An adaptive active vibration reduction system, method and application of an aviation remote sensing system

Abstract

The present invention belongs to the technical field of active vibration reduction equipment for aerial remote sensing, and discloses an adaptive active vibration reduction system, method and application of an aerial remote sensing system. The system comprises: a base is fixedly connected to a load through an upper plane, and a lower plane is fixedly connected to a vibration source, and the vibration frequency of the vibration source to the load is reduced through relative micro-displacement of the upper plane and the lower plane; a micro-displacement detection system is installed on the base, and is used to detect the displacement states of the upper plane and the lower plane in real time respectively; a controller is used to receive the detection signal of the micro-displacement detection system, and send a control instruction to the power component after analysis and processing; the power component is used to output a waveform with the same frequency and opposite acceleration direction as the vibration source according to the control instruction of the controller, and perform relative movement of the upper plane and the lower plane of the base 1 to reduce the vibration frequency of the vibration source to the load. The purpose of the present invention is to reduce the influence of micro-vibration on photoelectric instruments, accurately suppress micro-vibration, and improve system accuracy.

Description

Technical Field

[0001] The present invention belongs to the technical field of active vibration reduction equipment for aviation remote sensing, and in particular relates to an adaptive active vibration reduction system, method and application of an aviation remote sensing system. Background Art

[0002] As a space exploration technology, aerial remote sensing technology has become one of the fastest-growing disciplines at the beginning of this century. Aerial remote sensing technology is an important technical means to obtain ground information and is widely used in many fields such as topographic mapping, resource exploration, disaster monitoring, weather forecasting, military reconnaissance, etc. Among them, the vibration reduction system, as one of the important components of the aerial remote sensing system, mainly isolates the vibration interference of the photoelectric instrument through active and passive vibration reduction, and improves the detection accuracy of the photoelectric instrument.

[0003] Detection accuracy is one of the most important performance indicators of optoelectronic instruments in airborne remote sensing systems. During operation, airborne remote sensing equipment is affected by a variety of complex factors, such as external wind resistance, internal optoelectronic load movement, carrier movement, and carrier vibration. Among them, carrier vibration is one of the factors that has a more serious impact on the optical performance of optoelectronic instruments. During the movement of the carrier, there are airflow vibrations, engine vibrations, and resonance, which will cause continuous tiny displacements and deformations inside or between the optical elements of the optical system of the optoelectronic instrument, resulting in jitter and deviation in the direction of the visual axis, affecting the detection accuracy. Therefore, a vibration reduction platform is needed to isolate the vibration to suppress the impact of vibration on the optical elements.

[0004] In order to improve the detection quality of aerial remote sensing systems, domestic and foreign scholars have used vibration reduction platforms to isolate vibrations of different frequency bands and amplitudes by active or passive vibration isolation. They have used distributed parameter vibration systems, discrete vibration systems, random vibration systems, etc. to describe aerial remote sensing vibration systems, and used adaptive control, fuzzy control and other control methods to achieve vibration suppression. They have good vibration reduction effects for vibrations within a fixed frequency and amplitude range, but they also have limitations in control range and control methods. Researching the mechanical structure and control strategy of vibration reduction platforms that are suitable for aerial remote sensing systems and improving the vibration reduction effect of vibration reduction platforms are the prerequisites for ensuring the reliability of optoelectronic instruments in aerial remote sensing systems. It is of great significance to analyze the source of vibration, understand the causes of vibration, and study how to reduce, suppress or compensate for the impact of vibration on detection accuracy. This also makes aerial remote sensing vibration reduction technology one of the important research directions of aerial remote sensing systems.

[0005] Through the above analysis, the problems and defects of the prior art are as follows:

[0006] (1) In the prior art, the vibrations to which aerial remote sensing systems are subjected cause the accuracy of optoelectronic instruments to decrease.

[0007] (2) In the prior art, it is not possible to reduce the impact of the gap caused by parts assembly on the platform vibration reduction effect.

[0008] (3) In the prior art, the response speed is slow and the output force is small during vibration reduction, resulting in a relatively poor vibration reduction effect. Summary of the invention

[0009] In order to overcome the problems existing in the related art, the disclosed embodiments of the present invention provide an adaptive active vibration reduction system, method and application of an aviation remote sensing system. The purpose of the present invention is to reduce the influence of micro-vibration on optoelectronic instruments, accurately suppress micro-vibration and improve system accuracy.

[0010] The technical solution is as follows: An adaptive active vibration reduction system for an aviation remote sensing system comprises:

[0011] The base is fixedly connected to the load through the upper plane, and the lower plane is fixedly connected to the vibration source. The vibration frequency of the vibration source on the load is reduced through the relative micro displacement of the upper plane and the lower plane;

[0012] A micro-displacement detection system is installed on the base and is used to detect the displacement states of the upper plane and the lower plane in real time;

[0013] A controller is connected to the micro-displacement detection system, and is used to receive detection signals from the micro-displacement detection system, and send control instructions to the power component after analysis and processing;

[0014] The power component is installed on the base and is used to output a waveform with the same frequency and opposite acceleration direction as the vibration source according to the control instructions of the controller, so as to make the upper and lower planes of the base move relative to each other and reduce the vibration frequency of the vibration source on the load.

