Rotational flow premixed combustion micro propeller

Abstract

The invention discloses a rotational flow premixed combustion micro propeller which comprises a fixed frame and a movable frame, the opposite faces of the fixed frame and the movable frame are jointly and rotationally connected with a rotating rod, inner cavities of the fixed frame and the movable frame are jointly and rotationally connected with four propeller shells, and external connecting plates are fixedly installed at the tops of the propeller shells. A combustion chamber top cover is fixedly mounted at the bottom of the external connecting plate; the liquid high-energy fuel bin and the high-pressure gas bin at the top of the fixing frame inject fuel capable of combusting and enabling the propeller to move into an inner cavity of a propeller shell, the flow of the two bins is controlled through valves, the fuel and air firstly pass through internal thread connecting holes, and in the combustion process, corresponding substances pass through inner cavities of a fuel inlet and an air inlet; and then fuel and air flow in the rotational flow premixing channel and are fully mixed, finally, the fuel and the air which are fully mixed flow into an inner cavity of the combustion chamber, and the fuel is ignited through the ignition electric heating wire to generate thrust to provide rising thrust for the propeller.

Description

Technical Field

[0001] The present invention relates to the technical field of micro-propellers, in particular to a swirl premixed combustion micro-propeller. Background Art

[0002] Recently, micro-electromechanical systems based on micro / nanotechnology have developed rapidly. The structures of many devices tend to be miniaturized and functionally integrated. There is an urgent need for ultra-high energy density micro-thruster systems in aerospace, communications, national defense and other fields.

[0003] After searching, the patent document with publication number CN115419518A discloses a micro-thruster based on 3D printing of a nylon shell and a metal nozzle, which includes a combustion chamber, a shell, a medicine baffle, and a nozzle; the shell is a nylon shell, which is an integrated structure with the combustion chamber; the medicine baffle is arranged in the shell; the nozzle is a metal Rafale nozzle with a convergence half angle of 55° and an expansion half angle of 15°, and is connected to the shell by threads.

[0004] This thruster uses 3D printing technology to print the shell of a nylon-based micro-thruster; the nozzle structure is designed to have a stud shape and is assembled with other parts of the nylon-based micro-thruster using a threaded connection. This structure can effectively prevent nozzle erosion and achieve lightweight, short-cycle, high-precision and low-cost design of the micro-thruster. However, this micro-thruster is a simple size reduction based on a large thruster. Due to its small scale, the thruster surface area ratio increases exponentially, resulting in a large proportion of heat dissipation loss, making it difficult to maintain the thermal environment required for good combustion. The size reduction causes the fuel residence time to drop rapidly, and it is also difficult to achieve complete combustion. Therefore, this technical solution is mostly characterized by imperfect technology and low thermal efficiency.

[0005] Therefore, a swirl premixed combustion micro-thruster is proposed to solve the above problems. Summary of the Invention

[0006] In order to make up for the shortcomings of the existing technology and solve the problems of difficulty in complete combustion of fuel and low combustion efficiency, the present invention proposes a swirl premixed combustion micro-thruster, including a fixed frame and a movable frame, the opposite surfaces of the fixed frame and the movable frame are connected to a rotating rod for common rotation, the inner cavities of the fixed frame and the movable frame are connected to four thruster shells for common rotation, an external connecting plate is fixedly installed on the top of the thruster shell, and a combustion chamber top cover is fixedly installed on the bottom of the external connecting plate.

[0007] Preferably, a plurality of first sleeves are evenly fixedly installed on the outer surface of the fixing frame, and a first groove is formed on the top of the fixing frame.

[0008] Preferably, a plurality of second sleeves are evenly and fixedly mounted on the outer surface of the movable frame, a second groove is opened on the top of the movable frame, and the rotating rod is rotatably mounted on the inner surfaces of the first groove and the second groove.

[0009] Preferably, a plurality of internal thread connection holes are evenly opened on the top of the external connection plate, and four swirl baffles are fixedly installed on the top of the combustion chamber top cover.

[0010] Preferably, a fuel inlet is provided at the top of the swirl baffle, and the fuel inlet passes through the combustion chamber top cover and respectively passes through four internal thread connection holes.

[0011] Preferably, the four swirl baffles cooperate with each other, the gap between two adjacent swirl baffles is a swirl premixing channel, and an air inlet is provided at the top of the combustion chamber top cover.

