A lightweight unmanned aerial vehicle aviation engine with an integrally formed air intake

Abstract

The present invention provides a lightweight unmanned aerial vehicle aviation engine with an integrally formed air intake duct, which includes an engine body, and two groups of cylinder blocks and cylinder heads located at both ends of the engine body. An air intake cavity is provided on one side of the engine body, and an air inlet is opened outward on the outer wall of the air intake cavity. Air intake ducts are opened on the side walls of the cylinder heads and cylinder blocks, which are connected from the cylinder block to the inside of the cylinder head and communicate with the inside of the cylinder head. The air intake ducts are integrally formed with the cylinder heads on the side surfaces of the cylinder heads. Through the integrated design of the air intake ducts and the cylinder blocks, the present invention ingeniously solves the contradictory problem that the engine body temperature is too high and the air intake manifold needs to be heated, effectively realizes the thermal balance of heat energy utilization, saves energy consumption, and at the same time saves space in the overall volume of the engine, has a regular structure, and realizes lightweight and energy-saving designs.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine, and particularly to an engine for lightweight unmanned aerial vehicle with integrally formed air intake duct. Background Art

[0002] At present, piston aero-engines are widely used in small unmanned aerial vehicles and unmanned small aircraft. Their advantages are miniaturization, mature technology and stable operation. However, for such engines currently, air needs to be injected into the cylinder through an air intake pipe. Therefore, generally, there are two external air intake pipes connected to the cylinder head. Such a structure has long been a conventional design in the industry and has been used for many years. Although such a structure is mature, there are still some drawbacks. For example, the integrity is not high, the shape is bulky and not regular enough. When placed in a high-altitude and low-temperature environment, the intake manifold will have aerosol. For example, for Rotax engines, additional electricity is required to heat the intake manifold to eliminate the fog, resulting in additional energy consumption. At the same time, the steel and machine clamps of the engine will have too high temperature due to the operation of the engine. Summary of the Invention

[0003] To solve the deficiencies and defects existing in the above-mentioned prior art, through research and design, the inventor has ingeniously solved the contradictory problem of the over-high temperature of the engine body and the need to heat the intake manifold by designing the integration of the air intake duct and the cylinder block, effectively achieving the thermal balance of heat energy utilization, saving energy consumption, and at the same time saving space in the overall volume of the engine, making the structure regular, and realizing the lightweight and energy-saving design. Specifically, the present invention is realized as follows:

[0004] An engine for lightweight unmanned aerial vehicle with integrally formed air intake duct includes an engine body, and two groups of cylinder blocks and cylinder heads located at both ends of the engine body. An air intake cavity is provided on one side of the engine body, and an air inlet is opened outward on the outer wall of the air intake cavity. Intake ducts communicating from the cylinder block to the inside of the cylinder head are opened on the side walls of the cylinder head and the cylinder block, and the intake ducts are integrally formed with the cylinder head on the side surface of the cylinder head.

[0005] Further, a side port is opened at the contact position between the engine body and the cylinder head, and an inclined air duct is provided below the side port. The inclined air duct is closely distributed along the structure of the engine body and communicates with the air intake cavity.

[0006] Further, the cross-section of the intake duct can be in the shape of a rounded rectangle, a circle or an ellipse.

[0007] Further, the intake ducts on the two cylinder heads are axially symmetrically distributed with respect to the air inlet.

[0008] Further, the air inlet duct extends along the extension direction of the cylinder head from the bottom of the cylinder head close to the side wall of the cylinder head to the top of the cylinder head, and forms a transverse bending part in the area of the top of the cylinder head. The bending part extends towards the middle of the cylinder head and communicates with the intake manifold in the cylinder head.

[0009] Further, the bending part is provided with the other half airway cover adapted to the half side air inlet duct on the cylinder head body. The half side air inlet duct and the other half airway cover form the air inlet duct in the cylinder head part. A sealing cover is installed on the side port above the inclined air duct, and the sealing cover is installed on the cavity of the air inlet chamber.

