Aircraft driven by small single-cylinder aviation piston engine

Abstract

The invention discloses an aircraft driven by a small-sized single-cylinder aviation piston engine, which comprises a cabin with a columnar mounting cavity, the small-sized single-cylinder aviation piston engine is arranged in the columnar mounting cavity, and a water cooler communicated with a cooling water path of the small-sized single-cylinder aviation piston engine is arranged in the columnar mounting cavity. The windward side of a heat dissipation core body of the water cooler faces the axial direction of the columnar installation cavity, and the water cooler is flexibly connected with the inner wall of the cabin through a damping piece. According to the scheme, the problem that in the prior art, a small single-cylinder aviation piston engine is installed in a long and narrow cabin of an aircraft, power instability is prone to occurring is solved.

Description

Technical Field

[0001] The present invention relates to an aircraft, in particular to an aircraft driven by a small single-cylinder aviation piston engine. Background Art

[0002] A small single-cylinder aviation piston engine is an engine that only has one cylinder, piston, connecting rod and crankshaft, and its power does not exceed 25 horsepower. Due to its simple structure and light weight, it has high fuel utilization rate and good fuel economy under medium and small load conditions. Moreover, because the small single-cylinder aviation piston engine has a simple structure and few parts, its manufacturing cost is low, the failure probability is low, and the maintenance cost is low. In order to meet the space installation requirements and aerodynamic needs of the aircraft, the overall structure of the small single-cylinder aviation piston engine is relatively compact, approximately cylindrical or regular quadrangular prism-shaped, so as to be easily installed in the engine compartment of the aircraft and match the overall structure of the aircraft.

[0003] Since a large amount of heat is generated when the aviation piston engine is working, a cooling system is also provided for cooling. The existing cooling methods mainly include air cooling and water cooling. Among them, the water cooling method is widely used due to its high heat transfer efficiency and good temperature control stability. In the water cooling method, the key component for heat dissipation and cooling is the water cooler. The water cooler includes an inlet chamber and an outlet chamber. A heat dissipation core is arranged between the inlet chamber and the outlet chamber. The heat dissipation core has multiple groups of heat dissipation tubes connecting the inlet chamber and the outlet chamber. The inlet chamber is connected to the outlet pipe of the engine, and the outlet chamber is connected to the inlet pipe of the engine. Thus, the cooling water in the engine is discharged into the inlet chamber through the outlet pipe, then flows through the heat dissipation tubes from the inlet chamber and enters the outlet chamber, and finally flows through the inlet pipe from the outlet chamber and returns to the engine, realizing the circulating flow of the cooling water. When the cooling water flows through the engine, it will absorb the heat of the engine and increase in temperature. When flowing through the heat dissipation tubes, it will dissipate heat and cool down through the heat exchange between the heat dissipation tubes and the air. Thus, the cooling water realizes the cooling of the engine through the circulating flow.

[0004] Generally, the water coolers installed on existing aero-engines are welded or riveted with hanging brackets on the water chambers or side plates of the water coolers, and are connected to the outer frame of the engine through the brackets. In this way, the use of the water cooler requires the engine compartment for installing the aero-engine to have a relatively spacious installation space. Therefore, in the prior art, the water cooler is mainly used on multi-cylinder aero-engines or on small single-cylinder aero-piston engines with relatively spacious installation space. When using a water cooler on an aircraft with a relatively narrow installation space in the engine compartment for installing a small single-cylinder aero-piston engine, only by greatly reducing the volume of the water cooler can the installation requirements be met. However, it is found in use that such small single-cylinder aero-piston engines used on aircraft with relatively narrow installation spaces are prone to overheating. The high temperature reduces the air density, the amount of air inhaled by the engine decreases, and the density and oxygen content of the mixture in the combustion chamber decrease accordingly, resulting in incomplete combustion, a drop in engine power, and unstable power of the aircraft.

