WO2016000484A1 - 无人直升机的机壳开合系统 - Google Patents

无人直升机的机壳开合系统 Download PDF

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Publication number
WO2016000484A1
WO2016000484A1 PCT/CN2015/077890 CN2015077890W WO2016000484A1 WO 2016000484 A1 WO2016000484 A1 WO 2016000484A1 CN 2015077890 W CN2015077890 W CN 2015077890W WO 2016000484 A1 WO2016000484 A1 WO 2016000484A1
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WIPO (PCT)
Prior art keywords
opening
casing
unmanned helicopter
fuselage
hatch
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PCT/CN2015/077890
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English (en)
French (fr)
Inventor
赵曙光
齐勇
高宏伟
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天津曙光敬业科技有限公司
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Priority claimed from CN201410315372.3A external-priority patent/CN104058087B/zh
Priority claimed from CN201420368372.5U external-priority patent/CN203958602U/zh
Application filed by 天津曙光敬业科技有限公司 filed Critical 天津曙光敬业科技有限公司
Publication of WO2016000484A1 publication Critical patent/WO2016000484A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B64D33/10—Radiator arrangement

Definitions

  • the invention relates to the technical field of unmanned helicopters, in particular to a casing opening and closing system of an unmanned helicopter.
  • Unmanned rotor helicopters are widely used in civil and military fields due to their adaptability to weather, such as aerial photography, high-altitude overhead lines, and line inspections.
  • unmanned helicopters encounter special work. Under the circumstances, it takes a long time to hover, the unmanned helicopter can not rely on high-speed movement for natural air cooling, the internal temperature rises, it is easy to make the engine overheat and malfunction, and even cause the unmanned helicopter to crash, resulting in huge economic losses.
  • the invention is directed to the current unmanned helicopter heat sink, the heat dissipation efficiency is low, the engine temperature is slow, and the failure rate is still high.
  • the casing opening and closing system of the unmanned helicopter is designed.
  • the casing opening and closing system of the unmanned helicopter of the present invention including the casing, the engine, the rotor, the tail pipe, one end of the engine and the tail pipe are installed in the casing, and the casing opening and closing system includes the setting The hatch at the upper part of the casing, the opening and closing cover and the retractor mounted on the hatch, the opening and closing cover is connected to the casing through a hinge, the retractor is installed in the outer casing, and is connected with the opening and closing cover to control the opening and closing cover Open and close the hatch.
  • the retractor comprises a base, a swing rod, a connecting rod, a slider, a screw, a motor, the screw is rotatably mounted in the base, the slider is mounted on the screw by a screw connection, and the motor is mounted on the base
  • the inner part of the swing rod is hinged in the base, and the outer end of the swing rod is connected with the opening and closing cover through a connecting rod, and the outer end of the sliding rod is located in the swinging driving groove provided at the inner end of the swing rod.
  • a linear guide rail is further mounted in the base, and the inner end of the slider is slidably mounted on the linear guide rail, and the linear guide rail is parallel to the screw.
  • the main shaft of the motor is coaxially connected with the screw, and the limited position wheel is further mounted on the main shaft, and the limiting wheel is located in the limiting slot provided by the base.
  • the opening and closing cover is provided with two, which are respectively installed on the left and right sides of the hatch.
  • a baffle is further mounted in the casing, and the deflector is inclined.
  • the utility model has the beneficial effects that the casing opening and closing system of the unmanned helicopter introduces the downward swirling airflow of the high-speed rotary compression of the rotor into the casing by using the hatch provided at the upper part of the casing, and directly uses the downward swirling airflow to take the inside of the casing.
  • the heat is taken away and the heat dissipation efficiency is high, so that the engine located in the casing is cooled rapidly, the engine failure rate is reduced, the possibility of an unmanned helicopter crash is reduced, and unnecessary economic loss is avoided.
  • the opening and closing cover installed on the hatch is controlled by the retractor, which can open the hatch when it needs to use the downward swirling airflow to ensure the heat dissipation effect.
  • the hatch is closed when the helicopter is only required to move at a high speed, and the cooling is achieved by natural air cooling.
  • the purpose is to avoid the opening and closing cover to increase the flight resistance and the flexibility of use.
  • the slider and the screw of the retractor constitute a screw structure, which has high reliability, smooth motion and high precision, and high transmission efficiency, so that the small torque of the motor makes the slider get a large thrust, so that the slider is enough to swing the swing rod
