WO2013056492A1 - Composite aircraft consisting of fixed-wing and electrically driven propellers and having helicopter functions - Google Patents
Composite aircraft consisting of fixed-wing and electrically driven propellers and having helicopter functions Download PDFInfo
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- WO2013056492A1 WO2013056492A1 PCT/CN2011/083301 CN2011083301W WO2013056492A1 WO 2013056492 A1 WO2013056492 A1 WO 2013056492A1 CN 2011083301 W CN2011083301 W CN 2011083301W WO 2013056492 A1 WO2013056492 A1 WO 2013056492A1
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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
- B64C29/0025—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 fixed relative to the fuselage
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- the rotor that is directly connected to the power system is far less efficient than the wing of a fixed-wing aircraft, so power consumption is large. Because its forward speed is mainly provided by the component force generated by the tilting of the rotor paddle through the swash plate, the resistance of the helicopter to fly forward is also much larger than that of the fixed-wing aircraft. Therefore, its flight speed, distance and endurance are not as good as fixed-wing aircraft. For this reason, technicians in the aerospace industry have been looking for aircraft that combine the advantages of fixed-wing aircraft and helicopters.
- the separate lift engine is simple in design, the lift engine does not work during cruising, and it takes up the internal volume, which is dead weight. Reducing or eliminating dead weight is an urgent problem for vertical landing aircraft.
- the most straightforward way to combine cruise and lift engines is to tilt the jet engine and blow the engine directly to the ground, which of course produces direct lift. So simple, why not the first choice for vertical landing aircraft? First, tilting the engine imposes significant limitations on the position of the engine on the aircraft.
- the paddles are respectively disposed on both sides of the fuselage and upper and lower sides of the wing, and are symmetrically placed with respect to the center of gravity of the aircraft.
- each of the electric multi-blade power systems or paddles is coupled to the fuselage or wing by a support arm.
- the angle of attack angle is 10° -30°.
- the paddle is a foldable paddle.
- the aircraft comprises a fixed wing power system.
- the fixed wing power system is electric or fuel powered.
- the electronic gyro can be used to control the speed of four paddles to form a stable rotor helicopter flight platform. By changing the paddle speed, the lift and torque of the four blades are changed to control the flight and steering of the rotor helicopter in all directions.
- the electronic gyro is a commonly used device in the field, and the technician can select the type according to the specific needs.
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Abstract
A composite aircraft consisting of a fixed-wing and electrically driven propellers and having helicopter functions comprises a fixed-wing aircraft assembly. The assembly comprises an aircraft body (1), wings (2), and a fixed-wing rudder surface control system (61). The aircraft further comprises an electrically-driven-propellers power system (4) and a general controller (6). The general controller (6) comprises the fixed-wing rudder surface control system (61) and an electrically-driven-propellers control system (62). The general controller (6) is further used for controlling the fixed-wing rudder surface control system (61) and the electrically-driven-propellers control system (62) to work separately or in a coordinated manner. The blade rotation plane of the electrically-driven-propellers power system (4) is perpendicular to the central axis of the aircraft body. The composite aircraft consisting of the fixed-wing and the electrically driven propellers can not only take off, land, and fly vertically like a helicopter, but also take off, land and fly as a fixed-wing aircraft, or take off in a helicopter mode, fly in a fixed-wing mode, and then land in the helicopter mode.
Description
技术领域 Technical field
本发明涉及一种飞行器，特别是涉及一种固定翼与电动多桨组成的具有 直升机功能的复合飞行器。 背景技术 在航空领域常见的固定翼飞机， 由于主要靠机翼产生升力平衡飞机重 量， 动力***主要用来克服飞机飞行阻力， 因此远小于飞机重量的动力 （推 拉力） 就可以让固定翼飞机离地升空。 其飞行速度快， 航程和巡航时间长， 但起降距离长， 要求高质量的跑道， 严重影响和妨碍了固定翼飞机在偏远无 专用机场地区的应用。 The present invention relates to an aircraft, and more particularly to a composite aircraft having a helicopter function consisting of a fixed wing and an electric multi-blade. BACKGROUND OF THE INVENTION Fixed-wing aircraft commonly used in the aeronautical field, because the lift is mainly used to balance the weight of the aircraft, the power system is mainly used to overcome the flight resistance of the aircraft, so the power (push and pull) far less than the weight of the aircraft can make the fixed-wing aircraft away. Lift off the ground. It has a fast flight speed, long range and long cruising time, but long take-off and long distance, requiring high-quality runways, which seriously affects and hinders the application of fixed-wing aircraft in remote and non-dedicated airport areas.
在航空领域常见的旋翼直升机， 可以解决在狭小场地垂直起降的问题。 在已知的旋翼飞行器中， 除了常见的单桨直升机以外， 还有多桨直升机， 多 桨直升机一般是通过变化桨的转速来改变飞行姿态的。 如 4桨旋翼直升机， 4个桨相对于中心对称放置， 其中有 2个桨是顺时针旋转， 还有 2个桨是逆 时针方向旋转。 当飞机需要往一个方向转向时， 只要改变增加其中 2个顺时 针 /逆时针桨的转速，减少另外 2个逆时针 /顺时针桨的转速就可以改变航向。 需要倾斜飞行时， 只要减小飞行方向上的桨的转速， 增加对称位置的桨的转 速就能通过升力差向指定的方向飞行。 Rotor helicopters, which are common in the aviation field, can solve the problem of vertical take-off and landing in narrow spaces. In known rotorcraft, in addition to the common single-blade helicopters, there are multi-blade helicopters, which typically change the attitude of the propeller by varying the speed of the propeller. For example, a 4-blade rotor helicopter has four blades symmetrically placed with respect to the center. Two of the blades rotate clockwise and two of the blades rotate counterclockwise. When the aircraft needs to turn in one direction, simply change the speed of two of the clockwise/counterclockwise propellers and reduce the speed of the other two counterclockwise/clockwise propellers to change the heading. When it is necessary to tilt the flight, as long as the rotation speed of the paddle in the flight direction is reduced, the speed of the paddle in the symmetrical position can be increased to fly in the specified direction by the lift difference.
但直接和动力***相连的旋翼效率远不如固定翼飞机的机翼， 因此功耗 大。 又因其前进速度主要靠旋翼桨盘通过倾斜盘的倾斜产生的分力提供， 同 时直升机前进飞行的阻力也较固定翼飞机大的多。 因此其飞行速度， 距离和 续航时间都不如固定翼飞机。为此航空领域的技术人员一直在找寻能兼有固 定翼飞机和直升机优点的飞行器。 However, the rotor that is directly connected to the power system is far less efficient than the wing of a fixed-wing aircraft, so power consumption is large. Because its forward speed is mainly provided by the component force generated by the tilting of the rotor paddle through the swash plate, the resistance of the helicopter to fly forward is also much larger than that of the fixed-wing aircraft. Therefore, its flight speed, distance and endurance are not as good as fixed-wing aircraft. For this reason, technicians in the aerospace industry have been looking for aircraft that combine the advantages of fixed-wing aircraft and helicopters.
