WO2015127903A1 - 倾转旋翼直升机 - Google Patents

倾转旋翼直升机 Download PDF

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Publication number
WO2015127903A1
WO2015127903A1 PCT/CN2015/073396 CN2015073396W WO2015127903A1 WO 2015127903 A1 WO2015127903 A1 WO 2015127903A1 CN 2015073396 W CN2015073396 W CN 2015073396W WO 2015127903 A1 WO2015127903 A1 WO 2015127903A1
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fuselage
tail
wing
rotor
helicopter
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PCT/CN2015/073396
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English (en)
French (fr)
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刘世英
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武汉蓝天翔航空科技有限公司
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Publication of WO2015127903A1 publication Critical patent/WO2015127903A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/10—All-wing aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • the present invention relates to a "tilt rotor helicopter" in which two rotors are mounted at both ends of the wing and are rotatable up and down.
  • the rotor rotates upwards, it can take off and land vertically like a normal helicopter; when its rotor is tilted forward by a certain angle, it can take off at a short distance; when it flies into the air, its rotor rotates toward the front horizontal angle.
  • the helicopter can fly like a normal airplane, making it much faster than a normal helicopter, and it is more fuel efficient than a normal helicopter. It belongs to the field of aviation industry technology.
  • the existing "dip-rotor helicopter” in the world is mainly a V-22 Osprey tilt-rotor aircraft. It is a tilt-rotor aircraft jointly designed and manufactured by Bell and Boeing, and is also a medium-sized transport aircraft.
  • the tilting rotorcraft has the advantages of vertical lifting capability of the helicopter and high speed, long range and low fuel consumption of the fixed-wing propeller aircraft.
  • This type of helicopter is widely used in military operations, freight transportation and earthquake relief in the United States.
  • its fuselage is only a container for people's clothing. It relies on the lift generated by the wing and the rotor to lift the aircraft.
  • the handling is very complicated. Compared with the general helicopter, there are many failures. There have been many accidents involving the death of the aircraft. Safety Poor, so there is still a lot of room for improvement.
  • the present invention provides an improved tiltrotor helicopter which is characterized in that the plane of the fuselage is made into a rectangular shape, and each longitudinal section of the fuselage is formed into a cross-sectional shape of the wing so that when it is in the air When flying, the fuselage also produces lift; the fuselage tail is at the end of the fuselage, it can rotate up and down around the back of the fuselage, so the fuselage tail can also be used as a horizontal tail to control the pitch state of the fuselage.
  • the wing is vertically vertical, and is arranged on the hollow flat column on both sides of the arc-shaped top surface of the fuselage so as to have a certain distance from the arc top surface of the fuselage, the wing is extended to both sides, and then
  • the main rotor driven by the turboprop engine is mounted on both ends of the wing. Due to the lift generated by the fuselage, the wing is separated from the fuselage by a certain distance, the flow line is relatively smooth during the flight, and the efficiency of the wing is improved.
  • Figure 1 is a longitudinal sectional view of a fuselage of a "tilt rotor helicopter" of the present invention.
  • Figure 2 is a plan view of the fuselage of the "tilt rotor helicopter" of the present invention.
  • Figure 3 is a cross-sectional view of the fuselage of the "tilt rotor helicopter" of the present invention in a cruising flight in the sky.
  • Figure 4 is a side elevational view of the "tilt rotor helicopter" of the present invention ready for vertical takeoff on the ground.
  • Figure 5 is a side view of the "tilt rotor helicopter" of the present invention prepared for short takeoff on the ground. Figure.
  • Figure 6 is a side elevational view of the "tilt rotor helicopter" of the present invention preparing for long takeoff on the ground.
  • 7 to 9 are front, side and top plan views of the "tilt rotor helicopter" of the present invention.
  • 10 to 12 are front, side and top plan views of the "tilt rotor helicopter" large model (four rotors) of the present invention.
  • the longitudinal section of the fuselage combined with the fuselage 4 and the fuselage tail 12 is a cross-sectional shape of the airfoil, so that the fuselage can generate lift during flight.
  • the vertical body 4 of the wing 18 is placed on the hollow flat column 5 on both sides of the top of the fuselage 4, and has a certain distance from the top of the fuselage 4, so that the wing in the wide range of the fuselage also generates lift, which is equal to the wing.
  • the length has increased, so the wings of the existing tilt-rotor helicopter are extended directly from the fuselage to both sides, increasing the lift.
  • the plane of the fuselage 4 is rectangular, and a radar cabin 1, an instrument panel 2, a cockpit 3, an instrument cabin 20, a passenger cabin 7, a cargo compartment 8 and a fuselage tail 12 are arranged in order from front to back.
  • the fuselage tail 12 is connected with the rotating shaft 11 in the middle of the cargo compartment 8, and the fuselage tail 12 can be turned upside down around the rotating shaft 11, so that it can also be used as a horizontal tail.
  • the vertical body 4 of the wing 18 is placed on the hollow flat column 5 on both sides of the top of the fuselage 4, and the turbine worm engine 17 for driving the rotation of the main rotor 16 is mounted at both ends of the wing 18.
  • Both the passenger compartment 7 and the cargo compartment 8 are provided with a hatch 19 which is mounted at the rear of the fuselage 4.
  • a water surface escape staircase 9 is provided in the cargo compartment 8.
  • Figure 3 shows a cross-sectional view of the fuselage of a "tilt rotor helicopter" in a cruising flight in which the main rotor is horizontally forward.
  • Figure 4 shows a side view of the "tilt rotor helicopter" preparing for vertical takeoff on the ground.
  • the main rotor 16 driven by the turboprop engine 17 is turned to the vertical ground state, rotating upward, and the aircraft takes off vertically, and this state takes off. It is the most fuel-intensive and less efficient.
  • Figure 5 shows a side view of the "tilt rotor helicopter" preparing for short takeoff on the ground. At this time, the main rotor 16 driven by the turboprop engine 17 is rotated to a state of about 45 degrees with the ground.
  • Figure 6 shows a side view of the "tilt rotor helicopter" preparing for long takeoff on the ground.
  • the main rotor 16 driven by the turboprop engine 17 is turned to about 20 degrees with the ground, and the take-off run distance is longer. But this take-off is more fuel efficient.
  • 7 to 9 are front, side and top plan views of the "tilt rotor helicopter" of the present invention.
  • the fuselage 4 and the wing 18 are separated by a certain distance, the airflow in the front flight is relatively smooth, and the wing also generates lift in the wide range of the fuselage, which is directly relative to the wing of the existing tilting rotor helicopter. Mounted on both sides of the fuselage, equal to the length of the wing, so the lift is increased compared to the existing tilt-rotor helicopter.
  • 10 to 12 are front, side and top plan views of a large model of the "tilt rotor helicopter" of the present invention.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Abstract

