WO2016201661A1 - 一种用于飞机的升力装置以及使用该装置的起飞方法 - Google Patents
一种用于飞机的升力装置以及使用该装置的起飞方法 Download PDFInfo
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- WO2016201661A1 WO2016201661A1 PCT/CN2015/081742 CN2015081742W WO2016201661A1 WO 2016201661 A1 WO2016201661 A1 WO 2016201661A1 CN 2015081742 W CN2015081742 W CN 2015081742W WO 2016201661 A1 WO2016201661 A1 WO 2016201661A1
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- aircraft
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- 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
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
Definitions
- the present invention relates to the field of aircraft, and more particularly to a lifting device for an aircraft and a take-off method using the same.
- the vertical take-off is vertical lifting.
- the flight of the aircraft is divided into three main stages, namely take-off, leveling and landing.
- the way the plane takes off and land is the way of running, so the airport runway is needed, and the vertical takeoff and landing mainly refers to the aircraft. It can take vertical takeoff and vertical landing without using the runway. It can eliminate the airport runway, which can reduce the cost of airport construction and adapt to the takeoff of small space.
- the object of the present invention is to overcome the above-mentioned deficiencies in the prior art and to provide a lifting device for an aircraft which has a fast flying speed, a simple structure and a light weight.
- the present invention provides the following technical solutions:
- a lift apparatus for an aircraft mounted on an aircraft including a power source capable of generating an air flow that sweeps over an upper surface of the aircraft wing, the air flow imparting a primary effort effect to the airfoil.
- the airflow generates lift to the wing to cause the aircraft to fly, forming an airflow on the upper surface of the wing, causing a pressure difference between the upper surface and the lower surface of the wing, and the wing can be lifted upward to achieve take-off, and the setting can offset the pair.
- the airflow of the aircraft's horizontal thrust can cause the aircraft to receive only upward lift, achieve vertical lift, or lift the aircraft in a slower state relative to the ground level. After flying, the principle of continuing flight is the same as that of the fighter.
- the thrust generated by the device causes the aircraft to fly, and the lift or steering can be realized by changing the lift of the wing.
- the structure is more Simple, no need to rotate a complex rotating mechanism such as an engine, the structure is simpler and the weight is lighter.
- At least part of the airflow provided by the power source is opposite, so that the partial airflow direction is opposite, and when the aircraft is to fly forward, after the aircraft is lifted by the lift device, the part is changed.
- the direction of the forward airflow generated by the lift device causes the original airflow to be backward, so that the originally offset thrust is not offset, and the speed of the airflow does not change, so the lift of the aircraft does not change and the flight can still be maintained.
- the aircraft Under the horizontal thrust of the aircraft after the change, the aircraft flies forward, and when flying backwards, the direction of the backward airflow generated by the partial lift device is changed, so that the original airflow can be forward.
- the lifting device is capable of adjusting the flow rate and/or direction of the airflow so that the thrust generated by each airflow is balanced, and the aircraft is only vertically lifted by the upward lift by the wing.
- the lifting device is divided into two or more sections, which are respectively disposed on both sides of the aircraft, to make the balance of the aircraft easier.
- the lifting device on the same side of the aircraft is capable of simultaneously generating forward and backward airflow over the upper surface of the wing, and the forward and backward airflows against the aircraft are mutually thrust Offset, in the case where the total horizontal thrust received by the aircraft is zero, the thrusts on both sides of the aircraft fuselage are also mutually canceled, so that the aircraft does not rotate during the lifting process.
- the lifting device is a propeller, the most straightforward and simplest structure for generating an air flow, which is low in manufacturing cost and stable.
- the inclination angle of the propeller shaft is adjustable, and when the size or direction of the airflow generated by the propeller needs to be changed, it is not necessary to reversely rotate the engine, and the inclination angle of the propeller shaft is adjusted to be converted to a mirror position compared with the previous mirror position. It can realize that the conversion process of the propellers in different working states is smoother and more convenient. At the same time, the installation of the engine does not need to be bidirectional, and the cost is saved. At the same time, the upper surface of the wing can maintain the rapid flow of the airflow to generate the lift, and generate the forward power.
- the number of propellers located on the same side of the fuselage is equal to or greater than two, respectively producing forward and backward airflows that are blown over the upper surface of the airfoil.
- the lifting devices are respectively installed on the airfoil surfaces of different positions in front and rear of the fuselage, or airfoil surfaces of different heights, at least one of which can change the direction of the airflow, for example, in the same body
- the propellers on the side are set to the same height, and are adapted to the aircraft of a single-layer wing, or the propellers on the same side of the fuselage are vertically aligned and overlapped to fit the aircraft of the double-layer wing.
- the aircraft is heavier, after take-off The required lift is even greater.
