Light machine, vehicle lamp module and vehicle

Abstract

The embodiment of the invention provides a light machine, a vehicle lamp module and a vehicle, and belongs to the technical field of light machines. The ray machine comprises a light source unit, an imaging unit, a reflection unit, a lens and an integrally-formed machine body. The machine body is provided with a first opening, a second opening, a third opening and a fourth opening, and any one of the first opening, the second opening, the third opening and the fourth opening is communicated with the inside and the outside of the machine body. The light source unit is arranged at the first opening and connected with the machine body, the reflection unit is arranged at the second opening and connected with the machine body, the imaging unit is arranged at the third opening and connected with the machine body, and the lens is arranged at the fourth opening and connected with the machine body. According to the light machine provided by the embodiment of the invention, the light source unit, the reflection unit and other devices are borne by the machine body, so that the number of parts of the light machine can be reduced, and the production efficiency of the light machine can be improved.

Description

Technical Field

[0001] The embodiments of the present application relate to the technical field of optical engines, and particularly to an optical engine, a vehicle lamp module, and a vehicle. Background Art

[0002] Currently, an optical engine includes a lens, an optical component, a light source, a projection chip, and a body. Among them, the body is composed of multiple structural members. The optical component is composed of multiple optical elements, and each optical element is connected to the body through an optical bracket. The optical component is used to collimate the light beam emitted by the light source and transmit the collimated light beam to the projection chip. The projection chip is a digital micromirror device, which is used to process the received light beam to output the imaging light projected onto the lens. However, due to the large number of parts of the optical engine, the assembly process of the optical engine is cumbersome, which will reduce the production efficiency of the optical engine. Therefore, how to improve the production efficiency of the optical engine has become an urgent problem to be solved. Summary of the Invention

[0003] The embodiments of the present application provide an optical engine, a vehicle lamp module, and a vehicle, which can reduce the number of parts of the optical engine to improve the production efficiency of the optical engine.

[0004] In a first aspect of the present application, an optical engine is provided, which includes a light source unit, an imaging unit, a reflection unit, a lens, and an integrally formed body. The body is provided with a first opening, a second opening, a third opening, and a fourth opening, and any one of the first opening, the second opening, the third opening, and the fourth opening communicates the inside and the outside of the body. The light source unit is disposed at the first opening and connected to the body, the reflection unit is disposed at the second opening and connected to the body, the imaging unit is disposed at the third opening and connected to the body, and the lens is disposed at the fourth opening and connected to the body. The reflection unit is used to reflect the light emitted by the light source unit to the imaging unit, and the imaging unit is used to output the imaging light incident on the lens according to the light reflected by the reflection unit.

[0005] The optical engine provided by the embodiments of the present application can reduce the number of parts of the optical engine by using the integrally formed body to carry the light source unit, the imaging unit, the reflection unit, and the lens, thereby simplifying the assembly process of the optical engine, and further improving the production efficiency of the optical engine. In addition, since the light source unit, the imaging unit, the reflection unit, and the lens are all connected to the body, the length of the tolerance chain after the assembly of the optical engine can be shortened, thereby reducing the assembly error of the optical engine, and further improving the performance of the optical engine. In addition, since the body is formed by one-time molding, the production cost of the body can also be reduced, so the production cost of the optical engine can be reduced.

[0006] In a possible implementation, the light source unit includes a light source and at least one collimating lens. The light source is connected to the fuselage. At least part of each collimating lens is disposed inside the first opening. Each collimating lens is disposed on the optical path between the light source and the reflection unit and is connected to the fuselage.

[0007] By disposing at least part of each collimating lens inside the first opening, the optical machine provided by the embodiment of the present application can hide the collimating lens by using the first opening on the premise of collimating the light emitted by the light source, thereby improving the integration of the optical machine and being conducive to the miniaturization of the optical machine.

[0008] In a possible implementation, at least one annular stepped surface is provided on the inner wall of the first opening. Each annular stepped surface corresponds to a collimating lens and is used to carry the corresponding collimating lens.

[0009] During the assembly process of the optical machine provided by the embodiment of the present application, the relative positions of the collimating lens and the fuselage can be positioned by the cooperation of the annular stepped surface and the collimating lens, thereby reducing the assembly difficulty of the collimating lens and the fuselage and improving the production efficiency of the optical machine. In addition, the annular stepped surface can also be bonded to the bottom surface of the collimating lens by bonding to improve the connection reliability between the fuselage and the collimating lens.

[0010] In a possible implementation, the fuselage is further provided with a plurality of first protrusions. The plurality of first protrusions are disposed inside the first opening. Each collimating lens corresponds to the plurality of first protrusions, and each first protrusion contacts the side wall of the corresponding collimating lens.

[0011] During the assembly process of the optical machine provided by the embodiment of the present application, the relative positions of the collimating lens and the fuselage can be positioned by the contact between the first protrusion and the side wall of the collimating lens, thereby improving the installation speed of the collimating lens.

[0012] In a possible implementation, the reflection unit includes a bracket and a reflection element. The reflection element is disposed inside the fuselage and is connected to the fuselage through the bracket. The reflection element is used to reflect the light emitted by the light source unit to the imaging unit.

[0013] During the assembly process of the optical machine provided by the embodiment of the present application, the reflection element can be installed in the fuselage through the bracket, so that the reflection element is disposed inside the fuselage to reflect the light emitted by the light source unit to the imaging unit. In addition, the bracket and the reflection element can be assembled into a reflection unit in advance and then connected to the fuselage, thereby reducing the number of assembly times of the optical machine and further improving the assembly efficiency of the optical machine.

[0014] In a possible implementation, one of the reflection element and the bracket includes a first hole, and the other includes a first positioning portion at least partially disposed inside the first hole.

[0015] During the assembly process of the reflection unit, by inserting the first positioning portion into the interior of the first hole, the relative positions of the reflection element and the bracket can be positioned, so that after the bracket is connected to the fuselage, the relative positions of the reflection element and the fuselage can be ensured, and further the position accuracy of the reflection element relative to the light source unit and the imaging unit can be guaranteed.

[0016] In a possible implementation, one of the bracket and the fuselage includes a second hole, and the other includes a second positioning portion at least partially disposed inside the second hole.

[0017] During the assembly process of the optical engine, by inserting the second positioning portion into the interior of the second hole, the relative positions of the bracket and the fuselage can be positioned, so that the relative positions of the reflection element and the fuselage can be ensured, and further the position accuracy of the reflection element relative to the light source unit and the imaging unit can be guaranteed.

[0018] In a possible implementation, the imaging unit includes a circuit board and an imaging element. The circuit board is disposed outside the fuselage and connected to the fuselage. The imaging element is connected to the circuit board and disposed at the third opening. The imaging element is configured to output imaging light directed towards the lens according to the light reflected by the reflection unit.

[0019] By disposing the circuit board outside the fuselage in the optical engine provided by the embodiments of the present application, the difficulty of connecting the circuit board to the fuselage can be reduced, and the heat dissipation requirements of the imaging unit can also be met.

[0020] In a possible implementation, along the first direction, the projection of the imaging element covers the third opening, and the imaging element can be used to shield the third opening, so that the imaging element can seal the third opening, which helps to reduce the difficulty of sealing the third opening.