单独的升力发动机在设计上简单， 升力发动机在巡航时不工作， 又占用 机内体积，这是死重。减少或消除死重是垂直起落飞机一个急需解决的问题。
将升力和巡航发动机合二为一， 当然就消除了专用升力发动机的死重。 巡航 和升力发动机合二为一的最直接的方法， 莫过于倾转喷气发动机， 把发动机 直接对着地面吹， 当然就产生直接的升力。 这么简单的道理， 为什么不是垂 直起落飞机的首选呢？ 首先，倾转发动机对发动机在飞机上的位置带来很大 的限制， 不光机翼、 发动机的位置必须和飞机的重心一致， 也基本上只有翼 下或翼尖位置， 这样， 一旦部分升力发动机故障或瞬时出力不足， 非对称升 力容易引起灾难性的事故。 倾转旋翼用同步轴解决这个问题， 倾转喷气发动 机就基本不可能在一侧发动机失效时， 由另一侧发动机补偿。 再说， 发动机 本身十分沉重， 倾转机构谈何容易。 还有， 发动机对进气的要求很高， 否则 发动机效率直线下降，但发动机在倾转过程中，进气的条件很难保证。另外， 垂直起落要求在短时间内产生大量的推力， 巡航要求工作时间长但推力远远 要不了那么多， 两者之间在设计上很难协调。 由发动机直接产生升力， 没法 取巧。 从极端情况来说， 滑跑起飞、 用机翼产生升力， 只需要很少的推力； 但用喷气动力垂直起飞， 至少需要 1 : 1 的推重比， 动力要求高得多。 The separate lift engine is simple in design, the lift engine does not work during cruising, and it takes up the internal volume, which is dead weight. Reducing or eliminating dead weight is an urgent problem for vertical landing aircraft. Combining the lift and cruise engines into one, of course, eliminates the dead weight of the dedicated lift engine. The most straightforward way to combine cruise and lift engines is to tilt the jet engine and blow the engine directly to the ground, which of course produces direct lift. So simple, why not the first choice for vertical landing aircraft? First, tilting the engine imposes significant limitations on the position of the engine on the aircraft. Not only does the wing and engine position have to be consistent with the center of gravity of the aircraft, but also essentially the position of the wing or wing tip, so that once the lift engine fails Or the instantaneous output is insufficient, and the asymmetric lift is easy to cause a catastrophic accident. The tilting rotor solves this problem with a synchronous shaft, and it is almost impossible for a tilting jet engine to be compensated by the other engine when one engine fails. Besides, the engine itself is very heavy, and it is easy to talk about the tilting mechanism. Also, the engine has a high demand for intake air, otherwise the engine efficiency will drop linearly, but the condition of the intake air is difficult to guarantee during the engine tilting process. In addition, vertical landing requires a large amount of thrust in a short period of time. Cruise requires a long working time but the thrust is far less than that. It is difficult to coordinate the design between the two. It is impossible to take advantage of the lift generated directly by the engine. In extreme cases, the take-off and the use of the wing to generate lift require only a small amount of thrust; but with jet-powered vertical take-off, at least a 1:1 thrust-to-weight ratio is required, and the power requirements are much higher.
在已知的具有可垂直起降功能且有固定翼飞机功能的飞行器中， 大致分 为以下几类。一、如图 1， 将涵道风扇和前行桨叶 11结合起来的方案。 如西 科斯基的无人机 Mariner,通用公司的 XV-5等。这种飞行器的缺点是涵道增 加了较重的重量，增加较多的迎风阻力，同时妨碍了机内载荷和设备的布置， 或者减小了机翼的有效升力面积。 Among the known aircrafts having a vertical take-off and landing function and having a fixed-wing aircraft function, they are roughly classified into the following categories. First, as shown in Figure 1, the combination of the ducted fan and the preceding blade 11 is combined. Such as Sikorsky's drone Mariner, GM's XV-5 and so on. The disadvantage of this type of aircraft is that the ducts add heavier weight, increase the windward resistance, prevent the load and equipment arrangement in the machine, or reduce the effective lift area of the wing.
二、倾转动力实现垂直起降的固定翼飞机。如图 2中的 V22等， 其中螺 旋桨为 12。这类飞机在起飞时动力装置的推（拉）力垂直地面使飞机垂直离 地， 然后在空中逐渐使动力装置的推 （拉） 力， 转向飞机前进方向， 使飞机 像常规固定翼飞机一样向前飞行。 但其转向机构复杂， 造价贵， 可靠性差， 特别动力***转向时的 （飞机无前进速度时）安定性和操纵性， 一直是困扰 航空技术人员的难题。 Second, the fixed-wing aircraft that achieves vertical take-off and landing with tilting force. As shown in Figure 2, V22, etc., where the propeller is 12. The thrusting force of the power unit on the vertical plane of the aircraft makes the aircraft vertically off the ground, and then gradually pushes the thrusting force of the power unit in the air to the forward direction of the aircraft, so that the aircraft is like a conventional fixed-wing aircraft. Before flying. However, its steering mechanism is complex, expensive, and of poor reliability. The stability and maneuverability of the special powertrain when it is turned (the aircraft has no forward speed) has always been a problem for aviation technicians.
三、 旋翼机翼共用飞机。 如图 3a-3c中波音公司的 "蜻蜓"飞机。 这类 飞机机翼 13可以变为旋翼使用， 可以实现垂直起降。 和倾转动力飞行器一
样， 也存在结构复杂， 造价贵， 可靠性差等问题。 Third, the rotor wing shares the aircraft. Boeing's "蜻蜓" aircraft in Figures 3a-3c. This type of aircraft wing 13 can be used as a rotor to achieve vertical takeoff and landing. And tilting force aircraft As such, there are also problems such as complicated structure, expensive construction, and poor reliability.
四、如图 4a-4c中底部安装升力发动机 14的方案。这类飞机都是为了解 决固定翼飞机垂直起降的问题，升力发动机只是为了实现垂直起降时的升力 或者兼作一部分方向控制，不具备完全的直升机飞行模式，如多尼尔 D0.231 等飞机。 4. The solution for installing the lift engine 14 at the bottom as shown in Figures 4a-4c. This type of aircraft is designed to solve the problem of vertical take-off and landing of fixed-wing aircraft. The lift engine is only used to achieve lift during vertical take-off or as part of directional control. It does not have a complete helicopter flight mode, such as Dornier D0.231. .
五、 前苏联的雅克 -38 战机只有两台升力发动机和一台升力-巡航发动 机， 机体内的升力发动机也降低了单发失效对安全的威胁。但升力发动机安 装在机体内， 也是有其问题的。 首先， 炽热的喷气里发动机进气口很近， 容 易造成喷气回吸问题。 第二， 高速喷气在机体下延地面向两侧流动， 而机体 上方除升力发动机进气口附近外， 空气相对静止， 造成使机体向地面吸附的 效果， 即所谓 suck d0wn。 另外， 因为其要在甲板上垂直起落， 其向下喷出 的高温气体对甲板的烧蚀也相当严重， 所以这种战机很不实用。 5. The Jacques-38 fighters of the former Soviet Union had only two lift engines and one lift-cruise engine. The lift engine inside the aircraft also reduced the safety threat of single-shot failure. However, the lift engine is installed in the body and has its problems. First of all, the hot air intake of the engine is very close, which is easy to cause jet back suction. Second, the high-speed jet flows down the side of the body to the sides, and the air is relatively stationary above the air intake of the lift engine above the body, causing the body to adsorb to the ground, so-called suck d 0wn . In addition, because it is to rise and fall vertically on the deck, the high temperature gas that is ejected downwards is also quite ablated to the deck, so this type of fighter is not practical.
