An airborne device without angular displacement damping device of a multi-stage connecting rod mechanism

Abstract

The present application relates to a kind of onboard equipment angular displacement vibration damping device of multistage connecting rod mechanism, including support platform, the upper portion of the support platform is provided with adapter bottom plate and installation platform;Adapter bottom plate and support platform are connected with multiple groups of connecting rod mechanism, the axial direction of rotating pin shaft on the connecting rod mechanism is Y axis direction, and at least one group of connecting rod mechanism is parallelogram mechanism;Installation platform and support platform are connected with multiple dampers;Adapter bottom plate and installation platform are connected with multiple groups of guide pin assembly, the guide pin assembly includes the guide pin and guide sleeve that are coaxially inserted, the axial direction of the guide pin and guide sleeve is Y axis direction.The present application is suitable for the airborne optoelectronic pod, radar antenna, inertial navigation system and other high-precision equipment of aircraft or unmanned aerial vehicle, can effectively reduce the influence of vibration on imaging accuracy, measurement accuracy and aiming accuracy, improve the stability and reliability of overall system.

Description

TECHNICAL FIELD

[0001] The present application relates to a multi-stage linkage mechanism airborne equipment without angular displacement vibration damping device, and relates to the field of vibration control and damping. BACKGROUND

[0002] High-precision equipment such as airborne optical pod, radar antenna and inertial navigation system is easily affected by the vibration of the aircraft body during flight, resulting in blurred imaging, increased aiming error, and even affecting the accuracy of data. Airborne optical equipment is usually used in high dynamic environments such as unmanned aerial vehicles, fighter jets and reconnaissance aircraft, and its optical sensors need to maintain extremely high stability to ensure the clarity of the image and the accuracy of target recognition. However, under the influence of high-speed flight, maneuvering orbit change and complex air flow disturbance, the carrier aircraft will produce various forms of vibration, including structural vibration, flutter, buffeting and flow-induced vibration. These vibrations will be transmitted to the optical pod along multiple degrees of freedom, causing the optical pod to drift, the image to blur, and even affecting the target tracking and precision strike capability.

[0003] Among them, compared with linear displacement, angular displacement has a more serious impact on airborne optical equipment. Optical equipment usually relies on high-precision optical and inertial measurement systems for target locking and tracking, and even a small angular displacement error can cause a significant deviation of a long-distance target. For example, under high-speed flight conditions, if the optical pod changes slightly in angle due to the vibration of the aircraft body, the target it points to may deviate by hundreds of meters or even kilometers, greatly affecting its combat or reconnaissance capability. Therefore, achieving no angular displacement damping, i.e. eliminating linear vibration while ensuring the angular stability of the equipment, is the key to improving the precision of airborne optical equipment.

[0004] Currently, there are a variety of vibration control techniques applied to airborne equipment vibration isolation, including passive vibration isolation, parallelogram mechanism vibration isolation, active vibration isolation and three-degree-of-freedom vibration isolation system. However, these techniques still have certain limitations, which can be summarized as follows:

[0005] 1) Traditional passive vibration isolation: relying on rubber, air spring or metal spring materials for vibration isolation, suitable for high-frequency vibration environment, but limited in low-frequency vibration isolation performance. After a long time of use, the elastic material is prone to aging, affecting the damping effect. In high-speed dynamic environment, it is difficult to effectively control the angular displacement error, which may still cause the optical equipment to drift.

[0006] 2) Parallelogram mechanism: limiting angular displacement through parallelogram linkage mechanism to achieve a certain degree of angular displacement damping. However, in high-speed flight or complex vibration environment, the linkage mechanism may accumulate errors due to local stiffness changes, reducing the stability of the optical axis. Some designs are prone to secondary resonance under low-frequency vibration, affecting the quality of the image.

[0007] 3) Active vibration isolation technology: sensors are used to detect vibrations and real-time damping characteristics are adjusted through electromagnetic, piezoelectric or magnetorheological regulators to improve vibration suppression effect. It has high adaptability, but the system is complex and has high power consumption, which is not suitable for all lightweight airborne equipment. Additional power supply and computing resources are required, increasing the weight and cost of the overall system.

