Large unmanned aerial vehicle meteorological detection plateau configuration

Abstract

The utility model relates to the technical field of meteorological detection, and discloses a large unmanned aerial vehicle meteorological detection plateau configuration, which comprises a nose external load arranged at a nose and in signal connection with a task data recorder through a combined navigation system, and the task data recorder is in signal connection with a control link; the machine head equipment cabin load is arranged in the machine head equipment cabin and is in signal connection with the control link; the nose radar cabin load is arranged in the nose radar cabin and is in signal connection with the task data recorder through the universal interface unit; the belly load is arranged at the front section or the middle section of the belly and is in signal connection with the task data recorder through the universal interface unit; and the sounding pod load is arranged in the sounding pod hung below the wings and is in signal connection with the task data recorder through the universal interface unit. Meteorological monitoring loads are arranged on the nose, the nose cabin, the belly and the lower hanging points of the wings, the carrying positions of the loads do not interfere with one another, and the loads can be independently controlled, so that the usability, the reliability and the expandability are high.

Description

Technical Field

[0001] The utility model relates to the technical field of meteorological detection, and more specifically, to a plateau configuration for meteorological detection by a large unmanned aerial vehicle (UAV). Background Art

[0002] The main environment of the plateau is harsh, with drastic changes and difficult survival. Moreover, the terrain around the plateau is steep, the climate is complex and diverse, which makes it difficult to conduct land-based meteorological observations on the plateau.

[0003] At present, most of the UAVs equipped with meteorological monitoring payloads are small and medium-sized UAVs, which are difficult to adapt to the flight environment with a vast area and complex conditions in the plateau environment, and cannot achieve meteorological monitoring with a long flight range. Multiple meteorological monitoring data need to be obtained by flying multiple times and replacing different payloads, resulting in low monitoring efficiency. At the same time, in order to reduce the volume of the UAV, multiple payloads in small and medium-sized UAVs usually share one or two common interfaces for control connection. Although the number of control connections can be reduced, the payloads and their control connections need to be frequently replaced between multiple flights, which also reduces the monitoring efficiency.

[0004] In summary, how to provide a plateau configuration for meteorological detection by a UAV with high monitoring efficiency is an urgent problem to be solved by those skilled in the art at present. Summary of the Utility Model

[0005] In view of this, the purpose of the utility model is to provide a plateau configuration for meteorological detection by a UAV, which is provided with meteorological monitoring payloads at the nose, nose cabin, belly and underwing suspension points. The mounting positions of each payload do not interfere with each other, and each payload can be independently controlled, with strong usability, reliability and scalability.

[0006] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0007] A plateau configuration for meteorological detection by a large UAV includes:

[0008] An external nose payload, which is arranged at the nose of the UAV and is signal-connected to the mission data recorder through a combined navigation system, and the mission data recorder is signal-connected to the control link;

[0009] A nose equipment cabin payload, which is arranged in the nose equipment cabin and is signal-connected to the control link;

[0010] A nose radar cabin payload, which is arranged in the nose radar cabin and is signal-connected to the mission data recorder through a general interface unit;

[0011] A belly payload, which is arranged at the front section or middle section of the belly and is signal-connected to the mission data recorder through the general interface unit;

[0012] The sounding pod payload is arranged in the sounding pod hung under the wing, and is connected to the mission data recorder signal through the universal interface unit.

[0013] Preferably, the nose external load includes a route weather detector, and the route weather detector is connected to the integrated navigation system signal via an RS-422 interface.

[0014] Preferably, the nose equipment bay payload includes a visible light high-resolution digital imaging system, and the visible light high-resolution digital imaging system is connected to the control link signal via an HD-SDI interface.

[0015] Preferably, the nose radar cabin payload includes a weather radar, and the weather radar can be connected to the universal interface unit signal through an RS-422 interface, and the weather radar is connected to the mission data recorder signal through a Camera Link interface.

[0016] Preferably, the belly load includes an optoelectronic spherical cabin load located at the front section of the belly and a visible light CCD cabin load located at the middle section of the belly, and the belly load is connected to the universal interface unit signal via an RS-422 interface.

