WO2019062126A1 - 拍摄组件及具有此拍摄组件的无人飞行器 - Google Patents

拍摄组件及具有此拍摄组件的无人飞行器 Download PDF

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Publication number
WO2019062126A1
WO2019062126A1 PCT/CN2018/086065 CN2018086065W WO2019062126A1 WO 2019062126 A1 WO2019062126 A1 WO 2019062126A1 CN 2018086065 W CN2018086065 W CN 2018086065W WO 2019062126 A1 WO2019062126 A1 WO 2019062126A1
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WIPO (PCT)
Prior art keywords
connecting member
mounting portion
damping
fixedly mounted
mounting plate
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PCT/CN2018/086065
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English (en)
French (fr)
Inventor
张正力
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深圳市道通智能航空技术有限公司
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Publication of WO2019062126A1 publication Critical patent/WO2019062126A1/zh

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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64UUNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00Constructional aspects of UAVs
    • B64U20/80Arrangement of on-board electronics, e.g. avionics systems or wiring
    • B64U20/87Mounting of imaging devices, e.g. mounting of gimbals
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64UUNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2101/00UAVs specially adapted for particular uses or applications
    • B64U2101/30UAVs specially adapted for particular uses or applications for imaging, photography or videography

Definitions

  • the present invention relates to the field of aircraft, and more particularly to a shooting assembly for an unmanned aerial vehicle and an unmanned aerial vehicle having the same.
  • Unmanned aerial vehicles have broad application prospects in disaster investigation and rescue, air surveillance, transmission line inspection, aerial photography, aerial survey and military.
  • the commonly used shooting unit for panoramic shooting needs to fix the two sets of pan/tilt and camera, and simultaneously dampen the two sets of pan/tilt and camera and their couplings.
  • the current shooting components do not have a good damping effect and cannot fully meet the needs of use.
  • an embodiment of the present invention provides a shooting assembly with good shock absorption effect and an unmanned aerial vehicle having the same.
  • the embodiment of the present invention provides the following technical solutions:
  • a shooting assembly is applied to an unmanned aerial vehicle, the unmanned aerial vehicle including a fuselage.
  • the photographing assembly includes: a first connecting member, a second connecting member, at least one damper device, a first pan/tilt head, a second pan/tilt head, and a first camera device and a second camera device.
  • At least one of the shock absorbing devices is coupled between one end of the first connecting member and one end of the second connecting member, or is connected to the other end of the first connecting member and the second connecting member.
  • the first connecting member, the second connecting member and the damper device enclose a passage for receiving the body.
  • the damper device located between one end of the first connecting member and one end of the second connecting member mounts the first pan/tilt at the other end of the first connecting member and the second connection Another of the damper devices between the other end of the piece mounts the second head.
  • the first camera device is mounted on the first cloud platform
  • the second camera device is mounted on the second cloud platform.
  • the damping device (206) is two; one of the damping devices (206) is coupled to one end of the first connector (202) and the second connector (204) Between one end, another of the damping devices (206) is coupled between the other end of the first connector (202) and the other end of the second connector (204).
  • each of the damper devices includes a first surface facing the fuselage, and one end of the first connecting member is fixedly mounted to a first surface of one of the damper devices The other end of the first connecting member is fixedly mounted to the first surface of the other damping device.
  • the first connecting member includes a first mounting portion, a first connecting portion and a second mounting portion, the first connecting portion being connected between the first mounting portion and the second mounting portion; the first mounting portion Fixedly mounted on a first surface of one of the damping devices, the second mounting portion being fixedly mounted to the first surface of the other of the damping devices.
  • first mounting portion and the second mounting portion are both perpendicular to the first connecting portion.
  • each of the damper devices includes a first mounting plate, a damper element and a second mounting plate, the damper element being sandwiched between the first mounting plate and the second mounting plate,
  • the first mounting plate is closer to the fuselage relative to the second mounting plate, and the first mounting plate includes the first surface.
  • the second mounting plate includes a second surface facing the fuselage, and one end of the second connecting member is fixedly mounted on a second surface of the damper device. The other end of the second connecting member is fixedly mounted to the second surface of the other damping device.
  • the second connector includes a third mounting portion, a second connecting portion and a fourth mounting portion, the second connecting portion being coupled between the third mounting portion and the fourth mounting portion;
  • the third mounting portion is fixedly mounted to a second surface of the damper device, and the fourth mounting portion is fixedly mounted to the second surface of the other damper device.
  • the first pan/tilt head is fixedly mounted to a second mounting plate of one of the damper devices, and the second pan/tilt head is fixedly mounted to a second mounting plate of the other damper device.
  • the first pan/tilt and/or the second pan/tilt head are three-axis stabilizing pan/tilt heads.
