WO2019184277A1 - 探照灯、云台组件和无人机 - Google Patents

探照灯、云台组件和无人机 Download PDF

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Publication number
WO2019184277A1
WO2019184277A1 PCT/CN2018/107017 CN2018107017W WO2019184277A1 WO 2019184277 A1 WO2019184277 A1 WO 2019184277A1 CN 2018107017 W CN2018107017 W CN 2018107017W WO 2019184277 A1 WO2019184277 A1 WO 2019184277A1
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WO
WIPO (PCT)
Prior art keywords
light source
searchlight
chamber
pan
heat sink
Prior art date
Application number
PCT/CN2018/107017
Other languages
English (en)
French (fr)
Inventor
刘煜程
周琦
陈汉平
Original Assignee
深圳市大疆创新科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Priority to CN201880016706.3A priority Critical patent/CN110462279A/zh
Publication of WO2019184277A1 publication Critical patent/WO2019184277A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/02—Arrangements or adaptations of signal or lighting devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/02—Arrangements or adaptations of signal or lighting devices
    • B64D47/06—Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F21—LIGHTING
    • F21S—NON-PORTABLE LIGHTING DEVICES; SYSTEMS THEREOF; VEHICLE LIGHTING DEVICES SPECIALLY ADAPTED FOR VEHICLE EXTERIORS
    • F21S8/00—Lighting devices intended for fixed installation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F21—LIGHTING
    • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
    • F21V19/00—Fastening of light sources or lamp holders
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F21—LIGHTING
    • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
    • F21V19/00—Fastening of light sources or lamp holders
    • F21V19/02—Fastening of light sources or lamp holders with provision for adjustment, e.g. for focusing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F21—LIGHTING
    • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
    • F21V23/00—Arrangement of electric circuit elements in or on lighting devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F21—LIGHTING
    • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
    • F21V29/00—Protecting lighting devices from thermal damage; Cooling or heating arrangements specially adapted for lighting devices or systems
    • F21V29/50—Cooling arrangements
    • F21V29/502—Cooling arrangements characterised by the adaptation for cooling of specific components
    • F21V29/503—Cooling arrangements characterised by the adaptation for cooling of specific components of light sources
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F21—LIGHTING
    • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
    • F21V29/00—Protecting lighting devices from thermal damage; Cooling or heating arrangements specially adapted for lighting devices or systems
    • F21V29/50—Cooling arrangements
    • F21V29/60—Cooling arrangements characterised by the use of a forced flow of gas, e.g. air
    • F21V29/67—Cooling arrangements characterised by the use of a forced flow of gas, e.g. air characterised by the arrangement of fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F21—LIGHTING
    • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
    • F21V29/00—Protecting lighting devices from thermal damage; Cooling or heating arrangements specially adapted for lighting devices or systems
    • F21V29/50—Cooling arrangements
    • F21V29/70—Cooling arrangements characterised by passive heat-dissipating elements, e.g. heat-sinks
    • F21V29/74—Cooling arrangements characterised by passive heat-dissipating elements, e.g. heat-sinks with fins or blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F21—LIGHTING
    • F21V—FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMS THEREOF; STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHER ARTICLES, NOT OTHERWISE PROVIDED FOR
    • F21V29/00—Protecting lighting devices from thermal damage; Cooling or heating arrangements specially adapted for lighting devices or systems
    • F21V29/50—Cooling arrangements
    • F21V29/70—Cooling arrangements characterised by passive heat-dissipating elements, e.g. heat-sinks
    • F21V29/83—Cooling arrangements characterised by passive heat-dissipating elements, e.g. heat-sinks the elements having apertures, ducts or channels, e.g. heat radiation holes

Definitions

  • the invention relates to a searchlight, a pan/tilt assembly and a drone, and belongs to the technical field of manufacturing drones.
  • UAV The drone is abbreviated as "UAV”, abbreviated as “UAV”, which is a non-manned aircraft operated by radio remote control equipment and self-contained program control device, or operated autonomously by the onboard computer completely or intermittently.
  • drones With the development of drone technology, the use of drones is also rapidly expanding, for example, searching for victims in disaster accidents, finding out where the grid is faulty, and tracking target people.
  • the illumination of the surrounding environment is relatively low, such as searching or taking pictures at night or in a tunnel, there is often a situation in which the operator cannot clearly identify the target.
  • some drones have one or more searchlights fixed under the center frame through the brackets, thereby providing an additional light source when the drone is looking for or tracking the target, so that the operator It is possible to see the objects in the visible area illuminated by the searchlight.
  • the embodiments of the present invention provide a searchlight, a pan/tilt assembly, and a drone to solve the above or other potential technical problems existing in the prior art.
  • a searchlight for use in a movable platform, the searchlight is provided with a first light source and a second light source, and the light emitted by the first light source is used to illuminate a target area, The light emitted by the two light sources is used to indicate the position of the target area.
  • the first light source comprises a plurality of light beads, a plurality of the light bead arrays are arranged, and the laser light source is disposed at a center of an array in which the plurality of the light beads are arranged.
  • each of the lamp beads is provided with a reflector.
  • searchlight as described above, wherein the searchlight is further provided with a heat sink, the heat sink being located behind the first light source.
  • searchlight as described above, wherein the searchlight is further provided with a fan, the fan being located behind the heat sink.
  • searchlight as described above, wherein the searchlight further comprises: a first chamber and a second chamber, the first light source and the second light source being mounted in the first chamber, the heat sink and the fan Installed in the second chamber.
  • the heat sink comprises a plurality of heat dissipating fins arranged in parallel, and two ends of the plurality of heat dissipating fins respectively extend to a top opening of the second chamber, the second cavity The bottom of the chamber is open.
  • the second chamber is provided with a plurality of strip-shaped through holes, and a spacer between adjacent two strip-shaped through holes protrudes from an outer surface of the second chamber.
  • searchlight as described above, wherein the searchlight is further provided with a controller, the controller is electrically connected to the first light source and the second light source, the controller is installed in the first chamber, and is located at the Between the first light source and the heat sink.
  • a pan/tilt head assembly comprising: a first head and a searchlight as described above, the searchlight being mounted on the first head.
  • a drone comprising: a center frame and a pan/tilt assembly as described above mounted below the center frame.
  • a second pan/tilt head is mounted below the center frame, and the second pan/tilt head is mounted with an imaging device.
  • the position of the target area illuminated by the first light source is indicated by setting the second light source, so that the operator can observe the illumination area of the first light source by observing the light emitted by the second light source. Accurate adjustments are made to increase the accuracy of the control.
  • FIG. 1 is a schematic structural diagram of a drone according to an embodiment of the present invention.
