Ground starting power generation test platform and test method for UAV engines

Abstract

The present invention discloses a ground starting and power generation test platform and test method for unmanned aerial vehicle (UAV) engines, which relate to the field of UAV avionics. The platform comprises: a starter generator, wherein the starter generator's on / off state and operating mode are respectively controlled by a starter generator controller and a starter-generator switching box, and the starter generator is connected to the engine via a gear set; an engine controller, which controls the engine; a ground battery, which is connected to the starter generator and supplies power to the engine when it is needed to start the engine; a ground load, which is connected to the starter generator; an emergency protection box, which is arranged between the starter generator and the ground battery and the ground load; and a ground control box, which is connected to the starter generator controller, the starter-generator switching box, the engine controller, and the emergency protection box via signal cables, and the ground control box is used to display operating parameters of the starter generator, the engine, the ground battery, and the ground load.

Description

Technical Field

[0001] The present invention belongs to the field of unmanned aerial vehicle (UAV) avionics, and more specifically, relates to a ground starting power generation test platform and a test method for UAV engines. Background Art

[0002] During ground tests of UAV power systems, it is often necessary to start the engine on the ground. After the engine is running normally, the engine is subjected to a loading test to test the impact of the load on the engine. Therefore, it is necessary to design a ground starting power generation platform to complete the ground starting and loading tests of the engine.

[0003] Therefore, a ground starting power generation platform for UAV engines is designed to achieve the purpose of ground starting and loading test of UAV engines. Summary of the Invention

[0004] The purpose of the present invention is to address the deficiencies in the existing technology and provide a ground starting and power generation test platform and test method for UAV engines. The test platform can perform comprehensive inspections on UAV engines and, during the test, can effectively protect the test platform to avoid damage to the test platform caused by engine overload.

[0005] In order to achieve the above-mentioned object, the present invention provides a ground starting power generation test platform for UAV engines, comprising:

[0006] A starter generator, whose on / off state is controlled by a starter generator controller, whose operating mode is controlled by a starter-generator switching box, and whose mechanical output is connected to the engine via a gear set;

[0007] An engine controller, controlling the starting, ignition and parameter adjustment of the engine;

[0008] a ground battery connected to the starter generator, and when the engine needs to be started by the starter generator, the ground battery supplies power to the starter generator;

[0009] A ground load is connected to the starter generator, and when the engine is started, the engine drives the starter generator to supply power to the ground load;

[0010] An emergency protection box is provided between the starter generator, the ground battery and the ground load;

[0011] A ground control box is connected to the starter generator controller, the starter-generation switching box, the engine controller and the emergency protection box through signal cables, and the operating parameters of the starter generator, the engine, the ground battery and the ground load are displayed through the ground control box.

[0012] Optionally, the starting-generation switching box includes:

[0013] a first aviation socket, disposed on an outer layer of the switching housing; the outer layer of the switching housing is further provided with a first positive terminal, a second positive terminal, a first negative terminal, and a second negative terminal; the first positive terminal and the second positive terminal are connected by a first power supply cable, and the first negative terminal and the second negative terminal are connected by a second power supply cable;

[0014] The auxiliary starting contactor, the auxiliary power generation contactor and the in-position contactor are connected to the first aviation socket via a first signal cable, and the first aviation socket is connected to the starter generator via a platform cable;

[0015] A starting contactor, interlocked with the auxiliary starting contactor;

[0016] The power generation contactor is linked to the auxiliary power generation contactor.

[0017] Optionally, the emergency protection box includes:

[0018] a second aviation socket, disposed on an outer layer of the protective shell; the outer layer of the protective shell is further provided with a third positive terminal, a fourth positive terminal, a third negative terminal, and a fourth negative terminal; the third positive terminal and the fourth positive terminal are connected by a third power supply cable, and the third negative terminal and the fourth negative terminal are connected by a fourth power supply cable;

[0019] a first current protection sensor, arranged on the third power supply cable;

[0020] a second current protection sensor, arranged on the fourth power supply cable;

[0021] The emergency contactor, the first current protection sensor, and the second current protection sensor are connected to the second aviation socket through a second signal cable.