[0012] Preferably, four connectors are fixedly mounted on the outer surface of the thruster housing, and the four connectors are rotatably mounted on the inner surfaces of the first sleeve and the second sleeve respectively.

[0013] Preferably, a combustion chamber and a nozzle are provided in the inner cavity of the thruster casing, the combustion chamber and the nozzle inner cavity are connected to each other, and a guide vane is rotatably installed in the inner cavity of the combustion chamber.

[0014] A swirl premixed combustion micro-thruster, comprising:

[0015] The present invention is beneficial in that:

[0016] 1. The present invention uses a liquid high-energy fuel tank and a high-pressure air tank on the top of the fixed frame to inject fuel that can burn and move the thruster into the inner cavity of the thruster shell. The two tanks control the flow rate through valves. The fuel and air first pass through the internal threaded connection hole. During the combustion process, corresponding substances pass through the inner cavities of the fuel inlet and the air inlet. Then, the fuel and air flow and mix in the swirl premixing channel, and finally flow into the inner cavity of the combustion chamber, and the fuel is ignited by the ignition heating wire.

[0017] 2. The present invention generates high-temperature gas through fuel combustion. The high-temperature gas diffuses in all directions, but under the restriction of the propeller shell, the high-temperature gas will flow downward. When the high-temperature gas passes through the guide vane, since the guide vane contains four fully three-dimensional blades, the high-temperature gas will be guided and concentrated to spray downward at high speed, and will generate an upward reaction force on the propeller, so that the propeller obtains thrust.

[0018] 3. The present invention limits the connector on the outer surface of the thruster housing by means of the first sleeve and the second sleeve on the fixed frame and the movable frame, and can also bundle the four thruster housings together. The micro stepping motor inside the rotating rod drives the rotating rod to cause misalignment between the fixed frame and the movable frame, thereby causing the four thruster housings to have an inclination angle, thereby achieving the purpose of adjusting the thruster propulsion angle. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0020] Figure 1 This is a schematic diagram of the overall structure of an embodiment of the present invention;

[0021] Figure 2 This is a schematic diagram of the connection structure of the fixed frame and the movable frame according to an embodiment of the present invention;

[0022] Figure 3 This is a schematic structural diagram of an external connection plate according to an embodiment of the present invention;

[0023] Figure 4 This is a schematic diagram of the combustion chamber top cover structure according to an embodiment of the present invention;

[0024] Figure 5 This is a schematic diagram of the propeller housing structure according to an embodiment of the present invention;

[0025] Figure 6 The figure is a schematic diagram of the cross-sectional structure of a thruster casing according to an embodiment of the present invention.

[0026] In the figure: 1. Fixed frame; 11. First sleeve; 12. First groove; 2. Movable frame; 21. Second sleeve; 22. Second groove; 3. Rotating rod; 4. External connecting plate; 41. Internal threaded connecting hole; 5. Combustion chamber top cover; 51. Swirl baffle; 52. Fuel inlet; 53. Swirl premixing channel; 54. Air inlet; 6. Propeller casing; 61. Connector; 62. Guide vane; 63. Combustion chamber; 64. Nozzle. DETAILED DESCRIPTION

[0027] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0028] See also Figures 1 to 6 As shown, a swirl premixed combustion micro-thruster includes a fixed frame 1 and a movable frame 2, wherein the fixed frame 1 and the movable frame 2 have opposite surfaces that are rotatably connected to a rotating rod 3, and the inner cavities of the fixed frame 1 and the movable frame 2 are rotatably connected to four thruster shells 6, and an external connecting plate 4 is fixedly installed on the top of the thruster shell 6, and a combustion chamber top cover 5 is fixedly installed on the bottom of the external connecting plate 4.

[0029] Existing micro-thrusters are simply size-reduced based on large-scale thrusters. Due to their small size, the thruster surface area ratio increases exponentially, resulting in a large proportion of heat dissipation losses, making it difficult to maintain the thermal environment required for good combustion. The size reduction causes the fuel residence time to drop rapidly, and it is also difficult to achieve complete combustion. Therefore, most of these technical solutions are characterized by imperfect technology and low thermal efficiency.

