WO2017036080A1 - 伞降自转旋翼机及其制造方法 - Google Patents

伞降自转旋翼机及其制造方法 Download PDF

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Publication number
WO2017036080A1
WO2017036080A1 PCT/CN2016/072100 CN2016072100W WO2017036080A1 WO 2017036080 A1 WO2017036080 A1 WO 2017036080A1 CN 2016072100 W CN2016072100 W CN 2016072100W WO 2017036080 A1 WO2017036080 A1 WO 2017036080A1
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parachute
rotor
disposed
fuselage
rotorcraft
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PCT/CN2016/072100
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English (en)
French (fr)
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陶亮
申守健
秦立新
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河南三和航空工业有限公司
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Publication of WO2017036080A1 publication Critical patent/WO2017036080A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/02—Gyroplanes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof

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  • the present application relates to the field of aircraft technology, and in particular to a parachute rotation rotorcraft and a method thereof.
  • the self-rotating rotorcraft is a rotor-type aircraft with a rotating rotor as a lifting surface and a propeller as a forward power.
  • the self-rotating rotorcraft is actually an aircraft between the helicopter and the fixed-wing aircraft. It removes the rotor and also has a pair of propellers to provide forward power.
  • the biggest difference between a rotary rotorcraft and a helicopter is that the rotor of the rotary rotorcraft is not connected to the engine transmission system.
  • the engine only drives the propeller to provide forward thrust to the aircraft, but during the flight of the rotorcraft, the rotor is rotated by the forward airflow. Generate lift.
  • the helicopter's rotor is connected to the engine's transmission system, which produces both lift and flight power. Since the rotor of the self-rotating rotorcraft is self-rotating and the torque transmitted to the fuselage is small, the self-rotating rotorcraft does not require a tail rotor like a helicopter, but is generally equipped with a tail rudder to control the flight attitude.
  • the present application discloses a parachute-rotating rotorcraft with good stability and high work safety factor and equipped with a parachute of a whole machine.
  • the technical scheme is as follows: an umbrella-falling self-rotating rotorcraft, characterized in that it comprises : fuselage, rotor device, propeller device and parachute device, among them,
  • the airframe includes a cabin and a rudder, a control system is disposed at a front end of the cockpit, an engine is disposed at a rear end of the cockpit, and a landing gear is further disposed under the fuselage;
  • the rotor device is disposed at the top of the fuselage, and includes a rotor head and a rotor blade symmetrically disposed around the rotor head;
  • the propeller device is disposed at a tail portion of the cabin, and is connected to the engine through a gear box;
  • the parachute device is disposed above the rotor head, and includes a whole machine parachute, a storage compartment for accommodating the whole machine parachute, and an ejector for opening the umbrella.
  • control system includes an operation panel, a joystick, and an emergency trigger handle.
  • the emergency trigger handle is used to control the opening of the whole machine parachute.
  • the joystick is coupled to the rotor head by a connecting rod.
  • the number of the rotor blades is two or more.
  • the present application also discloses a method for a parachute rotation rotorcraft, which comprises the following steps:
  • parachute-rotating rotorcraft Configuring the parachute-rotating rotorcraft to include a fuselage, a rotor device, a propeller device, and a parachute device, wherein
  • the fuselage is provided with a cabin and a rudder, a control system is disposed at a front end of the cockpit, an engine and a propeller are disposed at a rear end of the cockpit, and a landing gear is disposed under the fuselage;
  • the parachute device is disposed above the rotor head and is configured to include a complete parachute, a storage compartment for accommodating the complete parachute, and an ejector for parachute.
  • the method further includes: setting the control system as an operation panel, a joystick, and an emergency trigger handle.
  • the method further includes: using the emergency trigger handle to control opening of the whole machine parachute.
  • the method further includes: connecting the joystick to the rotor head through a connecting rod.
  • the method further includes: setting the number of the rotor blades to two or more.
  • the takeoff and landing distance is short: the rotary rotorcraft has a distinctive feature, that is, its landing run The distance is much shorter than the take-off distance, and even if it is well maneuvered, it can land without landing.
  • high stability, strong wind resistance the stability of the rotorcraft is the highest in all aircraft, it can be automatically adjusted, so that the fuselage has good pitch stability, roll stability and speed stability.
