Ignition mechanism for extended-range aircraft engines of electric helicopters

Abstract

An ignition mechanism for an extended-range aero-engine for an electric helicopter comprises a shell, a signal input terminal is arranged on the shell, a high-voltage output terminal is arranged at the bottom of the shell, a high-voltage positioning block is arranged in the shell, a first coil assembly and a second coil assembly are arranged above the high-voltage positioning block, a spacer block is arranged below the high-voltage positioning block, a plurality of partition walls are respectively arranged on the upper surface and the lower surface of the spacer block, the partition walls respectively separate the upper surface and the lower surface of the spacer block into a plurality of independent areas, a plurality of flow guide holes connecting the independent areas are arranged on the spacer block, the shell is filled with epoxy resin as a whole, an upper epoxy resin assembly is formed on the upper surface of the spacer block, and a lower epoxy resin assembly is formed on the lower surface of the spacer block; the invention can meet the requirements of the extended-range aero-engine for an electric helicopter, and the structure is relatively reliable, and the product performance is improved. In addition, the adaptive structure makes each component compatible with existing products, and can meet the requirements of an automatic production line.

Description

Technical Field

[0001] The invention relates to an ignition coil structure. Background Art

[0002] The existing ignition coil structures are all designed for automobile engines and cannot be directly applied to electric helicopter extended-range aircraft engines. Since the structures and performance requirements of automobile engines and electric helicopter extended-range aircraft engines are somewhat different, for example, the group ignition sequence of automobile engines is generally diagonal 1-3-4-2, while the electric helicopter extended-range aircraft engine requires a counterclockwise ignition sequence. Therefore, the existing ignition coils need to be changed before they can be applied to electric helicopter extended-range aircraft engines. Summary of the invention

[0003] In order to make corresponding design / process improvements to the existing product design to meet the requirements of the electric helicopter extended-range aircraft engine, the purpose of the present invention is to provide an ignition mechanism of the electric helicopter extended-range aircraft engine with a completely new structure.

[0004] In order to achieve the above-mentioned object, the technical scheme adopted by the present invention is: an electric helicopter extended-range aviation engine ignition mechanism, comprising a shell, a signal input terminal is arranged on the shell, a high-voltage output terminal A, a high-voltage output terminal B, a high-voltage output terminal C, and a high-voltage output terminal D are arranged at the bottom of the shell, and high-voltage output terminals A, B, C, and D are respectively provided with high-voltage pins, a high-voltage positioning block is arranged in the shell, a first positioning groove and a second positioning groove are arranged in parallel along the horizontal direction above the high-voltage positioning block, a first coil assembly is arranged on the first positioning groove, and a second coil assembly is arranged on the second positioning groove, and a spacer block is arranged below the high-voltage positioning block, and the upper surface and the lower surface of the spacer block are respectively provided with a plurality of partition walls, and the partition walls respectively separate the upper surface and the lower surface of the spacer block into a plurality of independent areas, and the spacer block is provided with a plurality of guide holes connecting the independent areas, and the shell is filled with epoxy resin as a whole, and an upper epoxy resin assembly is formed on the upper surface of the spacer block, and a lower epoxy resin assembly is formed on the lower surface of the spacer block. The liposome assembly; wherein the bottom surface of the high-voltage positioning block is provided with a first high-voltage connecting piece, a second high-voltage connecting piece, a third high-voltage connecting piece, and a fourth high-voltage connecting piece, wherein the first high-voltage connecting piece includes an a end and an A end, wherein the a end is connected to one end of the secondary winding of the first coil assembly through a longitudinally extending high-voltage connecting head, wherein the high-voltage pin of the high-voltage output terminal A extends upward through the spacer block and is connected to the A end, wherein the second high-voltage connecting piece includes a b end and a B end, wherein the b end is connected to one end of the secondary winding of the second coil assembly through a longitudinally extending high-voltage connecting head, wherein the The high-voltage pin of the high-voltage output terminal B extends upward through the spacer block and is connected to the B end. The third high-voltage connecting piece includes a C end and a D end. The C end is connected to the other end of the secondary winding of the second coil assembly through a longitudinally extending high-voltage connecting head. The high-voltage pin of the high-voltage output terminal D extends upward through the spacer block and is connected to the D end. The fourth high-voltage connecting piece includes a D end and a C end. The D end is connected to the other end of the secondary winding of the first coil assembly through a longitudinally extending high-voltage connecting head. The high-voltage pin of the high-voltage output terminal C extends upward through the spacer block and is connected to the C end.

