WO2017070911A1 - 飞行控制装置以及具有该飞行控制装置的无人机 - Google Patents

飞行控制装置以及具有该飞行控制装置的无人机 Download PDF

Info

Publication number
WO2017070911A1
WO2017070911A1 PCT/CN2015/093285 CN2015093285W WO2017070911A1 WO 2017070911 A1 WO2017070911 A1 WO 2017070911A1 CN 2015093285 W CN2015093285 W CN 2015093285W WO 2017070911 A1 WO2017070911 A1 WO 2017070911A1
Authority
WO
WIPO (PCT)
Prior art keywords
cover
cover body
main control
control board
power management
Prior art date
Application number
PCT/CN2015/093285
Other languages
English (en)
French (fr)
Inventor
于云
唐尹
王永根
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 CN201580067012.9A priority Critical patent/CN107000828B/zh
Priority to PCT/CN2015/093285 priority patent/WO2017070911A1/zh
Publication of WO2017070911A1 publication Critical patent/WO2017070911A1/zh
Priority to US15/964,997 priority patent/US11142313B2/en

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K5/00—Casings, cabinets or drawers for electric apparatus
    • H05K5/02—Details
    • H05K5/03—Covers
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K7/00—Constructional details common to different types of electric apparatus
    • H05K7/14—Mounting supporting structure in casing or on frame or rack
    • H05K7/1422—Printed circuit boards receptacles, e.g. stacked structures, electronic circuit modules or box like frames
    • H05K7/1427—Housings
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K7/00—Constructional details common to different types of electric apparatus
    • H05K7/20—Modifications to facilitate cooling, ventilating, or heating
    • H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
    • H05K7/20136—Forced ventilation, e.g. by fans
    • H05K7/20145—Means for directing air flow, e.g. ducts, deflectors, plenum or guides
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K7/00—Constructional details common to different types of electric apparatus
    • H05K7/20—Modifications to facilitate cooling, ventilating, or heating
    • H05K7/20845—Modifications to facilitate cooling, ventilating, or heating for automotive electronic casings
    • H05K7/20863—Forced ventilation, e.g. on heat dissipaters coupled to components
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K7/00—Constructional details common to different types of electric apparatus
    • H05K7/20—Modifications to facilitate cooling, ventilating, or heating
    • H05K7/2089—Modifications to facilitate cooling, ventilating, or heating for power electronics, e.g. for inverters for controlling motor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2201/00—UAVs characterised by their flight controls
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2201/00—UAVs characterised by their flight controls
    • B64U2201/10—UAVs characterised by their flight controls autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K2201/00—Indexing scheme relating to printed circuits covered by H05K1/00
    • H05K2201/10—Details of components or other objects attached to or integrated in a printed circuit board