  • the biggest advantage of a rotary rotorcraft unlike other aircraft is its high wind resistance, and it also likes wind when it takes off.
  • the wind is beneficial to the starting and accelerating rotation of the rotor, which can shorten the distance of the running.
  • the general self-rotating rotorcraft can also take off in place.
  • FIG. 1 is a schematic structural view of a parachute rotation rotary wing machine provided by the present application
  • FIG. 2 is a schematic structural view of a parachute rotation rotary wing machine provided by the present application.
  • first device if a first device is coupled to a second device, the first device can be directly electrically coupled to the second device, or electrically coupled indirectly through other devices or coupling means. Connected to the second device.
  • the description of the specification is intended to be illustrative of the preferred embodiments of the invention. The scope of protection of the application is subject to the definition of the appended claims.
  • the embodiment provides a parachute-rotating rotorcraft, comprising: a fuselage 1, a rotor device 2, a propeller device 3, and a parachute device 4, wherein
  • the fuselage 1 comprises a cabin 5 and a rudder 6 , a control system 7 is arranged at the front end of the cabin 5 , an engine 8 is arranged at the rear end of the cabin 5 , and a landing gear is arranged below the fuselage 1 . 9;
  • the rotor device 2 is disposed at the top of the fuselage 1, and includes a rotor head 201 and a rotor blade 202 symmetrically disposed around the rotor head 201;
  • the screw device 3 is disposed at a tail portion of the cabin 5, and passes through the gear box and the The engine 8 is connected;
  • the parachute device 4 is disposed above the rotor head 201 and includes a whole machine parachute 401, a storage compartment 402 for accommodating the whole machine parachute, and an ejector for opening the umbrella.
  • control system 7 includes an operation panel, a joystick, and an emergency trigger handle.
  • the emergency trigger handle is used to control the opening of the whole machine parachute.
  • the working principle of the complete parachute system is equivalent to the airbag on the car.
  • the pilot pulls the emergency trigger handle.
  • the catapult in the parachute storage bin 402 will automatically pop up, and the whole aircraft parachute will be aired in the air and after a few seconds. Unfolding, thereby instantaneously controlling the descending speed of the rotorcraft to achieve the purpose of safely landing the rotorcraft and the onboard personnel.
  • the joystick is coupled to the rotor head by a connecting rod.
  • one end of the connecting rod is connected to the rotor head, and the other end is connected to the operating lever, and the tilting angle of the rotor head is changed by controlling the operating lever to realize the change of the rolling and pitching attitude of the rotorcraft. .
  • the screw device 3 is a propeller having an aerodynamic torsion paddle.
  • the number of the rotor blades is two or more.
  • the embodiment provides a method for a parachute rotation rotorcraft, which comprises the following steps:
  • parachute-rotating rotorcraft Configuring the parachute-rotating rotorcraft to include a fuselage, a rotor device, a propeller device, and a parachute device, wherein
  • the fuselage is provided with a cabin and a rudder, a control system is disposed at a front end of the cockpit, an engine and a propeller are disposed at a rear end of the cockpit, and a landing gear is disposed under the fuselage;
  • the parachute device is disposed above the rotor head and is configured to include a complete parachute, a storage compartment for accommodating the complete parachute, and an ejector for parachute.
  • the method further includes: setting the control system as an operation panel, a joystick, and an emergency trigger handle.
  • the method further includes: using the emergency trigger handle to control opening of the whole machine parachute.
  • the working principle of the complete parachute system is equivalent to the airbag on the car.
  • the pilot pulls the emergency trigger handle.
  • the catapult in the parachute storage bin 402 will automatically pop up, and the whole aircraft parachute will be aired in the air and after a few seconds. Unfolding, thereby instantaneously controlling the descending speed of the rotorcraft to achieve the purpose of safely landing the rotorcraft and the onboard personnel.
  • the method further includes: connecting the joystick to the rotor head through a connecting rod. Specifically, one end of the connecting rod is connected to the rotor head, and the other end is connected to the operating lever, and the tilting angle of the rotor head is changed by controlling the operating lever to realize the change of the rolling and pitching attitude of the rotorcraft. .