因此航空界迫切需要寻找一种结构简单、性能可靠的兼有固定翼飞机和 旋翼直升机性能且在两种飞行模式之间能随时自由转换的飞行器。 发明内容 Therefore, there is an urgent need in the aviation industry to find an aircraft that has a simple structure and reliable performance and has the performance of a fixed-wing aircraft and a rotary-wing helicopter, and can be freely converted between the two flight modes at any time. Summary of the invention
本发明要解决的技术问题是为了克服现有技术中的上述缺陷， 提供一种 结构简单、性能可靠的兼有固定翼飞机和旋翼直升机性能且在两种飞行模式 之间能随时自由转换的飞行器。 The technical problem to be solved by the present invention is to overcome the above-mentioned drawbacks in the prior art, and to provide an aircraft with both simple structure and reliable performance, which can combine the performance of a fixed-wing aircraft and a rotary-wing helicopter, and can be freely converted between two flight modes at any time. .
本发明是通过下述技术方案来解决上述技术问题的： The present invention solves the above technical problems by the following technical solutions:
一种固定翼与电动多桨组成的具有直升机功能的复合飞行器，包括一套 固定翼飞机组件， 该组件包括机身、 机翼和固定翼舵面控制***， 其特点在 于， 该飞行器还包括一组电动多桨动力***和一个总控制器， 该总控制器包 括该固定翼舵面控制***和用于控制所述电动多桨动力***工作的电动多 桨控制***， 该总控制器还用于控制该固定翼舵面控制***和电动多桨控制 ***单独工作或者协同工作；所述电动多桨动力***的桨叶旋转平面与机身 中心轴垂直。
优选地， 该电动多桨控制***用于控制飞行器的升降、 姿态和航向。 优选地，该电动多桨控制***用于通过增减所有桨叶的转速和 /或螺距控 制飞行器的升降。 A helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade, comprising a fixed-wing aircraft assembly, the assembly comprising a fuselage, a wing and a fixed-wing control surface control system, characterized in that the aircraft further comprises a a group of electric multi-blade power system and a master controller, the master controller comprising the fixed wing control surface control system and an electric multi-blade control system for controlling operation of the electric multi-blade power system, the total controller is further used for The fixed-wing rudder surface control system and the electric multi-blade control system are controlled to work alone or in cooperation; the blade rotation plane of the electric multi-blade power system is perpendicular to the central axis of the fuselage. Preferably, the electric multi-blade control system is used to control the lift, attitude and heading of the aircraft. Preferably, the electric multi-blade control system is used to control the lift of the aircraft by increasing or decreasing the rotational speed and/or pitch of all the blades.
优选地， 该电动多桨控制***用于通过减小在飞行方向上相对于飞行器 的重心靠前的桨叶的转速和 /或螺距，同时增加在飞行方向上相对于飞行器的 重心靠后的桨叶的转速和 /或螺距， 控制飞行器的姿态。 Preferably, the electric multi-blade control system is for increasing the rotational speed and/or pitch of the blade in front of the center of gravity of the aircraft in the flight direction while increasing the paddle in the flight direction relative to the center of gravity of the aircraft The speed and/or pitch of the leaf controls the attitude of the aircraft.
优选地， 该电动多桨控制***用于通过增加与飞行器转向反向的桨叶的 转速和 /或螺距， 减少与飞行器转向同向的桨叶的转速和 /或螺距， 控制飞行 器的航向。 Preferably, the electric multi-blade control system is operative to control the heading of the aircraft by increasing the rotational speed and/or pitch of the blades that are opposite to the steering of the aircraft, reducing the rotational speed and/or pitch of the blades in the same direction as the steering of the aircraft.
优选地，所述电动多桨动力***至少为四套，所述各桨处于同一平面内， 且该平面与机身中心线垂直。 Preferably, the electric multi-blade power system is at least four sets, the each paddle being in the same plane, and the plane is perpendicular to the fuselage center line.
优选地， 所述各桨分别设置在该机身的两侧和机翼上下侧， 相对于该飞 行器的重心呈对称放置。 Preferably, the paddles are respectively disposed on both sides of the fuselage and upper and lower sides of the wing, and are symmetrically placed with respect to the center of gravity of the aircraft.
优选地，所述每套电动多桨动力***或者桨均通过一支撑臂连接到所述 机身或者机翼上。 Preferably, each of the electric multi-blade power systems or paddles is coupled to the fuselage or wing by a support arm.
优选地，所述各套电动多桨动力***中的若干套***或者若干套桨共用 一支撑臂连接到该机身或者机翼上。 Preferably, several sets of systems or sets of paddles in each set of electric multi-blade power systems share a support arm to the fuselage or wing.
优选地， 所述电动多桨动力***的动力装置为电机。 Preferably, the power device of the electric multi-blade power system is a motor.
优选地，所述总控制器用于控制在从多桨直升机飞行模式到固定翼飞行 模式的转换过程中， 飞行器由从悬停开始通过控制机身上方桨叶转速增加， 下方转速减小， 飞行器飞行方向逐渐从垂直方向转向水平方向， 飞行器逐步 转向固定翼飞机水平运动的方式， 当对应机身方向的空速大于失速速度后， 各桨的转速变为相同， 同时固定翼舵面控制***对舵面进行控制， 就完成了 多桨直升机飞行模式与固定翼飞行模式的转换。 Preferably, the overall controller is used to control the transition from the multi-blade helicopter flight mode to the fixed-wing flight mode, the aircraft is increased from the hovering by controlling the upper blade speed of the fuselage, the lower speed is reduced, and the aircraft is flying. The direction gradually turns from the vertical direction to the horizontal direction, and the aircraft gradually turns to the horizontal movement of the fixed-wing aircraft. When the airspeed corresponding to the direction of the fuselage is greater than the stall speed, the rotation speed of each propeller becomes the same, and the fixed-rudder control system of the fixed-rudder is opposite to the rudder. The control of the surface completes the conversion of the multi-blade helicopter flight mode and the fixed-wing flight mode.
优选地，所述总控制器用于控制在从固定翼飞行模式到多桨直升机飞行 模式转换过程中， 飞行器由水平运动开始， 控制机身下方桨叶转速先增加， 上方桨叶转速在达到一定迎角后逐步增加， 飞行器飞行方向逐渐从水平爬升
后转向垂直于地面， 空速变为零， 实现固定翼飞行模式到多桨直升机飞行模 式的转换。 Preferably, the total controller is used to control the transition from the fixed-wing flight mode to the multi-blade helicopter flight mode, the aircraft starts from the horizontal motion, and the blade speed below the control fuselage increases first, and the upper blade speed reaches a certain welcome. After the angle gradually increases, the flight direction of the aircraft gradually climbs from the horizontal The rear turn is perpendicular to the ground and the airspeed becomes zero, enabling the conversion of the fixed-wing flight mode to the multi-blade helicopter flight mode.