Definitions

  • the present invention relates to the field of avionics technology, and in particular to a flight control device and a drone having the flight control device.
  • the existing flight controller system generally consists of a discretely installed Inertial Measurement Unit (IMU), a Power Management Unit (PMU), and a main controller, which need to occupy more space in the limited space of the aircraft.
  • the installation area has high requirements on the stability of the CAN (Controller Area Network) interface connection.
  • the structure is redundant and the interface is complicated, which is inconvenient in installation and use. Excessive connection lines can also cause the risk of user error, and the system reliability is low.
  • this discrete system limits the function expansion of the system and cannot meet the requirements of complex application requirements and variable functional requirements.
  • a flight control device comprising:
  • a main control board disposed in the housing and configured to set an electronic component
  • An inertial measurement unit disposed in the housing and electrically connected to the main control board;
  • a power management unit disposed on the housing and electrically connected to the main control board;
  • the main control board, the inertial measurement unit, and the power management unit are fixedly connected to the housing to form a whole.
  • the housing includes a first cover body and a second cover body, the first cover body and the second cover body are disposed opposite to each other, and the first cover body and the second cover body are Disassembling the connection to form a receiving cavity for receiving the main control board and the inertial measurement unit between the first cover and the second cover.
  • first cover body and the second cover body are respectively provided with opposite connecting holes, and the first cover body and the second cover body pass through the connecting member and the opposite connecting hole Fixed together; or
  • the first cover body and the second cover body are connected together by snapping or bonding.
  • the first cover body is provided with a first mounting area, the shape of the first mounting area is matched with the shape of the main control board, and the main control board is fixed to the first installation area in.
  • first cover body is further provided with a second mounting area, the shape of the second mounting area is adapted to the shape of the inertial measurement unit, and the inertial measurement unit is disposed in the second installation In the area.
  • a periphery of the second mounting area protrudes from the first cover body with a stop for limiting the inertial measurement unit to the second mounting area;
  • a receiving groove of the second cover facing the first cover is disposed opposite to the second mounting area, and the receiving slot is configured to form a stop together with the stopper around the second mounting area A receiving cavity for receiving and fixing the inertial measurement unit.
  • the inertial measurement unit is electrically connected to the main control board through a flexible circuit board.
  • a side of the second cover facing away from the first cover body is provided with an accommodating portion for accommodating the power management unit.
  • the electronic component disposed on the main control board includes an electrical connector, and the receiving portion is provided with a through hole facing the electrical connector, and the power management unit faces the side of the receiving portion
  • a socket is provided for mating with the electrical connector, and a socket of the power management unit is electrically connected to the electrical connector through the through hole, thereby electrically connecting the power management unit to the main control board.
  • the opposite ends of the power management unit have a protruding edge extending in the same direction, and the two protruding edges are respectively mounted on opposite sides of the receiving portion, and are detachably connected to the second cover. .
  • the flight control device further includes a shroud provided with a heat dissipation passage, the shroud being disposed opposite to a surface of the housing, and the shroud and the shell Body detachable connection.
  • a surface of the housing is provided with a receiving portion for receiving the power management unit
  • the air guiding cover is provided with a recess opposite to the receiving portion, and the recess on the shroud
  • the accommodating portion of the second cover body forms a receiving cavity for accommodating the power management unit, and the heat dissipation channel is in communication with the accommodating cavity.
  • the shroud is provided with a heat dissipating device for dissipating heat to the power management unit.
  • the heat dissipation device includes an axial flow fan
  • the air flow cover further includes an air inlet, a mounting hole, and an air outlet, wherein the air inlet, the mounting hole, the heat dissipation channel, and the air outlet are sequentially connected, and the installation is performed.
  • the hole is used for mounting the heat dissipating device, and the heat dissipating passage passes through the recess, and the air inlet and the air outlet are respectively disposed at two ends of the heat dissipation channel.
  • the electronic component disposed on the main control board includes at least one function expansion interface, and the first cover body and/or the second cover body is provided with an opening corresponding to the at least one function expansion interface.
  • the function extension interface is exposed.
  • the function expansion interface includes at least one of the following: an SD card slot, a USB interface, and a VGA interface.
  • a drone includes a fuselage and a flight control device mounted on the fuselage.
  • the flight control device includes:
  • a main control board disposed in the housing and configured to set an electronic component
  • An inertial measurement unit disposed in the housing and electrically connected to the main control board;
  • a power management unit disposed on the housing and electrically connected to the main control board;
  • the main control board, the inertial measurement unit, and the power management unit are fixedly connected to the housing to form a whole.
  • the housing includes a first cover body and a second cover body, the first cover body and the second cover body are disposed opposite to each other, and the first cover body and the second cover body are Disassembling the connection to form a receiving cavity for receiving the main control board and the inertial measurement unit between the first cover and the second cover.
  • first cover body and the second cover body are respectively provided with opposite connecting holes, and the first cover body and the second cover body pass through the connecting member and the opposite connecting hole Fixed together; or
  • the first cover body and the second cover body are connected together by snapping or bonding.
  • the first cover body is provided with a first mounting area, the shape of the first mounting area is matched with the shape of the main control board, and the main control board is fixed to the first installation area in.
  • first cover body is further provided with a second mounting area, the shape of the second mounting area is adapted to the shape of the inertial measurement unit, and the inertial measurement unit is disposed in the second installation In the area.
  • a periphery of the second mounting area protrudes from the first cover body with a stop for limiting the inertial measurement unit to the second mounting area;
  • a receiving groove of the second cover facing the first cover is disposed opposite to the second mounting area, and the receiving slot is configured to form a stop together with the stopper around the second mounting area A receiving cavity for receiving and fixing the inertial measurement unit.
  • the inertial measurement unit is electrically connected to the main control board through a flexible circuit board.
  • a side of the second cover facing away from the first cover body is provided with an accommodating portion for accommodating the power management unit.
  • the electronic component disposed on the main control board includes an electrical connector, and the receiving portion is provided with a through hole facing the electrical connector, and the power management unit faces the side of the receiving portion
  • a socket is provided for mating with the electrical connector, and a socket of the power management unit is electrically connected to the electrical connector through the through hole, thereby electrically connecting the power management unit to the main control board.
  • the opposite ends of the power management unit have a protruding edge extending in the same direction, and the two protruding edges are respectively mounted on opposite sides of the receiving portion, and are detachably connected to the second cover. .
  • the flight control device further includes a flow guide cover, the flow guide cover is provided with a heat dissipation channel, the flow guide cover is disposed opposite to a surface of the housing, and the flow guide cover and the shell Body detachable connection.
  • a surface of the housing is provided with a receiving portion for receiving the power management unit
  • the air guiding cover is provided with a recess opposite to the receiving portion, and the recess on the shroud
  • the accommodating portion of the second cover body forms a receiving cavity for accommodating the power management unit, and the heat dissipation channel is in communication with the accommodating cavity.
  • the shroud is provided with a heat dissipating device for dissipating heat to the power management unit.
  • the heat dissipation device includes an axial flow fan
  • the air flow cover further includes an air inlet, a mounting hole, and an air outlet, wherein the air inlet, the mounting hole, the heat dissipation channel, and the air outlet are sequentially connected, and the installation is performed.
  • the hole is used for mounting the heat dissipating device, and the heat dissipating passage passes through the recess, and the air inlet and the air outlet are respectively disposed at two ends of the heat dissipation channel.
  • the electronic component disposed on the main control board includes at least one function expansion interface, and the first cover body and/or the second cover body is provided with an opening corresponding to the at least one function expansion interface.
  • the function extension interface is exposed.
