WO2019127528A1 - 自旋式发光飞行器 - Google Patents

自旋式发光飞行器 Download PDF

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Publication number
WO2019127528A1
WO2019127528A1 PCT/CN2017/120260 CN2017120260W WO2019127528A1 WO 2019127528 A1 WO2019127528 A1 WO 2019127528A1 CN 2017120260 W CN2017120260 W CN 2017120260W WO 2019127528 A1 WO2019127528 A1 WO 2019127528A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
substrate
spin
aircraft body
type illuminating
Prior art date
Application number
PCT/CN2017/120260
Other languages
English (en)
French (fr)
Inventor
刘建东
邓宇翔
Original Assignee
深圳市钛翼科技有限公司
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 深圳市钛翼科技有限公司 filed Critical 深圳市钛翼科技有限公司
Priority to CN201780002298.1A priority Critical patent/CN110214111A/zh
Priority to PCT/CN2017/120260 priority patent/WO2019127528A1/zh
Publication of WO2019127528A1 publication Critical patent/WO2019127528A1/zh

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters

Definitions

  • the present application relates to the field of aircraft, and more particularly to a spin-type illuminating aircraft.
  • the purpose of the present application is to provide a spin-type illuminating aircraft, which aims to solve the technical problem that the prior art rotor-type aircraft can not directly use the body structure to convey information or display due to limitations of the conventional structure and control mode.
  • a spin-type illuminating aircraft as claimed in the present application includes an aircraft body and at least one spiral unit capable of rotating the aircraft body about a center of the aircraft body, at least one of the spiral units including a rotor and for driving the A rotor-rotating electric machine; the spin-type illuminating aircraft further includes a illuminating device that rotates around a center of the aircraft body when the aircraft body rotates, the illuminating device being fixedly coupled to the aircraft body.
  • the light emitting device includes a substrate and a plurality of light source devices disposed on the substrate, and the substrate is fixedly coupled to the aircraft body through a support bar.
  • the substrate is annular, and the support strip is connected between the inner edge of the substrate and the aircraft body.
  • the substrate has a notch.
  • the substrate has a polygonal frame shape, and the support bar is connected between the inner edge of the substrate and the aircraft body.
  • the spin-light aircraft has two substrates, two of which are vertically disposed, and the support bars are connected between the inner edges of the two substrates and the aircraft body.
  • the support bar includes a first support bar and a second support bar, the first support bar extending from an inner edge of the substrate to a top and a bottom of the aircraft body, the second support bar Radially extending from an inner edge of the substrate to a sidewall portion of the aircraft body; the support strip is integrally formed with the substrate, and the support strip is detachably coupled to the aircraft body.
  • a plurality of the light source devices are disposed along the entire circumference of the substrate.
  • the aircraft body forms a rotating surface when rotated about the center of the aircraft body, the rotating surface being orthogonal to a plane in which the substrate is located.
  • a reinforcing rib is disposed between the aircraft body and the substrate.
  • the light emitting device includes a substrate and a plurality of light source devices disposed on the substrate, the substrate being in a straight shape and having one end connected to the aircraft body.
  • the substrate is a flexible circuit board
  • the light source device is disposed on the flexible circuit board.
  • the light source device is a light emitting diode.
  • the spin-illuminated aircraft has the beneficial effects of including an aircraft body and at least one spiral unit capable of rotating the aircraft body about the center of the aircraft body, and the at least one spiral unit includes a rotor and for driving the rotor
  • the rotating motor adjusts the rotation direction of each rotor separately to achieve the purpose of spinning the aircraft body around its center;
  • the spin-type illuminating aircraft further includes a illuminating device, and the illuminating device is fixedly connected with the aircraft body,
  • the illuminating device can rotate around the center of the aircraft body while rotating the aircraft body, thereby controlling the illuminating and color change of the illuminating device, and utilizing the visual persistence characteristic of the human eye, so that the illuminating device displays the customized preset information; In this way, when using the aircraft to display and convey information, it is not necessary to use multiple aircraft in combination, and one aircraft can be used.