  • the method further includes: setting the number of the rotor blades to two or more.
  • the take-off and landing distance is short: the self-rotating rotorcraft has a remarkable feature, that is, its landing run distance is much shorter than the take-off run distance, and even if it is well-steered, it can land without landing.
  • high stability, strong wind resistance the stability of the rotorcraft is the highest in all aircraft, it can be automatically adjusted, so that the fuselage has good pitch stability, roll stability and speed stability.
  • the biggest advantage of a rotary rotorcraft unlike other aircraft is its high wind resistance, and it also likes wind when it takes off.
  • the wind is beneficial to the starting and accelerating rotation of the rotor, which can shorten the distance of the running.
  • the general self-rotating rotorcraft can also take off in place.

Abstract

一种伞降自转旋翼机，包括：机身（1）、旋翼装置（2）、螺旋桨装置（3）和降落伞装置（4），其中，所述机身（1）包括座舱（5）和尾舵（6），在所述座舱（5）的前端设置有控制系统（7），在所述座舱（5）的后端设置有发动机（8），所述机身（1）下方还设置有起落架（9）；所述旋翼装置（2）设置于所述机身（1）的顶部，其包括旋翼头（201）及对称设置于所述旋翼头（201）周围的旋翼片（202）；所述螺旋桨装置（3）设置于所述座舱（5）的尾部，其通过齿轮箱与所述发动机（8）相连；所述降落伞装置（4）设置于所述旋翼头（201）的上方，包括整机降落伞（401）、用于容纳所述整机降落伞（401）的存储舱(402)及开伞用的弹射器。该伞降自转旋翼机达到了以下效果：安全性高、起降距离短、稳定性高、抗风性强，具有较高的性价比。

Description

[根据细则37.2由ISA制定的发明名称]　伞降自转旋翼机及其制造方法 技术领域
本申请涉及飞行器技术领域，具体地，是涉及一种伞降自转旋翼机及其方法。
背景技术
自转旋翼机是一种以自转旋翼作为升力面、螺旋桨作为前进动力的旋翼类飞行器。自转旋翼机实际上是一种介于直升机和固定翼飞机之间的飞行器，它除去旋翼外，还带有一副螺旋桨以提供前进的动力。自转旋翼机与直升机的最大区别是，自转旋翼机的旋翼不与发动机传动系统相连，发动机只是驱动螺旋桨为飞机提供前进推力，而是在旋翼机飞行的过程中，由前方气流吹动旋翼旋转动产生升力。而直升机的旋翼与发动机传动系统相连，既能产生升力，又能提供飞行的动力。由于自转旋翼机的旋翼为自转式，传递到机身上的扭矩很小，因此自转旋翼机无需直升机那样的尾桨，但是一般装有尾舵，以控制飞行姿态。
