Photoelectric pod vibration isolation unit and aircraft system
By designing a photoelectric pod vibration isolation unit including longitudinal vibration isolation parts and three-way rigidity vibration isolators, the problem of the photoelectric pod being affected by vibration and airflow disturbance during flight is solved, and higher image quality and tracking accuracy are achieved.
Patent Information
- Application Number
- CN202411816247.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-11
- Publication Date
- 2025-03-11
AI Technical Summary
During flight, the photoelectric pod is affected by vibrations from the engine and propeller and external airflow disturbances, resulting in a decrease in image quality and low tracking accuracy, especially the angular vibration has a great impact on image quality changes.
An optoelectronic pod vibration isolation unit is designed, including a hanger module, a first vibration isolation module and an optoelectronic pod. The first vibration isolation module consists of a longitudinal vibration isolation member, a three-way and other rigidity vibration isolator and a first connecting member. These components realize longitudinal and transverse vibration isolation, reducing angular displacement.
Through multi-point vibration isolation, the measurement effect of the photoelectric pod is improved, the angular displacement is reduced, the image quality and tracking accuracy are improved, and the designed vibration isolation unit is small in size, light in weight and good stability.
Smart Images
Figure CN119590631A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the technical field of pod vibration isolation systems, and in particular to an optoelectronic pod vibration isolation unit and an aircraft system. Background Art
[0002] Optical-electronic pods are often installed on helicopters, UAVs or fixed-wing aircraft for observation, search, attack and mapping, and they mostly use optical equipment such as visible light, infrared and laser. During the flight of the aircraft, the vibration of the engine and propeller, as well as the disturbance of the external airflow, will affect the movement of the optoelectronic pod in the six directions of X, Y, Z, around X, around Y and around Z, thereby reducing its image quality and tracking accuracy.
[0003] The basic task of the optoelectronic pod is to detect and locate the target. For target detection, the image must be clear and free of jitter, that is, the image quality must not change. The image quality change caused by angular vibration is greater than that caused by linear vibration, especially in the plane perpendicular to the optical axis. For target positioning, the optoelectronic pod is required to accurately measure the spatial position of the target relative to the aircraft in the automatic tracking state, so as to solve the actual position of the target. The angular displacement caused by vibration will cause the pod coordinate system to rotate relative to the aircraft coordinate system, making the measurement of the optoelectronic pod with measurement function inaccurate. The linear displacement moves in a plane and has almost no effect on the measurement of the optoelectronic pod. Therefore, when designing the optoelectronic pod vibration isolation unit, emphasis should be placed on reducing the angular displacement caused by various vibrations.
[0004] A commonly used method for achieving passive vibration isolation in engineering is to arrange three-way equal-stiffness isolators symmetrically between the inner and outer frames about the center of mass of the inner frame and its load to isolate vibration. However, in order to achieve a satisfactory vibration isolation effect, the resonant frequency of the three-way equal-stiffness isolators is generally not greater than 20 Hz, so their stiffness is small and the linear displacements in three directions are large, especially in the z-direction perpendicular to the optical axis plane. More space needs to be reserved, which not only increases the internal volume, thereby affecting the volume and weight of the entire pod, but also may cause the isolators to fail in the z-direction and may even cause poor stability of the system and easy shaking. Summary of the invention
[0005] The purpose of the present application is to provide an optoelectronic pod vibration isolation unit and an aircraft system in view of at least one technical problem involved in the background technology.
[0006] In order to achieve the above objectives, this application adopts the following technical solutions:
[0007] One aspect of the present application provides an optoelectronic pod vibration isolation unit, comprising a hanger module, a first vibration isolation module and an optoelectronic pod, wherein the hanger module is used to connect to an aircraft.
[0008] The first vibration isolation module includes a longitudinal vibration isolation member, a three-way equal-rigidity vibration isolator and a first connecting member. The first connecting member and the optoelectronic pod are both fixedly connected to the top end of the longitudinal vibration isolation member, the bottom end of the longitudinal vibration isolation member is fixedly connected to the hanger module, one end of the three-way equal-rigidity vibration isolator is fixedly connected to the hanger module in the axial direction of the three-way equal-rigidity vibration isolator, and the other end of the three-way equal-rigidity vibration isolator is fixedly connected to the first connecting member.
