Airborne equipment angular displacement-free damping device of multi-stage connecting rod mechanism

Abstract

The invention relates to an airborne equipment angular displacement-free damping device of a multi-stage connecting rod mechanism. The airborne equipment angular displacement-free damping device comprises a supporting platform, and a switching bottom plate and a mounting platform are arranged above the supporting platform; a plurality of connecting rod mechanisms are connected between the switching bottom plate and the supporting platform, the axial directions of rotating pin shafts on the connecting rod mechanisms are all the Y-axis directions, and at least one connecting rod mechanism is a parallelogram mechanism; a plurality of shock absorbers are connected between the mounting platform and the supporting platform; a plurality of groups of guide pin assemblies are connected between the adapter bottom plate and the mounting platform, each guide pin assembly comprises a guide pin and a guide sleeve which are mutually and coaxially inserted, and the axial directions of the guide pins and the guide sleeves are Y-axis directions. The method is suitable for high-precision equipment such as an airborne photoelectric pod, a radar antenna and an inertial navigation system of an airplane or an unmanned aerial vehicle, the influence of vibration on imaging precision, measurement precision and aiming precision can be effectively reduced, and the stability and reliability of the whole system are improved.

Description

Technical Field

[0001] The present invention relates to an angular displacement-free vibration damping device for airborne equipment with a multi-stage link mechanism, and relates to the technical fields of vibration control and vibration damping. Background Art

[0002] High-precision equipment such as airborne optoelectronic pods, radar antennas, and inertial navigation systems are prone to being affected by the vibration of the airframe during flight, resulting in blurred imaging, increased aiming errors, and even affecting the accuracy of data. Airborne optoelectronic equipment is usually used in high-dynamic environments such as unmanned aerial vehicles, fighter jets, and reconnaissance aircraft. Its optical sensors need to maintain extremely high stability to ensure the clarity of imaging and the accuracy of target recognition. However, under the influence of high-speed flight, maneuvering orbit changes, and complex airflow disturbances of the carrier aircraft, various forms of vibration will be generated, including structural vibration, flutter, buffeting, and flow-induced vibration caused by aerodynamics. These vibrations will be transmitted to the optoelectronic pod along multiple degrees of freedom, resulting in visual axis drift, blurred images, and even affecting the target tracking and precision strike capabilities.

[0003] Among them, compared with linear displacement, angular displacement has a more serious impact on airborne optoelectronic equipment. Optoelectronic equipment usually relies on high-precision optical and inertial measurement systems for target locking and tracking. Even a tiny angular displacement error may lead to significant deviations of distant targets. For example, under high-speed flight conditions, if the optoelectronic pod undergoes a small angular change due to the vibration of the airframe, its pointing at the target may deviate by hundreds of meters or even several kilometers, greatly affecting its combat or reconnaissance capabilities. Therefore, achieving angular displacement-free vibration damping, that is, while eliminating linear vibration, ensuring the angular stability of the equipment, is the key to improving the accuracy of airborne optoelectronic equipment.

[0004] Currently, a variety of vibration control technologies have been applied to vibration isolation of airborne equipment, including passive vibration isolation, parallelogram mechanism vibration isolation, active vibration isolation, and three-degree-of-freedom vibration isolation systems. However, these technologies still have certain limitations, which can be summarized as follows: 1) Traditional passive vibration isolation: relies on materials such as rubber, air springs, or metal springs for vibration isolation, suitable for high-frequency vibration environments, but has limited low-frequency vibration isolation performance. After long-term use, the elastic materials are prone to aging, affecting the vibration damping effect. In high-speed dynamic environments, it cannot effectively control angular displacement errors and may still cause pointing drift of optoelectronic equipment.

[0005] 2) Parallelogram mechanism: restricts angular displacement through a parallelogram link mechanism to achieve a certain degree of angular displacement-free vibration damping. However, in high-speed flight or complex vibration environments, the link mechanism may cause error accumulation due to local stiffness changes, reducing the visual axis stability. Some designs are prone to secondary resonance under low-frequency vibration, affecting the imaging quality.

[0006] 3) Active vibration isolation technology: Sensors are used to detect vibrations, and electromagnetic, piezoelectric, or magnetorheological regulators are employed to adjust the damping characteristics in real time, enhancing the vibration suppression effect. It has high adaptability, but the system is complex, consumes a high amount of power, and is not suitable for all lightweight airborne equipment. It requires additional power supply and computing resources, increasing the weight and cost of the overall system.

