Ignition system of unmanned aerial vehicle

Abstract

The utility model discloses an ignition system of an unmanned aerial vehicle, which relates to the technical field of electronic circuits and comprises an engine cylinder body and a crankshaft, the crankshaft is connected with an inner bearing of the engine cylinder body, a cam shaft is arranged at the outer end of the crankshaft, and a gear is sleeved on the outer surface of the cam shaft. A first mounting support is arranged on the outer surface of the engine cylinder body, and a mounting groove is formed in the middle of the first mounting support. According to the ignition system of the unmanned aerial vehicle, through four groups of independent and symmetrically arranged crankshafts, camshafts, gears and trigger structures, the ignition system of the unmanned aerial vehicle realizes accurate detection of the rotating speed and the position of a four-cylinder engine. The design of the magnetic conductive disc of the gear and the reference positioning function of the tooth missing part are matched with the trigger to be stably fixed by the long kidney-shaped mounting groove of the U-shaped first mounting bracket and the fastening screw, so that the accuracy and the stability of signal capture are ensured, a reliable basis is provided for subsequent ignition control, and the ignition precision and the operation efficiency of an engine are remarkably improved.

Description

Technical Field

[0001] This utility model relates to the field of electronic circuit technology, specifically to an ignition system for unmanned aerial vehicles (UAVs). Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft controlled by radio remote control equipment and their own program control devices, or operated autonomously by an onboard computer, either completely or intermittently. Compared with manned aircraft, UAVs are often more suitable for tasks that are too "dull, dirty, or dangerous".

[0003] However, existing drone ignition systems still have certain problems:

[0004] An existing example, application number CN202020197613.X, describes a novel drone ignition device, including an ignition switch and an off switch, as well as a shielding cover, a support rod, a rotating rod, a conductive block, a magnetic block, and an electromagnet. The advantages of this invention are: integrating the ignition switch and off switch within the shielding cover, and generating magnetism through the alternating energization of two electromagnets, which attracts the magnetic block, causing the rotating rod to rotate. This allows the conductive block on the rotating rod to contact the metal casing of the ignition switch or off switch. Since the conductive block is electrically connected to an external power source, the ignition switch and off switch can be energized, thereby controlling the drone's ignition and shutdown. This eliminates the need for manual operation of ignition and shutdown, improving operational efficiency to a certain extent.

[0005] The existing drone power systems on the market are mostly single-cylinder or dual-cylinder engines. Their ignition systems generally use Hall sensors as input signals, are powered by 12V power, and discharge ignition after voltage boosting. They only have one or two outputs, which have defects such as limited power output and narrow voltage adaptation range, making it difficult to meet the power requirements of high-performance multi-cylinder drone engines.

[0006] Therefore, we propose an unmanned aerial vehicle (UAV) ignition system to address the problems mentioned above. Utility Model Content

[0007] The purpose of this invention is to provide an ignition system for unmanned aerial vehicles (UAVs) to address the problem mentioned in the background art that most UAV power systems on the market use single-cylinder or dual-cylinder engines. Their ignition systems generally use Hall sensors as input signals, are powered by a 12V power supply, and discharge ignition after voltage boosting. They only have one or two outputs, which have defects such as limited power output and narrow voltage adaptability, making it difficult to meet the power requirements of high-performance multi-cylinder UAV engines.

[0008] To achieve the above objectives, this utility model provides the following technical solution: an unmanned aerial vehicle (UAV) ignition system, comprising an engine block and a crankshaft:

[0009] The engine block has an internal bearing connected to a crankshaft. A camshaft is located at the outer end of the crankshaft, and a gear is fitted onto the outer surface of the camshaft. A first mounting bracket is located on the outer surface of the engine block, and a mounting groove is formed in the middle of the first mounting bracket. A trigger is located above the engine block, and extension plates are welded to both ends of the trigger. A fastening screw passes through the middle of the extension plates. A second mounting bracket is welded to the outer side of the engine block, and an ignition controller is mounted on the outer surface of the second mounting bracket. A third mounting bracket is welded to the outer side of the engine block, and a high-voltage transformer is mounted on the outer surface of the third mounting bracket. An interface is located above the high-voltage transformer.