[0017] Preferably, the photoelectric cabin load includes an airborne temperature and humidity profiler or a visible infrared spectrometer, and the photoelectric cabin load is installed in the photoelectric cabin through a transfer beam, and the photoelectric cabin load is bolted to the transfer beam.

[0018] Preferably, the visible light CCD cabin payload includes a millimeter wave cloud detection radar or an aerosol lidar, and the visible light CCD cabin payload can be connected to the universal interface unit signal through a Camera Link interface.

[0019] Preferably, when the belly load exceeds the surface of the aircraft body, a fairing is provided outside the belly load, and the fairing is used to reduce the flow resistance at the belly load.

[0020] The large-scale UAV with plateau weather detection configuration provided by the utility model has weather monitoring payloads installed on the nose, nose cabin, belly and underwing hanging points. The loading positions of the various payloads do not interfere with each other, and multiple weather monitoring data can be obtained in one flight, with high monitoring efficiency.

[0021] The nose, nose compartment, belly and underwing attachment points can all carry different types of payloads according to different monitoring tasks. The payloads in the same installation position can be quickly replaced through co-location, which has strong applicability.

[0022] Each load can be independently controlled. The operating state of the loads that are not replaced will not be affected by the replaced load. It can be quickly replaced to a position with the same communication state in case of a communication failure at a certain position, and the system has strong reliability and scalability. Brief Description of the Drawings

[0023] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only the embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on the provided drawings.

[0024] Figure 1 It is a schematic structural diagram of a specific embodiment of the high-altitude configuration for meteorological detection of large unmanned aerial vehicles provided by the present invention;

[0025] Figure 2 It is a schematic diagram of signal connection for the high-altitude configuration of large unmanned aerial vehicle meteorological detection;

[0026] Figure 3 It is an assembly schematic diagram of the load in the nose radar compartment.

[0027] Figures 1-3 Where:

[0028] 1 - External load on the nose; 2 - Load in the nose equipment compartment; 3 - Load in the nose radar compartment; 4 - Load in the optoelectronic sphere compartment; 5 - Load in the visible light CCD compartment; 6 - Radiosonde pod load; 7 - Mission data recorder; 8 - General interface unit; 9 - Control link, 10 - Integrated navigation system. Detailed Embodiment

[0029] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present invention.

[0030] The core of the present invention is to provide a high-altitude configuration for unmanned aerial vehicle meteorological detection, with meteorological monitoring loads provided at the nose, nose compartment, belly, and wing suspension points. The mounting positions of the loads do not interfere with each other, and each load can be independently controlled, with strong usability, reliability, and scalability.

[0031] The high-altitude configuration for large unmanned aerial vehicle meteorological detection provided by the present invention includes:

[0032] The nose external load 1 is installed at the nose of the UAV. It is signal-connected to the mission data recorder 7 through the integrated navigation system 10, and the mission data recorder 7 is signal-connected to the control link 9.

[0033] The nose equipment compartment load 2 is installed in the nose equipment compartment. It is signal-connected to the control link 9.

[0034] The nose radar compartment load 3 is installed in the nose radar compartment. It is signal-connected to the mission data recorder 7 through the general interface unit 8.

[0035] The belly load is installed in the front section or the middle section of the belly. It is signal-connected to the mission data recorder 7 through the general interface unit 8.

[0036] The sounding pod load 6 is installed in the sounding pod suspended under the wing. It is signal-connected to the mission data recorder 7 through the general interface unit 8.

[0037] Please refer to Figure 1 , there is no obstruction in the range of ±90° in the forward direction of the nose and ±90° in the course direction of the UAV's nose, which can simultaneously meet the detection field of view requirements of the nose loads such as the nose external load 1, the nose equipment compartment load 2, and the nose radar compartment load 3. The above-mentioned nose loads may include route meteorological detectors, visible light high-resolution imaging systems, meteorological radars, etc. Their specific types and models are determined according to the actual detection task needs and will not be elaborated here.

