WO2014206058A1 - Helicopter with forward tilting main airscrew - Google Patents

Helicopter with forward tilting main airscrew Download PDF

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Publication number
WO2014206058A1
WO2014206058A1 PCT/CN2014/000578 CN2014000578W WO2014206058A1 WO 2014206058 A1 WO2014206058 A1 WO 2014206058A1 CN 2014000578 W CN2014000578 W CN 2014000578W WO 2014206058 A1 WO2014206058 A1 WO 2014206058A1
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WO
WIPO (PCT)
Prior art keywords
main
helicopter
engine
airscrew
wing
Prior art date
Application number
PCT/CN2014/000578
Other languages
French (fr)
Chinese (zh)
Inventor
李宏生
Original Assignee
Li Hongsheng
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 Li Hongsheng filed Critical Li Hongsheng
Publication of WO2014206058A1 publication Critical patent/WO2014206058A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
    • 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

Definitions

  • the invention relates to a helicopter, and in particular to a main propeller forward-tilting helicopter, belonging to the field of aircraft manufacturing technology.
  • the helicopter has a balance force due to the absence of the wing, and on the other hand, since the main propeller is mostly fixed, the resistance is large, which affects the forward speed.
  • the object of the present invention is to provide a main propeller forward tilting helicopter which reduces the forward resistance, improves the load capacity, and improves the speed of the forward movement.
  • the technical solution created by the invention comprises: a main propeller forward tilting helicopter, comprising a fuselage main body, a main propeller, a main propeller shaft and a tail fin, and a main engine is connected through a bracket on a back ridge of the fuselage main body, and a hydraulic pressure is arranged at a lower rear of the main engine.
  • the rod I, the end of the hydraulic rod I is fixed to the fuselage main body, and the main propeller shaft is connected to the main engine drive.
  • a wing is arranged horizontally and horizontally above the main body of the fuselage, and the two ends of the wing are respectively provided with a sub-engine, and the auxiliary engine is connected with the auxiliary propeller through the transmission shaft; the two auxiliary engines are connected by a concentric shaft.
  • the concentric shaft is located at the center of the wing and is driven to rotate by the hydraulic rod II.
  • the ends of the main propeller and the sub propeller are both designed to be curved.
  • the front half of the wing is horizontally fixedly coupled to the fuselage body, the rear half is rotatably coupled relative to the front half, and the concentric shaft is mounted to the rear half of the wing.
  • Both the fuselage body and the outer engine casing are designed in a polygonal shape.
  • the beneficial effects created by the invention are as follows: 1. Since the hydraulic rod I is added on the back ridge of the fuselage main body, the main propeller can be tilted forward by a certain angle to reduce the resistance of the helicopter, thereby improving the helicopter's forward movement. Speed; 2, because a wing is installed horizontally and horizontally above the main body of the fuselage, so that the balance capacity of the helicopter can be improved; 3. Since the auxiliary propeller is added to the wing, the auxiliary propeller and the main propeller cooperate to enhance the helicopter. The speed of ascending and moving forward; 4.
  • the main propeller and the sub propeller can be rotated when the maximum capacity is reduced, and the wind is lost outward;
  • the front half of the wing is designed to be horizontally fixed, and the rear half is designed to be rotatable relative to the front half so that when the helicopter is raised, the rear half is bent downwards, which reduces the resistance of the main propeller to the downward blow, while the secondary propeller It also blows down, and cooperates with the main propeller to increase the lift.
  • the rear half When the helicopter is moving forward, the rear half is flush with the front half.
  • Vice rearward propeller can increase the forward speed of the helicopter; 6, since the housing body and the housing are designed as secondary engine polygonal shape, is not easily detected by radar, it can achieve the purpose of stealth.
  • Fig. 1 is a schematic view showing the structure of the present invention when it is raised.
  • Figure 2 is a side elevational view of the present invention when it is raised.
  • FIG. 3 is a schematic structural view of the present invention when it is created.
  • Figure 4 is a side elevational view of the present invention when it is created.
  • Figure 5 is a top plan view of the present invention when it is created.
  • Figure 6 is a schematic view of the structure of the main propeller.
  • Figure 7 is a schematic view showing the connection structure of the sub-propeller and the sub-engine, the concentric shaft, and the IS-clamp II.
  • the main propeller forward tilting helicopter includes a fuselage main body 1, a main propeller 2, a main propeller shaft 3 and a tail fin 4, and a main engine 10 is connected to the ridge of the fuselage main body 1 via a bracket 13, and a rear engine of the main engine 10 is provided.
  • the hydraulic rod I9, the end of the hydraulic rod I9 is fixed to the fuselage main body 1, and the main propeller shaft 3 is drivingly coupled to the main engine 10.
  • a wing 6 is horizontally and horizontally mounted on the upper side of the fuselage main body 1.
  • the two ends of the wing 6 are respectively provided with a sub-engine 8, and the sub-engine 8 is connected to the sub-propeller 7 through a transmission shaft; two sub-engines 8
  • the concentric shaft 11 is fixedly connected between them, and the concentric shaft 11 is located at the center of the wing 6 and is driven to rotate by the hydraulic rod II 12 as shown in FIG.
  • the ends of the main propeller 2 and the sub propeller 7 are each designed to be curved 5 as shown in FIG.
  • the front half of the wing 6 is fixedly connected horizontally to the fuselage body 1, the rear half is rotatably coupled to the front half, and the concentric shaft 11 is mounted on the rear half of the wing 6.
  • Both the fuselage main body 1 and the outer casing 8 are designed in a polygonal shape.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Toys (AREA)