一种倾转旋翼直升机，包括机身（4）、驾驶舱（3）、客舱（7）、货舱（8）、机身尾（12）、垂尾（10）、起落架（15）、机翼（18）、涡轮蜗轴发动机（17）和主旋翼（16）。该直升机机身（4）和机身尾（12）的组合纵剖面是机翼剖面形状，因此空中飞行时机身也能产生升力。另外机翼（18）安装在机身（4）圆弧形顶面的两侧的中空扁柱（5）上，距离机身（4）一段距离，机翼（18）比同等规模的现有倾转旋翼直升机更长，空中飞行时流线比较平顺，使机翼的效率更高。

Description

倾转旋翼直升机
本申请要求于2014年2月28日提交中国专利局、申请号为201410071052.8、发明名称为“倾转旋翼直升机”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，本申请所引用并包含的其披露的所有相关申请是本申请不可分割的一部分。
技术领域
本发明涉及一种“倾转旋翼直升机”，这种直升机的两个旋翼安装在机翼两端，而且可以上下旋转。当旋翼朝上旋转，它既可以像普通直升机一样垂直起飞和降落；当它的旋翼朝前倾斜一定角度，它可以实现短距起飞；它飞到空中后，其旋翼朝前水平角度旋转，该直升机又可以像普通飞机一样飞翔，使其速度比一般直升机快很多，也相对一般直升机更节约燃油。属于航空工业技术领域。
背景技术
目前世界上现有的“倾转旋翼直升机”主要是V-22鱼鹰式倾转旋翼机，它是由美国贝尔公司和波音公司联合设计制造的一款倾转旋翼机，也是一款中型运输机。倾转旋翼机具备直升机的能垂直升降能力及固定翼螺旋桨飞机较高速、航程较远及耗油量较低的优点。这种直升机被美国广泛运用军事作战、货运和抗震救灾中。但是其机身只是装人装物的容器，全靠机翼和旋翼产生的升力托举飞机；另外操纵很复杂，相对一般直升机故障较多，出现过多次机毁人亡的事故，安全性较差，因此还是有很多的改进空间。
发明内容
为了克服这些缺点，本发明提供了一种改进的倾转旋翼直升机，它的特征是将机身平面做成长方形，且机身的各个纵剖面都做成机翼剖面形状，这样当它在空中飞翔时，机身也产生升力；机身尾在机身最后面，它可以绕机身后部上下旋转，因此机身尾可以兼做水平尾翼来控制机身的俯仰状态。另外将机翼垂直机身，且设在机身圆弧形顶面两侧的中空扁柱上，使之距离机身的圆弧顶面有一定的距离，机翼向两侧伸展，然后将涡轮蜗轴喷气发动机带动的主旋翼安装在机翼两端。由于其机身产生升力，其机翼又离开机身一定距离，空中飞行时流线比较平顺，使机翼的效率有所提高，这两项改进共同作用，使本倾转旋翼直升机比现有的倾转旋翼直升机的性能和效率将有较大的提高。现有的倾转旋翼直升机只有两个主旋翼，本发明的机身扁平，方便做成四个主旋翼的倾转旋翼直升机，使机型可以更大，满足装载更大荷载的功能所需。
附图说明
下面结合附图和实施实例对本发明作进一步的说明。
图1是本发明“倾转旋翼直升机”的机身纵剖面图。
图2是本发明“倾转旋翼直升机”的机身平面图。
图3是是本发明“倾转旋翼直升机”在天上巡航飞行的机身剖面图。
图4是本发明“倾转旋翼直升机”在地面准备垂直起飞的侧视图。
图5是本发明“倾转旋翼直升机”在地面准备短距起飞的侧视 图。
图6是本发明“倾转旋翼直升机”在地面准备长距起飞的侧视图。
图7至图9是本发明“倾转旋翼直升机”的前视、侧视和俯视的外形图。
图10至图12是本发明“倾转旋翼直升机”大机型(四个旋翼)的前视、侧视和俯视的外形图。