  • the aircraft purchase cost is reduced, the configuration of a single aircraft is optimized, and the functional diversity and practical value of the aircraft are improved
  • FIG. 1 is a perspective schematic view 1 of a spin-type luminous aircraft provided by a first embodiment of the present application;
  • FIG. 2 is a perspective view 2 of a spin-type illuminating aircraft according to a first embodiment of the present application
  • FIG. 3 is a perspective view of a spin-type illuminating aircraft according to a second embodiment of the present application.
  • FIG. 4 is a perspective view of a spin-type illuminating aircraft according to a third embodiment of the present application.
  • FIG. 5 is a perspective view of a spin-type illuminating aircraft according to a fourth embodiment of the present application.
  • FIG. 6 is a perspective view of a spin-type illuminating aircraft according to a fifth embodiment of the present application.
  • FIG. 7 is a perspective view of a spin-type illuminating aircraft according to a sixth embodiment of the present application.
  • FIG. 8 is a perspective view of a spin-type illuminating aircraft according to a seventh embodiment of the present application.
  • 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” and “second” may include one or more of the features either explicitly or implicitly.
  • connection shall be understood broadly, and may be, for example, a fixed connection, a detachable connection, or an integral body, unless otherwise specifically defined and defined;
  • the connection may also be an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and may be an internal connection of two elements or an interaction relationship of two elements.
  • specific meanings of the above terms in the present application can be understood on a case-by-case basis.
  • a spin-type illuminating aircraft provided by this embodiment includes an aircraft body 2 and at least one spiral unit (not shown), and the spiral unit can surround the aircraft body 2 around the aircraft body.
  • the center 1 of the aircraft 1 rotates, where the center 1 of the aircraft body 2 is defined as a point that is surrounded by the aircraft body 2 and located inside the aircraft body 2;
  • the at least one spiral unit includes a rotor 4 and is used to drive the rotor 4 to rotate Motor (not shown), the rotation direction of each rotor 4 is separately adjusted by adjusting the motor to achieve the purpose of the aircraft body 2 spinning about its center 1;
  • the spin-type aircraft further includes a lighting device 3, By connecting and fixing the illuminating device 3 and the aircraft body 2, the illuminating device 3 can be rotated around the center 1 of the aircraft body 2 while the aircraft body 2 is rotating, thereby utilizing the human eye by controlling the lighting and color change of the illuminating device 3.
  • the visual persistence feature enables the illumination device 3 to display customized preset information; thus, when people use the aircraft display to convey information, it is not necessary Combined use of multiple planes, to use an aircraft, reducing the cost of ownership of the aircraft at the same time, optimize the allocation of a single aircraft to enhance the functional diversity of the aircraft, practical value and user experience.
  • the rotor 4 of the spin-illuminated aircraft includes a first rotor group (not shown) and a second rotor group (not shown) when the first rotor group and the second rotor group are rotated.
  • first rotor group is rotated clockwise (counterclockwise)
  • second rotor group controls the motor speed to achieve, in order to maintain the total lift of the whole machine, the lift of the increased speed should compensate for the lift of the reduced speed, by adjusting the speed of the control motor of the first rotor group and the control motor of the second rotor group.
  • the difference realizes the control of the spin speed of the aircraft body 2 and the illuminating device 3, in the extreme case, the first rotor group and the second rotor group rotate in the same direction; the aircraft body 2 can be provided with a balance protection device (not shown), When the spin speed of the spin-illuminated aircraft exceeds a certain preset value, the balance protection device will be activated to ensure smooth spin of the aircraft body 2 and the illuminating device 3.
  • the light-emitting device 3 includes a substrate 31 and a plurality of light source devices 32 disposed on the substrate 31.
  • the substrate 31 is fixedly connected to the aircraft body 2 through the support bars 33, that is, the light-emitting device 3 is ensured to be around the aircraft.
  • the substrate 31 has an annular shape
  • the support bar 33 is connected between the inner edge of the substrate 31 and the aircraft body 2; when the substrate 31 is rotated, a spherical surface is formed outside the substrate 31 according to the visual persistence characteristic of the human eye.
  • the preset pattern or character can be displayed on the spherical surface, which is not only visually beautiful, but also has a simple shape and is easy to be processed.
  • the position of the support bar 33 has various forms. For details, please refer to FIG. 1 and FIG. 2.