Abstract

A helicopter with a forward tilting main airscrew comprises a helicopter main body (1), a main airscrew (2), a main airscrew rotating shaft (3), and an empennage (4). The helicopter main body (1) is connected to a main engine (10) on the spine by a rack (13), a hydraulic rod I (9) is disposed at the rear of and below the main engine (10), the tail of the hydraulic rod I (9) is secured on the helicopter main body (1), and the main airscrew rotating shaft (3) is transmissively connected to the main engine (10). A wing (6) is horizontally disposed on the upper portion of the helicopter main body (1), is provided with a secondary engine (8) at each of two extremities thereof, the two secondary engines (8) being transmissively connected to a secondary airscrew (7) by a transmission shaft and being firmly connected by a concentric shaft (11), and the concentric shaft (11) being located at the center of the wing (6) and rotating under the drive of a hydraulic rod II (12). The tail of the main airscrew (2) and that of the secondary airscrew (7) are both designed to a bent form (5), and the housing of the helicopter main body (1) and that of the secondary engine (8) are both designed to a multi-faceted shape. The helicopter with a forward tilting main airscrew can reduce the helicopter advancing resistance, improve a load capability, and accelerate the advancing speed.

Description

说 明 书  Description
主螺旋桨前倾式直升机  Main propeller forward tilt helicopter
技术领域 Technical field
本发明创造涉及一种直升机， 具体涉及一种主螺旋桨前倾式直升机， 属于飞机制造技术 领域。  The invention relates to a helicopter, and in particular to a main propeller forward-tilting helicopter, belonging to the field of aircraft manufacturing technology.
背景技术 Background technique
现有技术中的直升机， 一方面由于没有机翼使得平衡力差， 另一方面由于主螺旋桨大都 是固定的， 因此阻力大， 影响前行速度。  In the prior art, the helicopter has a balance force due to the absence of the wing, and on the other hand, since the main propeller is mostly fixed, the resistance is large, which affects the forward speed.
发明创造内容 Invention content
本发明创造的目的是提供一种主螺旋桨前倾式直升机， 减小前行的阻力， 提高载重能 力， 提高了前行的速度。  The object of the present invention is to provide a main propeller forward tilting helicopter which reduces the forward resistance, improves the load capacity, and improves the speed of the forward movement.
本发明创造的技术方案： 主螺旋桨前倾式直升机， 包括机身主体、 主螺旋桨、 主螺旋桨 转轴和尾翼， 在机身主体的背脊上通过支架连接有一主发动机， 主发动机的后下方设有液压 杆 I， 液压杆 I的末端固定在机身主体， 主螺旋桨转轴与主发动机传动连接。  The technical solution created by the invention comprises: a main propeller forward tilting helicopter, comprising a fuselage main body, a main propeller, a main propeller shaft and a tail fin, and a main engine is connected through a bracket on a back ridge of the fuselage main body, and a hydraulic pressure is arranged at a lower rear of the main engine. The rod I, the end of the hydraulic rod I is fixed to the fuselage main body, and the main propeller shaft is connected to the main engine drive.