[0022] Optionally, the ground control box includes a touch screen and a circuit board, and the touch screen is provided with a ground battery status light, a ground battery start switch, a load status light, a load start switch, a generator parameter display bar, an engine parameter display bar, a start button, a reset button and an emergency stop button.

[0023] Optionally, the ground battery start switch is control-connected to the ground battery, the load start switch is control-connected to the ground load, the emergency stop button is control-connected to the emergency protection box, and the start button is control-connected to the starting controller.

[0024] Optionally, the starter generator, the starter-generator switching box and the emergency protection box are connected by a cable, and the current flows in the cable in opposite directions during the starting phase and the power generation phase.

[0025] Optionally, the first current protection sensor, the second current protection sensor and the emergency contactor will automatically cut off the current circuit when the current is too large or an abnormal situation occurs.

[0026] Optionally, in the starting phase, the in-position contactor and the starting contactor are in the same current loop, and the current loop directions of the generating contactor in the generating phase and the starting phase are opposite to each other.

[0027] Optionally, the ground battery is a lithium battery, the starter generator is a low-voltage DC brushed generator, and the starter generator has two operating modes: starting and generating electricity.

[0028] The present invention also provides a ground starting power generation test method for a UAV engine. Utilizing the above-mentioned ground starting power generation test platform for a UAV engine, the test method comprises:

[0029] The ground control box sends instructions to the starter-generator switching box, the emergency protection box, and the starter generator controller, the ground battery supplies power to the starter generator, and the starter generator drives the engine to rotate through the gear set. After the engine is successfully ignited, the engine starts to rotate, and the engine drives the starter generator to rotate through the gear set. The ground battery stops supplying power to the starter generator, and the emergency protection box monitors the current generated by the starter generator.

[0030] When the engine drives the starter generator to a speed that reaches a power generation speed, the starter generator controller switches the operation mode of the starter generator, and the starter generator supplies power to the ground load. The parameters of the starter generator and the engine are monitored by the ground control box, and the emergency protection box monitors the current generated by the starter generator.

[0031] The present invention provides a ground starting and power generation test platform and test method for unmanned aerial vehicle engines, which have the following beneficial effects: a starting-power generation switching box is provided in the test platform, so that the engine is started by switching the operating mode of the starter generator. After the engine is started, the output current of the starter generator is loaded onto the ground load, and the operating conditions of the engine and the ground load are observed through the touch screen. In addition, the engine parameters are adjusted through the engine controller, so that the ground load conditions are observed accordingly, and the test items are completed in this way. In addition, an emergency protection box is provided in the test platform. When the output current of the starter generator driven by the engine is abnormal, the test process can be immediately terminated through the emergency protection box to avoid damage to the test platform.

[0032] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention with reference to the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0034] Figure 1 A schematic structural diagram of a ground starting power generation test platform for UAV engines according to an embodiment of the present invention is shown.

[0035] Figure 2 A diagram showing a touch screen interface in a ground control box according to an embodiment of the present invention is shown.

[0036] Figure 3 A schematic diagram of the internal structure of an emergency protection box according to an embodiment of the present invention is shown.

[0037] Figure 4 A schematic diagram of the internal structure of a starting-generating switching box according to an embodiment of the present invention is shown.

