CN114394254A - Ground test system for solar unmanned aerial vehicle - Google Patents
Ground test system for solar unmanned aerial vehicle Download PDFInfo
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- CN114394254A CN114394254A CN202111629888.1A CN202111629888A CN114394254A CN 114394254 A CN114394254 A CN 114394254A CN 202111629888 A CN202111629888 A CN 202111629888A CN 114394254 A CN114394254 A CN 114394254A
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention discloses a ground test system for a solar unmanned aerial vehicle, which comprises: the equipment cabinet is sequentially provided with a first case, a second case and a third case from top to bottom; the main control and interface unit is arranged in the first case and comprises a main control board and an interface board, wherein the main control board is respectively connected with the solar simulator, the electronic load and the unmanned aerial vehicle through the interface board; the solar simulator is arranged in the second case and is respectively connected with the unmanned aerial vehicle and the main control and interface unit; the electronic load is arranged in the third case and is respectively connected with the unmanned aerial vehicle and the main control and interface unit; the heat dissipation mechanism is arranged on the machine cabinet. The ground test system can test the functions and the performances of the energy system of the solar unmanned aerial vehicle on the ground, effectively improves the convenience and the coverage of the test, and shortens the period of the total dispatching test.
Description
Technical Field
The invention belongs to the technical field of solar unmanned aerial vehicles, and particularly relates to a ground test system for a solar unmanned aerial vehicle.
Background
The solar unmanned aerial vehicle is a novel aircraft with great development potential, takes solar energy as a power source, does not need to carry any fuel, and can theoretically realize permanent air flight. Compared with a conventional unmanned aerial vehicle, the solar unmanned aerial vehicle has obvious advantages and very wide application prospect, and can even play the role of an atmospheric satellite. Because the energy source of the solar unmanned aerial vehicle is a solar cell, the energy management system is complex, the total dispatching test difficulty is high, the task amount is large, the whole system needs sufficient sunlight for working, the long-time continuous test of the whole system under the condition of sufficient sunlight is difficult to guarantee in the prior art, the test condition is harsh, and the coverage is poor. The current total tone test is divided into an indoor part and an outdoor part, and the test flow is complicated and complicated. The ground test of the solar unmanned aerial vehicle is mostly single-system test equipment of a conventional unmanned aerial vehicle system, and ground special intelligent equipment for the general regulation test of the solar unmanned aerial vehicle is not provided.
Therefore, the testing system for the solar unmanned aerial vehicle is expected to be invented, so that the vacancy of ground special intelligent equipment in the general regulation test of the solar unmanned aerial vehicle can be filled, and the problems of long general regulation test period, harsh test conditions and poor coverage of the solar unmanned aerial vehicle in the prior art are solved.
Disclosure of Invention
The invention aims to provide a test system for a solar unmanned aerial vehicle, which fills the vacancy of ground special intelligent equipment in the general regulation test of the solar unmanned aerial vehicle and solves the problems of long general regulation test period, harsh test conditions and poor coverage of the solar unmanned aerial vehicle in the prior art.
In order to achieve the above object, the present invention provides a ground test system for a solar drone, comprising:
the equipment cabinet is sequentially provided with a first case, a second case and a third case from top to bottom;
the main control and interface unit is arranged in the first case and comprises a main control board and an interface board, wherein the main control board is respectively connected with the solar simulator, the electronic load and the unmanned aerial vehicle through the interface board and is used for controlling the solar simulator and the electronic load to test the unmanned aerial vehicle and receive test data of the unmanned aerial vehicle;
the solar simulator is arranged in the second case, is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and is used for receiving the control of the main control and interface unit so as to test the unmanned aerial vehicle;
the electronic load is arranged in the third case, is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and is used for receiving the control of the main control and interface unit to provide a load for the unmanned aerial vehicle;
and the heat dissipation mechanism is arranged on the machine cabinet and used for dissipating heat of the electronic load, the solar simulator and the main control and interface unit.