  • the first camera device and/or the second camera device comprise at least one lens.
  • An unmanned aerial vehicle includes a fuselage and a photographing assembly as described above, the fuselage being received in the passage, and one end of the first connecting member is fixedly mounted to the fuselage.
  • the other end of the first connector is spaced from the fuselage.
  • the fuselage includes opposite first and second ends, one end of the first connector is fixedly mounted to the first end; when the UAV is flying, the The first end is located on a lower side of the fuselage and the second end is located on an upper side of the fuselage.
  • the fuselage includes opposite first and second ends, one end of the first connector is fixedly mounted to the first end; when the UAV is flying, the The first end is located on the left side of the fuselage and the second end is located on the right side of the fuselage.
  • At least one of the shock absorbing devices is connected between one end of the first connecting member and one end of the second connecting member, or is connected to the Between the other end of the first connecting member and the other end of the second connecting member, the shock absorber of the unmanned aerial vehicle is damped to the first camera device and the second camera device during flight The effects are consistent, and the consistency of the shock absorption is improved, so that the first imaging device and the second imaging device can stably capture, thereby obtaining a high-quality image.
  • FIG. 1 is a perspective view of an unmanned aerial vehicle according to an embodiment of the present invention.
  • Figure 2 is a front elevational view of the unmanned aerial vehicle of Figure 1;
  • Figure 4 is a perspective view of the photographing assembly shown in Figure 3;
  • Figure 5 is a perspective view of another angle of the photographing assembly shown in Figure 3.
  • an unmanned aerial vehicle 100 includes a body 10 and a photographing assembly 20 , and the photographing assembly 20 is mounted on the body 10 .
  • the body 10 includes a control circuit component composed of electronic components such as an MCU, and the control circuit component includes a plurality of control modules, such as a flight control module for controlling an unmanned aircraft flight attitude, and a navigation unmanned aerial vehicle.
  • the Beidou module and a data processing module for processing environmental information acquired by related onboard devices.
  • the body 10 includes a first end 102 and a second end 104 that are disposed opposite each other.
  • the first end 102 and the second end 104 are located on the lower side and the upper side of the body 10, respectively.
  • the photographing assembly 20 includes a first connecting member 202 , a second connecting member 204 , a damping device 206 , a first head 208 , a second head 210 , a first camera 212 , and a first camera Two camera devices 214.
  • One end of the first connecting member 202 is fixedly mounted to the body 10
  • one of the damper devices 206 is fixedly mounted between one end of the first connecting member 202 and one end of the second connecting member 204, and the other
  • the damper device 206 is fixedly mounted between the other end of the first connecting member 202 and the other end of the second connecting member 204.
  • the first connecting member 202, the second connecting member 204 and the damper device 206 are collectively formed to form a passage 30, and the body 10 is received in the passage 30.
  • the first cloud platform 208 and the second cloud platform 210 are respectively mounted on two of the damper devices 206.
  • the first camera device 212 is mounted on the first cloud platform 208, and the second camera device 214 is installed. In the second pan/tilt 210.
  • the damping device 206 can be one.
  • a damper device 206 may be coupled between one end of the first connector 202 and one end of the second connector 204, or may be coupled between the other end of the first connector 202 and the other end of the second connector 204.
  • the damper device 206 can also be multiple, in which case the connection can be made by adding a connector, and the second connector 204 is a separate component to ensure that the damper device 206 is The damping effects of one imaging device 212 and second imaging device 214 are the same, thereby obtaining a high quality image.
  • the first connecting member 202 is strip-shaped and can be made of a metal material or a plastic material, such as magnesium alloy, to provide sufficient rigidity.
  • the first connecting member 202 includes a first mounting portion 2020, a first connecting portion 2022 and a second mounting portion 2024.
  • the first connecting portion 2022 is connected between the first mounting portion 2020 and the second mounting portion 2024. .
  • the first mounting portion 2020 and the second mounting portion 2024 are parallel to each other and are perpendicular to the first connecting portion 2022.
  • the first mounting portion 2020 is fixedly mounted to the first end 102 of the body 10
  • the second mounting portion 2024 is spaced apart from the body 10 .
  • first mounting portion 2020 can be fixedly mounted to the first end 102 of the body 10
  • second mounting portion 2024 can be fixedly mounted to the body.
  • the second connector 204 is strip-shaped and may be made of a metal material or a plastic material, such as a magnesium alloy, to provide sufficient rigidity.
  • the second connecting member 204 includes a third mounting portion 2040, a second connecting portion 2042 and a fourth mounting portion 2044.
  • the second connecting portion 2042 is connected between the third mounting portion 2040 and the fourth mounting portion 2044. .