[0008] 4) Three-degree-of-freedom vibration isolation design: multi-degree-of-freedom vibration isolators are used to reduce vibration propagation through rigid-flexible coupling structures. It can optimize vibration suppression in each direction to a certain extent, but it is not specifically optimized for angular displacement error. The line-of-sight stability may still be affected under complex aircraft motion conditions, resulting in a decrease in long-range measurement or aiming accuracy.

[0009] To solve the above problems, the present application provides an airborne equipment angular displacement-free vibration reduction device combined with a multi-stage connecting rod mechanism and a metal rubber vibration absorber. By optimizing the connecting rod structure and reasonably configuring the damping elements, the body vibration can be effectively controlled, the angular displacement error can be avoided, and the imaging accuracy and pointing stability of the photoelectric equipment can be improved. SUMMARY

[0010] In view of the shortcomings of the prior art, the technical problem to be solved by the present application is to provide a multi-stage connecting rod mechanism airborne equipment angular displacement-free vibration reduction device to overcome the problems of ineffective suppression of angular displacement, insufficient low-frequency vibration isolation performance, and mismatch between structural stiffness and damping in the prior art, thereby improving the line-of-sight stability of the photoelectric equipment.

[0011] To solve the above technical problems, the technical solution of the present application is: a multi-stage connecting rod mechanism airborne equipment angular displacement-free vibration reduction device, comprising a support platform, a transfer bottom plate and a mounting platform are arranged above the support platform;

[0012] A plurality of connecting rod mechanisms are connected between the transfer bottom plate and the support platform, the axial direction of the rotating pin shaft on the connecting rod mechanism is Y-axis direction, and at least one connecting rod mechanism is a parallelogram mechanism;

[0013] A plurality of vibration absorbers are connected between the mounting platform and the support platform;

[0014] A plurality of guide pin assemblies are connected between the transfer bottom plate and the mounting platform, the guide pin assembly comprises a guide pin and a guide sleeve which are coaxially inserted, and the axial direction of the guide pin and the guide sleeve is Y-axis direction.

[0015] Preferably, the connecting rod mechanism has three groups, which are a first connecting rod mechanism, a second connecting rod mechanism and a third connecting rod mechanism, the first and second connecting rod mechanisms are arranged on the two opposite sides between the transfer bottom plate and the support platform along the X-axis direction, and the third connecting rod mechanism is arranged on one side between the transfer bottom plate and the support platform along the Y-axis direction.

[0016] Preferably, the first and second connecting rod mechanisms are both two in number on their corresponding mounting sides and are both composed of a lower fixing base, a first lower connecting rod, a first upper connecting rod and an upper fixing base.

[0017] Preferably, the lower fixing bases are both fixedly connected to the support platform, the bottom ends of the first lower connecting rods are both hingedly connected to the lower fixing bases via rotating pin shafts, the top ends of the first lower connecting rods are both hingedly connected to the first upper connecting rods via rotating pin shafts, the top ends of the first upper connecting rods are both hingedly connected to the upper fixing bases via rotating pin shafts, and the upper fixing bases are both fixedly connected to the adapter bottom plate.

[0018] Preferably, 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.

[0019] Preferably, the two lower supports are both fixedly connected to the support platform, the bottom ends of the two second lower connecting rods are both hingedly connected to the corresponding lower supports via rotating pin shafts, the top ends of the two second lower connecting rods are both hingedly connected to the corresponding second upper connecting rods via rotating pin shafts, the top ends of the two second upper connecting rods are both hingedly connected to the corresponding upper supports via rotating pin shafts, and the two upper supports are both fixedly connected to the adapter bottom plate; one end of the long connecting rod is hingedly connected to the rotating pin shafts of one set of second lower connecting rod and second upper connecting rod, and the other end of the long connecting rod is hingedly connected to the rotating pin shafts of the other set of second lower connecting rod and second upper connecting rod.

[0020] Preferably, the shock absorber is a three-dimensional metal rubber shock absorber.

[0021] Preferably, the shock absorber has four and is arranged at the left upper corner, the left lower corner, the right upper corner and the right lower corner positions between the mounting platform and the support platform.

[0022] Preferably, one end of each guide pin is fixedly connected with a U-shaped fixing base, the U-shaped fixing bases are all fixedly connected to the annular inner edge of the adapter bottom plate, and the guide sleeves are all linear bearings fixedly connected to the mounting platform.

