation analysis to adaptive control of the physical entity, improving the overall response efficiency and disturbance rejection capability of the system.

[0018] As a preferred embodiment of the present invention, a pre-simulation optimization module is also included. This module stores a structural finite element solver, used to perform strength and stiffness analysis on the input attitude model containing different projection angles and azimuth angles. It iteratively modifies the structural parameters and outputs a main structural model that meets the fundamental mechanical requirements to the modal analysis and positioning module. By further employing a pre-simulation optimization module with an embedded finite element solver, the present invention can also achieve automated lightweight verification of the foundation bearing structure, assisting designers in obtaining a structural benchmark that balances stiffness and weight.

[0019] In a preferred embodiment of the present invention, the adaptive vibration damping device is a hydraulic spring vibration absorber, which integrates an electromagnetic proportional valve capable of changing the area of ​​the fluid flow throttling orifice or a servo drive mechanism capable of adjusting the spring preload, so as to steplessly adjust the mechanical impedance of the overall component according to the signal of the control unit. By further employing a hydraulic spring actuation structure with an electromagnetic proportional valve or servo drive mechanism, the present invention can also achieve reliable actuation power output under high load environments, especially meeting the damping and dissipation requirements of heavy launch platforms with huge instantaneous recoil.

[0020] In a preferred embodiment of the present invention, when there are complex excitations in multiple spatial dimensions, the modal analysis and positioning module outputs multiple position coordinates at inverse nodes of different local modes. The adaptive vibration reduction device consists of multiple independent actuators arranged in an array, each installed at one of the multiple inverse node positions. By further employing a multi-point arrayed distribution arrangement, the present invention can also achieve decoupled collaborative control for complex multi-order modes, effectively suppressing parasitic vibration components of the system in multiple spatial degrees of freedom.

[0021] In a preferred embodiment of the present invention, the system further includes a high-frequency accelerometer arranged on the launch system tube and base. The high-frequency accelerometer collects the system's micro-vibration response signal and inputs it as a negative feedback quantity to the control unit, thus forming a closed-loop vibration reduction control system. By further employing the technical feature of constructing a hardware closed loop using a high-frequency sensor, the present invention can also achieve real-time correction of theoretical matching errors, ensuring that the final output of the adaptive vibration reduction device can continuously and stably reduce the actual vibration level.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. Improved energy absorption efficiency of vibration damping devices: This invention, through theoretical analysis and calculation, transforms the installation location of vibration damping devices from traditional experience-based judgment to quantitative scientific optimization. Vibration damping devices arranged at modal inverse nodes (the points of maximum displacement and energy) can generate the maximum dissipation torque against harmful vibration modes with relatively minimal volume and energy consumption, thus improving the targeted nature of vibration damping design.

[0024] 2. Significantly improved adaptability to complex operating conditions: It solves the problem of reduced vibration suppression efficiency caused by frequency drift when fixed-parameter vibration dampers face changes in firing angle or different foundation impedance boundaries. The system can sense and automatically adjust mechanical impedance parameters in real time, maintaining the continuous firing stability of the weapon system under all operating conditions.

[0025] 3. Facilitates lightweighting of the main structure: Since the high-frequency vibrations and main residual vibrations of the system are dissipated at fixed points by the adaptive vibration damping device, the main frame design does not need to excessively increase wall thickness or weight to absorb this energy. While ensuring overall performance, it frees up space for structural optimization and effectively controls the overall mass of the platform. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of the embodiments disclosed in this invention, the accompanying drawings of the embodiments will be briefly described below. These drawings are for illustrative purposes only and are not intended to limit the scope of protection of this invention.

[0027] Figure 1 This is a flowchart illustrating an adaptive vibration reduction method for a launch system based on modal inverse node positioning provided by the present invention.