[0021] In a possible implementation, the fuselage is further provided with a receiving groove for receiving at least a part of the imaging element, and the receiving groove communicates with the interior of the fuselage through the third opening.

[0022] During the assembly process of the optical engine, the relative positions of the imaging unit and the fuselage can be roughly positioned through the receiving groove to improve the installation speed of the imaging unit. In addition, the sealing performance between the imaging unit and the fuselage can also be improved by the cooperation of the receiving groove and the imaging element.

[0023] In a possible implementation, the optical engine further includes an elastic member having an annular structure. The elastic member is disposed between the fuselage and the imaging element and is in contact with the imaging element and the fuselage respectively.

[0024] In the embodiment of the present application, an optical machine is provided. By arranging an elastic member between the fuselage and the imaging element, the sealing performance between the imaging element and the fuselage can be improved. In addition, since the elastic member can elastically deform, the imaging element is in soft contact with the elastic member, thereby avoiding hard contact between the imaging element and the fuselage, and further preventing damage to the imaging element.

[0025] In a possible implementation manner, one of the fuselage and the elastic member includes a third hole, and the other includes a third positioning portion at least partially disposed inside the third hole.

[0026] During the assembly process of the optical machine, by inserting the third positioning portion into the third hole, the relative positions of the elastic member and the fuselage can be positioned, and the installation speed of the elastic member can be improved. In addition, the elastic member can also be pre-assembled with the imaging unit into a component, thereby reducing the number of assembly times of the optical machine, and further improving the assembly speed of the optical machine.

[0027] In a possible implementation manner, a part of the lens is disposed inside the fourth opening and is threadedly connected to the fuselage, which can reduce the difficulty of connecting the lens and the fuselage on the premise of realizing the connection between the lens and the fuselage. In addition, the focal length of the lens can be adjusted by rotating the lens, which can reduce the difficulty of focusing. In addition, by disposing at least a part of the lens inside the fourth opening, the size of the optical machine in the first direction can be reduced, which is helpful for miniaturization of the optical machine.

[0028] In a possible implementation manner, the optical machine further includes a heat dissipation device, and the heat dissipation device includes a first heat dissipation member, a second heat dissipation member, and a heat pipe member. One end of the heat pipe member is disposed inside the first heat dissipation member and is connected to the first heat dissipation member, and the other end of the heat pipe member is disposed inside the second heat dissipation member and is connected to the second heat dissipation member. The first heat dissipation member covers the light source of the light source unit and is connected to the fuselage, and the second heat dissipation member covers the imaging unit and is connected to the fuselage.

[0029] The optical machine provided by the embodiment of the present application can dissipate heat from the imaging unit and the light source through the heat dissipation device composed of the first heat dissipation member, the second heat dissipation member, and the heat pipe member, so that the temperatures of the imaging unit and the light source are within a reasonable range. In addition, through the heat pipe member, the heat transferred from the light source to the first heat dissipation member can be transferred to the second heat dissipation member, thereby simplifying the structure of the first heat dissipation member on the premise of ensuring heat dissipation of the light source, and further avoiding the structure of the first heat dissipation member from being too complex, or avoiding the size of the first heat dissipation member in the second direction from being too large, resulting in an excessive size of the optical machine in the second direction. In addition, since the second heat dissipation member is disposed at one end of the fuselage, by reasonably designing the second heat dissipation member, the size of the second heat dissipation member in the second direction can be avoided from being too large on the premise of meeting the heat dissipation requirements of the light source and the imaging unit, and further reducing the volume of the optical machine.

[0030] In a possible implementation, the fuselage is further provided with an avoidance notch for avoiding the first heat dissipation member and the heat pipe member.

[0031] By providing the avoidance notch to avoid the heat pipe member, the length of the heat pipe member can be reduced, which helps to improve the heat transfer speed of the heat pipe member. In addition, during the assembly process of the optical engine, the heat dissipation device can also move towards the fuselage along the first direction so that the heat dissipation device is docked with the fuselage, thereby improving the assembly speed of the heat dissipation device and the fuselage.

[0032] In a possible implementation, along the second direction, the projection of the fuselage covers the projection of the first heat dissipation member. The first heat dissipation member is arranged between the opposite ends of the fuselage, which can avoid the optical engine being too large due to the oversize of the first heat dissipation member while meeting the heat dissipation requirements of the light source, and helps to miniaturize the optical engine. Among them, the first direction is perpendicular to the second direction, and the optical axis direction of the lens is defined as the first direction.

[0033] In a possible implementation, one of the fuselage and the first heat dissipation member includes a positioning structure, and the other includes a fourth positioning portion. The positioning structure is used to cooperate with the fourth positioning portion to position the relative positions of the fuselage and the first heat dissipation member.

[0034] During the assembly process of the optical engine, by the cooperation of the positioning structure and the fourth positioning portion, the relative positions of the first heat dissipation member and the fuselage can be positioned, thereby improving the assembly speed of the heat dissipation device and the fuselage.

[0035] In a possible implementation, the positioning structure is a positioning notch provided on the first heat dissipation member, and the fuselage includes a fourth positioning portion inserted into the positioning notch.

[0036] During the assembly process of the optical engine, the heat dissipation device can move towards the fuselage along the first direction until the fourth positioning portion is inserted into the inside of the positioning notch, so that the first heat dissipation member and the fuselage can be quickly positioned, and further the assembly speed of the heat dissipation device and the fuselage can be improved.

[0037] In a possible implementation, one of the second heat dissipation member and the fuselage is provided with a positioning hole, and the other is provided with a fifth positioning portion for inserting into the positioning hole.

[0038] During the assembly process of the optical engine, the relative positions of the fuselage and the second heat dissipation member are positioned by the cooperation of the positioning hole and the fifth positioning portion, so that the relative positions of the heat dissipation device and the fuselage can be positioned, and further the assembly efficiency of the heat dissipation device and the fuselage can be improved.

[0039] In a possible implementation, the second heat dissipation member includes a second protrusion portion. Along the first direction, the projection of the second protrusion portion overlaps with the projection of the imaging element of the imaging unit, and there is a gap between the second protrusion portion and the imaging element of the imaging unit or the second protrusion portion is in contact with the imaging element.

[0040] By providing a second convex portion close to the imaging element, the optical engine provided by the embodiment of the present application enables heat exchange between the imaging element and the second heat sink, thereby improving the heat dissipation capacity of the imaging element.

[0041] The second aspect of the present application provides a vehicle headlight module, including a housing and an optical engine according to any one of the first aspect, and at least a part of the optical engine is disposed inside the housing.

[0042] The vehicle headlight module provided by the embodiment of the present application can improve the production efficiency and optical performance of the optical engine through a one-piece body. In addition, since the production cost of the one-piece body is low, the cost of the vehicle headlight module can be reduced.

[0043] The third aspect of the present application provides a vehicle, including an optical engine according to any one of the first aspect.