[0005] Chinese patent document CN219888148U discloses an aero-engine, including a cylinder block structure system, a crank connecting rod system, a transmission system, an intake system, an exhaust system, a fuel system, a lubrication system, an ignition system, and a power generation system. It is characterized in that: the cylinder block structure system, the crank connecting rod system, the transmission system, and the power generation system are arranged in a straight line in sequence; the exhaust system is located on the side of the crank connecting rod system and extends from one side of the cylinder block structure system towards the power generation system; the fuel injection device of the fuel system is located on the side of the cylinder block structure system away from the crank connecting rod system; the ignition actuator of the ignition system is located on the side of the cylinder block structure system away from the crank connecting rod system; the fuel tank of the lubrication system is located on the side of the transmission system, and the oil pump of the lubrication system is located on the side of the cylinder block structure system. This prior art aero-engine is actually a small single-cylinder aero-piston engine. By designing the overall structure into a cuboid shape with a square cross-section and having a compact structure, it is convenient to install the engine into a narrow and long engine compartment with a square cross-section and limited space while ensuring the engine performance. Such aero-engines mostly use air cooling for cooling, which greatly limits the power performance of the aero-engine, and thus also affects the power performance of the aircraft using the single-cylinder aero-piston engine.

[0006] Chinese Patent Document CN212508542U discloses a single-cylinder piston opposed start or / and power generation integrated unmanned aerial engine, including: a cylinder, including a cylinder block, the cylinder block is a through tubular structure, and the two ends of the cylinder block are provided with opposed pistons and valve mechanisms. One side of the piston close to the end of the cylinder block is movably connected with a connecting rod, and the other end of the connecting rod is connected with a rotating shaft, and the rotating shaft includes a first rotating shaft and a second rotating shaft; a cooler, the cooler is connected with the cylinder to cool the cylinder; a one-key starter for starting the rotation of the rotating shaft; wherein, the rotating shaft is respectively connected with the rotors of the unmanned aircraft, and after the rotating shaft is started and rotated, it drives the connecting rod to drive the piston to compress the combustibles injected into the cylinder from both sides. Through the combustion of the combustibles, mechanical kinetic energy is generated to drive the first rotating shaft and the second rotating shaft to rotate, and then drive the rotors of the unmanned aircraft to rotate. In fact, there are two cylinders in the existing technical solution, and the two pistons share one cylinder block, which is not a single-cylinder aviation piston engine in the traditional sense. Such an aviation engine is relatively large in size and difficult to be installed in a narrow cabin. Since the engine in the existing technical solution is relatively large in size, there is enough space beside the engine for installing the cooler, so the cylinder can be cooled by installing the cooler on the side of the cylinder block. However, such an aviation engine cannot be installed in an aircraft with a narrow cabin where the installation space is limited.

[0007] Therefore, how to improve the phenomenon that the power of an aircraft with a small single-cylinder aviation piston engine installed in a narrow cabin is prone to instability has become an urgent problem to be solved at present. Summary of the Invention

[0008] The purpose of the present invention is to provide an aircraft driven by a small single-cylinder aviation piston engine to solve the problem that the power of an aircraft with a small single-cylinder aviation piston engine installed in a narrow cabin in the prior art is prone to instability.

[0009] To achieve the above purpose, the basic solution of the present invention provides an aircraft driven by a small single-cylinder aviation piston engine, including a cabin with a columnar installation cavity, a small single-cylinder piston engine is arranged in the columnar installation cavity, a water cooler communicated with the cooling water circuit of the small single-cylinder piston engine is arranged in the columnar installation cavity, the windward surface of the heat dissipation core of the water cooler faces the axial direction of the columnar installation cavity, and the water cooler is flexibly connected with the inner wall of the cabin through a damping member.

[0010] The beneficial effects of this basic solution are as follows: By adopting this solution, a water cooler is arranged in the cabin of the aircraft, and the water cooler is flexibly connected to the inner wall of the cabin through a damping member, so that the inner wall of the cabin supports and positions the water cooler, greatly reducing the vibration amplitude generated when the small single-cylinder piston engine works, and avoiding the situation where the water cooler vibrates and fails in the cabin; at the same time, such an arrangement enables the heat dissipation surface of the water cooler to dissipate heat better, and the airflow flowing through the cabin passes through the heat dissipation core of the water cooler to take away the heat of the water cooler, thereby avoiding the phenomenon that the small single-cylinder piston engine fails due to insufficient cooling effect. Therefore, by adopting this solution, the small single-cylinder aviation piston engine can also obtain good cooling effect when installed in a narrow cabin, avoiding the influence of cooling failure and insufficiency on the engine, and thus solving the problem that the aircraft with a small single-cylinder aviation piston engine installed in a narrow cabin is prone to power instability.

[0011] Preferably, the small single-cylinder piston engine and the water cooler are sequentially distributed along the axial direction of the columnar installation cavity. With such an arrangement, the influence of the engine on the installation of the water cooler can be reduced, which is beneficial to further improving the cooling effect of the water cooler on the engine, and thus ensuring the power stability of the aircraft.