[0015] In one embodiment, the base is an integrated design, and the base includes a base lower end platform and a base upper end platform;

[0016] The micro-displacement detection system includes: an acceleration sensor and a displacement sensor; the acceleration sensor includes a lower platform acceleration sensor and an upper platform acceleration sensor; the lower platform acceleration sensor is used to measure vibration source data and provide real-time input signals to the controller; the upper platform acceleration sensor is used to measure vibration reduction effects and provide real-time feedback signals to the controller;

[0017] The upper platform of the base is evenly distributed with upper platform acceleration sensors; the lower platform of the base is evenly distributed with lower platform acceleration sensors; the displacement sensor is used for real-time feedback of the distance between the upper platform of the base and the lower platform of the base.

[0018] In one embodiment, the power assembly includes: a piezoelectric ceramic actuator top cover, a gasket, and an adjustment screw;

[0019] The piezoelectric ceramic actuator is tightly fitted with the lower platform of the base and the upper platform of the base through the top cover, the gasket and the adjusting screw.

[0020] In one embodiment, the piezoelectric ceramic actuator is tightly attached to the inner wall of the base groove.

[0021] In one embodiment, flexible hinge structures are connected to both sides of the shell of the power component; the flexible hinge structures are tightly fitted with the upper plane and the lower plane of the base respectively; the relative micro-displacement of the upper plane and the lower plane of the base is achieved through the elastic deformation of the flexible hinge structure and different shapes and sizes; the upper plane includes the upper end platform of the base; the lower plane includes the lower end platform of the base.

[0022] Another object of the present invention is to provide an adaptive active vibration reduction system control method for an aviation remote sensing system, comprising the following steps:

[0023] S1, when the external vibration source generates vibration, the lower platform acceleration sensor of the lower platform of the base collects the vibration signal;

[0024] S2, after analysis and processing, the controller is input in real time, the controller receives the vibration signal and outputs a control signal to the piezoelectric ceramic actuator; the driver realizes the two-level voltage change of the piezoelectric ceramic actuator, so that the piezoelectric ceramic actuator outputs a waveform with the same frequency and opposite acceleration direction as the vibration source, realizes the relative movement of the lower platform of the base and the upper platform of the base, and reduces the vibration frequency of the upper platform of the base caused by the vibration of the lower platform of the base;

[0025] S3, when linear vibration and angular vibration are generated by the outside world, the lower platform acceleration sensor collects the vibration signal as the system input, and the upper platform acceleration sensor outputs the angle change data of the upper platform of the base, and adjusts the angle change value through the controller to compensate for the linear vibration and angular vibration generated by the outside world in the form of angular motion.

[0026] Another object of the present invention is to provide an adaptive active vibration reduction device for an aerial remote sensing system for terrain mapping, wherein the adaptive active vibration reduction device for an aerial remote sensing system for terrain mapping is equipped with the adaptive active vibration reduction system of the aerial remote sensing system.

[0027] Another object of the present invention is to provide an adaptive active vibration reduction device for an aerial remote sensing system for resource exploration, wherein the adaptive active vibration reduction device for an aerial remote sensing system for resource exploration is equipped with the adaptive active vibration reduction system of the aerial remote sensing system.

[0028] Another object of the present invention is to provide an adaptive active vibration reduction device for an aviation remote sensing system for disaster monitoring, wherein the adaptive active vibration reduction device for an aviation remote sensing system for disaster monitoring is equipped with the adaptive active vibration reduction system of the aviation remote sensing system.

[0029] Another object of the present invention is to provide an adaptive active vibration reduction device for an aviation remote sensing system used for weather forecasting and military reconnaissance, wherein the adaptive active vibration reduction device for an aviation remote sensing system used for weather forecasting and military reconnaissance is equipped with the adaptive active vibration reduction system of the aviation remote sensing system.

[0030] Combining all the above technical solutions, the advantages and positive effects of the present invention are as follows:

[0031] First, in view of the technical problems existing in the above-mentioned prior art and the difficulty of solving the problems, the technical solutions to be protected by the present invention and the results and data during the research and development process are closely combined to analyze in detail and deeply how the technical solutions of the present invention solve the technical problems, and some creative technical effects brought about after solving the problems. The specific description is as follows:

[0032] The present invention reduces the impact of vibration on the optoelectronic instruments of the aviation remote sensing system, thereby improving the detection accuracy of the optoelectronic instruments. Compared with other vibration reduction platforms, the present invention adopts an integrated design, which greatly reduces the impact of the gap caused by the assembly of parts on the vibration reduction effect of the platform. At the same time, the piezoelectric ceramic actuator has the characteristics of high resolution, fast response speed, and large output force, which can meet the system's requirements for actuators in various vibration environments. The vibration reduction platform reduces the impact of vibration on the optoelectronic instruments, which greatly improves the detection results of the optoelectronic instruments.