- Increasing the power of the lift and increasing the area of the wing can increase the lift, but the range of individual wing area increases is limited.
- two or more layers of wings can be used to achieve the wing.
- the area is increased in a larger range, and then the lift received by the aircraft is separated into upper and lower layers.
- vertical lift can also be completed.
- the propellers on the same side of the fuselage are all disposed on the upper surface of one of the wings, and a partition plate for isolating the airflow is disposed between the adjacent propellers to prevent interference of the airflow in the opposite direction.
- the structure only needs to be provided with one wing on each side of the fuselage to reduce material cost and process cost.
- the lifting device is an electric field generating device (changing the polarity of the electric field on the upper surface of the wing, without requiring complicated structure and excessive structural weight), which is disposed on the upper surface of the wing and capable of By making the air above the wing positively or negatively charged, the air can generate airflow in different directions along the electric field force.
- the space on the upper surface of the wing is saved, and the resistance of the airflow is smaller, and the power source is The utilization rate is higher, the electric field generating device and the propeller manner can be arranged at the same time, and the different airflows are respectively generated when used together, but the airflow direction can be adjusted, and the airflow direction is changed while ensuring that the wing receives sufficient lift.
- the principle is the same as using one of the lift devices alone.
- the present application also discloses a take-off method for an aircraft using the above-described lifting device, the steps of which are:
- step B the forward and backward thrusts generated by the aircraft on the same side of the aircraft are mutually canceled to achieve vertical lift.
- the take-off method further includes the step C, after the aircraft is raised, the partial lift devices on both sides of the aircraft are quickly mirrored to change the direction of the airflow generated, so that the aircraft flies forward or backward. Row.
- the take-off method further includes the step D, when the aircraft flies forward or backward, adjusting the power of the different lifting devices, so that the lift on the wings of both sides of the fuselage is changed, the aircraft is tilted, and the steering is realized. .
- the structure makes the flight speed of the aircraft faster, the structure is simple, and the weight is light.
- the flight method using the structure makes the take-off and the peaceful flight better and more adaptable.
- Embodiment 1 is a schematic view showing vertical take-off of an aircraft in Embodiment 1 of the present invention
- Embodiment 1 of the present invention is a schematic view showing an airplane flying in Embodiment 1 of the present invention
- FIG. 3 is a schematic view showing the vertical take-off of an aircraft in Embodiment 2 of the present invention.
- Embodiment 4 is a schematic view showing an airplane flying in Embodiment 2 of the present invention.
- Figure 5 is a schematic view showing the vertical take-off of an aircraft in Embodiment 4 of the present invention.
- Figure 6 is a schematic view showing the plane flying in the fourth embodiment of the present invention.
- Figure 7 is a schematic view showing the vertical take-off of an aircraft in Embodiment 3 of the present invention.
- Figure 8 is a schematic view showing the plane flying in the third embodiment of the present invention.
- Figure 9 is a schematic view showing the vertical take-off of an aircraft in Embodiment 5 of the present invention.
- Figure 10 is a schematic view showing the plane flying of the aircraft in Embodiment 5 of the present invention.
- a lifting device for an aircraft which is mounted on an aircraft, is connected with a power source, and is capable of generating a flow of air that is blown over the upper surface of the aircraft wing 2.
- the lifting device is a propeller 3 It is installed on the wing 2 on both sides of the fuselage 1 (the number of the wings 2 is two in the embodiment, symmetrically disposed on both sides of the fuselage 1), and the number of the propellers 3 on the same side of the fuselage 1 is equal to or greater than Two (two in this embodiment) generate forward and backward airflow on the upper surface of the wing 2, respectively, and the propeller 3 which generates the forward airflow is disposed in front of the other propeller 3, so that the two propellers 3 The forward airflow and the backward airflow respectively generated are not interfered with each other, and the inclination angle of the propeller 3 axis is adjustable, thereby changing the flow velocity of the generated airflow (fast mirroring changes the direction of the airflow to make part of the airflow direction Conversely
- the propellers 3 on both sides of the aircraft are quickly mirrored to change the direction of the airflow generated, so that the aircraft can fly forward or backward.
- B and C can be synchronized, so that the aircraft also has a horizontal displacement relative to the ground when lifting, and the adaptability is stronger.
- a lifting device for an aircraft which is mounted on an aircraft, is connected with a power source, and is capable of generating a flow of air that is blown over the upper surface of the aircraft wing 2.
- the lifting device is a propeller 3 It is installed on the wings 2 on both sides of the fuselage 1 (the number of the wings 2 in this embodiment is four, symmetrically disposed on both sides of the fuselage 1, and the wings 2 on the same side are disposed at the same height in parallel with each other),
- the number of propellers 3 located on the same side of the fuselage 1 is equal to or greater than two (two in this embodiment, and different from the first embodiment, the two are respectively disposed on different wings 2), respectively on the wing 2
- the upper surface generates forward and backward airflow.