Optionally, the main control and interface unit further includes a power board, and the power board is electrically connected to the interface board, the main control board, and the heat dissipation mechanism, respectively, and is configured to convert 220V ac power into 28V dc power for use by the interface board, the main control board, and the heat dissipation mechanism.
Optionally, a back plate is also included,
the main control board and the interface board are integrated on the back board, and the main control board is electrically connected with the interface board through a bus of the back board.
Optionally, the interface board includes a serial communication board and an interface communication board, the serial communication board is electrically connected to the interface communication board through a bus of the backplane, wherein,
a serial port is integrated on the serial port communication board;
and the interface communication board is integrated with a bus interface and an Ethernet interface.
Optionally, the main control board is connected with the unmanned aerial vehicle sequentially through the serial port and the bus interface;
the main control board is respectively connected with the solar simulator and the electronic load through the Ethernet interface and is used for controlling the solar simulator and the electronic load.
Optionally, the serial port includes an RS485 serial port, an RS422 serial port, and an RS232 serial port;
the bus interface comprises an FC bus interface, a CAN bus interface and a CANFD interface.
Optionally, the heat dissipation mechanism comprises a suction fan and a blowing fan, wherein,
the blowing fan is arranged at the rear end of the first case and communicated with the first case, the air-extracting fan is arranged at the rear end of the third case and communicated with the third case, and an air channel matched with the blowing fan and the air-extracting fan is arranged in the cabinet and used for dissipating heat of equipment in the cabinet.
Optionally, the heat dissipation mechanism further comprises a temperature relay;
the air-draft fan and the air-blowing fan are respectively provided with the temperature relay, and the temperature relay is used for controlling the on-off of the air-draft fan or the air-blowing fan.
Optionally, the cabinet is provided with guide rails respectively matched with the first cabinet, the second cabinet and the third cabinet, and the first cabinet, the second cabinet and the third cabinet are respectively inserted into the cabinet or drawn out of the cabinet through the guide rails.
Optionally, the first chassis, the second chassis, and the third chassis have the same length and are smaller than the length of the cabinet, and the first chassis, the second chassis, and the third chassis have the same width and are smaller than the width of the cabinet;
the heights of the first case, the second case and the third case are all 3U.
The invention has the beneficial effects that:
all equipment of the ground test system is arranged in a cabinet, the cabinet is sequentially provided with a first cabinet, a second cabinet and a third cabinet from top to bottom, the first cabinet is provided with a main control and interface unit, the second cabinet is provided with a solar simulator, and the third cabinet is provided with an electronic load; the ground test system can test the function and performance of the energy system of the solar unmanned aerial vehicle on the ground; the ground test system can simulate the flight control machine to complete the function and performance joint test of other airborne electronic systems, can also simulate the onboard equipment to complete the communication function test of the flight control machine, quickly verifies the logic correctness of the interface protocol of the unmanned aerial vehicle, completes the function and performance test of the energy system of the solar unmanned aerial vehicle, and improves the test convenience; meanwhile, the ground test system is integrated with the solar simulator, and can be used for the total system tone test, so that the test coverage is improved; therefore, the ground test system of the invention fills the vacancy of ground special intelligent equipment in the general regulation test of the solar unmanned aerial vehicle and solves the problems of long general regulation test period, harsh test conditions and poor coverage of the solar unmanned aerial vehicle in the prior art.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
Fig. 1 shows a block diagram of a ground test system for a solar drone according to one embodiment of the invention.
Fig. 2 shows a schematic diagram of electrical connections for a ground test system for a solar drone, according to one embodiment of the invention.
Fig. 3 shows a block diagram of a master control and interface unit of a ground test system for solar drones, according to an embodiment of the invention.