[0010] Introduction to the working principle and beneficial effects of the present invention: When the engine is in flight, a large amount of air will rush into the air inlet and enter the air inlet chamber. The air inlet chamber is in direct contact with the engine body, which can achieve a certain degree of air cooling for the body wall. At the same time, there are two intake ducts in the air inlet chamber leading to their respective cylinder heads, and the intake ducts are also arranged integrally along the cylinder wall. During the process of the air flow passing through the intake ducts, a part of the heat on the surface of the intake ducts can also be taken away, so as to achieve the effect of cooling the engine. At the same time, when the gas passes through the intake ducts, due to the heat absorption effect, the temperature of the gas itself rises. Therefore, when the spacecraft flies at low temperature at high altitude, the inhaled cold air will be affected by the heat energy of the engine and the air flow temperature will be increased. Without the need for additional electric heating maintenance of the intake manifold, the fogging of the intake manifold can be effectively avoided and the anti-fog effect can be achieved. That is, the integrated design structure of the intake duct and the engine eliminates the structural form of using a separate intake pipe. It can not only achieve the cooling control of the engine, but also use the heat absorbed as the heat source to increase the temperature of its own air flow, effectively ensuring the temperature of the intake manifold, eliminating the fogging problem, achieving the thermal balance of cooling and temperature control, realizing the overall structural regularity and neatness of the engine while saving energy, with strong integration and high stability, and effectively realizing the lightweight design of the engine structure. Description of the Drawings

[0011] Figure 1 It is a three-dimensional view of the structure of a lightweight unmanned aerial vehicle aviation engine with an integrally formed intake duct;

[0012] Figure 2 It is a front view of the internal structure of a lightweight unmanned aerial vehicle aviation engine with an integrally formed intake duct;

[0013] Figure 3 It is a three-dimensional view of the engine without the airway cover and the sealing cover installed;

[0014] Figure 4 It is a three-dimensional structure schematic diagram of the intake duct and the intake chamber of a lightweight unmanned aerial vehicle aviation engine with an integrally formed intake duct;

[0015] Wherein: 1 engine body, 2 cylinder block, 3 cylinder head, 4 air inlet chamber, 5 air inlet, 6 air intake passage, 7 side port, 8 inclined air duct, 9 bending portion, 10 sealing cover, 11 air duct cover. Detailed implementation manner

[0016] To make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the specific implementation manners and with reference to the accompanying drawings. It should be understood that these descriptions are merely exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessarily confusing the concepts of the present invention.

[0017] Example 1: As Figures 1 to 4As shown in the figure, a lightweight unmanned aerial vehicle (UAV) aviation engine with an integrally formed air intake duct includes an engine body 1 and two groups of cylinder blocks 2 and cylinder heads 3 located at both ends of the engine body 1. An air intake chamber 4 is provided on one side of the engine body 1, and an air inlet 5 is opened outward on the outer wall of the air intake chamber 4. Intake ducts 6 are opened on the side walls of the cylinder head 3 and the cylinder block 2, which are connected from the cylinder block 2 to the inside of the cylinder head 3 and extend into the cylinder head 3. The intake ducts 6 are respectively opened on the sides of the cylinder head 3 and the cylinder block 2 and are integrally formed with the cylinder head 3 and the cylinder block 2. During use, air flows into the air intake chamber 4 from the air inlet 5, enters the intake ducts 6 at both ends from the air intake chamber 4, passes through the bottom to the head of the cylinder head 3 along the intake ducts 6, and enters the cylinder. The cross-section of the intake duct 6 can be a rounded rectangle, a circle, or an ellipse, and is integrally formed with the cylinder block 2 and connected to the air intake chamber 4. The overall engine is cooled by the airflow in the air intake chamber 4 and the intake ducts 6. A side port 7 is opened at the contact between the engine body 1 and the cylinder head 3. Below the side port 7 is an inclined air duct 8, which is closely distributed along the structure of the engine body 1 and is connected to the air intake chamber 4. The inclined air duct 8 is determined by the shape of the engine body 1 and is a docking area for smooth connection between the air intake chamber 4 and the intake ducts 6. It can not only allow air to flow smoothly from the air intake chamber 4 into the intake ducts 6 without interruption, but also fit well with the surface of the engine body 1 to improve the cooling efficiency. The intake ducts 6 on the two cylinder heads 3 are axially symmetrically distributed relative to the air inlet 5. The intake duct 6 extends closely along the side wall of the cylinder head 3 from the bottom of the cylinder head 3 to the top of the cylinder head 3 in the extending direction of the cylinder head 3, and forms a horizontal bending part 9 in the area at the top of the cylinder head 3. The bending part 9 extends towards the middle of the cylinder head 3 and is connected to the intake manifold inside the cylinder head 3. The bent intake duct 6 can reasonably increase the stroke outside the cylinder head 3 to achieve more heat exchange, fully meet the time required for heat absorption and improve the thermal energy exchange required to increase the temperature of the airflow itself, so that the temperature of the airflow entering the intake manifold is sufficient, and condensation such as atomization will not occur, improving the smoothness and stability of the cylinder operation. A half airway cover 11 adapted to the half side intake duct 6 on the cylinder head 3 body is provided on the bending part 9. The half side intake duct 6 and the other half airway cover 11 constitute the intake duct 6 in the cylinder head 3 part. A sealing cover 10 is installed on the side port 7 above the inclined air duct 8, and the sealing cover 10 is installed on the cavity of the air intake chamber 4. Such a design facilitates the assembly and installation of various components of the engine.