[0033] The present invention utilizes a flexible hinge structure as a connecting structure for the upper and lower planes. Changing the shape and size of the flexible hinge can make the present invention applicable to various vibration conditions and have better adaptability and reliability.

[0034] The present invention improves the imaging quality of optoelectronic instruments. Taking an aerial camera as an example, the present invention makes the images taken by the aerial camera clearer and makes the images have a better modulation transfer function.

[0035] In the present invention, the piezoelectric ceramic actuator is connected to the upper platform of the base through the top cover, and is connected to the lower platform of the base through the gasket and the adjusting screw. By controlling the two-level voltage of the piezoelectric ceramic actuator, the actuator outputs a micro-displacement, actively reducing the impact of the lower platform on the upper platform when it is vibrated. The displacement sensor provides real-time feedback of the distance between the upper and lower platforms. The acceleration sensors evenly distributed on the lower platform are used to measure the vibration source data and provide real-time input signals to the control system; the acceleration sensors evenly distributed on the upper platform are used to measure the vibration reduction effect and provide real-time feedback signals to the control system. Real-time and accurate adjustment of vibration is achieved.

[0036] Second, considering the technical solution as a whole or from the perspective of the product, the technical effects and advantages of the technical solution to be protected by the present invention are described in detail as follows:

[0037] The present invention effectively suppresses the vibration of the bottom of the platform through displacement and acceleration sensors, piezoelectric ceramic actuators, and flexible hinge structures, so that the plane on the platform is less affected by the vibration and the carrier is precisely damped.

[0038] Third, as auxiliary evidence of the inventiveness of the claims of the present invention, it is also reflected in the following important aspects:

[0039] The invention has a small number of parts, is simple to prepare and has a low cost. It can improve the detection quality when applied to an aerial remote sensing system and has a high commercial value.

[0040] The present invention discloses for the first time a line of sight tracking method for comprehensively processing linear vibration and angular vibration, and for the first time applies a flexible hinge structure to a vibration reduction platform to realize the integration of the vibration reduction platform, thereby achieving precise vibration reduction of the optoelectronic load of the aviation remote sensing system.

[0041] The technical solution of the present invention solves the vibration problem through a line of sight tracking and positioning method, thereby achieving accurate vibration suppression of the optoelectronic load of an aviation remote sensing system. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and, together with the description, serve to explain the principles of the present disclosure.

[0043] Figure 1 is a block diagram of an adaptive active vibration reduction system of an aviation remote sensing system provided by an embodiment of the present invention;

[0044] Figure 2 Schematic diagram of the installation structure of the adaptive active vibration reduction system of the aviation remote sensing system provided by an embodiment of the present invention;

[0045] Figure 3 is a front view of an adaptive active vibration reduction system of an aviation remote sensing system provided by an embodiment of the present invention;

[0046] Figure 4 1 is a schematic diagram of the connection of a piezoelectric ceramic actuator of an adaptive active vibration reduction system of an aviation remote sensing system provided by an embodiment of the present invention;

[0047] Figure 5 is a flow chart of a method for controlling an adaptive active vibration reduction system of an aviation remote sensing system provided by an embodiment of the present invention;

[0048] Figure 6 is a stereoscopic diagram of an adaptive active vibration reduction system of an aviation remote sensing system provided by an embodiment of the present invention;

[0049] Figure 7 The embodiment of the present invention provides Figure 6 Side view of the adaptive active vibration reduction system of the aviation remote sensing system;

[0050] Figure 8 The embodiment of the present invention provides Figure 6 A magnified schematic diagram of the installation location of the piezoelectric ceramic actuator in the adaptive active vibration reduction system of the aviation remote sensing system;

[0051] In the figure: 1. base; 1a. lower platform of base; 1b. upper platform of base; 2. piezoelectric ceramic actuator; 3. acceleration sensor; 3a. lower platform acceleration sensor; 3b. upper platform acceleration sensor; 4. displacement sensor; 5. controller; 6. top cover; 7. gasket; 8. adjustment screw; 9. flexible hinge structure; 10. micro-displacement detection system; 11. power assembly. DETAILED DESCRIPTION

[0052] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the specific embodiments of the present invention are described in detail below in conjunction with the accompanying drawings. In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without violating the connotation of the present invention, so the present invention is not limited by the specific implementation disclosed below.