  • FIG. 2 is a schematic structural diagram of another unmanned aerial vehicle according to an embodiment of the present invention.
  • FIG. 3 is a schematic structural diagram of a cloud platform component according to an embodiment of the present invention.
  • FIG. 4 is a schematic structural view of the pan/tilt assembly of FIG. 3 in another perspective;
  • Figure 5 is a cross-sectional view of the searchlight of Figure 3.
  • first and second are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated.
  • features defining “first” or “second” may include at least one of the features, either explicitly or implicitly.
  • the meaning of "a plurality” is at least two, such as two, three, etc., unless specifically defined otherwise.
  • the terms “installation”, “connected”, “connected”, “fixed” and the like shall be understood broadly, and may be either a fixed connection or a detachable connection, unless explicitly stated and defined otherwise. , or integrated; may be directly connected, or may be indirectly connected through an intermediate medium, may be the internal communication of two elements or the interaction of two elements, unless explicitly defined otherwise.
  • the specific meanings of the above terms in the present invention can be understood on a case-by-case basis.
  • FIG. 1 is a schematic structural view of a drone provided by the embodiment
  • FIG. 2 is a schematic structural view of another drone provided by the embodiment.
  • the drone 1 includes a center frame 11 which is a main body portion of the drone 1.
  • the center frame 11 is provided with a flight control system for controlling the flight state of the drone 1, for example, controlling the drone 1 to ascend, land, turn, and hover.
  • the flight control system can be a microprocessor, a microcontroller or an integrated circuit or the like.
  • the center frame 11 includes a top surface, a bottom surface, and a side surface between the top surface and the bottom surface.
  • a mounting cavity for mounting a battery may be recessed from the bottom surface of the center frame 11, and a battery cover may be detachably disposed at the opening of the mounting cavity.
  • a plurality of arms 12 may be evenly arranged around the center frame 11, and these arms 12 may be symmetrical about the horizontal or vertical axis of the center frame 11.
  • FIG. 1 and FIG. 2 show that four arms 12 are symmetrically disposed about the horizontal axis and the longitudinal axis around the center frame 11, and the arm 12 can be fixedly coupled to the center frame 11 or to the center frame 11.
  • the connection is rotated, or the arm 12 can also be designed to be foldable relative to the center frame 11 to reduce the space occupied by the drone 1 in the stowed state.
  • an end of the arm 12 near the center frame 11 may be inserted from the side of the center frame 11 between the top surface and the bottom surface of the center frame 11 to increase the connection strength between the arm 12 and the center frame 11.
  • the arm 12 can be fabricated into any suitable shape using any material in the prior art, for example, a metal (for example, iron or aluminum) or a non-metal (for example, a polymer plastic) can be used to form a rod-like structure (see FIGS. 1 and 2). ).
  • a metal for example, iron or aluminum
  • a non-metal for example, a polymer plastic
  • the arm 12 can be made into a hollow rod-like structure using a carbon fiber material, or can be formed into a plate-like structure in which a weight reducing hole is opened.
  • One or more power assemblies 13 may be mounted at one end of the arm 12 away from the center frame 11 to provide power to the UAV 1 for ascending, advancing, hovering, and rotating.
  • the power assembly 13 may include a propeller (not shown in FIG. 1), a drive motor that drives the propeller to rotate, and an ESC that controls the operating parameters of the drive motor. It should be understood that when a plurality of power components 13 are disposed on the same arm 12 of the drone 1, the power components 13 may be disposed on the arm 12 at intervals along the extending direction of the arm 12, or may be two The power assembly 13 is disposed at the end of the arm 12 in a vertically symmetrical manner.
  • a plurality of tripods 14 are disposed under the center frame 11 so as to be supported on the ground or other ground fixed crops when the drone 1 is landed, thereby avoiding the main structure of the center frame 11 of the drone 1 and the ground or the ground. Crop contact to protect the drone 1 .
  • the tripod 14 can be made into a hollow rod-like structure using a carbon fiber material to reduce the weight of the drone 1 and improve the dynamic performance of the drone 1; of course, this embodiment does not exclude other lightweight materials.
  • the stand 14 is made of high strength or other materials.
  • pan/tilt head assembly including: a pan/tilt head 15 and a searchlight 16 mounted thereon.
  • the pan/tilt 15 may be any one of a single-axis pan/tilt, a two-axis pan/tilt head, and a three-axis pan/tilt head.
  • the drone 1 provides supplemental illumination to the target in a low illumination environment, thereby enabling the operator to clearly see the searchlight. 16 illuminated areas to quickly find, track targets, etc.
  • pan/tilt assemblies when a plurality of pan/tilt assemblies are disposed under the center frame 11, the pan/tilt assemblies can be spaced apart in a horizontal plane, so that the coverage of the illumination of the searchlights 16 can be improved.
  • the angle between the two pan-tilt assemblies in the horizontal plane may be 180°; if three pan/tilt assemblies are disposed below the center frame 11, this The three pan/tilt assemblies may be at an angle of 120° to each other in the horizontal plane.
  • the imaging device 17 (a visual imaging device including an image capturing device and a camera, and an infrared imaging device) may be mounted under the center frame 11 through another pan/tilt 15 , ultraviolet imaging device, thermal imaging device, etc.) in order to realize the aerial photography function of the drone 1 .
  • the imaging device 17 not only the imaging device 17 but also the searchlight 16 is disposed under the center frame 11 of the drone 1 so that a supplementary light source can be provided for the aerial photography of the drone 1 so that the drone 1 is Under low illumination, the target can be clearly captured, making it easy to search, shoot and track the target remotely.
  • a pan-tilt assembly and a searchlight 16 in the pan-tilt assembly will be described in detail by taking a three-axis pan/tilt and a searchlight 16 mounted on a three-axis pan/tilt as an example.
  • the three-axis pan/tilt means that it can be respectively wound around a first axis (for example, a yaw axis (yaw axis)), a second axis (for example, a roll axis (roll axis)), and a third axis (for example, a pitch axis (pitch axis)).
  • a first axis for example, a yaw axis (yaw axis)
  • a second axis for example, a roll axis (roll axis)
  • a third axis for example, a pitch axis (pitch axis)
  • FIG. 3 is a schematic structural diagram of a pan-tilt assembly according to the embodiment
  • FIG. 4 is a schematic structural view of the pan-tilt assembly of FIG.
  • the searchlight 16 is detachably mounted on a three-axis head.
  • the three-axis pan/tilt includes: a left arm 151, a right arm 152, an upper arm 153, a pitch motor, a roll motor, and a yaw motor.
  • the left arm 151 and the right arm 152 are oppositely disposed, and a pitch motor mount for mounting the pitch motor is formed at the front end of the left arm 151, and the motor shaft of the pitch motor extends toward the right arm, that is, in FIG.
