Airborne high-definition video recording system

Abstract

The invention provides an airborne high-definition video recording system, and belongs to the technical field of aircraft photoelectric detection and tracking, and the airborne high-definition video recording system specifically comprises a pod end and a cabin end, the pod end is located outside an aircraft, and the pod end and the cabin end are connected through a wireless communication link; the pod end comprises a photoelectric imaging subsystem, a satellite positioning subsystem, an information processing subsystem, a power supply subsystem and an uplink radio station; the photoelectric imaging subsystem is used for carrying out video shooting and tracking on a target, the satellite positioning subsystem is used for accurately positioning an aerial carrier, the information processing subsystem is used for controlling the working state of the system, controlling the photoelectric imaging subsystem to work and carrying out compression processing and storage on video data, and the cabin end comprises a downlink radio station and a display control device. The display and control device provides a display and control interface and control keys for a pilot to operate the pod end, and the pod end and the cabin end communicate through the uplink radio station and the downlink radio station. And remote, multi-angle and high-definition video recording is realized.

Description

Technical Field

[0001] The present application relates to the field of aircraft optoelectronic detection and tracking, and in particular to an airborne high-definition video recording system. Background Art

[0002] The accompanying flight video recording system is an airborne optoelectronic detection and tracking system that integrates multiple sensors such as television and infrared. It is interconnected with the flying aircraft to realize the identification and verification of the target, and realize quick reporting according to the multi-angle visualization requirements.

[0003] The current means of recording flight escort videos all use handheld commercial digital cameras or head-mounted sports cameras. It is difficult to capture the target stably, the effective distance is very limited, and the quality of the image / video evidence obtained is very poor, which cannot meet the analysis requirements of the design department, flight test department and pilots. Summary of the invention

[0004] In view of this, the present application provides an airborne high-definition video recording system to solve the problems of existing accompanying flight video recording methods, such as difficulty in stably capturing targets, very limited effective distance, and poor quality of acquired image / video evidence. It realizes long-distance, multi-angle, high-definition video recording, and is simple to operate, install and maintain.

[0005] The present application provides an airborne high-definition video recording system that adopts the following technical solutions:

[0006] An airborne high-definition video recording system comprises a pod end and a cockpit end, wherein the pod end is located outside the aircraft, and the pod end and the cockpit end are connected via a wireless communication link;

[0007] The pod end includes an optoelectronic imaging subsystem, a satellite positioning subsystem, an information processing subsystem, a power supply subsystem and an uplink radio station;

[0008] The optoelectronic imaging subsystem is used to shoot and track the target, the satellite positioning subsystem is used to accurately locate the carrier, the information processing subsystem is used to control the system working state, control the operation of the optoelectronic imaging subsystem, compress and store the video data, the power subsystem is used to provide various working power supplies for other subsystems on the pod end, and the uplink radio is used to transmit video recordings and system working state information to the cockpit end;

[0009] The cockpit end includes a downlink radio and a display and control device. The downlink radio is used to transmit the pilot's operating control instructions to the pod end. The display and control device is used to display the video acquired by the optoelectronic imaging subsystem and provide the pilot with a display and control interface and control buttons for operating the pod end.

[0010] Optionally, the uplink radio station and the downlink radio station realize data interaction between the cockpit end and the pod end through wireless communication.

[0011] Optionally, the display and control device is an electronic flight kneeboard.

[0012] Optionally, the optoelectronic imaging subsystem includes a front-view component with a stable platform, two left-view components, two right-view components and an infrared component, wherein the front-view component, the left-view component and the right-view component are all television sensors, the front-view component (4), the left-view component and the right-view component use visible light television bands for target detection, the infrared component uses long-wave infrared bands for target detection, the front-view component is used for detailed inspection and shooting with a small field of view, and the two left-view components, the two right-view components and the infrared component are used for scene monitoring with a large field of view.

[0013] Optionally, the forward-view component is installed at the head of the front compartment section of the pod, the stabilizing platform adopts a rolling structure, the two left-view components are distributed front and back along the flight direction of the carrier aircraft, and the two right-view components are distributed front and back along the flight direction of the carrier aircraft.