优选地， 所述迎角角度为 10° -30° 。 Preferably, the angle of attack angle is 10° -30°.
优选地， 所述飞行器的尾翼结构为不带尾翼的飞翼式、 "^ "、 " u "、 "丄"形、 "T"字形、 "V"形或 " Λ，，形。 Preferably, the tail structure of the aircraft is a flying wing type without a tail, "^", "u", "丄" shape, "T" shape, "V" shape or "Λ, shape.
优选地， 该飞行器还包括一组额外设置于机身尾部的垂直起降用的起落 架。 Preferably, the aircraft further includes a set of landing gears for vertical take-off and landing that are additionally disposed at the rear of the fuselage.
优选地， 所述桨为可折叠桨。 Preferably, the paddle is a foldable paddle.
优选地， 所述飞行器包括一固定翼动力***。 Preferably, the aircraft comprises a fixed wing power system.
优选地， 所述固定翼动力***为电动或者燃油动力。 Preferably, the fixed wing power system is electric or fuel powered.
本发明的积极进步效果在于： 本发明的复合飞行器不但兼有固定翼飞机和旋翼直升机的性能， 而且能 够在这两种飞行模式之间自由的转换， 既可以像直升机一样垂直起降和飞 行， 可以像固定翼飞机一样起降和飞行。 The positive progress of the present invention is: The composite aircraft of the present invention not only combines the performance of a fixed-wing aircraft and a rotary-wing helicopter, but also can freely convert between the two flight modes, and can take off and land vertically like a helicopter. It can take off and land and fly like a fixed-wing aircraft.
本发明因为采用电动， 所以重量增加很轻， 从而使固定翼飞机模式时增 加的死重 （旋翼直升机部分的重量）很少。 同时由于是电动动力方案， 整个 飞机噪音很小， 旋翼直升机向下吹的气流无高温， 比用传统发动机的其他飞 行器更加环保。 另外， 采用电机作为动力装置， 可以使电动多旋翼动力*** 的重量控制在整个飞机的 20%以内， 比采用传统的动力***要轻很多， 从而 使飞机更加易于控制， 节省能量。 Since the present invention uses electric power, the weight increase is light, so that the dead weight (the weight of the rotor helicopter portion) which is increased in the fixed-wing aircraft mode is small. At the same time, due to the electric power scheme, the noise of the whole aircraft is very small, and the airflow from the rotor helicopter is no high temperature, which is more environmentally friendly than other aircraft with traditional engines. In addition, the use of a motor as a power unit allows the weight of the electric multi-rotor power system to be controlled within 20% of the entire aircraft, which is much lighter than the conventional power system, making the aircraft easier to control and save energy.
本发明在结构上更加简单， 不需要很复杂的转向结构， 也不会影响机内 载荷和设备的布置。 最后， 本发明应用广泛， 包括民航领域和军事领域， 不 仅适用于模型飞机、 而且适用于无人驾驶飞机， 以及载人飞机等等。 附图说明 The present invention is structurally simpler, does not require a very complicated steering structure, and does not affect the internal load and equipment arrangement. Finally, the invention is widely used, including in the civil aviation and military fields, not only for model aircraft, but also for drones, as well as manned aircraft and the like. DRAWINGS
图 1为现有的将涵道风扇和前行桨叶结合起来的飞行器结构示意图。 图 2为现有的倾转动力实现垂直起降的飞行器结构示意图。
图 3a-3c为现有的旋翼机翼共用的飞行器结构示意图。 Fig. 1 is a schematic view showing the structure of an existing aircraft combining a ducted fan and a preceding blade. FIG. 2 is a schematic structural view of an aircraft that realizes vertical take-off and landing with the existing tilting force. Figures 3a-3c are schematic views of the structure of an aircraft shared by existing rotor wings.
图 4a-4c为现有的底部安装升力发动机的飞行器结构示意图。 4a-4c are schematic views of the structure of an existing bottom mounted lift engine.
图 5a-5c分别为本发明第一实施例的飞行器的俯视图、正视图和侦 图 6为本发明的飞行器的控制***的结构示意图。 5a-5c are a plan view, a front view and a view of an aircraft according to a first embodiment of the present invention, respectively, showing a structural schematic view of a control system of the aircraft of the present invention.
图 7a、 7b分别为本发明第二实施例的飞行器的正视图和俯视图。 具体实施方式 7a, 7b are front and top views, respectively, of an aircraft according to a second embodiment of the present invention. detailed description
下面结合附图给出本发明较佳实施例， 以详细说明本发明的技术方案。 第一实施例 DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. First embodiment
如图 5所示为本发明的一种复合飞行器， 其包括一套固定翼飞机组件， 该组件包括机身 1、主翼 2、尾翼 3。也可视情况而定安装固定翼动力***（也 称固定翼飞机动力***）， 即为固定翼飞机组件提供动力的***。 本领域技 术人员应当理解， 全文中出现的主翼和固定翼所指的是同一个部件， 叫做固 定翼是相对于旋翼来讲的； 叫做主翼， 是从飞机的结构组成上来说， 相对于 尾翼来讲的。 在该固定翼飞机组件的基础上， 增加了四套电动多桨动力*** 4， 但不限于四套， 也可以为六套或者八套等， 而电动多桨动力*** 4可以 采用现有的具体组成和结构来实现， 所以不再赘述。 As shown in FIG. 5, a composite aircraft of the present invention includes a fixed-wing aircraft assembly including a fuselage 1, a main wing 2, and a rear wing 3. A fixed-wing power system (also known as a fixed-wing aircraft power system), a system that powers fixed-wing aircraft components, may also be installed as appropriate. It should be understood by those skilled in the art that the main wing and the fixed wing appearing in the whole article refer to the same component, that is, the fixed wing is relative to the rotor; the main wing is called from the structural composition of the aircraft, relative to the tail wing. Said. On the basis of the fixed-wing aircraft component, four sets of electric multi-paddle power system 4 are added, but not limited to four sets, or six sets or eight sets, etc., and the electric multi-blade power system 4 can adopt the existing specific The composition and structure are implemented, so I won't go into details.