[0005] Preferably, the bottom surface of the high-voltage positioning block is provided with a positioning groove matching the shape of the first high-voltage connecting piece, the second high-voltage connecting piece, the third high-voltage connecting piece, and the fourth high-voltage connecting piece, and the first high-voltage connecting piece, the second high-voltage connecting piece, the third high-voltage connecting piece, and the fourth high-voltage connecting piece are arranged in the corresponding positioning grooves.

[0006] Preferably, the upper epoxy resin assembly and the lower epoxy resin assembly include a series of epoxy resin units with different thicknesses.

[0007] Preferably, the high-pressure positioning block is provided with a guide hole.

[0008] Preferably, the first coil assembly and the second coil assembly respectively include a magnetic core, a primary frame arranged outside the magnetic core, a primary winding wound around the primary frame, a secondary frame arranged outside the primary frame, and a secondary winding wound around the secondary frame.

[0009] Preferably, the magnetic core includes a T-type core assembly and a C-type core assembly combined with the T-type core assembly, the T-type core assembly passes through the interior of the primary frame, the C-type core assembly has a long end and a short end, the bottom surface and the long end of the T-type core assembly are fixed together, the T-type core assembly and the primary frame pass through the secondary frame and are fixed together with the short end, and the C-type core assembly and the T-type core assembly as a whole constitute a complete magnetic circuit.

[0010] Preferably, the side surface of the long end of the C-type core assembly is adsorbed together with the bottom surface of the T-type core assembly through a magnet, and the top of the T-type core assembly is adsorbed together with the top surface of the short end of the C-type core assembly through a magnet.

[0011] Preferably, a primary wire slot is provided on the primary skeleton of the first coil assembly and the second coil assembly, a primary connecting piece is provided on the inner wall of the shell, the primary connecting piece is inserted into the primary wire slot and connected to the primary winding, and the signal input terminal is electrically connected to the primary connecting piece.

[0012] Preferably, a positioning hole is provided on the high-voltage positioning block, the lower end of the high-voltage connector is inserted into the positioning hole, a connecting sleeve is provided on the secondary skeleton of the first coil assembly and the second coil assembly, and the top end of the high-voltage connector is inserted into the connecting sleeve and connected to the secondary winding.

[0013] Preferably, a buffer layer is provided on the inner side wall of the C-type core assembly.

[0014] Due to the adoption of the above technical scheme, the present invention can meet the requirements of the extended-range aviation engine of the electric helicopter, and the structure is relatively reliable, which improves the product performance. In addition, the adaptive structure makes each component compatible with the existing products and can meet the requirements of the automatic production line. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Attached Figure 1 A three-dimensional diagram of an ignition mechanism of an electric helicopter range-extending aviation engine according to the present invention;

[0016] Attached Figure 2 It is a working principle diagram of the ignition mechanism of the electric helicopter range-extending aero-engine according to the present invention;

[0017] Attached Figure 3 and attached Figure 4 It is a three-dimensional exploded view of the coil assembly of the electric helicopter range-extended aviation engine ignition mechanism according to the present invention. DETAILED DESCRIPTION

[0018] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making a clearer and more definite definition of the protection scope of the present invention.