图中1、雷达舱，2、仪表盘，3、驾驶舱，4、机身，5、中空扁柱，6、主旋翼转动轴，7、客舱，8、货舱，9、水上逃生楼梯，10、垂尾，11、转轴，12、机身尾，13、卫生间，14、主起落架，15、前起落架，16、主旋翼，17、涡轮蜗轴喷气发动机，18、机翼，19、舱门，20、仪表舱21、燃油箱。
具体实施方式
在本发明的描述中，需要理解的是，术语“中心”、“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。
在本发明的描述中，需要说明的是，除非另有明确的规定和限定，术语“安装”、“相连”、“设置”应做广义理解，例如，可以是固定相连、设置，也可以是可拆卸连接、设置，或一体地连接、设置。 对于本领域的普通技术人员而言，可以具体情况理解上述术语在本发明中的具体含义。
在图1所示的本发明“倾转旋翼直升机”中，机身4和机身尾12组合的机身纵剖面是机翼剖面形状，因此空中飞行时机身能够产生升力。机翼18垂直机身4安放在机身4顶部两侧的中空扁柱5上，距离机身4顶部有一定的距离，这样在机身宽的范围内的机翼也产生升力，等于机翼长度增加了，所以相对现有的倾转旋翼直升机的机翼直接从机身向两侧伸展，增加了升力。
在图2中表示的机身平面图中，机身4平面是长方形，从前向后依次安排有雷达舱1、仪表盘2、驾驶舱3、仪表舱20、客舱7，货舱8和机身尾12，机身尾12与货舱8中间有转轴11相连接，机身尾12可以绕转轴11上下翻转，因此可以兼做水平尾翼。机翼18垂直机身4安放在机身4顶部两侧的中空扁柱5上，机翼18的两端安装了带动主旋翼16旋转的涡轮蜗轴喷气发动机17。客舱7和货舱8都开有舱门19，燃油箱21安装在机身4的最后面。货舱8内设有水面逃生楼梯9。
图3表示了“倾转旋翼直升机”在天上巡航飞行的机身剖面图，此时主旋翼水平朝前。
图4表示了“倾转旋翼直升机”在地面准备垂直起飞的侧视图，此时涡轮蜗轴喷气发动机17带动的主旋翼16转至垂直地面状态，朝上旋转，飞机垂直起飞，这种状态起飞最耗费燃油，效率较低。
图5表示了“倾转旋翼直升机”在地面准备短距起飞的侧视图， 此时涡轮蜗轴喷气发动机17带动的主旋翼16转至与地面呈约45度的状态。
图6表示了“倾转旋翼直升机”在地面准备长距起飞的侧视图，此时涡轮蜗轴喷气发动机17带动的主旋翼16转至与地面呈约20度的状态，起飞滑跑距离更长，但是这样起飞比较节省燃油。
图7至图9是本发明“倾转旋翼直升机”的前视、侧视和俯视的外形图。
从图中可以看出机身4与机翼18之间相隔一段距离，前飞时气流比较顺畅，在机身宽的范围内机翼也产生升力，相对现有倾转旋翼直升机的机翼直接安装在机身两侧，等于机翼长度增加了，所以相对现有的倾转旋翼直升机，升力增加了。
图10至图12是本发明“倾转旋翼直升机”大机型的前视、侧视和俯视的外形图。
因为荷载加重，两个涡轮蜗轴喷气发动机17带主旋翼16旋转产生的升力不够，因此增加一副机翼18、机翼两端再增加两个涡轮蜗轴喷气发动机17带动主旋翼16旋转，这样产生的升力大多了，就可以满足制造大型“倾转旋翼直升机”的功能要求。
尽管已经示出和描述了本发明的实施例，本领域的普通技术人员可以理解：在不脱离本发明的原理和宗旨的情况下可以对这些实施例进行多种变化、修改、替换和变型，本发明的范围由权利要求及其等同物限定。