- the aircraft since the propellers 3 of different functions are respectively disposed on different wings 2, the interference of the two airflows is smaller, the utilization rate is higher, and the stability is more stable.
- the inclination angle of the propeller 3 shaft is adjustable to change the flow rate of the generated air flow (the direction of the air flow is rapidly mirrored to make the partial air flow direction opposite), and the propeller 3 can adjust the flow rate of the air flow to make the air flow to the aircraft Forward and backward or directional thrust in one state
- the aircraft is only subjected to upward lift and vertical lift, as shown in Fig. 3, when the forward and backward airflow generated by the propeller 3 does not completely cancel each other.
- the aircraft will also have horizontal thrust, as shown in Figure 4, for level flight, or for non-vertical lifting,
- Adjusting the propeller 3 causes the aircraft to rise in a state of maintaining left and right balance, and the forward and backward thrusts generated by the propellers 3 on the same side of the aircraft are mutually canceled;
- the propellers 3 on both sides of the aircraft are quickly mirrored to change the direction of the airflow generated, so that the aircraft can fly forward or backward.
- B and C can be synchronized, so that the aircraft also has a horizontal displacement relative to the ground when lifting, and the adaptability is stronger.
- a lifting device for an aircraft is mounted on an aircraft, is connected with a power source, and is capable of generating a flow of air that is blown over the upper surface of the aircraft wing 2.
- the lifting device is a propeller 3 It is installed on the wings 2 on both sides of the fuselage 1 (the number of the wings 2 is four in this embodiment, symmetrically disposed on both sides of the fuselage 1, and the wings 2 on the same side are arranged in parallel with each other at different heights, In the embodiment, the upper and lower sides are aligned, and the number of the propellers 3 on the same side of the fuselage 1 is equal to or greater than two (two in this embodiment, mounted on different wings 2), which are respectively produced on the upper surface of the wing 2.
- the forward and backward airflows are arranged such that the two propellers 3 are staggered up and down, so that the forward airflow and the backward airflow respectively generated by the two propellers 3 do not interfere with each other, and the inclination angle of the propeller 3-axis is adjustable. Varying the flow rate of the generated airflow (fast mirroring the direction of the airflow so that the partial airflow direction is opposite), the propeller 3 is capable of adjusting the flow rate of the airflow to make the airflow forward and backward or outward of the aircraft
- the thrust cancels each other in one state, in the propeller 3 When the forward and backward airflows cancel each other out, the aircraft is only subjected to upward lift and vertical lift. As shown in Fig. 7, when the forward and backward airflow generated by the propeller 3 does not completely cancel each other, the aircraft is not uplifted. Lift, there will be horizontal thrust, as shown in Figure 8, for leveling, or for non-vertical lifting,
- Adjusting the propeller 3 causes the aircraft to rise in a state of maintaining left and right balance, and the forward and backward thrusts generated by the propellers 3 on the same side of the aircraft are mutually canceled;
- the propellers 3 on both sides of the aircraft are quickly mirrored to change the direction of the airflow generated, so that the aircraft can fly forward or backward.
- B and C can be synchronized, so that the aircraft also has a horizontal displacement relative to the ground when lifting, and the adaptability is stronger.
- a lifting device for an aircraft which is mounted on an aircraft, is connected with a power source, and is capable of generating a flow of air that is blown over the upper surface of the aircraft wing 2.
- the lifting device is a propeller 3 It is installed on the wing 2 on both sides of the fuselage 1 (the number of the wings 2 is two in the embodiment, symmetrically disposed on both sides of the fuselage 1), and the number of the propellers 3 on the same side of the fuselage 1 is equal to or greater than Two (two in this embodiment, mounted on the same wing 2, but two wings 2 are staggered, and two partitions 4 are provided with isolated airflow between the memories), respectively on the wing 2.
- the surface generates forward and backward airflow, and since the two propellers 3 are separated by the partition 4, the forward airflow and the backward airflow respectively generated by the two propellers 3 do not interfere with each other, and the inclination of the propeller 3 axes Adjustable to change the flow rate of the generated airflow (fast mirroring of the direction of the airflow to reverse the direction of the partial airflow), the propeller 3 being able to adjust the flow rate of the airflow to make the airflow forward and toward the aircraft
- the rear or outward thrusts cancel each other out in one state and are produced in the propeller 3 When the forward and backward flow cancel each other, only the upward lift aircraft, vertical lift, FIG. 5, the forward and backward flow is not completely cancel each other in 3 produced by the propeller, the aircraft In addition to the upward lift, there will be horizontal thrust, as shown in Figure 6, for leveling, or for non-vertical lifting,
- Adjusting the propeller 3 causes the aircraft to rise in a state of maintaining left and right balance, and the forward and backward thrusts generated by the propellers 3 on the same side of the aircraft are mutually canceled;
- the propellers 3 on both sides of the aircraft are quickly mirrored to change the direction of the airflow generated, so that the aircraft can fly forward or backward.