[0023] Preferably, the guide pin assembly has four sets and is arranged at the left upper corner, the left lower corner, the right upper corner and the right lower corner positions between the adapter bottom plate and the mounting platform.

[0024] Compared with the prior art, the present application has the following beneficial effects:

[0025] 1) Realize all-around angle displacement-free shock absorption: adopt multi-stage connecting rod mechanism to improve the torsional stiffness of the system and effectively suppress angle displacement error; combine with flexible support structure to reduce the influence of machine body vibration on the pointing of the nacelle.

[0026] 2) Enhance the wide-band vibration suppression capability: through metal rubber shock absorption, optimize the isolation performance of low-frequency vibration and improve the long-term stability of the system.

[0027] 3) Improved system durability and environmental adaptability: Compared to traditional rubber damping elements, metal-rubber materials have better high-temperature resistance and corrosion resistance, making them suitable for harsh flight environments. The passive design eliminates the need for additional power sources, making the system more reliable and suitable for long-term operation.

[0028] This invention is applicable to high-precision equipment such as airborne optoelectronic pods, radar antennas, and inertial navigation systems for aircraft or drones. It can effectively reduce the impact of vibration on imaging accuracy, measurement accuracy, and aiming accuracy, thereby improving the overall system stability and reliability.

[0029] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments. Attached Figure Description

[0030] Figure 1 This is a schematic diagram illustrating the structure of an embodiment of the present invention.

[0031] Figure 2 This is a schematic diagram of the first / second linkage mechanism.

[0032] Figure 3 This is a schematic diagram of the third linkage mechanism.

[0033] Figure 4 This is a schematic diagram of the adapter base plate.

[0034] Figure 5 This is a schematic diagram of the installation platform. Detailed Implementation

[0035] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0036] It should be noted that the following detailed descriptions are exemplary and intended to provide further explanation of this application. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains.

[0037] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, 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.

[0038] like Figures 1-5 As shown, this embodiment provides an airborne equipment vibration reduction device with a multi-stage linkage mechanism and no angular displacement, including a support platform 1, and a transfer base plate 2 and an installation platform 3 are provided above the support platform;

[0039] A plurality of connecting rod mechanisms are connected between the adapter base plate and the support platform, the rotation pin shafts 4 on the connecting rod mechanisms are all in the Y-axis direction, and at least one of the connecting rod mechanisms is a parallelogram mechanism;

[0040] A plurality of shock absorbers 5 are connected between the mounting platform and the support platform;

[0041] A plurality of guide pin assemblies are connected between the adapter base plate and the mounting platform, and each guide pin assembly comprises a guide pin 6 and a guide sleeve 7 coaxially inserted with each other, and the guide pin and the guide sleeve are both in the Y-axis direction.

[0042] In the embodiment of the present application, the connecting rod mechanism has three groups, namely a first connecting rod mechanism 8, a second connecting rod mechanism 9, and a third connecting rod mechanism 10, the first and second connecting rod mechanisms are arranged on the two opposite sides between the adapter base plate and the support platform along the X-axis direction, and the third connecting rod mechanism is arranged on one side between the adapter base plate and the support platform along the Y-axis direction.

[0043] In the embodiment of the present application, the number of the first and second connecting rod mechanisms on the corresponding mounting side is two, and each is composed of a lower fixed seat 11, a first lower connecting rod 12, a first upper connecting rod 13, and an upper fixed seat 14.

[0044] In the embodiment of the present application, the lower fixed seat is fixedly connected to the support platform, the bottom end of the first lower connecting rod is hingedly connected to the lower fixed seat through a rotation pin shaft, the top end of the first lower connecting rod is hingedly connected to the first upper connecting rod through a rotation pin shaft, the top end of the first upper connecting rod is hingedly connected to the upper fixed seat through a rotation pin shaft, and the upper fixed seat is fixedly connected to the adapter base plate.

[0045] The length of the first lower connecting rod is 80 mm, the thickness is 20 mm, and the initial installation position is arranged at an angle of 45° inwardly to the support platform; the length of the first upper connecting rod is 80 mm, and the initial installation position is arranged at an angle of 45° outwardly to the support platform.