虽然自转旋翼机安全性能好，即使遇到紧急情况，也可利用自身优越的滑翔性能寻找到合适的场地安全着陆，但在紧急情况的前提下，未必所有的飞行员都能做出正确合理的操作来保证所有飞机乘员的安全。所以，在飞机上搭载整机降落伞，是在事故发生时增加乘员生存概率的最好途径。
因此，如何研发一种稳定性好，工作安全系数高，搭载整机降落 伞的伞降自转旋翼机，便成为亟待解决的技术问题。
发明内容
为有效解决上述问题，本申请公开了一种稳定性好，工作安全系数高，搭载整机降落伞的伞降自转旋翼机，其技术方案如下：一种伞降自转旋翼机，其特征在于，包括：机身、旋翼装置、螺旋浆装置和降落伞装置，其中，
所述机身包括座舱和尾舵，在所述座舱的前端设置有控制系统，在所述座舱的后端设置有发动机，所述机身下方还设置有起落架；
所述旋翼装置设置于所述机身的顶部，其包括旋翼头及对称设置于所述旋翼头周围的旋翼片；
所述螺旋浆装置设置于所述座舱的尾部，其通过齿轮箱与所述发动机相连；
所述降落伞装置设置于所述旋翼头的上方，包括整机降落伞、用于容纳所述整机降落伞的存储舱、及开伞用的弹射器。
进一步地，所述控制系统包括操作面板、操纵杆和紧急触发手柄。
进一步地，所述紧急触发手柄用于控制所述整机降落伞的打开。
进一步地，所述操纵杆通过连杆与所述旋翼头相连接。
进一步地，所述旋翼片的数量为两个以上。
本申请还公开了一种伞降自转旋翼机的方法，其特征在于，包括以下步骤：
将所述伞降自转旋翼机设置为包括机身、旋翼装置、螺旋浆装置和降落伞装置，其中，
将所述机身设置座舱和尾舵，在所述座舱的前端设置控制系统，在所述座舱的后端设置发动机和螺旋桨，在所述机身下方设置起落架；
将所述旋翼装置设置于所述机身的顶部，将所述旋翼装置设置为包括旋翼头及对称设置于所述旋翼头周围的旋翼片；
将所述螺旋浆装置设置于所述座舱的尾部，通过齿轮箱与所述发动机相连；
将所述降落伞装置设置于所述旋翼头的上方，并将其设置为包括整机降落伞、用于容纳所述整机降落伞的存储舱、及开伞用的弹射器。
进一步地，还包括：将所述控制系统设置为操作面板、操纵杆和紧急触发手柄。
进一步地，还包括：将所述紧急触发手柄用于控制所述整机降落伞的打开。
进一步地，还包括：将所述操纵杆通过连杆与所述旋翼头相连接。
进一步地，还包括：将所述旋翼片的数量设置为两个以上。
与现有技术相比，本申请提供的伞降自转旋翼机及其方法，达到了如下效果：
1、安全性高：由于旋翼机的旋翼头上方安装有整机降落伞，在飞行中如果出现发动机空中停车，或者其他机械故障，飞行员可以迅速打开设在座舱内的降落伞紧急触发手柄打开降落伞，使飞行员和飞机安全落地。
2、起降距离短：自转旋翼机有个显著特点，就是它的着陆滑跑 距离大大地短于起飞滑跑距离，甚至操纵得好可以不滑跑就地着陆。
3、稳定性高，抗风性强：旋翼机的稳定性在所有航空器中最高，它可自动调节，使机身具有良好的俯仰稳定性、滚转稳定性和速度稳定性。自转旋翼机有别于其他类飞行器的最大优点是抗风能力高，而且在起飞时，它还喜欢有风。对于自转旋翼机来说，风有利于旋翼的起动和加速旋转，可以缩短滑跑的距离，当达到足够大的风速时，一般的自转旋翼机也可以不需要滑跑原地起飞。
4、具有较高的性价比：由于自转旋翼机相对于直升机结构简单，没有尾桨传动系统、减速器、自动倾斜器和主旋翼传动系统，所以不仅价格低，而且故障率也低。此外使用维护简单方便，所需费用也低。自转旋翼机其好用、安全、便利的特点，使其在未来的航空器家族中将占有一席之地。
附图说明
此处所说明的附图用来提供对本申请的进一步理解，构成本申请的一部分，本申请的示意性实施例及其说明用于解释本申请，并不构成对本申请的不当限定。在附图中：
图1为本申请提供的伞降自转旋翼机的结构示意图；
图2为本申请提供的伞降自转旋翼机的结构示意图。
具体实施方式