而电动多桨动力*** 4包括动力装置和桨，所述各桨可以设置在同一平 面内， 且该平面与机身中心线垂直， 即围绕在机身中心轴周围成近似等角放 射状分布。 具体地， 可以把桨分别设置在该机身的两侧和主翼上下侧， 相对 于该飞行器的重心呈对称放置， 将动力装置设置于机身上。 或者将整套电动 多桨动力*** 4分别设置在该机身的两侧和主翼上下侧，相对于该飞行器的 重心呈对称放置。 这样的设置保证了飞行器整体重心处于机身的中心线上， 使飞机在起降和飞行过程中始终保持平衡， 不影响其工作状态。 当然， 也可 以采用其他的位置设置，只要能达到前述效果的设置方式皆可。本实施例中， 每套电动多桨动力*** 4整体地或者桨单独地通过一支撑臂 5连接到主翼 2 上， 当然在其他实施例中， 也可以将各套电动多桨动力***中的若干套***
或者桨共用一支撑臂连接到机身或者机翼上。 The electric multi-blade power system 4 includes a power unit and a paddle, and the paddles may be disposed in the same plane, and the plane is perpendicular to the centerline of the fuselage, that is, approximately equiangularly distributed around the central axis of the fuselage. Specifically, the paddles may be respectively disposed on both sides of the fuselage and the upper and lower sides of the main wing, symmetrically placed with respect to the center of gravity of the aircraft, and the power device is disposed on the fuselage. Alternatively, the entire electric multi-blade power system 4 is disposed on both sides of the fuselage and the upper and lower sides of the main wing, respectively, symmetrically placed with respect to the center of gravity of the aircraft. This arrangement ensures that the overall center of gravity of the aircraft is on the centerline of the fuselage, so that the aircraft is always balanced during take-off and landing and does not affect its working condition. Of course, other position settings can also be used, as long as the above effects can be achieved. In this embodiment, each set of electric multi-blade power system 4 is integrally or paddlely connected to the main wing 2 through a support arm 5, although in other embodiments, several sets of electric multi-blade power systems may also be used. Set system Or the paddles share a support arm connected to the fuselage or the wing.
本实施例中的电动多桨动力***采用电动动力***，包括电机和与该电 机连接的旋翼， 可以根据实际情况决定是否添加变速箱。 因为采用电动， 所 以重量增加很轻， 从而使固定翼飞机模式时增加的死重（旋翼直升机部分的 重量） 很少。 同时由于是电动动力方案， 整个飞机噪音很小， 旋翼直升机向 下吹的气流无高温， 比用传统发动机的其他飞行器更加环保。 而固定翼动力 ***的动力也可以采用电动或者其他动力。固定翼动力***的数量可以为单 套或者多套，固定翼动力***的螺旋桨位于机身前方、机身后部或机身两侧， 或者前后方同时设置均可。 The electric multi-blade power system in this embodiment employs an electric power system including a motor and a rotor connected to the motor, and whether or not to add a gearbox can be determined according to actual conditions. Because of the electric power, the weight increase is light, so that the dead weight (the weight of the rotor helicopter part) is small in the fixed-wing aircraft mode. At the same time, due to the electric power scheme, the noise of the whole aircraft is very small, and the airflow blown down by the rotorcraft has no high temperature, which is more environmentally friendly than other aircraft with conventional engines. The power of the fixed-wing power system can also be powered by electric or other power. The number of fixed-wing power systems can be single or multiple sets. The propellers of the fixed-wing power system can be located at the front of the fuselage, at the rear of the fuselage or on both sides of the fuselage, or at the same time.
为保证本发明的飞行器在两种模式之间自由的切换， 配备一个总控制器 In order to ensure that the aircraft of the invention is free to switch between the two modes, a master controller is provided
6以实现在两种模式之间的切换控制。 该总控制器 6包括固定翼舵面控制系 统 61和用于控制所述电动多桨动力***工作的电动多桨控制*** 62， 该总 控制器还用于控制该固定翼舵面控制*** 61和电动多桨控制*** 62单独工 作或者协同工作。 因为固定翼舵面控制*** 61可以采用现有的固定翼飞机 的控制***结构和组成来实现， 所以在此不做赘述。 这里， 固定翼舵面控制 *** 61单独工作时， 配合各桨的转速相同， 对应的是固定翼飞机模式； 电 动多桨控制*** 62单独工作时对应的是直升机模式， 用于控制飞行器的升 降、姿态和航向，而两个***协同工作时称之为固定翼飞机直升机混合模式。 为便于本领域技术人员的理解，下面从整个飞机的起降过程和飞行过程 来详细描述这三种模式的具体工作原理。 需要明确的是， 飞行过程是指飞机 在起飞之后降落之前的水平飞行过程，而升降过程是指飞机起飞和降落的过 程。 6 to achieve switching control between the two modes. The master controller 6 includes a fixed-wing rudder surface control system 61 and an electric multi-blade control system 62 for controlling the operation of the electric multi-blade power system, the master controller also being used to control the fixed-wing rudder surface control system 61 and The electric multi-blade control system 62 works alone or in concert. Because the fixed-wing control surface control system 61 can be implemented by the control system structure and composition of the existing fixed-wing aircraft, it will not be described here. Here, when the fixed-wing control surface control system 61 is operated alone, the rotation speed of each of the propellers is the same, corresponding to the fixed-wing aircraft mode; the electric multi-blade control system 62 is operated in a helicopter mode for controlling the lifting and lowering of the aircraft, Attitude and heading, while the two systems work together, they are called fixed-wing aircraft helicopter hybrid mode. To facilitate the understanding of those skilled in the art, the specific working principles of the three modes are described in detail below from the takeoff and landing process and flight process of the entire aircraft. It should be clarified that the flight process refers to the horizontal flight process before the aircraft landed after take-off, and the lifting process refers to the process of take-off and landing of the aircraft.
其中起降过程可以采用直升机模式、 固定翼飞机模式： The takeoff and landing process can be in helicopter mode or fixed-wing aircraft mode:
1、 在直升机模式起降时， 飞行器垂直于地面放置， 即机身中心线垂直 于地面， 而桨叶的旋转平面平行于地面， 从而实现 4组 （或者以上） 的电动 多桨控制*** 62完全按照直升机模式飞行。 使用垂直起降功率消耗较大，
但使用旋翼升降***时间很短， 起降消耗能量占整个飞行能耗能量比例不 大， 故这种方式是此飞行器主要的起降模式， 此时飞机像一般直升机一样起 降。 这种起降方式不但适用于模型飞机和无人机， 而且也适用于载人飞机， 在载人飞机中设置现有的悬挂装置， 使飞机无论是升降还是水平飞行时， 人 体都能够保持正常的状态， 不会倾斜。 1. When taking off and landing in helicopter mode, the aircraft is placed perpendicular to the ground, that is, the centerline of the fuselage is perpendicular to the ground, and the plane of rotation of the blades is parallel to the ground, so that 4 sets (or more) of the electric multi-blade control system 62 are completely realized. Fly in helicopter mode. Use vertical take-off and power consumption is large, However, the use of the rotor lift system is very short, and the energy consumption of the take-off and landing energy accounts for a small proportion of the energy consumption of the entire flight. Therefore, this method is the main take-off and landing mode of the aircraft, and the aircraft takes off and land like a general helicopter. This method of take-off and landing is applicable not only to model aircraft and drones, but also to manned aircraft. The existing suspension device is installed in the manned aircraft, so that the human body can maintain normal when the aircraft is moving up or down horizontally. The state will not be tilted.