[0038] Description of reference numerals:

[0039] 1. Ground battery; 1-1. Ground battery status light; 1-2. Ground battery start switch; 1-3. Load status light; 1-4. Load start switch; 1-5. Start button; 1-6. Reset button; 1-7. Emergency stop button; 1-8. Generator parameter display bar; 1-9. Engine parameter display bar; 2. Ground load; 3. Emergency protection box; 3-1. Second aviation socket; 3-2. First current protection sensor; 3-3. Third positive terminal; 3-4. Third negative terminal; 3-5. Emergency contactor; 3-6. Second current protection sensor; 3-7. Fourth power supply cable; 3-8. Fourth negative terminal; 3-9. Fourth positive terminal; 3-10. Third power supply cable; 3- 11. Second signal cable; 3-12. Protective housing; 4. Starter-generator switching box; 4-1. Starting contactor; 4-2. Second positive terminal; 4-3. Auxiliary starting contactor; 4-4. First negative terminal; 4-5. First aviation socket; 4-6. First power supply cable; 4-7. Second negative terminal; 4-8. Auxiliary generator contactor; 4-9. Generator contactor; 4-10. First signal cable; 4-11. First positive terminal; 4-12. Second power supply cable; 4-13. In-position contactor; 4-14. Switch housing; 5. Ground control box; 6. Starter generator; 7. Starter generator controller; 8. Engine; 9. Engine controller; 10. Gear set; 11. Connecting cables. DETAILED DESCRIPTION

[0040] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. Instead, these embodiments are provided to make the present invention more thorough and complete and to fully convey the scope of the present invention to those skilled in the art.

[0041] like Figures 1 to 4 As shown, the present invention provides a ground starting and power generation test platform for unmanned aerial vehicle engines, comprising: a ground storage battery (1), a ground load (2), an emergency protection box (3), a starting-power generation switching box (4), a ground control box (5), a starter generator (6), a starter generator controller (7), an engine (8), an engine controller (9), a gear set (10), and a connecting cable (11).

[0042] The ground control box (5) includes an LCD touch screen and an embedded microcomputer circuit board. The circuit board analyzes the data received by the ground control box (5) and displays it on the LCD touch screen. At the same time, the experimenter can operate the ground control box (5) through the touch screen to start, reset, and stop the starting power generation test platform in an emergency state. At the same time, the parameters of the engine (8) and the starting generator (6) in the power generation state during the experiment are monitored to complete the experiment of the ground starting power generation platform. The parameters displayed on the touch screen include: a ground battery status light (1-1), a ground battery start switch (1-2), a load status light (1-3), a load start switch (1-4), a generator parameter display bar (1-8), an engine parameter display bar (1-9), a start button (1-5), a reset button (1-6), and an emergency stop button (1-7).

[0043] The ground storage battery (1) can be a 28V lithium battery capable of achieving a high rate discharge of 10-20C, and supplies power to the starter generator (6) during the starting process, thereby causing the starter generator (6) to rotate. The ground storage battery (1) can be turned on and off by a ground storage battery start switch (1-2) on the touch screen. When turned on, the ground storage battery (1) is connected to the platform circuit, and when turned off, the ground storage battery (1) is disconnected and no longer supplies power.

[0044] The ground load (2) is a resistive electronic load. After the engine (8) is started, the ground load (2) can be turned on and off by means of the load start switch (1-4) on the touch screen, and the power generation state of the starter generator (6) can be loaded and unloaded to test the influence of the loading and unloading on the engine (8).

[0045] The starter generator (6) is controlled by a starter generator controller (7). The starter generator (6) can adopt a brushed DC motor and has two operating modes: starting and generating. When the engine (8) is started, the starter generator (6) drives the engine (8) to rotate. After the engine (8) is ignited and works normally, it serves as a power generation module. When in the air, the engine (8) can supply power to the engine and the unmanned aerial vehicle, and supply power to the ground load (2) during the ground experiment. The starter generator controller (7) switches the generator between the starting mode and the generating mode by controlling the starter-generating switching box (4) during the starting stage and the generating stage, and protects the generator by controlling the emergency protection box (3). At the same time, the power generation parameters of the engine (8) are monitored during the operation of the platform and displayed in real time on the touch screen of the ground control box (5).