  • the motor shaft of the pitch motor extends to the right; a mounting shaft hole is formed at a front end of the right arm, and a mounting shaft is installed in the mounting shaft hole, and the mounting shaft extends toward the left arm, that is, In Figure 3, the mounting shaft extends to the left, and an end cap may be provided at the right end of the mounting shaft to shield the mounting shaft.
  • the left arm 151 and the right arm 152 are combined to form a mounting space for mounting the searchlight 16, so that the searchlight 16 can be rotated by the motor shaft of the pitch motor, and due to the rotation of the motor shaft on which the shaft assist pitch motor is mounted, The rotation of the searchlight 16 is more stable.
  • the mounting shaft may also be disposed at the front end of the left arm 151, and the pitch motor is disposed at the front end of the right arm 152, respectively.
  • the mounting shaft may not be provided, or further, only the left arm 151 or the right arm 152 for mounting the pitch motor may be provided.
  • the left arm 151 or the right arm 152 may also be located at other positions of the searchlight 16.
  • the bottom end of the upper arm 153 is formed with a rolling motor mount for mounting a rolling motor, and the rear ends of the left arm 151 and the right arm 152 are fixed on the motor shaft of the rolling motor;
  • a yaw motor mount for mounting a yaw motor is formed at the top end of the arm 153.
  • the left arm 151 and the right arm 152 are integrally formed one piece.
  • a quick release joint 18 is further disposed on the top end of the upper arm 153 for fixed connection with the center frame 11.
  • the quick-release joint 18 can be any quick-release structure used in the prior art, especially the quick-release structure used on the drone 1 . For details, refer to the description of the prior art, and details are not described herein again.
  • the pitch motor mount, the tumbling motor mount and the yaw motor mount described above may be separate components attached to the left arm 151, the upper arm 153, or may be left-handed.
  • the structure of the three-axis pan/tilt is described in detail above, as described above, the single-axis pan/tilt or the two-axis pan/tilt can also be used to mount the searchlight 16.
  • the pitch motor, the roll motor, and the yaw motor may be selectively provided with one or more of them.
  • the left arm 151, the right arm 152, and the upper arm 153 may also be adapted.
  • the one piece can be formed by integral molding.
  • the searchlight 16 may be detachably mounted at the bottom end of the upper arm 153.
  • the yaw motor and the tumbling motor are provided, only the upper arm 153 may be provided, or the upper arm 153, the left arm 151, and/or the right arm 152 may be provided.
  • the searchlight 16 includes a housing and a first light source 166 and a second light source 167 disposed on the housing.
  • the light emitted by the first light source 166 is used to illuminate the target area
  • the light emitted by the second light source 167 is used to indicate the position of the target area.
  • the first light source 166 may be a visible light source or an infrared light source
  • the second light source 167 may be a laser light source.
  • an indication can be provided for the target area illuminated by the first light source 166, so that when the searchlight 16 is adjusted, the operator can directly observe the light emitted by the second light source 167.
  • the irradiation direction and the irradiation position of the first light source 166 are determined, and the irradiation position of the searchlight 16 can be accurately adjusted.
  • Figure 5 is a cross-sectional view of the searchlight of Figure 3.
  • the housing may form a first chamber for mounting the first light source 166 and the second light source 167, and a second chamber.
  • the first chamber may be formed as a closed chamber in which the first chamber can be installed and A light source 166 and a second light source 167 are electrically connected to a controller for controlling opening/closing of the first light source 166 and the second light source 167, brightness adjustment, and the like.
  • the housing can be in various forms and configurations.
  • the housing may include a front housing 161, a rear housing 162, and a partition 163, and the front housing 161 and the rear housing 162 are closed to form a receiving space, the partition A 163 is disposed in the accommodating space to divide the accommodating space into a front chamber 164 (that is, a first chamber) and a rear chamber 165 (that is, a second chamber).
  • a first light source 166 and a second light source 167 are mounted in the front chamber 164, and a controller electrically coupled to the first light source 166 and the second light source 167 is mounted in the front chamber 164 to prevent the controller and the electrical connection portion from being exposed.
  • the front case 161 may include a front plate and a front half side wall fixed to the outer edge of the front plate, and the rear case 162 may include a rear plate and a rear side wall fixed to the outer edge of the rear plate; or, the front case
  • the body 161 includes only the front panel, and the rear housing 162 includes a rear panel and side walls (i.e., the front and rear side walls).
  • the embodiment of the present embodiment will be described in detail by taking the housing including the front housing 161, the rear housing 162 and the partition 163 shown in FIGS. 3 to 5 as an example, but the technology in the art It should be understood that the following description should not be taken as a limitation of the invention, and any housing structure capable of forming the first chamber and the second chamber is within the scope of protection of the embodiments of the present invention.
  • the first light source 166 is mounted on the front chamber 164 formed by the front case 161, the rear case 162 and the partition 163, and may include a plurality of lamp beads 1661 arranged in an array, the second light source A 167 (for example, a laser light source) is disposed at the center of the array in which the plurality of lamp beads 1661 are arranged.
  • Figure 3 shows that the first source 166 includes four beads, and the four beades are arranged in a 2 x 2 array with the second source disposed in the center of the 2 x 2 array.
  • the lamp bead 1661 may be an arc lamp, a tungsten halogen lamp, an ultra-high pressure mercury lamp, a metal halide lamp, an ultra-high pressure xenon lamp, or the like.
  • a reflector 1662 is sleeved on the outside of each of the lamp beads 1661.
  • the reflector 1662 may be formed in a tapered shape, and the lamp bead 1661 is disposed at the small diameter end of the tapered reflector 1662 so that the light emitted by the lamp beacon 1661 can be reflected on the inner surface of the tapered reflector 1662.
  • the majority of the light is concentrated and emitted from the large-diameter end of the tapered reflector 1662, thereby increasing the light intensity of the light emitted by the first light source 166, enhancing the sharpness of the target area, and contributing to Target search and tracking, etc.
  • the reflector 1662 can be an orange peel reflector to uniform the intensity of the light.
  • the partition 163 may be a heat sink to improve the heat dissipation effect of the first light source 166 and the second light source.
  • a plurality of louvers are formed in the front chamber 164 and/or the rear chamber 165, that is, a plurality of louvers are formed in the front housing 161 and/or the rear housing 162 so that The heat is dissipated for electronic components such as the first light source 166, the second light source 167, and the controller. In this way, the air in the external environment can enter the accommodating space from some of the vent holes, and then flow out from the other vent holes, thereby bringing the heat of the electronic components to the external environment.
  • the heat dissipation holes when they are provided, they may be disposed at any position.