[0009] Optionally, the optoelectronic pod vibration isolation unit provided in the present application includes a plurality of the first vibration isolation modules, and the first vibration isolation modules are evenly arranged in the circumferential direction of the optoelectronic pod.
[0010] The beneficial effect of this technical solution is that: in this way, longitudinal and lateral vibration isolation can be performed at multiple positions between the aircraft and the optoelectronic pod through the first vibration isolation module, thereby improving the measurement effect of the optoelectronic pod.
[0011] Optionally, the axial direction of each of the three-way equal-rigidity vibration isolators is perpendicular to the axial direction of the optoelectronic pod.
[0012] Optionally, the longitudinal vibration isolator comprises a wire rope vibration isolator, and the axial direction of the wire rope vibration isolator is perpendicular to the axial direction of the three-way equal-rigidity vibration isolator.
[0013] The beneficial effect of this technical solution is that: in this way, the longitudinal vibration isolator includes a wire rope vibration isolator, which is more conducive to obtaining a longitudinal vibration isolator with smaller stiffness, greater damping and lower natural frequency, and further improves the vibration isolation effect.
[0014] Optionally, the first connecting member includes a first connecting plate portion and a second connecting plate portion, the first connecting plate portion and the second connecting plate portion are vertically connected to form an L-shape, the first connecting plate portion is parallel to the axial direction of the three-way equal-stiffness vibration isolator, and the second connecting plate portion is located below the first connecting plate portion, the longitudinal vibration isolator and the optoelectronic pod are both connected to the first connecting plate portion, and the second connecting plate portion is connected to the three-way equal-stiffness vibration isolator.
[0015] The beneficial effect of this technical solution is that the first connecting member is an L-shaped plate, which, on the one hand, facilitates the connection of the longitudinal vibration isolator and the three-way equal-rigidity vibration isolator into one, and on the other hand, while ensuring that the first connecting member itself has good rigidity and is not prone to breakage and failure, the first connecting member has a smaller volume and weight, thereby reducing the space occupied by the optoelectronic pod vibration isolation unit and making the connection between the optoelectronic pod vibration isolation unit and the aircraft less likely to fail.
[0016] Optionally, the hanger module includes a cylindrical portion, a mounting gap is formed on a side wall of the cylindrical portion, and the longitudinal vibration isolator is located in the mounting gap.
[0017] The beneficial effect of this technical solution is that it reduces the length of the hanger module protruding outward from the hanger module, thereby reducing the volume occupied by the optoelectronic pod vibration isolation unit.
[0018] Optionally, the optoelectronic pod vibration isolation unit provided in the present application further includes a second vibration isolation module, and the hanger module is used to be connected to the aircraft through the second vibration isolation module.
[0019] The beneficial effect of this technical solution is that: in this way, the first vibration isolation module and the second vibration isolation module form a composite vibration isolation system with two-level vibration isolation, thereby improving the vibration isolation effect, and further improving the image quality and tracking accuracy of the optoelectronic pod.
[0020] Optionally, the second vibration isolation module includes a first elastic bushing, a second elastic bushing, a hanging member and a second connecting member. A connecting hole is formed on the hanger module. The axial direction of the connecting hole is parallel to the radial direction of the optoelectronic pod. The connecting hole is sleeved outside the first elastic bushing. The second connecting member fixes the second elastic bushing, the hanging member, the connecting hole and the second elastic bushing in sequence. The hanging member is used to be fixedly connected to the aircraft.
[0021] The beneficial effect of this technical solution is that: in this way, the first elastic bushing can play a vibration isolation role in the longitudinal direction, and the first elastic bushing and the second elastic bushing can both play a vibration isolation role in the lateral direction.
[0022] Optionally, the optoelectronic pod vibration isolation unit provided in the present application includes a plurality of second vibration isolation modules, and each of the second vibration isolation modules is evenly distributed in the circumferential direction of the optoelectronic pod.