  • the function expansion interface includes at least one of the following: an SD card slot, a USB interface, and a VGA interface.
  • the flight control device of the invention has high integration degree and compact structure, can improve the reliability of the system, and facilitates redundant expansion, and effectively solves the problems of complicated structure of the existing system and difficulty in system expansion.
  • FIG. 1 is an exploded perspective view showing a flight control device according to an embodiment of the present invention.
  • FIG. 2 is a structural exploded view of another perspective of the flight control device of FIG. 1.
  • Figure 3 is a partially exploded view showing the structure of the flight control device of Figure 1.
  • FIG. 4 is another partially exploded view showing the structure of the flight control device of FIG. 1.
  • FIG. 5 is a schematic structural view of a drone according to an embodiment of the present invention.
  • Drone 100 Flight control device 20 case twenty one First cover 211 First installation area 2111 Second installation area 2112 Stoppers 2113 Second cover 212 Storage slot 2121 Containment department 2122 Through hole 2123 Opening 2124 Shroud 213 Concave 2130 Inlet 2131 Mounting holes 2132 Cooling channel 2133 Air outlet 2134 Main control board twenty two Electrical connector 221 Function expansion interface 222 Power management unit twenty three socket 231 Convex edge 232 Inertial measurement unit twenty four Flexible circuit board 25 Connection hole 261, 262, 271, 272, 273, 291, 292 Connector 281,282 body 30
  • FIG. 1 is a structural exploded view of a flight control device 20 according to an embodiment of the present invention.
  • the flight control device 20 includes a housing 21, a main control board 22, a power management unit 23, and an inertial measurement unit 24.
  • the main control board 22 is disposed in the housing 21 and is used for setting electronic components.
  • the power management unit 23 is disposed on the housing 21 and electrically connected to the main control board 22 .
  • the inertia measurement unit 24 is disposed in the housing 21 and electrically connected to the main control board 22 .
  • the main control board 22, the power management unit 23, and the inertial measurement unit 24 are fixedly coupled to the housing 21 to form a single unit.
  • the housing 21 includes a first cover 211 and a second cover 212.
  • the first cover 211 is disposed opposite to the second cover 212, and the first cover
  • the second cover 212 is detachably connected to the first cover 211 and the second cover 212 for receiving the main control board 22 and the inertial measurement unit. 24 cavity.
  • the first cover 211 and the second cover 212 are respectively provided with opposite connecting holes 271 and 291, and the first cover 211 and the first The two covers 212 are fixed together by the cooperation of the connecting members 281 and the opposing connecting holes 271, 291.
  • the connecting holes 271 and 291 are respectively threaded holes, and the connecting member 281 can be a screw.
  • the first cover 211 and the second cover 212 may be coupled together by snapping or bonding.
  • the first cover body 211 is provided with a first mounting area 2111, and the shape of the first mounting area 2111 is matched with the shape of the main control board 22, and the main control board 22 is It is fixed in the first mounting area 2111.
  • the main control board 22 and the first cover body 211 are respectively provided with opposite connecting holes 261 and 272, and the main control board 22 is opposite to the main control board 22 through a connecting member (not shown).
  • the connecting holes 261 and 272 are fixed to the first mounting region 2111 of the first cover 211.
  • the connecting holes 261, 272 can be respectively threaded holes, and the connecting member can be a screw.
  • the first cover 211 is further provided with a second mounting area 2112, and the shape of the second mounting area 2112 is adapted to the shape of the inertial measurement unit 24, and the inertial measurement unit 24 is disposed in the second mounting area 2112.
  • a stop 2113 is protruded from the first cover 211 around the second mounting area 2112, and the stop 2113 is used to limit the inertial measurement unit 24 to the second Installed in area 2112.
  • the inertial measurement unit 24 is electrically connected to the main control board 22 via a flexible circuit board 25.
  • one end of the flexible circuit board 25 is bonded to the inertial measurement unit 24, and the other end is bonded to the main control board 22, and the main control board
  • the printed circuit (not shown) on 22 is electrically connected.
  • a side of the second cover 212 facing the first cover 211 is provided with a receiving slot 2121 opposite to the second mounting area 2112, and the receiving slot 2121 is configured to form a receiving cavity for receiving and fixing the inertial measurement unit 24 together with the stopper 2113 around the second mounting area 2112, so as to facilitate installation and disassembly of the inertial measurement unit 24, and prevent The inertial measurement unit 24 is shaken or detached from the receiving cavity.
  • a side of the second cover 212 facing away from the first cover 211 is further provided with a receiving portion 2122, and the receiving portion 2122 is configured to receive the Power management unit 23 (shown in Figure 3).
  • the electronic component disposed on the main control board 22 includes an electrical connector 221, and the receiving portion 2122 is provided with a through hole 2123 opposite to the electrical connector 221, and the power management unit A socket 231 that cooperates with the electrical connector 221 is disposed on a side of the receiving portion 2122 , and the socket 231 of the power management unit 23 is electrically connected to the electrical connector 221 through the through hole 2123 ( As shown in FIG. 4, the power management unit 23 is electrically connected to the main control board 22.
  • the opposite ends of the power management unit 23 extend in the same direction with a protruding edge 232, and the two protruding edges 232 are respectively mounted on opposite sides of the receiving portion 2122, and are The second cover 212 is detachably connected.
  • the protruding edge 232, the second cover 212, and the first cover 211 are respectively provided with opposite connecting holes 262, 292, and 273, and the power management unit 23 is connected.
  • the member 282 is fixedly coupled to the second cover 212 and the first cover 211 in cooperation with the opposite connection holes 262, 292, 273, thereby preventing the power management unit 23 from being in the housing 21. Shake up and reduce the risk of power outages in independent systems.
  • the connecting holes 262, 292, 273 are respectively threaded holes, and the connecting member 282 can be a screw.
  • fixing the power management unit 23 to the outside of the second cover 212 facilitates heat dissipation of the power management unit 23 and reduces heat.
  • the influence on the performance of the main control board 22 and the inertial measurement unit 24 also facilitates the disassembly and maintenance of the power management unit 23. Further, when the flight control device 20 expands other functional modules and needs to change the specifications of the power management unit 23 accordingly, the replacement of the power management unit 23 can be facilitated.
  • the flight control device 20 may further include a flow guide cover 213, the flow guide cover 213 is disposed opposite to the surface of the housing 21, and the The shroud 213 is detachably coupled to the housing 21.
  • the flow guiding cover 213 is provided with a concave portion 2130 opposite to the receiving portion 2122 on the casing 21, and the concave portion 2130 and the second portion of the flow guiding cover 213 are The receiving portion 2122 of the cover 212 collectively forms a receiving cavity for receiving and fixing the power management unit 23, thereby maintaining the integrity and aesthetic appearance of the flight control device 20.
  • the airflow cover 213 is further provided with a heat dissipation device for dissipating heat to the power management unit 23.
  • the heat dissipation device is an axial flow fan
  • the air flow cover 213 is provided with an air inlet 2131, a mounting hole 2132, a heat dissipation channel 2133, and an air outlet 2134.
  • the air inlet 2131, the mounting hole 2132, the heat dissipation channel 2133, and the air outlet 2134 are sequentially connected.
  • the mounting hole 2132 is used to install the heat dissipation device, and the heat dissipation channel 2133 passes through the recess 2130 and the capacitor.
  • the air inlet 2131 and the air outlet 2134 are respectively disposed at two ends of the heat dissipation channel 2133.
  • the shroud 213 can also serve as a carrier for other extended hardware. Providing other expansion hardware on the shroud 213 facilitates the miniaturization of the flight control device 20 and enables The flight control device 20 is compact in structure. It can be understood that in other embodiments, the shroud 213 can be omitted.
  • the electronic component disposed on the main control board 22 includes at least one function expansion interface 222, and the first cover body 211 and/or the second cover body 212 correspond to the at least one function.
  • An opening 2124 is provided at the expansion interface 222 to expose the function expansion interface 222.
  • the function expansion interface 222 includes at least one of the following: an SD card slot, a USB interface, and a VGA interface.
  • the flight control device 20 of the present invention is integrally formed by fixedly connecting the main control board 22, the power management unit 23, and the inertial measurement unit 24 with the housing 21, and optimizes the flight control device on the one hand.
  • the appearance of the aircraft 20 makes the flight control device 20 compact to effectively reduce the volume of the flight control device 20, so that the flight control device 20 has a wider application range and enriches the system redundancy expansion interface, which is convenient and redundant.
  • it also reduces the installation and debugging between functional modules, and reduces the risk of disconnection or error, and improves the stability and reliability of the system.
  • the degree of identification can be improved, that is, the independent system and the redundant system are more clearly distinguished.
  • the flight control device 20 can be applied to a drone 100.
  • the drone 100 may further include a body 30, wherein the flight control device 20 may be mounted on the body 30.

