Airborne photoelectric load external damping device with inertial navigation

Abstract

The airborne photoelectric load external vibration damping device with inertial navigation is suitable for installation of image acquisition equipment on a carrier, an electromechanical system and a controller are arranged on the carrier, the electromechanical system comprises a guide rail, the image acquisition equipment comprises an electronic cabin and a shell, the upper installation support is installed on the guide rail, and the lower installation support is installed on the shell. A first hole is formed in the central area; the shell is mounted on the bottom surface of the lower mounting bracket; one end of the shock absorber is mounted at the edge position of the lower mounting bracket, the other end of the shock absorber is movably mounted on the bottom surface of the upper mounting bracket, and the shock absorber can carry the transmitted vibration; the mounting plate is arranged above the upper mounting bracket and is connected with the lower mounting bracket through a supporting rod penetrating through the first hole; and the inertial navigation device is mounted on the top surface of the mounting plate, is electrically connected with the controller and the image acquisition equipment, and can acquire the position information of the image acquisition equipment, so that the image acquisition efficiency is improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of airborne auxiliary equipment, and particularly relates to an external vibration damping device for an airborne optoelectronic payload with an inertial navigation system. Background Art

[0002] With the rapid development of high-tech in various fields, the capabilities of large-scale aerial reconnaissance and aerial search have become increasingly important in modern society, such as forest fire prevention, target tracking, etc. An airborne optoelectronic payload, that is, an image acquisition device, is a core device for aerial reconnaissance and the main carrier for realizing reconnaissance, search, and monitoring. However, due to external vibrations during the flight of the carrier aircraft, image shift will occur in the imaging of the optoelectronic system, resulting in a decrease in the imaging contrast of the optoelectronic system, unclear images, a reduction in the image acquisition efficiency, and an impact on the tracking accuracy of the optoelectronic payload servo system, leading to the loss of the tracked target. In addition, if the external vibration of the carrier aircraft causes resonance of the optoelectronic payload, it will also cause serious damage to the optical system. Content of the Utility Model

[0003] In view of this, the external vibration damping device for an airborne optoelectronic payload with an inertial navigation system provided by the utility model ensures the image acquisition efficiency and improves the positioning accuracy of the optoelectronic payload.

[0004] An external vibration damping device for an airborne optoelectronic payload with an inertial navigation system is applicable to the installation of an image acquisition device on a carrier aircraft. An electromechanical system and a controller are provided on the carrier aircraft. The electromechanical system includes a guide rail, and the image acquisition device includes an electronic cabin and a housing, including,

[0005] An upper mounting bracket is mounted on the guide rail, and a first hole is provided in the central area;

[0006] A lower mounting bracket has its bottom surface mounted with the housing;

[0007] A shock absorber has one end mounted at the edge position of the lower mounting bracket and the other end movably mounted on the bottom surface of the upper mounting bracket, capable of absorbing the vibration transmitted by the carrier aircraft;

[0008] A mounting plate is placed above the upper mounting bracket and is connected to the lower mounting bracket through a support rod passing through the first hole;

[0009] An inertial navigation system is mounted on the top surface of the mounting plate and is electrically connected to the controller and the image acquisition device respectively, for collecting the position information of the image acquisition device.

[0010] Preferably, an adapter bottom plate is detachably mounted on the mounting plate, and the adapter bottom plate is used for fixing the inertial navigation system.

[0011] Preferably, bosses are symmetrically arranged on the side surface parallel to the center line of the lower mounting bracket, and the bosses are used for mounting the shock absorber.

[0012] Preferably, the number of the shock absorbers is 4.

[0013] Preferably, it also includes an M12 high-strength screw, one end of which is mounted on the bottom surface of the upper mounting bracket, and the other end is fixedly connected to the spring of the shock absorber.