如在说明书及权利要求当中使用了某些词汇来指称特定组件。本领域技术人员应可理解，硬件制造商可能会用不同名词来称呼同一个组件。本说明书及权利要求并不以名称的差异来作为区分组件的方 式，而是以组件在功能上的差异来作为区分的准则。如在通篇说明书及权利要求当中所提及的“包含”为一开放式用语，故应解释成“包含但不限定于”。“大致”是指在可接收的误差范围内，本领域技术人员能够在一定误差范围内解决所述技术问题，基本达到所述技术效果。此外，“耦接”一词在此包含任何直接及间接的电性耦接手段。因此，若文中描述一第一装置耦接于一第二装置，则代表所述第一装置可直接电性耦接于所述第二装置，或通过其他装置或耦接手段间接地电性耦接至所述第二装置。说明书后续描述为实施本申请的较佳实施方式，然所述描述乃以说明本申请的一般原则为目的，并非用以限定本申请的范围。本申请的保护范围当视所附权利要求所界定者为准。
以下结合附图对本申请作进一步详细说明，但不作为对本申请的限定。
实施例1
本实施例提供一种伞降自转旋翼机，其特征在于，包括：机身1、旋翼装置2、螺旋浆装置3和降落伞装置4，其中，
所述机身1包括座舱5和尾舵6，在所述座舱5的前端设置有控制系统7，在所述座舱5的后端设置有发动机8，所述机身1下方还设置有起落架9；
所述旋翼装置2设置于所述机身1的顶部，其包括旋翼头201及对称设置于所述旋翼头201周围的旋翼片202；
所述螺旋装置3设置于所述座舱5的尾部，其通过齿轮箱与所述 发动机8相连；
所述降落伞装置4设置于所述旋翼头201的上方，包括整机降落伞401、用于容纳所述整机降落伞的存储舱402、及开伞用的弹射器。
进一步地，所述控制系统7包括操作面板、操纵杆和紧急触发手柄。
进一步地，所述紧急触发手柄用于控制所述整机降落伞的打开。具体地，整机降落伞系统的工作原理相当于汽车上的安全气囊。当旋翼机在飞行途中遇到紧急情况时，飞行员拉动所述紧急触发手柄，此时，降落伞存储仓402里的弹射器会自动向上弹出，并将整机降落伞弹至空中并于几秒钟后展开，从而瞬时控制旋翼机的下降速度，达到使旋翼机和机上人员安全降落的目的。
进一步地，所述操纵杆通过连杆与所述旋翼头相连接。具体地，所述连杆的一端与所述旋翼头连接，另一端与所述操纵杆连接，通过控制所述操纵杆来改变旋翼头的倾角，以实现旋翼机的滚转和俯仰姿态的变化。
进一步地，所述螺旋装置3为具有气动力变扭桨桨片的螺旋桨。
进一步地，所述旋翼片的数量为两个以上。
实施例2
本实施例提供一种伞降自转旋翼机的方法，其特征在于，包括以下步骤：
将所述伞降自转旋翼机设置为包括机身、旋翼装置、螺旋浆装置和降落伞装置，其中，
将所述机身设置座舱和尾舵，在所述座舱的前端设置控制系统，在所述座舱的后端设置发动机和螺旋桨，在所述机身下方设置起落架；
将所述旋翼装置设置于所述机身的顶部，将所述旋翼装置设置为包括旋翼头及对称设置于所述旋翼头周围的旋翼片；
将所述螺旋浆装置设置于所述座舱的尾部，通过齿轮箱与所述发动机相连；
将所述降落伞装置设置于所述旋翼头的上方，并将其设置为包括整机降落伞、用于容纳所述整机降落伞的存储舱、及开伞用的弹射器。
进一步地，还包括：将所述控制系统设置为操作面板、操纵杆和紧急触发手柄。
进一步地，还包括：将所述紧急触发手柄用于控制所述整机降落伞的打开。具体地，整机降落伞系统的工作原理相当于汽车上的安全气囊。当旋翼机在飞行途中遇到紧急情况时，飞行员拉动所述紧急触发手柄，此时，降落伞存储仓402里的弹射器会自动向上弹出，并将整机降落伞弹至空中并于几秒钟后展开，从而瞬时控制旋翼机的下降速度，达到使旋翼机和机上人员安全降落的目的。
进一步地，还包括：将所述操纵杆通过连杆与所述旋翼头相连接。具体地，所述连杆的一端与所述旋翼头连接，另一端与所述操纵杆连接，通过控制所述操纵杆来改变旋翼头的倾角，以实现旋翼机的滚转和俯仰姿态的变化。
进一步地，还包括：将所述旋翼片的数量设置为两个以上。
与现有技术相比，本申请所述的伞降自转旋翼机及其方法，达到了如下效果：
1、安全性高：由于旋翼机的旋翼头上方安装有整机降落伞，在飞行中如果出现发动机空中停车，或者其他机械故障，飞行员可以迅速打开设在座舱内的降落伞紧急触发手柄打开降落伞，使飞行员和飞机安全落地。