Abstract

一种飞行控制装置（20），包括壳体（21）、主控板（22）以及电源管理单元（23）。主控板（22）设于壳体（21）中，并用于设置电子元器件。电源管理单元（23）设于壳体（21）上，并与主控板（22）电连接。惯性测量单元（24）设于壳体（21）中，并与主控板（22）电连接。主控板（22）、惯性测量单元（24）以及电源管理单元（23）与壳体固定连接形成一个整体。本发明还涉及一种具有飞行控制装置（20）的无人机。

Description

飞行控制装置以及具有该飞行控制装置的无人机 技术领域
本发明涉及航空电子技术领域，特别涉及一种飞行控制装置以及具有该飞行控制装置的无人机。
背景技术
现有飞行控制器系统一般由分立安装的惯性测量单元（Inertial measurement unit，简称IMU）、电源管理单元（Power Management Unit，简称PMU）和主控制器组成，需要在飞行器有限的空间上占据较多的安装面积，对产品CAN（Controller Area Network，控制器局域网总线）口连接稳定性要求也高，同时这种组成结构冗余、接口复杂，在安装以及使用中都很不方便，各功能模块之间过多的连接线路也易造成用户接错的风险，且系统可靠性较低。此外，由于冗余系统接口有限，这种分立式系统限制了系统的功能扩展，不能适应应用场合复杂、功能需求多变的要求。
发明内容
有鉴于此，有必要提出一种飞行控制装置以及具有所述飞行控制装置的无人机，以解决上述问题。
一种飞行控制装置，包括：
壳体；
主控板，设于所述壳体中，并用于设置电子元器件；
惯性测量单元，设于所述壳体中，并与所述主控板电连接；以及
电源管理单元，设于所述壳体上，并与所述主控板电连接；
其中，所述主控板、所述惯性测量单元以及所述电源管理单元与所述壳体固定连接形成一个整体。
进一步地，所述壳体包括第一盖体以及第二盖体，所述第一盖体与所述第二盖体对合设置，并且所述第一盖体与所述第二盖体可拆卸连接，以在所述第一盖体与所述第二盖体之间形成一个用于容置所述主控板以及所述惯性测量单元的容置腔。
进一步地，所述第一盖体以及所述第二盖体上分别设有相对的连接孔，所述第一盖体和所述第二盖体之间通过连接件与所述相对的连接孔的配合而固定在一起；或者
所述第一盖体与所述第二盖体之间通过卡接或者粘接的方式连接在一起。
进一步地，所述第一盖体上设置有第一安装区域，所述第一安装区域的形状与所述主控板的形状相适配，所述主控板固定于所述第一安装区域中。
进一步地，所述第一盖体上还设置有第二安装区域，所述第二安装区域的形状与所述惯性测量单元的形状相适配，所述惯性测量单元设置于所述第二安装区域中。
进一步地，所述第二安装区域的周围自所述第一盖体凸设有挡块，所述挡块用于将所述惯性测量单元限位于所述第二安装区域中；
所述第二盖体面向所述第一盖体的一侧设置有与所述第二安装区域相对的收容槽，所述收容槽用于与所述第二安装区域周围的挡块一起形成一个用于收容并固定所述惯性测量单元的收容腔。
进一步地，所述惯性测量单元通过柔性电路板与所述主控板电连接。
进一步地，所述第二盖体背向所述第一盖体的一侧设置有收容部，所述收容部用于收容所述电源管理单元。
进一步地，所述主控板上设置的电子元器件包括电连接器，所述收容部上设有正对所述电连接器的通孔，所述电源管理单元面向所述收容部的一侧设有与所述电连接器相配合的插口，所述电源管理单元的插口通过所述通孔与所述电连接器电连接，从而使所述电源管理单元与所述主控板电连接。
进一步地，所述电源管理单元的相对两端向同侧方向延伸有凸沿，两个所述凸沿分别安装于所述收容部的相对两侧，并与所述第二盖体可拆卸连接。
进一步地，所述飞行控制装置还包括导流罩，所述导流罩设有散热通道，所述导流罩与所述壳体的表面对合设置，并且所述导流罩与所述壳体可拆卸连接。
进一步地，所述壳体的表面设有用于收容所述电源管理单元的收容部，所述导流罩上设有与所述收容部相对的凹部，并且所述导流罩上的所述凹部与所述第二盖体的收容部共同形成一个用于容置所述电源管理单元的容置腔，并且所述散热通道与所述容置腔连通。
进一步地，所述导流罩上设有散热装置，用于给所述电源管理单元散热。
进一步地，所述散热装置包括为轴流风扇，所述导流罩还设有进风口、安装孔、以及出风口，所述进风口、安装孔、散热通道以及出风口依次相通，所述安装孔用于安装所述散热装置，所述散热通道经过所述凹部，所述进风口与所述出风口分别设于所述散热通道的两端。
进一步地，所述主控板上设置的电子元器件包括至少一个功能扩展接口，所述第一盖体及/或所述第二盖体对应于所述至少一个功能扩展接口处设有开口，使所述功能扩展接口外露。
进一步地，所述功能扩展接口包括如下至少一种：SD卡槽、USB接口、VGA接口。
一种无人机，包括机身以及安装于所述机身上的飞行控制装置。所述飞行控制装置包括：
壳体；
主控板，设于所述壳体中，并用于设置电子元器件；
惯性测量单元，设于所述壳体中，并与所述主控板电连接；以及
电源管理单元，设于所述壳体上，并与所述主控板电连接；
其中，所述主控板、所述惯性测量单元以及所述电源管理单元与所述壳体固定连接形成一个整体。
进一步地，所述壳体包括第一盖体以及第二盖体，所述第一盖体与所述第二盖体对合设置，并且所述第一盖体与所述第二盖体可拆卸连接，以在所述第一盖体与所述第二盖体之间形成一个用于容置所述主控板以及所述惯性测量单元的容置腔。
进一步地，所述第一盖体以及所述第二盖体上分别设有相对的连接孔，所述第一盖体和所述第二盖体之间通过连接件与所述相对的连接孔的配合而固定在一起；或者
所述第一盖体与所述第二盖体之间通过卡接或者粘接的方式连接在一起。
进一步地，所述第一盖体上设置有第一安装区域，所述第一安装区域的形状与所述主控板的形状相适配，所述主控板固定于所述第一安装区域中。
进一步地，所述第一盖体上还设置有第二安装区域，所述第二安装区域的形状与所述惯性测量单元的形状相适配，所述惯性测量单元设置于所述第二安装区域中。
进一步地，所述第二安装区域的周围自所述第一盖体凸设有挡块，所述挡块用于将所述惯性测量单元限位于所述第二安装区域中；
所述第二盖体面向所述第一盖体的一侧设置有与所述第二安装区域相对的收容槽，所述收容槽用于与所述第二安装区域周围的挡块一起形成一个用于收容并固定所述惯性测量单元的收容腔。
进一步地，所述惯性测量单元通过柔性电路板与所述主控板电连接。
进一步地，所述第二盖体背向所述第一盖体的一侧设置有收容部，所述收容部用于收容所述电源管理单元。
进一步地，所述主控板上设置的电子元器件包括电连接器，所述收容部上设有正对所述电连接器的通孔，所述电源管理单元面向所述收容部的一侧设有与所述电连接器相配合的插口，所述电源管理单元的插口通过所述通孔与所述电连接器电连接，从而使所述电源管理单元与所述主控板电连接。
进一步地，所述电源管理单元的相对两端向同侧方向延伸有凸沿，两个所述凸沿分别安装于所述收容部的相对两侧，并与所述第二盖体可拆卸连接。
进一步地，所述飞行控制装还包括导流罩，所述导流罩设有散热通道，所述导流罩与所述壳体的表面对合设置，并且所述导流罩与所述壳体可拆卸连接。
进一步地，所述壳体的表面设有用于收容所述电源管理单元的收容部，所述导流罩上设有与所述收容部相对的凹部，并且所述导流罩上的所述凹部与所述第二盖体的收容部共同形成一个用于容置所述电源管理单元的容置腔，并且所述散热通道与所述容置腔连通。
进一步地，所述导流罩上设有散热装置，用于给所述电源管理单元散热。
进一步地，所述散热装置包括为轴流风扇，所述导流罩还设有进风口、安装孔、以及出风口，所述进风口、安装孔、散热通道以及出风口依次相通，所述安装孔用于安装所述散热装置，所述散热通道经过所述凹部，所述进风口与所述出风口分别设于所述散热通道的两端。
进一步地，所述主控板上设置的电子元器件包括至少一个功能扩展接口，所述第一盖体及/或所述第二盖体对应于所述至少一个功能扩展接口处设有开口，使所述功能扩展接口外露。
进一步地，所述功能扩展接口包括如下至少一种：SD卡槽、USB接口、VGA接口。
本发明的飞行控制装置集成度高，结构紧凑，可提高系统的可靠性，并方便冗余拓展，有效地解决了现有系统结构复杂、系统扩展困难等问题。
 附图说明
图1是本发明一实施例的一种飞行控制装置的结构分解图。
图2是图1的飞行控制装置的另一视角的结构分解图。
图3是图1的飞行控制装置的结构的部分分解图。
图4是图1的飞行控制装置的结构另一种部分分解图。