- B and C can be synchronized, so that the aircraft also has a horizontal displacement relative to the ground when lifting, and the adaptability is stronger.
- a lifting device for an aircraft which is mounted on an aircraft, is connected with a power source, and is capable of generating a flow of air that is blown over the upper surface of the aircraft wing 2.
- the lifting device is an electric field.
- the device 5 is disposed on the upper surface of the wing 2 (the number of the wings 2 is two in the embodiment, symmetrically disposed on both sides of the fuselage 1), and can positively or negatively charge the air above the wing 2, thereby
- the air is caused to generate airflow in different directions along the electric field force, and the single electric field generating device 5 can simultaneously generate a forward or backward airflow on the upper surface of the wing 2, or divide the electric field generating device 5 of the same side fuselage 1 into multiple
- the power of the electric field generating device 5 is adjustable, and the flow rate of the generated airflow is different.
- the electric field generating device 5 on the single wing 2 is one, which is disposed at The upper surface of the wing 2 is divided into a front part and a rear part, which can positively or negatively charge the air above the wing 2 through different states, so that the air generates airflow in different directions along the electric field force, as shown in FIG.
- Electric field generating device The front part of 5 produces forward airflow, giving the plane a forward forward thrust and upward lift, while the rear part produces a flat backward thrust and upward lift, the front and rear thrusts cancel out, leaving only the upward lift,
- the aircraft is vertically lifted, as shown in Figure 10. When the current rear thrust is in the same direction, the aircraft achieves a level flight.
- B and C can be synchronized, so that the aircraft also has a horizontal displacement relative to the ground when lifting, and the adaptability is stronger.
Abstract