  • the substrate 31 has a notch, that is, the substrate 31 may be a closed structure or a semi-closed structure.
  • the substrate 31 is a 1/2 circular arc or a quarter circular arc shaped annular plate.
  • the support member can ensure the substrate 31 and the aircraft body 2 as long as The relative position is stable and reliable, and the specific position is not limited here.
  • the substrate 31 has a polygonal frame shape, for example, a quadrangular frame shape, and the support bar 33 is connected between the inner edge of the substrate 31 and the aircraft body 2; when the substrate 31 rotates around the center 1 of the aircraft body 2, the outer side thereof can be formed.
  • a cylindrical surface is provided with the light source device 32 disposed on the periphery of the substrate 31 so that the top surface, the bottom surface and the side surface of the cylindrical surface can display information, so that by subtly arranging and controlling the light source device 32, the present invention can be presented.
  • the substrate 31 can also be set as a five-sided ring, a six-sided ring or even an octagonal ring, and the number of sides is not limited to a single parity.
  • the specific number of sides is not limited herein; similarly, the support member can ensure the substrate 31 and The relative position of the aircraft body 2 is stable and reliable, and the specific position is not limited herein.
  • the spin-lighting aircraft has two substrates 31, two substrates 31 are vertically disposed, and the support bars 33 are connected between the inner edges of the two substrates 31 and the aircraft body 2; of course, the number of the substrates 31 may also be More specifically, not specifically limited herein, and the spin-illuminated aircraft includes at least one spiral unit.
  • the double-rotor and the quad-rotor are exemplified, but the number of the spiral units cannot be limited;
  • the combination of 31 not only demonstrates more complex and cool visual effects, but also contributes to making the entire structure more stable, reducing its damage rate and extending the life of the spin-illuminated aircraft.
  • the support bar 33 includes a first support bar 331 and a second support bar 332 extending radially from the inner edge of the substrate 31 to the top and bottom of the aircraft body 2, second The support bar 332 extends radially from the inner edge of the substrate 31 to the side wall portion of the aircraft body 2; the support bar 33 is integrally formed with the substrate 31, and the support bar 33 is detachably connected to the aircraft body 2; by increasing the number of the support bars 33, there are The position of the support plate 33 and the base plate 31 can be detachably connected. It can be a screw connection or a snap connection, etc., and the integral molding method such as welding or integral molding using a mold, etc., is not specifically limited herein.
  • a plurality of light source devices 32 are disposed along the entire circumference of the substrate 31 such that the substrate 31 forms a maximum range of light-emitting regions when rotated about the center 1 of the aircraft body 2, of course, the plurality of light source devices 32 may also be presented as presets.
  • the information and effects are selectively disposed in a partial region of the substrate 31, which is not limited herein.
  • the aircraft body 2 when rotated about the center 1 of the aircraft body 2, constitutes a rotating surface 10 that is orthogonal to the plane in which the substrate 31 is located, when the substrate 31 is rotated about the center 1 of the aircraft body 2
  • a regular three-dimensional light-emitting area can be formed; of course, the plane in which the substrate 31 is located and the rotating surface 10 can be set to be non-orthogonal as needed, and the specific angle is not limited herein.
  • an electronic torsion device (not shown) may be disposed between the support rod and the substrate 31, and the electronic torsion device may be controlled by the remote control device and used to rotate around the center 1 of the aircraft body 2 on the substrate 31. Adjusting the angle between the rotating surface 10 and the plane where the substrate 31 is located, so that the shape of the entire stereoscopic light-emitting area is variable in real time, and the information displayed on the outside is variable in real time, thereby enabling the spin-lighting aircraft to Shows more complex and cool visuals.
  • a rib 5 is disposed between the aircraft body 2 and the substrate 31.
  • the light-emitting device 3 includes a substrate 31 and a plurality of light source devices 32 disposed on the substrate 31.
  • the substrate 31 has a straight shape and one end is connected to the aircraft body 2, wherein the substrate 31 can be along from the center 1 of the aircraft body 2 The direction of the outer extension of the aircraft body 2 is extended.