[0014] Optionally, the airborne high-definition video recording system is used to be mounted on an aircraft with missiles, the pod end is installed at the hanging point of one of the missiles, the outer shell shape of the pod end is consistent with the appearance of the missile, the optoelectronic imaging subsystem is in the front cabin section of the pod end, the power supply subsystem, satellite positioning subsystem, uplink radio and information processing subsystem are in the middle cabin section, and a data link antenna is provided on the tail cabin section of the pod end.

[0015] Optionally, the pod end is installed on the aircraft through a simulated hair guide frame cabin, and the electrical interface and mechanical interface of the pod end are located on the simulated hair guide frame cabin.

[0016] In summary, this application includes the following beneficial technical effects:

[0017] The airborne high-definition video recording system of the present application overcomes the problems of existing video recording methods, such as difficulty in stably capturing targets, very limited effective distance, and poor quality of acquired image / video evidence. It can realize long-distance, multi-angle, high-definition video recording, and is simple to operate, install and maintain. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, 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 application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0019] Figure 1This is a block diagram of the airborne high-definition video recording system for this application;

[0020] Figure 2 This is the structural block diagram of the pod end of this application;

[0021] Figure 3 This is a structural block diagram of the optoelectronic imaging subsystem of this application.

[0022] Explanation of the reference numerals: 1. pod end; 11. optoelectronic imaging subsystem; 12. satellite positioning subsystem; 13. information processing subsystem; 14. power supply subsystem; 15. uplink radio; 16. cabin structure subsystem; 17. satellite antenna; 18. data link antenna; 19. front cabin section; 1010. middle cabin section; 1011. tail cabin section; 2. cockpit end; 21. downlink radio; 22. electronic flight kneeboard; 3. simulated launcher cabin; 4. forward-looking component; 41. forward-looking camera; 42. stabilizing platform; 5. left-looking component L1; 6. left-looking component L2; 7. right-looking component R1; 8. right-looking component R2; 9. infrared component. DETAILED DESCRIPTION

[0023] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0024] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0025] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. 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 merely illustrative. Based on the present application, it should be understood by those skilled in the art that an 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. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0026] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The illustrations only show the components related to the present application rather than being drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed at will, and the component layout may also be more complicated.

[0027] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects described may be practiced without these specific details.

[0028] An embodiment of the present application provides an airborne high-definition video recording system.

[0029] like Figures 1 to 3 As shown, an airborne high-definition video recording system includes a pod end 1 and a cockpit end 2, wherein the pod end 1 is located outside the aircraft, and the pod end 1 and the cockpit end 2 are connected via a short-range wireless communication link.

[0030] The pod end 1 includes an optoelectronic imaging subsystem 11, a satellite positioning subsystem 12, an information processing subsystem 13, a power supply subsystem 14, an uplink radio 15 and a pod structure subsystem 16; wherein the pod structure subsystem 16 is the physical structure of the pod section.

[0031] The optoelectronic imaging subsystem 11 is used to take video and track the target, the satellite positioning subsystem 12 is used to accurately locate the carrier, the information processing subsystem 13 is used to control the system working state, control the operation of the optoelectronic imaging subsystem 11, compress and store the video data, the power subsystem 14 is used to provide various working power supplies for the operation of other subsystems of the pod end 1, and the uplink radio 15 is used to transmit the video recording video and system working state information to the cockpit end 2;

[0032] The cockpit end 2 includes a downlink radio 21 and a display and control device. The downlink radio 21 is used to transmit the pilot's operating control instructions for the pod end 1 to the pod end 1. The display and control device is used to display the video acquired by the optoelectronic imaging subsystem 11 and provide the pilot with a display and control interface and control buttons for operating the pod end 1.

[0033] The airborne high-definition video recording system is used to be mounted on an aircraft with missiles. The pod end 1 is installed at the hanging point of one of the missiles to replace the original missile. The outer shell shape of the pod end 1 is consistent with the appearance of the missile. The optoelectronic imaging subsystem 11 is in the front cabin section 19 of the pod end 1, the power subsystem 14, the satellite positioning subsystem 12, the uplink radio 15 and the information processing subsystem 13 are in the middle cabin section 1010 of the pod end 1. The front cabin section 19 of the pod end 1 is also provided with a satellite antenna 17, and the tail cabin section 1011 is provided with a data link antenna 18.