一种用于飞机的升力装置及使用该升力装置的起飞方法。该升力装置连接有动力源，其能够产生吹扫过飞机机翼(2)上表面的气流，通过该气流对机翼(2)产生升力使飞机飞起，可以使飞机垂直升降，或者以飞机相对于地面水平移动较慢的状态升降。该升力装置在起飞行状态下还能有较快飞行速度、结构简单、重量轻。
Description
本发明涉及飞机领域，特别涉及一种用于飞机的升力装置以及使用该装置的起飞方法。
垂直起飞即垂直升降，飞机的飞行分为三个主要阶段，即起飞、平飞和降落，其中飞机实现起飞和降落的方式就是滑跑方式，所以需要机场跑道，而垂直起降主要指飞机可以不用借助跑道而在原地就能垂直起飞和垂直降落，可以不用机场跑道，其能够减少机场建设的成本，也能够适应小空间的飞机起飞。
目前飞机垂直起飞的办法，主要有两种，一种是类似于直升机的结构，另一种是通过旋转发动机的推力方向来实现从垂直起飞转向平飞，类似于美国的鱼鹰旋转翼飞机或者是英国的鹞式战斗机，前一种方式飞机的飞行速度较慢，后一种方式飞机有复杂的旋转机构，结构重量较大。
发明内容
本发明的目的在于克服现有技术中所存在的上述不足，提供一种飞行速度较快、结构简单、重量轻的用于飞机的升力装置。
为了实现上述发明目的，本发明提供了以下技术方案：
一种用于飞机的升力装置，其安装于飞机上，所述升力装置包括动力源，该动力源能够产生吹扫过飞机机翼上表面的气流，该气流能让翼面产生伯努力效应。
通过该气流对机翼产生升力使飞机飞起，在机翼上表面形成气流，使机翼上表面和下表面形成压强差，机翼可以受到向上的升力，实现起飞，而设置能够抵消掉对飞机的水平的推力的若干气流，可以使飞机只受到向上的升力，实现垂直升降，或者以飞机相对于地面水平移动较慢的状态升降，飞起来以后，继续飞行的原理和战斗机相同，通过某装置产生的推力使飞机飞行，通过改变机翼受到的升力实现升降或转向，相比较于直升机的飞行速度，更快，同时相比较同类的垂直升降的鱼鹰旋转翼飞机或者鹞式战斗机，结构更简单，不需要旋转发动机等复杂的旋转机构，结构较简单，重量较轻。
作为本发明的优选方案，所述动力源提供的气流中，至少有部分气流方向是相反的，使部分气流方向相反，要向前飞时，在飞机通过所述升力装置升起来以后，改变部分升力装置产生的向前的气流的方向，使原本的气流向后，这样原本相抵消的推力则没有抵消，而气流的速度没变，所以飞机受到的升力没变，依然能够保持飞行，这时在改变后飞机受到的水平方向的推力下，飞机向前飞，向后飞时，改变部分升力装置产生的向后的气流的方向，使原本的气流向前即可。
作为本发明的优选方案，所述升力装置能够调整所述气流的流速和/或方向，使各个气流产生的推力达到平衡，飞机通过机翼只受到向上的升力，进行垂直升降。
作为本发明的优选方案，所述升力装置分为两个或多个部分，分别设置在飞机的两侧，使飞机保持平衡更简单。
作为本发明的优选方案，位于飞机同侧的所述升力装置能够同时产生吹扫过机翼上表面的向前和向后的气流，并且向前和向后的气流对飞机的推力相互
抵消，在飞机受到的总的水平的推力为零的情况下，使飞机机身两侧的的推力也保持相互抵消状态，使飞机不会在升降过程中旋转。
作为本发明的优选方案，所述升力装置为螺旋桨，最直接地最简单的产生气流的结构，制造成本低，且稳定。
作为本发明的优选方案，所述螺旋桨轴的倾角可调，需要改变螺旋桨产生的气流大小或者方向时，不需要反向转动发动机，调整螺旋桨轴的倾角，转换到相比于以前的镜像位置即可实现，使螺旋桨不同工作状态的转换过程更流畅、方便，同时对发动机的安装也不需双向的，节约成本，同时可以使机翼上表面保持气流快速流动产生升力的同时，产生前进的动力(螺旋桨飞机产生反向推力的方式，是将螺旋桨的仰角改变，即改变螺旋桨与其旋转平面的倾角，令前进方向转为前方，这种使用螺旋桨产生反向推力的方法，早在1930年代就开始使用，可变仰角螺旋桨的发展，除了可用于推力反向之外，也可以在不同的情况下，充分使用发动机的动力)。
作为本发明的优选方案，位于所机身同侧的螺旋桨数量等于或大于两个，分别产生吹扫过机翼上表面的向前和向后的气流。
作为本发明的优选方案，所述的升力装置分别装在所述机身前后不同位置的翼面上，或不同高度的翼面上，其中至少有一组能变换气流方向，比如位于所机身同侧的螺旋桨设置的高度均相同，适应单层机翼的飞机，或者，位于所机身同侧的螺旋桨上下对齐重叠安装，适应双层机翼的飞机，在飞机的重量更大时，起飞后需要的升力就更大，增大升力装置的功率、增大机翼面积可以提高升力，但是单个的机翼面积增大范围有限，这时采用两层或多层的机翼，可以实现机翼面积更大范围的增大，然后把飞机受到的升力分开到上下层分别的
机翼上，只要保证机身同侧的所有机翼所受到的合力仅为升力，也可完成垂直升降。
作为本发明的优选方案，位于所机身同侧的螺旋桨均设置在一个机翼的上表面，且相邻的螺旋桨之间设置有隔离气流的隔板，防止相反方向的气流产生干扰，这种结构在机身两侧只需要分别设置一个机翼即可，降低材料成本和工艺成本。