[0044] The vehicle provided by the embodiment of the present application can reduce the production cost of the vehicle through an optical engine with a one-piece body. Description of the Drawings

[0045] Figure 1 It is a schematic structural diagram of a vehicle headlight module provided by the embodiment of the present application;

[0046] Figure 2 It is a three-dimensional structural diagram of an optical engine provided by the embodiment of the present application;

[0047] Figure 3 It is Figure 2 an exploded schematic diagram of the optical engine in

[0048] Figure 4 It is Figure 2 a cross-sectional schematic diagram of the optical engine in

[0049] Figure 5 It is Figure 4 a partial enlarged schematic diagram at A in

[0050] Figure 6 It is Figure 2 a three-dimensional structural diagram of the separation of the body and a collimating lens in

[0051] Figure 7 It is Figure 6 a partial enlarged schematic diagram at the dashed line in

[0052] Figure 8 It is Figure 2 a three-dimensional structural diagram of the reflection unit in

[0053] Figure 9 It is Figure 2 a bottom view schematic diagram of the optical engine in

[0054] Figure 10 is Figure 2 a first three-dimensional structural schematic diagram of the fuselage in

[0055] Figure 11 is Figure 4 a partial enlarged schematic diagram at position B in

[0056] Figure 12 is Figure 2 a second three-dimensional structural schematic diagram of the fuselage in

[0057] Figure 13 is Figure 2 a cross-sectional schematic diagram of the heat dissipation device in with the fan and air guide cover removed;

[0058] Figure 14 is Figure 2 a top view schematic diagram of the optical engine in

[0059] Figure 15 is Figure 2 a three-dimensional structural schematic diagram of the heat dissipation device in with the fan and air guide cover removed.

[0060] Description of reference numerals:

[0061] 100, optical engine;

[0062] 200, headlight module;

[0063] 300, housing;

[0064] 10, light source unit; 11, light source; 12, collimating lens;

[0065] 20, reflection unit; 21, reflection element; 211, first hole; 22, bracket; 221, first positioning portion; 222, second hole; 223, supporting portion; 224, main body portion;

[0066] 30, imaging unit; 31, imaging element; 32, circuit board;

[0067] 40, lens;

[0068] 50, fuselage; 51, first opening; 511, annular step surface; 52, second opening; 53, third opening; 54, fourth opening; 55, first protrusion; 56, second positioning portion; 57, third positioning portion; 58, fourth positioning portion; 59, positioning hole;

[0069] 60, elastic member; 61, third hole;

[0070] 70, heat dissipation device; 71, first heat dissipation member; 711, positioning structure; 712, first heat exchange member; 713, second heat exchange member;

[0071] 72. Second heat dissipation member; 721. Fifth positioning portion; 722. Second protrusion; 723. Third heat exchange member; 724. Radiator;

[0072] 73. Heat pipe fitting; 74. Fan; 75. Air guide cover;

[0073] 81. Through hole; 82. Accommodating groove; 83. Avoidance notch. Detailed implementation manner

[0074] Currently, the optical engine includes a lens, an optical component, a light source, a projection chip, and a body. Among them, the body is composed of multiple structural members. The optical component includes a reflector and multiple collimating lenses. The reflector is connected to the body through a first bracket, and the collimating lenses are connected to the body through a second bracket. The collimating lenses are used to collimate the light beam emitted by the light source, and the reflector is used to reflect the light beam collimated by the collimating lenses to the projection chip. The projection chip is a digital micromirror device (DMD for short). The projection chip can modulate the image content onto the received light beam and output the imaging light modulated with the image content to the lens.

[0075] However, since the body is composed of multiple structural members and devices such as the reflector, the projection chip, and the collimating lenses are connected to the body through brackets, the number of parts of the optical engine is relatively large, resulting in too many assembly times of the optical engine, which will reduce the production efficiency of the optical engine. In addition, since the body is composed of multiple structural members, the production cost of the body will also increase, resulting in an increase in the production cost of the optical engine. In addition, installing devices such as collimating lenses and reflectors on the body through brackets will also increase the cost of the optical engine. Finally, since the body is composed of multiple structural members, the tolerance chain after the optical engine is assembled is very long, resulting in a large assembly error of the optical engine, which will reduce the performance of the optical engine.

[0076] In view of this, the embodiments of the present application provide an optical engine 100, a vehicle lamp module 200, and a vehicle. By cooperating the integrally formed body 50 with devices such as the light source 11 and the collimating lens 12, the number of parts of the optical engine 100 can be reduced, the assembly times of the optical engine 100 can be reduced, and the production efficiency of the optical engine 100 can be improved. In addition, the length of the tolerance chain after the optical engine 100 is assembled can be shortened, the assembly error of the optical engine 100 can be reduced, and the performance of the optical engine 100 can be improved. In addition, the part cost of the optical engine 100 can be reduced to reduce the production cost of the optical engine 100.

[0077] Figure 1 It is a schematic structural diagram of a vehicle lamp module provided by an embodiment of the present application. The vehicle provided by the embodiment of the present application includes a vehicle body which includes a vehicle lamp module 200. Among them, see Figure 1As shown, the vehicle lamp module 200 includes a housing 300 and an optical engine 100. At least a part of the optical engine 100 is disposed inside the housing 300. For example, a part of the optical engine 100 can be disposed inside the housing 300 and another part can be disposed outside the housing 300. Of course, the optical engine 100 can also be disposed inside the housing 300. The vehicle lamp module 200 can be used as a vehicle lamp to emit illumination light to ensure driving requirements. Alternatively, it can also project interactive information such as pictures and symbols on the ground to improve driving safety or realize rich intelligent vehicle lamp interaction scenarios.

[0078] Among them, the vehicle of the embodiment of the present application may include, but is not limited to, vehicles, ships, aircraft, rail trains, handcarts, etc. Among them, the vehicle may include, but is not limited to, unicycles, bicycles, tricycles, four-wheel vehicles, etc. In addition, the vehicle may include, but is not limited to, fuel vehicles, electric vehicles or hybrid vehicles, etc.

[0079] It should be noted that the optical engine 100 provided in the embodiment of the present application can be used not only in the vehicle lamp module 200, but also in electronic devices such as head-up displays, projectors, and vehicle-mounted displays.

[0080] The implementation manner of the optical engine 100 provided in the embodiment of the present application will be described below.