[0007] 4) Three-degree-of-freedom vibration isolation design: Multi-degree-of-freedom vibration isolators are used, and the rigid-flexible coupling structure is adopted to reduce vibration propagation. It can optimize vibration suppression in all directions to a certain extent, but it is not specifically optimized for angular displacement errors. The line-of-sight stability may still be affected under complex carrier aircraft motion conditions, resulting in a decline in the accuracy of long-range measurement or aiming.

[0008] To address the above problems, the present invention proposes an airborne equipment angular displacement-free vibration damping device combining a multi-stage link mechanism and metal rubber vibration damping. By optimizing the link structure and reasonably configuring damping elements, it can effectively control the vibration of the airframe, avoid angular displacement errors, and improve the imaging accuracy and pointing stability of optoelectronic devices. Summary of the Invention

[0009] In view of the deficiencies of the prior art, the technical problem to be solved by the present invention is to provide an airborne equipment angular displacement-free vibration damping device with a multi-stage link mechanism to overcome the problems in the prior art such as difficult effective suppression of angular displacement, insufficient low-frequency vibration isolation performance, and mismatch between structural stiffness and damping, thereby improving the line-of-sight stability of optoelectronic devices.

[0010] To solve the above technical problems, the technical solution of the present invention is: An airborne equipment angular displacement-free vibration damping device with a multi-stage link mechanism, including a support platform, above which a transfer base plate and an installation platform are provided; A plurality of groups of link mechanisms are connected between the transfer base plate and the support platform. The axial directions of the rotating pins on the link mechanisms are all in the Y-axis direction, and at least one group of link mechanisms is a parallelogram mechanism; A plurality of shock absorbers are connected between the installation platform and the support platform; A plurality of groups of guide pin assemblies are connected between the transfer base plate and the installation platform. Each guide pin assembly includes a guide pin and a guide sleeve that are coaxially inserted into each other, and the axial directions of the guide pin and the guide sleeve are both in the Y-axis direction.

[0011] Preferably, there are three groups of link mechanisms, namely the first link mechanism, the second link mechanism, and the third link mechanism. The first and second link mechanisms are arranged on two opposite sides between the transfer base plate and the support platform along the X-axis direction, and the third link mechanism is arranged on one side between the transfer base plate and the support platform along the Y-axis direction.

[0012] Preferably, the number of the first and second link mechanisms on their corresponding mounting sides are both two, and both are composed of a lower fixing seat, a first lower connecting rod, a first upper connecting rod, and an upper fixing seat.

[0013] Preferably, the lower fixed seats are fixedly connected to the supporting platform, the bottom end of the first lower connecting rod is hinged to the lower fixed seat via a rotating pin, the top end of the first lower connecting rod is hinged to the first upper connecting rod via a rotating pin, the top end of the first upper connecting rod is hinged to the upper fixed seat via a rotating pin, and the upper fixed seats are fixedly connected to the transfer base plate.

[0014] Preferably, the third link mechanism is a parallelogram mechanism, and is composed of two lower supports, two second lower connecting rods, two second upper connecting rods, two upper supports, and a long connecting rod.

[0015] Preferably, the two lower supports are fixedly connected to the supporting platform, the bottom ends of the two second lower connecting rods are hinged to the corresponding lower supports via rotating pins, the top ends of the two second lower connecting rods are hinged to the corresponding second upper connecting rods via rotating pins, the top ends of the two second upper connecting rods are hinged to the corresponding upper supports via rotating pins, and the two upper supports are fixedly connected to the transfer base plate; one end of the long connecting rod is hinged to the rotating pins of one group of the second lower connecting rods and the second upper connecting rods, and the other end of the long connecting rod is hinged to the rotating pins of another group of the second lower connecting rods and the second upper connecting rods.

[0016] Preferably, the shock absorber is a three-dimensional metal rubber shock absorber.

[0017] Preferably, there are four shock absorbers and they are arranged at the upper left corner, lower left corner, upper right corner and lower right corner between the mounting platform and the supporting platform.

[0018] Preferably, one end of the guide pin is fixedly connected to a U-shaped fixing seat, the U-shaped fixing seat is fixedly connected to the annular inner edge of the adapter base plate, and the guide sleeve is a linear bearing and is fixedly connected to the mounting platform.