图5是本发明一实施例的一种无人机的结构示意图。
主要元件符号说明
无人机 100
飞行控制装置 20
壳体 21
第一盖体 211
第一安装区域 2111
第二安装区域 2112
挡块 2113
第二盖体 212
收容槽 2121
收容部 2122
通孔 2123
开口 2124
导流罩 213
凹部 2130
进风口 2131
安装孔 2132
散热通道 2133
出风口 2134
主控板 22
电连接器 221
功能扩展接口 222
电源管理单元 23
插口 231
凸沿 232
惯性测量单元 24
柔性电路板 25
连接孔 261、262、271、272、273、291、292
连接件 281、282
机身 30
如下具体实施方式将结合上述附图进一步说明本发明。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
请参阅图1，为本发明一实施例的一种飞行控制装置20的结构分解图。所述飞行控制装置20包括壳体21、主控板22、电源管理单元23以及惯性测量单元24。其中，所述主控板22设于所述壳体21中，并用于设置电子元器件。所述电源管理单元23设于所述壳体21上，并与所述主控板22电连接。所述惯性测量单元24设于所述壳体21中，并与所述主控板22电连接。在本实施方式中，所述主控板22、所述电源管理单元23以及所述惯性测量单元24与所述壳体21固定连接形成一个整体。
在本实施方式中，所述壳体21包括第一盖体211以及第二盖体212，所述第一盖体211与所述第二盖体212对合设置，并且所述第一盖体211与所述第二盖体212可拆卸连接，以在所述第一盖体211与所述第二盖体212之间形成一个用于容置所述主控板22以及所述惯性测量单元24的容置腔。
请同时参阅图2，在本实施方式中，所述第一盖体211以及所述第二盖体212上分别设有相对的连接孔271、291，所述第一盖体211和所述第二盖体212之间通过连接件281与所述相对的连接孔271、291的配合而固定在一起。其中，所述连接孔271、291可分别为螺纹孔，所述连接件281可为螺钉。在其他实施方式中，所述第一盖体211与所述第二盖体212之间可通过卡接或者粘接的方式连接在一起。
在本实施方式中，所述第一盖体211上设置有第一安装区域2111，所述第一安装区域2111的形状与所述主控板22的形状相适配，所述主控板22固定于所述第一安装区域2111中。在本实施方式中，所述主控板22与所述第一盖体211上分别设有相对的连接孔261、272，所述主控板22通过连接件（图未示）与所述相对的连接孔261、272的配合而固定于所述第一盖体211的第一安装区域2111中。其中，所述连接孔261、272可分别为螺纹孔，所述连接件可为螺钉。
在本实施方式中，所述第一盖体211上还设置有第二安装区域2112，所述第二安装区域2112的形状与所述惯性测量单元24的形状相适配，所述惯性测量单元24设置于所述第二安装区域2112中。在本实施方式中，所述第二安装区域2112的周围自所述第一盖体211凸设有挡块2113，所述挡块2113用于将所述惯性测量单元24限位于所述第二安装区域2112中。
在本实施方式中，所述惯性测量单元24通过柔性电路板25与所述主控板22电连接。在本实施方式中，如图3所示，所述柔性电路板25一端粘接于所述惯性测量单元24上，另一端粘接于所述主控板22上，并与所述主控板22上的印刷电路（图未示）电连接。
在本实施方式中，如图2所示，所述第二盖体212面向所述第一盖体211的一侧设置有与所述第二安装区域2112相对的收容槽2121，所述收容槽2121用于与所述第二安装区域2112周围的挡块2113一起形成一个用于收容并固定所述惯性测量单元24的收容腔，以便于所述惯性测量单元24的安装与拆卸，并防止所述惯性测量单元24在所述收容腔中晃动或从所述收容腔中脱落。
请再次参阅图1-2，在本实施方式中，所述第二盖体212背向所述第一盖体211的一侧还设置有收容部2122，所述收容部2122用于收容所述电源管理单元23（如图3所示）。
在本实施方式中，所述主控板22上设置的电子元器件包括电连接器221，所述收容部2122上设有正对所述电连接器221的通孔2123，所述电源管理单元23面向所述收容部2122的一侧设有与所述电连接器221相配合的插口231，所述电源管理单元23的插口231通过所述通孔2123与所述电连接器221电连接（如图4所示），从而使所述电源管理单元23与所述主控板22电连接。
在本实施方式中，所述电源管理单元23的相对两端向同侧方向延伸有凸沿232，两个所述凸沿232分别安装于所述收容部2122的相对两侧，并与所述第二盖体212可拆卸连接。在本实施方式中，所述凸沿232、所述第二盖体212、以及所述第一盖体211上分别设有相对的连接孔262、292、273，所述电源管理单元23通过连接件282与所述相对的连接孔262、292、273的配合而与所述第二盖体212以及所述第一盖体211固定连接，从而避免所述电源管理单元23在所述壳体21上晃动，并减小独立系统断电的风险。其中，所述连接孔262、292、273可分别为螺纹孔，所述连接件282可为螺钉。
由于所述电源管理单元23在工作过程中会产生较大的热量，将所述电源管理单元23固定在所述第二盖体212的外侧有利于所述电源管理单元23的散热，并减少热量对所述主控板22以及所述惯性测量单元24的性能的影响，同时也便于所述电源管理单元23的拆卸维修。此外，当在所述飞行控制装置20扩展其他功能模块而需要对所述电源管理单元23的规格作相应改变时，可便于所述电源管理单元23的更换。
请再次参阅图1-2，在本实施方式中，所述的飞行控制装置20还可包括导流罩213，所述导流罩213与所述壳体21的表面对合设置，并且所述导流罩213与所述壳体21可拆卸连接。在本实施方式中，所述导流罩213上设有与所述壳体21上的所述收容部2122相对的凹部2130，并且所述导流罩213的所述凹部2130与所述第二盖体212的收容部2122共同形成一个用于容置并固定所述电源管理单元23的容置腔，从而保持所述飞行控制装置20的外形完整和美观。
为利于所述电源管理单元23的散热，所述导流罩213上还设有散热装置，用于给所述电源管理单元23散热。在本实施方式中，所述散热装置为轴流风扇，所述导流罩213设有进风口2131、安装孔2132、散热通道2133以及出风口2134。其中，所述进风口2131、安装孔2132、散热通道2133以及出风口2134依次相通，所述安装孔2132用于安装所述散热装置，所述散热通道2133经过所述凹部2130并与所述容置腔连通，所述进风口2131与所述出风口2134分别设于所述散热通道2133的两端。
在其他实施方式中，所述导流罩213还可作为其他扩展硬件的载体，将其他扩展硬件设于所述导流罩213上有利于所述飞行控制装置20的小型化设计，并使所述飞行控制装置20结构紧凑。可以理解的是，在其他实施方式中，所述导流罩213可以省略。
在本实施方式中，所述主控板22上设置的电子元器件包括至少一个功能扩展接口222，所述第一盖体211及/或所述第二盖体212对应于所述至少一个功能扩展接口222处设有开口2124，使所述功能扩展接口222外露。在本实施方式中，所述功能扩展接口222包括如下至少一种：SD卡槽、USB接口、VGA接口。
本发明的飞行控制装置20通过将所述主控板22、所述电源管理单元23以及所述惯性测量单元24与所述壳体21固定连接形成一个整体，一方面优化了所述飞行控制装置20的外观，使所述飞行控制装置20结构紧凑以有效地减小所述飞行控制装置20体积，使得所述飞行控制装置20的应用范围更广泛，并丰富系统冗余拓展的接口，方便冗余拓展；另一方面也减少了各功能模块之间的安装与调试，并降低断开或接错的风险，提高了系统的稳定性与可靠性。此外还能提高辨识度，即较为明显的区分了独立系统和冗余系统。
在本实施方式中，所述飞行控制装置20可应用于一种无人机100中。如图5所示，所述无人机100还可包括机身30，其中，所述飞行控制装置20可安装于所述机身30上。
最后应说明的是，以上实施例仅用以说明本发明的技术方案而非限制，尽管参照较佳实施例对本发明进行了详细说明，本领域的普通技术人员应当理解，可以对本发明的技术方案进行修改或等同替换，而不脱离本发明技术方案的精神和范围。