2、 在固定翼飞机模式起降时， 飞行器水平置于地面， 即机身中心线平 行于地面， 而桨叶的旋转平面近似垂直于地面， 各桨转速相同， 从而使 4组 (或者以上） 电动多桨控制*** 62作为固定翼飞机动力***组。 飞机像一 般固定翼飞机一样在跑道上起降。 2. When taking off and landing in the fixed-wing aircraft mode, the aircraft is horizontally placed on the ground, that is, the centerline of the fuselage is parallel to the ground, and the rotation plane of the blades is approximately perpendicular to the ground, and the speed of each paddle is the same, thus making 4 groups (or more) The electric multi-blade control system 62 acts as a fixed-wing aircraft powertrain group. The plane took off and landed on the runway like a fixed-wing aircraft.
而飞行模式可以分为直升机模式、 固定翼飞机模式： The flight mode can be divided into helicopter mode and fixed-wing aircraft mode:
1、 在直升机模式飞行时， 4组 （或者以上） 电动多桨控制*** 62完全 按照直升机模式飞行，飞行器可以完成所有直升机的功能，从而能完成航拍、 固定位置侦查等任务， 此时飞机像一般直升机一样飞行。 此种方式飞行时， 机身中心线是垂直于地面的， 而桨叶的旋转平面平行于地面。 其中， 电动多 桨控制***通过减小在飞行方向上相对于飞行器的重心靠前的桨的转速和 / 或螺距，同时增加在飞行方向上相对于飞行器的重心靠后的桨的转速和 /或螺 距， 来控制飞行器的姿态。 电动多桨控制***通过增加与飞行器转向反向的 桨的转速和 /或螺距， 减少与飞行器转向同向的桨的转速和 /或螺距， 控制飞 行器的航向。 1. When flying in helicopter mode, 4 groups (or more) of the electric multi-paddle control system 62 can completely fly according to the helicopter mode, and the aircraft can complete the functions of all the helicopters, so that the tasks such as aerial photography and fixed position detection can be completed. Fly like a helicopter. When flying in this way, the centerline of the fuselage is perpendicular to the ground, and the plane of rotation of the blades is parallel to the ground. Wherein the electric multi-blade control system increases the rotational speed and/or the pitch of the paddle in front of the center of gravity of the aircraft in the flight direction while increasing the rotational speed of the paddle in the flight direction relative to the center of gravity of the aircraft and/or Pitch to control the attitude of the aircraft. The electric multi-blade control system controls the heading of the aircraft by increasing the speed and/or pitch of the propellers that are opposite to the steering of the aircraft, reducing the speed and/or pitch of the propellers in the same direction as the aircraft's steering.
具体来讲， 就是使其中一半的桨顺时针方向旋转， 另一半桨逆时针方向 旋转， 在直升机模式下， 可以利用电子陀螺控制 4个桨的转速， 形成一个稳 定的旋翼直升机飞行平台。 通过改变桨转速， 改变 4个桨的升力和扭矩， 从 而控制旋翼直升机向各个方向的飞行及转向。其中电子陀螺为本领域常用的 装置， 技术人员可根据具体需要自己选择其类型。 Specifically, half of the paddles are rotated clockwise and the other half of the paddles are rotated counterclockwise. In helicopter mode, the electronic gyro can be used to control the speed of four paddles to form a stable rotor helicopter flight platform. By changing the paddle speed, the lift and torque of the four blades are changed to control the flight and steering of the rotor helicopter in all directions. Among them, the electronic gyro is a commonly used device in the field, and the technician can select the type according to the specific needs.
2、 在固定翼飞机模式飞行时， 4组 （或者以上） 电动多桨控制*** 62 做为固定翼机动力***。 可以完成所有固定翼飞机的功能。 优点是功耗小， 飞行距离和时间长。 此模式是此飞行器的主要飞行模式。 在转换成固定翼机
模式后由于不需要那么大的动力， 所以可以只开其中的部分桨， 其他桨可以 折叠以降低固定翼飞机模式下的飞行阻力。 2. In the fixed-wing aircraft mode, four (or more) electric multi-blade control systems 62 are used as the fixed-wing power system. The function of all fixed-wing aircraft can be completed. The advantages are low power consumption, long flight distance and long time. This mode is the main flight mode of this aircraft. Converted to a fixed wing aircraft Since the mode does not require such a large amount of power, only a part of the paddles can be opened, and the other paddles can be folded to reduce the flight resistance in the fixed-wing aircraft mode.
当固定翼舵面控制*** 61和电动多桨控制*** 62协同工作时，在从多 桨直升机模式飞行到固定翼模式飞行的转换过程中， 飞行器由从悬停开始通 过控制机身上方桨叶转速增加， 下方转速减小， 飞行器飞行方向逐渐从垂直 方向转向水平方向， 飞行器逐步转向固定翼飞机水平运动的方式， 当对应机 身方向的空速大于失速速度后， 各桨的转速变为相同， 同时固定翼舵面控制 ***对舵面进行控制，就完成了多桨直升机模式飞行与固定翼模式飞行的转 换。 也就是说直升机模式升降或者飞行时， 桨是起到直升机旋翼的功能； 而 转换到固定翼模式时， 各桨转速相同， 此时桨起到的是固定翼飞机推进桨的 作用。 When the fixed-wing rudder surface control system 61 and the electric multi-blade control system 62 work together, during the transition from the multi-blade helicopter mode flight to the fixed-wing mode flight, the aircraft is controlled from the hovering speed by controlling the blade speed above the fuselage Increase, the lower speed decreases, the flight direction of the aircraft gradually turns from the vertical direction to the horizontal direction, and the aircraft gradually turns to the horizontal movement of the fixed-wing aircraft. When the airspeed corresponding to the fuselage direction is greater than the stall speed, the speed of each propeller becomes the same. At the same time, the fixed-wing control system controls the rudder surface, which completes the conversion of multi-blade helicopter mode flight and fixed-wing mode flight. That is to say, when the helicopter mode is lifted or flies, the paddle functions as a helicopter rotor; when the switch is converted to the fixed-wing mode, the speed of each paddle is the same, and the paddle plays the role of the fixed-wing aircraft propeller.
在从固定翼模式飞行到多桨直升机模式飞行转换过程中， 飞行器由水平 运动开始， 控制机身下方桨叶转速先增加， 上方桨叶转速在飞行器达到一定 迎角 （比如 10° -30° 之间） 后逐步增加， 飞行器飞行方向逐渐从水平爬升 后转向垂直于地面， 空速变为零， 本领域技术人员应当理解也包括接近于零 的情况， 实现固定翼模式飞行到多桨直升机模式飞行的转换。 以上两种情形 可以分别通过两个协同工作模式控制器来实现。 During the flight transition from fixed-wing mode to multi-blade helicopter mode, the aircraft starts with horizontal motion, and the blade speed below the control fuselage increases first, and the upper blade speed reaches a certain angle of attack (such as 10° -30°). After the gradual increase, the flight direction of the aircraft gradually climbs from the horizontal to the vertical, and the airspeed becomes zero. Those skilled in the art should understand that the situation is also close to zero, and the fixed-wing mode flight to the multi-blade helicopter mode flight is realized. Conversion. The above two situations can be achieved by two cooperative working mode controllers respectively.