  • the third mounting portion 2040 and the fourth mounting portion 2044 are parallel to each other and are perpendicular to the second connecting portion 2042, and the first mounting portion 2020, the second mounting portion 2024, the third mounting portion 2040, and the The four mounting portions 2044 are all parallel to each other.
  • first connector 202 and the second connector 204 may be adjustable in length, for example, using a telescoping structure to accommodate different sized aircraft.
  • the number of the damper devices 206 is two, one of the damper devices 206 is fixedly mounted between the first mounting portion 2020 and the third mounting portion 2040, and the other damper device 206 is mounted on The second mounting portion 2024 is between the second mounting portion 2044 and the fourth mounting portion 2044.
  • Each of the damper devices 206 includes a first mounting plate 2060, a damper element 2062 and a second mounting plate 2064.
  • the damper element 2062 is sandwiched between the first mounting plate 2060 and the second mounting plate 2064.
  • the first mounting plate 2060 is closer to the body 10 relative to the second mounting plate 2064.
  • the first mounting plate 2060 includes a first surface 2061 that faces the body 10.
  • the second mounting plate 2064 includes a second surface 2065 that also faces the fuselage 10.
  • the first mounting plate 2060 and the second mounting plate 2064 are square plates, each of the damping devices 206 includes four of the damping elements 2062, and the four damping elements 2062 are respectively disposed on the Four corners of the first mounting plate 2060 and the second mounting plate 2064.
  • first mounting portion 2020, the second mounting portion 2024, the third mounting portion 2040, and the fourth mounting portion 2044 may be omitted, and the two ends of the first connecting portion 2022 are respectively
  • the first mounting plate 2060 of the two shock absorbing devices 206 is directly fixedly connected
  • the two ends of the second connecting portion 2022 are directly fixedly connected to the second mounting plates 2064 of the two shock absorbing devices 206, respectively.
  • the damping element 2062 is a shock absorbing ball made of an elastic material such as a rubber material or the like.
  • the damper element 2062 can be an elastic damper column or other damper element as long as the first mounting plate 2060 and the second mounting plate 2064 can be reached. Shock absorption can be.
  • the number and distribution of the damping elements 2062 can be varied according to actual needs.
  • the first mounting plate 2060 and the second mounting plate 2064 are not limited to a square plate, and may be changed according to actual needs, for example, a rectangular or circular plate.
  • the first platform 208 is fixedly mounted to the second mounting plate 2064 of one of the dampers 206, and the first platform 208 and the body 10 are respectively located on opposite sides of the damper 206.
  • the second platform 210 is fixedly mounted to the second mounting plate 2064 of the other damper device 206, and the second platform 210 and the body 10 are respectively located on opposite sides of the damper device 206.
  • the first cloud platform 208 and the second cloud platform 210 are disposed on opposite sides of the body 10 .
  • the first cloud platform 208 and the second cloud platform 210 are both three-axis stabilization pans, and each of the three-axis stabilization pans 208, 210 pairs the first camera device 208 or the second in flight on three axes.
  • the imaging device 210 performs stabilization: a heading axis (Yaw), a pitch axis (Pitch), and a roll axis (Roll).
  • the pitch axis is perpendicular to the roll axis
  • the heading axis is perpendicular to the pitch axis and the roll axis.
  • Each pan/tilt 208, 210 includes a first motor, a second motor, and a third motor.
  • the central axis of the rotor of the first motor is coaxial with the roll axis.
  • the central axis of the rotor of the second motor is coaxial with the pitch axis, and the central axis of the rotor of the third motor is coaxial with the heading axis.
  • the stator of the third motor is mounted to the second mounting plate 2064 of the damper 206 via a mount, the rotor of the third motor is coupled to the stator of the second motor, and the rotor of the second motor is coupled to the stator of the first motor.
  • the third motor can be omitted, and the stator of the second motor is mounted to the second mounting plate 2064 of the damper device 206 through the mounting seat.
  • the first camera 208 is fixed to the rotor of the first motor mounted on the first head 208
  • the second camera 210 is fixed to the rotor of the first motor mounted on the second platform 210.
  • the first camera 208 and the second camera 210 are disposed in opposite directions, and the optical axis of the first camera 208 is coaxial with the optical axis of the second camera 210.
  • first pan/tilt 208 and the second pan/tilt head 210 can be single-axis pan/tilt heads.
  • the first camera 212 and the second camera 214 may include more than one lens.
  • the UAV 100 of the embodiment of the present invention When the UAV 100 of the embodiment of the present invention is flying, since one of the damper devices 206 is connected between one end of the first connecting member 202 and one end of the second connecting member 20, the other is reduced.
  • the shock device 206 is connected between the other end of the first connecting member 202 and the other end of the second connecting member 204, and the damping device 206 is opposite to the first camera device 208 and the second camera device 210.