[0018] It should be understood that the above specific embodiments of the present invention are only used for exemplary illustration or explanation of the principle of the present invention, and do not constitute a limitation to the present invention. Therefore, any modifications, equivalent replacements, improvements, etc. made without departing from the spirit and scope of the present invention shall be included within the protection scope of the present invention. In addition, the appended claims of the present invention are intended to cover all changes and modification examples falling within the scope and boundary of the appended claims, or equivalent forms of such scope and boundary.

Claims

1. A lightweight unmanned aerial vehicle (UAV) aviation engine with an integrally formed air intake duct, comprising an engine body (1), and two groups of cylinder blocks (2) and cylinder heads (3) located at both ends of the engine body (1). It is characterized in that An air intake chamber (4) is provided on one side of the engine body (1). An air inlet (5) is opened outward on the outer wall of the air intake chamber (4). Intake ducts (6) that communicate from the cylinder block (2) to the inside of the cylinder head (3) are provided on the side walls of the cylinder head (3) and the cylinder block (2). The intake ducts (6) are respectively opened on the side surfaces of the cylinder head (3) and the cylinder block (2) and are integrally formed with the cylinder head (3) and the cylinder block (2). A side port (7) is opened at the contact position between the engine body (1) and the cylinder head (3). An inclined air duct (8) is provided below the side port (7). The inclined air duct (8) is closely distributed along the structure of the engine body (1) and communicates with the air intake chamber (4). The intake ducts (6) on the two cylinder heads (3) are axially symmetrically distributed with respect to the air inlet (5). The intake duct (6) extends closely along the side wall of the cylinder head (3) from the bottom of the cylinder head (3) in the extending direction of the cylinder head (3) to the top of the cylinder head (3), and a horizontal bending part (9) is formed in the area of the top of the cylinder head (3). The bending part (9) extends towards the middle of the cylinder head (3) and communicates with the intake manifold inside the cylinder head (3).

2. The lightweight UAV aviation engine with an integrally formed intake duct (6) according to claim 1, It is characterized in that The cross-section of the intake duct (6) can be a rounded rectangle, a circle, or an ellipse.

3. The lightweight UAV aviation engine with an integrally formed intake duct (6) according to claim 1, It is characterized in that The bending part (9) is provided with the other half airway cover (11) that is adapted to the half-side intake duct (6) on the cylinder head (3) body. The half-side intake duct (6) and the other half airway cover (11) constitute the intake duct (6) in the cylinder head (3) part. A sealing cover (10) is installed on the side port (7) above the inclined air duct (8). The sealing cover (10) is installed on the cavity of the air intake chamber (4).

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