[0053] 1. Explanation of the embodiment:

[0054] like Figure 1 As shown, an embodiment of the present invention provides an adaptive active vibration reduction system for an aviation remote sensing system, comprising:

[0055] The base 1 is fixedly connected to the load through the upper plane, and the lower plane is fixedly connected to the vibration source. The vibration frequency of the vibration source on the load is reduced through the relative micro displacement of the upper plane and the lower plane;

[0056] The micro-displacement detection system 10 is installed on the base 1 and is used to detect the displacement states of the upper plane and the lower plane in real time respectively;

[0057] The controller 5 is connected to the micro-displacement detection system 10, and is used to receive the detection signal of the micro-displacement detection system 10, and send the control instruction to the power component 11 after analysis and processing;

[0058] The power assembly 11 is mounted on the base 1 and is used to output a waveform with the same frequency as the vibration source and opposite acceleration direction according to the control instructions of the controller 5, so as to make the upper plane and the lower plane of the base 1 move relative to each other and reduce the vibration frequency of the vibration source to the load.

[0059] In a preferred embodiment, the base 1 is an integrated design, and the base 1 includes a base lower end platform 1a and a base upper end platform 1b;

[0060] The micro-displacement detection system 10 includes: an acceleration sensor 3 and a displacement sensor 4; the acceleration sensor 3 includes a lower platform acceleration sensor 3a and an upper platform acceleration sensor 3b; the lower platform acceleration sensor 3a is used to measure vibration source data and provide a real-time input signal to the controller 5; the upper platform acceleration sensor 3b is used to measure the vibration reduction effect and provide a real-time feedback signal to the controller 5;

[0061] The upper platform 1b of the base is evenly distributed with upper platform acceleration sensors 3b; the lower platform 1a of the base is evenly distributed with lower platform acceleration sensors 3a; the displacement sensor 4 is used to provide real-time feedback on the distance between the upper platform 1b and the lower platform 1a of the base.

[0062] In a preferred embodiment, the power assembly 11 includes: a piezoelectric ceramic actuator 2, a top cover 6, a gasket 7 and an adjustment screw 8;

[0063] The piezoelectric ceramic actuator 2 is tightly fitted with the lower platform 1a and the upper platform 1b of the base through the top cover 6, the gasket 7 and the adjustment screw 8.

[0064] In a preferred embodiment, flexible hinge structures 9 are connected to both sides of the outer shell of the power component 11; the flexible hinge structure 9 is tightly fitted with the upper plane and the lower plane of the base 1 respectively; the relative micro-displacement of the upper plane and the lower plane of the base 1 is achieved through the elastic deformation of the flexible hinge structure 9 and the different shapes and sizes; the upper plane includes the upper end platform 1b of the base; the lower plane includes the lower end platform 1a of the base. Example

[0065] like Figure 2-Figure 4 As shown, an embodiment of the present invention provides an adaptive active vibration reduction system for an aviation remote sensing system, comprising a base 1, a piezoelectric ceramic actuator 2, an acceleration sensor 3, a displacement sensor 4, a controller 5, a top cover 6, a gasket 7, an adjustment screw 8, and a flexible hinge structure 9;

[0066] The base 1 is an integrated design, and the base 1 includes a base lower end platform 1a and a base upper end platform 1b;

[0067] The acceleration sensor 3 includes a lower platform acceleration sensor 3a and an upper platform acceleration sensor 3b;

[0068] The piezoelectric ceramic actuator 2 is tightly fitted with the lower platform 1a of the base and the upper platform 1b of the base through the top cover 6, the gasket 7 and the adjustment screw 8;

[0069] Preferably, the upper end of the piezoelectric ceramic actuator 2 of the power assembly 11 is connected to the top cover 6 and is connected to the upper platform 1b of the base through the top cover 6; the lower end of the piezoelectric ceramic actuator 2 is in contact with the gasket 7 and is connected to the lower platform 1a of the base through the adjusting screw 8.

[0070] In a preferred embodiment of the present invention, the piezoelectric ceramic actuator 2 is close to the inner wall of the groove of the base 1; the upper platform acceleration sensors 3b are evenly distributed on the lower platform 1a and the upper platform 1b of the base; the lower platform acceleration sensors 3a are evenly distributed on the lower platform 1a of the base;

[0071] Displacement sensors 4 are evenly distributed between the lower platform 1a of the base and the upper platform 1b of the base; the plane of the upper platform 1b of the base is fixedly connected to the load, and the plane of the lower platform 1a of the base is fixedly connected to the vibration source.

[0072] In a preferred embodiment of the present invention, the two-level voltage of the piezoelectric ceramic actuator 2 is controlled by the controller 5, so that the piezoelectric ceramic actuator 2 outputs a micro displacement, actively reducing the impact of the vibration of the lower platform 1a of the base on the table surface of the upper platform 1b of the base. The displacement sensor 4 is used to provide real-time feedback on the distance between the upper platform 1b of the base and the lower platform 1a of the base.