[0023] The beneficial effect of this technical solution is that it increases the lifting points between the aircraft and the optoelectronic pod vibration isolation unit, improves stability, and further improves the vibration isolation effect.
[0024] Another aspect of the present application provides an aircraft system, including an aircraft and the optoelectronic pod vibration isolation unit provided in the present application, wherein the aircraft is fixedly connected to the hanger module.
[0025] The technical solution provided by this application can achieve at least one of the following beneficial effects:
[0026] The optoelectronic pod vibration isolation unit and aircraft system provided by the present application, when in use, the aircraft, the hanger module, the first vibration isolation module and the optoelectronic pod are connected in sequence, the vibration of the aircraft is transmitted to the first vibration isolation module through the hanger module, the longitudinal vibration isolation is achieved by the longitudinal vibration isolation member, and the lateral vibration isolation is achieved by the three-way equal-rigidity vibration isolator. In this way, the longitudinal vibration isolation member with appropriate stiffness, damping and natural frequency can be selected according to the requirements for the longitudinal vibration attenuation rate, which is conducive to using the longitudinal vibration isolation member of suitable volume and weight while ensuring the longitudinal vibration isolation effect. In addition, since the three-way equal-rigidity vibration isolator has a high lateral stiffness, it can provide a better stabilization effect, so that the optoelectronic pod vibration isolation unit is not easy to shake.
[0027] The additional technical features and advantages of the present application will be more clearly explained in the following description, or can be understood through the specific practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS
[0028] In order to more clearly illustrate the technical solutions of the specific implementation methods of the present application, the following is a brief introduction to the drawings required for the description of the specific implementation methods. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.
[0029] Figure 1 A schematic diagram of the three-dimensional structure of an implementation of the optoelectronic pod vibration isolation unit provided in an embodiment of the present application;
[0030] Figure 2 A schematic diagram of the three-dimensional structure of an implementation of an optoelectronic pod provided in an embodiment of the present application;
[0031] Figure 3 A partial three-dimensional structural schematic diagram of an implementation manner of an optoelectronic pod vibration isolation unit provided in an embodiment of the present application;
[0032] Figure 4 A partial three-dimensional structural schematic diagram of an implementation manner of an optoelectronic pod vibration isolation unit provided in an embodiment of the present application;
[0033] Figure 5 A partial three-dimensional structural schematic diagram of an implementation manner of the optoelectronic pod vibration isolation unit provided in an embodiment of the present application.
[0034] Reference numerals:
[0035] 10. Lower hanging frame; 20. Second vibration isolation module;
[0036] 21. first elastic bushing; 22. nut;
[0037] 23. second elastic bushing; 24. screw;
[0038] 25. Hanging parts; 30. Upper hanging frame;
[0039] 40. A first vibration isolation module; 41. A first connecting member;
[0040] 42. Longitudinal vibration isolator; 43. Three-way equal stiffness vibration isolator;
[0041] 50. Photoelectric pod; 51. Flange;
[0042] 52. Outer frame; 53. Inner frame. DETAILED DESCRIPTION
[0043] The technical solution of the present application will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present application.
[0044] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.
[0045] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.
[0046] like Figures 1 to 5 As shown, one aspect of the present application provides an optoelectronic pod vibration isolation unit, comprising a hanger module, a first vibration isolation module 40 and an optoelectronic pod 50, wherein the hanger module is used to connect to an aircraft,
[0047] The first vibration isolation module 40 includes a longitudinal vibration isolation member 42, a three-dimensional equal-rigidity vibration isolator 43 and a first connecting member 41. The first connecting member 41 and the optoelectronic pod 50 are both fixedly connected to the top end of the longitudinal vibration isolation member 42. The bottom end of the longitudinal vibration isolation member 42 is fixedly connected to the hanger module. In the axial direction of the three-dimensional equal-rigidity vibration isolator 43, one end of the three-dimensional equal-rigidity vibration isolator 43 is fixedly connected to the hanger module, and the other end of the three-dimensional equal-rigidity vibration isolator 43 is fixedly connected to the first connecting member 41.