  • the substrate 31 can be symmetrically disposed on opposite sides of the aircraft body 2 as shown in the figure, or only one side can be reserved, which is not limited herein;
  • the device 32 is disposed on the top and/or bottom of the substrate 31 such that when the substrate 31 is rotated about the center 1 of the aircraft body 2, a planar circular illumination region is integrally formed by controlling the illumination and color of the plurality of light source devices 32.
  • the change utilizes the visual persistence characteristics of the human eye to make the aircraft as a whole planar display panel.
  • the body when the substrate 31 rotates around the center 1 of the aircraft body 2, according to the visual persistence characteristic of the human eye, the body can form a three-dimensional light-emitting area, and a planar light-emitting area can also be formed, wherein the three-dimensional light-emitting area can be a rule. Or two kinds of irregularities, which may be closed or semi-closed, and all of the above forms are within the scope of protection of the present application.
  • the substrate 31 is a flexible printed circuit board (Flexible Printed Circuit, referred to as FPC), may also be other material substrates, which are not limited herein; the light source device 32 is disposed on the flexible circuit board; of course, the connection between the light source device 32 and the flexible circuit board may be solder or other forms, here Nor is it the only limit.
  • FPC Flexible Printed Circuit
  • the plurality of light source devices 32 can emit light of the same color or light of different colors, wherein each of the light source devices 32 can emit light of a single color or light of multiple colors, so that On the basis of a single light-emitting device emitting light of different colors, combining a plurality of light-emitting devices together will produce more unexpected effects, thereby conveying more abundant and personalized pattern text information, and therefore, the specific light source device 32 itself emits light.