  • the pendulum rod opens and closes the opening and closing cover which is subjected to large wind resistance through the connecting rod, and also controls the position of the sliding movement to prevent the opening and closing of the opening and closing cover from being insufficient, and prevents the sliding block from the swinging driving groove. Disengage in the middle to avoid damage to the opening and closing system.
  • the slider is also mounted on the linear guide rail, so that the linear guide rail and the screw jointly guide the movement of the slider, thereby further improving the smoothness of the slider movement.
  • the installed limit wheel can avoid the axial movement of the screw, ensure the accuracy of the movement of the slider, and avoid the opening or opening of the opening and closing cover due to the deviation of the position of the slider.
  • the opening and closing cover is provided with two, in a split-type setting, which reduces the weight of each opening and closing cover, thereby reducing the resistance and the required power when the opening and closing cover is opened and closed, and improving the opening and closing of the opening and closing cover.
  • Speed and in the case of the size of the hatch, reduce the width of each opening and closing cover, thereby increasing the distance between the edge and the rotor when the opening and closing cover is opened, preventing the rotor from hitting the opening and closing cover and avoiding damage to the rotor A crash occurred.
  • the deflector mounted on the casing guides the airflow into the casing to the engine, further increasing the speed at which the airflow carries away heat from the engine.
  • 1 is an overall structural view of a casing opening and closing system of the unmanned helicopter.
  • Figure 2 is a partial enlarged view of a portion A of Figure 1.
  • Figure 3 is a view showing the internal structure of the retractor when the hatch is opened.
  • Figure 4 is a view showing the internal structure of the retractor when the hatch is closed.
  • the unmanned helicopter includes a casing 1, an engine 2, a rotor 3, a tail pipe 4, and one end of the engine 2 and the tail pipe 4 are installed at In the casing 1.
  • the cabinet opening and closing system includes a hatch 5 provided at an upper portion of the cabinet 1, an opening and closing cover 6 mounted on the hatch 5, and a retractor 7.
  • the opening and closing cover 6 is connected to the casing 1 through a hinge, and the opening and closing cover 6 is provided with two, which are respectively installed on the left and right sides of the hatch 5, so that the two opening and closing covers 6 are disposed in a split manner.
  • the retractor 7 is mounted in the outer casing 1 for controlling the opening and closing cover 6 to open and close the hatch 5.
  • the retractor 7 includes a base 8, a swing rod 9, a connecting rod 10, a slider 11, a screw 12, and a motor 13.
  • the screw 12 is rotatably mounted in the base 8, and the slider 11 is mounted on the screw 12 by a screw connection.
  • the slider 11 and the screw 12 constitute a screw mechanism.
  • the motor 13 is mounted in the base 8 and drives the screw 12 to rotate.
  • the inner end of the swing rod 9 is hinged in the base 8, and the outer end of the swing rod 9 passes through the connecting rod 10 and The opening and closing cover 6 is connected, and the outer end of the slider 11 is located in the swing driving groove 14 provided at the inner end of the swinging rod 9.
  • a linear guide 15 is also mounted in the base 8, and the inner end of the slider 11 is slidably mounted on the linear guide 15, and the linear guide 15 is parallel to the screw 12.
  • the main shaft of the motor 13 is coaxially connected with the screw 12, and a limit wheel 16 is also mounted on the main shaft.
  • the limit wheel 16 is located in the limiting slot 17 provided by the base 8.
  • a deflector 18 is also mounted in the casing 1, and the deflector 18 is disposed obliquely.
  • the swing lever 9 of the retractor 7 When the hatch 5 is in the closed state, as shown in FIG. 4, the swing lever 9 of the retractor 7 is in a state of being perpendicular to the base 8.
  • the motor 13 drives the screw 12 to rotate, the rotating screw 12 slides the slider 11 downward, and the moving slider 11 pushes the side wall of the lower side of the swing drive groove 14, outside the swing lever 9. The end swings upward, causing the swing lever 9 to push the opening and closing cover 6 through the connecting rod 11, and the hatch 5 is opened.
  • the airflow generated by the rotor 3 enters the casing 1 from the hatch 5. Since the deflector 18 is high and low, the deflector 18 is guided by the airflow of the hatch 5 into the casing 1 to the cabin.
  • the engine on the front side of the port 5 allows the airflow to come into contact with the engine 2 as much as possible, removes heat, and finally flows out from some openings in the lower portion of the casing 1.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Power-Operated Mechanisms For Wings (AREA)