作为本发明的优选方案，所述升力装置为电场发生装置(改变机翼上表面电场的带点极性，不需要复杂结构和过多结构重量的付出)，其设置在机翼上表面，能够通过使机翼上方的空气带正电或负电，从而使空气沿电场力产生不同方向的气流，相比较螺旋桨的方式，更节约机翼上表面的空间，使气流受到的阻力更小，动力源的利用率更高，电场发生装置和所述螺旋桨的方式可同时布置，配合使用，分别产生不同的气流，但均可调节气流方向，在保证机翼受到足够升力的情况下，改变气流方向，使飞机向前或向后飞，原理和单独使用其中一种升力装置相同。
本申请还公开了使用上述升力装置的飞机的起飞方法，其步骤为：
A、同时启动飞机机身两侧的升力装置；
B、调整升力装置使飞机在保持左右平衡的状态下升起。
作为本发明的优选方案，步骤B中，飞机同侧的升力装置对飞机产生的向前和向后推力保持相互抵消的状态，实现垂直升降。
作为本发明的优选方案，所述起飞方法还包括步骤C，飞机升起后，使飞机两侧的部分升力装置快速镜像变换所产生的气流的方向，使飞机向前或向后飞
行。
作为本发明的优选方案，所述起飞方法还包括步骤D，飞机向前或向后飞时，调整不同升力装置的功率，使机身两侧机翼所受升力改变，飞机产生倾斜，实现转向。
与现有技术相比，本发明的有益效果：
结构上使飞机的飞行速度较快、结构简单、重量轻，运用此结构的飞行方法使起飞和平飞的状态更优，适应性更强。
图1为本发明实施例1中飞机垂直起飞示意图；
图2为本发明实施例1中飞机平飞示意图；
图3为本发明实施例2中飞机垂直起飞示意图；
图4为本发明实施例2中飞机平飞示意图；
图5为本发明实施例4中飞机垂直起飞示意图；
图6为本发明实施例4中飞机平飞示意图；
图7为本发明实施例3中飞机垂直起飞示意图；
图8为本发明实施例3中飞机平飞示意图；
图9为本发明实施例5中飞机垂直起飞示意图；
图10为本发明实施例5中飞机平飞示意图；
图中标记：1-机身，2-机翼，3-螺旋桨，4-隔板，5-电场发生装置。
下面结合实施例及具体实施方式对本发明作进一步的详细描述。但不应将此理解为本发明上述主题的范围仅限于以下的实施例，凡基于本发明内容所实现的技术均属于本发明的范围。
实施例1
如图1、2，一种用于飞机的升力装置，其安装于飞机上，连接有动力源，并且能够产生吹扫过飞机机翼2上表面的气流，本实施例中升力装置为螺旋桨3，其安装在机身1两侧的机翼2上(本实施例中机翼2数量为两个，对称设置在机身1两侧)，位于机身1同侧的螺旋桨3数量等于或大于两个(本实施例中为两个)，分别在机翼2上表面产生向前和向后的气流，产生向前的气流的螺旋桨3设置位置在另一个螺旋桨3的前方，使两个螺旋桨3分别产生的向前的气流和向后的气流互不干扰，所述螺旋桨3轴的倾角可调，以此改变所产生的气流的流速(快速镜像变换所述气流的方向，使部分气流方向相反)，所述螺旋桨3能够调整所述气流的流速，使气流对飞机的向前和向后或各向的推力在一种状态下相互抵消，在螺旋桨3产生的向前和向后的气流相互抵消时，飞机只受到向上的升力，垂直升降，如图1，在螺旋桨3产生的向前和向后的气流相互不完全抵消时，飞机除了受到向上的升力，还会有水平方向的推力，如图2，进行平飞，或者进行非垂直的升降；
一种如本实施例中所述的飞机的飞行方法，其步骤为：
A、同时启动飞机机身1两侧的螺旋桨3；
B、调整螺旋桨3使飞机在保持左右平衡的状态下升起，飞机同侧的螺旋桨
3对飞机产生的向前和向后推力保持相互抵消的状态；
C、飞机升起后，使飞机两侧的部分螺旋桨3快速镜像变换所产生的气流的方向，使飞机向前或向后飞行。
本实施例中，B和C可同步进行，使飞机在升降时相对地面也有水平的位移，适应性更强。
实施例2
如图3、4，一种用于飞机的升力装置，其安装于飞机上，连接有动力源，并且能够产生吹扫过飞机机翼2上表面的气流，本实施例中升力装置为螺旋桨3，其安装在机身1两侧的机翼2上(本实施例中机翼2数量为四个，对称设置在机身1两侧，同侧的机翼2相互平行设置在同一高度)，位于机身1同侧的螺旋桨3数量等于或大于两个(本实施例中为两个，和实施例1不同，这两个是分别设置在不同的机翼2上)，分别在机翼2上表面产生向前和向后的气流，本实施例中由于不同功能的螺旋桨3分别设置在不同的机翼2上，这两个气流的干扰更小，利用率更高，更稳定，所述螺旋桨3轴的倾角可调，以此改变所产生的气流的流速(快速镜像变换所述气流的方向，使部分气流方向相反)，所述螺旋桨3能够调整所述气流的流速，使气流对飞机的向前和向后或各向的推力在一种状态下相互抵消，在螺旋桨3产生的向前和向后的气流相互抵消时，飞机只受到向上的升力，垂直升降，如图3，在螺旋桨3产生的向前和向后的气流相互不完全抵消时，飞机除了受到向上的升力，还会有水平方向的推力，如图4，进行平飞，或者进行非垂直的升降，
一种如本实施例中所述的飞机的飞行方法，其步骤为：
A、同时启动飞机机身1两侧的螺旋桨3；
B、调整螺旋桨3使飞机在保持左右平衡的状态下升起，飞机同侧的螺旋桨3对飞机产生的向前和向后推力保持相互抵消的状态；