[0046] In the embodiment of the present application, the third connecting rod mechanism is a parallelogram mechanism, and is composed of two lower supports 15, two second lower connecting rods 16, two second upper connecting rods 17, two upper supports 18, and a long connecting rod 19.

[0047] In the embodiment of the present application, the two lower supports are fixedly connected to the support platform, the bottom ends of the two second lower connecting rods are hingedly connected to the corresponding lower supports through rotation pin shafts, the top ends of the two second lower connecting rods are hingedly connected to the corresponding second upper connecting rods through rotation pin shafts, the top ends of the two second upper connecting rods are hingedly connected to the corresponding upper supports through rotation pin shafts, and the two upper supports are fixedly connected to the adapter base plate; one end of the long connecting rod is hingedly connected to the rotation pin shafts of one set of second lower connecting rod and second upper connecting rod, and the other end of the long connecting rod is hingedly connected to the rotation pin shafts of another set of second lower connecting rod and second upper connecting rod.

[0048] The length of the second upper and lower connecting rods is 80 mm, and the thickness is 24 mm, and the initial installation position is arranged at 45° with the support platform.

[0049] In the embodiment of the present application, the damper is a three-dimensional metal rubber damper.

[0050] The metal rubber damper is used as the main vibration isolation component. The metal rubber material not only provides elastic support, but also absorbs and dissipates vibration energy of different frequency ranges through its inherent damping characteristics, achieving efficient low-frequency vibration attenuation capability, while overcoming the problem of easy aging of traditional rubber materials.

[0051] In the embodiment of the present application, the damper has four left upper corner, left lower corner, right upper corner and right lower corner positions vertically arranged between the mounting platform and the support platform.

[0052] The multi-stage connecting rod mechanism forms a multi-stage flexible support structure, realizing efficient angular displacement-free vibration reduction. The metal rubber-based damping components are arranged at key nodes to enhance the overall vibration isolation capability of the system.

[0053] In the embodiment of the present application, the shape of the adapter base plate is annular.

[0054] In the embodiment of the present application, one end of each guide pin is fixedly connected with a U-shaped fixing seat 20, and the U-shaped fixing seat is fixedly connected to the inner edge of the annular adapter base plate. The guide sleeve is a linear bearing and is fixedly connected to the mounting platform. The length of the guide pin is 150 mm.

[0055] In the embodiment of the present application, the guide pin assembly has four groups of left upper corner, left lower corner, right upper corner and right lower corner positions respectively arranged between the adapter base plate and the mounting platform.

[0056] In the embodiment of the present application, 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 body) by bolts. The adapter base plate is made of a steel plate with a thickness of 14 mm, and serves to connect the mounting platform. The mounting platform is used to connect the electro-optical pod.

[0057] In the embodiment of the present application, the vibration reduction method of the multi-stage connecting rod mechanism angular displacement-free vibration reduction device for airborne equipment is as follows:

[0058] When the support platform is disturbed to rotate around the X direction after assembly is completed, the adapter base plate is driven by the three groups of connecting rod mechanisms to rotate synchronously around the X direction. The mounting platform forms a moving pair through the guide pin assembly, and can move along the Y direction when the support platform rotates synchronously around the X direction.

[0059] When the support platform is disturbed to rotate around the Y direction, the adapter bottom plate converts the rotation around the Y direction into translation along the X and Z directions through the three sets of connecting rod mechanisms. Meanwhile, the mounting platform forms a moving pair through the guide pin assembly, and when the adapter bottom plate translates along the X and Z directions, the mounting platform still has the freedom of Y direction translation.

[0060] When the support platform is disturbed to rotate around the Z direction, the adapter bottom plate is driven to synchronously rotate around the Z direction through the three sets of connecting rod mechanisms. The mounting platform forms a moving pair through the guide pin assembly, and when the support platform synchronously rotates around the Z direction, the mounting platform still has the freedom of Y direction translation.

[0061] Therefore, the vibration damping device realizes the angular displacement of the optoelectronic pod relative to the support platform along the X, Y and Z directions in space, and can perform three-way damping through the dampers.

[0062] The vibration damping device provided by the application limits the rotation of the optoelectronic pod on the mounting platform along the X and Z directions through the connecting rod mechanisms, so that the optoelectronic pod can translate along the X and Z directions. The rotation of the optoelectronic pod on the mounting platform along the Y direction is limited through the cooperation of the guide pin assembly, so that the optoelectronic pod can translate along the Y direction. Therefore, the three-dimensional rotation of the optoelectronic pod relative to the support platform in space is limited, the angular displacement in the three directions is converted into linear displacement, and the angular displacement damping of the airborne optoelectronic pod is realized.