  • the shock absorption effect is uniform, and the consistency of the shock absorption is improved, so that the first imaging device 208 and the second imaging device 210 can stably capture, thereby obtaining a high quality image.
  • the motors on the three axes of the first pan/tilt 208 and the second pan/tilt 210 may output the same rotation to keep the first camera device 208 and the second camera device 210 simultaneously stabilized.
  • the first camera 208 and the second camera 210 can further stably acquire high-quality images for splicing into a panoramic image.
  • the photographing assembly 20 can flexibly increase the damper device according to actual needs, for example, adding two of the damper devices 206, that is, each end 102, 104 of the body 10 has two of the dampers Device 206. At each end 102, 104 of the fuselage 10, two of the damping devices 206 are stacked together, one end of the first connecting member 202 is connected to one of the damping devices 206, and the second connecting member 204 One end is connected to the other of the damper devices 206.
  • the first end 102 and the second end 104 may be respectively located on the left and right sides of the body 10, that is, the The first head 208 and the second head 210 are located on the left and right sides of the body 10, respectively.

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  • Engineering & Computer Science (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Accessories Of Cameras (AREA)
  • Studio Devices (AREA)

Abstract

一种拍摄组件(20),包括第一连接件(202)、第二连接件(204)、减震装置(206),第一云台(208)、第二云台(210)以及第一摄像装置(212)和第二摄像装置(214)。一个减震装置(206)连接于第一连接件(202)的一端和第二连接件(204)的一端之间,另一个减震装置(206)连接于第一连接件(202)的另一端和第二连接件(204)的另一端之间。第一连接件(202)的一端和第二连接件(204)的一端之间的减震装置(206)安装第一云台(208),第一连接件(202)的另一端和第二连接件(204)的另一端之间的另一个减震装置(206)安装第二云台(210)。第一摄像装置(212)和第二摄像装置(214)分别安装于第一云台(208)和第二云台(210)。以及一种具有该拍摄组件(20)的无人飞行器(100)。该无人飞行器在飞行过程中,减震装置对第一、二摄像装置的减震效果一致,提高减震的一致性,使得第一、二摄像装置可稳定地拍摄,从而得到高质量图像。

Description

拍摄组件及具有此拍摄组件的无人飞行器
申请要求于2017年9月26日申请的、申请号为201710883254.6、申请名称为“拍摄组件及具有此拍摄组件的无人飞行器”的中国专利申请的优先权,其全部内容通过引用结合在本申请中。
【技术领域】
本发明涉及飞行器领域,尤其涉及一种用于无人飞行器的拍摄组件及具有此拍摄组件的无人飞行器。
【背景技术】
无人飞行器在灾情调查和救援、空中监控、输电线路巡检、航拍、航测以及军事领域有着广泛的应用前景。