[0019] Preferably, the guide pin assembly has four groups and is respectively arranged at the upper left corner, lower left corner, upper right corner and lower right corner between the adapter base plate and the mounting platform.

[0020] Compared with the prior art, the present invention has the following beneficial effects: 1) Achieve all-round vibration reduction without angular displacement: adopt a multi-stage linkage mechanism to improve the torsional rigidity of the system and effectively suppress the angular displacement error. Combined with a flexible support structure, reduce the impact of body vibration on the pod pointing.

[0021] 2) Enhance wide-band vibration suppression capability: Through metal rubber vibration reduction, optimize the isolation performance of low-frequency vibration and improve the long-term stability of the system.

[0022] 3) Improve the system durability and environmental adaptability: Compared with traditional rubber damping components, metal rubber materials have better high-temperature resistance and corrosion resistance, and are suitable for harsh flight environments. With a passive design that does not rely on additional energy, the system is more reliable and suitable for long-term operating environments.

[0023] The present invention is applicable to high-precision equipment such as airborne optoelectronic pods, radar antennas, and inertial navigation systems of aircraft or unmanned aerial vehicles, and can effectively reduce the impact of vibration on imaging accuracy, measurement accuracy, and aiming accuracy, and improve the stability and reliability of the overall system.

[0024] The following further elaborates on the present invention in conjunction with the attached drawings and specific embodiments. Description of the Drawings

[0025] Figure 1 It is a schematic structural diagram of an embodiment of the present invention.

[0026] Figure 2 It is a schematic structural diagram of the first / second link mechanism.

[0027] Figure 3 It is a schematic structural diagram of the third link mechanism.

[0028] Figure 4 It is a schematic structural diagram of the adapter base plate.

[0029] Figure 5 It is a schematic structural diagram of the mounting platform. Specific Embodiments

[0030] The following further describes the present invention in conjunction with the attached drawings and embodiments.

[0031] It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the present application. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which the present application belongs.

[0032] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0033] As Figures 1 to 5 shown, this embodiment provides a vibration damping device without angular displacement for airborne equipment with a multi-stage link mechanism, including a support platform 1, and an adapter base plate 2 and a mounting platform 3 are arranged above the support platform; A plurality of link mechanisms are connected between the adapter base plate and the support platform. The axial directions of the rotating pin shafts 4 on the link mechanisms are all in the Y-axis direction, and at least one group of link mechanisms is a parallelogram mechanism; A plurality of shock absorbers 5 are connected between the mounting platform and the support platform; A plurality of guide pin assemblies are connected between the adapter base plate and the mounting platform. Each guide pin assembly includes a guide pin 6 and a guide sleeve 7 that are coaxially inserted into each other. The axial directions of the guide pin and the guide sleeve are both in the Y-axis direction.

[0034] In the embodiment of the present invention, there are three groups of link mechanisms, namely a first link mechanism 8, a second link mechanism 9, and a third link mechanism 10. The first and second link mechanisms are arranged on two opposite sides between the adapter base plate and the support platform along the X-axis direction, and the third link mechanism is arranged on one side between the adapter base plate and the support platform along the Y-axis direction.

[0035] In the embodiment of the present invention, the number of the first and second link mechanisms on their corresponding mounting sides is two, and each of them is composed of a lower fixed seat 11, a first lower link 12, a first upper link 13, and an upper fixed seat 14.

[0036] In the embodiment of the present invention, the lower fixed seats are all fixedly connected to the support platform. The bottom ends of the first lower links are all hinged to the lower fixed seats via rotating pin shafts, the top ends of the first lower links are all hinged to the first upper links via rotating pin shafts, the top ends of the first upper links are all hinged to the upper fixed seats via rotating pin shafts, and the upper fixed seats are all fixedly connected to the adapter base plate.

[0037] The length of the first lower link is 80 mm, the thickness is 20 mm, and the initial installation position is arranged at an angle of 45° inward with respect to the support platform; the length of the first upper link is 80 mm, and the initial installation position is arranged at an angle of 45° outward with respect to the support platform.

[0038] In the embodiment of the present invention, the third link mechanism is a parallelogram mechanism and is composed of two lower supports 15, two second lower links 16, two second upper links 17, two upper supports 18, and a long link 19.