[0046] The emergency protection box (3) comprises a second aviation socket (3-1), a protective shell (3-12), a first current protection sensor (3-2), a second current protection sensor (3-6), an emergency contactor (3-5), four metal terminals, two power supply cables, and a signal cable. The second aviation socket (3-1) and the metal terminals are both mounted on the outer layer of the protective shell (3-12), and other components are mounted inside the protective shell. During a normal test, the emergency contactor (3-5) is closed, and a large current flows between the third positive terminal (3-3), the fourth positive terminal (3-9) and the third negative terminal (3-4), and the fourth negative terminal (3-8). At the same time, the signals of the two current protection sensors and the emergency contactor (3-5) are connected to the second aviation socket (3-1) via the second signal cable (3-11); the signal of the emergency equipment box (3) is connected to the cable of the test platform via the aviation socket (3-1). After being connected to the test platform, current detection is realized and the emergency contactor (3-5) is disconnected. When the current is too large or the current difference detected by the two current protection sensors is too large, the platform detects this situation and stops the starting or power generation process; or when other abnormal situations occur, the emergency contactor (3-5) can be disconnected and the test can be stopped by pressing the emergency stop button (1-7) on the touch screen of the ground control box (5).

[0047] The starting-generation switching box (4) comprises a first aviation socket (4-5), a switching shell (4-14), an in-position contactor (4-13), a starting contactor (4-1), an auxiliary starting contactor (4-3), a power generation contactor (4-9), an auxiliary power generation contactor (4-8), four metal terminals, two power supply cables, and a signal cable (4-10). The first aviation socket (4-5) and the four metal terminals are installed on the outer layer of the switching shell (4-14), and other components are installed inside the switching shell (4-14). During a normal test, a large current flows between the first positive terminal (4-11), the second positive terminal (4-2), the first negative terminal (4-4), and the second negative terminal (4-7). At the same time, the control signals of the auxiliary starting contactor (4-3) and the auxiliary power generation contactor (4-8) and the control signal of the in-position contactor (4-13) are connected to the first aviation socket (4-5) via the first signal cable (4-10); the control signal of the starting-power generation switching box (4) is connected to the starting power generation platform (6) via the first aviation socket (4-5) and the platform cable, thereby realizing switching between the starting mode and the power generation mode. The starting contactor (4-1) and the auxiliary starting contactor (4-3), the power generation contactor (4-9) and the auxiliary power generation contactor (4-8) are two pairs of interlocking contactors. When the auxiliary starting contactor (4-3) and the auxiliary power generation contactor (4-8) are closed, the main contactor will be closed. Therefore, during the starting process, when the on-site contactor (4-13), the auxiliary starting contactor (4-3) and the starting contactor (4-1) are all closed, the current flows from the ground battery (1) through the metal terminal, the on-site contactor (4-13) and the starting contactor (4-1) to the starter generator (6); after the starting process is completed, the starter generator controller (7) sends a control instruction to the starting-power generation switching box (4), disconnects the starting contactor (4-1) and closes the auxiliary power generation contactor (4-8). At this time, the power generation contactor (4-9) is closed, and the current flows from the starter generator (6) through the four metal terminals and the power generation contactor (4-9) to the load.

[0048] The connecting cables (11) connect the various devices in the starting and generating test platform, wherein the power supply cables passing large current include: connecting cables between the ground battery (1) and the ground load (2) and the emergency protection box (3), connecting cables between the emergency protection box (3) and the starting-generating switching box (4), and connecting cables between the starting-generating switching box (4) and the starting generator (6); and the signal cables include: interconnecting cables between the ground control box (5), the starting generator controller (7), the emergency protection box (3), the starting-generating switching box (4), and the engine controller (9).

[0049] The engine (8) comprises a gear set (10) and an engine body. During the starting phase, the starter generator (6) switches to a starting mode and drives the engine body to rotate via the gear set (10). After the engine body is ignited, the engine (8) drives the starter generator (6) to rotate and generate electricity via the gear set (10). The engine body is a turboprop aircraft engine powered by fuel. The engine controller (9) controls the normal operation of the engine body during the starting, ignition and normal operation of the engine body, and transmits the parameters of the engine body to the ground control box (5) via a connecting cable and displays them on a touch screen.