在目前的无人飞行器中,常用的实现全景拍摄的拍摄组件需要固联上下两组云台和相机,并对两组云台和相机及其联接件同时进行减振处理。然而,目前的拍摄组件减震效果不佳,不能完全满足使用需求。
【发明内容】
为了解决上述技术问题,本发明实施例提供一种减震效果佳的拍摄组件及具有此拍摄组件的无人飞行器。
为了解决上述技术问题,本发明实施例提供以下技术方案:
一种拍摄组件,应用于无人飞行器,所述无人飞行器包括机身。所述拍摄组件包括:第一连接件、第二连接件,至少一个减震装置,第一云台、第二云台以及第一摄像装置、第二摄像装置。至少一个所述减震装置连接于所述第一连接件的一端和所述第二连接件的一端之间,或连接于所述第一连接件的另一端和所述第二连接件的另一端之间,所述第一连接件、第二连接件和所述减震装置围设形成一用于收容所述机身的通道。位于所述第一连接件的一端和所述第二连接件的一端之间的所述减震装置安装所述第一云台,位 于所述第一连接件的另一端和所述第二连接件的另一端之间的另一个所述减震装置安装所述第二云台。所述第一摄像装置安装于所述第一云台,所述第二摄像装置安装于所述第二云台。
在一些实施例中,所述减震装置(206)为两个;一个所述减震装置(206)连接于所述第一连接件(202)的一端和所述第二连接件(204)的一端之间,另一个所述减震装置(206)连接于所述第一连接件(202)的另一端和所述第二连接件(204)的另一端之间。
在一些实施例中,每个所述减震装置包括第一表面,所述第一表面朝向所述机身,所述第一连接件的一端固定安装于一个所述减震装置的第一表面,所述第一连接件的另一端固定安装于另一个所述减震装置的第一表面。
所述第一连接件包括第一安装部,第一连接部和第二安装部,所述第一连接部连接于所述第一安装部与第二安装部之间;所述第一安装部固定安装于一个所述减震装置的第一表面,所述第二安装部固定安装于另一个所述减震装置的第一表面。
在一些实施例中,所述第一安装部和第二安装部皆垂直于所述第一连接部。
在一些实施例中,每个所述减震装置包括第一安装板,减震元件和第二安装板,所述减震元件夹于所述第一安装板和第二安装板之间,所述第一安装板相对于所述第二安装板更靠近所述机身,所述第一安装板包括所述第一表面。
在一些实施例中,所述减震元件为减震球。
在一些实施例中,所述第二安装板包括第二表面,所述第二表面朝向所述机身,所述第二连接件的一端固定安装于一个所述减震装置的第二表面,所述第二连接件的另一端固定安装于另一个所述减震装置的第二表面。
在一些实施例中,所述第二连接件包括第三安装部,第二连接部和第四安装部,所述第二连接部连接于所述第三安装部与第四安装部之间;所述第三安装部固定安装于一个所述减震装置的第二表面,所述第四安装部固定安装于另一个所述减震装置的第二表面。
在一些实施例中,所述第三安装部和第四安装部皆垂直于所述第二连接部。
在一些实施例中,所述第一云台固定安装于一个所述减震装置的第二安装板,所述第二云台固定安装于另一个所述减震装置的第二安装板。
在一些实施例中,所述第一云台和/或第二云台为三轴增稳云台。
在一些实施例中,所述第一摄像装置和/或第二摄像装置包括至少一个镜头。
本发明实施例还提供以下技术方案:
一种无人飞行器,包括机身和以上所述的拍摄组件,所述机身被收容于所述通道,所述第一连接件的一端固定安装于所述机身。
在一些实施例中,所述第一连接件的另一端与所述机身间隔设置。
在一些实施例中,所述机身包括相对设置的第一端和第二端,所述第一连接件的一端固定安装于所述第一端;在所述无人飞行器飞行时,所述第一端位于所述机身的下侧,所述第二端位于所述机身的上侧。
在一些实施例中,所述机身包括相对设置的第一端和第二端,所述第一连接件的一端固定安装于所述第一端;在所述无人飞行器飞行时,所述第一端位于所述机身的左侧,所述第二端位于所述机身的右侧。
与现有技术相比较,在本发明实施例的拍摄组件中,至少一个所述减震装置连接于所述第一连接件的一端和所述第二连接件的一端之间,或连接于所述第一连接件的另一端和所述第二连接件的另一端之间,使得无人飞行器在飞行过程中,所述减震装置对所述第一摄像装置、第二摄像装置的减震效果一致,提高减震的一致性,使得第一摄像装置、第二摄像装置可稳定地拍摄,从而得到高质量图像。
【附图说明】
一个或多个实施例通过与之对应的附图进行示例性说明,这些示例性说明并不构成对实施例的限定,附图中具有相同参考数字标号的元件表示为类似的元件,除非有特别申明,附图中的图不构成比例限制。对于本领域普通技术人员来讲,在不付出创造性劳动的前提下,还可以根据这些附图获得其他实施例的附图。
图1为本发明其中一实施例提供的一种无人飞行器的立体图;
图2为图1所示的无人飞行器的主视图;
图3为图1所示的无人飞行器的拍摄组件的主视图;
图4为图3所示的拍摄组件的立体图;
图5为图3所示的拍摄组件的另一角度的立体图。
【具体实施方式】
为了便于理解本发明,下面结合附图和具体实施方式,对本发明进行更详细的说明。需要说明的是,当元件被表述“固定于”另一个元件,它可以直接在另一个元件上、或者其间可以存在一个或多个居中的元件。当一个元件被表述“连接”另一个元件,它可以是直接连接到另一个元件、或者其间可以存在一个或多个居中的元件。本说明书所使用的术语“垂直的”、“水平的”、“左”、“右”、“内”、“外”以及类似的表述只是为了说明的目的。