[0010] Using the above technical solution, the crankshaft rotation drives the camshaft and gear rotation. The trigger generates an AC voltage signal by detecting the change in the tooth groove of the gear, and transmits it to the ignition controller to calculate the ignition angle, drive the high-voltage pack to generate high-voltage ignition, realize the precise ignition of the four-cylinder drone engine, improve power performance, and support wide voltage power supply to enhance environmental adaptability.

[0011] Preferably, the gear is a magnetically conductive disk structure, the gear includes a tooth-deficient portion with a wide tooth pitch on the outer surface, and the gear has a central hole in the middle that is adapted to the camshaft.

[0012] Using the above technical solution, the gear acts as a magnetic disk. When it rotates, the tooth grooves alternately pass through the trigger to generate changes in magnetic flux. The missing tooth section is used for reference positioning through a special tooth spacing design. The trigger generates speed and position signals accordingly. Through the mechanical structure of the missing tooth section and the center hole, the gear achieves precise speed detection and position feedback, providing a reliable input signal to the ignition controller and ensuring sequential ignition of the four-cylinder engine.

[0013] Preferably, the crankshaft, camshaft, gears, and trigger are arranged in four sets along the engine block.

[0014] By adopting the above technical solution, the configuration of four sets of crankshafts, camshafts, gears, and triggers enables each cylinder to independently have a speed detection and ignition triggering mechanism. When the gears rotate, they generate signals through changes in the tooth grooves. The triggers then generate four synchronous speed and position signals. Through four independent structures, the precise sequential ignition of the four-cylinder engine is achieved, ensuring that the ignition timing of each cylinder is consistent, which significantly improves the stability of power output and the operating efficiency of the engine.

[0015] Preferably, the ignition controller and the high-voltage coil are each arranged in four sets along the outer side of the engine block.

[0016] Using the above technical solution, the four ignition controllers receive the speed and position signals of the corresponding triggers, independently calculate the ignition angle of each cylinder, and drive the high-voltage transformer to generate high-voltage ignition, forming a four-way synchronous ignition control. Through the four independently controlled ignition controllers and high-voltage transformers, the precise sequential ignition of the four-cylinder engine is achieved, ensuring uniform power output of each cylinder and significantly improving the engine's running stability and power performance.

[0017] Preferably, the first mounting bracket has a U-shaped structure, and two sets of the first mounting bracket are symmetrically arranged along the trigger, and the mounting groove is elongated, and the trigger is fixedly connected to the engine cylinder block by fastening screws.

[0018] Using the above technical solution, the U-shaped structure and elongated mounting groove design of the first mounting bracket facilitate the precise positioning and flexible adjustment of the trigger. The two sets of symmetrical brackets are used to firmly fix the trigger to the engine block with fastening screws, ensuring its precise relative position with the gear. Through this structural layout, the trigger can stably detect the speed and position signals of the gear, providing a reliable input to the ignition controller, thereby ensuring the precise ignition and efficient operation of the four-cylinder engine.

[0019] Preferably, the second mounting bracket has an L-shaped structure, and mounting plates are welded to the upper and lower end faces of the ignition controller, and the mounting plates are fixedly connected to the second mounting bracket by bolts.

[0020] By adopting the above technical solution, the L-shaped structure of the second mounting bracket provides a stable support for the ignition controller. The ignition controller is reliably installed on the engine block through the fixed connection of the mounting plate and bolts, which ensures the stability of the ignition controller during operation, reduces the impact of vibration on ignition accuracy, and thus ensures the normal operation and high efficiency of the four-cylinder engine ignition system.

[0021] Compared with the prior art, the beneficial effects of this utility model are:

[0022] 1. Through four sets of independent and symmetrically arranged crankshafts, camshafts, gears, and triggers, the UAV ignition system achieves precise detection of the speed and position of a four-cylinder engine. The magnetic disk design of the gears and the reference positioning function of the missing teeth, combined with the trigger's secure fixation in the long waist-shaped mounting slot of the U-shaped first mounting bracket and the fastening screws, ensures the accuracy and stability of signal capture, providing a reliable basis for subsequent ignition control and significantly improving engine ignition accuracy and operating efficiency.