[0081] Figure 2 It is a three-dimensional structure schematic diagram of an optical engine provided in an embodiment of the present application. Figure 3 For Figure 2 the exploded schematic diagram of the optical engine in Figure 4 For Figure 2 the cross-sectional schematic diagram of the optical engine in

[0082] Combined with Figure 3 it can be seen that the optical engine 100 of the embodiment of the present application includes a light source unit 10, an imaging unit 30, a reflection unit 20, a lens 40 and an integrally formed body 50. Among them, the body 50 is provided with a first opening 51 (as shown in Figure 3 or Figure 4 ), a second opening 52 (as shown in Figure 4 or Figure 10 ), a third opening 53 (as shown in Figure 4 ), and a fourth opening 54 (as shown in Figure 3 ). Any one of the first opening 51, the second opening 52, the third opening 53 and the fourth opening 54 communicates the inside and the outside of the body 50. The first opening 51 is opposite to the second opening 52 along the second direction (for example, the Y direction in Figure 2 ), and the third opening 53 is opposite to the fourth opening 54 along the first direction (for example, the X direction in Figure 2 ). Among them, the first direction, the second direction and the third direction (for example, Figure 2The Z direction) is perpendicular, and the optical axis direction of the lens 40 is defined as the first direction. The light source unit 10 is disposed at the first opening 51 and connected to the fuselage 50 (for example Figure 4 as shown), the reflection unit 20 is disposed at the second opening 52 and connected to the fuselage 50 (for example Figure 4 as shown), the imaging unit 30 is disposed at the third opening 53 and connected to the fuselage 50 (for example Figure 4 as shown), and the lens 40 is disposed at the fourth opening 54 and connected to the fuselage 50 (for example Figure 2 or Figure 4 as shown). The light source unit 10 is used to emit light towards the reflection unit 20, the reflection unit 20 is used to reflect the light emitted by the light source unit 10 to the imaging unit 30, and the imaging unit 30 is used to output imaging light towards the lens 40 according to the light reflected by the reflection unit 20.

[0083] In the embodiment of the present application, by integrating the fuselage 50 to carry the light source unit 10, the imaging unit 30, the reflection unit 20, and the lens 40, the number of parts of the optical engine 100 can be reduced, thereby simplifying the assembly process of the optical engine 100, and further improving the production efficiency of the optical engine 100. In addition, since the light source unit 10, the imaging unit 30, the reflection unit 20, and the fuselage 50 are all connected to the fuselage 50, the length of the tolerance chain generated after the assembly of the optical engine 100 can be shortened, thereby reducing the assembly error of the optical engine 100, and further improving the performance of the optical engine 100. In addition, since the fuselage 50 is formed in one piece, the production cost of the fuselage 50 can be reduced, and thus the production cost of the optical engine 100 can be reduced. At the same time, devices such as the light source unit 10, the imaging unit 30, the reflection unit 20, and the lens 40 are connected to the fuselage 50, and the bracket 22 connecting one of the light source unit 10, the imaging unit 30, the reflection unit 20, and the lens 40 to the fuselage 50 can be removed, which can reduce the part cost of the optical engine 100, and thus reduce the production cost of the optical engine 100.

[0084] Combined with Figure 2 it can be seen that the light source unit 10 may include a light source 11 and at least one collimating lens 12. For example, the number of collimating lenses 12 may be two. Of course, the number of collimating lenses 12 may also be less than or more than two. Among them, the light source 11 is connected to the fuselage 50, and the light source 11 is used to emit light towards the collimating lens 12. When the number of collimating lenses 12 is multiple, the multiple collimating lenses 12 are arranged at intervals along the second direction (such as Figure 4 the Y direction in Figure 5 as shown), two collimating lenses 12 are arranged at intervals, and one of the two collimating lenses 12 is disposed between the light source 11 and the other collimating lens 12 and is spaced from the light source 11. At least a part of each collimating lens 12 is disposed inside the first opening 51, for example Figure 5As shown, each collimating lens 12 is disposed inside the first opening 51. Of course, a part of the plurality of collimating lenses 12 can also be disposed inside the first opening 51, and another part can be partially disposed inside the first opening 51. Each collimating lens 12 is disposed on the optical path between the light source 11 and the reflection unit 20 and is connected to the fuselage 50, so that each collimating lens 12 can collimate the light emitted by the light source 11. Among them, Figure 5 is Figure 4 a partial enlarged schematic view of part A in

[0085] Regarding the specific structure of the light source 11, no limitation is made here. Exemplarily, the light source 11 can be a surface-emitting semiconductor light source. For example, it can be a light emitting diode (LED) lamp board.

[0086] Combined with Figure 5 it can be seen that the light source 11 can be disposed outside the first opening 51 and shield the first opening 51. Of course, the light source 11 can also be partially disposed outside the first opening 51 and shield the first opening 51. By shielding the first opening 51 with the light source 11, the first opening 51 can be sealed by the light source 11, and the number of parts of the optical engine 100 can be reduced. In addition, the light source 11 can be in contact with or not in contact with the fuselage 50, and no specific limitation is made here.

[0087] Combined with Figure 5 as shown, by disposing at least a part of each collimating lens 12 inside the first opening 51, on the premise of collimating the light emitted by the light source 11, the integration degree of the optical engine 100 can be improved, which is beneficial to the miniaturization of the optical engine 100.

[0088] Figure 6 is Figure 2 a three-dimensional structural schematic view of the separation of the fuselage and a collimating lens in Figure 7 is Figure 6 a partial enlarged schematic view of the dashed line in

[0089] In some possible implementation manners, at least one annular stepped surface 511 can be provided on the inner wall of the first opening 51. For example Figure 7 as shown, two annular stepped surfaces 511 are provided on the inner wall of the first opening 51, and the two annular stepped surfaces 511 are spaced apart. Combined with Figure 5 it can be seen that each annular stepped surface 511 corresponds to a collimating lens 12 and is used to carry the corresponding collimating lens 12.

[0090] During the assembly process of the optical engine 100, the relative positions of the collimating lens 12 and the fuselage 50 can be positioned by the cooperation of the annular stepped surface 511 and the collimating lens 12, thereby reducing the assembly difficulty of the collimating lens 12 and the fuselage 50, and further improving the production efficiency of the optical engine 100. In addition, the annular stepped surface 511 can also be bonded to the bottom surface of the collimating lens 12 by bonding to connect the fuselage 50 and the collimating lens 12.

[0091] There is no limitation on how the annular stepped surface 511 cooperates with the collimating lens 12. Exemplarily, for example Figure 5 As shown, there is a gap for accommodating glue between the annular stepped surface 511 and the collimating lens 12, so that the annular stepped surface 511 is connected to the bottom surface of the collimating lens 12 by bonding. Alternatively, the annular stepped surface 511 can also be in contact with the bottom surface of the collimating lens 12.

[0092] In some embodiments, as shown in Figure 7 the fuselage 50 can also be provided with a plurality of first protrusions 55, and the plurality of first protrusions 55 are arranged inside the first opening 51. Each collimating lens 12 corresponds to a plurality of first protrusions 55, and each first protrusion 55 is in contact with the side wall of the corresponding collimating lens 12 (for example Figure 5 as shown). During the assembly process of the optical engine 100, the relative positions of the collimating lens 12 and the fuselage 50 can be positioned by the cooperation of the first protrusions 55 and the collimating lens 12, so that the assembly speed of the optical engine 100 can be improved.

[0093] The number of the first protrusions 55 corresponding to the plurality of collimating lenses 12 can be the same. For example, each collimating lens 12 can correspond to six first protrusions 55. Of course, the number of the first protrusions 55 corresponding to each collimating lens 12 can also be more or less than six. In addition, the number of the first protrusions 55 corresponding to the plurality of collimating lenses 12 can also be different, or the number of the first protrusions 55 corresponding to a part of the plurality of collimating lenses 12 can be the same, and the number of the first protrusions 55 corresponding to the other part can be different.