[0073] In a preferred embodiment of the present invention, the lower platform acceleration sensor 3a is used to measure vibration source data and provide real-time input signals to the controller 5;

[0074] The upper platform acceleration sensor 3b is used to measure the vibration reduction effect and provide a real-time feedback signal to the controller 5, thereby achieving real-time and accurate adjustment of the vibration.

[0075] In a preferred embodiment of the present invention, the piezoelectric ceramic actuator 2, the top cover 6, the gasket 7 and the adjustment screw 8 constitute a power assembly 11; the two sides of the housing of the power assembly 11 are connected with a flexible hinge structure 9; the flexible hinge structure 9 is tightly fitted with the lower end platform 1a of the base and the upper end platform 1b of the base respectively;

[0076] The relative micro displacement of the upper and lower planes of the integrated vibration reduction platform is achieved through the elastic deformation of the flexible hinge structure 9.

[0077] Through the technical solution provided by the above-mentioned embodiment of the present invention, the present invention adopts a piezoelectric ceramic actuator 2, which has extremely high displacement resolution, fast response speed, large output force, and high real-time control performance.

[0078] The relative micro displacement of the upper and lower planes of the integrated vibration reduction platform is achieved through the elastic deformation of the flexible hinge structure 9.

[0079] The displacement sensors 4 are used to measure the displacements of four points of the uniformly distributed base 1 to calculate the angular changes of the two degrees of freedom of the vibration reduction platform.

[0080] The lower platform acceleration sensor 3a collects vibration signals as input signals of the controller 5, and the upper platform acceleration sensor 3b outputs detection signals. The controller 5 is adjusted by the input signal and the output detection signal, so that the plane of the upper platform 1b of the base has good stability. Example

[0081] like Figure 5 As shown, an embodiment of the present invention provides an adaptive active vibration reduction system control method for an aviation remote sensing system, comprising the following steps:

[0082] Step 1, when an external vibration source generates vibration, the lower platform acceleration sensor 3a of the lower platform 1a of the base collects vibration signals;

[0083] Step 2, after analysis and processing, the signal is input to the controller 5 in real time, the controller 5 receives the vibration signal, and outputs a control signal to the piezoelectric ceramic actuator 2; the two-level voltage change of the piezoelectric ceramic actuator 2 is realized, so that the piezoelectric ceramic actuator 2 outputs a waveform with the same frequency as the vibration source and the opposite acceleration direction, thereby realizing the relative movement of the lower platform 1a of the base and the upper platform 1b of the base, and reducing the influence of the vibration of the lower platform 1a of the base on the upper platform 1b of the base.

[0084] Step 3, when linear vibration and angular vibration are generated by the outside world, the lower platform acceleration sensor 3a collects the vibration signal as the system input, and the upper platform acceleration sensor 3b outputs the angle change data of the upper platform 1b of the base, and adjusts the angle change value through the controller 5, so as to compensate for the linear vibration and angular vibration generated by the outside world in the form of angular motion, thereby improving the vibration resistance of the upper platform 1b of the base and the load.

[0085] For the vibration of the lower platform 1a of the base, the lower platform acceleration sensor 3a collects the vibration amplitude A and the vibration period T=2π / ω in real time, and extracts useful information through filter processing. At the same time, for only linear vibration, it is also necessary to collect the distance h between the carrier of the aviation remote sensing system and the target position, and the linear vibration displacement x=Asinωt is converted into angular vibration through Ɵ=arctan(x / h), and used together with the directly collected angular vibration as the system input. The influence of this converted comprehensive angular vibration on the optoelectronic instrument is controlled by the controller 5 at both ends of the piezoelectric ceramic actuator 2 The control of voltage U causes the piezoelectric ceramic actuator 2 to output force F=k1U+k2 (k1 and k2 are constants), and the relationship between the output force F and the displacement ΔX is k3=F / ΔX (k3 is a constant). The relationship between voltage U and displacement ΔX can be obtained, and the linear displacement ΔX is converted into angular motion through the platform structure, thereby achieving reverse cancellation of the system input angular vibration, reducing the vibration resistance of the upper platform 1b and the load of the base, and at the same time, the upper platform acceleration sensor 3b collects the angle change data of the upper platform 1b and feeds it back to the controller 5 to realize the control closed loop. Example

[0086] Such as 6- Figure 8As shown, the adaptive active vibration reduction system of the aviation remote sensing system provided by the embodiment of the present invention includes a base 1, a piezoelectric ceramic actuator 2, an acceleration sensor 3, a displacement sensor 4, a controller 5, a top cover 6, a gasket 7, and an adjustment screw 8. A flexible hinge structure 9;

[0087] The adaptive active vibration reduction system of the aviation remote sensing system provided in the embodiment 1 is different from the flexible hinge structure 9 in shape and size in the embodiment 1;

[0088] The base 1 is an integrated design, and the base 1 includes a base lower end platform 1a and a base upper end platform 1b;

[0089] The acceleration sensor 3 includes a lower platform acceleration sensor 3a and an upper platform acceleration sensor 3b;

[0090] The piezoelectric ceramic actuator 2 is tightly fitted with the lower platform 1a of the base and the upper platform 1b of the base through the top cover 6, the gasket 7 and the adjustment screw 8;

[0091] Preferably, the upper end of the piezoelectric ceramic actuator 2 of the power assembly 11 is connected to the top cover 6 and is connected to the upper platform 1b of the base through the top cover 6; the lower end of the piezoelectric ceramic actuator 2 is in contact with the gasket 7 and is connected to the lower platform 1a of the base through the adjusting screw 8.