Abstract

一种无人直升机的机壳开合系统，无人直升机包括机壳、马达、旋翼、尾管，马达和尾管的一头都安装在机壳中，所述的机壳开合系统包括设置在机壳上部的舱口、安装在舱口上的开合盖、收放器，开合盖通过铰链与机壳相连，收放器安装在外壳内，并与开合盖连接，控制开合盖打开和关闭舱口。无人直升机的机壳开合系统利用设置在机壳上部的舱口将旋翼高速旋转压缩的下旋气流引入到机壳内，直接利用下旋气流将机壳内的热量带走，散热效率高，使位于机壳内的马达迅速降温，降低马达的故障率，减小无人直升机坠毁的可能，避免不必要的经济损失。

Description

无人直升机的机壳开合系统 技术领域
本发明涉及无人直升机技术领域，具体涉及一种无人直升机的机壳开合系统。
背景技术
无人驾驶的旋翼直升机由于天气适应能力强，广泛应用在民用和军用领域，进行例如航拍、高空架线、线路巡查等作业，但无人直升机在实际使用的过程中，在遇到特殊的工况下，需要长时间悬停，无人直升机无法依靠高速移动进行自然风冷，内部温度上升，容易使发动机过热而发生故障，甚至造成无人直升机的坠毁，产生巨大的经济损失。
在先专利《带有发动机散热罩的无人直升机》申请号：201310635702.2虽然一定程度上解决了上述的技术问题，但仍然存在较大缺陷，只利用散热罩的散热网眼进行散热，散热效率较低，依然无法快速的将发动机的热量撒发出去，发动机的温度依然较高，发生故障的概率也依然较大。
发明内容
本发明针对目前的无人直升机散热装置，散热效率低，发动机温度下降的速度慢，故障率仍然较高等问题，设计了一种无人直升机的机壳开合系统。
本发明的无人直升机的机壳开合系统，无人直升机包括机壳、发动机、旋翼、尾管，发动机和尾管的一头都安装在机壳中，所述的机壳开合系统包括设置在机壳上部的舱口、安装在舱口上的开合盖、收放器，开合盖通过铰链与机壳相连，收放器安装在外壳内，并与开合盖连接，控制开合盖打开和关闭舱口。
优选的是，所述收放器包括基座、摆杆、连杆、滑块、螺杆、电机，螺杆可旋转的安装在基座内，滑块通过螺纹连接安装在螺杆上，电机安装在基座内并驱动螺杆旋转，摆杆的内端铰接在基座内，摆杆的外端通过连杆与开合盖相连，滑块的外端位于摆杆的内端设置的摆动驱动槽中。
优选的是，基座内还安装有直线导轨，滑块的内端滑动安装在直线导轨上，直线导轨与螺杆平行。
优选的是，电机的主轴与螺杆同轴连接，主轴上还安装有限位轮，限位轮位于基座设置的限位槽中。
优选的是，开合盖设置有两个，分别安装在舱口的左右两侧。
优选的是，机壳内还安装有导流板，导流板倾斜设置。
本发明的有益效果是：无人直升机的机壳开合系统利用设置在机壳上部的舱口将旋翼高速旋转压缩的下旋气流引入到机壳内，直接利用下旋气流将机壳内的热量带走，散热效率高，使位于机壳内的发动机迅速降温，降低发动机的故障率，减小无人直升机坠毁的可能，避免不必要的经济损失。
舱口上安装的开合盖，由收放器控制，可在需要利用下旋气流散热时将舱口打开，保证散热效果，在只需要直升机高速移动时将舱口关闭，由自然风冷达到冷却目的，避免打开的开合盖增加飞行阻力，使用灵活度高。