[0094] As shown in Figure 2 it can be seen that the reflection unit 20 can include a bracket 22 and a reflection element 21. Among them, the reflection element 21 is arranged inside the fuselage 50 and is connected to the fuselage 50 through the bracket 22 (for example Figure 4 as shown), and the reflection element 21 is used to reflect the light emitted by the light source unit 10 to the imaging unit 30. A part of the bracket 22 is arranged outside the fuselage 50 through the third opening 53, and another part is arranged inside the fuselage 50 and is fixedly connected to the reflection element 21 (for example Figure 4 as shown).

[0095] During the assembly process of the optical machine 100, the reflecting element 21 can be installed on the fuselage 50 through the bracket 22, so that the reflecting element 21 is arranged inside the fuselage 50 to reflect the light emitted by the light source unit 10 to the imaging unit 30. In addition, the bracket 22 and the reflecting element 21 can be pre-assembled into a component and then connected to the fuselage 50, which can reduce the difficulty of connecting the reflecting element 21 to the fuselage 50 and improve the assembly efficiency of the optical machine 100.

[0096] There is no limitation on the specific structure of the reflecting element 21 here. Exemplarily, for example Figure 8 As shown, the reflecting element 21 can be a curved mirror. Or in some embodiments, the reflecting element 21 can also be a prism. Among them, Figure 8 is Figure 2 a three-dimensional structure schematic diagram of the reflecting unit in

[0097] There is no limitation on how the reflecting element 21 is connected to the bracket 22 here. Exemplarily, for example Figure 4 As shown, there is a gap for accommodating glue between the reflecting element 21 and the bracket 22, so that the reflecting element 21 is bonded to the bracket 22.

[0098] In some possible implementation manners, one of the reflecting element 21 and the bracket 22 can include a first hole 211, and the other can include a first positioning portion 221 at least partially disposed inside the first hole 211. For example Figure 8 As shown, the reflecting element 21 can be provided with the first hole 211 and the bracket 22 can be provided with the first positioning portion 221. Of course, the first hole 211 can also be provided on the bracket 22 and the first positioning portion 221 can also be provided on the reflecting element 21.

[0099] Figure 9 is Figure 2 a bottom view schematic diagram of the optical machine in Figure 9 As shown, during the assembly process of the reflecting unit 20, by inserting the first positioning portion 221 into the inside of the first hole 211 (for example

[0100] There is no limitation on the specific shape of the first hole 211 here. Exemplarily, the first hole 211 can be a circular hole. Or, the first hole 211 can also be a square hole.

[0101] To locate the relative positions of the reflection element 21 and the bracket 22, it is necessary to make the structure of the first positioning portion 221 match the structure of the first hole 211. Exemplarily, when the first hole 211 is a circular hole, the first positioning portion 221 can be cylindrical (for example Figure 8 as shown). Of course, when the first hole 211 has other structures, the first positioning portion 221 can also have other structures. For example, the first positioning portion 221 can also be prismatic.

[0102] In the embodiment of the present application, the number of the first holes 211 is two, and the two first holes 211 are distributed at opposite ends of the reflection element 21. Of course, the number of the first holes 211 can also be more than two. In this case, at least one first hole 211 is provided at each of the opposite ends of the reflection element 21. When the number of the first holes 211 is multiple, each first hole 211 corresponds to a first positioning portion 221. For example Figure 8 as shown, the two first holes 211 and the two first positioning portions 221 correspond one by one.

[0103] Figure 10 For Figure 2 the first three-dimensional structural schematic diagram of the fuselage in. In some possible implementation manners, one of the bracket 22 and the fuselage 50 includes a second hole 222, and the other includes a second positioning portion 56 at least partially disposed inside the second hole 222. For example, the second hole 222 can be disposed on the bracket 22 (such as Figure 8 shown) and the second positioning portion 56 can be disposed on the fuselage 50 (such as Figure 10 shown), or the second hole 222 can also be disposed on the fuselage 50 and the second positioning portion 56 can also be disposed on the bracket 22.

[0104] During the assembly process of the optical engine 100, by inserting the second positioning portion 56 into the inside of the second hole 222, the relative positions of the bracket 22 and the fuselage 50 can be located, so that the relative positions of the reflection element 21 and the fuselage 50 can be ensured, and further the relative positions of the reflection element 21 and the light source unit 10 and the imaging unit 30 can be ensured.

[0105] Combined with Figure 8 shown, the number of the second holes 222 is two, and the two second holes 222 are disposed at opposite ends of the bracket 22, and each second hole 222 corresponds to a second positioning portion 56. Of course, the number of the second holes 222 can also be more than two. In this case, at least one second hole 222 is provided at each of the opposite ends of the bracket 22, and each second hole 222 corresponds to a second positioning portion 56.

[0106] There is no limitation on the specific structure of the second hole 222. Exemplarily, the second hole 222 may be a circular hole. Of course, the second hole 222 may also have other structures. Additionally, when the number of the second holes 222 is multiple, the structures of the multiple second holes 222 may be the same, partially the same, or different.

[0107] In the embodiments of the present application, there is no limitation on the specific structure of the second positioning portion 56. Exemplarily, as Figure 10 shown, the second positioning portion 56 may be cylindrical.

[0108] In some possible implementation manners, in combination with Figure 8 it can be known that the bracket 22 may include a supporting portion 223 and a main body portion 224. Among them, a part of the supporting portion 223 is disposed inside the fuselage 50 and fixedly connected to the reflection element 21 (for example Figure 4 shown), the main body portion 224 is disposed outside the fuselage 50 and shields the second opening 52 (for example Figure 4 shown), and the main body portion 224 is fixedly connected to the fuselage 50.

[0109] Correspondingly, when connecting the reflection element 21 to the fuselage 50 by using the bracket 22 formed by the main body portion 224 and the supporting portion 223, the second opening 52 can also be sealed to ensure the sealing performance of the optical machine 100. Additionally, the number of parts of the optical machine 100 can be reduced, thereby improving the production efficiency of the optical machine 100.

[0110] In combination with Figure 8 it can be known that since the fuselage 50 is connected to the main body portion 224, the second hole 222 is disposed in the main body portion 224. Additionally, since the reflection element 21 is connected to the supporting portion 223, the first positioning portion 221 is disposed in the supporting portion 223.

[0111] Figure 11 For Figure 4 is a partial enlarged schematic view at position B in Figure 2 . In combination with Figure 11 it can be known that the imaging unit 30 may include a circuit board 32 and an imaging element 31. Among them, as seen in Figure 11 shown, the circuit board 32 is disposed outside the fuselage 50 and connected to the fuselage 50, the imaging element 31 is connected to the circuit board 32 and disposed at the third opening 53, and the imaging element 31 is configured to output imaging light directed towards the lens 40 according to the light reflected by the reflection unit 20. Correspondingly, by disposing the circuit board 32 outside the fuselage 50, the difficulty of connecting the circuit board 32 to the fuselage 50 can be reduced, and the heat dissipation requirements of the imaging unit 30 can also be met.

[0112] Among them, the imaging element 31 may include, but is not limited to, digital micromirror devices (DMDs) and micro electro mechanical systems (MEMS). For example, in the embodiments of the present application, the DMD is taken as an example of the imaging element 31 for illustration.