[0012] Preferably, the water cooler is in a plate shape, and the circumferential edges of the water cooler are all flexibly connected to the inner wall of the cabin through the damping members. With such an arrangement, the water cooler occupies less space while ensuring the cooling effect, which is beneficial to further improving the cooling effect of the water cooler on the engine, and thus ensuring the power stability of the aircraft.

[0013] Preferably, the areas of the water cooler connected to the cooling water circuit are symmetrically distributed about the center. With such an arrangement, the acting forces on the water cooler from the engine are more evenly distributed, which is beneficial to improving the stability of the water cooler, and thus beneficial to further ensuring the cooling effect of the water cooler.

[0014] Preferably, the damping member is a rubber sleeve wrapped around the edge of the water cooler, and the water cooler abuts against the inner wall of the cabin through the rubber sleeve. With such an arrangement, when the water cooler abuts against the inner wall of the cabin through the rubber sleeve, the rubber sleeve will be compressed, so that the water cooler receives a force from the circumferential edge towards the middle of the water cooler, and thus the entire water cooler receives a compressive force from the four edges towards the middle. This compressive force can effectively offset the tensile force generated when the water cooler vibrates, and thus the water cooler is not easily damaged under the vibration; at the same time, the damping effect of the rubber sleeve can also reduce the vibration acting on the water cooler, and thus the water cooler is less likely to vibrate and be damaged.

[0015] Preferably, the rubber sleeve is provided with a limiting groove that engages with the uneven edges of the water cooler, and the circumferential side, the windward side, and the leeward side of the edge of the water cooler are all in contact with the inner surface of the limiting groove. With such a setting, the water cooler is supported and limited in six directions: front and back, left and right, up and down, so that the water cooler can move slightly in six directions through the rubber sleeve to weaken the destructive effect of vibration on the water cooler, which is conducive to further improving the durability and reliability of the water cooler.

[0016] Preferably, the rubber sleeve is provided with a groove extending along the axial direction of the columnar installation cavity. With such a setting, when the water cooler is assembled into the engine compartment along the axial direction of the columnar installation cavity, the extending direction of the groove is consistent with the assembly movement direction of the water cooler, which is conducive to reducing the frictional resistance generated by the rubber sleeve, and thus conducive to reducing the adverse impact of the rubber sleeve on the installation of the water cooler.

[0017] Preferably, the width of the cross-section of the groove gradually decreases from the top to the bottom of the groove. With such a setting, a gradually increasing stiffness can be formed in the compression direction of the groove, taking into account vibration absorption and position control, and can better improve the adaptability of the water cooler to different vibration environments.

[0018] Preferably, a threaded bushing is connected to the rubber sleeve, and the threaded bushing is connected to the engine compartment by screws. With such a setting, the position of the water cooler in the engine compartment is limited by the screws and the threaded bushing, thus avoiding a large deviation in the installation position of the water cooler in the engine compartment, which is conducive to improving the structural stability of the water cooler.

[0019] Preferably, the outer contour of the water cooler is rectangular, and the outer contour of the heat dissipation core is parallelogram-shaped. With such a setting, it is conducive to further improving the cooling effect of the water cooler, which is conducive to further ensuring the power stability of the aircraft.

[0020] The present invention has the following beneficial effects: By adopting the present invention, by arranging a water cooler in the engine compartment and using the inner wall of the engine compartment to support and limit the water cooler through damping members, the vibration amplitude generated when the small single-cylinder piston engine works is greatly reduced, avoiding the situation that the water cooler vibrates and fails in the engine compartment, and the water cooler will not be affected by the installation space of the small single-cylinder piston engine and shrink. Thus, the small single-cylinder aviation piston engine can also obtain a good cooling effect when installed in a narrow engine compartment, avoiding the influence of cooling failure or insufficient cooling on the engine, and thus solving the problem that the aircraft with a small single-cylinder aviation piston engine installed in a narrow engine compartment is prone to power instability. Description of the Drawings

[0021] Figure 1Schematic diagram of the cabin part of an embodiment of an aircraft driven by a small single-cylinder aviation piston engine according to the present invention; Figure 2 is Figure 1 Schematic diagram after omitting the part of the cabin outside the small single-cylinder aviation piston engine; Figure 3 is Figure 2 End view along the axial direction of the cabin when the water cooler, damping member and cabin are in a mating state in [reference numeral]; Figure 4 is Figure 3 Partial cross-sectional view of the water cooler and the damping member in a mating state in [reference numeral]; Figure 5 is Figure 1 Stereogram of the water cooler and the damping member in a mating state in [reference numeral]. Specific embodiments

[0022] As is known to those skilled in the art, a narrow and long cabin refers to a cabin with a length-to-diameter ratio greater than 2.5.