除非另有定义,本说明书所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。在本发明的说明书中所使用的术语只是为了描述具体的实施方式的目的,不是用于限制本发明。本说明书所使用的术语“和/或”包括一个或多个相关的所列项目的任意的和所有的组合。
此外,下面所描述的本发明不同实施例中所涉及的技术特征只要彼此之间未构成冲突就可以相互结合。
请参阅图1和图2,本发明其中一实施例提供的无人飞行器100包括机身10和拍摄组件20,所述拍摄组件20安装于机身10。
所述机身10内包括由MCU等电子元器件组成的控制电路组件,该控制电路组件包括多个控制模块,如,用于控制无人飞行器飞行姿态的飞行控制模块、用于导航无人飞行器的北斗模块、以及用于处理相关机载设备所获取的环境信息的数据处理模块等。
所述机身10包括相对设置的第一端102和第二端104。在所述无人飞行器100飞行时,所述第一端102和第二端104分别位于所述机身10的下侧和上侧。
请参阅图3至图5,所述拍摄组件20包括第一连接件202,第二连接件 204,减震装置206,第一云台208,第二云台210,第一摄像装置212和第二摄像装置214。所述第一连接件202的一端固定安装于所述机身10,一个所述减震装置206固定安装于所述第一连接件202的一端与第二连接件204的一端之间,另一个所述减震装置206固定安装于所述第一连接件202的另一端与第二连接件204的另一端之间。所述第一连接件202,第二连接件204和减震装置206共同围设形成一通道30,所述机身10被收容于所述通道30。所述第一云台208和第二云台210分别安装于两个所述减震装置206,所述第一摄像装置212安装于所述第一云台208,所述第二摄像装置214安装于所述第二云台210。
可以理解,在其它实施例中,减震装置206可以为一个。一个减震装置206可以连接于第一连接件202的一端和第二连接件204的一端之间,也可以连接于第一连接件202的另一端和第二连接件204的另一端之间。
可以理解,在其它实施例中,减震装置206还可以为多个,这时可以通过增加连接件的方式进行连接,且第二连接件204为一独立元件,以确保减震装置206对第一摄像装置212、第二摄像装置214的减震效果一致,从而得到高质量图像。
所述第一连接件202为条状,可由金属材料或塑胶材料制得,例如镁铝合金,以提供足够的刚度。所述第一连接件202包括第一安装部2020,第一连接部2022和第二安装部2024,所述第一连接部2022连接于所述第一安装部2020与第二安装部2024之间。所述第一安装部2020和第二安装部2024相互平行,并且都垂直于所述第一连接部2022。所述第一安装部2020固定安装于所述机身10的第一端102,而所述第二安装部2024与所述机身10间隔设置。
可以理解的是,在一些其它实施例中,所述第一安装部2020可固定安装于所述机身10的第一端102,而所述第二安装部2024可固定安装于所述机身10的第二端104。
相似地,所述第二连接件204为条状,可由金属材料或塑胶材料制得,例如镁铝合金,以提供足够的刚度。所述第二连接件204包括第三安装部2040,第二连接部2042和第四安装部2044,所述第二连接部2042连接于所述第三安装部2040与第四安装部2044之间。所述第三安装部2040和第四安装部2044 相互平行,并且都垂直于所述第二连接部2042,并且所述第一安装部2020,第二安装部2024,第三安装部2040和第四安装部2044都相互平行。
可以理解的是,在一些其它实施例中,第一连接件202和第二连接件204长度可调整,例如,采用伸缩结构,以适配不同尺寸的飞行器。
所述减震装置206的个数为两个,其中一个所述减震装置206固定安装于所述第一安装部2020与第三安装部2040之间,另一个所述减震装置206安装于所述第二安装部2024与第四安装部2044之间。
每个所述减震装置206包括第一安装板2060,减震元件2062和第二安装板2064,所述减震元件2062夹于所述第一安装板2060与第二安装板2064之间,所述第一安装板2060相对于第二安装板2064更靠近所述机身10。所述第一安装板2060包括第一表面2061,所述第一表面2061朝向所述机身10。所述第二安装板2064包括第二表面2065,所述第二表面2065也朝向所述机身10。
其中一个所述减震装置206的所述第一表面2061固定安装所述第一安装部2020,另一个所述减震装置206的所述第一表面2061固定安装第三安装部2044;其中一个所述减震装置206的所述第二表面2065固定安装所述第三安装部2040,另一个所述减震装置206的所述第二表面2065固定安装第四安装部2044。
所述第一安装板2060与第二安装板2064皆为正方形的平板,每个所述减震装置206包括4个所述减震元件2062,4个所述减震元件2062分别设置于所述第一安装板2060和第二安装板2064的4个角。
可以理解的是,在一些其它实施例中,所述第一安装部2020,第二安装部2024,第三安装部2040和第四安装部2044可以省略,而第一连接部2022的两端分别直接固定连接两个所述减震装置206的第一安装板2060,第二连接部2022的两端分别直接固定连接两个所述减震装置206的第二安装板2064。