[0113] In some possible implementation manners, as shown in Figure 11 and along the first direction (such as Figure 11 the X direction in ), the projection of the imaging element 31 may cover the third opening 53. The imaging element 31 can be used to shield the third opening 53 and can be used to seal the third opening 53, which can reduce the number of parts of the optical engine 100 and help to further improve the production efficiency of the optical engine 100.

[0114] Among them, the projection of the imaging element 31 covering the third opening 53 along the first direction can be understood as the imaging element 31 covering the third opening 53 along the first direction.

[0115] In some embodiments, as shown in Figure 11 , the body 50 may further be provided with a receiving groove 82 for receiving at least a part of the imaging element 31. For example, the imaging element 31 may be disposed inside the receiving groove 82. Of course, a part of the imaging element 31 may also be disposed inside the receiving groove 82. The receiving groove 82 communicates with the inside of the body 50 through the third opening 53. Therefore, the inside of the body 50 communicates with the outside of the body 50 through the third opening 53 and the receiving groove 82. During the assembly process of the optical engine 100, the relative positions of the imaging unit 30 and the body 50 can be roughly positioned through the receiving groove 82. In addition, the receiving groove 82 can be matched with the imaging element 31 to improve the sealing performance between the imaging unit 30 and the body 50.

[0116] In some possible implementation manners, as shown in Figure 11 , the optical engine 100 may further include an elastic member 60 in a ring structure. The elastic member 60 is disposed between the body 50 and the imaging element 31 and abuts against the imaging element 31 and the body 50 respectively.

[0117] As shown in Figure 11 , by providing the elastic member 60 between the body 50 and the imaging element 31, the sealing performance between the imaging element 31 and the body 50 can be improved. In addition, since the material of the elastic member 60 is relatively soft, the imaging element 31 is in soft contact with the elastic member 60, which can avoid hard contact between the imaging element 31 and the body 50, and thus can prevent the imaging element 31 from being damaged during the assembly process of the optical engine 100.

[0118] Among them, the outer diameter of the elastic member 60 is larger than the size of the third opening 53. Additionally, the inner diameter of the elastic member 60 can be larger than or equal to the size of the third opening 53 to prevent the elastic member 60 from affecting the imaging element 31's reception of light and output of imaging light.

[0119] There is no limitation on the specific material of the elastic member 60 here. For example, it can be rubber.

[0120] In some embodiments, the elastic member 60 can be fixedly connected to the imaging element 31, such that the imaging unit 30 and the elastic member 60 can be pre-assembled into a component in advance, thereby reducing the number of assembly times of the optical engine 100 and further improving the production efficiency of the optical engine 100.

[0121] Figure 12 For Figure 2 the second three-dimensional structural schematic diagram of the fuselage in Figure 2 shown. In some embodiments, one of the fuselage 50 and the elastic member 60 can include a third hole 61, and the other can include a third positioning portion 57 at least partially disposed inside the third hole 61. For example, the third hole 61 can be disposed in the elastic member 60 (as Figure 12 shown) and the third positioning portion 57 can be disposed in the fuselage 50 (as

[0122] shown). Of course, the third hole 61 can also be disposed in the fuselage 50 and the third positioning portion 57 can also be disposed in the elastic member 60.

[0123] Combined with Figure 12 it can be seen that the number of the third positioning portions 57 is two. Of course, the number of the third positioning portions can also be less than or more than two. Additionally, when the number of the third positioning portions 57 is multiple, the structures of the multiple third positioning portions 57 can be the same or partially the same, or they can also be different.

[0124] Combined with Figure 2 and Figure 4It can be known that a part of the lens 40 is disposed inside the fourth opening 54 and can be threadedly connected to the body 50. Since the lens 40 is threadedly connected to the body 50, the difficulty of connecting the lens 40 to the body 50 can be reduced on the premise of realizing the connection between the lens 40 and the body 50. In addition, the focal length of the lens 40 can be adjusted by turning the lens 40, which can reduce the difficulty of focusing. In addition, by disposing at least a part of the lens 40 inside the fourth opening 54, the size of the optical machine 100 in the first direction can be reduced, which helps to miniaturize the optical machine 100.

[0125] There is no limitation on the specific structure of the lens 40 here. Exemplarily, the lens 40 may include a hollow frame body and a plurality of lenses. The plurality of lenses are disposed inside the frame body and arranged side by side in the first direction. A part of the frame body is disposed inside the fourth opening 54 and is threadedly connected to the body 50.

[0126] It should be noted that in addition to being connected to the body 50 by threaded connection, the lens 40 may also be connected to the body 50 by other means, such as snap connection.

[0127] Figure 13 For Figure 2 the cross-sectional schematic view of the heat dissipation device in Figure 1 removing the fan and the air guide cover. In some possible implementation manners, in combination with Figure 2 and Figure 13 it can be known that the optical machine 100 may further include a heat dissipation device 70. The heat dissipation device 70 includes a first heat dissipation member 71, a second heat dissipation member 72, and a heat pipe member 73. Among them, as shown in Figure 4 one end of the heat pipe member 73 is disposed inside the first heat dissipation member 71 and connected to the first heat dissipation member 71, and the other end of the heat pipe member 73 is disposed inside the second heat dissipation member 72 and connected to the second heat dissipation member 72. As shown in the above

[0128] The heat dissipation device 70 composed of the first heat dissipation member 71, the second heat dissipation member 72, and the heat pipe member 73 can dissipate heat from the imaging unit 30 and the light source 11, so that the temperatures of the imaging unit 30 and the light source 11 are within a reasonable range. In addition, through the heat pipe member 73, the heat transferred from the light source 11 to the first heat dissipation member 71 can be transferred to the second heat dissipation member 72, thereby simplifying the structure of the first heat dissipation member 71 on the premise of ensuring the heat dissipation of the light source 11, and further avoiding the structure of the first heat dissipation member 71 from being too complex, or avoiding the size of the first heat dissipation member 71 in the second direction from being too large, resulting in an overly large size of the optical machine 100 in the second direction. In addition, since the second heat dissipation member 72 is disposed at one end of the fuselage 50, through reasonable design of the second heat dissipation member 72, it is possible to avoid the size of the second heat dissipation member 72 in the second direction from being too large on the premise of meeting the heat dissipation requirements of the light source 11 and the imaging unit 30, and further reduce the volume of the optical machine 100.

[0129] A gap may be provided between the first heat dissipation member 71 and the light source 11 (for example Figure 5 as shown), and this gap can be used to accommodate a heat-conducting medium. Of course, a heat-conducting medium may not be provided between the first heat dissipation member 71 and the light source 11, or the first heat dissipation member 71 may also be in contact with the light source 11.

[0130] Regarding the specific structure of the first heat dissipation member 71, no limitation is imposed here. Exemplarily, in combination with Figure 13 it can be seen that the first heat dissipation member 71 may include a first heat exchange member 712 and a second heat exchange member 713. One end of the heat pipe member 73 is disposed between the first heat exchange member 712 and the second heat exchange member 713, and the first heat exchange member 712 is disposed between the heat pipe member 73 and the light source 11. During the heat dissipation process, the heat generated by the light source 11 is transferred to the second heat exchange member 713 and the heat pipe member 73 respectively through the first heat exchange member 712. The second heat exchange member 713 exchanges heat with the air in its vicinity, and the heat pipe member 73 transfers the heat generated by the light source 11 to the second heat dissipation member 72.