[0028] Figure 2 This is a schematic diagram of the hierarchical logical connection of functional modules of an adaptive vibration reduction system for a launch system provided by the present invention. Detailed Implementation

[0029] The technical solutions (including preferred technical solutions) of the present invention will be further described in detail below with reference to the accompanying drawings and by way of listing some optional embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0030] Example 1

[0031] This embodiment provides an adaptive vibration reduction method for a launch system based on modal inverse node localization, specifically covering the preferred method steps and details of the present invention. Please refer to... Figure 1 This method constructs a tight link from analysis to execution, mainly including the following steps:

[0032] In the early stages of system development and finalization, a preliminary optimization step is implemented. A three-dimensional finite element model of the main structure 10 of the launching system (e.g., the gun base and turntable assembly) is created using 3D modeling software. To cover actual service conditions, multiple sets of analysis scenarios are set, including different rotational azimuth angles of the main structure from 0 to 180 degrees, and attitude combinations from 0 to the maximum elevation angle. Static strength analysis and deformation stiffness analysis are performed under these scenarios. When the finite element calculation shows that the maximum stress of a local component exceeds the allowable stress threshold of the material, or the maximum deformation displacement in the firing axis exceeds the set accuracy threshold, structural optimization (such as local thickening or adjusting the layout of reinforcing ribs) is performed on the three-dimensional finite element model, iterating repeatedly until the preset basic safety and mechanical performance conditions are met.

[0033] Subsequently, time-frequency domain excitation force analysis is performed. During actual launches, ground conditions (such as rigid concrete or soft soil) significantly alter the foundation impedance. In this embodiment, the excitation force time-domain signal is obtained through live-fire tests using a physical prototype under different foundation impedance boundary conditions; alternatively, the recoil curve is calculated using internal ballistics theory and input as a dynamic load into the simulation system for calculation. After acquiring the time-domain signal, a Fast Fourier Transform (FFT) is performed to convert it into a frequency domain spectrum, and one or more dominant frequencies within the energy distribution concentration are identified and extracted, designated as peak frequencies.

[0034] Next, modal analysis and precise positioning are performed. Modal solutions are obtained for the optimized main structure 10 of the launch system, acquiring its first few natural frequencies and corresponding mode shapes. The system automatically optimizes to find the natural frequency order that best matches the extracted peak frequency values. For this matching order, its corresponding modal displacement contour map is extracted. In structural vibration mechanics, the spatial location where the displacement amplitude reaches its maximum value signifies the accumulation of the greatest deformation energy. This method precisely determines this spatial coordinate through an extraction algorithm and defines it as the modal inverse node.

[0035] Finally, adaptive vibration reduction is implemented. In the physical entity, the adaptive vibration reduction device 50 is directly arranged at the aforementioned determined modal inverse node position. In this embodiment, the adaptive vibration reduction device 50 is a hydraulic spring composite vibration absorber. During the artillery firing phase, a sensor network (high-frequency acceleration sensor 40) arranged on the structure collects the current excitation force frequency or system vibration response signal in real time and transmits it to the control unit 60. The control unit 60 has a built-in adaptive filtering algorithm (such as the FXLMS algorithm) to quickly generate adjustment commands. This command drives the electromagnetic proportional valve inside the hydraulic spring composite vibration absorber to change the area of ​​the fluid flow throttling orifice (changing the equivalent damping coefficient), and simultaneously drives the servo mechanism to change the spring preload (changing the equivalent stiffness coefficient). By dynamically changing the stiffness and damping, the optimal vibration absorption frequency of the vibration reduction device is always precisely matched with the currently changing external excitation parameters, maximizing the dissipation of destructive residual vibration energy.

[0036] Example 2

[0037] This embodiment provides an adaptive vibration reduction system for a launch system, which integrates the hardware and software of the above method. Figure 2 The logical connections and data flow between the modules are shown.

[0038] The system's front-end design platform mainly comprises two parts: digital signal processing and physical actuation. The digital processing unit is equipped with a signal processing module 20 and a modal analysis and localization module 30. The signal processing module 20 primarily handles data reception and FFT time-frequency conversion to extract peak frequencies obtained from measurements or simulations. The modal analysis and localization module 30 possesses model space resolution capabilities. It receives the main structural model provided by the front-end simulation optimization module, which already meets the basic mechanical performance requirements, performs eigenvalue solving, and calculates the precise coordinates of the inverse nodes of the output spatial modes.