  • the principle and color composition of the light source device 32 are not exclusively defined herein; obviously, by providing the light source devices 32 of different color combinations, the substrate 31 can be made richer and more cool when rotated around the center 1 of the aircraft body 2. The visual effects optimize the configuration of a single aircraft, enhancing the functional diversity, practical value and user experience of the aircraft.
  • the light source device 32 is a light emitting diode. It should be noted that the light source device 32 can be a single LED light bead, or an integrated Led light bar, and the specific light source device 32 type and different types. The corresponding form of the light source device 32 mounted on the substrate 31 is not limited herein.

Abstract

一种自旋式发光飞行器，包括飞行器本体（2）和至少一个螺旋单元，螺旋单元能够使得飞行器本体（2）绕该飞行器本体（2）的中心（1）旋转，上述至少一个螺旋单元包括旋翼（4）和用于驱使旋翼（4）转动的电机，自旋式发光飞行器还包括发光装置（3），通过将发光装置（3）与飞行器本体（2）连接固定，使得发光装置（3）能够在飞行器本体（2）旋转的同时绕飞行器本体（2）的中心（1）旋转，进而通过控制发光装置（3）的亮灭和颜色变化，利用人眼的视觉暂留特性，使得发光装置（3）显示传达自定义的预设信息，这样人们在利用飞行器显示传达信息时，无需组合使用多架，使用一架飞行器即可。

Description

自旋式发光飞行器 技术领域
本申请涉及飞行器领域，尤其涉及一种自旋式发光飞行器。
 背景技术
近年来，飞行器技术向着高效、智能化和多功能化的方向飞速发展，其被广泛应用于军事、海洋、农业、影像采集以及科学研究等多个领域；在日常生活中，越来越多的人开始关注飞行器技术，并把操控飞行器作为业余消遣的活动之一。常见的旋翼式飞行器中无论是单旋翼式还是多旋翼式，均需要通过调节旋翼电机转速来实现竖直方向升力的变化，从而控制飞行器的姿态和位置，且在飞行器工作过程中必须尽量消除自旋现象，避免其因空气反扭力作用而产生陀螺效应；另外，现有的旋翼式飞行器大多不具备发光功能，进而限制其无法依靠自身结构实现传达信息以及显像的目的；因此，关于旋翼式飞行器的更多功能及优势有待进一步发掘。
 技术问题
本申请的目的在于提供一种自旋式发光飞行器，旨在解决现有技术中的旋翼式飞行器因传统结构及控制模式的限制，无法单独利用本体结构传达信息或者显像的技术问题。
 技术解决方案
本申请提出的一种自旋式发光飞行器，包括飞行器本体和能够使得所述飞行器本体绕所述飞行器本体的中心旋转的至少一个螺旋单元，至少一个所述螺旋单元包括旋翼和用于驱使所述旋翼转动的电机；所述自旋式发光飞行器还包括在所述飞行器本体旋转时绕所述飞行器本体的中心旋转的发光装置，所述发光装置与所述飞行器本体连接固定。
进一步地，所述发光装置包括基板和设置在所述基板上的多个光源器件，所述基板通过支撑条与所述飞行器本体连接固定。
进一步地，所述基板呈圆环状，所述支撑条连接在所述基板的内缘与所述飞行器本体之间。
进一步地，所述基板具有一缺口。
进一步地，所述基板呈多边形框状，所述支撑条连接在所述基板的内缘与所述飞行器本体之间。
进一步地，所述自旋式发光飞行器具有两个基板，两个所述基板垂直设置，所述支撑条连接在两个所述基板的内缘与所述飞行器本体之间。
进一步地，所述支撑条包括第一支撑条和第二支撑条，所述第一支撑条从所述基板的内缘径向延伸至所述飞行器本体的顶部和底部，所述第二支撑条从所述基板的内缘径向延伸至所述飞行器本体的侧壁部；所述支撑条与所述基板一体成型，所述支撑条与所述飞行器本体可拆卸连接。