[0092] In a preferred embodiment of the present invention, the piezoelectric ceramic actuator 2 is close to the inner wall of the groove of the base 1; the upper platform acceleration sensors 3b are evenly distributed on the lower platform 1a and the upper platform 1b of the base; the lower platform acceleration sensors 3a are evenly distributed on the lower platform 1a of the base;

[0093] Displacement sensors 4 are evenly distributed between the lower platform 1a of the base and the upper platform 1b of the base; the plane of the upper platform 1b of the base is fixedly connected to the load, and the plane of the lower platform 1a of the base is fixedly connected to the vibration source.

[0094] In a preferred embodiment of the present invention, the two-level voltage of the piezoelectric ceramic actuator 2 is controlled by the controller 5, so that the piezoelectric ceramic actuator 2 outputs a micro displacement, actively reducing the impact of the vibration of the lower platform 1a of the base on the table surface of the upper platform 1b of the base. The displacement sensor 4 is used to provide real-time feedback on the distance between the upper platform 1b of the base and the lower platform 1a of the base.

[0095] In a preferred embodiment of the present invention, the lower platform acceleration sensor 3a is used to measure vibration source data and provide real-time input signals to the controller 5;

[0096] The upper platform acceleration sensor 3b is used to measure the vibration reduction effect and provide a real-time feedback signal to the controller 5, thereby achieving real-time and accurate adjustment of the vibration.

[0097] In a preferred embodiment of the present invention, the piezoelectric ceramic actuator 2, the top cover 6, the gasket 7 and the adjustment screw 8 constitute a power assembly 11; the two sides of the housing of the power assembly 11 are connected with a flexible hinge structure 9; the flexible hinge structure 9 is tightly fitted with the lower end platform 1a of the base and the upper end platform 1b of the base respectively;

[0098] The relative micro displacement of the upper and lower planes of the integrated vibration reduction platform is achieved through the elastic deformation of the flexible hinge structure 9.

[0099] Through the technical solution provided by the above-mentioned embodiment of the present invention, the present invention adopts a piezoelectric ceramic actuator 2, which has extremely high displacement resolution, fast response speed, large output force, and high real-time control performance.

[0100] The displacement sensors 4 are used to measure the displacements of four points of the uniformly distributed base 1 to calculate the angular changes of the two degrees of freedom of the vibration reduction platform.

[0101] The lower platform acceleration sensor 3a collects vibration signals as input signals of the controller 5, and the upper platform acceleration sensor 3b outputs detection signals. The controller 5 is adjusted by the input signal and the output detection signal, so that the plane of the upper platform 1b of the base has good stability.

[0102] An embodiment of the present invention provides an adaptive active vibration reduction system control method for an aviation remote sensing system, comprising the following steps:

[0103] Step 1, when an external vibration source generates vibration, the lower platform acceleration sensor 3a of the lower platform 1a of the base collects vibration signals;

[0104] Step 2, after analysis and processing, the signal is input to the controller 5 in real time, the controller 5 receives the vibration signal and outputs a control signal to the piezoelectric ceramic actuator 2; the two-level voltage change of the piezoelectric ceramic actuator 2 is realized through the driver, so that the piezoelectric ceramic actuator 2 outputs a waveform with the same frequency as the vibration source and the opposite acceleration direction, thereby realizing the relative movement of the lower platform 1a of the base and the upper platform 1b of the base, and reducing the influence of the vibration of the lower platform 1a of the base on the upper platform 1b of the base.

[0105] Step 3, when linear vibration and angular vibration are generated by the outside world, the lower platform acceleration sensor 3a collects the vibration signal as the system input, and the upper platform acceleration sensor 3b outputs the angle change data of the upper platform 1b of the base, and adjusts the angle change value through the controller 5, so as to compensate for the linear vibration and angular vibration generated by the outside world in the form of angular motion, thereby improving the vibration resistance of the upper platform 1b of the base and the load.

[0106] In the above embodiments, the description of each embodiment has its own emphasis. For parts that are not described or recorded in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0107] Since the information interaction, execution process, etc. between the above-mentioned devices / units are based on the same concept as the method embodiment of the present invention, their specific functions and technical effects can be found in the method embodiment part and will not be repeated here.