C、飞机升起后，使飞机两侧的部分螺旋桨3快速镜像变换所产生的气流的方向，使飞机向前或向后飞行。
本实施例中，B和C可同步进行，使飞机在升降时相对地面也有水平的位移，适应性更强。
实施例3
如图7、8，一种用于飞机的升力装置，其安装于飞机上，连接有动力源，并且能够产生吹扫过飞机机翼2上表面的气流，本实施例中升力装置为螺旋桨3，其安装在机身1两侧的机翼2上(本实施例中机翼2数量为四个，对称设置在机身1两侧，同侧的机翼2相互平行设置在不同高度，本实施例中为上下对齐)，位于机身1同侧的螺旋桨3数量等于或大于两个(本实施例中为两个，安装在不同的机翼2上)，分别在机翼2上表面产生向前和向后的气流，由于两个螺旋桨3上下错开设置，使两个螺旋桨3分别产生的向前的气流和向后的气流互不干扰，所述螺旋桨3轴的倾角可调，以此改变所产生的气流的流速(快速镜像变换所述气流的方向，使部分气流方向相反)，所述螺旋桨3能够调整所述气流的流速，使气流对飞机的向前和向后或各向的推力在一种状态下相互抵消，在螺旋桨3产生的向前和向后的气流相互抵消时，飞机只受到向上的升力，垂直升降，如图7，在螺旋桨3产生的向前和向后的气流相互不完全抵消时，飞机除了受到向上的升力，还会有水平方向的推力，如图8，进行平飞，或者进行非垂直的升降，
一种如本实施例中所述的飞机的飞行方法，其步骤为：
A、同时启动飞机机身1两侧的螺旋桨3；
B、调整螺旋桨3使飞机在保持左右平衡的状态下升起，飞机同侧的螺旋桨3对飞机产生的向前和向后推力保持相互抵消的状态；
C、飞机升起后，使飞机两侧的部分螺旋桨3快速镜像变换所产生的气流的方向，使飞机向前或向后飞行。
本实施例中，B和C可同步进行，使飞机在升降时相对地面也有水平的位移，适应性更强。
实施例4
如图5、6，一种用于飞机的升力装置，其安装于飞机上，连接有动力源，并且能够产生吹扫过飞机机翼2上表面的气流，本实施例中升力装置为螺旋桨3，其安装在机身1两侧的机翼2上(本实施例中机翼2数量为两个，对称设置在机身1两侧)，位于机身1同侧的螺旋桨3数量等于或大于两个(本实施例中为两个，安装在同一个机翼2上，但两个机翼2错开设置，两个记忆之间设置有隔离气流的隔板4)，分别在机翼2上表面产生向前和向后的气流，由于两个螺旋桨3被隔板4隔开，使两个螺旋桨3分别产生的向前的气流和向后的气流互不干扰，所述螺旋桨3轴的倾角可调，以此改变所产生的气流的流速(快速镜像变换所述气流的方向，使部分气流方向相反)，所述螺旋桨3能够调整所述气流的流速，使气流对飞机的向前和向后或各向的推力在一种状态下相互抵消，在螺旋桨3产生的向前和向后的气流相互抵消时，飞机只受到向上的升力，垂直升降，如图5，在螺旋桨3产生的向前和向后的气流相互不完全抵消时，飞机
除了受到向上的升力，还会有水平方向的推力，如图6，进行平飞，或者进行非垂直的升降，
一种如本实施例中所述的飞机的飞行方法，其步骤为：
A、同时启动飞机机身1两侧的螺旋桨3；
B、调整螺旋桨3使飞机在保持左右平衡的状态下升起，飞机同侧的螺旋桨3对飞机产生的向前和向后推力保持相互抵消的状态；
C、飞机升起后，使飞机两侧的部分螺旋桨3快速镜像变换所产生的气流的方向，使飞机向前或向后飞行。
本实施例中，B和C可同步进行，使飞机在升降时相对地面也有水平的位移，适应性更强。
实施例5
如图9、10，一种用于飞机的升力装置，其安装于飞机上，连接有动力源，并且能够产生吹扫过飞机机翼2上表面的气流，本实施例中升力装置为电场发生装置5，其设置在机翼2上表面(本实施例中机翼2数量为两个，对称设置在机身1两侧)，能够通过使机翼2上方的空气带正电或负电，从而使空气沿电场力产生不同方向的气流，所述单个的电场发生装置5可同时在机翼2上表面产生向前或向后的气流，或者同侧机身1的电场发生装置5分为多个，每个单独的产生一个方向的气流，电场发生装置5的功率可调，使其产生的气流的流速不同，本实施例中单个机翼2上的电场发生装置5为一个，其设置在机翼2上表面，分为前部分和后部分，其均可通过不同的状态使机翼2上方的空气带正电或者负电，从而使空气沿电场力产生不同方向的气流，如图9，电场发生装置
5的前部分产生向前的气流，给飞机平向向前的推力和向上的升力，后部分则产生平向的向后的推力和向上的升力，前后推力相抵消，只剩向上的升力，飞机垂直升降，如图10，当前后推力同向时，飞机实现平飞。
一种如本实施例中所述的飞机的飞行方法，其步骤为：
A、同时启动飞机机身1两侧的电场发生装置5；
B、调整电场发生装置5使飞机在保持左右平衡的状态下升起，飞机同侧的电场发生装置5对飞机产生的向前和向后推力保持相互抵消的状态；
C、飞机升起后，使飞机两侧的电场发生装置5的一部分快速镜像变换所产生的气流的方向，使飞机向前或向后飞行。
本实施例中，B和C可同步进行，使飞机在升降时相对地面也有水平的位移，适应性更强。
Claims (14)