[0023] The following is a further detailed description through specific embodiments: The reference numerals in the accompanying drawings of the specification include: cabin 1, screw 2, water cooler 3, heat dissipation core 31, water outlet chamber 32, engine inlet pipe 4, water pump 5, small single-cylinder piston engine 6, engine outlet pipe 7, rubber sleeve 8, threaded bushing 81, groove 82.

[0024] The embodiment is basically as shown in the appendix Figures 1 to 5 An aircraft driven by a small single-cylinder aviation piston engine includes a cabin 1 having a columnar installation cavity, and a small single-cylinder piston engine 6 is arranged in the columnar installation cavity. In this embodiment, the cross-section of the columnar installation cavity of the cabin 1 is rectangular. A water cooler 3 communicated with the cooling water path of the small single-cylinder piston engine 6 is arranged in the columnar installation cavity. Specifically, an engine outlet pipe 7 and an engine inlet pipe 4 are connected between the water cooler 3 and the small single-cylinder piston engine 6. A water pump 5 for driving the cooling water to flow is installed on the engine inlet pipe 4, so that a cooling water circulation path is formed by the cooling water path, the engine outlet pipe 7, the water cooler 3, the engine inlet pipe 4 and the water pump 5. Both the engine outlet pipe 7 and the engine inlet pipe 4 are made of hoses or partially made of hoses, so that the vibration transmission effect between the small single-cylinder piston engine 6 and the water cooler 3 can be greatly weakened.

[0025] In this embodiment, the small single-cylinder piston engine 6 and the water cooler 3 are sequentially distributed along the axial direction of the columnar installation cavity. The windward surface of the heat dissipation core 31 of the water cooler 3 is arranged towards the axial direction of the columnar installation cavity, and the water cooler 3 is flexibly connected to the inner wall of the engine compartment 1 through a damping member. In this embodiment, the water cooler 3 is in a plate shape, and the water cooler 3 is arranged with its plate surface parallel to the cross-section of the columnar installation cavity, so that the airflow flowing along the axial direction of the columnar installation cavity can act on the water cooler 3 to the greatest extent. The circumferential edges of the water cooler 3 are all flexibly connected to the inner wall of the engine compartment 1 through damping members. In this embodiment, the outer contour of the water cooler 3 is rectangular, the heat dissipation core 31 of the water cooler 3 is located in the middle, the water inlet chamber and the water outlet chamber 32 of the water cooler 3 are respectively located on both sides of the heat dissipation core 31, and the heat dissipation core 31 is provided with heat dissipation pipes connecting the water inlet chamber and the water outlet chamber 32. The water inlet chamber of the water cooler 3 is connected to the engine outlet pipe 7, and the water outlet chamber 32 of the water cooler 3 is connected to the engine inlet pipe 4. In this embodiment, the position where the water inlet chamber is connected to the engine outlet pipe 7 and the position where the water outlet chamber 32 is connected to the engine inlet pipe 4 are symmetrically distributed about the center on the water cooler 3, so that the areas on the water cooler 3 connected to the cooling water circuit are symmetrically distributed about the center, and further, the acting forces transmitted from the small single-cylinder piston engine 6 to the water cooler 3 through the engine inlet pipe 4 and the engine outlet pipe 7 are evenly distributed on the water cooler 3, which is beneficial to improving the stability of the water cooler 3.

[0026] In this embodiment, the outer contour of the heat dissipation core 31 of the water cooler 3 is in a parallelogram shape, which is beneficial to increasing the area of the heat dissipation core 31 as much as possible and improving the heat dissipation performance of the water cooler 3. In this embodiment, the damping member is preferably a rubber sleeve 8 wrapped around the edge of the water cooler 3, and the water cooler 3 abuts against the inner wall of the engine compartment 1 through the rubber sleeve 8. The rubber sleeve 8 is provided with a limiting groove that engages with the unevenness of the edge of the water cooler 3, and the circumferential side surface, the windward surface, and the leeward surface of the edge of the water cooler 3 are all in contact with the inner surface of the limiting groove. The rubber sleeve 8 is provided with a groove 82 extending along the axial direction of the columnar installation cavity. When the water cooler 3 is assembled into the engine compartment 1, the water cooler 3 is slid along the axial direction of the columnar installation cavity to the installation position. By extending the extending direction of the groove 82 along the axial direction of the columnar installation cavity, the resistance caused by the groove 82 during the assembly of the water cooler 3 can be reduced, thereby reducing the assembly difficulty. In this embodiment, the width of the cross-section of the groove 82 gradually decreases from the groove top to the groove bottom, which is beneficial to improving the adaptability of the water cooler 3 to different vibration environments. A threaded bushing 81 is connected to the rubber sleeve 8, and the threaded bushing 81 is connected to the engine compartment 1 through a screw 2.