进一步地，多个所述光源器件沿所述基板的整个周向布设。
进一步地，所述飞行器本体在绕所述飞行器本体的中心旋转时构成一旋转面，所述旋转面与所述基板所在的平面正交。
进一步地，所述飞行器本体与所述基板之间设有加强筋。
进一步地，所述发光装置包括基板和设置在所述基板上的多个光源器件，所述基板呈直板状且一端与所述飞行器本体连接。
进一步地，所述基板为柔性电路板，所述光源器件设置在所述柔性电路板上。
进一步地，所述光源器件为发光二极管。
 有益效果
本申请提供的自旋式发光飞行器的有益效果在于：包括飞行器本体和至少一个螺旋单元，螺旋单元能够使得飞行器本体绕该飞行器本体的中心旋转，且上述至少一个螺旋单元包括旋翼和用于驱使旋翼转动的电机，通过调节电机使得每个旋翼的转动方向单独可调，以实现飞行器本体绕其中心自旋的目的；自旋式发光飞行器还包括发光装置，通过将发光装置与飞行器本体连接固定，使得发光装置能够在飞行器本体旋转的同时绕飞行器本体的中心旋转，进而通过控制发光装置的亮灭和颜色变化，利用人眼的视觉暂留特性，使得发光装置显示传达自定义的预设信息；这样，人们在利用飞行器显示传达信息时，无需组合使用多架，使用一架飞行器即可，在降低了飞行器购置成本的同时，优化了单个飞行器的配置，提升了飞行器的功能多样性、实用价值以及用户体验。
 附图说明
为了更清楚地说明本申请实施例中的技术方案，下面将对实施例或现有技术描述中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本申请的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动性的前提下，还可以根据这些附图获得其他的附图。
图1是本申请第一实施例提供的自旋式发光飞行器的立体示意图一；
图2为本申请第一实施例提供的自旋式发光飞行器的立体示意图二；
图3为本申请第二实施例提供的自旋式发光飞行器的立体示意图；
图4为本申请第三实施例提供的自旋式发光飞行器的立体示意图；
图5为本申请第四实施例提供的自旋式发光飞行器的立体示意图；
图6为本申请第五实施例提供的自旋式发光飞行器的立体示意图；
图7为本申请第六实施例提供的自旋式发光飞行器的立体示意图；
图8为本申请第七实施例提供的自旋式发光飞行器的立体示意图。
其中，图中各附图标记：
1—中心、2—飞行器本体、3—发光装置、4—旋翼、31—基板、5—加强筋、32—光源器件、33—支撑条、331—第一支撑条、332—第二支撑条、10—旋转面。
 本发明的实施方式
下面详细描述本申请的实施例，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，旨在用于解释本申请，而不能理解为对本申请的限制。
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一个或者更多个该特征。
在本申请中，除非另有明确的规定和限定，术语 “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；可以是机械连接，也可以是电连接；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。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申请中的具体含义。
实施例一
如图1和图2所示，本实施例提供的一种自旋式发光飞行器，包括飞行器本体2和至少一个螺旋单元（图中未示出），螺旋单元能够使得飞行器本体2绕该飞行器本体2的中心1旋转，此处的飞行器本体2的中心1定义为飞行器本体2自旋时环绕着的且位于飞行器本体2内部的一点；上述至少一个螺旋单元包括旋翼4和用于驱使旋翼4转动的电机（图中未示出），通过调节电机使得每个旋翼4的转动方向单独可调，以实现飞行器本体2绕其中心1自旋的目的；自旋式发光飞行器还包括发光装置3，通过将发光装置3与飞行器本体2连接固定，使得发光装置3能够在飞行器本体2旋转的同时绕飞行器本体2的中心1旋转，进而通过控制发光装置3的亮灭和颜色变化，利用人眼的视觉暂留特性，使得发光装置3显示传达自定义的预设信息；这样，人们在利用飞行器显示传达信息时，无需组合使用多架，使用一架飞行器即可，在降低了飞行器购置成本的同时，优化了单个飞行器的配置，提升了飞行器的功能多样性、实用价值以及用户体验。
需要说明的是，自旋式发光飞行器的旋翼4包括第一旋翼组（图中未示出）和第二旋翼组（图中未示出），当第一旋翼组和第二旋翼组旋向互为相反时，若第一旋翼组旋向为顺时针（逆时针），那么飞行器本体2顺时针自旋即通过同时增加（减小）第一旋翼组的控制电机转速且同时减小（增加）第二旋翼组的控制电机转速来实现，为了维持整机的总升力，转速增加的升力要补偿转速减小的升力，通过调节第一旋翼组的控制电机和第二旋翼组的控制电机的转速差实现控制飞行器本体2和发光装置3的自旋速度，极限情况下，第一旋翼组和第二旋翼组旋向达到相同；飞行器本体2内可设置平衡保护装置（图中未示出），当自旋式发光飞行器的自旋速度超出某一预设值时，该平衡保护装置将被启动，用以保证飞行器本体2和发光装置3的平稳自旋。