在机身主体的上方水平横向安装设有一个机翼， 机翼的两个端部各设有副发动机， 副发 动机通过传动轴与副螺旋桨传动连接； 两个副发动机之间通过同心轴连接固定， 同心轴位于 机翼的中心处并通过液压杆 II驱动旋转。  A wing is arranged horizontally and horizontally above the main body of the fuselage, and the two ends of the wing are respectively provided with a sub-engine, and the auxiliary engine is connected with the auxiliary propeller through the transmission shaft; the two auxiliary engines are connected by a concentric shaft. The concentric shaft is located at the center of the wing and is driven to rotate by the hydraulic rod II.
主螺旋桨和副螺旋桨的末端均设计成弯状。  The ends of the main propeller and the sub propeller are both designed to be curved.
所述机翼的前半部水平与机身主体固定连接， 后半部相对于前半部可旋转连接， 且同心 轴安装在机翼后半部上。  The front half of the wing is horizontally fixedly coupled to the fuselage body, the rear half is rotatably coupled relative to the front half, and the concentric shaft is mounted to the rear half of the wing.
机身主体及副发动机的外壳均设计成多棱形状。  Both the fuselage body and the outer engine casing are designed in a polygonal shape.
本发明创造的有益效果： 1、 由于在机身主体的背脊上增加设有液压杆 I， 可使得主螺 旋桨向前倾斜一定角度， 以减小直升机前行的阻力， 因此提高了直升机前行的速度； 2、 由 于在机身主体的上方水平横向安装设有一个机翼， 因此可提高直升机的平衡能力； 3、 由于 在机翼上增加副螺旋桨， 副螺旋桨与主螺旋桨协同作用， 可提高直升机上升及前行的速度； 4、 由于将主螺旋桨和副螺旋桨的末端均设计成弯状， 可使主螺旋桨和副螺旋桨在旋转时， 最大能力的减小风力向外散失； 5、 由于将机翼的前半部设计成水平固定， 后半部设计成可 相对于前半部旋转， 使得直升机在上升时， 后半部向下弯折， 这样可减小主螺旋桨向下吹风 的阻力， 同时副螺旋桨也向下吹风， 与主螺旋桨协同作用进而提高升力， 直升机在前行时， 后半部与前半部齐平， 此时副螺旋桨朝向后方， 可提高直升机的前进速度； 6、 由于将机身 主体及副发动机的外壳均设计成多棱形状， 不易被雷达侦测到， 可达到隐身目的。 说 明 书 The beneficial effects created by the invention are as follows: 1. Since the hydraulic rod I is added on the back ridge of the fuselage main body, the main propeller can be tilted forward by a certain angle to reduce the resistance of the helicopter, thereby improving the helicopter's forward movement. Speed; 2, because a wing is installed horizontally and horizontally above the main body of the fuselage, so that the balance capacity of the helicopter can be improved; 3. Since the auxiliary propeller is added to the wing, the auxiliary propeller and the main propeller cooperate to enhance the helicopter. The speed of ascending and moving forward; 4. Because the ends of the main propeller and the sub propeller are designed to be curved, the main propeller and the sub propeller can be rotated when the maximum capacity is reduced, and the wind is lost outward; The front half of the wing is designed to be horizontally fixed, and the rear half is designed to be rotatable relative to the front half so that when the helicopter is raised, the rear half is bent downwards, which reduces the resistance of the main propeller to the downward blow, while the secondary propeller It also blows down, and cooperates with the main propeller to increase the lift. When the helicopter is moving forward, the rear half is flush with the front half. Vice rearward propeller, can increase the forward speed of the helicopter; 6, since the housing body and the housing are designed as secondary engine polygonal shape, is not easily detected by radar, it can achieve the purpose of stealth. Instruction manual
附图说明 DRAWINGS
图 1为本发明创造上升时的结构示意图。  Fig. 1 is a schematic view showing the structure of the present invention when it is raised.
图 2为本发明创造上升时的侧视图。  Figure 2 is a side elevational view of the present invention when it is raised.