[0039] In the embodiment of the present invention, the two lower supports are all fixedly connected to the support platform. The bottom ends of the two second lower links are all hinged to the corresponding lower supports via rotating pin shafts, the top ends of the two second lower links are all hinged to the corresponding second upper links via rotating pin shafts, the top ends of the two second upper links are all hinged to the corresponding upper supports via rotating pin shafts, and the two upper supports are all fixedly connected to the adapter base plate; one end of the long link is hinged to the rotating pin shaft of one group of the second lower link and the second upper link, and the other end of the long link is hinged to the rotating pin shaft of the other group of the second lower link and the second upper link.

[0040] The length of the second upper and lower connecting rods is 80 mm, the thickness is 24 mm, and the initial installation position is arranged at 45° with the support platform layer.

[0041] In the embodiment of the present invention, the shock absorber is a three-dimensional metal rubber shock absorber.

[0042] Using a metal rubber shock absorber as the main vibration isolation component, the metal rubber material not only provides elastic support, but also can absorb and dissipate vibration energy in different frequency ranges through its inherent damping characteristics, realizing efficient low-frequency vibration attenuation ability, while overcoming the problem of easy aging of traditional rubber materials.

[0043] In the embodiment of the present invention, the shock absorber has four and is vertically arranged at the upper left corner, lower left corner, upper right corner, and lower right corner positions between the installation platform and the support platform.

[0044] Multiple sets of link mechanisms form a multi-stage flexible support structure to achieve efficient vibration reduction without angular displacement. The vibration isolation components based on metal rubber are arranged at key nodes to enhance the overall vibration isolation ability of the system.

[0045] In the embodiment of the present invention, the shape of the adapter bottom plate is annular.

[0046] In the embodiment of the present invention, one end of each guide pin is fixedly connected with a U-shaped fixing seat 20, the U-shaped fixing seats are fixedly connected to the annular inner edge of the adapter bottom plate, and the guide sleeves are all linear bearings and are fixedly connected to the installation platform. The length of the guide pin is 150 mm.

[0047] In the embodiment of the present invention, the guide pin assembly has four groups and is respectively arranged at the upper left corner, lower left corner, upper right corner, and lower right corner positions between the adapter bottom plate and the installation platform.

[0048] In the embodiment of the present invention, the support platform is made of a steel plate with a thickness of 10 mm, and the support platform is fixedly connected to the carrier (aircraft fuselage) by bolts. The adapter bottom plate is made of a steel plate with a thickness of 14 mm and serves to connect the installation platform. The installation platform is used to connect the optoelectronic pod.

[0049] In the embodiment of the present invention, the vibration reduction method of the airborne equipment angular displacement-free vibration reduction device with a multi-stage link mechanism is as follows: When the assembly is completed, when the support platform is disturbed and rotates around the X direction, the three sets of link mechanisms drive the adapter bottom plate to rotate synchronously around the X direction. The installation platform forms a moving pair through the guide pin assembly, and when it rotates synchronously with the support platform around the X direction, it can translate along the Y direction.

[0050] When the support platform is disturbed and rotates around the Y direction, the adapter baseplate converts the rotation around the Y direction into translational motions along the X and Z directions through three sets of link mechanisms. At the same time, the installation platform forms a prismatic pair through the guide pin assembly. When it translates along the X and Z directions following the adapter baseplate, it still has the freedom of translational motion in the Y direction.

[0051] When the support platform is disturbed and rotates around the Z direction, the adapter baseplate is driven to rotate synchronously around the Z direction through three sets of link mechanisms. The installation platform forms a prismatic pair through the guide pin assembly. When it rotates synchronously around the Z direction following the support platform, it still has the freedom of translational motion in the Y direction.

[0052] Thus, this vibration damping device achieves no angular displacement of the optoelectronic pod relative to the support platform in the X, Y, and Z directions in space, and can perform three-way vibration damping through the shock absorbers.

[0053] The vibration damping device provided by the present invention restricts the rotation of the optoelectronic pod located on the installation platform along the X and Z directions through the link mechanisms, enabling it to translate along the X and Z directions; restricts the rotation of the optoelectronic pod located on the installation platform along the Y direction through the cooperation of the guide pin assembly, enabling it to translate along the Y direction; thus restricting the three-dimensional rotation of the optoelectronic pod relative to the support platform in space, converting the angular displacements in three directions into linear displacements, and achieving vibration damping without angular displacement of the airborne optoelectronic pod.

