CN219623144U - Damping device suitable for filtering multiple vibration frequencies - Google Patents

Abstract

The utility model relates to a damping device suitable for filtering various vibration frequencies, which comprises an airplane switching frame, a platform switching piece and a plurality of hydraulic damping rods; the airplane switching frame is connected with the platform switching piece through a plurality of hydraulic damping rods. The utility model ensures the consistency of the structure of the photoelectric pod on different types of airplanes, has reasonable design and simple structure assembly, and is suitable for damping various vibration frequencies.

Description

Damping device suitable for filtering multiple vibration frequencies

Technical Field

The utility model belongs to the technical field of photoelectric pods, and particularly relates to a damping device for filtering multiple vibration frequencies of a photoelectric pod.

Background

An on-board optoelectronic pod is an optoelectronic device for airborne reconnaissance, typically mounted under the belly or wing of a vehicle, for precise searching, tracking and locking of targets by the vehicle and guiding precise guidance. Has the characteristics of flexibility, real-time accuracy, strong pertinence and the like. The real-time image is transmitted to the ground command post through wireless communication transmission, and meanwhile, the stored image is recorded, so that the capability of actively distinguishing a moving target in a continuously-changing environment of the carrier can be greatly improved. The photoelectric pod is generally provided with optical loads such as visible light and infrared, besides the quality of the optical loads, vibration on the carrier can enable imaging of the optical loads to generate image shift, so that imaging contrast of a system is poor, image blurring is caused, servo tracking precision is further affected, even a tracking target is lost, once resonance occurs, damage to the photoelectric loads is caused, and effective vibration isolation measures are required to ensure imaging quality and tracking precision of the photoelectric pod. The visual axis direction of the photoelectric task load is controlled not to deviate from the expected reconnaissance route and target no matter how the gesture and route change, so that the preset reconnaissance aim and reconnaissance effect are achieved.

The vibration received by the photoelectric pod during operation mainly comes from two parts, one part comes from a carrier, including vibration generated by the operation of an aircraft engine unit, vibration generated by the abrupt change of the aircraft route, speed, height and gesture, vibration caused by various atmospheric phenomena and aerodynamic phenomena such as flutter, turbulent flow and buffeting, vibration caused by air flow and low-frequency thermodynamic phenomena relative to an optical load window, and the other part comes from the photoelectric pod, including vibration caused by the operation of a focusing zoom, a dimming mechanism and the like in the optical load, and vibration caused by the swinging of an optical load frame, and the vibration caused by the optical load can reduce the vibration level to be very small through precise design, processing and assembly. Thus, the main source of vibration to which the optoelectronic pod is subjected is the environment of use, and the nature of vibration is mainly random vibration.

The photoelectric pod is often used on different types, different frequencies and different types of aircrafts, so that the problem of poor matching degree of a damping scheme is generally existed. The conventional means for controlling the image stabilization of the optoelectronic pod is to customize the damping scheme specifically for each type of aircraft. The problems of high difficulty in selecting a shock absorber are often caused by different vibration frequencies of various airplanes, different vibration excitation directions in the flight process and the like, each shock absorber scheme can be finally determined after long-time ground test selection and air test verification, and the problems of greatly increasing the production cost and the production time of the photoelectric pod in the matching process of the shock absorber scheme are necessarily caused.

Disclosure of Invention

The utility model aims to provide a damping device suitable for filtering various vibration frequencies.

In order to solve the technical problems, the damping device suitable for filtering various vibration frequencies comprises an airplane switching frame, a platform switching piece and a plurality of hydraulic damping rods; the airplane switching frame is connected with the platform switching piece through a plurality of hydraulic damping rods.

Further, the airplane switching frame is connected with the platform switching piece through a plurality of rubber shock absorbers;

the rubber shock absorber adopts an inflatable rubber shock absorber.

The aircraft adapter frame is connected with the platform adapter piece through a plurality of hydraulic damping rods distributed in the circumferential direction, and each rubber damper is inserted between every two adjacent hydraulic damping rods.

The airplane adapter rack is a semi-closed shell formed by an airplane adapter plate, a shell and a lower connecting plate with a central through hole, wherein the airplane adapter plate, the shell and the lower connecting plate are connected together; the top edge of the shell is fixedly connected with the airplane adapter plate, and the bottom edge of the shell is fixedly connected with the lower connecting plate; the platform adapter is embedded in the semi-closed shell, the upper end of the hydraulic damping rod is fixedly connected with the top end of the platform adapter, and the lower end of the hydraulic damping rod is fixedly connected with the lower connecting plate.

Each hydraulic damping rod is positioned between the platform adapter and the shell.

The rubber shock absorber is located between the platform adapter and the shell.

And the edges of the airplane adapter plate and the lower connecting plate are provided with rabbets.

The top end of the platform adapter is fixedly provided with an upper connecting plate, and the upper end of each hydraulic damping rod is fixedly connected with the upper connecting plate.

The top of the rubber shock absorber is fixedly connected with a suspension frame which is integrally connected below the upper connecting plate.