  • the front chamber 164 may be provided as a closed chamber, and the heat dissipation holes may be opened in the rear chamber 165.
  • openings are formed in the top and bottom of the rear case 162 for use as heat dissipation holes.
  • a heat sink 168 may be disposed behind the first light source 166, that is, behind the partition 163, and the heat sink 168 may be fabricated using any suitable material in the prior art, and its shape and The structure can also be designed as needed, and no specific limitation is imposed here.
  • the heat sink 168 may have a portion that extends to the opening formed in the housing, or a portion that protrudes from the opening formed in the housing to the outside of the housing, that is, a portion of the heat sink 168 protrudes.
  • the opening of the housing row For example, when dustproof and waterproof are considered, the fins 168 may be mounted on the rear case 162 as shown in FIGS.
  • the top and bottom ends of the fins 168 are respectively from the top and bottom of the rear case 162.
  • the opening opened is extended.
  • the heat sink 168 includes a plurality of heat dissipating fins 1681 arranged in parallel, and the top end and the bottom end of the heat dissipating fins 1681 may respectively extend to an opening opened by the housing or protrude through the opening to the outside of the housing.
  • openings are respectively formed at the top end and the bottom end of the rear case 162, and the top ends of the plurality of parallel-arranged heat-dissipating fins 1681 protrude from the top opening 1621, and the heat-dissipating fins 1681
  • the bottom end also extends to be flush with the upper or lower surface of the bottom opening.
  • the bottom end of the heat dissipation fins 1681 can also protrude out of the rear housing 162 through the bottom opening.
  • the heat dissipation area of the heat dissipation fins 168 can be increased, the heat dissipation effect can be improved, and the top and/or bottom ends of the heat dissipation fins 1681 can be enlarged if they protrude from the top opening 1621 or the bottom opening.
  • the contact area of the heat dissipation fins 1681 with the external environment improves heat dissipation efficiency.
  • a fan 169 may be disposed behind the heat sink 168.
  • the first light source 166 and/or the second light source 167 can be disposed on the front housing 161 with the heat sink 168 and the fan 169 mounted on the rear housing 162, as shown in FIGS. 3 and 4.
  • the rear housing 162 includes a rear plate and a side wall, and the fan 169 can be fixed to the inner surface of the rear plate by the bracket.
  • the side of the heat sink 168 adjacent to the rear plate may be provided with an inwardly recessed accommodating space for the fan 169 to be disposed in the accommodating space.
  • the length dimension of the searchlight in the optical axis direction can be reduced.
  • a plurality of strip-shaped through holes 1622 are defined in the rear end surface of the rear housing 162 (for example, the rear plate) for the wind generated by the fan 169 to flow.
  • a spacer 1623 between adjacent two strip-shaped through holes 1622 protrudes from the rear surface of the rear case 162 to reinforce the structure.