[0050] The specific working process of the ground starting power generation test platform is as follows:

[0051] Press the ground battery start switch (1-2) on the ground control box (5), and the ground control box sends a control instruction to the starter-generator switching box (4), closing the in-position contactor (4-13); press the start button (1-5) on the ground control box (5), and the ground control box (5) sends an instruction to the emergency protection box (3) and the starter generator controller (7), and the emergency protection box (3) closes the emergency contactor (3-5). After receiving the instruction, the starter generator controller (7) sends an instruction to the starter-generator switching box (4), closing the starter contactor (4-1). At this time, the current of the ground battery (1) flows from the positive electrode of the battery through the emergency protection box (3) and the positive terminal of the starter-generator switching box (4) to the positive electrode of the starter generator (6), and is output from the negative electrode of the starter generator (6) through the motor winding, and then flows back to the negative electrode of the ground battery (1) through the starter-generator switching box (4) and the emergency protection box (3), forming a The current loop starter generator controller (7) controls the starter generator (6) to start rotating, and drives the engine (8) to rotate through the gear set (10). After the power generation speed of the starter generator (6) reaches the ignition speed of the engine (8), the engine controller (9) controls the engine (8) to ignite, and the engine body starts to rotate, and drives the starter generator (6) to rotate through the gear set (10). At this time, the starter generator controller (7) disconnects the starter contactor (4-1), and the ground battery (1) no longer supplies power, and the starting phase ends. During the starting process, the power generation mode of the starter generator (6) and the engine speed can be monitored on the touch screen of the ground control box (5). At the same time, the current protection sensor in the emergency protection box (3) also monitors the current. If an abnormal situation occurs, the emergency stop button (1-7) can be manually pressed to end the starting process. The starter generator controller (7) will also terminate the starting process when monitoring abnormal parameters.

[0052] After the start phase is completed, the engine (8) drives the starter generator (6) to rotate. When the starter generator (6) reaches the power generation speed, the starter generator controller (7) closes the power generation contactor (4-9) in the starter-power generation switching box (4). At this time, the current flows through the positive (negative) pole of the starter generator (6) through the starter-power generation switching box (4) and the emergency protection box (3) to the positive (negative) pole of the ground load (2), forming a voltage at both ends of the ground load (2). The ground starter power generation test platform enters the power generation phase. At this time, the load start switch (1-4) on the display screen of the ground control box (1) is pressed. The ground load (2) is connected to the circuit, and the starter generator (6) rotates with the ground load (2), and the engine (8) is loaded. The size of the ground load (2) can be adjusted through the load control software to test the influence of loads of different sizes on the engine (8). During the test, the parameters of the starter generator (6) and the engine (8) can be monitored through the ground control box (5). At the same time, the current protection sensor in the emergency protection box (3) also monitors the current. If an abnormal situation occurs, the emergency stop button (1-7) can be manually pressed to end the test process. The starter generator controller (7) will also terminate the test process when monitoring abnormal parameters.

[0053] At this point, the starting and power generation test functions of the ground starting power generation test platform have been realized.