在本申请的一个实施例中，发光装置3包括基板31和设置在基板31上的多个光源器件32，基板31通过支撑条33与飞行器本体2连接固定，即保证了发光装置3在绕飞行器本体2的中心1旋转时的结构稳定性；实际上，基板31和支撑条33的形状、位置以及数量等均不限定，具体地，请参照以下不同实施例。
可选地，基板31呈圆环状，支撑条33连接在基板31的内缘与飞行器本体2之间；基板31自旋时，根据人眼的视觉暂留特性，基板31外侧形成一球面，球面上可显示预设的图案或文字，不仅视觉上较为美观，且圆环状基板31形状简单，易于加工制造；此时，支撑条33的位置具有多种形式，具体请参照图1和图2。
实施例二
下面结合附图3仅就与前述实施例中不同之处作详细说明。
可选地，基板31为具有一缺口，即基板31可为封闭式结构，也可为半封闭式结构，例如基板31为1/2圆弧或1/4圆弧状的环形板，此处不作唯一限定；此时，基板31自旋时基板31外侧形成半球状面，同样可实现信息的显示功能，且节约了材料和加工成本；另外，支撑件只要能够保证基板31与飞行器本体2的相对位置稳定可靠即可，具体位置此处不作唯一限定。
实施例三
下面结合附图4仅就与前述实施例中不同之处作详细说明。
可选地，基板31呈多边形框状，例如四边形框状，支撑条33连接在基板31的内缘与飞行器本体2之间；基板31在绕飞行器本体2的中心1旋转时，其外侧可形成一圆柱面，通过在基板31的四周均设置光源器件32，使得上述圆柱面的顶面、底面以及侧面均可显示信息，这样，通过巧妙地布置和控制光源器件32，即可呈现出令人意想不到的效果；当然，基板31还可设置为五边环、六边环甚至八边环，边数不限奇偶，具体边数此处不作唯一限定；同样地，支撑件只要能够保证基板31与飞行器本体2的相对位置稳定可靠即可，具体位置此处亦不作唯一限定。
实施例四
下面结合附图5仅就与前述实施例中不同之处作详细说明。
可选地，自旋式发光飞行器具有两个基板31，两个基板31垂直设置，支撑条33连接在两个基板31的内缘与飞行器本体2之间；当然，基板31的数量也可为更多个，具体此处不作唯一限定，且自旋式发光飞行器包括至少一个螺旋单元，实施例中虽以双旋翼和四旋翼为例，但不能用以限定螺旋单元的数量；通过多个基板31的组合，不仅能够展示更加复杂和炫酷的视觉效果，同时，有利于使得整个结构更加稳固，降低其受损率，延长了自旋式发光飞行器的使用寿命。
实施例五
下面结合附图6仅就与前述实施例中不同之处作详细说明。
在本申请的一个实施例中，支撑条33包括第一支撑条331和第二支撑条332，第一支撑条331从基板31的内缘径向延伸至飞行器本体2的顶部和底部，第二支撑条332从基板31的内缘径向延伸至飞行器本体2的侧壁部；支撑条33与基板31一体成型，支撑条33与飞行器本体2可拆卸连接；通过增加支撑条33的数量，有利于保证基板31与飞行器本体2的相对位置稳定可靠；当然，支撑条33与基板31之间也可以设置为可拆卸连接，支撑条33与飞行器本体2也可一体成型，其中，可拆卸连接方式可为螺纹连接或卡扣连接等，一体成型方式如焊接或利用模具一体成型等，具体此处均不作唯一限定。
可选地，多个光源器件32沿基板31的整个周向布设，使得基板31在绕飞行器本体2的中心1旋转时形成最大范围的发光区域，当然多个光源器件32也可按照预设呈现的信息和效果选择性地布设在基板31的部分区域，此处不作唯一限定。
可选地，飞行器本体2在绕飞行器本体2的中心1旋转时构成一旋转面10，该旋转面10与基板31所在的平面正交，此时基板31在绕飞行器本体2的中心1旋转时，可形成一规则的立体发光区域；当然，根据需要也可使基板31所在的平面与上述旋转面10设置为非正交，具体角度此处不作唯一限定。
需要说明的是，可在支撑杆与基板31之间设置一电子扭转装置（图中未示出），该电子扭转装置可通过遥控装置控制且用以在基板31绕飞行器本体2的中心1旋转的过程中调节旋转面10与基板31所在的平面之间的夹角，从而使得整个立体发光区域的形状实时可变，加之，外部显示的信息实时可变，进而使得该自旋式发光飞行器能够呈现出更加复杂和炫酷的视觉效果。
实施例六
下面结合附图7仅就与前述实施例中不同之处作详细说明。
在本申请的一个实施例中，飞行器本体2与基板31之间设有加强筋5，当飞行器本体2及发光装置3在高速自旋时会产生的较大的离心力，该结构使得基板31与飞行器本体2之间的连接更加稳定可靠，降低了整体结构的受损率。
实施例七
下面结合附图8仅就与前述实施例中不同之处作详细说明。