Compared with the prior art, the utility model has the following beneficial effects:

1. the two shock absorbers with different shock absorption principles are utilized for combined use, so that the consistency of the structure of the photoelectric pod on the aircraft with different types is ensured.

2. The two shock absorbers can independently adjust the shock absorbing capacity, are easy and convenient to operate, greatly save time for rectifying the shock absorbers, and ensure timeliness of the photoelectric pod.

3. On the basis of guaranteeing the use function, the compact design is realized, and the use purposes of small occupied space and convenient operation are achieved.

4. The airplane switching frame and the platform switching piece are used for semi-sealing the whole damping device, so that the dustproof and rainproof performances of the whole damping device are guaranteed.

The utility model has reasonable design and simple structure assembly, and is suitable for damping of various vibration frequencies. On the basis of convenient operation and reliability guarantee, the processing technology is simplified, the design cost is saved, and the economic performance of the photoelectric pod is guaranteed.

Drawings

The utility model is described in further detail below with reference to the drawings and the detailed description.

Fig. 1 is a perspective view of a structural hidden housing of the present utility model.

Fig. 2 is a perspective view of the present utility model in partial cutaway.

Fig. 3 is a cross-sectional view of the present utility model.

Fig. 4 is a cross-sectional view taken along A-A of fig. 3.

In the figure, an airplane adapter plate 11, a shell 12, a lower connecting plate 13, a platform adapter piece 2, an upper connecting plate 21, a suspension 22, a hydraulic shock absorption damping rod 3 and a rubber shock absorber 4; 51. screw, 52, screw, 53, nut; 54. and (5) a screw.

Detailed Description

The present utility model will now be described in further detail with reference to the drawings and examples, it being understood that the specific examples described herein are intended to illustrate the utility model only and are not intended to be limiting. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present utility model are shown in the drawings.

In the description of the present utility model, unless explicitly stated and limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements or interaction relationship between the two elements. The specific meaning of the above terms in the present utility model can be understood in detail by those skilled in the art.

In the present utility model, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below", "beneath" the second feature includes the first feature being "directly under" and obliquely below "the second feature, or simply indicating that the first feature is less level than the second feature.

In the description of the present embodiment, the terms "upper", "lower", "left", "right", and the like are orientation or positional relationships based on those shown in the drawings, for convenience of description and simplicity of operation, and are not meant to indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the utility model. Furthermore, the terms "first," "second," and the like, are used merely for distinguishing between descriptions and not for distinguishing between them.

As shown in fig. 1 to 4, the vibration damping device for filtering various vibration frequencies of the present utility model includes an airplane adapter bracket, a platform adapter 2, a plurality of hydraulic vibration damping rods 3 and a plurality of rubber dampers 4; taking four hydraulic damping rods 3 and four rubber dampers 4 as examples, the airplane adapter frame is connected with the platform adapter 2 through four hydraulic damping rods 3 distributed in the circumferential direction and four rubber dampers 4 inserted between the four hydraulic damping rods 3; the aircraft switching frame is fixedly connected with the aircraft body, and the platform switching piece 2 is fixedly connected with the photoelectric pod.

The airplane adapter frame is a semi-closed shell formed by an airplane adapter plate 11, a shell 12 and a lower connecting plate 13 with a central through hole, wherein the airplane adapter plate 11, the shell 12 and the lower connecting plate 13 are connected together; the shell 12 is cylindrical, the top edge of the shell is fixedly connected with the airplane adapter plate 11 through a plurality of screws, and the bottom edge of the shell is fixedly connected with the lower connecting plate 13 through a plurality of screws 51; the edges of the airplane adapter plate 11 and the lower connecting plate 13 are provided with rabbets so as to ensure the overall rigidity of the device.

An upper connecting plate 21 is fixed at the top end of the platform adapter 2, and the upper connecting plate 21 is fixedly connected with the platform adapter 2 through a screw 52; four hydraulic shock-absorbing damping rods 3 are positioned between the platform adapter 2 and the shell 12, the lower ends of the four hydraulic shock-absorbing damping rods are fixedly connected with the lower connecting plate 13 through nuts, and the upper ends of the four hydraulic shock-absorbing damping rods are fixedly connected with the upper connecting plate 21 through nuts 53.

The four rubber shock absorbers 4 are uniformly distributed between the platform adapter 2 and the shell 12 and are arranged between the four hydraulic shock absorption damping rods 3 in a penetrating way; the bottom of the rubber damper 4 is fixedly connected with the lower connecting plate 13 by a screw 54, and the top is fixedly connected with the suspension 22 integrally connected below the upper connecting plate 21 by a screw.

The hydraulic damping rod 3 can adjust bearing capacity, namely damping strength, and hydraulic damping is adjusted by adjusting a rotary screw at the middle part of the damping rod, so that an ideal damping effect is achieved.

The rubber shock absorber 4 is an inflatable rubber shock absorber, and the internal inflation pressure can be adjusted through the lateral inflation knob so as to achieve the shock absorption effect.

The screw thread parts of all screws and nuts in the whole damping device are coated with a small amount of medium-strength screw thread glue so as to ensure the reliability of the damping device.