Description of the reference numerals
1. A cabinet; 2. a first chassis; 3. a second chassis; 4. and a third chassis.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
According to the invention, the ground test system for the solar unmanned aerial vehicle comprises:
the equipment cabinet is sequentially provided with a first case, a second case and a third case from top to bottom;
the main control and interface unit is arranged in the first case and comprises a main control board and an interface board, wherein the main control board is respectively connected with the solar simulator, the electronic load and the unmanned aerial vehicle through the interface board and is used for controlling the solar simulator and the electronic load to test the unmanned aerial vehicle and receive test data of the unmanned aerial vehicle;
the solar simulator is arranged in the second case, is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and is used for receiving the control of the main control and interface unit so as to test the unmanned aerial vehicle;
the electronic load is arranged in the third case, is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and is used for receiving the control of the main control and interface unit to provide a load for the unmanned aerial vehicle;
and the heat dissipation mechanism is arranged on the machine cabinet and used for dissipating heat of the electronic load, the solar simulator and the main control and interface unit.
Specifically, all the equipment of the ground test system is arranged in a cabinet, the cabinet is sequentially provided with a first cabinet, a second cabinet and a third cabinet from top to bottom, the first cabinet is provided with a main control and interface unit, the second cabinet is provided with a solar simulator, and the third cabinet is provided with an electronic load, wherein the main control and interface unit comprises a main control board and an interface board, the main control board is respectively connected with the solar simulator, the electronic load and the unmanned aerial vehicle through the interface board, the solar simulator is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and the electronic load is respectively connected with the unmanned aerial vehicle and the main control and interface unit; the ground test system can test the function and performance of the energy system of the solar unmanned aerial vehicle on the ground; the ground test system can simulate the flight control machine to complete the function and performance joint test of other airborne electronic systems, can also simulate the onboard equipment to complete the communication function test of the flight control machine, quickly verifies the logic correctness of the interface protocol of the unmanned aerial vehicle, completes the function and performance test of the energy system of the solar unmanned aerial vehicle, and improves the test convenience; meanwhile, the ground test system is integrated with the solar simulator, and can be used for the total system tone test, so that the test coverage is improved.
Further, in practical application, the power of the electronic load meets the requirement that the rated power is 10kW, and the power supply voltage is AC 220V; the maximum output power of the solar simulator is 9 kW.
Further, the control of the solar simulator, the electronic load and the main control panel are all the prior art, and the control method is easy to be mastered by those skilled in the art, and the detailed description of the invention is omitted.
In one example, the main control and interface unit further comprises a power board electrically connected to the interface board, the main control board and the heat dissipation mechanism, respectively, for converting 220V ac power to 28V dc power for use by the interface board, the main control board and the heat dissipation mechanism.
Specifically, a chip of the main control board selects heterogeneous multi-core system on chip (SoC) devices, the recommended models are 66AK2G12ABY60, 1 Cortex-A-15ARMCore and 1C 66XDSPCore are arranged in 66AK2G12ABY60, a DSP and an ARM core can control all memories and peripherals in the system, a program programming interface is reserved, and a preset intelligent test function can be realized by programming a test application program; the main control board completes drive control of the interface on the interface board through the bus of the back board, and therefore the main control board controls and monitors the solar unmanned aerial vehicle through the interface on the interface board. The interface board takes FPGA as a core, and the FPGA selects XC7K325T-1FFG900I of Xilinx.
Furthermore, the size of the power panel, the main control panel and the interface panel is matched with that of the back panel; in practical application, the power panel is mainly designed as AD/DC, the input is AC220V commercial power, and the output is DC28V voltage
In one example, the ground testing system further comprises a back plate,
the main control board and the interface board are integrated on the back board, and the main control board is electrically connected with the interface board through a bus of the back board.
Specifically, the bus of the backplane adopts a PCIE bus architecture.
In one example, the interface board includes a serial communication board and an interface communication board, the serial communication board is electrically connected with the interface communication board through a bus of the backplane, wherein,
a serial port is integrated on the serial port communication board;
the interface communication board is integrated with a bus interface and an Ethernet interface.