[0027] With this solution, by installing a water cooler 3 in the cabin 1 of the aircraft, the water cooler 3 is flexibly connected to the inner wall of the cabin 1 through damping members, so that the inner wall of the cabin 1 supports and limits the water cooler 3, greatly reducing the vibration amplitude generated when the small single-cylinder piston engine 6 operates, and avoiding the situation where the water cooler 3 vibrates and is damaged and fails in the cabin 1. At the same time, such a setting enables the heat dissipation surface of the water cooler 3 to dissipate heat better. The airflow flowing through the cabin 1 passes through the heat dissipation core 31 of the water cooler 3 and takes away the heat of the water cooler 3, thereby avoiding the phenomenon that the small single-cylinder piston engine 6 fails due to insufficient cooling effect. Therefore, with this solution, the small single-cylinder aviation piston engine can also obtain good cooling effect when installed in the narrow cabin 1, avoiding the influence of cooling failure and insufficiency on the engine, and thus solving the problem that the aircraft with a small single-cylinder aviation piston engine installed in the narrow cabin 1 is prone to power instability.

[0028] The above are only embodiments of the present invention. Specific structures and common knowledge such as characteristics known in the solution are not described in detail here. It should be pointed out that for those skilled in the art, without departing from the structure of the present invention, several deformations and improvements can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the implementation effect of the present invention and the practicality of the patent.

Claims

1. An aircraft driven by a small single-cylinder aviation piston engine, comprising a cabin with a columnar mounting cavity, wherein a small single-cylinder piston engine is arranged in the columnar mounting cavity, characterized in that: A water cooler connected to the cooling water circuit of a small single-cylinder piston engine is arranged in the columnar mounting cavity. The windward surface of the heat dissipation core of the water cooler is arranged axially toward the columnar mounting cavity. The water cooler is flexibly connected to the inner wall of the cabin through a damping member.

2. A small single-cylinder aviation piston engine driven aircraft according to claim 1, characterized in that: The small single-cylinder piston engine and the water cooler are sequentially distributed along the axial direction of the columnar installation cavity.

3. A small single-cylinder aviation piston engine-driven aircraft according to claim 2, characterized in that: The water cooler is plate-shaped, and the peripheral edges of the water cooler are flexibly connected to the inner wall of the cabin through the damping member.

4. A small single-cylinder aviation piston engine driven aircraft according to claim 3, characterized in that: The areas on the water cooler connected to the cooling water channel are distributed in a centrally symmetrical manner.

5. A small single-cylinder aviation piston engine driven aircraft according to claim 1, 2, 3 or 4, characterized in that: The damping member is a rubber sleeve wrapped around the edge of the water cooler, and the water cooler is abutted against the inner wall of the cabin through the rubber sleeve.

6. A small single-cylinder aviation piston engine-driven aircraft according to claim 5, characterized in that: The rubber sleeve is provided with a limiting groove which is concave-convexly matched with the edge of the water cooler, and the circumferential side surface, the windward surface and the leeward surface of the edge of the water cooler are all in contact with the inner surface of the limiting groove.

7. A small single-cylinder aviation piston engine driven aircraft according to claim 6, characterized in that: The rubber sleeve is provided with a groove extending along the axial direction of the columnar installation cavity.

8. The small single-cylinder aviation piston engine-driven aircraft according to claim 7, characterized in that: The width of the cross section of the groove gradually decreases from the groove top to the groove bottom.

9. A small single-cylinder aviation piston engine-driven aircraft according to claim 8, characterized in that: The rubber sleeve is connected with a threaded bushing, and the threaded bushing is connected to the cabin through screws.

10. A small single-cylinder aviation piston engine driven aircraft according to claim 9, characterized in that: The outer contour of the water cooler is rectangular, and the outer contour of the heat dissipation core is a parallelogram.

Images