In order to ensure the stability of each angle of the photoelectric pod, the whole damping device is uniformly distributed and combined with the four rubber dampers 4 through the four hydraulic damping rods 3, and meanwhile, the four hydraulic damping rods 3 have the same damping capacity in adjusting and the four rubber dampers 4 have the same inflation pressure. Through adjusting the damping strength of each damping rod and the damper, the effect of stabilizing the nacelle in the running process of the aircraft is achieved, the accurate searching, tracking and locking of the target are ensured, and the accurate guidance is guided.

The utility model adopts two dampers with adjustable bearing capacity for combined use, so as to ensure collision caused by the change of the displacement of the dampers in the damping process, and enough space is reserved between the platform adapter piece 2 and the lower connecting plate 13, thereby ensuring the exertion of the capacity of the dampers, ensuring the use safety of the whole damping device, simultaneously considering confidentiality and tightness in the design of the damping device, and the lower connecting plate 13, the shell 12, the airplane adapter plate 11 and the platform adapter piece 2 semi-seal the whole damping device, ensuring the dustproof and rainproof performance of the whole damping device, and simultaneously ensuring the replacement of multiple types of airplanes, wherein the upper connecting plate 21 can be changed according to the requirement of a mechanical interface, thereby greatly facilitating the installation and reducing the cost. Namely, the damping scheme reduces the production cost and the production time of the optoelectronic pod.

Working principle: the utility model adopts two dampers with adjustable bearing capacity for combined use, the lower connecting plate 13 and the upper connecting plate 21 are connected by the two dampers, the platform adapter 2 and the upper connecting plate 21 are fixed by screws, the platform adapter 2 is connected with the photoelectric pod, the lower connecting plate 13 is fixedly connected with the shell 12 and the airplane adapter plate 11 to form a semi-sealed space, and the requirements of dust prevention and rain prevention are met while the damping effect of the damping device is ensured. Meanwhile, in order to ensure the stability of all angles of the photoelectric pod, the whole damping device is uniformly distributed and combined through 4 hydraulic damping rods 3 and 4 rubber dampers 4, and meanwhile, the 4 hydraulic damping rods 3 have the same damping capacity in adjusting and the 4 rubber dampers 4 have the same inflation pressure. The vibration absorption intensity of each vibration absorber is adjusted according to different types of the aircraft, different photoelectric pod placement positions and different vibration frequencies, so that the imaging quality and tracking precision of the photoelectric pod are ensured during the running of the aircraft, the accurate searching, tracking and locking of a target are ensured, and the accurate guidance is guided. The upper connecting plate can be changed according to the requirement of the mechanical interface, so that the installation is greatly facilitated, and the cost is reduced. Namely, the damping scheme reduces the production cost and the production time of the optoelectronic pod.

Preferably, all structural materials are made of aviation aluminum, so that the weight is reduced, and meanwhile, the rigidity is increased.

Claims (8)

1. The damping device suitable for filtering various vibration frequencies is characterized by comprising an airplane switching frame, a platform switching piece (2) and a plurality of hydraulic damping rods (3); the airplane switching frame is connected with the platform switching piece through a plurality of hydraulic damping rods; the airplane adapter frame is a semi-closed shell formed by an airplane adapter plate (11), a shell (12) and a lower connecting plate (13) with a central through hole, wherein the airplane adapter plate, the shell and the lower connecting plate are connected together; the top edge of the shell is fixedly connected with the airplane adapter plate, and the bottom edge of the shell is fixedly connected with the lower connecting plate; the platform adapter is embedded in the semi-closed shell, the upper end of the hydraulic damping rod is fixedly connected with the top end of the platform adapter, and the lower end of the hydraulic damping rod is fixedly connected with the lower connecting plate; each hydraulic shock absorption damping rod is positioned between the platform adapter and the shell.

2. The vibration-damping device for filtering multiple vibration frequencies according to claim 1, wherein the aircraft adapter is further connected to the platform adapter by a plurality of rubber dampers (4).

3. The vibration-damping device for filtering multiple vibration frequencies according to claim 2, wherein said rubber damper is an inflatable rubber damper.

4. The vibration damping device for filtering multiple vibration frequencies according to claim 2, wherein the aircraft adapter is connected to the platform adapter through a plurality of circumferentially distributed hydraulic damping rods, and each rubber damper is interposed between adjacent hydraulic damping rods.

5. The vibration-damping device of claim 2, wherein the rubber vibration damper is located between the platform adapter and the housing.

6. The damping device for filtering multiple vibration frequencies according to claim 1, wherein the edges of the airplane adapter plate and the lower connecting plate are provided with rabbets.

7. The damping device for filtering multiple vibration frequencies according to claim 1, wherein the top end of the platform adapter is fixed with an upper connecting plate (21), and the upper end of each hydraulic damping rod (3) is fixedly connected with the upper connecting plate (21).

8. The vibration-damping apparatus for filtering multiple vibration frequencies according to claim 5, wherein the top of the rubber damper is fixedly connected to a suspension (22) integrally connected under the upper connection plate.