Claims (32)

  1. 一种飞行控制装置，包括：
    壳体；
    主控板，设于所述壳体中，并用于设置电子元器件；
    惯性测量单元，设于所述壳体中，并与所述主控板电连接；以及
    电源管理单元，设于所述壳体上，并与所述主控板电连接；
    其中，所述主控板、所述惯性测量单元以及所述电源管理单元与所述壳体固定连接形成一个整体。
  2. 如权利要求1所述的飞行控制装置，其特征在于，所述壳体包括第一盖体以及第二盖体，所述第一盖体与所述第二盖体对合设置，并且所述第一盖体与所述第二盖体可拆卸连接，以在所述第一盖体与所述第二盖体之间形成一个用于容置所述主控板以及所述惯性测量单元的容置腔。
  3. 如权利要求2所述的飞行控制装置，其特征在于，所述第一盖体以及所述第二盖体上分别设有相对的连接孔，所述第一盖体和所述第二盖体之间通过连接件与所述相对的连接孔的配合而固定在一起；或者
    所述第一盖体与所述第二盖体之间通过卡接或者粘接的方式连接在一起。
  4. 如权利要求2所述的飞行控制装置，其特征在于，所述第一盖体上设置有第一安装区域，所述第一安装区域的形状与所述主控板的形状相适配，所述主控板固定于所述第一安装区域中。
  5. 如权利要求4所述的飞行控制装置，其特征在于，所述第一盖体上还设置有第二安装区域，所述第二安装区域的形状与所述惯性测量单元的形状相适配，所述惯性测量单元设置于所述第二安装区域中。
  6. 如权利要求5所述的飞行控制装置，其特征在于，所述第二安装区域的周围自所述第一盖体凸设有挡块，所述挡块用于将所述惯性测量单元限位于所述第二安装区域中；
    所述第二盖体面向所述第一盖体的一侧设置有与所述第二安装区域相对的收容槽，所述收容槽用于与所述第二安装区域周围的挡块一起形成一个用于收容并固定所述惯性测量单元的收容腔。
  7. 如权利要求5所述的飞行控制装置，其特征在于，所述惯性测量单元通过柔性电路板与所述主控板电连接。
  8. 如权利要求2所述的飞行控制装置，其特征在于，所述第二盖体背向所述第一盖体的一侧设置有收容部，所述收容部用于收容所述电源管理单元。
  9. 如权利要求8所述的飞行控制装置，其特征在于，所述主控板上设置的电子元器件包括电连接器，所述收容部上设有正对所述电连接器的通孔，所述电源管理单元面向所述收容部的一侧设有与所述电连接器相配合的插口，所述电源管理单元的插口通过所述通孔与所述电连接器电连接，从而使所述电源管理单元与所述主控板电连接。
  10. 如权利要求8所述的飞行控制装置，其特征在于，所述电源管理单元的相对两端向同侧方向延伸有凸沿，两个所述凸沿分别安装于所述收容部的相对两侧，并与所述第二盖体可拆卸连接。
  11. 如权利要求1所述的飞行控制装置，其特征在于，还包括导流罩，所述导流罩设有散热通道，所述导流罩与所述壳体的表面对合设置，并且所述导流罩与所述壳体可拆卸连接。
  12. 如权利要求11所述的飞行控制装置，其特征在于，所述壳体的表面设有用于收容所述电源管理单元的收容部，所述导流罩上设有与所述收容部相对的凹部，并且所述导流罩上的所述凹部与所述第二盖体的收容部共同形成一个用于容置所述电源管理单元的容置腔，并且所述散热通道与所述容置腔连通。
  13. 如权利要求12所述的飞行控制装置，其特征在于，所述导流罩上设有散热装置，用于给所述电源管理单元散热。
  14. 如权利要求13所述的飞行控制装置，其特征在于，所述散热装置包括为轴流风扇，所述导流罩还设有进风口、安装孔、以及出风口，所述进风口、安装孔、散热通道以及出风口依次相通，所述安装孔用于安装所述散热装置，所述散热通道经过所述凹部，所述进风口与所述出风口分别设于所述散热通道的两端。
  15. 如权利要求1所述的飞行控制装置，其特征在于，所述主控板上设置的电子元器件包括至少一个功能扩展接口，所述第一盖体及/或所述第二盖体对应于所述至少一个功能扩展接口处设有开口，使所述功能扩展接口外露。
  16. 如权利要求15所述的飞行控制装置，其特征在于，所述功能扩展接口包括如下至少一种：SD卡槽、USB接口、VGA接口。
  17. 一种无人机，包括：
    机身；以及
    飞行控制装置，安装于所述机身上，所述飞行控制装置包括：
    壳体；
    主控板，设于所述壳体中，并用于设置电子元器件；
    惯性测量单元，设于所述壳体中，并与所述主控板电连接；以及
    电源管理单元，设于所述壳体上，并与所述主控板电连接；
    其中，所述主控板、所述惯性测量单元以及所述电源管理单元与所述壳体固定连接形成一个整体。
  18. 如权利要求17所述的无人机，其特征在于，所述壳体包括第一盖体以及第二盖体，所述第一盖体与所述第二盖体对合设置，并且所述第一盖体与所述第二盖体可拆卸连接，以在所述第一盖体与所述第二盖体之间形成一个用于容置所述主控板以及所述惯性测量单元的容置腔。
  19. 如权利要求18所述的无人机，其特征在于，所述第一盖体以及所述第二盖体上分别设有相对的连接孔，所述第一盖体和所述第二盖体之间通过连接件与所述相对的连接孔的配合而固定在一起；或者
    所述第一盖体与所述第二盖体之间通过卡接或者粘接的方式连接在一起。
  20. 如权利要求18所述的无人机，其特征在于，所述第一盖体上设置有第一安装区域，所述第一安装区域的形状与所述主控板的形状相适配，所述主控板固定于所述第一安装区域中。
  21. 如权利要求20所述的无人机，其特征在于，所述第一盖体上还设置有第二安装区域，所述第二安装区域的形状与所述惯性测量单元的形状相适配，所述惯性测量单元设置于所述第二安装区域中。
  22. 如权利要求21所述的无人机，其特征在于，所述第二安装区域的周围自所述第一盖体凸设有挡块，所述挡块用于将所述惯性测量单元限位于所述第二安装区域中；
    所述第二盖体面向所述第一盖体的一侧设置有与所述第二安装区域相对的收容槽，所述收容槽用于与所述第二安装区域周围的挡块一起形成一个用于收容并固定所述惯性测量单元的收容腔。
  23. 如权利要求21所述的无人机，其特征在于，所述惯性测量单元通过柔性电路板与所述主控板电连接。
  24. 如权利要求18所述的无人机，其特征在于，所述第二盖体背向所述第一盖体的一侧设置有收容部，所述收容部用于收容所述电源管理单元。
  25. 如权利要求24所述的无人机，其特征在于，所述主控板上设置的电子元器件包括电连接器，所述收容部上设有正对所述电连接器的通孔，所述电源管理单元面向所述收容部的一侧设有与所述电连接器相配合的插口，所述电源管理单元的插口通过所述通孔与所述电连接器电连接，从而使所述电源管理单元与所述主控板电连接。
  26. 如权利要求24所述的无人机，其特征在于，所述电源管理单元的相对两端向同侧方向延伸有凸沿，两个所述凸沿分别安装于所述收容部的相对两侧，并与所述第二盖体可拆卸连接。
  27. 如权利要求17所述的无人机，其特征在于，所述飞行控制装还包括导流罩，所述导流罩设有散热通道，所述导流罩与所述壳体的表面对合设置，并且所述导流罩与所述壳体可拆卸连接。
  28. 如权利要求27所述的无人机，其特征在于，所述壳体的表面设有用于收容所述电源管理单元的收容部，所述导流罩上设有与所述收容部相对的凹部，并且所述导流罩上的所述凹部与所述第二盖体的收容部共同形成一个用于容置所述电源管理单元的容置腔，并且所述散热通道与所述容置腔连通。
  29. 如权利要求28所述的无人机，其特征在于，所述导流罩上设有散热装置，用于给所述电源管理单元散热。
  30. 如权利要求29所述的无人机，其特征在于，所述散热装置包括为轴流风扇，所述导流罩还设有进风口、安装孔、以及出风口，所述进风口、安装孔、散热通道以及出风口依次相通，所述安装孔用于安装所述散热装置，所述散热通道经过所述凹部，所述进风口与所述出风口分别设于所述散热通道的两端。
  31. 如权利要求17所述的无人机，其特征在于，所述主控板上设置的电子元器件包括至少一个功能扩展接口，所述第一盖体及/或所述第二盖体对应于所述至少一个功能扩展接口处设有开口，使所述功能扩展接口外露。
  32. 如权利要求31所述的无人机，其特征在于，所述功能扩展接口包括如下至少一种：SD卡槽、USB接口、VGA接口。
PCT/CN2015/093285 2015-10-30 2015-10-30 飞行控制装置以及具有该飞行控制装置的无人机 WO2017070911A1 (zh)