[0034] The pod end 1 is installed on the aircraft through the simulated launcher bay 3, and the electrical interface and mechanical interface of the pod end 1 are located on the simulated launcher bay 3. The simulated launcher bay 3 has the same structure as the launcher bay of the original missile.

[0035] The uplink radio station 15 and the downlink radio station 21 realize data interaction between the cockpit end 2 and the pod end 1 through wireless communication.

[0036] The optoelectronic imaging subsystem 11 includes a forward-view component 4 with a stable platform 42, two left-view components, two right-view components and an infrared component 9, the infrared component 9 includes a left-view infrared component and a right-view infrared component, the forward-view component 4, the left-view component and the right-view infrared component are all television sensors, using the visible light television band for target detection, and the infrared component uses the long-wave infrared band for target detection, and the long-wave infrared refers to the section with a wavelength range of 8-14 microns; the forward-view component 4 is used for small-field detailed inspection and shooting, and the two left-view components and the two right-view components and the infrared component 9 are used for large-field scene monitoring. When working, the onboard high-definition video recording system first determines that the target is located at the left and right positions of the carrier aircraft, and then selects the spliced ​​large-field image of the corresponding side, and quickly finds the target through large-field scene monitoring. The pilot sends a command at the cockpit end 2 to adjust the aiming line of the forward-view component 4, or the information processing subsystem 13 sends a command to adjust the aiming line of the forward-view component 4, so as to have both small-field detailed inspection and shooting and large-field scene monitoring functions. The front view component 4 includes a front view camera 41 and a stabilizing platform 42; the two left view components are respectively a left view component L1 5 and a left view component L2 6; the two right view components are respectively a right view component R1 7 and a right view component R2 8.

[0037] The forward-looking component 4 is installed at the head of the front compartment section 19 of the pod. The stabilizing platform 42 adopts a two-axis two-frame rolling structure, which can achieve a pitch range coverage of no less than ±60 degrees. At the same time, the mechanical stabilization + electronic image stabilization method is adopted to greatly improve the accuracy of the stabilizing platform 42, thereby ensuring that the captured video and recorded video are more stable and clear.

[0038] The two left-view components are on the left side of the pod and are distributed front and back along the flight direction of the carrier aircraft. The two right-view components are on the right side of the pod and are distributed front and back along the flight direction of the carrier aircraft. The field of view of the two left-view components is 70-90 degrees in total, and 80 degrees can be selected. The two right-view components are 70-90 degrees in total, and 80 degrees can be selected. The two left-view components, the two right-view components and the side-view infrared component 9 all adopt a large-field-of-view fixed-focus camera design method and are fixedly installed on one side of the pod. Through reasonable layout, they can jointly detect an azimuth range coverage of not less than ±75 degrees, thereby greatly expanding the scene monitoring range of the pod. At the same time, the combined detection method of television and long-wave infrared can further reduce the false alarm rate of target detection.

[0039] The information processing subsystem 13 of the pod end 1 can process 3 channels of high-definition television color video images and 1 channel of high-definition infrared video images at the same time, and use the H.265 algorithm to compress and record 5 channels of video data at the same time, and has the functions of target recognition, image tracking processing and electronic image stabilization; the information processing subsystem 13 of the pod end 1 has a detachable large-capacity electronic disk, which is convenient for subsequent query, reading and playback of video recording data; specifically, the information processing subsystem 13 of the pod end 1 mainly includes a system control board, an image processing board and a compression recording board, wherein the system control board is mainly used to manage the system working state and perform relevant information solution, the image processing board is mainly used to realize the functions of target detection, tracking, electronic image stabilization, image derotation, etc., and the compression recording board mainly realizes the parallel compression recording of multiple channels of video, and collects and records the system bus data. The electronic disk is used to store video recording videos and system working parameters, and is designed with a quick-release mechanism and a hatch door at the corresponding position of the cabin section 1010 of the pod end 1, which supports the quick removal and unloading of the electronic disk, and facilitates the subsequent data export and further processing of the data.