[0048] In the embodiment of the present application, the three-dimensional equal-rigidity vibration isolator 43 can also be called a three-dimensional equal-rigidity metal vibration isolator. It can be understood that although the longitudinal vibration isolator 42 and the three-dimensional equal-rigidity vibration isolator 43 are rigidly connected to the hanger module, and the longitudinal vibration isolator 42 and the three-dimensional equal-rigidity vibration isolator 43 are rigidly connected to the first connecting member 41, during use, the rigid structure will inevitably produce a slight elastic deformation due to vibration, and the vibration isolated by the longitudinal vibration isolator 42 and the three-dimensional equal-rigidity vibration isolator 43 includes the vibration transmitted by this slight elastic deformation.
[0049] The optoelectronic pod vibration isolation unit provided in the present application, when in use, the aircraft, the hanger module, the first vibration isolation module 40 and the optoelectronic pod 50 are connected in sequence, the vibration of the aircraft is transmitted to the first vibration isolation module 40 through the hanger module, the longitudinal vibration isolation is achieved by the longitudinal vibration isolation member 42, and the lateral vibration isolation is achieved by the three-way equal-rigidity vibration isolator 43. In this way, the longitudinal vibration isolation member 42 with appropriate stiffness, damping and natural frequency can be selected according to the requirements for the longitudinal vibration attenuation rate, which is conducive to using the longitudinal vibration isolation member 42 of suitable volume and weight while ensuring the longitudinal vibration isolation effect. In addition, since the three-way equal-rigidity vibration isolator 43 has a high lateral stiffness, it can provide a better stabilization effect, so that the optoelectronic pod vibration isolation unit is not easy to shake.
[0050] Optionally, the optoelectronic pod vibration isolation unit provided in the embodiment of the present application includes a plurality of the first vibration isolation modules 40, and the first vibration isolation modules 40 are evenly arranged in the circumferential direction of the optoelectronic pod 50. In this way, the first vibration isolation modules 40 can be used to perform longitudinal and transverse vibration isolation at multiple positions between the aircraft and the optoelectronic pod 50, thereby improving the measurement effect of the optoelectronic pod 50. In the embodiment of the present application, the number of the first vibration isolation modules 40 is 2 to 6, for example, the number of the first vibration isolation modules 40 can be 3, 4 or 5, etc. Preferably, the number of the first vibration isolation modules 40 is 4.
[0051] Optionally, the axial direction of each of the three-way equal-rigidity vibration isolators 43 is perpendicular to the axial direction of the optoelectronic pod 50 .
[0052] Optionally, the longitudinal vibration isolator 42 includes a wire rope vibration isolator, and the axial direction of the wire rope vibration isolator is perpendicular to the axial direction of the three-way equal stiffness vibration isolator 43. In this way, the longitudinal vibration isolator 42 includes a wire rope vibration isolator, which is more conducive to obtaining a longitudinal vibration isolator 42 with lower stiffness, greater damping and lower natural frequency, and further improves the vibration isolation effect. In the embodiment of the present application, the longitudinal vibration isolator 42 can also adopt a three-way equal stiffness vibration isolator.
[0053] Optionally, the first connecting member 41 includes a first connecting plate portion and a second connecting plate portion, the first connecting plate portion and the second connecting plate portion are vertically connected to form an L-shape, the first connecting plate portion is parallel to the axial direction of the three-way equal stiffness vibration isolator 43, the second connecting plate portion is located below the first connecting plate portion, the longitudinal vibration isolator 42 and the optoelectronic pod 50 are both connected to the first connecting plate portion, and the second connecting plate portion is connected to the three-way equal stiffness vibration isolator 43. Making the first connecting member 41 an L-shaped plate, on the one hand, facilitates the longitudinal vibration isolator 42 and the three-way equal stiffness vibration isolator 43 to be connected as one, and on the other hand, while ensuring that the first connecting member 41 itself has good stiffness and is not easy to break and fail, the first connecting member 41 has a smaller volume and weight, thereby reducing the space occupied by the optoelectronic pod vibration isolation unit, and making the connection between the optoelectronic pod vibration isolation unit and the aircraft less likely to fail. Of course, the first connecting member 41 can also be T-shaped, or the first connecting member 41 can be an L-shaped rod.