  • an opening may be provided at the top and/or bottom of the rear chamber 165 (eg, at the top and/or bottom of the rear housing 162) and at the rear side of the rear chamber 165 (eg, behind the rear housing 162)
  • the plate defines a plurality of strip-shaped through holes.
  • a plurality of strip-shaped through holes may be formed in the top and/or bottom of the rear chamber 165 (eg, the top and/or the bottom of the rear housing 162), and on the rear side of the rear chamber 165 (eg, the rear housing)
  • the rear plate of 162 is provided with a plurality of air inlet holes.
  • the heat of the partition 163 and the heat sink fins can be transferred to the external environment, achieving one of the first light source 166, the second light source 167, and the controller. Or multiple to cool down.
  • searchlight 16 of the present embodiment can also be applied to other movable platforms other than the drone 1, such as a handheld gimbal, a car, a train, a ship or a manned aircraft or a spacecraft, a robot, and the like.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Non-Portable Lighting Devices Or Systems Thereof (AREA)

Abstract

一种探照灯，应用于可移动平台，所述探照灯(16)设置有第一光源(166)和第二光源(167)，所述第一光源(166)发出的光线用于照亮目标区域，所述第二光源(167)发出的光线用于指示所述目标区域的位置。上述探照灯(16)，通过设置第二光源(167)来指示第一光源(166)照亮的目标区域的位置，这样，操作人员就可以通过观察该第二光源(167)所发出的光线对第一光源(166)的照射区域进行精确调整，提高了控制的精准度。本发明实施例还提供一种云台组件和无人机。

Description

探照灯、云台组件和无人机 技术领域
本发明涉及一种探照灯、云台组件和无人机，属于无人机制造技术领域。
背景技术
无人驾驶飞机简称“无人机”，英文缩写为“UAV”，是利用无线电遥控设备和自备的程序控制装置操纵的不载人飞机，或者由车载计算机完全地或间歇地自主地操作。
随着无人机技术的发展，无人机的用途也在快速的扩充，例如，搜救灾害事故中的遇难人员、查找电网出现故障的位置、对目标人物进行跟踪等。但是，如果周围环境的照度比较低，例如在夜晚或者隧道中进行搜寻或者拍照时，往往会出现操作人员无法清楚识别出目标的情况。有鉴于此，在现有技术中，某些无人机通过支架在中心架的下方固定有一个或者多个探照灯，从而在无人机寻找或者跟踪目标的时候提供额外的光源，以使操作人员能够看清楚探照灯照射的可见区域内的物体。
但是，上述无人机在进行控制的时候，操作人员在只能通过调整无人机的姿态才能实现对探照灯光照对探照灯的光照方向很难进行精确控制。
发明内容
本发明实施例提供一种探照灯、云台组件和无人机，以解决现有技术存在的以上或者其他潜在的技术问题。
根据本发明的一些实施例，提供一种探照灯，应用于可移动平台，所述探照灯设置有第一光源和第二光源，所述第一光源发出的光线用于照亮目标区域，所述第二光源发出的光线用于指示所述目标区域的位置。
如上所述的探照灯，其中，所述第一光源为可见光光源或红外光光源，所述第二光源为激光光源。
如上所述的探照灯，其中，所述第一光源包括多个灯珠，多个所述灯珠阵列排布，所述激光光源设置在多个所述灯珠排列成的阵列的中心。
如上所述的探照灯，其中，每个所述灯珠外均套设有反光杯。
如上所述的探照灯，其中，所述探照灯还设置有散热片，所述散热片位于与所述第一光源的后方。
如上所述的探照灯，其中，所述探照灯还设置有风扇，所述风扇位于所述散热片的后方。
如上所述的探照灯，其中，所述探照灯还包括：第一腔室和第二腔室，所述第一光源和第二光源安装在所述第一腔室，所述散热片和所述风扇安装在所述第二腔室。
如上所述的探照灯，其中，所述散热片包括多个平行排列的散热鳍片，多个所述散热鳍片的两端分别延伸至所述第二腔室的顶部开口、所述第二腔室的底部开口。
如上所述的探照灯，其中，多个所述散热鳍片延伸至所述顶部开口的一端凸出所述顶部开口，多个所述散热鳍片延伸至所述底部开口的一端与所述底部开口齐平。
如上所述的探照灯，其中，所述第二腔室设置有多个条形通孔，相邻两个条形通孔之间的隔条凸出于所述第二腔室的外表面。
如上所述的探照灯，其中，所述探照灯还设置有控制器，所述控制器与所述第一光源和第二光源电连接，所述控制器安装在所述第一腔室内，且位于所述第一光源与所述散热片之间。
根据本发明的一些实施例，提供一种云台组件，包括：第一云台以及如上所述的探照灯，所述探照灯搭载在所述第一云台上。
根据本发明的一些实施例，提供一种无人机，包括：中心架以及安装在所述中心架下方的如上所述的云台组件。
如上所述的无人机，其中，所述中心架的下方安装有多个所述云台组件。
如上所述的无人机，其中，所述中心架的下方还安装有第二云台，所述第二云台上搭载有成像装置。
根据本发明实施例的技术方案，通过设置第二光源来指示第一光源照亮的目标区域的位置，这样，操作人员就可以通过观察该第二光源所发出的光线对第一光源的照射区域进行精确调整，提高了控制的精准度。
本发明的附加方面的优点将在下面的描述中部分给出，部分将从下面的描述中变得明显，或通过本发明的实践了解到。
附图说明
通过参照附图的以下详细描述，本发明实施例的上述和其他目的、特征和优点将变得更容易理解。在附图中，将以示例以及非限制性的方式对本发明的多个实施例进行说明，其中：
图1为本发明实施例提供的一种无人机的结构示意图；
图2为本发明实施例提供的另一种无人机的结构示意图；
图3为本发明实施例提供的云台组件的结构示意图；
图4为图3中云台组件在另一个视角下的结构示意图；
图5为图3中探照灯的剖视图。
图中：
1、无人机；            11、中心架；         12、机臂；
13、动力组件；         14、脚架；           15、云台；
151、左支臂；          152、右支臂；        153、上支臂；
16、探照灯；           161、前壳体；        162、后壳体；
1621、顶部开口；       1622、条形通孔；     1623、隔条；
163、隔板；            164、前腔室；        165、后腔室；