总结来讲，就是说在整个直升机模式中，机身中心线都是垂直于地面的， 当然这种垂直是近似的垂直， 本领域技术人员应当理解。 In summary, that is to say, in the entire helicopter mode, the fuselage center line is perpendicular to the ground, and of course this vertical is approximately vertical, as will be understood by those skilled in the art.
以上提到的总控制器、各控制***的具体制作与实现均可通过现有的电 子控制方式或者软件方式来实现， 在此不做赘述。 The specific production and implementation of the above-mentioned general controller and each control system can be realized by the existing electronic control mode or software mode, and will not be described herein.
在其他实施例中， 本发明的固定翼机组件的尾翼结构还可以为其他类 型，如不带尾翼的飞翼式、 "丄，，形、 " "、 " "、 "T"字形、 "V"形或" Λ " 形等等。 In other embodiments, the empennage structure of the fixed wing assembly of the present invention may also be of other types, such as a flying wing without a tail, "丄,", "", "", "T", "V" "Shape or" Λ" shape and so on.
第二实施例 Second embodiment
如图 7a、 7b, 本实施例与第一实施例的不同之处主要在于： 本实施例中 有 6套电动多桨动力***， 呈放射状安装在机身上靠近主翼的位置处。 其余
部分与第一实施例基本相同。 7a, 7b, the difference between this embodiment and the first embodiment is mainly: In this embodiment, there are six sets of electric multi-blade power systems, which are radially mounted on the fuselage at a position close to the main wing. the remaining The part is basically the same as the first embodiment.
图中， 升降时 6个桨全部增加或者减小转速。 向左侧飞时： 桨 73、 74 增速， 桨 71、 76减速。 向右侧飞时： 桨 71、 76增速， 桨 73、 74减速。 左 转向时： 桨 71、 73、 75增速， 桨 72、 74、 76减速； 右转向时： 桨 72、 74、 76增速， 桨 71、 73、 75减速； 前飞： 桨 74、 76增速， 桨 71、 73减速； 后 飞： 桨 71、 73增速， 桨 74、 76减速。 In the figure, all the 6 paddles increase or decrease the speed when lifting. When flying to the left: Paddles 73, 74 increase speed, and Paddles 71, 76 decelerate. When flying to the right: Paddles 71, 76 increase speed, and Paddles 73, 74 decelerate. When turning to the left: Paddles 71, 73, 75 increase speed, Paddles 72, 74, 76 decelerate; Right turn: Paddles 72, 74, 76 increase speed, Paddles 71, 73, 75 decelerate; Front fly: Paddles 74, 76 increase Speed, Paddle 71, 73 deceleration; After fly: Paddle 71, 73 increase speed, Paddle 74, 76 decelerate.
虽然以上描述了本发明的具体实施方式，但是本领域的技术人员应当理 解， 这些仅是举例说明， 本发明的保护范围是由所附权利要求书限定的。 本 领域的技术人员在不背离本发明的原理和实质的前提下， 可以对这些实施方 式做出多种变更或修改， 但这些变更和修改均落入本发明的保护范围。
While the invention has been described with respect to the embodiments of the present invention, it is understood that the scope of the invention is defined by the appended claims. A person skilled in the art can make various changes or modifications to these embodiments without departing from the spirit and scope of the invention, and such changes and modifications fall within the scope of the invention.
Claims
1、 一种固定翼与电动多桨组成的具有直升机功能的复合飞行器， 包括 一套固定翼飞机组件， 该组件包括机身、 机翼和固定翼舵面控制***， 其特 征在于， 该飞行器还包括一组电动多桨动力***和一个总控制器， 该总控制 器包括该固定翼舵面控制***和用于控制所述电动多桨动力***工作的电 动多桨控制***， 该总控制器还用于控制该固定翼舵面控制***和电动多桨 控制***单独工作或者协同工作； 所述电动多桨动力***的桨叶旋转平面与 机身中心轴垂直。 1. A helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade, comprising a fixed-wing aircraft assembly, the assembly comprising a fuselage, a wing and a fixed-wing control surface control system, characterized in that the aircraft is further The utility model comprises a set of electric multi-blade power system and a total controller, the total controller comprising the fixed wing control surface control system and an electric multi-blade control system for controlling the operation of the electric multi-blade power system, the total controller further The fixed-rudder control surface control system and the electric multi-blade control system are controlled to work alone or in cooperation; the blade rotation plane of the electric multi-blade power system is perpendicular to the central axis of the fuselage.
2、 如权利要求 1所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 该电动多桨控制***用于控制飞行器的升降、 姿态 和航向。 2. A helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 1, wherein the electric multi-blade control system is used to control the lifting, attitude and heading of the aircraft.
3、 如权利要求 2所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 该电动多桨控制***用于通过增减所有桨叶的转速 和 /或螺距控制飞行器的升降。 3. The helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 2, wherein the electric multi-blade control system is used to control the aircraft by increasing or decreasing the rotational speed and/or pitch of all the blades. Lifting.
4、 如权利要求 2所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 该电动多桨控制***用于通过减小在飞行方向上相 对于飞行器的重心靠前的桨叶的转速和 /或螺距，同时增加在飞行方向上相对 于飞行器的重心靠后的桨叶的转速和 /或螺距， 控制飞行器的姿态。 4. The helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 2, wherein the electric multi-blade control system is used to reduce the center of gravity of the aircraft relative to the aircraft in the flight direction. The rotational speed and/or pitch of the blades, while increasing the rotational speed and/or pitch of the blades in the flight direction relative to the center of gravity of the aircraft, controls the attitude of the aircraft.
5、 如权利要求 2所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 该电动多桨控制***用于通过增加与飞行器转向反 向的桨叶的转速和 /或螺距，减少与飞行器转向同向的桨叶的转速和 /或螺距， 控制飞行器的航向。 5. The helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 2, wherein the electric multi-blade control system is used to increase the rotational speed of the blade opposite to the steering of the aircraft and/or Or pitch, reducing the speed and / or pitch of the blades in the same direction as the aircraft steering, controlling the heading of the aircraft.
6、 如权利要求 1所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 所述电动多桨动力***至少为四套， 所述各桨处于 同一平面内， 且该平面与机身中心线垂直。 6. The helicopter-equipped composite aircraft comprising the fixed wing and the electric multi-blade according to claim 1, wherein the electric multi-blade power system is at least four sets, and the each paddle is in the same plane, and This plane is perpendicular to the centerline of the fuselage.
7、 如权利要求 6所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 所述各桨分别设置在该机身的两侧和机翼上下侧， 相对于该飞行器的重心呈对称放置。 7. The helicopter-equipped complex of the fixed wing and the electric multi-blade according to claim 6. The aircraft is characterized in that each of the blades is disposed on both sides of the fuselage and on the upper and lower sides of the wing, and is symmetrically placed with respect to the center of gravity of the aircraft.
8、 如权利要求 6所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 所述每套电动多桨动力***或者桨均通过一支撑臂 连接到所述机身或者机翼上。 8. The helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 6, wherein each of the electric multi-blade power systems or the paddles is connected to the fuselage through a support arm. Or on the wing.