In one example, the main control board is connected with the unmanned aerial vehicle sequentially through a serial port and a bus interface;
the main control panel is respectively connected with the solar simulator and the electronic load through the Ethernet interface and is used for controlling the solar simulator and the electronic load.
In one example, the serial ports include an RS485 serial port, an RS422 serial port, and an RS232 serial port;
the bus interface comprises an FC bus interface, a CAN bus interface and a CAN FD interface.
Specifically, the number of CANFD interfaces of the interface communication board is not less than 2, the number of RS422 interfaces/RS 485 interfaces/RS 232 interfaces is not less than 7, the number of FC bus interfaces is not less than 2, the number of ethernet interfaces is not less than 2, and all communication interfaces adopt an isolation design.
In one example, the heat dissipation mechanism includes an induced draft fan and a blower fan, wherein,
the blowing fan is arranged at the rear end of the first case and communicated with the first case, the air draft fan is arranged at the rear end of the third case and communicated with the third case, and an air channel matched with the blowing fan and the air draft fan is arranged in the cabinet and used for dissipating heat of equipment in the cabinet.
In one example, the heat dissipation mechanism further comprises a temperature relay;
the air-draft fan and the air-blowing fan are respectively provided with a temperature relay, and the temperature relays are used for controlling the on-off of the air-draft fan or the air-blowing fan.
Specifically, the temperature relay is closed when the temperature operation characteristic is 40 ℃ or higher, and is opened when the temperature operation characteristic is 35 ℃ or lower.
In one example, the cabinet is provided with guide rails respectively matched with the first cabinet, the second cabinet and the third cabinet, and the first cabinet, the second cabinet and the third cabinet are respectively inserted into the cabinet or drawn out of the cabinet through the guide rails.
Specifically, the cabinet structure adopts a standard cabinet form, guide rails matched with the first cabinet, the second cabinet and the third cabinet are arranged on the cabinet, the first cabinet, the second cabinet and the third cabinet are respectively inserted into the cabinet or drawn out from the cabinet through the guide rails, the module cannot be impacted or shaken by external vibration, and preferably, the interval range between the first cabinet and the second cabinet and the interval range between the second cabinet and the third cabinet are both 30-50 mm; in practical application, the back of rack still is equipped with the trough to this simultaneously, the back of rack is equipped with a plurality of auto-lock wheels for the rack can remove everywhere, has improved the convenience that ground test system used.
Further, the material of the cabinet is preferably stainless steel material, and the thickness of the cabinet is preferably 1 mm-2 mm; the periphery of first quick-witted case, second quick-witted case and third machine case is equipped with a plurality of regularly arranged's round hole, and the aperture size is preferred 45mm, and the interval between the adjacent round hole is preferred 60 mm.
In one example, the first, second, and third enclosures are equal in length and less than the length of the cabinet, and the first, second, and third enclosures are equal in width and less than the width of the cabinet;
the heights of the first case, the second case and the third case are all 3U.
Specifically, first quick-witted case, second quick-witted case and the third machine case of 3U height are standard machine case structure, and in practical application, the width of industrial computer is 19 inches, and the height uses U as the unit, and wherein 1U 1.75 inches 44.45 millimeters, usually have 1U machine case, 2U machine cases, 3U machine cases, 4U machine cases, 5U machine cases, 6U machine cases, 7U machine cases, 8U machine cases.
Example one
As shown in fig. 1, a ground test system for a solar drone includes:
the equipment cabinet 1 is sequentially provided with a first case 2, a second case 3 and a third case 4 from top to bottom;
the main control and interface unit is arranged in the first case 2 and comprises a main control board and an interface board, wherein the main control board is respectively connected with the solar simulator, the electronic load and the unmanned aerial vehicle through the interface board and is used for controlling the solar simulator and the electronic load to test the unmanned aerial vehicle and receive test data of the unmanned aerial vehicle;
the solar simulator is arranged in the second case 3, is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and is used for receiving the control of the main control and interface unit so as to test the unmanned aerial vehicle;
the electronic load is arranged in the third case 4, is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and is used for receiving the control of the main control and interface unit to provide a load for the unmanned aerial vehicle;
and the heat dissipation mechanism is arranged on the machine cabinet and used for dissipating heat of the electronic load, the solar simulator and the main control and interface unit.