图 3为本发明创造前行时的结构示意图。  FIG. 3 is a schematic structural view of the present invention when it is created.
图 4为本发明创造前行时的的侧视图。  Figure 4 is a side elevational view of the present invention when it is created.
图 5为本发明创造前行时的俯视图。  Figure 5 is a top plan view of the present invention when it is created.
图 6为主螺旋桨的结构示意图。  Figure 6 is a schematic view of the structure of the main propeller.
图 7为副螺旋桨与副发动机、 同心轴及 IS压衧 II的连接结构示意图。  Figure 7 is a schematic view showing the connection structure of the sub-propeller and the sub-engine, the concentric shaft, and the IS-clamp II.
具体实施方式 detailed description
主螺旋桨前倾式直升机， 包括机身主体 1、 主螺旋桨 2、 主螺旋桨转轴 3和尾翼 4， 在 机身主体 1 的背脊上通过支架 13连接有一主发动机 10， 主发动机 10的后下方设有液压杆 I 9， 液压杆 I 9的末端固定在机身主体 1， 主螺旋桨转轴 3与主发动机 10传动连接。 在机 身主体 1的上方水平横向安装设有一个机翼 6， 机翼 6的两个端部各设有副发动机 8， 副发 动机 8通过传动轴与副螺旋桨 7传动连接； 两个副发动机 8之间通过同心轴 11连接固定， 同心轴 11位于机翼 6的中心处并通过液压杆 II 12驱动旋转， 如图 7所示。 主螺旋桨 2和副 螺旋桨 7的末端均设计成弯状 5， 如图 6所示。 所述机翼 6的前半部水平与机身主体 1固定 连接， 后半部相对于前半部可旋转连接， 且同心轴 11安装在机翼 6后半部上。  The main propeller forward tilting helicopter includes a fuselage main body 1, a main propeller 2, a main propeller shaft 3 and a tail fin 4, and a main engine 10 is connected to the ridge of the fuselage main body 1 via a bracket 13, and a rear engine of the main engine 10 is provided. The hydraulic rod I9, the end of the hydraulic rod I9 is fixed to the fuselage main body 1, and the main propeller shaft 3 is drivingly coupled to the main engine 10. A wing 6 is horizontally and horizontally mounted on the upper side of the fuselage main body 1. The two ends of the wing 6 are respectively provided with a sub-engine 8, and the sub-engine 8 is connected to the sub-propeller 7 through a transmission shaft; two sub-engines 8 The concentric shaft 11 is fixedly connected between them, and the concentric shaft 11 is located at the center of the wing 6 and is driven to rotate by the hydraulic rod II 12 as shown in FIG. The ends of the main propeller 2 and the sub propeller 7 are each designed to be curved 5 as shown in FIG. The front half of the wing 6 is fixedly connected horizontally to the fuselage body 1, the rear half is rotatably coupled to the front half, and the concentric shaft 11 is mounted on the rear half of the wing 6.
机身主体 1及副发动机 8的外壳均设计成多棱形状。  Both the fuselage main body 1 and the outer casing 8 are designed in a polygonal shape.
如图 1 和图 2所示， 直升机在起飞状态时， 启动液压杆 1112， 液压杆 Π 12驱动同心轴 11旋转， 使副螺旋桨 7朝下； 如图 3至图 5所示， 直升机在前行状态时， 启动液压杆 1 9， 液压杆 1 9驱动主螺旋桨 2 向前倾斜一定角度， 然后再通过液压杆 II 12 驱动同心轴 11 旋 转， 使副螺旋桨 7朝后。  As shown in Fig. 1 and Fig. 2, when the helicopter is in the take-off state, the hydraulic rod 1112 is activated, and the hydraulic rod Π 12 drives the concentric shaft 11 to rotate, so that the sub propeller 7 faces downward; as shown in Fig. 3 to Fig. 5, the helicopter is moving forward. In the state, the hydraulic lever 1 is activated, the hydraulic rod 1 9 drives the main propeller 2 to be inclined forward by a certain angle, and then the concentric shaft 11 is driven to rotate by the hydraulic rod II 12 so that the sub propeller 7 faces backward.