166、第一光源；        1661、灯珠；         1662、反光杯；
167、第二光源；        168、散热片；        1681、散热鳍片；
169、风扇；        17、成像装置；       18、快拆接头。
具体实施方式
下面详细描述本发明的实施例，所述实施例的示例在附图中示出，其中自始至终相同或类似的标号表示相同或类似的元件或具有相同或类似功能的元件。下面通过参考附图描述的实施例是示例性的，旨在用于解释本发明，而不能理解为对本发明的限制。
在本发明的描述中，需要理解的是，术语“上”、“下”、“前”、“后”、“左”、“右”、“顶”、“底”、“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。
此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括至少一个该特征。在本发明实施例的描述中，“多个”的含义是至少两个，例如两个，三个等，除非另有明确具体的限定。
在本发明中，除非另有明确的规定和限定，术语“安装”、“相连”、“连接”、“固定”等术语应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或成一体；可以是直接相连，也可以通过中间媒介间接相连，可以是两个元件内部的连通或两个元件的相互作用关系，除非另有明确的限定。对于本领域的普通技术人员而言，可以根据具体情况理解上述术语在本发明中的具体含义。
在本说明书的描述中，参考术语“一个实施例”、“一些实施例”、“示例”、“具体示例”、或“一些示例”等的描述意指结合该实施例或示例描述的具体特征、结构、材料或者特点包含于本发明的至少一个实施例或示例中。在本说明书中，对上述术语的示意性表述不必须针对的是相同的实施例或示例。而且，描述的具体特征、结构、材料或者特点可以在任一个或多个实施例或示例中以合适的方式结合。此外，在不相互矛盾的情况下，本领域 的技术人员可以将本说明书中描述的不同实施例或示例以及不同实施例或示例的特征进行结合和组合。
图1为本实施例提供的无人机的结构示意图；图2为本实施例提供的另一种无人机的结构示意图。如图1和图2所示，无人机1包括中心架11，其为无人机1的主体部分。中心架11设置有飞行控制系统，用于对无人机1的飞行状态进行控制，例如控制无人机1上升、降落、转向、悬停。具体来说，飞行控制系统可以是微处理器、微控制器或者集成电路等。中心架11包括顶面、底面以及位于顶面和底面之间的侧面，顶面、底面和侧面围合成的空间内用于安装上述飞行控制系统以及为无人机1供电的电池等。当然，在另一些实施方式中，也可以由中心架11的底面凹陷形成用于安装电池的安装腔，在该安装腔的开口处可拆卸的设置一个电池盖。
在中心架11的四周可以均匀布置有多个机臂12，这些机臂12可以关于中心架11的横轴或者纵轴对称。例如，图1和图2中示出了在中心架11的四周关于横轴和纵轴对称设置有四个机臂12，机臂12可以固定连接在中心架11上，也可以与中心架11转动连接，或者还可以将机臂12设计成为能够相对于中心架11折叠以减少无人机1在收纳状态时所占用的空间。例如，机臂12靠近中心架11的一端可以从中心架11的侧面插入到中心架11的顶面和底面之间，以提高机臂12和中心架11的连接强度。应当理解，虽然上面描述了机臂12的一端可以从中心架11的侧面插入到中心架11内，但其并不影响机臂12和中心架11之间的固定连接或者转动连接等关系。机臂12可以采用现有技术中的任意材料制作成任意合适的形状，例如可以使用金属(例如铁或者铝)或者非金属(例如高分子塑料)制作成为杆状结构(参阅图1和图2)。当然，为了降低无人机1的重量、提升无人机1的动力性能，机臂12可以使用碳纤维材料制作成中空的杆状结构，或者制作成为开设有减重孔的板状结构。
在机臂12远离中心架11的一端可以安装一个或多个动力组件13，以为无人机1的上升、前进、悬停和转动等提供动力。动力组件13可以包括螺旋桨(图1中未示出)、驱动螺旋桨转动的驱动电机以及控制驱动电机工作参数的电调等。应当理解，当无人机1的同一个机臂12上设置有多个动力组件13时，这些动力组件13可以沿机臂12的延伸方向间隔设置在机臂12上， 也可以是将两个动力组件13按照上下对称式的布置在机臂12的端部。
在中心架11的下方设置有多个脚架14，以便在无人机1着陆时支撑在地面或者其他地面定作物上，从而避免无人机1的中心架11等主体结构与地面或者地面定作物接触，以保护无人机1。一般来讲，脚架14可以使用碳纤维材料制作成为空心的杆状结构，以降低无人机1的重量，提升无人机1的动力性能；当然，本实施例也不排除使用其他重量轻、强度高或者其他材料来制作脚架14。
继续参照图1和图2，在中心架11的下方还设置有一个或者多个云台组件，该云台组件包括：云台15以及搭载在该云台15上的探照灯16。其中，云台15可以是单轴云台、双轴云台和三轴云台中的任意一个。在本实施例中，通过在中心架11下方设置包括有探照灯16的云台组件，使得无人机1在照度较低的环境下为目标提供补充照明，从而使操作者能够清晰的看见被探照灯16照射的区域，从而快速寻找、跟踪目标等。可以理解，当中心架11的下方设置有多个云台组件时，这些云台组件可以在水平面内间隔设置，从而可以提高探照灯16照明的覆盖范围。举例来说，如果在中心架11的下方设置有两个云台组件，这两个云台组件在水平面的夹角可以为180°；如果在中心架11的下方设置有三个云台组件，这三个云台组件在水平面内相互之间的夹角可以为120°。
如图2所示，在一些可选的实施方式中，还可以在中心架11的下方通过另一个云台15搭载成像装置17(包括图像捕捉装置和相机在内的视觉成像装置、红外线成像装置、紫外线成像装置、热成像装置等)，以便实现无人机1的航拍功能。当然，由于在本实施例中，无人机1的中心架11下方不仅设置有成像装置17还设置有探照灯16，从而可以为无人机1的航拍提供补充光源，以使无人机1在低照度环境下能够清晰的拍摄到目标，便于远程对目标进行寻找、拍摄和跟踪等。
在以下的实施例中将以三轴云台以及搭载在三轴云台上的探照灯16为例，对云台组件以及该云台组件中的探照灯16进行详细说明。其中，三轴云台是指可以分别绕第一轴(例如偏航轴(yaw轴))、第二轴(例如横滚轴(roll轴))以及第三轴(例如俯仰轴(pitch轴))旋转。举例来说，当三 轴云台绕偏航轴旋转时，由三轴云台支撑的成像装置17也同步绕偏航轴旋转。
图3为本实施例提供的云台组件的结构示意图；图4为图3中云台组件在另一视角下的结构示意图。如图3和图4所示，探照灯16可拆卸的安装在三轴云台上。
具体的，如图3和图4所示，三轴云台包括：左支臂151、右支臂152、上支臂153、俯仰电机、滚转电机和偏航电机。左支臂151和右支臂152相对设置，在左支臂151的前端形成有用于安装俯仰电机的俯仰电机安装座，且俯仰电机的电机轴往右支臂方向延伸，也即，在图3中该俯仰电机的电机轴往右方延伸；在右支臂的前端形成有安装轴孔，在该安装轴孔内安装有安装轴，且该安装轴往左支臂方向延伸，也即，在图3中该安装轴往左方延伸，在安装轴的右端还可以设置端盖以遮蔽该安装轴。左支臂151和右支臂152围合成用于安装探照灯16的安装空间，从而探照灯16可以在俯仰电机的电机轴的带动下转动，而且由于有安装轴辅助俯仰电机的电机轴的转动，使得探照灯16的转动更加稳定。可选的，在一些实施方式中，安装轴也可以设置在左支臂151的前端，俯仰电机则相应设置在右支臂152的前端。进一步，在另外一些实施方式中，也可以不设置安装轴，或者更进一步的，还可以仅设置用于安装俯仰电机的左支臂151或者右支臂152。当然，当仅设置左支臂151或者右支臂152时，该左支臂151或者右支臂152也可以位于探照灯16的其他位置。