[0054] While various embodiments of the present invention have been described above, the above description is intended to be illustrative, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A ground starting power generation test platform for UAV engines, characterized by: include: A starter generator, whose on / off state is controlled by a starter generator controller, whose operating mode is controlled by a starter-generator switching box, and whose mechanical output is connected to the engine via a gear set; An engine controller, controlling the starting, ignition and parameter adjustment of the engine; a ground battery connected to the starter generator, and when the engine needs to be started by the starter generator, the ground battery supplies power to the starter generator; A ground load is connected to the starter generator, and when the engine is started, the engine drives the starter generator to supply power to the ground load; An emergency protection box is provided between the starter generator, the ground battery and the ground load; a ground control box connected to the starter generator controller, the starter-generator switching box, the engine controller, and the emergency protection box via signal cables, and displaying operating parameters of the starter generator, the engine, the ground battery, and the ground load via the ground control box; The starting-generating switching box includes: a first aviation socket, disposed on an outer layer of the switching housing; the outer layer of the switching housing is further provided with a first positive terminal, a second positive terminal, a first negative terminal, and a second negative terminal; the first positive terminal and the second positive terminal are connected by a first power supply cable, and the first negative terminal and the second negative terminal are connected by a second power supply cable; The auxiliary starting contactor, the auxiliary power generation contactor and the in-position contactor are connected to the first aviation socket via a first signal cable, and the first aviation socket is connected to the starter generator via a platform cable; A starting contactor, interlocked with the auxiliary starting contactor; The power generation contactor is linked to the auxiliary power generation contactor.

2. The ground starting power generation test platform for UAV engines according to claim 1, characterized in that: The emergency protection box includes: a second aviation socket, disposed on an outer layer of the protective shell; the outer layer of the protective shell is further provided with a third positive terminal, a fourth positive terminal, a third negative terminal, and a fourth negative terminal; the third positive terminal and the fourth positive terminal are connected by a third power supply cable, and the third negative terminal and the fourth negative terminal are connected by a fourth power supply cable; a first current protection sensor, arranged on the third power supply cable; a second current protection sensor, arranged on the fourth power supply cable; The emergency contactor, the first current protection sensor, and the second current protection sensor are connected to the second aviation socket through a second signal cable.

3. The ground starting power generation test platform for UAV engines according to claim 1, characterized in that: The ground control box includes a touch screen and a circuit board. The touch screen is provided with a ground battery status light, a ground battery start switch, a load status light, a load start switch, a generator parameter display bar, an engine parameter display bar, a start button, a reset button and an emergency stop button.

4. The ground starting power generation test platform for UAV engines according to claim 3, characterized in that: The ground battery start switch is controllably connected to the ground battery, the load start switch is controllably connected to the ground load, the emergency stop button is controllably connected to the emergency protection box, and the start button is controllably connected to the starter generator controller.

5. The ground starting power generation test platform for UAV engines according to claim 1, characterized in that: The starter generator, the starter-generator switching box and the emergency protection box are connected by cables. During the starting stage and the power generation stage, the current in the cables flows in opposite directions.

6. The ground starting power generation test platform for UAV engines according to claim 2, characterized in that: The first current protection sensor, the second current protection sensor and the emergency contactor will automatically cut off the current circuit when the current is too large or an abnormal situation occurs.

7. The ground starting power generation test platform for UAV engines according to claim 1, characterized in that: During the starting phase, the in-position contactor and the starting contactor are in the same current loop, and the current loop directions of the power generation contactor during the power generation phase and the starting phase are opposite to each other.

8. The ground starting power generation test platform for UAV engines according to claim 1, characterized in that: The ground storage battery is a lithium battery, the starter generator is a low-voltage DC brushed generator, and the starter generator has two operating modes: starting and generating electricity.

9. A ground starting power generation test method for a UAV engine, using the ground starting power generation test platform for a UAV engine according to any one of claims 1 to 8, characterized in that: The test method includes: The ground control box sends instructions to the starter-generator switching box, the emergency protection box, and the starter generator controller, the ground battery supplies power to the starter generator, and the starter generator drives the engine to rotate through the gear set. After the engine is successfully ignited, the engine starts to rotate, and the engine drives the starter generator to rotate through the gear set. The ground battery stops supplying power to the starter generator, and the emergency protection box monitors the current generated by the starter generator. When the engine drives the starter generator to a speed that reaches a power generation speed, the starter generator controller switches the operation mode of the starter generator, and the starter generator supplies power to the ground load. The parameters of the starter generator and the engine are monitored by the ground control box, and the emergency protection box monitors the current generated by the starter generator.

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