[0039] At the physical architecture level, the core actuator of the vibration damping system is the adaptive vibration damping device 50. Guided by the coordinates output by the modal analysis and positioning module 30, this device is mechanically fastened to the modal inverse node of the main structure 10 of the launch system. In this hardware architecture, the system further integrates a high-frequency acceleration sensor 40, which is placed on the key force transmission paths of the front section of the barrel, the cradle, or the base.

[0040] The control unit 60 receives the micro-vibration response signal from the high-frequency acceleration sensor 40 via a high-speed bus, forming a real-time negative feedback control loop. When the launch system's operational position is moved from hard, rigid ground to muddy ground with a certain buffering effect, the system's boundary impedance changes significantly, causing the excitation force's dominant frequency to drift. At this time, the control unit 60 can capture the change in response phase within milliseconds through the sensor network and automatically calculate a new control current based on a fuzzy logic control algorithm. This current is sent to the adaptive vibration damping device 50 at the modal inverse node, rapidly reshaping its impedance characteristics so that it can maintain optimal smooth vibration damping performance throughout the entire service life and under various variable operating conditions.

[0041] Example 3

[0042] When faced with large, multi-axial launch platforms that require wider bandwidth response and are more complex (such as shipborne missile vertical launch bases or heavy phased array radar bases), the physical actuators and layout schemes of this invention also have a high degree of scalability and applicability.

[0043] In large and complex structures, external impact loads often excite complex vibrations in multiple spatial dimensions, such as torsion and bending. In this scenario, the modal analysis and localization module 30 in this system extracts and outputs the position coordinates of multiple anti-nodes of different local modes after solving the problem. To cope with this multi-degree-of-freedom coupled vibration, the adaptive vibration reduction device 50 in this embodiment adopts an array-distributed design, that is, multiple independent actuating units are installed at the positions of the aforementioned multiple anti-nodes of local modes.

[0044] Meanwhile, this embodiment replaces the actuator itself with an equivalent one to meet the requirements of ultra-fast response for high-frequency, small-stroke applications. The arrayed adaptive vibration damping device 50 can be a magnetorheological fluid damper or a piezoelectric ceramic actuator. The control unit 60 adopts a MIMO (Multiple Input Multiple Output) predictive control strategy based on an artificial neural network to coordinate the arrayed actuators. Specifically, the input of the artificial neural network receives real-time spatial vibration response signals collected by a multi-point sensor network and the current angle of incidence and azimuth parameters of the system. It performs feature extraction and temporal inference through an internally pre-trained model network, and its output calculates the control commands corresponding to each independent actuator in parallel. When multi-source vibration signals are received, the control unit allocates different control quantities according to the above output commands to instantaneously change the shear yield strength of each magnetorheological fluid damper, applying independent suppression forces of different directions and magnitudes to each anti-node, achieving precise vibration cancellation in the entire space and multiple dimensions, and significantly improving the overall working accuracy of the system.

[0045] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, several specific algorithm adjustments or equivalent substitutions for the selection of execution mechanisms can be made without departing from the spirit and principles of the present invention. These improvements and modifications based on this concept should also be considered within the scope of protection of the present invention.

Claims

1. An adaptive vibration reduction method for a launch system based on modal inverse node localization, characterized in that, Includes the following steps: The time-domain signal of the launch excitation force of the launch system under set operating conditions is obtained, and the time-domain signal of the launch excitation force is converted into a frequency-domain signal to extract the peak frequency, wherein the peak frequency is the dominant frequency of energy distribution concentration; Modal analysis was performed on the main structure of the launch system to obtain several natural frequencies and corresponding mode shapes of the main structure. For the natural frequency order that matches the peak frequency, the spatial location where the displacement amplitude reaches its maximum value is determined according to the corresponding mode shape, and this spatial location is defined as the modal inverse node; An adaptive vibration damping device is arranged at the modal inverse node of the main structure, and during the launch process, the dynamic parameters of the adaptive vibration damping device are dynamically adjusted according to the external excitation parameters acquired in real time, so that the optimal vibration absorption frequency of the adaptive vibration damping device matches the current external excitation parameters.