[0038] Regarding the control connection methods of different types of nose loads, since the nose external load 1 is close to the integrated navigation system 10 in front of the nose, the nose external load 1 can be signal-connected to the mission data recorder 7 through the integrated navigation system 10, and then signal-connected to the control link 9 through the mission data recorder 7.

[0039] The nose equipment compartment load 2 and the nose radar compartment load 3 are respectively installed in the nose equipment compartment and the nose radar compartment. Considering issues such as the installation space of the UAV's nose compartment and the layout of the UAV's control link, the nose equipment compartment load 2 can be directly signal-connected to the control link 9, while the nose radar compartment load 3 is mostly signal-connected to the mission data recorder 7 through the general interface unit 8, and then signal-connected to the control link 9 through the mission data recorder 7.

[0040] The specific connection methods of the signal connections among the nose external load 1 and the integrated navigation system 10, the nose equipment compartment load 2 and the control link 9, and the nose radar compartment load 3 and the general interface unit 8, such as the serial data interface standard and the measurement and control bandwidth, are determined with reference to the existing technology according to factors such as the actual load type.

[0041] There are no obstructions in the space under the belly of the UAV. The maximum detection range of the belly payloads is within ±45°, and it is not affected by the UAV's own structure, adjacent payloads, or the radiosonde pod suspended under the wing. Therefore, it can meet the detection field-of-view requirements for two types of belly payloads (front belly and middle belly), nose payloads, and external payloads when installed simultaneously.

[0042] Payloads at the front of the belly are mostly set as electro-optical pod payloads such as airborne temperature and humidity profilers or visible and infrared spectrometers 4. Payloads in the middle of the belly are mostly set as visible light CCD pod payloads such as aerosol lidars or millimeter-wave cloud radars 5. The specific types of electro-optical pod payloads 4 and visible light CCD pod payloads 5 can be determined according to the needs of the detection task.

[0043] Affected by the control link layout of the UAV, the belly payloads are signal-connected to the mission data recorder 7 through the general interface unit 8, and then signal-connected to the control link 9 through the mission data recorder 7. The specific connection method between the belly payloads and the general interface unit 8, such as the serial data interface standard and measurement and control bandwidth, is determined with reference to existing technologies according to factors such as the actual payload type.

[0044] The radiosonde pod payload 6 is installed in the radiosonde pod suspended under the wing, usually at the 5th and 6th suspension points of the wing. Since it is far from the fuselage and other payloads, it is not affected by other payloads. Since the radiosonde pod payload 6 is set far from the control link 9, it is usually set that the radiosonde pod payload 6 is signal-connected to the mission data recorder 7 through the general interface unit 8, and then signal-connected to the control link 9 through the mission data recorder 7.

[0045] The specific connection method between the radiosonde pod payload 6 and the general interface unit 8, such as the serial data interface standard and measurement and control bandwidth, is determined with reference to existing technologies according to factors such as the actual payload type.

[0046] To simplify the circuit layout, the external nose payload 1, nose equipment bay payload 2, nose radar bay payload 3, belly payloads, and radiosonde pod payload 6 are mostly connected to the power distribution box through cables, such as 28V aviation DC cables. Each payload is uniformly powered on and controlled using ground / open signals, and the drive current is less than or equal to 100 mA.

[0047] When the power consumption requirements of the payload exceed the power supply characteristics of the above cables, to ensure the safety and reliability of the circuit, the electrical connection between the payload and the power distribution box is not changed, but a power conversion device is set at the payload to meet its power consumption requirements.

[0048] Regarding the setting methods of different types of loads, the nose external load 1 is usually connected and fixed to the nose structure through fasteners such as fastening bolts; the nose equipment cabin load 2, the nose radar cabin load 3 and the visible light CCD cabin load 5 are mostly connected to the cabin structure through common detachable connection methods such as bolt connection; the optoelectronic spherical cabin load 4 is mostly installed in the optoelectronic spherical cabin through an adapter beam, the optoelectronic spherical cabin load 4 is bolted to the adapter beam, and the adapter beam is bolted to the optoelectronic spherical cabin.