[0019] See attached Figure 1 To Attachment Figure 4 As shown, attached Figure 1 is a three-dimensional diagram of the ignition mechanism of the electric helicopter range-extending aero-engine according to the present invention, Figure 2 The working principle diagram of the ignition mechanism of the electric helicopter range-extending aero-engine according to the present invention is shown in FIG. Figure 3 and attached Figure 4 It is a three-dimensional exploded view of the coil assembly of the electric helicopter range-extended aviation engine ignition mechanism according to the present invention.

[0020] The electric helicopter extended-range aircraft engine ignition mechanism in this embodiment includes a shell 1, a signal input terminal 2 is arranged on the shell 1, a high-voltage output terminal A3, a high-voltage output terminal B4, a high-voltage output terminal C5, and a high-voltage output terminal D6 are arranged at the bottom of the shell 1, and high-voltage pins 7 are respectively arranged in the high-voltage output terminals A3, B4, C5, and D6. A high-voltage positioning block 8 is arranged in the shell 1, and a first positioning groove 9 and a second positioning groove 10 are arranged in parallel in the horizontal direction above the high-voltage positioning block 8, a first coil assembly 11 is arranged on the first positioning groove 9, and a second coil assembly 12 is arranged on the second positioning groove 10, and a spacer block 17 is arranged below the high-voltage positioning block 8.

[0021] The first coil assembly 11 and the second coil assembly 12 respectively include a T-shaped core assembly 13 and a C-shaped core assembly 14 combined with the T-shaped core assembly 13, the T-shaped core assembly 13 passes through the interior of the primary frame, the C-shaped core assembly 14 has a long end and a short end, the bottom surface of the T-shaped core assembly 13 and the long end are fixed together, the T-shaped core assembly 13 and the primary frame are fixed together with the short end after passing through the secondary frame, and the T-shaped core assembly 13 and the C-shaped core assembly 14 form a complete magnetic circuit as a whole. The side surface of the long end of the C-shaped core assembly 14 can be adsorbed together with the bottom surface of the T-shaped core assembly 13 by a magnet, and the top of the T-shaped core assembly 13 is adsorbed together with the top surface of the short end of the C-shaped core assembly 14 by a magnet. In other embodiments of the present invention, the inner side wall of the C-shaped core assembly 14 is provided with a buffer layer of rubber material, and a locking mechanism is provided between the top of the T-shaped core assembly 13 and the short end of the C-shaped core assembly 14.

[0022] The primary frame of the first coil assembly 11 and the second coil assembly 12 is wound with primary windings, and the secondary frame is provided with secondary windings outside. The primary frame is provided with a positioning column to maintain the position of the secondary frame. The primary frame is provided with a primary wire clamping groove 15, and the inner wall of the housing 1 is provided with a primary connecting piece 16. When the first coil assembly 11 and the second coil assembly 12 are installed in place, the primary connecting piece 16 is inserted into the primary wire clamping groove 15 and just fits into the primary wire in the groove. Around The signal input terminal 2 is electrically connected to the primary connection piece 16.

[0023] A first high-voltage connecting piece 21, a second high-voltage connecting piece 22, a third high-voltage connecting piece 23, and a fourth high-voltage connecting piece 24 are arranged on the bottom surface of the high-voltage positioning block 8. The first high-voltage connecting piece 21 includes an a end and an A end. The a end is connected to one end of the secondary winding of the first coil assembly 11 through a longitudinally extending high-voltage connector 20. The high-voltage pin 7 of the high-voltage output terminal A extends upward through the spacer block 17 and is connected to the A end. The second high-voltage connecting piece 22 includes a b end and a B end. The b end is connected to one end of the secondary winding of the second coil assembly 12 through a longitudinally extending high-voltage connector 20. The high-voltage pin 7 of the output terminal B extends upward through the spacer block 17 and is connected to the B terminal. The third high-voltage connecting piece 23 includes a C terminal and a D terminal. The C terminal is connected to the other end of the secondary winding of the second coil assembly 12 through a longitudinally extending high-voltage connector 20. The high-voltage pin 7 of the high-voltage output terminal D extends upward through the spacer block 17 and is connected to the D terminal. The fourth high-voltage connecting piece 24 includes a D terminal and a C terminal. The D terminal is connected to the other end of the secondary winding of the first coil assembly 11 through a longitudinally extending high-voltage connector 20. The high-voltage pin 7 of the high-voltage output terminal C extends upward through the spacer block 17 and is connected to the C terminal. The coil has built-in high-voltage connection sequence adapters T1-A, T2-D, T3-B, T4-C, and the input terminal signals C1, B+, C2 meet the engine counterclockwise ignition sequence ABCD requirements (high-voltage tower mark).