[0014] Beneficial Effects

[0015] By adjusting the frequency of the vibration absorber, the photoelectric load is tested in flight, and the image quality during the flight is observed to determine the model of the vibration absorber, so that the photoelectric load vibration reduction can achieve the expected effect. The photoelectric load positioning effect is achieved by installing an inertial navigation system, and the inertial navigation system is directly installed on the lower mounting bracket. While reducing the vibration of the product, it can directly reduce the size of the photoelectric load, and can be adapted to inertial navigation systems of different sizes and specifications. The replacement of the inertial navigation system has the advantages of simple replacement and good openness. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0017] Figure 1 It is a three-dimensional diagram of the utility model;

[0018] Figure 2 The schematic diagram of setting up the transfer base plate is shown in FIG.

[0019] 1. Lower mounting bracket; 2. Upper mounting bracket; 3. Shock absorber; 4. Support rod; 5. Mounting plate; 6. Inertial navigation; 7. Adapter base plate; 11. Second hole; 21. First hole. DETAILED DESCRIPTION

[0020] The embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.

[0021] The following describes the embodiments of the present disclosure through specific specific examples. Those skilled in the art can easily understand other advantages and effects of the present disclosure from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all embodiments. The present disclosure can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present disclosure. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present disclosure, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present disclosure.

[0022] It should be noted that the following describes various aspects of the embodiments within the scope of the appended claims. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is illustrative only. Based on the present disclosure, those skilled in the art should understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using other structures and / or functionality in addition to one or more of the aspects described herein.

[0023] It should also be noted that the diagrams provided in the following embodiments only illustrate the basic concept of the present disclosure in a schematic manner. The diagrams only show the components related to the present disclosure, rather than being drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and ratio of each component in its actual implementation can be arbitrarily changed, and the component layout type may also be more complex.

[0024] In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the aspects can be practiced without these specific details.

[0025] As Figures 1 to 2 shown, the external vibration damping device of the airborne optoelectronic payload with an inertial navigation system 6 is applicable to the installation of an image acquisition device on an aircraft. An electromechanical system and a controller are provided on the aircraft. The electromechanical system includes a guide rail. The image acquisition device includes an electronic cabin and a housing, and includes:

[0026] An upper mounting bracket 2, for example, a flat plate with a square structure, is mounted on the guide rail, and a first hole 21 is opened in the central area;

[0027] A lower mounting bracket 1, for mounting the housing, preferably, is hung on the bottom surface of the lower mounting bracket 1;

[0028] The shock absorber 3 has one end mounted at the edge position of the lower mounting bracket 1 and the other end movably mounted on the bottom surface of the upper mounting bracket 2, and can absorb the vibration transmitted by the carrier aircraft. Specifically, due to the external vibration during the flight of the carrier aircraft being absorbed by the shock absorber 3, the occurrence of image shift, reduced imaging contrast, and unclear images in the imaging of the optoelectronic system is avoided;

[0029] The mounting plate 5 is placed above the upper mounting bracket 2 and is connected to the lower mounting bracket 1 through one end of the support rod 4 passing through the first hole 21. The other end of the support rod 4 is mounted on the bottom surface of the mounting plate 5. Preferably, the size of the mounting plate 5 is smaller than the size of the first hole 21 to prevent the mounting plate 5 from contacting the upper mounting bracket 2 and thus causing wear;

[0030] The inertial navigation 6 is mounted on the top surface of the mounting plate 5 and is electrically connected to the controller and the image acquisition device respectively, and is used to collect the position information of the image acquisition device, such as the longitude and latitude information and altitude information of the image acquisition device, and feedback it to the controller. When the controller receives the image data fed back by the image acquisition device at the same time, the two are fused through the fusion software, that is, the currently displayed image information includes longitude and latitude information and altitude information.

[0031] As a specific implementation manner provided in this case, as Figure 2 shown, a transfer bottom plate 7 is detachably mounted on the mounting plate 5. The transfer bottom plate 7 is used for fixing the inertial navigation 6, which is convenient for replacing inertial navigations 6 of different precision models. Generally, one inertial navigation 6 is equipped with one transfer bottom plate 7. When the inertial navigation 6 needs to be replaced, only the transfer bottom plate 7 needs to be replaced. For example, the transfer bottom plate 7 is mounted on the mounting plate 5 by means of a bolt assembly, and rapid replacement can be achieved.