[0023] 2. The independent configuration of four ignition controllers and the high-voltage transformer, along with the stable mounting method of the L-shaped second mounting bracket welded to the third mounting bracket, enables precise sequential ignition of the four-cylinder engine. The ignition controller is fixed to the second mounting bracket via a mounting plate and bolts, and the high-voltage transformer outputs a high-voltage spark through an interface. This design not only simplifies the system structure but also improves the reliability and durability of the ignition system, ensuring stable operation and high-efficiency performance of the UAV engine in complex environments. Attached Figure Description

[0024] Figure 1 This is a front view schematic diagram of the structure of this utility model;

[0025] Figure 2 This is a schematic diagram of the rear structure of the main body of this utility model;

[0026] Figure 3 This is a schematic diagram of the crankshaft and gear connection structure of this utility model;

[0027] Figure 4 This is a schematic diagram of the installation structure of the ignition controller and high-voltage transformer of this utility model;

[0028] Figure 5 This is a schematic diagram of the trigger installation structure of this utility model;

[0029] Figure 6 This is a schematic diagram of the gear structure of this utility model.

[0030] In the diagram: 1. Engine block; 2. Crankshaft; 3. Camshaft; 4. Gear; 401. Missing tooth section; 402. Center hole; 5. First mounting bracket; 6. Mounting slot; 7. Trigger; 8. Extension plate; 9. Fastening screw; 10. Second mounting bracket; 11. Ignition controller; 12. Mounting plate; 13. Third mounting bracket; 14. High voltage transformer; 15. Interface. Detailed Implementation

[0031] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0032] Please see Figures 1-6This utility model provides a technical solution: an ignition system for unmanned aerial vehicles (UAVs), comprising an engine block 1 and a crankshaft 2. The crankshaft 2 is connected to an internal bearing in the engine block 1. A camshaft 3 is located at the outer end of the crankshaft 2. A gear 4 is fitted onto the outer surface of the camshaft 3. A first mounting bracket 5 is located on the outer surface of the engine block 1. A mounting groove 6 is formed in the middle of the first mounting bracket 5. A trigger 7 is located above the engine block 1. Extension plates 8 are welded to both ends of the trigger 7. A fastening screw 9 passes through the middle of the extension plates 8. A second mounting bracket 10 is welded to the outer side of the engine block 1. An ignition controller 11 is mounted on the outer surface of the second mounting bracket 10. A third mounting bracket 13 is welded to the outer side of the engine block 1. A high-voltage transformer 14 is mounted on the outer surface of the third mounting bracket 13. An interface 15 is located above the high-voltage transformer 14. The gear 4 is a magnetically conductive disc structure. The gear 4 includes a toothed portion 401 with a wide tooth pitch on its outer surface. A central hole 402, adapted to the camshaft 3, is formed in the middle of the gear 4. The crankshaft 2, camshaft 3, gear 4, and trigger 7 are each arranged in four sets along the engine block 1. The ignition controller 11 and high-voltage coil 14 are each arranged in four sets along the outer side of the engine block 1. The first mounting bracket 5 has a U-shaped structure, and two sets of the first mounting bracket 5 are symmetrically arranged along the trigger 7. The mounting groove 6 is elongated, and the trigger 7 is fixedly connected to the engine block 1 by fastening screws 9. The second mounting bracket 10 has an L-shaped structure. Mounting plates 12 are welded to the upper and lower end faces of the ignition controller 11, and the mounting plates 12 are fixedly connected to the second mounting bracket 10 by bolts.