Claims (3)

  1. 一种倾转旋翼直升机，它包括机身、驾驶舱、客舱、货舱、机身尾、垂尾、起落架、机翼、涡轮蜗轴发动机和主旋翼有序组合，其特征是：其机身和机身尾的组合纵剖面是机翼剖面形状，且机身尾可以绕机身后部的转轴上下翻转而兼做水平尾翼；机翼垂直机身安放在机身圆弧形顶面两侧的中空扁柱上，距离机身有一段距离；由涡轮蜗轴发动机带动的主旋翼安装在机翼两端，且相对机翼可以上下翻转。
  2. 根据权利要求1所述的一种倾转旋翼直升机，其特征是：机身平面是长方形，从前向后依次安排驾驶舱、客舱、货舱、机身尾，机身和机身尾的组合纵剖面是机翼剖面形状，机身尾可以相对机身绕转轴上下翻转而兼做水平尾翼，垂尾安放在机身后部上方，仅靠机身尾，燃油箱安装在货舱后部。
  3. 根据权利要求1所述的一种倾转旋翼直升机，其特征是：机翼垂直机身安放在机身圆弧形顶面两侧的中空扁柱上，距离机身有一段距离；由涡轮蜗轴发动机带动的主旋翼安装在机翼两端，且相对机翼可以绕主旋翼转动轴上下翻转。
PCT/CN2015/073396 2014-02-28 2015-02-28 倾转旋翼直升机 WO2015127903A1 (zh)

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CN111348196A (zh) * 2019-11-25 2020-06-30 西安空天能源动力智能制造研究院有限公司 一种倾转旋翼机的引气燃烧分布式动力航空发动机
CN113022848A (zh) * 2021-04-18 2021-06-25 上海尚实能源科技有限公司 一种翼载人客机
US20230406504A1 (en) * 2018-12-31 2023-12-21 Jetzero, Inc. Emergency egress in a blended wing body aircraft

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CN103786881A (zh) * 2014-02-28 2014-05-14 武汉蓝天翔航空科技有限公司 倾转旋翼直升机
CN104229130B (zh) * 2014-09-25 2016-08-17 佛山市安尔康姆航空科技有限公司 气动结构四旋翼无人飞行器
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