[0032] As a specific implementation manner provided in this case, the number of shock absorbers is 4 and they are symmetrically distributed. For example, bosses are symmetrically arranged on the side surface parallel to the center line of the lower mounting bracket 1, and the bosses are used for mounting the shock absorbers.

[0033] As a specific implementation manner provided in this case, the upper mounting bracket 2 is used as the main load-bearing component. Considering the stability of the overall assembly, it also includes M12 type high-strength screws. Preferably, military standard M12 type screws are used. One end of it is mounted on the bottom surface of the upper mounting bracket 2, and the other end is fixedly connected to the spring of the shock absorber. Preferably, protrusions (not marked in the figure) are arranged at intervals on the bottom surface of the upper mounting bracket 2, and one end of the M12 type screw is mounted on the protrusions, and the protrusions are symmetrically arranged with the first hole as the center.

[0034] Furthermore, the shock absorber 3 adopts a metal shock absorber 3, and the center of gravity of the image acquisition device is consistent with the geometric center of the shock absorber 3 in the vertical direction.

[0035] Furthermore, a second hole 11 is provided in the central area of the lower mounting bracket 1 for accommodating the electronic cabin. Considering the actual installation situation, generally, the height of the electronic cabin is greater than the distance between the lower mounting bracket 1 and the upper mounting bracket 2. Therefore, the mounting plate 5 needs to be placed above the upper mounting bracket 2 to ensure that the mounting plate 5 does not contact the electronic cabin during the vibration absorption process of the shock absorber, and a wiring groove is provided on one side of the lower mounting bracket 1 accordingly.

[0036] As described above, it is only the specific implementation manner of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present disclosure should be covered by the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be subject to the protection scope of the claims.

Claims

1. An external vibration reduction device for an airborne optoelectronic payload with an inertial navigation system, suitable for the installation of an image acquisition device on a carrier, the carrier being provided with an electromechanical system and a controller, the electromechanical system comprising a guide rail, characterized in that: The image acquisition device includes an electronic compartment and a housing, including, An upper mounting bracket is mounted on the guide rail and has a first hole in the central area; A lower mounting bracket, the bottom surface of which is used to mount the housing; A shock absorber, one end of which is mounted on the edge of the lower mounting bracket and the other end of which is movably mounted on the bottom surface of the upper mounting bracket, capable of absorbing vibration transmitted by the carrier; A mounting plate, placed above the upper mounting bracket, connected to the lower mounting bracket via a support rod passing through the first hole; The inertial navigation system is installed on the top surface of the installation plate and is electrically connected to the controller and the image acquisition device respectively, so as to obtain the position information of the image acquisition device.

2. The external vibration damping device according to claim 1, characterized in that: The mounting plate is detachably mounted with a transfer base plate, and the transfer base plate is used for fixing the inertial navigation.

3. The external vibration damping device according to claim 1, characterized in that: Bosses are symmetrically arranged on the side surface parallel to the center line of the lower mounting bracket, and the bosses are used for mounting the shock absorber.

4. The external vibration damping device according to claim 3, characterized in that: The number of the shock absorbers is 4.

5. The external vibration damping device according to claim 4, characterized in that: It also includes an M12 high-strength screw, one end of which is mounted on the bottom surface of the upper mounting bracket, and the other end of which is fixedly connected to the spring of the shock absorber.

6. The external vibration damping device according to claim 5, characterized in that: The bottom surface of the upper mounting bracket is provided with projections at intervals, and one end of the screw is mounted on the projections.

7. The external vibration damping device according to claim 1, characterized in that: The vibration absorber is a metal vibration absorber.

8. The external vibration damping device according to claim 1, characterized in that: The center of gravity of the image acquisition device is consistent with the geometric center of the shock absorber in the vertical direction.

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