所述减震元件2062为减震球,由弹性材料制得,如橡胶材料等。
可以理解的是,在一些其它实施例中,所述减震元件2062可为弹性的减震柱或其他减震元件,只要能达到所述第一安装板2060与第二安装板2064之间的减震即可。所述减震元件2062的个数及分布方式,可根据实际需要变 化。所述第一安装板2060与第二安装板2064不限于为正方形的平板,可根据实际需要而变化,例如,长方形或圆形的平板。
所述第一云台208固定安装于其中一个所述减震装置206的第二安装板2064,第一云台208与机身10分别位于所述减震装置206的相对两侧。相似地,所述第二云台210固定安装于另一个所述减震装置206的第二安装板2064,第二云台210与机身10分别位于所述减震装置206的相对两侧。所述第一云台208与第二云台210设置于所述机身10的相对两侧。
所述第一云台208与第二云台210皆为三轴增稳云台,每个三轴增稳云台208,210在三个轴上对飞行中的第一摄像装置208或第二摄像装置210进行增稳:航向轴(Yaw),俯仰轴(Pitch)和翻滚轴(Roll)。所述俯仰轴垂直于翻滚轴,航向轴垂直于俯仰轴和翻滚轴。
每个云台208,210包括:第一电机、第二电机以及第三电机。第一电机的转子的中心轴与翻滚轴同轴。第二电机的转子的中心轴与俯仰轴同轴,而第三电机的转子的中心轴与航向轴同轴。第三电机的定子通过安装座安装于所述减震装置206的第二安装板2064,第三电机的转子连接第二电机的定子,而第二电机的转子连接第一电机的定子。
可以理解的是,在一些其它实施例中,所述第三电机可以省略,第二电机的定子通过安装座安装于所述减震装置206的第二安装板2064。
所述第一摄像装置208固定安装于第一云台208的第一电机的转子,而第二摄像装置210固定安装于第二云台210的第一电机的转子。第一摄像装置208和第二摄像装置210朝向相反方向设置,并且第一摄像装置208的光轴与第二摄像装置210的光轴同轴。
可以理解的是,在一些其它实施例中,所述第一云台208和第二云台210可为单轴云台。所述第一摄像装置212和第二摄像装置214可以包括一个以上的镜头。
在本发明实施例的无人飞行器100飞行时,由于一个所述减震装置206连接于所述第一连接件202的一端和所述第二连接件20的一端之间,另一个所述减震装置206连接于所述第一连接件202的另一端和所述第二连接件204的另一端之间,所述减震装置206对所述第一摄像装置208、第二摄像装置210的减震效果一致,提高减震的一致性,使得第一摄像装置208、第二摄像 装置210可稳定地拍摄,从而得到高质量图像。
另外,第一云台208和第二云台210的三轴上的电机会输出相同的转动来保持第一摄像装置208和第二摄像装置210同时被增稳。在这种情况下,第一摄像装置208和第二摄像装置210可以进一步稳定地获取高质量图像,以供拼接成全景图像。
而且,所述拍摄组件20可以根据实际需求灵活增加减震装置,例如,增加两个所述减震装置206,也即所述机身10的每一端102,104皆具有两个所述减震装置206。在所述机身10的每一端102,104,两个所述减震装置206堆叠在一起,所述第一连接件202的一端连接一个所述减震装置206,所述第二连接件204的一端连接另一个所述减震装置206。
可以理解的是,在一些其它实施例中,所述无人飞行器100在飞行时,所述第一端102和第二端104可分别位于所述机身10的左右两侧,也即所述第一云台208和第二云台210分别位于所述机身10的左右两侧。
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,而非对其限制;在本发明的思路下,以上实施例或者不同实施例中的技术特征之间也可以进行组合,步骤可以以任意顺序实现,并存在如上所述的本发明的不同方面的许多其它变化,为了简明,它们没有在细节中提供;尽管参照前述实施例对本发明进行了详细的说明,本领域的普通技术人员应当理解:其依然可以对前述各实施例所记载的技术方案进行修改,或者对其中部分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各实施例技术方案的范围。

Claims (17)

  1. 一种拍摄组件(20),应用于无人飞行器(100),所述无人飞行器(100)包括机身(10),其特征在于,所述拍摄组件(20)包括:
    第一连接件(202)、第二连接件(204);
    至少一个减震装置(206),至少一个所述减震装置(206)连接于所述第一连接件(202)的一端和所述第二连接件(204)的一端之间,或连接于所述第一连接件(202)的另一端和所述第二连接件(204)的另一端之间,所述第一连接件(202)、二连接件(204)和所述减震装置(206)围设形成一用于收容所述机身(10)的通道(30);
    第一云台(208)、第二云台(210),位于所述第一连接件(202)的一端和所述第二连接件(204)的一端之间的所述减震装置(206)安装所述第一云台(208),位于所述第一连接件(202)的另一端和所述第二连接件(204)的另一端之间的另一个所述减震装置(206)安装所述第二云台(210);