2、起降距离短：自转旋翼机有个显著特点，就是它的着陆滑跑距离大大地短于起飞滑跑距离，甚至操纵得好可以不滑跑就地着陆。
3、稳定性高，抗风性强：旋翼机的稳定性在所有航空器中最高，它可自动调节，使机身具有良好的俯仰稳定性、滚转稳定性和速度稳定性。自转旋翼机有别于其他类飞行器的最大优点是抗风能力高，而且在起飞时，它还喜欢有风。对于自转旋翼机来说，风有利于旋翼的起动和加速旋转，可以缩短滑跑的距离，当达到足够大的风速时，一般的自转旋翼机也可以不需要滑跑原地起飞。
4、具有较高的性价比：由于自转旋翼机相对于直升机结构简单，没有尾桨传动系统、减速器、自动倾斜器和主旋翼传动系统，所以不仅价格低，而且故障率也低。此外使用维护简单方便，所需费用也低。自转旋翼机其好用、安全、便利的特点，使其在未来的航空器家族中将占有一席之地。
上述说明示出并描述了本申请的若干优选实施例，但如前所述，应当理解本申请并非局限于本文所披露的形式，不应看作是对其他实 施例的排除，而可用于各种其他组合、修改和环境，并能够在本文所述申请构想范围内，通过上述教导或相关领域的技术或知识进行改动。而本领域人员所进行的改动和变化不脱离本申请的精神和范围，则都应在本申请所附权利要求的保护范围内。

Claims (10)

  1. 一种伞降自转旋翼机，其特征在于，包括：机身、旋翼装置、螺旋浆装置和降落伞装置，其中，所述机身包括座舱和尾舵，在所述座舱的前端设置有控制系统，在所述座舱的后端设置有发动机，所述机身下方还设置有起落架；所述旋翼装置设置于所述机身的顶部，其包括旋翼头及对称设置于所述旋翼头周围的旋翼片；所述螺旋浆装置设置于所述座舱的尾部，其通过齿轮箱与所述发动机相连；所述降落伞装置设置于所述旋翼头的上方，包括整机降落伞、用于容纳所述整机降落伞的存储舱及开伞用的弹射器。
  2. 根据权利要求1所述的伞降自转旋翼机，其特征在于，所述控制系统包括操作面板、操纵杆和紧急触发手柄。
  3. 根据权利要求2所述的伞降自转旋翼机，其特征在于，所述紧急触发手柄用于控制所述整机降落伞的打开。
  4. 根据权利要求2所述的伞降自转旋翼机，其特征在于，所述操纵杆通过连杆与所述旋翼头相连接。
  5. 根据权利要求1所述的伞降自转旋翼机，其特征在于，所述旋翼片的数量为两个以上。
  6. 一种伞降自转旋翼机的方法，其特征在于，包括以下步骤：将所述伞降自转旋翼机设置为包括机身、旋翼装置、螺旋浆装置和降落伞装置，其中，将所述机身设置座舱和尾舵，在所述座舱的前端设置控制系统，在所述座舱的后端设置发动机和螺旋桨，在所述机身下方设置起落架；将所述旋翼装置设置于所述机身的顶部，将所述旋翼装 置设置为包括旋翼头及对称设置于所述旋翼头周围的旋翼片；将所述螺旋浆装置设置于所述座舱的尾部，通过齿轮箱与所述发动机相连；将所述降落伞装置设置于所述旋翼头的上方，并将其设置为包括整机降落伞、用于容纳所述整机降落伞的存储舱及开伞用的弹射器。
  7. 根据权利要求6所述的伞降自转旋翼机的方法，其特征在于，还包括：将所述控制系统设置为操作面板、操纵杆和紧急触发手柄。
  8. 根据权利要求7所述的伞降自转旋翼机的方法，其特征在于，还包括：将所述紧急触发手柄用于控制所述整机降落伞的打开。
  9. 根据权利要求7所述的伞降自转旋翼机的方法，其特征在于，还包括：将所述操纵杆通过连杆与所述旋翼头相连接。
  10. 根据权利要求6所述的伞降自转旋翼机的方法，其特征在于，还包括：将所述旋翼片的数量设置为两个以上。
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CN105059534A (zh) * 2015-09-02 2015-11-18 河南三和航空工业有限公司 伞降自转旋翼机及其方法
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