收放器的滑块和螺杆组成丝杠结构，可靠性高，运动平稳且精度高，传动效率高，使电机较小的扭矩使滑块得到较大的推力，让滑块足够拨动摆杆，使摆杆通过连杆将受到较大风阻的开合盖打开和关闭，还使滑块运动的位置可控，避免开合盖过渡打开或者打开的不够，还可防止滑块从摆动驱动槽中脱出，避免开合系统的损坏。
滑块还安装在直线导轨上，使直线导轨与螺杆共同对滑块的运动形成导向作用，进一步提高了滑块运动的平稳性。
安装的限位轮可避免螺杆发生轴向运动，保证滑块运动到位的准确性，避免因滑块运动位置偏差造成开合盖过渡打开或者打开的不够。
开合盖设置两个，呈对开式设置，减小了每个开合盖的重量，从而降低开合盖打开和关闭时的阻力以及所需要的动力，提高了开合盖打开和关闭的速度，而且在舱口大小确定的情况下，减小每个开合盖的宽度，从而增大开合盖打开时其边缘与旋翼之间的距离，防止旋翼碰到开合盖，避免旋翼损坏发生坠毁事故。
机壳倾斜安装的导流板，将进入机壳内的气流引导向发动机，进一步提高气流带走发动机热量的速度。
附图说明
附图1为本无人直升机的机壳开合系统的整体结构图。
附图2为图1的A部分的局部放大图。
附图3为舱口打开时的收放器内部结构图。
附图4为舱口关闭时的收放器内部结构图。
具体实施方式
本发明的无人直升机的机壳开合系统，如图1至4所示，无人直升机包括机壳1、发动机2、旋翼3、尾管4，发动机2和尾管4的一头都安装在机壳1中。
机壳开合系统包括设置在机壳1上部的舱口5、安装在舱口5上的开合盖6、收放器7。
开合盖6通过铰链与机壳1相连，开合盖6设置有两个，分别安装在舱口5的左右两侧，使两个开合盖6呈对开式设置。
收放器7安装在外壳1内，用于控制开合盖6打开和关闭舱口5。
收放器7包括基座8、摆杆9、连杆10、滑块11、螺杆12、电机13，螺杆12可旋转的安装在基座8内，滑块11通过螺纹连接安装在螺杆12上，滑块11和螺杆12组成丝杠机构，电机13安装在基座8内并驱动螺杆12旋转，摆杆9的内端铰接在基座8内，摆杆9的外端通过连杆10与开合盖6相连，滑块11的外端位于摆杆9的内端设置的摆动驱动槽14中。
基座8内还安装有直线导轨15，滑块11的内端滑动安装在直线导轨15上，直线导轨15与螺杆12平行。
电机13的主轴与螺杆12同轴连接，主轴上还安装有限位轮16，限位轮16位于基座8设置的限位槽17中。
机壳1内还安装有导流板18，导流板18倾斜设置。
当舱口5处于关闭状态时，如图4所示，收放器7的摆杆9处于相对于基座8垂直的状态。当要将舱口5打开时，电机13驱动螺杆12旋转，旋转的螺杆12使滑块11向下滑动，移动的滑块11推挤摆动驱动槽14下侧的侧壁，摆杆9的外端向上摆动，使摆杆9通过连杆11推动开合盖6，将舱口5打开。
舱口5打开后，旋翼3产生的气流从舱口5进入到机壳1内，由于导流板18后高前低，导流板18由舱口5进入机壳1的气流引导向位于舱口5前侧的发动机，让气流尽可能的与发动机2接触，带走热量，最后从机壳1下部的一些开口流出。
当舱口5完全打开时，收放器7处于如图3所示状态，收放器7的摆杆9运行到相对于基座8平行的状态。当要将舱口5关闭时，只需要反转电机13，让滑块11向上滑动，滑块11推挤摆动驱动槽14上侧的侧壁，摆杆9的外端向下摆动，使摆杆9通过连杆11拉动开合 盖6，将舱口5关闭。