Priority Applications (3)

Application Number Priority Date Filing Date Title
CN201580067012.9A CN107000828B (zh) 2015-10-30 2015-10-30 飞行控制装置以及具有该飞行控制装置的无人机
PCT/CN2015/093285 WO2017070911A1 (zh) 2015-10-30 2015-10-30 飞行控制装置以及具有该飞行控制装置的无人机
US15/964,997 US11142313B2 (en) 2015-10-30 2018-04-27 Flight control device and unmanned aerial vehicle having the same

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CN2015/093285 WO2017070911A1 (zh) 2015-10-30 2015-10-30 飞行控制装置以及具有该飞行控制装置的无人机

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US15/964,997 Continuation US11142313B2 (en) 2015-10-30 2018-04-27 Flight control device and unmanned aerial vehicle having the same

Publications (1)

Publication Number Publication Date
WO2017070911A1 true WO2017070911A1 (zh) 2017-05-04

Family

ID=58629670

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2015/093285 WO2017070911A1 (zh) 2015-10-30 2015-10-30 飞行控制装置以及具有该飞行控制装置的无人机

Country Status (3)

Country Link
US (1) US11142313B2 (zh)
CN (1) CN107000828B (zh)
WO (1) WO2017070911A1 (zh)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108470011A (zh) * 2018-05-15 2018-08-31 赫星科技有限公司 无人机用载板
CN110155354A (zh) * 2018-11-12 2019-08-23 北京机电工程研究所 一种无人飞行器电子系统模块化集成装置
CN110799900A (zh) * 2018-10-31 2020-02-14 深圳市大疆创新科技有限公司 电路板系统、拍摄装置、云台组件及可移动平台
US20200283118A1 (en) * 2018-01-19 2020-09-10 SZ DJI Technology Co., Ltd. Unmanned aerial vehicle

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019140658A1 (zh) * 2018-01-19 2019-07-25 深圳市大疆创新科技有限公司 散热结构、散热方法及装置、无人机、可读存储介质
US10827629B2 (en) * 2018-01-19 2020-11-03 Ge Aviation Systems Llc Control boxes and system-on-module circuit boards for unmanned vehicles
EP3892547A1 (en) * 2018-12-03 2021-10-13 SZ DJI Technology Co., Ltd. Control assembly and aircraft
CN111198575A (zh) * 2020-02-27 2020-05-26 西北工业大学 一种无人机飞行控制器
CN112478186B (zh) * 2020-12-17 2022-10-18 石家庄嘉诚联信科技开发有限公司 一种基于车载系统的电力配网巡检无人机