[0054] Optionally, the hanger module includes a cylindrical portion, and a mounting gap is formed on the side wall of the cylindrical portion, and the longitudinal vibration isolation member 42 is located in the mounting gap. This reduces the length of the hanger module protruding outward from the hanger module, thereby reducing the volume occupied by the optoelectronic pod vibration isolation unit. In the embodiment of the present application, when the hanger module includes an upper hanging frame 30 and a lower hanging frame 10 both of which are annular, the mounting gap is located between the upper hanging frame 30 and the lower hanging frame 10.
[0055] Optionally, the optoelectronic pod vibration isolation unit provided in the embodiment of the present application further includes a second vibration isolation module 20, and the hanger module is used to be connected to the aircraft through the second vibration isolation module 20. In this way, the first vibration isolation module 40 and the second vibration isolation module 20 form a composite vibration isolation system with two-stage vibration isolation, thereby improving the vibration isolation effect, and further improving the image quality and tracking accuracy of the optoelectronic pod 50.
[0056] Optionally, the second vibration isolation module 20 includes a first elastic bushing 21, a second elastic bushing 23, a hanging member 25 and a second connecting member. A connecting hole is formed on the hanger module, the axial direction of the connecting hole is parallel to the radial direction of the optoelectronic pod 50, the connecting hole is sleeved outside the first elastic bushing 21, and the second connecting member fixes and connects the second elastic bushing 23, the hanging member 25, the connecting hole and the second elastic bushing 23 in sequence, and the hanging member 25 is used to be fixedly connected to the aircraft. In this way, the first elastic bushing 21 can play a vibration isolation role in the longitudinal direction, and the first elastic bushing 21 and the second elastic bushing 23 can both play a vibration isolation role in the transverse direction. In the embodiment of the present application, the second connecting member is preferably a screw 24, which passes through the second elastic bushing 23, the hanging member 25, the connecting hole and the second elastic bushing 23 in sequence and is fixedly connected to the nut 22; the connecting hole is preferably a step hole, and the first elastic bushing 21 preferably has a step structure on the outer wall. After the connecting hole and the first elastic bushing 21 are matched, the relative position between the connecting hole and the first elastic bushing 21 is limited by the step structure; the first elastic bushing 21 and the second elastic bushing 23 are preferably made of rubber.
[0057] Optionally, the optoelectronic pod vibration isolation unit provided in the embodiment of the present application includes a plurality of second vibration isolation modules 20, and each of the second vibration isolation modules 20 is evenly distributed in the circumferential direction of the optoelectronic pod 50. This increases the number of lifting points between the aircraft and the optoelectronic pod vibration isolation unit, improves stability, and further improves the vibration isolation effect. In the embodiment of the present application, preferably, the optoelectronic pod vibration isolation unit includes an even number of second vibration isolation modules 20, and each of the second vibration isolation modules 20 is symmetrically arranged with a certain radial direction of the optoelectronic pod 50 as the axis.
[0058] Preferably, the optoelectronic pod 50 includes a flange 51, an outer frame 52 and an inner frame 53. The lugs of the flange 51 are connected to the longitudinal vibration isolators 42 by bolts, the outer frame 52 is connected to the bottom of the flange 51 by an azimuth axis, and is connected to the inner frame 53 by a pitch axis. This two-axis and two-frame design enables the optoelectronic pod 50 to have a wider field of view.
[0059] Another aspect of the present application provides an aircraft system, including an aircraft and an optoelectronic pod vibration isolation unit provided in an embodiment of the present application, wherein the aircraft is fixedly connected to the hanger module.