[0108] Those skilled in the art can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional units and modules is used as an example for illustration. In practical applications, the above-mentioned function allocation can be completed by different functional units and modules as needed, that is, the internal structure of the device can be divided into different functional units or modules to complete all or part of the functions described above. The functional units and modules in the embodiment can be integrated into a processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The above-mentioned integrated unit can be implemented in the form of hardware or in the form of software functional units. In addition, the specific names of the functional units and modules are only for the convenience of distinguishing each other, and are not used to limit the scope of protection of the present invention. The specific working process of the units and modules in the above-mentioned system can refer to the corresponding process in the aforementioned method embodiment, which will not be repeated here.

[0109] 2. Application examples:

[0110] Application Examples

[0111] An embodiment of the present invention further provides a computer device, which includes: at least one processor, a memory, and a computer program stored in the memory and executable on the at least one processor, wherein the processor implements the steps in any of the above-mentioned method embodiments when executing the computer program.

[0112] An embodiment of the present invention further provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, the steps in the above-mentioned method embodiments can be implemented.

[0113] An embodiment of the present invention further provides an information data processing terminal, which, when executed on an electronic device, provides a user input interface to implement the steps in the above method embodiments. The information data processing terminal is not limited to mobile phones, computers, and switches.

[0114] An embodiment of the present invention further provides a server, which is used to provide a user input interface to implement the steps in the above method embodiments when executed on an electronic device.

[0115] An embodiment of the present invention provides a computer program product. When the computer program product runs on an electronic device, the electronic device can implement the steps in the above-mentioned method embodiments when executing the computer program product.

[0116] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the present invention implements all or part of the processes in the above-mentioned embodiment method, which can be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium. When the computer program is executed by the processor, the steps of the above-mentioned method embodiments can be implemented. Among them, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form. The computer-readable medium may at least include: any entity or device that can carry the computer program code to the camera device / terminal device, recording medium, computer memory, read-only memory (ROM), random access memory (RAM), electric carrier signal, telecommunication signal and software distribution medium. For example, a USB flash drive, a mobile hard disk, a disk or an optical disk.

[0117] III. Evidence of the relevant effects of the embodiments:

[0118] The present invention has made great progress in the research and application field of vibration reduction systems, abandoning the existing vibration reduction ideas, such as absorbing vibration, isolating vibration, eliminating vibration, etc., looking at the impact of vibration on the detection results of the aviation remote sensing system from a new perspective, combining external vibration parameters, the distance between the carrier and the target, etc., and comprehensively analyzing the impact of vibration on the line of sight of the optoelectronic instrument. From this perspective, in order to achieve the purpose of accurate positioning of the line of sight under vibration, a piezoelectric ceramic actuator 2 with high precision and fast response speed is used as a driving component to control the platform angular movement in real time to achieve the purpose of real-time tracking and positioning of the line of sight.

[0119] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any modifications, equivalent substitutions and improvements made by any technician familiar with the technical field within the technical scope disclosed by the present invention and within the spirit and principles of the present invention should be covered within the protection scope of the present invention.

Claims

1. An adaptive active vibration reduction control method for an aviation remote sensing system using an adaptive active vibration reduction system of an aviation remote sensing system, characterized in that: The adaptive active vibration reduction control method of the aviation remote sensing system comprises the following steps: S1, when an external vibration source generates vibration, a lower platform acceleration sensor (3a) of the lower platform (1a) of the base collects a vibration signal; S2, after analysis and processing, is input into the controller in real time, the controller (5) receives the vibration signal and outputs a control signal to the piezoelectric ceramic actuator (2); the driver realizes the two-level voltage change of the piezoelectric ceramic actuator 2, thereby causing the piezoelectric ceramic actuator (2) to output a waveform with the same frequency as the vibration source and the opposite acceleration direction, thereby realizing the relative movement of the base lower end platform (1a) and the base upper end platform (1b), and reducing the vibration frequency of the base upper end platform (1b) caused by the vibration of the base lower end platform (1a); S3, when linear vibration and angular vibration are generated externally, the lower platform acceleration sensor (3a) collects vibration signals as system input, the upper platform acceleration sensor (3b) outputs angle change data of the upper platform (1b) of the base, and controls the angle change value through the controller (5), thereby compensating the linear vibration and angular vibration generated externally in the form of angular motion; The adaptive active vibration reduction system of the aviation remote sensing system comprises: The base (1) is fixedly connected to the load via an upper plane, and the lower plane is fixedly connected to the vibration source, and the vibration frequency of the vibration source on the load is reduced by relative micro-displacement of the upper plane and the lower plane; A micro-displacement detection system (10) is installed on the base (1) and is used to detect the displacement states of the upper plane and the lower plane in real time respectively; A controller (5) is connected to the micro-displacement detection system (10) and is used to receive a detection signal from the micro-displacement detection system (10) and send a control instruction to the power component (11) after analysis and processing; A power assembly (11) is mounted on the base (1) and is used to output a waveform having the same frequency as the vibration source and opposite acceleration direction according to a control instruction of the controller (5), so as to make the upper plane and the lower plane of the base (1) move relative to each other and reduce the vibration frequency of the vibration source on the load; For the vibration of the lower platform (1a) of the base, the lower platform acceleration sensor (3a) collects the vibration amplitude A and the vibration period T = 2π / ω in real time, and extracts useful information through filter processing. At the same time, for only linear vibration, it is also necessary to collect the distance h between the carrier of the aerial remote sensing system and the target position, and the linear vibration displacement x = Asinωt is converted into angular vibration through θ = arctan (x / h), and the angular vibration directly collected is used as the system input. The influence of the converted comprehensive angular vibration on the photoelectric instrument is controlled by the controller (5) to control the piezoelectric ceramic. The voltage U at both ends of the piezoelectric ceramic actuator (2) is controlled so that the piezoelectric ceramic actuator (2) outputs a force F=k1U+k2, and the relationship between the output force F and the displacement ΔX is k3=F / ΔX, thereby obtaining a relationship between the voltage U and the displacement ΔX. The linear displacement ΔX is converted into angular motion through the platform structure, thereby achieving reverse offset of the system input angular vibration, reducing the vibration resistance of the upper platform (1b) and the load of the base, and at the same time, the upper platform acceleration sensor (3b) collects the angle change data of the upper platform (1b) and feeds it back to the controller (5) to realize a control closed loop.