请参照图4，上支臂153的底端形成有用于安装滚转电机的滚转电机安装座，左支臂151和右支臂152的后端固定在滚转电机的电机轴上；上支臂153的顶端形成有用于安装偏航电机的偏航电机安装座。可选的，左支臂151和右支臂152为一体成型的一体件。又可选的，在上支臂153的顶端还设置有快拆接头18，用于与中心架11固定连接。其中，快拆接头18可以是现有技术中使用的任意快拆结构，尤其是使用在无人机1上的快拆结构，具体可以参见现有技术的记载，在此不再赘述。
可以理解的，上文所描述的俯仰电机安装座、滚转电机安装座以及偏航电机安装座可以是附接在左支臂151、上支臂153上的单独部件，也可以是由左支臂151、上支臂153自身所形成的结构。此外，虽然上文详细介绍了 三轴云台的结构，但是正如前文所描述到的也可以使用单轴云台或者两轴云台来搭载探照灯16。具体来说，俯仰电机、滚转电机和偏航电机可以选择设置其中的一个或者多个，为了配合所选择的电机个数，左支臂151、右支臂152和上支臂153也可以适应性的选择一个或者多个，并且当选择多个时，可以通过一体成型的方式形成一体件。例如，当仅设置偏航电机时，可以仅设置上支臂153，并将探照灯16可拆卸的安装在上支臂153的底端。又如，当设置偏航电机和滚转电机时，可以仅设置上支臂153，或者也可以设置上支臂153、左支臂151和/或右支臂152。
继续参阅图3和图4，探照灯16包括：壳体以及设置在壳体上的第一光源166和第二光源167。其中，第一光源166发出的光线用于照亮目标区域，第二光源167发出的光线用于指示该目标区域的位置。其中，第一光源166可以是可见光光源或者红外光光源，第二光源167则可以为激光光源。在本实施例中，通过设置第二光源167，可以为第一光源166所照射的目标区域提供指示，从而在对探照灯16进行调整时，操作人员可以通过直接观察第二光源167所发出的光线来确定第一光源166的照射方向和照射位置，进而能够对探照灯16的照射位置进行精确的调整。
图5为图3中探照灯的剖视图。如图5所示，壳体可以形成用于安装第一光源166和第二光源167的第一腔室，以及第二腔室。一般来说，为了提高防水、防尘等性能，以提高第一光源166和第二光源167的使用寿命，第一腔室可以做成密闭的腔室，在该第一腔室内可以安装与第一光源166和第二光源167电连接的控制器，该控制器用来控制第一光源166和第二光源167的开/闭、亮度调整等。
在本实施例中，壳体可以为各种形式和结构。例如，如图3和图4所示，壳体可以包括前壳体161、后壳体162、以及隔板163，前壳体161和后壳体162盖合在一起形成有容纳空间，隔板163设置在该容纳空间内，以将该容纳空间分隔成前腔室164(也即为第一腔室)和后腔室165(也即为第二腔室)。在前腔室164安装第一光源166和第二光源167，与第一光源166和第二光源167电连接的控制器则安装在前腔室164内，以避免控制器以及电连接部分暴露在外部环境内，从而提高防尘和防水效果。可选的，前壳体161可以包括前板以及固定在前板外边沿的前半侧壁，后壳体162则可以包括后板以 及固定在后板外边缘的后半侧壁；或者，前壳体161仅包括前板，后壳体162则包括后板以及侧壁(也即前半侧壁和后半侧壁)。
在以下实施例中，将以图3至图5中示出的包括有前壳体161、后壳体162和隔板163的壳体为例对本实施例的方案进行详细描述，但本领域技术人员应该理解，以下描述不应视为对本发明的具体限制，任何能够形成第一腔室和第二腔室的壳体结构均属于本发明实施例的保护范围。
第一光源166安装在由前壳体161、后壳体162和隔板163所形成的前腔室164，其可以包括多个灯珠1661，这些灯珠1661呈阵列式排布，第二光源167(例如激光光源)设置在这多个灯珠1661所排列成的阵列的中心。例如，图3中示出了第一光源166包括四个灯珠，且这四个灯珠按照2×2的阵列排列，第二光源设置在该2×2阵列的正中心。在本实施例中，灯珠1661可以是电弧灯、卤钨灯、超高压汞灯、金属卤化物灯和超高压氙灯等。可选的，在每个灯珠1661的外面均套设有反光杯1662。在本实施例中，反光杯1662可以形成为锥形，灯珠1661设置在锥形反光杯1662的小径端，从而灯珠1661发射出的光线可以在锥形反光杯1662的内表面进行反射，使得大部分光线被汇聚在一起后从该锥形反光杯1662的大径端射出，这样也就提高了第一光源166发射出的光线的光强，增强了目标区域的清晰度，有助于目标的寻找和跟踪等。
在一些实施例中，反光杯1662可以为橘皮反光杯，以均匀光斑的光线的强度。
在本实施例中，隔板163可以是散热器，以提高第一光源166和第二光源的散热效果。在一些可选的示例中，在前腔室164和/或后腔室165开设有多个散热孔，也即，在前壳体161和/或后壳体162上开设多个散热孔，以便为第一光源166、第二光源167以及控制器等电子元器件散热。这样，外部环境中的空气可以从其中一些散热孔中进入容纳空间内，再从另外一些散热孔中流出，进而将电子元器件的热量带到外部环境中。具体在设置散热孔时，可以设置在任何位置，当然，为了防尘和防水考虑，可以将前腔室164设置成为密闭的腔室，而将散热孔开设在后腔室165。例如，如图3所示，在后壳体162的顶部和底部均开设有开口，用来作为散热孔。
在另一些可选的示例中，在第一光源166的后方，即隔板163的后方可以设置散热片168，该散热片168可以使用现有技术中任意合适的材料制作而成，其形状和结构也可以根据需要进行设计，在此不作具体的限制。在一些示例中，散热片168可以有部分延伸至壳体上所开设的开口，或者有部分从壳体上所开设的开口伸出到壳体的外面，也即散热片168的部分凸出于壳体行所开设的开口。例如，在考虑防尘和防水时，可以如图3和图4所示的在后壳体162安装散热片168，且该散热片168的顶端和底端分别从后壳体162的顶部和底部所开设的开口伸出。通过设置散热片168，电子元器件所产生的热量可以在散热片168的热传导作用下迅速的传递到外部环境中，从而避免了包括第一光源166在内的电子元器件的温度过高，进而保证了这些电子元器件能够正常的工作。
进一步，散热片168包括有多个平行排列的散热鳍片1681，这些散热鳍片1681的顶端和底端可以分别延伸至壳体所开设的开口，或者穿过该开口伸出到壳体外。例如，图3和图4中示出了在后壳体162的顶端和底端分别开设有开口，多个平行排列的散热鳍片1681的顶端凸出于顶部开口1621，并且这些散热鳍片1681的底端还延伸到与底部开口的上表面或者下表面平齐，当然，散热鳍片1681的底端也可以穿过底部开口伸出到后壳体162外。通过设置多个散热鳍片1681，可以加大散热片168的散热面积，提高散热效果，而且如果散热鳍片1681的顶端和/或底端凸出于顶部开口1621或者底部开口时，可以增大散热鳍片1681与外部环境的接触面积，从而提高散热效率。
进一步，为了提高散热效率，在散热片168的后方还可以设置风扇169。例如，在一些示例中，可以将第一光源166和/或第二光源167设置在前壳体161上，将散热片168和风扇169安装在后壳体162上，如图3和图4所示。以后壳体162包括后板和侧壁为例，风扇169可以通过支架与后板的内表面固定。
更进一步，为了有利于空间集成度的提高以及探照灯的小型化设计，散热片168靠近后板的一侧可以设有向内凹陷的容置空间，以将风扇169设于该容置空间内，从而可以减小探照灯在光轴方向上的长度尺寸。
可选的，在后壳体162的后端面(例如后板)上开设有多个条形通孔1622， 用于供风扇169产生的风流动。相邻两个条形通孔1622之间的隔条1623凸出于后壳体162的后表面，以对结构起加强作用。