[0131] Among them, the first heat exchange member 712 may include, but is not limited to, a copper plate, an aluminum alloy plate, etc. Regarding the specific structure of the second heat dissipation member 72, no limitation is imposed here. For example, the second heat dissipation member 72 may be a plate-like structure.

[0132] Regarding the specific structure of the second heat dissipation member 72, no limitation is imposed here. Exemplarily, in combination with Figure 13It can be known that the second heat dissipation member 72 can include a third heat exchange member 723 and a radiator 724. The other end of the heat pipe member 73 is disposed between the third heat exchange member 723 and the radiator 724, and the third heat exchange member 723 is disposed close to the imaging unit 30. The radiator 724 includes a plurality of heat dissipation teeth, which can increase the heat exchange area between the radiator 724 and the air, thereby improving the heat dissipation capacity of the second heat dissipation member 72. During the heat dissipation process, the heat generated by the imaging unit 30 can be transferred to the heat pipe member 73 and the radiator 724, and the heat pipe member 73 can transfer the heat generated by the imaging unit 30 to the radiator 724.

[0133] In some possible implementation manners, in combination with Figure 2 It can be known that along the second direction, the projection of the fuselage 50 can cover the projection of the first heat dissipation member 71, and the first heat dissipation member 71 is disposed between the opposite ends of the fuselage 50.

[0134] Correspondingly, it is possible to avoid the excessive size of the optical engine 100 caused by the size of the first heat dissipation member 71 while meeting the heat dissipation requirements of the light source 11, which helps to miniaturize the optical engine 100.

[0135] Figure 14 For Figure 2 is a top view schematic diagram of the optical engine in Figure 14 In some possible implementation manners, one of the fuselage 50 and the first heat dissipation member 71 may include a positioning structure 711, and the other may include a fourth positioning portion 58. The positioning structure 711 is used to cooperate with the fourth positioning portion 58 to position the relative positions of the fuselage 50 and the first heat dissipation member 71. For example,

[0136] As shown, the positioning structure 711 can be disposed on the first heat dissipation member 71 and the fourth positioning portion 58 can be disposed on the fuselage 50. Of course, the positioning structure 711 can also be disposed on the fuselage 50 and the fourth positioning portion 58 can also be disposed on the first heat dissipation member 71.

[0137] In combination with Figure 14 It can be known that the number of the positioning structures 711 can be two, and the two positioning structures 711 are respectively disposed at the opposite ends of the first heat dissipation member 71, and each positioning structure 711 corresponds to a fourth positioning portion 58. Of course, the number of the positioning structures 711 can also be more than two. At this time, at least one positioning structure 711 is disposed at each end of the opposite ends of the first heat dissipation member 71.

[0138] Regarding the specific structure of the positioning structure 711, no limitation is imposed here. Exemplarily, for exampleFigure 14 As shown, the positioning structure 711 can be a positioning notch provided on the first heat dissipation member 71, and the fuselage 50 can include a fourth positioning portion 58 inserted into the positioning notch. During the assembly process of the optical engine 100, the heat dissipation device 70 can move along the axial direction of the lens 40 towards the fuselage 50 until the fourth positioning portion 58 is inserted into the interior of the positioning notch, so that the relative position between the fuselage 50 and the heat dissipation device 70 can be quickly realized, and further the assembly speed of the heat dissipation device 70 and the fuselage 50 can be improved.

[0139] Among them, in addition to being a positioning notch, the positioning structure 711 can also be structures such as a groove or an opening.

[0140] Among them, no limitation is imposed here on the specific structure of the fourth positioning portion 58. Exemplarily, the fourth positioning portion 58 can be cylindrical (for example Figure 12 as shown).

[0141] It should be noted that when the number of the positioning structures 711 is multiple, the positioning structures 711 and the fourth positioning portion 58 can be provided on the fuselage 50 simultaneously.

[0142] Figure 15 is Figure 2 a three-dimensional structural schematic diagram of the heat dissipation device in [reference] without the fan and the air guide cover. In some possible implementation manners, one of the second heat dissipation member 72 and the fuselage 50 can be provided with a positioning hole 59, and the other can be provided with a fifth positioning portion 721 for inserting into the positioning hole 59. For example, the fuselage 50 can be provided with a positioning hole 59 (for example Figure 12 as shown) and the second heat dissipation member 72 can be provided with a fifth positioning portion 721 (for example Figure 15 as shown). Of course, the positioning can also be provided on the second heat dissipation member 72 and the fifth positioning portion 721 can also be provided on the fuselage 50.

[0143] Correspondingly, during the assembly process of the optical engine 100, the relative position between the fuselage 50 and the second heat dissipation member 72 can be positioned by the cooperation of the positioning hole 59 and the fifth positioning portion 721, so that the relative position between the heat dissipation device 70 and the fuselage 50 can be positioned, and further the assembly efficiency of the heat dissipation device 70 and the fuselage 50 can be improved.

[0144] No limitation is imposed here on the specific structure of the fifth positioning portion 721. Exemplarily, in combination with Figure 15 it can be known that the fifth positioning portion 721 can be cylindrical.

[0145] In combination with Figure 15It can be seen that the number of the fifth positioning parts 721 can be two, and the two fifth positioning parts 721 are respectively arranged at opposite ends of the second heat dissipation part 72, and each fifth positioning part 721 corresponds to a positioning hole 59. Of course, the number of the fifth positioning parts 721 can also be more than two.

[0146] It should be noted that when the number of the fifth positioning parts 721 and the positioning holes 59 is multiple, the fifth positioning parts 721 and the positioning holes 59 can be arranged on the fuselage 50 at the same time. Correspondingly, the fifth positioning parts 721 and the positioning holes 59 can also be arranged on the second heat dissipation part 72 at the same time.

[0147] In some possible implementation manners, in combination with Figure 11 It can be seen that the second heat dissipation part 72 can include a second protrusion part 722. The circuit board 32 includes a through hole 81 for the second protrusion part 722 to pass through. The imaging element 31 is arranged between the lens 40 and the second protrusion part 722. A gap can be provided between the imaging element 31 and the second protrusion part 722, and this gap can be used to accommodate a heat conduction medium. Of course, the imaging element 31 can also be in contact with the second protrusion part 722.

[0148] Correspondingly, as shown in the figure, by arranging the second protrusion part 722 close to the imaging element 31, the imaging element 31 can exchange heat with the second heat dissipation part 72, so as to improve the heat dissipation capacity of the imaging element 31.

[0149] In combination with Figure 11 It can be seen that since the third heat exchange part 723 is close to the circuit board 32, the second protrusion part 722 is arranged on the third heat exchange part 723, so that the heat generated by the imaging element 31 is transferred to the third heat exchange part 723, ensuring that the temperature of the imaging element 31 is within a reasonable range.