[0030] When the present invention is in use, a liquid high-energy fuel tank and a high-pressure gas tank are connected to the top of the fixing frame 1. Both tanks are provided with microvalves to adjust the flow rate. The fuel enters the thruster housing 6 through the internal threaded connection hole 41 on the external connecting plate 4. The fuel burns in the inner cavity of the thruster housing 6. A catalyst PT is provided on the inner side of the thruster housing 6 to catalyze the combustion. Then the air and fuel pass through the combustion chamber top cover 5 into the thruster housing 6. The fuel-air mixture burns in the thruster housing 6. The high-temperature and high-pressure gas generated by the combustion will be guided by the guide vanes 62 and ejected from the bottom at high speed. According to the interaction of forces, the force generated by the fuel combustion further pushes the thruster housing 6 to move upward.

[0031] Further, such as Figures 3 to 5 As shown, a plurality of internal thread connection holes 41 are evenly opened on the top of the external connection plate 4, and four swirl baffles 51 are fixedly installed on the top of the combustion chamber top cover 5;

[0032] A fuel inlet 52 is provided on the top of the swirl baffle 51. The fuel inlet 52 passes through the combustion chamber top cover 5 and respectively passes through the four internal thread connection holes 41.

[0033] The four swirl baffles 51 cooperate with each other, and the gap between two adjacent swirl baffles 51 is a swirl premixing channel 53. An air inlet 54 is opened on the top of the combustion chamber top cover 5.

[0034] When the present invention is in use, air and fuel are introduced into the inlet of the thruster housing 6 through the internal threaded connection hole 41. The combustion chamber top cover 5 and the thruster housing 6 are connected by screws, and a sealing ring is provided at the connection to seal the connection to prevent combustion gas leakage resulting in insufficient thrust. It also ensures that after the inner cavity of the thruster housing 6 is sealed, the gas thrust generated by the fuel combustion can be emitted entirely from the bottom of the thruster housing 6, and the generated reaction force propels the entire thruster upward.

[0035] Four swirl premixing channels 53 can be further formed by the mutual cooperation of the four swirl baffles 51. By controlling the flow direction of the high-temperature gas, the high-temperature gas generated by the fuel combustion can be concentrated to flow in one direction, further improving the utilization rate of the thrust generated by the fuel combustion.

[0036] Further, such as Figure 2 and Figure 5 As shown, a plurality of first sleeves 11 are evenly fixedly installed on the outer surface of the fixing frame 1, and a first groove 12 is opened on the top of the fixing frame 1;

[0037] A plurality of second sleeves 21 are evenly fixedly installed on the outer surface of the movable frame 2. A second groove 22 is opened on the top of the movable frame 2. The rotating rod 3 is rotatably installed on the inner surface of the first groove 12 and the second groove 22.

[0038] Four connectors 61 are fixedly mounted on the outer surface of the propeller housing 6 , and the four connectors 61 are rotatably mounted on the inner surfaces of the first sleeve 11 and the second sleeve 21 , respectively.

[0039] When the present invention is in use, several connecting heads 61 are respectively located on the inner surfaces of the second sleeve 21 and the first sleeve 11. The rotating rod 3 is driven by a micro stepping motor. After the control system receives the steering signal, it controls the rotating rod 3 to rotate a certain angle. The rotating rod 3 will drive the fixed frame 1 and the movable frame 2 to move relative to each other, thereby changing the relative position of the fixed frame 1 and the movable frame 2, and then making the four thruster housings 6 rotate together to realize the steering of the entire array thruster.

[0040] Further, such as Figure 5 and Figure 6 As shown, a combustion chamber 63 and a nozzle 64 are provided in the inner cavity of the propeller housing 6. The inner cavities of the combustion chamber 63 and the nozzle 64 are interconnected. A guide vane 62 is rotatably installed in the inner cavity of the combustion chamber 63.

[0041] When the present invention is in use, the guide vane 62 contains four full three-dimensional leaf-shaped blades, which are used to guide the high-temperature gas after combustion. The combustion chamber top cover 5 and the thruster housing 6 are also connected by screws, and a sealing ring is provided to prevent high-temperature gas leakage. An insulating layer is coated on the outer surface of the thruster. The throat between the thruster housing 6 and the nozzle 64 is an arc with a certain curvature radius and reduces the gas boundary layer, thereby increasing the thrust of the thruster. The entire thruster housing 6 and the nozzle 64 are three-dimensional circles to adapt to the swirl motion of the swirl airflow in the combustion chamber, reduce gas resistance, and increase thrust.