[0024] The bottom surface of the high-voltage positioning block 8 is provided with a positioning groove 25 matching the shape of the first high-voltage connecting piece 21, the second high-voltage connecting piece 22, the third high-voltage connecting piece 23, and the fourth high-voltage connecting piece 24. The first high-voltage connecting piece 21, the second high-voltage connecting piece 22, the third high-voltage connecting piece 23, and the fourth high-voltage connecting piece 24 are arranged in the corresponding positioning grooves 25. In addition, the high-voltage positioning block 8 is provided with a guide hole 19.

[0025] A positioning hole 26 is provided on the high-voltage positioning block 8, and the lower end of the high-voltage connector 20 is inserted into the positioning hole 26. A connecting sleeve 27 is provided on the secondary skeleton of the first coil assembly 11 and the second coil assembly 12, and the top end of the high-voltage connector 20 is inserted into the connecting sleeve 27 and connected to the secondary winding.

[0026] The upper surface and the lower surface of the spacer block 17 are respectively provided with a plurality of partition walls 18, and the partition walls 18 respectively divide the upper surface and the lower surface of the spacer block 17 into a plurality of independent areas. The spacer block 17 is provided with a plurality of guide holes 19 connecting the independent areas. The entire housing 1 is filled with epoxy resin, and an upper epoxy resin assembly is formed on the upper surface of the spacer block 17, and a lower epoxy resin assembly is formed on the lower surface of the spacer block 17. The upper epoxy resin assembly and the lower epoxy resin assembly include a series of epoxy resin units with different thicknesses. Due to the continuous operation of the ignition mechanism of the electric helicopter extended-range aircraft engine, huge internal stress is generated at the high-voltage connecting piece due to the cold and hot shock process, which is easy to cause the epoxy resin to crack and make the product fail. The present invention places the high-voltage connecting piece in the same plane to form a thermal plane, and sets an upper epoxy resin assembly at a position adjacent to the thermal plane. Since the upper epoxy resin assembly includes a series of epoxy resin units with different thicknesses, the internal stress here is eliminated, and the lower epoxy resin assembly is adjacent to the high-voltage tower, which disperses the stress in the vertical direction, further eliminating the risk of cracking. The present invention can meet the requirements of the electric helicopter extended-range aircraft engine, and the structure is more reliable, which improves the product performance. In addition, the adaptive structure makes each component compatible with existing products and can meet the requirements of the automatic production line.

[0027] The above implementation modes are only for illustrating the technical concept and features of the present invention, and their purpose is to enable people familiar with this technology to understand the content of the present invention and implement it, and they cannot be used to limit the protection scope of the present invention. Any equivalent changes or modifications made according to the spirit of the present invention should be included in the protection scope of the present invention.