2. The adaptive active vibration reduction control method of the aviation remote sensing system according to claim 1, characterized in that: The base (1) is of an integrated design, and comprises a base lower end platform (1a) and a base upper end platform (1b); The micro-displacement detection system (10) comprises: an acceleration sensor (3) and a displacement sensor (4); the acceleration sensor (3) comprises a lower platform acceleration sensor (3a) and an upper platform acceleration sensor (3b); the lower platform acceleration sensor (3a) is used to measure vibration source data and provide a real-time input signal to a controller; the upper platform acceleration sensor (3b) is used to measure a vibration reduction effect and provide a real-time feedback signal to a controller (5); The upper platform (1b) of the base is evenly distributed with upper platform acceleration sensors (3b); the lower platform (1a) of the base is evenly distributed with lower platform acceleration sensors (3a); and the displacement sensor (4) is used for real-time feedback of the distance between the upper platform (1b) of the base and the lower platform (1a) of the base.

3. The adaptive active vibration reduction control method for an aviation remote sensing system according to claim 2, characterized in that: The power assembly (11) comprises: a piezoelectric ceramic actuator (2), a top cover (6), a gasket (7) and an adjustment screw (8); The piezoelectric ceramic actuator (2) is tightly fitted with the base lower end platform (1a) and the base upper end platform (1b) via a top cover (6), a gasket (7) and an adjustment screw (8).

4. The adaptive active vibration reduction control method for an aviation remote sensing system according to claim 2, characterized in that: The piezoelectric ceramic actuator (2) is tightly attached to the inner wall of the groove of the base (1) on all sides.

5. The adaptive active vibration reduction control method for an aviation remote sensing system according to claim 1, characterized in that: Flexible hinge structures (9) are connected to both sides of the shell of the power component (11); the flexible hinge structures (9) are tightly fitted to the upper plane and the lower plane of the base respectively; the upper plane and the lower plane of the base (1) are relatively slightly displaced by elastic deformation and different shapes and sizes of the flexible hinge structures (9); the upper plane includes an upper end platform (1b) of the base; and the lower plane includes a lower end platform (1a) of the base.

6. An adaptive active vibration reduction device for an aerial remote sensing system for terrain mapping, characterized in that: The adaptive active vibration reduction device of the aerial remote sensing system for terrain mapping is equipped with an adaptive active vibration reduction system of the aerial remote sensing system of the control method according to any one of claims 1-5.

7. An adaptive active vibration reduction device for an aerial remote sensing system for resource exploration, characterized in that: The adaptive active vibration reduction device of the aerial remote sensing system for resource exploration is equipped with an adaptive active vibration reduction system of the aerial remote sensing system according to the control method described in any one of claims 1-5.

8. An adaptive active vibration reduction device for an aviation remote sensing system for disaster monitoring, characterized in that: The adaptive active vibration reduction device of the aviation remote sensing system for disaster monitoring is equipped with an adaptive active vibration reduction system of the aviation remote sensing system according to the control method described in any one of claims 1-5.

9. An adaptive active vibration reduction device for an aviation remote sensing system used for weather forecasting and military reconnaissance, characterized in that: The adaptive active vibration reduction device of the aviation remote sensing system used for weather forecasting and military reconnaissance is equipped with an adaptive active vibration reduction system of the aviation remote sensing system using the control method described in any one of claims 1-5.

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