As shown in fig. 2, the main control and interface unit further includes a power board, the power board is electrically connected to the interface board, the main control board and the heat dissipation mechanism, respectively, and is configured to convert 220V ac power into 28V dc power for use by the interface board, the main control board and the heat dissipation mechanism.
Wherein, the ground test system also comprises a back plate,
the main control board and the interface board are integrated on the back board, and the main control board is electrically connected with the interface board through a bus of the back board.
As shown in fig. 3, the interface board includes a serial communication board and an interface communication board, the serial communication board is electrically connected to the interface communication board through a bus of the backplane, and a serial port is integrated on the serial communication board; the interface communication board is integrated with a bus interface and an Ethernet interface. The main control board is connected with the unmanned aerial vehicle through the serial port and the bus interface in sequence; the main control panel is respectively connected with the solar simulator and the electronic load through the Ethernet interface and is used for controlling the solar simulator and the electronic load.
Wherein, heat dissipation mechanism includes air-extracting fan and the formula of blowing fan, and wherein, the formula of blowing fan is located the rear end of first quick-witted case 2 and is linked together with first quick-witted case 2, and air-extracting fan locates the rear end of third machine case 4 and is linked together with third machine case 4, and is equipped with in the rack 1 and blows formula electric fan and air flue that air-extracting fan matched with for dispel the heat to the equipment in the rack 1. The heat dissipation mechanism also comprises a temperature relay; the air-draft fan and the air-blowing fan are respectively provided with a temperature relay, and the temperature relays are used for controlling the on-off of the air-draft fan or the air-blowing fan.
The cabinet 1 is provided with guide rails respectively matched with the first cabinet 2, the second cabinet 3 and the third cabinet 4, and the first cabinet 2, the second cabinet 3 and the third cabinet 4 are respectively inserted into the cabinet 1 or drawn out from the cabinet 1 through the guide rails. The lengths of the first case 2, the second case 3 and the third case 4 are equal and smaller than that of the cabinet 1, and the widths of the first case 2, the second case 3 and the third case 4 are equal and smaller than that of the cabinet 1; the heights of the first case 2, the second case 3 and the third case 4 are all 3U.
In summary, all the devices of the ground testing system are arranged in a cabinet, the cabinet is sequentially provided with a first cabinet, a second cabinet and a third cabinet from top to bottom, the first cabinet is provided with a main control and interface unit, the second cabinet is provided with a solar simulator, and the third cabinet is provided with an electronic load, wherein the main control and interface unit comprises a main control board and an interface board, the main control board is respectively connected with the solar simulator, the electronic load and the unmanned aerial vehicle through the interface board, the solar simulator is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and the electronic load is respectively connected with the unmanned aerial vehicle and the main control and interface unit; the ground test system can test the function and performance of the energy system of the solar unmanned aerial vehicle on the ground; the ground test system can simulate the flight control machine to complete the function and performance joint test of other airborne electronic systems, can also simulate the onboard equipment to complete the communication function test of the flight control machine, quickly verifies the logic correctness of the interface protocol of the unmanned aerial vehicle, completes the function and performance test of the energy system of the solar unmanned aerial vehicle, and improves the test convenience; meanwhile, the ground test system is integrated with the solar simulator, and can be used for the total system tone test, so that the test coverage is improved.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (10)
1. A ground test system for a solar unmanned aerial vehicle, comprising:
the equipment cabinet is sequentially provided with a first case, a second case and a third case from top to bottom;
the main control and interface unit is arranged in the first case and comprises a main control board and an interface board, wherein the main control board is respectively connected with the solar simulator, the electronic load and the unmanned aerial vehicle through the interface board and is used for controlling the solar simulator and the electronic load to test the unmanned aerial vehicle and receive test data of the unmanned aerial vehicle;
the solar simulator is arranged in the second case, is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and is used for receiving the control of the main control and interface unit so as to test the unmanned aerial vehicle;
the electronic load is arranged in the third case, is respectively connected with the unmanned aerial vehicle and the main control and interface unit, and is used for receiving the control of the main control and interface unit to provide a load for the unmanned aerial vehicle;
and the heat dissipation mechanism is arranged on the machine cabinet and used for dissipating heat of the electronic load, the solar simulator and the main control and interface unit.