Claims

1. An ignition mechanism for an electric helicopter range-extending aero-engine, characterized in that: The invention comprises a shell, wherein a signal input terminal is arranged on the shell, a high-voltage output terminal A, a high-voltage output terminal B, a high-voltage output terminal C, and a high-voltage output terminal D are arranged at the bottom of the shell, and high-voltage pins are arranged in the high-voltage output terminals A, B, C, and D respectively, and a high-voltage positioning block is arranged in the shell, and a first positioning groove and a second positioning groove are arranged in parallel in the horizontal direction above the high-voltage positioning block, a first coil assembly is arranged on the first positioning groove, and a second coil assembly is arranged on the second positioning groove, and a spacer block is arranged below the high-voltage positioning block, and a plurality of partition walls are arranged on the upper surface and the lower surface of the spacer block respectively, and each of the partition walls The upper surface and the lower surface of the spacer block are separated into a plurality of independent areas, and the spacer block is provided with a plurality of guide holes connecting the independent areas. The outer shell is filled with epoxy resin as a whole, and an upper epoxy resin assembly is formed on the upper surface of the spacer block, and a lower epoxy resin assembly is formed on the lower surface of the spacer block. The first coil assembly and the second coil assembly respectively include a magnetic core, a primary frame arranged outside the magnetic core, a primary winding wound on the primary frame, a secondary frame arranged outside the primary frame, and a secondary winding wound on the outside of the secondary frame. The primary frame is provided with a positioning column for maintaining the position of the secondary frame, and the high-voltage positioning block is provided with guide holes.

2. The electric helicopter range-extending aviation engine ignition mechanism according to claim 1, characterized in that: The magnetic core includes a T-type core assembly and a C-type core assembly combined with the T-type core assembly, the T-type core assembly passes through the interior of the primary frame, the C-type core assembly has a long end and a short end, the bottom surface of the T-type core assembly and the long end are fixed together, the T-type core assembly and the primary frame pass through the secondary frame and are fixed together with the short end, and the C-type core assembly and the T-type core assembly as a whole constitute a complete magnetic circuit.

3. The electric helicopter range-extending aviation engine ignition mechanism according to claim 2 is characterized by: The side surface of the long end of the C-shaped core component is adsorbed together with the bottom surface of the T-shaped core component through a magnet, and the top of the T-shaped core component is adsorbed together with the top surface of the short end of the C-shaped core component through a magnet.

4. The electric helicopter range-extending aviation engine ignition mechanism according to claim 2, characterized in that: The primary frames of the first coil assembly and the second coil assembly are provided with primary wire slots, the inner wall of the shell is provided with primary connecting pieces, the primary connecting pieces are inserted into the primary wire slots and connected to the primary windings, and the signal input terminals are electrically connected to the primary connecting pieces.

5. The electric helicopter range-extending aviation engine ignition mechanism according to claim 2, characterized in that: It also includes a high-voltage connector. The high-voltage positioning block is provided with a positioning hole, and the lower end of the high-voltage connector is inserted into the positioning hole. The secondary skeletons of the first coil assembly and the second coil assembly are provided with a connecting sleeve, and the top end of the high-voltage connector is inserted into the connecting sleeve and connected to the secondary winding.

6. The electric helicopter range-extending aviation engine ignition mechanism according to claim 2, characterized in that: The inner side wall of the C-shaped iron core assembly is provided with a buffer layer.

7. The electric helicopter range-extending aviation engine ignition mechanism according to claim 1, characterized in that: The bottom surface of the high-voltage positioning block is provided with a first high-voltage connecting piece, a second high-voltage connecting piece, a third high-voltage connecting piece, and a fourth high-voltage connecting piece. The bottom surface of the high-voltage positioning block is provided with a positioning groove matching the shape of the first high-voltage connecting piece, the second high-voltage connecting piece, the third high-voltage connecting piece, and the fourth high-voltage connecting piece. The first high-voltage connecting piece, the second high-voltage connecting piece, the third high-voltage connecting piece, and the fourth high-voltage connecting piece are arranged in the corresponding positioning grooves.

8. The electric helicopter range-extending aviation engine ignition mechanism according to claim 1, characterized in that: The upper epoxy resin assembly and the lower epoxy resin assembly include a series of epoxy resin units with different thicknesses.

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