    第一摄像装置(212)、第二摄像装置(214),所述第一摄像装置(212)安装于所述第一云台(208),所述第二摄像装置(214)安装于所述第二云台(210)。
  2. 根据权利要求1所述的拍摄组件(20),其特征在于,所述减震装置(206)为两个;
    一个所述减震装置(206)连接于所述第一连接件(202)的一端和所述第二连接件(204)的一端之间,另一个所述减震装置(206)连接于所述第一连接件(202)的另一端和所述第二连接件(204)的另一端之间。
  3. 根据权利要求1或2所述的拍摄组件(20),其特征在于,每个所述减震装置(206)包括第一表面(2061),所述第一表面(2061)朝向所述机身(10),所述第一连接件(202)的一端固定安装于一个所述减震装置(206)的第一表面(2061),所述第一连接件(202)的另一端固定安装于另一个所述减震装置(206)的第一表面(2061)。
  4. 根据权利要求3所述的拍摄组件(20),其特征在于,所述第一连接件(202)包括第一安装部(2020),第一连接部(2022)和第二安装部(2024),所述第一连接部(2022)连接于所述第一安装部(2020)与第二安装部(2024)之间;
    所述第一安装部(2020)固定安装于一个所述减震装置(206)的第一表面(2061),所述第二安装部(2024)固定安装于另一个所述减震装置(206)的第一表面(2061)。
  5. 根据权利要求4所述的拍摄组件(20),其特征在于,所述第一安装部(2020)和第二安装部(2024)皆垂直于所述第一连接部(2022)。
  6. 根据权利要求3至5任一项所述的拍摄组件(20),其特征在于,每个所述减震装置(206)包括第一安装板(2060),减震元件(2062)和第二安装板(2064),所述减震元件(2062)夹于所述第一安装板(2060)和第二安装板(2064)之间,所述第一安装板(2060)相对于所述第二安装板(2064)更靠近所述机身(10),所述第一安装板(2060)包括所述第一表面(2061)。
  7. 根据权利要求6所述的拍摄组件(20),其特征在于,所述减震元件(2062)为减震球。
  8. 根据权利要求6所述的拍摄组件(20),其特征在于,所述第二安装板(2064)包括第二表面(2065),所述第二表面(2065)朝向所述机身(10),所述第二连接件(204)的一端固定安装于一个所述减震装置(206)的第二表面(2065),所述第二连接件(204)的另一端固定安装于另一个所述减震装置(206)的第二表面(2065)。
  9. 根据权利要求8所述的拍摄组件(20),其特征在于,所述第二连接件(204)包括第三安装部(2040),第二连接部(2042)和第四安装部(2044),所述第二连接部(2042)连接于所述第三安装部(2040)与第四安装部(2044)之间;
    所述第三安装部(2040)固定安装于一个所述减震装置(206)的第二表面(2065),所述第四安装部(2044)固定安装于另一个所述减震装置(206)的第二表面(2065)。
  10. 根据权利要求9所述的拍摄组件(20),其特征在于,所述第三安装部(2040)和第四安装部(2044)皆垂直于所述第二连接部(2042)。
  11. 根据权利要求6至10任一项所述的拍摄组件(20),其特征在于,所述第一云台(208)固定安装于一个所述减震装置(206)的第二安装板(2064),所述第二云台(210)固定安装于另一个所述减震装置(206)的第二安装板(2064)。
  12. 根据权利要求1至11任一项所述的拍摄组件(20),其特征在于,所述第一云台(208)和/或第二云台(210)为三轴增稳云台。
  13. 根据权利要求1至12任一项所述的拍摄组件(20),其特征在于,所述第一摄像装置(212)和/或第二摄像装置(214)包括至少一个镜头。
  14. 一种无人飞行器(100),其特征在于,包括机身(10)和如权利要求1至13任一项所述的拍摄组件(20),所述机身(10)被收容于所述通道(30),所述第一连接件(202)的一端固定安装于所述机身(10)。
  15. 根据权利要求14所述的无人飞行器(100),其特征在于,所述第一连接件(202)的另一端与所述机身(10)间隔设置。
  16. 根据权利要求14或15所述的无人飞行器(100),其特征在于,所述机身(10)包括相对设置的第一端(102)和第二端(104),所述第一连接件(202)的一端固定安装于所述第一端(102);在所述无人飞行器(100)飞行时,所述第一端(102)位于所述机身(10)的下侧,所述第二端(104)位于所述机身(10)的上侧。
  17. 根据权利要求14或15所述的无人飞行器(100),其特征在于,所述机身(10)包括相对设置的第一端(102)和第二端(104),所述第一连接件(202)的一端固定安装于所述第一端(102);在所述无人飞行器(100)飞行时,所述第一端(102)位于所述机身(10)的左侧,所述第二端(104)位于所述机身(10)的右侧。
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