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102201027A (zh) * 2010-03-26 2011-09-28 国营东方仪器厂 无人机导航/飞控计算机
CN102431643A (zh) * 2011-11-30 2012-05-02 中国南方航空工业(集团)有限公司 无人机的自动驾驶仪
US20120169484A1 (en) * 2009-02-04 2012-07-05 Mikado Model Helicopters GmbH Model Aircraft Contol and Receiving Device
CN204102046U (zh) * 2014-10-11 2015-01-14 中国航空工业第六一八研究所 一种小型gnc一体化计算机电路板固定装置
CN204726664U (zh) * 2015-06-24 2015-10-28 零度智控（北京）智能科技有限公司 无人飞行器

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8618934B2 (en) * 2009-04-27 2013-12-31 Kolos International LLC Autonomous sensing module, a system and a method of long-term condition monitoring of structures
CN201904727U (zh) * 2010-07-28 2011-07-20 浙江飞越数字科技有限公司 一种机顶盒嵌入式电源
US8774982B2 (en) * 2010-08-26 2014-07-08 Leptron Industrial Robotic Helicopters, Inc. Helicopter with multi-rotors and wireless capability
CN202229682U (zh) * 2011-08-17 2012-05-23 北京航天自动控制研究所 基于mems的层叠式一体化飞行控制设备
US9518821B2 (en) * 2012-08-02 2016-12-13 Benjamin Malay Vehicle control system
US10054939B1 (en) * 2012-09-22 2018-08-21 Paul G. Applewhite Unmanned aerial vehicle systems and methods of use
US9070924B2 (en) * 2012-12-10 2015-06-30 Lenovo (Singapore) Pte. Ltd. Battery cover release
JP5421449B1 (ja) * 2012-12-18 2014-02-19 パナソニック株式会社 携帯端末装置
FR3020282B1 (fr) * 2014-04-24 2016-05-13 Parrot Platine universelle de montage pour drone a voilure tournante
US20160221683A1 (en) * 2014-05-19 2016-08-04 Google Inc. Hybrid Power Systems for Vehicle with Hybrid Flight Modes
CN203870472U (zh) * 2014-05-21 2014-10-08 中国航天时代电子公司 一种集成一体化飞行控制器
US9798322B2 (en) * 2014-06-19 2017-10-24 Skydio, Inc. Virtual camera interface and other user interaction paradigms for a flying digital assistant
US20160376000A1 (en) * 2014-07-10 2016-12-29 Christoph Kohstall Submersible unmanned aerial vehicles and associated systems and methods
US10152098B2 (en) * 2014-10-08 2018-12-11 AzTrong Inc. Dynamic heat conducting path for portable electronic device
CN104627361B (zh) * 2015-02-05 2018-01-05 深圳雷柏科技股份有限公司 一种模块化无人飞行器
US9738380B2 (en) * 2015-03-16 2017-08-22 XCraft Enterprises, LLC Unmanned aerial vehicle with detachable computing device
CN104833821B (zh) * 2015-05-07 2017-11-03 深圳导远科技有限公司 环形悬挂式内隔振的惯性测量组件
CN104931052A (zh) * 2015-07-10 2015-09-23 零度智控（北京）智能科技有限公司 一种无人飞行器惯性测量模块
CN205168871U (zh) * 2015-10-30 2016-04-20 深圳市大疆创新科技有限公司 飞行控制装置以及具有该飞行控制装置的无人机

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120169484A1 (en) * 2009-02-04 2012-07-05 Mikado Model Helicopters GmbH Model Aircraft Contol and Receiving Device
CN102201027A (zh) * 2010-03-26 2011-09-28 国营东方仪器厂 无人机导航/飞控计算机
CN102431643A (zh) * 2011-11-30 2012-05-02 中国南方航空工业(集团)有限公司 无人机的自动驾驶仪
CN204102046U (zh) * 2014-10-11 2015-01-14 中国航空工业第六一八研究所 一种小型gnc一体化计算机电路板固定装置
CN204726664U (zh) * 2015-06-24 2015-10-28 零度智控（北京）智能科技有限公司 无人飞行器

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20200283118A1 (en) * 2018-01-19 2020-09-10 SZ DJI Technology Co., Ltd. Unmanned aerial vehicle
EP3741661A4 (en) * 2018-01-19 2021-02-17 SZ DJI Technology Co., Ltd. PILOTLESS AIR VEHICLE
CN108470011A (zh) * 2018-05-15 2018-08-31 赫星科技有限公司 无人机用载板
CN110799900A (zh) * 2018-10-31 2020-02-14 深圳市大疆创新科技有限公司 电路板系统、拍摄装置、云台组件及可移动平台
WO2020087392A1 (zh) * 2018-10-31 2020-05-07 深圳市大疆创新科技有限公司 电路板系统、拍摄装置、云台组件及可移动平台
CN110799900B (zh) * 2018-10-31 2021-06-04 深圳市大疆创新科技有限公司 电路板系统、拍摄装置、云台组件及可移动平台
CN110155354A (zh) * 2018-11-12 2019-08-23 北京机电工程研究所 一种无人飞行器电子系统模块化集成装置

Also Published As

Publication number Publication date
CN107000828A (zh) 2017-08-01
US11142313B2 (en) 2021-10-12
US20180244388A1 (en) 2018-08-30
CN107000828B (zh) 2019-06-18

Similar Documents

Publication Publication Date Title
WO2017070911A1 (zh) 飞行控制装置以及具有该飞行控制装置的无人机
US7567434B1 (en) Computer system expansion device adaptable for internal and external use
TWI667577B (zh) 計算裝置及應用其之機架伺服器
EP3425336A1 (en) Inertia measurement apparatus and unmanned aerial vehicle
WO2018040585A1 (zh) 电力供应扩展卡及电脑机箱
WO2020000507A1 (zh) 无人机及其机身、云台相机
WO2018018637A1 (zh) 散热器、无人飞行器和可移动设备
WO2018040309A1 (zh) 电力供应扩展卡及电脑机箱
WO2016161626A1 (zh) 存储装置及采用该存储装置的无人飞行器
WO2018090613A1 (zh) Dmd器件装置及dmd器件固定组件
US20140140687A1 (en) Cover for photographing lens device
CN218866352U (zh) 一种plc可编程控制器
CN210143021U (zh) 符合cpex标准的6u抗恶劣环境的光口交换机模块
WO2014129705A1 (ko) 서버 방열시스템
EP4258830A1 (en) Modular information system
TWI783673B (zh) 具有頻寬切換功能之伺服器系統
CN219779369U (zh) 一种融合供电与can信号传输的装置
CN215835495U (zh) 光纤视频传输设备
WO2014205196A1 (en) Electronic assembly with thermal channel and method of manufacture thereof
WO2019109631A1 (zh) 显示模组、装配治具及显示装置
WO2024040932A1 (zh) 风扇插箱、风扇框及插箱系统
CN211239923U (zh) 摄像装置及无人驾驶设备
CN217216680U (zh) 一种小型条状工业相机
WO2020000653A1 (zh) 无人机扩展系统及其无人机、扩展模块
WO2023165555A1 (zh) 风扇结构及电子设备

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 15906974

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 15906974

Country of ref document: EP

Kind code of ref document: A1