可选地，发光装置3包括基板31和设置在基板31上的多个光源器件32，基板31呈直板状且一端与飞行器本体2连接，其中，基板31可沿从飞行器本体2的中心1到飞行器本体2的外部延伸的方向延伸设置，需要说明的是，基板31可如图所示对称设置在飞行器本体2相对两侧，也可只保留其中一侧，此处不作唯一限定；多个光源器件32设置在基板31的顶部和/或底部，使得基板31在绕飞行器本体2的中心1旋转时，整体形成一平面式的圆形发光区域，通过控制多个光源器件32的亮灭和颜色变化，利用人眼的视觉暂留特性，使得飞行器整体成为平面式信息显示面板。
因此，基板31在绕飞行器本体2的中心1旋转时，根据人眼的视觉暂留特性，其本体可形成立体式发光区域，也可形成平面式发光区域，其中，立体式发光区域可为规则或不规则两种，也可为封闭或半封闭两种，以上形式均属于本申请保护的范围。
在本申请的一个实施例中，基板31为柔性电路板（Flexible Printed Circuit，简称FPC），还可为其他材质基板，此处不作唯一限定；光源器件32设置在柔性电路板上；当然，光源器件32与柔性电路板的连接方式可为焊接或其他形式，此处亦不作唯一限定。
需要说明的是，多个光源器件32可发出相同颜色的光，也可发出不同颜色的光，其中，每个光源器件32可发出单一颜色的光，也可发出多种颜色的光，这样，在单个发光器件发出不同颜色的光的基础上，多个发光器件组合在一起将产生更加意想不到的效果，从而传达更加丰富和个性化的图案文字信息，因此，具体的光源器件32本身的发光原理以及光源器件32的颜色组成，此处皆不作为唯一限定；显然地，通过设置不同颜色组合的光源器件32，可使得基板31在绕飞行器本体2的中心1旋转时形成更加丰富和炫酷的视觉效果，优化了单个飞行器的配置，提升了飞行器的功能多样性、实用价值以及用户体验。
在本申请的一个实施例中，光源器件32为发光二极管，需要说明的是，光源器件32可为单个的Led灯珠，也可为集成的Led灯条，具体的光源器件32类型及不同类型光源器件32安装在基板31上的对应形式，此处均不作唯一限定。
以上所述仅为本申请的若干较佳实施例而已，并不用以限制本申请，凡在本申请的精神和原则之内所作的任何修改、等同替换和改进等，均应包含在本申请的保护范围之内。

Claims (13)

  1. 一种自旋式发光飞行器，其特征在于：包括飞行器本体和能够使得所述飞行器本体绕所述飞行器本体的中心旋转的至少一个螺旋单元，至少一个所述螺旋单元包括旋翼和用于驱使所述旋翼转动的电机；所述自旋式发光飞行器还包括在所述飞行器本体旋转时绕所述飞行器本体的中心旋转的发光装置，所述发光装置与所述飞行器本体连接固定。
  2. 根据权利要求1所述的自旋式发光飞行器，其特征在于：所述发光装置包括基板和设置在所述基板上的多个光源器件，所述基板通过支撑条与所述飞行器本体连接固定。
  3. 根据权利要求2所述的自旋式发光飞行器，其特征在于：所述基板呈圆环状，所述支撑条连接在所述基板的内缘与所述飞行器本体之间。
  4. 根据权利要求3所述的自旋式发光飞行器，其特征在于：所述基板具有一缺口。
  5. 根据权利要求2所述的自旋式发光飞行器，其特征在于：所述基板呈多边形框状，所述支撑条连接在所述基板的内缘与所述飞行器本体之间。
  6. 根据权利要求2所述的自旋式发光飞行器，其特征在于：所述自旋式发光飞行器具有两个基板，两个所述基板垂直设置，所述支撑条连接在两个所述基板的内缘与所述飞行器本体之间。
  7. 根据权利要求2~6任一项所述的自旋式发光飞行器，其特征在于：所述支撑条包括第一支撑条和第二支撑条，所述第一支撑条从所述基板的内缘径向延伸至所述飞行器本体的顶部和底部，所述第二支撑条从所述基板的内缘径向延伸至所述飞行器本体的侧壁部；所述支撑条与所述基板一体成型，所述支撑条与所述飞行器本体可拆卸连接。
  8. 根据权利要求7所述的自旋式发光飞行器，其特征在于：多个所述光源器件沿所述基板的整个周向布设。
  9. 根据权利要求7所述的自旋式发光飞行器，其特征在于：所述飞行器本体在绕所述飞行器本体的中心旋转时构成一旋转面，所述旋转面与所述基板所在的平面正交。
  10. 根据权利要求7所述的自旋式发光飞行器，其特征在于：所述飞行器本体与所述基板之间设有加强筋。
  11. 根据权利要求1所述的自旋式发光飞行器，其特征在于：所述发光装置包括基板和设置在所述基板上的多个光源器件，所述基板呈直板状且一端与所述飞行器本体连接。
  12. 根据权利要求8~11任一项所述的自旋式发光飞行器，其特征在于：所述基板为柔性电路板，所述光源器件设置在所述柔性电路板上。
  13. 根据权利要求12所述的自旋式发光飞行器，其特征在于：所述光源器件为发光二极管。
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