[0060] The aircraft system provided in the present application adopts the optoelectronic pod vibration isolation unit provided in the present application. When in use, the aircraft, the hanger module, the first vibration isolation module 40 and the optoelectronic pod 50 are connected in sequence, and the vibration of the aircraft is transmitted to the first vibration isolation module 40 through the hanger module. The longitudinal vibration isolation is achieved by the longitudinal vibration isolation member 42, and the lateral vibration isolation is achieved by the three-way equal-rigidity vibration isolator 43. In this way, the longitudinal vibration isolation member 42 with appropriate stiffness, damping and natural frequency can be selected according to the requirements for the longitudinal vibration attenuation rate, which is conducive to using the longitudinal vibration isolation member 42 of suitable volume and weight while ensuring the longitudinal vibration isolation effect. In addition, since the three-way equal-rigidity vibration isolator 43 has a high lateral stiffness, it can provide a better stabilization effect, so that the optoelectronic pod vibration isolation unit is not easy to shake.
[0061] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present application.
Claims
1. The photoelectric pod vibration isolation unit is characterized by: It includes a hanger module, a first vibration isolation module and an optoelectronic pod, wherein the hanger module is used to connect with the aircraft. The first vibration isolation module includes a longitudinal vibration isolation member, a three-way equal-rigidity vibration isolator and a first connecting member. The first connecting member and the optoelectronic pod are both fixedly connected to the top end of the longitudinal vibration isolation member, the bottom end of the longitudinal vibration isolation member is fixedly connected to the hanger module, one end of the three-way equal-rigidity vibration isolator is fixedly connected to the hanger module in the axial direction of the three-way equal-rigidity vibration isolator, and the other end of the three-way equal-rigidity vibration isolator is fixedly connected to the first connecting member.
2. The photoelectric pod vibration isolation unit according to claim 1, characterized in that: It comprises a plurality of the first vibration isolation modules, and the first vibration isolation modules are evenly arranged in the circumferential direction of the optoelectronic pod.
3. The photoelectric pod vibration isolation unit according to claim 2, characterized in that: The axial direction of each of the three-way equal-rigidity vibration isolators is perpendicular to the axial direction of the optoelectronic pod.
4. The photoelectric pod vibration isolation unit according to claim 1, characterized in that: The longitudinal vibration isolator comprises a wire rope vibration isolator, and the axial direction of the wire rope vibration isolator is perpendicular to the axial direction of the three-way equal-rigidity vibration isolator.
5. The optoelectronic pod vibration isolation unit according to claim 1, characterized in that: The first connecting member includes a first connecting plate portion and a second connecting plate portion, the first connecting plate portion and the second connecting plate portion are vertically connected to form an L-shape, the first connecting plate portion is parallel to the axial direction of the three-way equal-stiffness vibration isolator, the second connecting plate portion is located below the first connecting plate portion, the longitudinal vibration isolator and the optoelectronic pod are both connected to the first connecting plate portion, and the second connecting plate portion is connected to the three-way equal-stiffness vibration isolator.
6. The photoelectric pod vibration isolation unit according to claim 1, characterized in that: The hanger module includes a cylindrical portion, a mounting gap is formed on a side wall of the cylindrical portion, and the longitudinal vibration isolator is located in the mounting gap.
7. The optoelectronic pod vibration isolation unit according to any one of claims 1 to 6, characterized in that: It also includes a second vibration isolation module, and the hanger module is used to be connected to the aircraft through the second vibration isolation module.
8. The photoelectric pod vibration isolation unit according to claim 7, characterized in that: The second vibration isolation module includes a first elastic bushing, a second elastic bushing, a hanging member and a second connecting member. A connecting hole is formed on the hanger module. The axial direction of the connecting hole is parallel to the radial direction of the optoelectronic pod. The connecting hole is sleeved outside the first elastic bushing. The second connecting member fixes the second elastic bushing, the hanging member, the connecting hole and the second elastic bushing in sequence. The hanging member is used to be fixedly connected to the aircraft.
9. The photoelectric pod vibration isolation unit according to claim 8, characterized in that: It comprises a plurality of second vibration isolation modules, and each of the second vibration isolation modules is evenly distributed in the circumferential direction of the optoelectronic pod.
10. An aircraft system, characterized in that It comprises an aircraft and the optoelectronic pod vibration isolation unit according to any one of claims 1 to 9, wherein the aircraft is fixedly connected to the hanger module.
Citation Information
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