[0040] The uplink radio 15 of the pod end 1 and the downlink radio 21 of the cockpit end 2 adopt OFDM modulation technology and have an adaptive frequency selection function, so as to realize non-line-of-sight wireless video and data transmission.

[0041] The display and control device is an electronic flight kneeboard 22. The electronic flight kneeboard 22 mainly includes a CPU module, a display screen, a touch screen, buttons, a battery and peripherals. The CPU module includes LPDDR and FALSH storage modules, and the peripherals include a USB interface, an external charger, etc. In order to adapt to the small cockpit environment, the cockpit end 2 downlink data link radio is also built into the electronic flight kneeboard 22 through an integrated design. The electronic flight kneeboard 22 provides a human-machine interface and interactive means for the pilot in the cockpit through the matching application software.

[0042] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An airborne high-definition video recording system, characterized in that: It comprises a pod end (1) and a cockpit end (2), wherein the pod end (1) is located outside the aircraft, and the pod end (1) and the cockpit end (2) are connected via a wireless communication link; The pod end (1) comprises an optoelectronic imaging subsystem (11), a satellite positioning subsystem (12), an information processing subsystem (13), a power supply subsystem (14) and an uplink radio station (15); The optoelectronic imaging subsystem (11) is used for video recording and tracking of the target, the satellite positioning subsystem (12) is used for accurately positioning the carrier aircraft, the information processing subsystem (13) is used for controlling the system working state, controlling the operation of the optoelectronic imaging subsystem (11), compressing and storing video data, the power supply subsystem (14) is used for providing various working power supplies for the operation of other subsystems of the pod end (1), and the uplink radio (15) is used for transmitting video recording and system working state information to the cockpit end (2); The cockpit end (2) comprises a downlink radio (21) and a display and control device, wherein the downlink radio (21) is used to transmit the pilot's operating control instructions for the pod end (1) to the pod end (1), and the display and control device is used to display the video acquired by the optoelectronic imaging subsystem (11) and provide a display and control interface and control buttons for the pilot to operate the pod end (1).

2. The airborne high-definition video recording system according to claim 1, characterized in that: The uplink radio station (15) and the downlink radio station (21) realize data interaction between the cockpit end (2) and the pod end (1) through wireless communication.

3. The airborne high-definition video recording system according to claim 1, characterized in that: The display and control device is an electronic flight kneeboard (22).

4. The airborne high-definition video recording system according to claim 1, characterized in that: The optoelectronic imaging subsystem (11) comprises a front-view component (4) with a stable platform (42), two left-view components, two right-view components and an infrared component (9), wherein the front-view component (4), the left-view component and the right-view component are all television sensors, the front-view component (4), the left-view component and the right-view component use visible light television bands for target detection, the infrared component (9) uses long-wave infrared bands for target detection, the front-view component (4) is used for small-field-of-view detailed inspection and shooting, and the two left-view components, the two right-view components and the infrared component (9) are used for large-field-of-view scene monitoring.

5. The airborne high-definition video recording system according to claim 4, characterized in that: The front view component (4) is installed at the head of the front compartment section (19) of the pod, the stabilizing platform (42) adopts a rolling structure, the two left view components are distributed front and back along the flight direction of the carrier aircraft, and the two right view components are distributed front and back along the flight direction of the carrier aircraft.

6. The airborne high-definition video recording system according to claim 1, characterized in that: The airborne high-definition video recording system is used to be mounted on an aircraft with missiles. The pod end (1) is installed at the hanging point of one of the missiles. The outer shell shape of the pod end (1) is consistent with the appearance of the missile. The optoelectronic imaging subsystem (11) is in the front cabin section (19) of the pod end (1). The power subsystem (14), the satellite positioning subsystem (12), the uplink radio (15) and the information processing subsystem (13) are in the middle cabin section (1010) of the pod end (1). The tail cabin section (1011) of the pod end (1) is provided with a data link antenna (18).

7. The airborne high-definition video recording system according to claim 6, characterized in that: The pod end (1) is installed on the aircraft via a simulated guide frame cabin (3); the electrical interface and the mechanical interface of the pod end (1) are located on the simulated guide frame cabin (3).

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