[0049] For example, see Figure 3 The weather radar's transceiver unit and processing unit are located in the upper part of the nose radar cabin, and the antenna unit is located in the lower part of the nose radar cabin. On the one hand, it reduces the space required for the equipment, and on the other hand, it facilitates the exposure of the antenna unit.

[0050] Taking into account that the belly load exceeds the surface of the UAV body and will increase the flight resistance, it is preferred that the belly load, especially the photoelectric cabin load 4, exceeds the surface of the aircraft body, and a fairing is provided outside the belly load to reduce the flow resistance at the belly load.

[0051] The fairing adopts a streamlined design. The material, shape and installation method of the fairing can be determined based on the structure of the UAV used in actual detection, the shape and size of the part of the belly load that exceeds the surface of the UAV, and other factors, with reference to existing aircraft fairings. I will not go into details here.

[0052] Of course, the layout of the nose external load 1 and the sounding pod load 6 should also take into account the impact on flight resistance, and try to minimize the impact on the flight state of the UAV.

[0053] In addition, according to the light transmittance requirements of each load, a light window can be provided at the corresponding aircraft skin or fairing so that light can pass through the light window and shine on the load, thereby meeting the light transmittance requirements of the load.

[0054] In this implementation, meteorological monitoring payloads are installed on the nose, nose compartment, belly compartment, and underwing attachment points. The mounting positions of the payloads do not interfere with each other, so multiple meteorological monitoring data can be obtained in one flight, which improves monitoring efficiency.

[0055] The nose, nose compartment, belly and underwing attachment points can all carry different types of payloads according to different monitoring tasks. The payloads in the same installation position can be quickly replaced through co-location, which has strong applicability.

[0056] Each load can be controlled independently, and the working status of the unreplaced load will not be affected by the replaced load. When a communication failure occurs at a certain location, it can be quickly replaced to a location with the same communication status. The system has strong reliability and scalability.

[0057] In a specific embodiment, please refer to Figure 2, the external nose load 1 includes an in-flight meteorological detector, which can measure meteorological data such as total atmospheric pressure, static pressure, and total temperature. The in-flight meteorological detector is signal-connected to the integrated navigation system 10 through an RS-422 interface;

[0058] The load 2 in the nose equipment compartment includes a visible light high-resolution digital imaging system, which can measure meteorological data such as clouds and rain in front of the flight path. The visible light high-resolution digital imaging system is signal-connected to the control link 9 through an HD-SDI interface;

[0059] The load 3 in the nose radar compartment includes a weather radar, which is used to observe fully polarized SAR data. The weather radar can be signal-connected to the general interface unit 8 through an RS-422 interface. Since the fully polarized SAR data is image data, the weather radar can also be signal-connected to the mission data recorder 7 through a Camera Link interface;

[0060] The belly load includes the optoelectronic sphere pod load 4 provided at the front section of the belly and the visible light CCD pod load 5 provided at the middle section of the belly. The belly load is signal-connected to the general interface unit 8 through an RS-422 interface;

[0061] The radiosonde pod load 6 is signal-connected to the general interface unit 8 through an RS-422 interface;

[0062] The general interface unit 8 is signal-connected to the mission data recorder 7 through a 1394 interface, and the mission data recorder 7 is signal-connected to the control link 9 through a 1394 interface.

[0063] Among them, the external nose load 1, the nose equipment compartment load 2, the nose radar compartment load 3, and the radiosonde pod load 6 are set as fixed loads, which can be carried or disassembled according to the requirements of the detection task;

[0064] The optoelectronic sphere pod load 4 provided at the front section of the belly and the visible light CCD pod load 5 provided at the middle section of the belly can replace the types of loads carried according to the requirements of the detection task.