- 一种用于飞机的升力装置，其安装于飞机上，其特征在于，所述升力装置包括动力源，该动力源用于产生吹扫过飞机机翼上表面的气流。
- 根据权利要求1所述的一种用于飞机的升力装置，其特征在于，所述动力源提供的气流中，至少有部分气流方向是相反的。
- 根据权利要求2所述的一种用于飞机的升力装置，其特征在于，所述升力装置能够调整所述气流的流速和/或方向，使各个气流产生的推力达到平衡。
- 根据权利要求3所述的一种用于飞机的升力装置，其特征在于，所述升力装置分为两个或多个部分，分别设置在飞机的两侧。
- 根据权利要求4所述的一种用于飞机的升力装置，其特征在于，位于飞机同侧的所述升力装置能够同时产生吹扫过机翼上表面的向前和向后的气流，并且向前和向后的气流对飞机的推力相互抵消。
- 根据权利要求5所述的一种用于飞机的升力装置，其特征在于，所述升力装置为螺旋桨。
- 根据权利要求6所述的一种用于飞机的升力装置，其特征在于，所述螺旋桨轴的倾角可调。
- 根据权利要求7所述的一种用于飞机的升力装置，其特征在于，位于所述飞机机身同侧的螺旋桨数量等于或大于两个，分别产生吹扫过机翼上表面的向前和向后的气流。
- 根据权利要求4所述的一种用于飞机的升力装置，其特征在于，所述的升力装置分别装在所述机身前后不同位置的翼面上，或不同高度的翼面上，其中至少有一组能变换气流方向。
- 根据权利要求8所述的一种用于飞机的升力装置，其特征在于，位于所机身同侧的螺旋桨均设置在一个机翼的上表面，且相邻的螺旋桨之间设置有隔离气流的隔板。
- 根据权利要求5所述的一种用于飞机的升力装置，其特征在于，所述升力装置为电场发生装置，其设置在机翼上表面，能够通过使机翼上方的空气带正电或负电。
- 一种根据权利要求2-11任意一项所述的使用该升力装置的起飞方法，其步骤为：A、同时启动飞机机身两侧的升力装置；B、调整升力装置使飞机在保持左右平衡的状态下升起。
- 一种根据权利要求12任意一项所述的使用该升力装置的起飞方法，其特征在于，步骤B中，飞机同侧的升力装置对飞机产生的向前和向后推力保持相互抵消的状态。
- 一种根据权利要求13任意一项所述的使用该升力装置的起飞方法，其特征在于，还包括步骤C，飞机升起后，使飞机两侧的部分升力装置快速镜像变换所产生的气流的方向，使飞机向前或向后飞行。
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| CN102717887B (zh) * | 2012-05-23 | 2015-11-25 | 北京航空航天大学 | 一种采用充气式机翼和可倾转螺旋桨的临近空间飞艇 |
| DE202012013513U1 (de) * | 2012-07-27 | 2017-05-12 | Jonathan Hesselbarth | Senkrecht startendes Flugzeug |
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2015
- 2015-06-18 CN CN201580008893.7A patent/CN106163925B/zh active Active
- 2015-06-18 WO PCT/CN2015/081742 patent/WO2016201661A1/zh active Application Filing
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| US20080116808A1 (en) * | 2006-11-22 | 2008-05-22 | Mcclure Paul D | Over-Wing Traveling-Wave Axial Flow Plasma Accelerator |
| CN101274666A (zh) * | 2007-11-05 | 2008-10-01 | 穆骞 | 开裂复合式机翼 |
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| CN202728575U (zh) * | 2011-10-17 | 2013-02-13 | 田瑜 | 固定翼与电动多旋翼组成的复合飞行器 |
| CN102826215A (zh) * | 2012-09-11 | 2012-12-19 | 北京航空航天大学 | 一种可短距起降的轻小型飞翼载人机 |
| CN103738496A (zh) * | 2013-12-24 | 2014-04-23 | 西安交通大学 | 适用于垂直起降飞行器的动力系统结构及其控制方法 |
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| CN106163925A (zh) | 2016-11-23 |
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