[0054] The above are only the preferred embodiments of the present invention, and are not intended to limit the present invention in other forms. Any person skilled in the art may use the disclosed technical content to make changes or modifications into equivalent embodiments with equivalent changes. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the technical solution content of the present invention still fall within the protection scope of the technical solution of the present invention.

Claims

1. A non-angular displacement vibration reduction device for airborne equipment with a multi-stage linkage mechanism, characterized in that: It includes a supporting platform, and a transfer base plate and a mounting platform are arranged above the supporting platform; A plurality of linkage mechanisms are connected between the adapter base plate and the support platform, the axial directions of the rotating pins on the linkage mechanisms are all in the Y-axis direction, and at least one linkage mechanism is a parallelogram mechanism; A plurality of shock absorbers are connected between the mounting platform and the supporting platform; A plurality of guide pin assemblies are connected between the adapter base plate and the mounting platform. The guide pin assemblies include guide pins and guide sleeves coaxially plugged into each other. The axial directions of the guide pins and guide sleeves are both in the Y-axis direction.

2. The airborne equipment non-angular displacement vibration reduction device of the multi-stage linkage mechanism according to claim 1, characterized in that: The linkage mechanism has three groups, namely a first linkage mechanism, a second linkage mechanism, and a third linkage mechanism. The first and second linkage mechanisms are arranged on two opposite sides between the adapter base plate and the support platform along the X-axis direction, and the third linkage mechanism is arranged on a single side between the adapter base plate and the support platform along the Y-axis direction.

3. The airborne equipment non-angular displacement vibration reduction device of the multi-stage linkage mechanism according to claim 2, characterized in that: The number of the first and second link mechanisms on their corresponding mounting sides are both two, and both are composed of a lower fixing seat, a first lower connecting rod, a first upper connecting rod, and an upper fixing seat.

4. The airborne equipment non-angular displacement vibration reduction device of the multi-stage linkage mechanism according to claim 3 is characterized in that: The lower fixed seats are all fixedly connected to the supporting platform, the bottom ends of the first lower connecting rods are hinged to the lower fixed seats via rotating pins, the top ends of the first lower connecting rods are hinged to the first upper connecting rods via rotating pins, the top ends of the first upper connecting rods are hinged to the upper fixed seats via rotating pins, and the upper fixed seats are all fixedly connected to the transfer base plate.

5. The airborne equipment non-angular displacement vibration reduction device of the multi-stage linkage mechanism according to claim 2, characterized in that: The third connecting rod mechanism is a parallelogram mechanism, and is composed of two lower supports, two second lower connecting rods, two second upper connecting rods, two upper supports, and a long connecting rod.

6. The airborne equipment non-angular displacement vibration reduction device of the multi-stage linkage mechanism according to claim 5, characterized in that: The two lower supports are fixedly connected to the supporting platform, the bottom ends of the two second lower connecting rods are hinged to the corresponding lower supports via rotating pins, the top ends of the two second lower connecting rods are hinged to the corresponding second upper connecting rods via rotating pins, the top ends of the two second upper connecting rods are hinged to the corresponding upper supports via rotating pins, and the two upper supports are fixedly connected to the transfer base plate; one end of the long connecting rod is hinged to the rotating pins of one group of the second lower connecting rods and the second upper connecting rods, and the other end of the long connecting rod is hinged to the rotating pins of another group of the second lower connecting rods and the second upper connecting rods.

7. The airborne equipment non-angular displacement vibration reduction device of the multi-stage linkage mechanism according to claim 1, characterized in that: The shock absorber is a three-dimensional metal rubber shock absorber.

8. The airborne equipment non-angular displacement vibration reduction device of the multi-stage linkage mechanism according to claim 1, characterized in that: There are four shock absorbers, which are arranged at the upper left corner, lower left corner, upper right corner and lower right corner between the mounting platform and the supporting platform.

9. The airborne equipment non-angular displacement vibration reduction device of the multi-stage linkage mechanism according to claim 1, characterized in that: One end of the guide pin is fixedly connected to a U-shaped fixing seat, and the U-shaped fixing seat is fixedly connected to the annular inner edge of the adapter base plate. The guide sleeves are linear bearings and are fixedly connected to the mounting platform.

10. The airborne equipment non-angular displacement vibration reduction device of the multi-stage linkage mechanism according to claim 1, characterized in that: The guide pin assembly has four groups and is respectively arranged at the upper left corner, lower left corner, upper right corner and lower right corner between the adapter base plate and the mounting platform.

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