[0065] For example, the optoelectronic sphere pod load 4 includes an airborne temperature and humidity profiler or a visible and infrared spectrometer. The airborne temperature and humidity profiler is used to detect the temperature and humidity profile data of the atmosphere below the flight path, and the visible and infrared spectral imager is used to detect the high spatial resolution and spectral resolution data of the surface ecological underlying surface;

[0066] The visible light CCD pod load 5 includes a millimeter-wave cloud radar or an aerosol lidar. The millimeter-wave cloud radar is used to detect the dynamic data of cloud targets, and the aerosol lidar is used to detect meteorological data such as aerosols. Since most of the data measured by the visible light CCD pod load 5 is image data, the visible light CCD pod load can also be signal-connected to the general interface unit 8 through a Camera Link interface.

[0067] In this specification, the various embodiments are described in a progressive manner. The key point of each embodiment is to illustrate the differences from other embodiments. For the same or similar parts among the various embodiments, reference can be made to each other.

[0068] The above has introduced in detail the high-altitude configuration of the large unmanned aerial vehicle for meteorological detection provided by the present utility model. Specific examples are used herein to elaborate on the principle and implementation manner of the present utility model. The description of the above embodiments is only used to help understand the method and its core idea of the present utility model. It should be noted that for those of ordinary skill in the art in this technical field, without departing from the principle of the present utility model, several improvements and modifications can be made to the present utility model, and these improvements and modifications also fall within the protection scope of the claims of the present utility model.

Claims

1. A large unmanned aerial vehicle (UAV) meteorological detection plateau configuration, characterized in that Including: The nose external load (1) is provided at the nose of the UAV. It is signal-connected to the mission data recorder (7) through the integrated navigation system (10), and the mission data recorder (7) is signal-connected to the control link (9). The nose equipment cabin load (2) is provided in the nose equipment cabin and is signal-connected to the control link (9). The nose radar cabin load (3) is provided in the nose radar cabin and is signal-connected to the mission data recorder (7) through the general interface unit (8). The belly load is provided at the front section or the middle section of the belly and is signal-connected to the mission data recorder (7) through the general interface unit (8). The sounding pod load (6) is provided in the sounding pod suspended under the wing and is signal-connected to the mission data recorder (7) through the general interface unit (8).

2. The large unmanned aerial vehicle meteorological detection plateau configuration according to claim 1, wherein The nose external load (1) includes an in-flight weather detector, and the in-flight weather detector is signal-connected to the integrated navigation system (10) through an RS-422 interface.

3. The large unmanned aerial vehicle meteorological detection plateau configuration according to claim 1, wherein, The nose equipment cabin load (2) includes a visible light high-resolution digital imaging system, and the visible light high-resolution digital imaging system is signal-connected to the control link (9) through an HD-SDI interface.

4. The large unmanned aerial vehicle meteorological detection plateau configuration according to claim 1, wherein The nose radar cabin load (3) includes a weather radar. The weather radar can be signal-connected to the general interface unit (8) through an RS-422 interface, and the weather radar is signal-connected to the mission data recorder (7) through a Camera Link interface.

5. The large unmanned aerial vehicle meteorological detection plateau configuration according to claim 1, wherein, The belly load includes an optoelectronic spherical cabin load (4) provided at the front section of the belly and a visible light CCD cabin load (5) provided at the middle section of the belly. The belly load is signal-connected to the general interface unit (8) through an RS-422 interface.

6. The large unmanned aerial vehicle meteorological detection plateau configuration according to claim 5, characterized in that, The optoelectronic spherical cabin load (4) includes an airborne temperature and humidity profiler or a visible light infrared spectrometer. The optoelectronic spherical cabin load (4) is installed in the optoelectronic spherical cabin through an adapter beam, and the optoelectronic spherical cabin load (4) is bolt-connected to the adapter beam.

7. The large unmanned aerial vehicle meteorological detection plateau configuration according to claim 5, characterized in that, The visible light CCD cabin load (5) includes a millimeter wave cloud radar or an aerosol lidar. The visible light CCD cabin load (5) can be signal-connected to the general interface unit (8) through a Camera Link interface.

8. The large unmanned aerial vehicle meteorological detection plateau configuration according to any one of claims 1-7, characterized in that, When the belly load protrudes beyond the aircraft body surface, a fairing is provided outside the belly load, and the fairing is used to reduce the flow resistance at the belly load.

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