[0042] Working principle: First, the fuel that can burn and move the thruster is injected into the inner cavity of the thruster shell 6 through the liquid high-energy fuel tank and the high-pressure gas tank on the top of the fixed frame 1. The flow of the two tanks is controlled by valves. The fuel and air first pass through the internal threaded connection hole 41. During the combustion process, corresponding substances pass through the inner cavities of the fuel inlet 52 and the air inlet 54. Then the fuel and air flow and mix in the swirl premixing channel 53, and finally flow to the inner cavity of the combustion chamber 63. The fuel is ignited by the ignition heating wire. The fuel combustion produces high-temperature gas, which diffuses around. However, under the restriction of the thruster shell 6, the high-temperature gas will flow downward. When the high-temperature gas passes through the guide vane 62, since the guide vane 62 contains four full three-dimensional leaf-shaped blades, the high-temperature gas will be guided and concentrated to spray downward at high speed, and will generate an upward reaction force on the thruster, so that the thruster obtains thrust.

[0043] The connector 61 on the outer surface of the thruster housing 6 is restricted by the first sleeve 11 and the second sleeve 21 on the fixed frame 1 and the movable frame 2, and the four thruster housings 6 can also be bundled together. The micro stepping motor inside the rotating rod 3 drives the rotating rod 3 to cause misalignment between the fixed frame 1 and the movable frame 2, thereby causing the four thruster housings 6 to have a tilt angle, thereby achieving the purpose of adjusting the thruster propulsion angle.

[0044] Throughout this specification, references to terms such as "one embodiment," "example," or "specific example" indicate that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0045] The basic principles, main features, and advantages of the present invention are shown and described above. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and modifications may be made to the present invention without departing from the spirit and scope of the present invention, and such changes and modifications fall within the scope of the invention as claimed.

Claims

1. A swirl premixed combustion micro-thruster, comprising a fixed frame (1) and a movable frame (2), characterized in that: The opposite surfaces of the fixed frame (1) and the movable frame (2) are connected to a rotating rod (3) for joint rotation, and the inner cavities of the fixed frame (1) and the movable frame (2) are connected to four thruster shells (6) for joint rotation. An external connecting plate (4) is fixedly mounted on the top of the thruster shell (6), and a combustion chamber top cover (5) is fixedly mounted on the bottom of the external connecting plate (4).

2. The swirl premixed combustion micro-thruster according to claim 1, characterized in that: A plurality of first sleeves (11) are evenly fixedly mounted on the outer surface of the fixing frame (1), and a first groove (12) is provided on the top of the fixing frame (1).

3. The swirl premixed combustion micro-thruster according to claim 2, characterized in that: A plurality of second sleeves (21) are evenly and fixedly mounted on the outer surface of the movable frame (2), a second groove (22) is opened on the top of the movable frame (2), and the rotating rod (3) is rotatably mounted on the inner surfaces of the first groove (12) and the second groove (22).

4. The swirl premixed combustion micro-thruster according to claim 3, characterized in that: A plurality of internal thread connection holes (41) are evenly arranged on the top of the external connection plate (4), and four swirl baffles (51) are fixedly mounted on the top of the combustion chamber top cover (5).

5. The swirl premixed combustion micro-thruster according to claim 4, characterized in that: A fuel inlet (52) is provided on the top of the swirl baffle (51), and the fuel inlet (52) passes through the combustion chamber top cover (5) and respectively passes through four internal thread connection holes (41).

6. The swirl premixed combustion micro-thruster according to claim 5, characterized in that: The four swirl baffles (51) cooperate with each other, and the gap between two adjacent swirl baffles (51) is a swirl premixing channel (53). An air inlet (54) is provided on the top of the combustion chamber top cover (5).

7. The swirl premixed combustion micro-thruster according to claim 6, characterized in that: Four connectors (61) are fixedly mounted on the outer surface of the propeller housing (6), and the four connectors (61) are rotatably mounted on the inner surfaces of the first sleeve (11) and the second sleeve (21), respectively.

8. The swirl premixed combustion micro-thruster according to claim 7, characterized in that: The inner cavity of the propeller housing (6) is provided with a combustion chamber (63) and a nozzle (64). The inner cavities of the combustion chamber (63) and the nozzle (64) are interconnected. A guide vane (62) is rotatably mounted in the inner cavity of the combustion chamber (63).

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