Claims

权 利 要 求 书 Claim
1. 主螵旋奖前倾式直升諷， 包揺榲身主体 (I 主蠓旋 （2)、 主螵旋 转轴（3) 和尾翼 1. Main 螵 奖 前 前 直 , , , , , , , , , ( ( ( ( ( ( ( ( ( ( ( ( ( ( ( ( ( ( ( ( ( (
(4)5 其特概在于 在机身主 (1) 背脊上通过支架 （13) 连接有一主发动机 (10), 主发动机 (10) 的后" F方«有液 fiff I (9), 液 ffiff Ϊ (9) 的末端固定在机身 主体 (1), 主螺旋藥转轴 (3) 与主发动机 (10) 传动连接。 (4) 5 is characterized by a main engine (10) connected to the main (1) back of the fuselage via a bracket (13), and the rear "F-square" of the main engine (10) has a liquid fiff I (9), liquid The end of the ffiff Ϊ (9) is fixed to the fuselage body (1), and the main screw shaft (3) is connected to the main engine (10).
2. 如权利要求 1所逮 »主蠔旋浆售倾式直升机， 其特征在于： 在机身主体 （1) «I上方水平 横向安装«有一个机翼 (6), 桃翼 (6) 飾两个讕部各豫有副发动机 (8), 副发动机 2. The main squeezing rotary-propelled helicopter according to claim 1, characterized in that: horizontally and horizontally mounted on the fuselage main body (1) «I has a wing (6), peach wing (6) The two crotch parts each have a secondary engine (8), the secondary engine
(8)通过传动轴与副螵旋 ¾ (7)传动连接； 两个 «发瑜 Λ (8) 之间通过同 轴 （11) 连接圃定， R心轴 （11)位于机翼 （6) »中心 ft并通过液压杆 II (12)驱动簾转(8) The drive shaft is connected to the sub-turn 3⁄4 (7); the two «Yu Yoga (8) are connected by coaxial (11), and the R mandrel (11) is located on the wing (6) »Center ft and drive the curtain through hydraulic rod II (12)
3. 权利要求〗或 2 述》主螵旋藥前倾式直升机， 其特征在于； 主螺旋桨 (2) 副螵旋 桨 (7) 曲末端均 ft计戚弯 (5)c 3. Claims or 2: The main propellant forward-angle helicopter, characterized by; main propeller (2) sub-rotating propeller (7) end of the curve ft. ( bend (5)c
4. 如权利要求 2所述的主螺旋桨前倾式直升机， 其特征在于: 所通机翼 (6) 的前半部水平 与机身主# (1) 圍定连接， 后半部相 予前半部可旋转连接， 且同心轴〈11)安装在机 翼 (6) 后半部上。  4. The main propeller forward tilting helicopter according to claim 2, wherein: the front half of the through wing (6) is horizontally connected to the main body # (1), and the rear half is opposite to the front half. Rotatable connection and concentric shaft <11) mounted on the rear half of the wing (6).
5. 如 ft利要求 1或 2 购主鱲旋 前倾式直升机， 其特征在亍： 机身主体《1〉及副发动 机 (8) 外壳均设计慮多樓形状 -  5. If the ft is required to 1 or 2, the purchaser of the forward-tilting helicopter is characterized by: 机身: The main body of the fuselage "1" and the sub-engine (8) are designed with multiple floors in mind -
PCT/CN2014/000578 2013-06-28 2014-06-13 Helicopter with forward tilting main airscrew WO2014206058A1 (en)

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CN2013102785346A CN103318408A (en) 2013-06-28 2013-06-28 Helicopter with main propeller leaning forward
CN201310278534.6 2013-06-28

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