举例来说，可以在后腔室165的顶部和/或底部(例如在后壳体162的顶部和/或底部)设置开口，并在后腔室165的后侧(例如后壳体162的后板)开设多个条形通孔，当风扇启动时，外部环境中的空气可以从顶部和/或底部进入后腔室165内，然后从后侧开设的条形通孔流出。或者，也可以在后腔室165的顶部和/或底部(例如后壳体162的顶部和/或底部)开设多个条形通孔，并在后腔室165的后侧(例如后壳体162的后板)开设多个进风孔，当风扇启动时，外部环境中的空气从后腔室165的后侧所开设的进风孔进入后腔室165内，然后从后腔室165的顶部或者底部所开设的条形通孔流出后腔室165。通过使空气在外部环境和后腔室165进行不断的循环，可以将隔板163以及散热鳍片的热量传递到外部环境中，实现对第一光源166、第二光源167以及控制器中的一个或者多个进行降温。
此外，需要说明的是，本实施例的探照灯16还可以应用在除无人机1以外的其他可移动平台上，例如手持云台、汽车、火车、轮船或者载人飞机或者飞船、机器人等。
最后应说明的是：以上实施方式仅用以说明本发明的技术方案，而非对其进行限制；尽管参照前述实施方式对本发明已经进行了详细的说明，但本领域的普通技术人员应当理解：其依然可以对前述实施方式所记载的技术方案进行修改，或者对其中部分或者全部技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明实施方式技术方案的范围。

Claims (35)

  1. 一种探照灯，应用于可移动平台，其特征在于，
    所述探照灯设置有第一光源和第二光源，所述第一光源发出的光线用于照亮目标区域，所述第二光源发出的光线用于指示所述目标区域的位置。
  2. 根据权利要求1所述的探照灯，其特征在于，所述第一光源为可见光光源或红外光光源，所述第二光源为激光光源。
  3. 根据权利要求2所述的探照灯，其特征在于，所述第一光源包括多个灯珠，多个所述灯珠阵列排布，所述激光光源设置在多个所述灯珠排列成的阵列的中心。
  4. 根据权利要求3所述的探照灯，其特征在于，每个所述灯珠外均套设有反光杯。
  5. 根据权利要求1至4中任一项所述的探照灯，其特征在于，所述探照灯还设置有散热片，所述散热片位于所述第一光源的后方。
  6. 根据权利要求5所述的探照灯，其特征在于，所述探照灯还设置有风扇，所述风扇位于所述散热片的后方。
  7. 根据权利要求6所述的探照灯，其特征在于，所述探照灯还包括：第一腔室和第二腔室，所述第一光源和第二光源安装在所述第一腔室，所述散热片和所述风扇安装在所述第二腔室。
  8. 根据权利要求7所述的探照灯，其特征在于，所述散热片包括多个平行排列的散热鳍片，多个所述散热鳍片的两端分别延伸至所述第二腔室的顶部开口、所述第二腔室的底部开口。
  9. 根据权利要求8所述的探照灯，其特征在于，多个所述散热鳍片 延伸至所述顶部开口的一端凸出所述顶部开口，多个所述散热鳍片延伸至所述底部开口的一端与所述底部开口齐平。
  10. 根据权利要求8所述的探照灯，其特征在于，所述第二腔室设置有多个条形通孔，相邻两个条形通孔之间的隔条凸出于所述第二腔室的外表面。
  11. 根据权利要求7所述的探照灯，其特征在于，所述探照灯还设置有控制器，所述控制器与所述第一光源和第二光源电连接，所述控制器安装在所述第一腔室内，且位于所述第一光源与所述散热片之间。
  12. 一种云台组件，其特征在于，包括：第一云台以及探照灯，所述探照灯设置有第一光源和第二光源，所述第一光源发出的光线用于照亮目标区域，所述第二光源发出的光线用于指示所述目标区域的位置，所述探照灯搭载在所述第一云台上。
  13. 根据权利要求12所述的云台组件，其特征在于，所述第一光源为可见光光源或红外光光源，所述第二光源为激光光源。
  14. 根据权利要求13所述的云台组件，其特征在于，所述第一光源包括多个灯珠，多个所述灯珠阵列排布，所述激光光源设置在多个所述灯珠排列成的阵列的中心。
  15. 根据权利要求14所述的云台组件，其特征在于，每个所述灯珠外均套设有反光杯。
  16. 根据权利要求12至15中任一项所述的云台组件，其特征在于，所述探照灯还设置有散热片，所述散热片位于所述第一光源的后方。
  17. 根据权利要求16所述的云台组件，其特征在于，所述探照灯还 设置有风扇，所述风扇位于所述散热片的后方。
  18. 根据权利要求17所述的云台组件，其特征在于，所述探照灯还包括：第一腔室和第二腔室，所述第一光源和第二光源安装在所述第一腔室，所述散热片和所述风扇安装在所述第二腔室。
  19. 根据权利要求18所述的云台组件，其特征在于，所述散热片包括多个平行排列的散热鳍片，多个所述散热鳍片的两端分别延伸至所述第二腔室的顶部开口、所述第二腔室的底部开口。
  20. 根据权利要求19所述的云台组件，其特征在于，多个所述散热鳍片延伸至所述顶部开口的一端凸出所述顶部开口，多个所述散热鳍片延伸至所述底部开口的一端与所述底部开口齐平。
  21. 根据权利要求19所述的云台组件，其特征在于，所述第二腔室设置有多个条形通孔，相邻两个条形通孔之间的隔条凸出于所述第二腔室的外表面。
  22. 根据权利要求19所述的云台组件，其特征在于，所述探照灯还设置有控制器，所述控制器与所述第一光源和第二光源电连接，所述控制器安装在所述第一腔室内，且位于所述第一光源与所述散热片之间。
  23. 一种无人机，其特征在于，包括：中心架以及安装在所述中心架下方的云台组件，所述云台组件包括第一云台以及探照灯，所述探照灯设置有第一光源和第二光源，所述第一光源发出的光线用于照亮目标区域，所述第二光源发出的光线用于指示所述目标区域的位置，所述探照灯搭载在所述第一云台上。
  24. 根据权利要求23所述的无人机，其特征在于，所述第一光源为可见光光源或红外光光源，所述第二光源为激光光源。
  25. 根据权利要求24所述的无人机，其特征在于，所述第一光源包括多个灯珠，多个所述灯珠阵列排布，所述激光光源设置在多个所述灯珠排列成的阵列的中心。
  26. 根据权利要求25所述的无人机，其特征在于，每个所述灯珠外均套设有反光杯。
  27. 根据权利要求23至26中任一项所述的无人机，其特征在于，所述探照灯还设置有散热片，所述散热片位于所述第一光源的后方。
  28. 根据权利要求27所述的无人机，其特征在于，所述探照灯还设置有风扇，所述风扇位于所述散热片的后方。
  29. 根据权利要求28所述的无人机，其特征在于，所述探照灯还包括：第一腔室和第二腔室，所述第一光源和第二光源安装在所述第一腔室，所述散热片和所述风扇安装在所述第二腔室。
  30. 根据权利要求29所述的无人机，其特征在于，所述散热片包括多个平行排列的散热鳍片，多个所述散热鳍片的两端分别延伸至所述第二腔室的顶部开口、所述第二腔室的底部开口。
  31. 根据权利要求30所述的无人机，其特征在于，多个所述散热鳍片延伸至所述顶部开口的一端凸出所述顶部开口，多个所述散热鳍片延伸至所述底部开口的一端与所述底部开口齐平。
  32. 根据权利要求30所述的无人机，其特征在于，所述第二腔室设置有多个条形通孔，相邻两个条形通孔之间的隔条凸出于所述第二腔室的外表面。
  33. 根据权利要求30所述的无人机，其特征在于，所述探照灯还设置有控制器，所述控制器与所述第一光源和第二光源电连接，所述控制器安装在所述第一腔室内，且位于所述第一光源与所述散热片之间。
  34. 根据权利要求23至33中任一项所述的无人机，其特征在于，所述中心架的下方安装有多个所述云台组件。
  35. 根据权利要求34所述的无人机，其特征在于，所述中心架的下方还安装有第二云台，所述第二云台上搭载有成像装置。
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