2. The method according to claim 1, characterized in that, Before acquiring the time-domain signal of the launch excitation force of the launch system under set operating conditions, a pre-optimization step is also included: Establish a three-dimensional finite element model of the main structure; Multiple sets of analysis conditions are set, and the analysis conditions include the attitude combinations of the launch system under different rotation angles and different elevation angles; Static strength analysis and deformation stiffness analysis are performed under the multiple sets of analysis conditions respectively. When the maximum stress exceeds the allowable stress threshold or the maximum deformation displacement exceeds the set accuracy threshold, the three-dimensional finite element model is structurally optimized until the preset basic safety and mechanical performance conditions are met.

3. The method according to claim 1, characterized in that, The set operating conditions include variations in ground boundary conditions; the method for obtaining the time-domain signal of the emission excitation force includes: Excitation force data is obtained by conducting launch tests on a physical prototype under different foundation impedance boundary conditions; or... The excitation force data is obtained by using the internal ballistic recoil curve as the load input to the dynamic simulation system.

4. The method according to claim 1, characterized in that, The dynamic adjustment of the dynamic parameters of the adaptive vibration damping device based on the real-time acquired external excitation parameters includes: The current excitation force frequency or system vibration response signal is collected in real time by a sensor network arranged on the launch system; The control unit generates adjustment commands based on the excitation force frequency or system vibration response signal, using an adaptive filtering algorithm, a fuzzy logic control algorithm, or a predictive control algorithm based on an artificial neural network. The adaptive vibration reduction device changes its internal equivalent stiffness coefficient or equivalent damping coefficient based on the adjustment command in order to suppress the vibration energy transmitted to the main structure.

5. The method according to claim 4, characterized in that, The adaptive vibration reduction device includes a hydraulic spring composite vibration absorber, a magnetorheological fluid damper, an electrorheological fluid damper, an electromagnetic active actuator, or a pneumatic adjustable spring.

6. An adaptive vibration reduction system for a launch system, characterized in that, include: The signal processing module is used to acquire the time-domain signal of the transmission excitation force of the transmission system under the set operating conditions, and to perform time-frequency domain transformation to extract the peak frequency of the energy distribution concentration; The modal analysis and positioning module is used to analyze and solve the main structure of the launch system to obtain the mode shapes, and to select the position coordinates of the inverse node of the mode with the largest displacement amplitude based on the mode shapes; An adaptive vibration damping device is arranged at the position of the modal inverse node corresponding to the main structure. The adaptive vibration damping device has adjustable stiffness or damping characteristics. The control unit is communicatively connected to the adaptive vibration damping device, and is used to receive real-time excitation signal characteristics under multiple working conditions, and output control commands to drive the adaptive vibration damping device to perform real-time matching and tuning of dynamic parameters.

7. The system according to claim 6, characterized in that, It also includes a pre-simulation optimization module, which stores a structural finite element solver for performing strength and stiffness analysis on the input attitude model containing different projection angles and different azimuth angles, and outputs a main structure model that meets the mechanical requirements by iteratively modifying the structural parameters to the modal analysis and positioning module.

8. The system according to claim 6, characterized in that, The adaptive vibration damping device is a hydraulic spring vibration absorber, which integrates an electromagnetic proportional valve that can change the area of ​​the fluid flow throttling orifice or a servo drive mechanism that can adjust the spring preload, so as to adjust the mechanical impedance of the overall component according to the signal of the control unit.

9. The system according to claim 6, characterized in that, When there is complex excitation in multiple spatial dimensions, the modal analysis and localization module outputs multiple position coordinates of the anti-nodes of different local modes. The adaptive vibration reduction device consists of multiple independent actuators distributed in an array, which are respectively installed at the positions of the multiple anti-nodes of the modes.

10. The system according to claim 6, characterized in that, The system also includes a high-frequency acceleration sensor arranged on the tube and base of the launch system. The high-frequency acceleration sensor collects the system's micro-vibration response signal and inputs it as a negative feedback quantity into the control unit to form a closed-loop vibration reduction control system.

Images