[0150] In some possible implementation manners, as Figure 12 shown, the fuselage 50 can also be provided with an avoidance notch 83, and the avoidance notch 83 is used to avoid the first heat dissipation part 71 and the heat pipe part 73 (such as Figure 2 shown).

[0151] Correspondingly, by avoiding the heat pipe part 73 through the avoidance notch 83, the length of the heat pipe part 73 can be reduced, which helps to improve the heat transfer speed of the heat pipe part 73. In addition, during the assembly process of the optical machine 100, when the heat dissipation device 70 moves towards the fuselage 50 in the first direction, the fuselage 50 will not interfere with the first heat dissipation part 71 and the heat pipe part 73, so that the heat dissipation device 70 and the fuselage 50 can be quickly docked, and thus the assembly speed of the optical machine 100 can be improved.

[0152] In some possible implementation manners, in combination with Figure 2 and Figure 3It can be seen that the heat dissipation device 70 may further include a fan 74 and a wind guide cover 75. Among them, the second heat dissipation member 72 is disposed between the fan 74 and the fuselage 50, and the guiding fan 74 is disposed inside the wind guide cover 75. The wind guide cover 75 and the second heat dissipation member 72 can cooperate with each other to define a heat exchange cavity, an air inlet and an air outlet. The air inlet and the air outlet are spaced along a first direction, and the air inlet is close to the fuselage 50. During the heat dissipation process, the cooperation between the fan 74 and the wind guide cover 75 can improve the heat dissipation capacity of the second heat dissipation member 72. In addition, the noise can also be reduced.

[0153] In the description of the embodiments of the present application, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense. For example, it may be a fixed connection or an indirect connection through an intermediate medium. It may be the communication inside two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific situations.

[0154] The device or element referred to in the embodiments of the present application or implied must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the embodiments of the present application. In the description of the embodiments of the present application, the meaning of "a plurality" is two or more, unless otherwise specifically specified.

[0155] The terms "first", "second", "third", "fourth", etc. (if any) in the specification, claims and drawings of the embodiments of the present application are used to distinguish similar objects and do not necessarily describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "comprising" and "having" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product or device comprising a series of steps or units does not necessarily limit to those steps or units clearly listed, but may include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0156] The term "a plurality" herein refers to two or more. The term "and / or" herein is only a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B may indicate: A exists alone, A and B exist simultaneously, and B exists alone. In addition, the character " / " herein generally indicates that the associated objects before and after are in an "or" relationship; in a formula, the character " / " indicates that the associated objects before and after are in a "division" relationship.

[0157] It is understood that the various numerical numbers involved in the embodiments of the present application are only for convenience of description and are not used to limit the scope of the embodiments of the present application.

[0158] It is understood that in the embodiments of the present application, the magnitude of the serial numbers of the above processes does not mean the sequence of execution, and the execution sequence of each process should be determined by its function and internal logic, and should not constitute any limitation to the implementation process of the embodiments of the present application.

Claims

1. An optical machine, characterized in that, it includes a light source unit, an imaging unit, a reflection unit, a lens and an integrally formed body; the body is provided with a first opening, a second opening, a third opening and a fourth opening, and any one of the first opening, the second opening, the third opening and the fourth opening communicates the inside and the outside of the body; the light source unit is arranged at the first opening and connected to the body, the reflection unit is arranged at the second opening and connected to the body, the imaging unit is arranged at the third opening and connected to the body, and the lens is arranged at the fourth opening and connected to the body; the reflection unit is used for reflecting the light emitted by the light source unit to the imaging unit, and the imaging unit is used for outputting imaging light directed at the lens according to the light reflected by the reflection unit.

2. The optical machine according to claim 1, characterized in that, the light source unit includes a light source and at least one collimating lens, the light source is connected to the body, at least part of each collimating lens is arranged inside the first opening, and each collimating lens is arranged on the optical path between the light source and the reflection unit and connected to the body.

3. The optical machine according to claim 2, characterized in that, the inner wall of the first opening is provided with at least one annular step surface, and each annular step surface corresponds to one collimating lens and is used for carrying the corresponding collimating lens.

4. The optical machine according to claim 2 or 3, characterized in that, the body is further provided with a plurality of first protrusions, the plurality of first protrusions are arranged inside the first opening, each collimating lens corresponds to the plurality of first protrusions, and each first protrusion is in contact with the side wall of the corresponding collimating lens.

5. The optical machine according to any one of claims 1 to 4, characterized in that, the reflection unit includes a bracket and a reflection element, the reflection element is arranged inside the body and connected to the body through the bracket, and the reflection element is used for reflecting the light emitted by the light source unit to the imaging unit.

6. The optical machine according to claim 5, characterized in that, one of the reflection element and the bracket includes a first hole, and the other includes a first positioning portion at least partially arranged inside the first hole.

7. The optical machine according to claim 5 or 6, characterized in that, one of the bracket and the body includes a second hole, and the other includes a second positioning portion at least partially arranged inside the second hole.

8. The optical machine according to any one of claims 1 to 7, characterized in that, the imaging unit includes a circuit board and an imaging element, the circuit board is arranged outside the body and connected to the body, the imaging element is connected to the circuit board and arranged at the third opening, and the imaging element is used for outputting imaging light directed at the lens according to the light reflected by the reflection unit.

9. The optical machine according to claim 8, characterized in that, The fuselage is further provided with a receiving groove for receiving at least a part of the imaging element, and the receiving groove communicates with the interior of the fuselage through the third opening.

10. The optical engine according to claim 8 or 9, wherein, the optical engine further includes an elastic member in an annular structure, and the elastic member is disposed between the fuselage and the imaging element and is in contact with the imaging element and the fuselage respectively.

11. The optical engine according to any one of claims 1 to 10, wherein, a part of the lens is disposed inside the fourth opening and is threadedly connected to the fuselage.

12. The optical engine according to any one of claims 1 to 11, wherein, the optical engine further includes a heat dissipation device, and the heat dissipation device includes a first heat dissipation member, a second heat dissipation member and a heat pipe member; one end of the heat pipe member is disposed inside the first heat dissipation member and is connected to the first heat dissipation member, and the other end of the heat pipe member is disposed inside the second heat dissipation member and is connected to the second heat dissipation member; the first heat dissipation member covers the light source of the light source unit and is connected to the fuselage, and the second heat dissipation member covers the imaging unit and is connected to the fuselage.

13. The optical engine according to claim 12, wherein, along the second direction, the projection of the fuselage covers the projection of the first heat dissipation member, and the first heat dissipation member is disposed between the opposite ends of the fuselage; wherein, the first direction is perpendicular to the second direction, and the optical axis direction of the lens is defined as the first direction.

14. The optical engine according to claim 12 or 13, wherein, the second heat dissipation member includes a second convex portion, and along the first direction, the projection of the second convex portion overlaps with the projection of the imaging element of the imaging unit, and there is a gap between the second convex portion and the imaging element or the second convex portion is in contact with the imaging element.

15. A vehicle headlight module, wherein, it includes a housing and the optical engine according to any one of claims 1 to 14, and at least a part of the optical engine is disposed inside the housing.

16. A vehicle, wherein, it includes the optical engine according to any one of claims 1 to 14.

Images