[0063] The above is only a preferred embodiment of the application, and is not intended to limit the application in other forms. Any person skilled in the art can modify or change the above disclosed technical content into equivalent embodiments with equivalent changes. However, any simple modification, equivalent change and modification made on the basis of the technical essence of the application to the above embodiments, without departing from the technical solution of the application, still falls within the protection scope of the technical solution of the application.

Claims

1. An airborne device angular displacement free vibration damping device of a multi-stage linkage mechanism, characterized by: The support platform is provided with an adapter bottom plate and a mounting platform above it; A plurality of connecting rod mechanisms are connected between the adapter bottom plate and the support platform, the rotation pins on the connecting rod mechanisms are all in the Y-axis direction, and at least one connecting rod mechanism is a parallelogram mechanism; A plurality of dampers are connected between the mounting platform and the support platform; A plurality 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 coaxially inserted with each other, and the guide pin and the guide sleeve are both in the Y-axis direction; The connecting rod mechanisms have three groups, which are a first connecting rod mechanism, a second connecting rod mechanism and a third connecting rod mechanism; the first and second connecting rod mechanisms each comprise a lower fixed seat, a first lower connecting rod, a first upper connecting rod and an upper fixed seat; the lower fixed seat is fixedly connected to the support platform, the bottom end of the first lower connecting rod is hingedly connected to the lower fixed seat via a rotation pin, the top end of the first lower connecting rod is hingedly connected to the first upper connecting rod via a rotation pin, the top end of the first upper connecting rod is hingedly connected to the upper fixed seat via a rotation pin, and the upper fixed seat is fixedly connected to the adapter bottom plate; the third connecting rod mechanism is a parallelogram mechanism and comprises two lower supports, two second lower connecting rods, two second upper connecting rods, two upper supports and a long connecting rod; the two lower supports are fixedly connected to the support platform, the bottom ends of the two second lower connecting rods are hingedly connected to the corresponding lower supports via rotation pins, the top ends of the two second lower connecting rods are hingedly connected to the corresponding second upper connecting rods via rotation pins, the top ends of the two second upper connecting rods are hingedly connected to the corresponding upper supports via rotation pins, and the two upper supports are fixedly connected to the adapter bottom plate; one end of the long connecting rod is hingedly connected to the rotation pins of one of the second lower connecting rods and the second upper connecting rod, and the other end of the long connecting rod is hingedly connected to the rotation pins of the other of the second lower connecting rods and the second upper connecting rod.

2. The airborne apparatus angular displacement-free vibration damping device of a multi-stage linkage mechanism according to claim 1, characterized by: The first and second connecting rod mechanisms are arranged on two opposite sides between the adapter bottom plate and the support platform in the X-axis direction, and the third connecting rod mechanism is arranged on one side between the adapter bottom plate and the support platform in the Y-axis direction.

3. The airborne apparatus angular displacement-free vibration damping device of a multi-stage linkage mechanism according to claim 2, characterized by: The number of the first and second connecting rod mechanisms on the corresponding mounting side is two.

4. The airborne apparatus angular displacement-free vibration damping device of a multi-stage linkage mechanism according to claim 1, characterized by: The dampers are three-dimensional metal rubber dampers.

5. The airborne apparatus angular displacement-free vibration damping device of claim 1, wherein: The dampers have four and are arranged at the upper left corner, the lower left corner, the upper right corner and the lower right corner between the mounting platform and the support platform.

6. The airborne apparatus angular displacement-free vibration damping device of claim 1, wherein: One end of the guide pin is fixedly connected with a U-shaped fixed seat, the U-shaped fixed seat is fixedly connected to the inner edge of the adapter bottom plate, and the guide sleeve is a linear bearing fixedly connected to the mounting platform.

7. The airborne apparatus angular displacement-free vibration damping device of claim 1, wherein: The guide pin assemblies have four and are arranged at the upper left corner, the lower left corner, the upper right corner and the lower right corner between the adapter bottom plate and the mounting platform.

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