Claims (6)

  1. 一种无人直升机的机壳开合系统，无人直升机包括机壳(1)、发动机(2)、旋翼(3)、尾管(4)，发动机(2)和尾管(4)的一头都安装在机壳(1)中，其特征在于，所述的机壳开合系统包括设置在机壳(1)上部的舱口(5)、安装在舱口(5)上的开合盖(6)、收放器(7)，开合盖(6)通过铰链与机壳(1)相连，收放器(7)安装在外壳(1)内，并与开合盖(6)连接，控制开合盖(6)打开和关闭舱口(5)。
  2. 根据权利要求1所述的无人直升机的机壳开合系统，其特征在于，所述收放器(7)包括基座(8)、摆杆(9)、连杆(10)、滑块(11)、螺杆(12)、电机(13)，螺杆(12)可旋转的安装在基座(8)内，滑块(11)通过螺纹连接安装在螺杆(12)上，电机(13)安装在基座(8)内并驱动螺杆(12)旋转，摆杆(9)的内端铰接在基座(8)内，摆杆(9)的外端通过连杆(10)与开合盖(6)相连，滑块(11)的外端位于摆杆(9)的内端设置的摆动驱动槽(14)中。
  3. 根据权利要求2所述的无人直升机的机壳开合系统，其特征在于，基座(8)内还安装有直线导轨(15)，滑块(11)的内端滑动安装在直线导轨(15)上，直线导轨(15)与螺杆(12)平行。
  4. 根据权利要求2所述的无人直升机的机壳开合系统，其特征在于，电机(13)的主轴与螺杆(12)同轴连接，主轴上还安装有限位轮(16)，限位轮(16)位于基座(8)设置的限位槽(17)中。
  5. 根据权利要求1所述的无人直升机的机壳开合系统，其特征在于，开合盖(6)设置有两个，分别安装在舱口(5)的左右两侧。
  6. 根据权利要求1所述的无人直升机的机壳开合系统，其特征在于，机壳(1)内还安装有导流板(18)，导流板(18)倾斜设置。
PCT/CN2015/077890 2014-07-03 2015-04-30 无人直升机的机壳开合系统 WO2016000484A1 (zh)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
CN201410315372.3 2014-07-03
CN201410315372.3A CN104058087B (zh) 2014-07-03 2014-07-03 无人直升机的机壳开合系统
CN201420368372.5U CN203958602U (zh) 2014-07-03 2014-07-03 无人直升机的机壳开合系统
CN201420368372.5 2014-07-03

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Cited By (2)

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Publication number Priority date Publication date Assignee Title
CN113270263A (zh) * 2021-06-14 2021-08-17 江苏宏安变压器有限公司 易于控制散热的scb18型节能干式变压器设备
CN117302585A (zh) * 2023-11-28 2023-12-29 中影智能技术发展（福建）有限公司 一种纵列式双翼载重型无人直升机

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