[0033] The engine block 1 is connected to the crankshaft 2 via an internal bearing. The outer end of the crankshaft 3 is fitted with a gear 4 of a magnetic disk structure. The toothed part 401 of the gear 4 is used as a positioning reference. The four crankshafts 2, camshafts 3, gears 4 and triggers 7 are symmetrically arranged along the engine block 1. The triggers 7 are firmly fixed above the engine block 1 by the long waist-shaped mounting groove 6 of the U-shaped first mounting bracket 5 and the fastening screws 9, so as to accurately capture the speed and position signals of the gear 4. The four ignition controllers 11 are fixed to the engine block 1 by bolts through the L-shaped second mounting bracket 10 and mounting plate 12 welded to the outside of the engine block 1. After receiving the signal from the triggers 7, they calculate the ignition angle and drive the corresponding four high-voltage transformers 14 to generate high-voltage ignition through the interface 15. This system achieves precise sequential ignition of the four-cylinder engine through the coordinated work of four independent mechanical and electronic components, ensuring smooth and efficient power output.

[0034] Working principle: For this type of drone ignition system, the crankshaft 2 connected to the bearing inside the engine cylinder 1 rotates with the engine, driving the outer camshaft 3 and the magnetic disk structure gear 4 sleeved on it to rotate synchronously. The missing tooth part 401 on the gear 4 serves as a reference positioning point. The four triggers 7 are firmly installed above the engine cylinder 1 through the long waist-shaped mounting groove 6 of the U-shaped first mounting bracket 5 and the fastening screws 9, so as to accurately capture the magnetic flux signal generated by the change of the tooth groove when the gear 4 rotates. The triggers 7 transmit the signal to the four corresponding ignition controllers 11. The ignition controllers 11 are fixed to the L-shaped second mounting bracket 10 by the mounting plates 12 welded to their upper and lower end faces and bolts. After receiving the signal, they calculate the ignition angle and drive the four corresponding high voltage transformers 14 to generate high voltage electric sparks through the interface 15 to achieve precise sequential ignition of the four-cylinder engine.

[0035] This completes a series of tasks. The contents not described in detail in this specification are existing technologies known to those skilled in the art.

[0036] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An ignition system for an unmanned aerial vehicle (UAV), comprising an engine block (1) and a crankshaft (2), characterized in that: The engine cylinder block (1) has an internal bearing connected to a crankshaft (2), and a camshaft (3) is provided at the outer end of the crankshaft (2). A gear (4) is sleeved on the outer surface of the camshaft (3). A first mounting bracket (5) is provided on the outer surface of the engine cylinder block (1). A mounting groove (6) is provided in the middle of the first mounting bracket (5). A trigger (7) is provided above the engine cylinder block (1). An extension plate (8) is welded to both ends of the trigger (7). A fastening screw (9) passes through the middle of the extension plate (8). A second mounting bracket (10) is welded to the outer side of the engine cylinder block (1). An ignition controller (11) is installed on the outer surface of the second mounting bracket (10). A third mounting bracket (13) is welded to the outer side of the engine cylinder block (1). A high-voltage transformer (14) is installed on the outer surface of the third mounting bracket (13). An interface (15) is provided above the high-voltage transformer (14).

2. The unmanned aerial vehicle (UAV) ignition system according to claim 1, characterized in that: The gear (4) is a magnetic disk structure. The gear (4) includes a tooth-deficient part (401) with a wide tooth pitch on the outer surface. The gear (4) has a central hole (402) in the middle that is compatible with the camshaft (3).

3. The unmanned aerial vehicle (UAV) ignition system according to claim 1, characterized in that: The crankshaft (2), camshaft (3), gear (4), and trigger (7) are all arranged in four sets along the engine block (1).

4. The unmanned aerial vehicle (UAV) ignition system according to claim 1, characterized in that: The ignition controller (11) and the high voltage pack (14) are each arranged in four sets along the outer side of the engine block (1).

5. The unmanned aerial vehicle (UAV) ignition system according to claim 1, characterized in that: The first mounting bracket (5) is a U-shaped structure, and two sets of the first mounting bracket (5) are symmetrically arranged along the trigger (7), and the mounting groove (6) is long and narrow, and the trigger (7) is fixedly connected to the engine cylinder (1) by fastening screws (9).

6. The unmanned aerial vehicle (UAV) ignition system according to claim 1, characterized in that: The second mounting bracket (10) has an L-shaped structure. The upper and lower end faces of the ignition controller (11) are welded with mounting plates (12), and the mounting plates (12) are fixedly connected to the second mounting bracket (10) by bolts.

Images