2. The ground test system for a solar drone of claim 1, wherein the master control and interface unit further includes a power board electrically connected to the interface board, the master control board, and the heat dissipation mechanism, respectively, for converting 220V ac power to 28V dc power for use by the interface board, the master control board, and the heat dissipation mechanism.
3. The ground test system for solar drones, according to claim 1, further comprising a back panel,
the main control board and the interface board are integrated on the back board, and the main control board is electrically connected with the interface board through a bus of the back board.
4. The ground test system for a solar drone of claim 3, wherein the interface board includes a serial communication board and an interface communication board, the serial communication board being electrically connected with the interface communication board through a bus of the backplane, wherein,
a serial port is integrated on the serial port communication board;
and the interface communication board is integrated with a bus interface and an Ethernet interface.
5. The ground test system for the solar unmanned aerial vehicle as claimed in claim 4, wherein the main control board is connected with the unmanned aerial vehicle sequentially through the serial port and the bus interface;
the main control board is respectively connected with the solar simulator and the electronic load through the Ethernet interface and is used for controlling the solar simulator and the electronic load.
6. The ground test system for solar drones according to claim 4,
the serial ports comprise an RS485 serial port, an RS422 serial port and an RS232 serial port;
the bus interface comprises an FC bus interface, a CAN bus interface and a CANFD interface.
7. The ground testing system for solar drones of claim 1, wherein the heat dissipation mechanism comprises a suction fan and a blowing fan, wherein,
the blowing fan is arranged at the rear end of the first case and communicated with the first case, the air-extracting fan is arranged at the rear end of the third case and communicated with the third case, and an air channel matched with the blowing fan and the air-extracting fan is arranged in the cabinet and used for dissipating heat of equipment in the cabinet.
8. The ground testing system for solar drones as defined in claim 7, wherein the heat dissipation mechanism further comprises a temperature relay;
the air-draft fan and the air-blowing fan are respectively provided with the temperature relay, and the temperature relay is used for controlling the on-off of the air-draft fan or the air-blowing fan.
9. The ground test system for the solar unmanned aerial vehicle as claimed in claim 1, wherein the cabinet is provided with guide rails respectively matched with the first cabinet, the second cabinet and the third cabinet, and the first cabinet, the second cabinet and the third cabinet are respectively inserted into or withdrawn from the cabinet through the guide rails.
10. The ground test system for solar drones according to claim 1,
the first chassis, the second chassis and the third chassis are equal in length and smaller than the length of the cabinet, and the first chassis, the second chassis and the third chassis are equal in width and smaller than the width of the cabinet;
the heights of the first case, the second case and the third case are all 3U.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111629888.1A CN114394254A (en) | 2021-12-28 | 2021-12-28 | Ground test system for solar unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111629888.1A CN114394254A (en) | 2021-12-28 | 2021-12-28 | Ground test system for solar unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
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| CN114394254A true CN114394254A (en) | 2022-04-26 |
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| CN202111629888.1A Pending CN114394254A (en) | 2021-12-28 | 2021-12-28 | Ground test system for solar unmanned aerial vehicle |
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2021
- 2021-12-28 CN CN202111629888.1A patent/CN114394254A/en active Pending
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