9、 如权利要求 6所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 所述各套电动多桨动力***中的若干套***或者若 干套桨共用一支撑臂连接到该机身或者机翼上。 9. The helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 6, wherein a plurality of sets of systems or sets of paddles in each set of electric multi-blade power systems share a support arm Connect to the fuselage or wing.
10、如权利要求 1所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 所述电动多桨动力***的动力装置为电机。 A helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 1, wherein the power unit of the electric multi-blade power system is a motor.
11、如权利要求 1所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 所述总控制器用于控制在从多桨直升机飞行模式到 固定翼飞行模式的转换过程中， 飞行器由从悬停开始通过控制机身上方桨叶 转速增加， 下方转速减小， 飞行器飞行方向逐渐从垂直方向转向水平方向， 飞行器逐步转向固定翼飞机水平运动的方式， 当对应机身方向的空速大于失 速速度后，各桨的转速变为相同，同时固定翼舵面控制***对舵面进行控制， 就完成了多桨直升机飞行模式与固定翼飞行模式的转换。 11. A helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 1, wherein said master controller is adapted to control a transition process from a multi-blade helicopter flight mode to a fixed-wing flight mode. In the aircraft, the speed of the blade from the hovering is controlled by the upper part of the fuselage, the lower speed is reduced, the flight direction of the aircraft is gradually turned from the vertical direction to the horizontal direction, and the aircraft gradually turns to the horizontal movement of the fixed-wing aircraft. After the airspeed is greater than the stall speed, the speed of each paddle becomes the same, and the fixed-wing control system controls the rudder surface to complete the conversion of the multi-blade helicopter flight mode and the fixed-wing flight mode.
12、如权利要求 1所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器， 其特征在于， 所述总控制器用于控制在从固定翼飞行模式到多桨 直升机飞行模式转换过程中， 飞行器由水平运动开始， 控制机身下方桨叶转 速先增加， 上方桨叶转速在飞行器达到一定迎角后逐步增加， 飞行器飞行方 向逐渐从水平爬升后转向垂直于地面， 空速变为零， 实现固定翼飞行模式到 多桨直升机飞行模式的转换。 12. The helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 1, wherein said total controller is used to control a transition from a fixed wing flight mode to a multi-blade helicopter flight mode. The aircraft starts from the horizontal motion, and the speed of the blade below the control fuselage increases first. The speed of the upper blade gradually increases after the aircraft reaches a certain angle of attack. The flight direction of the aircraft gradually climbs from the horizontal to the vertical, and the airspeed becomes zero. Transform the fixed-wing flight mode to the multi-blade helicopter flight mode.
13、 如权利要求 12所述的固定翼与电动多桨组成的具有直升机功能的 复合飞行器， 其特征在于， 所述迎角角度为 10° -30° 。 13. The helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 12, wherein the angle of attack angle is 10° -30°.
14、如权利要求 1所述的固定翼与电动多桨组成的具有直升机功能的复 合飞行器，其特征在于，所述飞行器的尾翼结构为不带尾翼的飞翼式、 "^"、 〜"、 "丄"形、 "τ"字形、 "ν"形或 " Λ，，形。 14. The helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 1, wherein the tail structure of the aircraft is an airfoil type without a tail, "^", ~", "丄" shape, "τ" shape, "ν" shape or " Λ ,, shape.
15、如权利要求 1所述的固定翼与电动多桨组成的具有直升机功能的 合飞行器， 其特征在于， 该飞行器还包括一组额外设置于机身尾部的垂直 降用的起落架。 A helicopter-equipped combiner comprising a fixed wing and an electric multi-blade according to claim 1, wherein the aircraft further comprises a set of vertical lowering landing gears additionally disposed at the rear of the fuselage.
16、 如权利要求 1-15 任意一项所述的固定翼与电动多桨组成的具有 升机功能的复合飞行器， 其特征在于， 所述桨为可折叠桨。 A composite aircraft having a lift function comprising a fixed wing and an electric multi-blade according to any one of claims 1 to 15, wherein the paddle is a foldable paddle.
17、 如权利要求 16所述的固定翼与电动多桨组成的具有直升机功能 复合飞行器， 其特征在于， 所述飞行器包括一固定翼动力***。 17. A helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 16, wherein said aircraft comprises a fixed wing power system.
18、 如权利要求 17所述的固定翼与电动多桨组成的具有直升机功能 复合飞行器， 其特征在于， 所述固定翼动力***为电动或者燃油动力。 18. The helicopter-equipped composite aircraft comprising a fixed wing and an electric multi-blade according to claim 17, wherein the fixed-wing power system is electric or fuel-powered.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120397882.1 | 2011-10-17 | ||
| CN 201120397882 CN202728574U (en) | 2011-10-17 | 2011-10-17 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
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| Publication Number | Publication Date |
|---|---|
| WO2013056492A1 true WO2013056492A1 (en) | 2013-04-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/CN2011/083301 WO2013056492A1 (en) | 2011-10-17 | 2011-12-01 | Composite aircraft consisting of fixed-wing and electrically driven propellers and having helicopter functions |
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| Country | Link |
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| CN (1) | CN202728574U (en) |
| WO (1) | WO2013056492A1 (en) |
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| JP2022016568A (en) * | 2020-02-27 | 2022-01-21 | 義郎 中松 | Wing rotation vertical takeoff/landing long distance aircraft |
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| CN103640690A (en) * | 2013-09-02 | 2014-03-19 | 张更生 | Method for vertical takeoff and landing and rapid flight through change of aircraft engines |
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| CN105173076B (en) * | 2015-09-29 | 2018-09-14 | 广西圣尧航空科技有限公司 | A kind of vertical take-off and landing drone |
| CN106114854B (en) * | 2016-08-09 | 2019-06-25 | 烟台中飞海装科技有限公司 | A kind of push-button aircraft |
| CN106114853B (en) * | 2016-08-09 | 2019-05-10 | 烟台中飞海装科技有限公司 | A kind of push-button aircraft |
| CN107021219B (en) * | 2017-04-07 | 2020-06-09 | 南昌航空大学 | Fixed-wing unmanned aerial vehicle and control method thereof |
| US10053213B1 (en) * | 2017-05-08 | 2018-08-21 | Pinnacle Vista, LLC | Multi-copter lift body aircraft with tail pusher |
| CN109305356A (en) * | 2017-08-29 | 2019-02-05 | 陕西安康领航智能股份有限公司 | A kind of tilting type vertical take-off and landing drone |
| US20210354811A1 (en) * | 2018-09-22 | 2021-11-18 | Aeronext Inc. | Aircraft |
| CN110203387A (en) * | 2019-05-09 | 2019-09-06 | 深圳市禾启智能科技有限公司 | VTOL Fixed Wing AirVehicle |
| CN112849403B (en) * | 2019-11-26 | 2023-09-29 | 上海峰飞航空科技有限公司 | Unmanned aerial vehicle and control method thereof |
| JP6736198B1 (en) * | 2020-06-18 | 2020-08-05 | 株式会社エアロネクスト | Flying body |
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