CN110979661B - Multi-element ducted fan for vertical take-off and landing aircraft - Google Patents
Multi-element ducted fan for vertical take-off and landing aircraft Download PDFInfo
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- CN110979661B CN110979661B CN201911203878.4A CN201911203878A CN110979661B CN 110979661 B CN110979661 B CN 110979661B CN 201911203878 A CN201911203878 A CN 201911203878A CN 110979661 B CN110979661 B CN 110979661B
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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
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
- B64C29/04—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded characterised by jet-reaction propulsion
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C15/00—Attitude, flight direction, or altitude control by jet reaction
- B64C15/02—Attitude, flight direction, or altitude control by jet reaction the jets being propulsion jets
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Abstract
The invention discloses a multi-element ducted fan for a vertical take-off and landing aircraft, which comprises a cylindrical ducted shell, a vector grid plate, 2 or more than 2 fan units at each stage, and a flow guide grid, wherein the vector grid plate is arranged at the bottom of the cylindrical ducted shell and used for changing the airflow direction of the fan, the fan units at each stage are clamped on the inner wall of the cylindrical ducted shell and are vertically spaced at a certain distance, and the flow guide grid is arranged between the fan units at each stage and between a final-stage fan unit and the vector grid plate and used for adjusting airflow and keeping the airflow direction vertically downward; the fan units at all levels are non-coaxial fan units. The invention adopts more than two multi-fans, and the multi-ducted fans are connected with the central computer of the flight control system by adopting non-coaxial fan units and independent motor driving devices, so that the direction of air flow in the non-coaxial fan units is optimized, and the air flow is sprayed downwards to generate lifting force. Compared with the conventional ducted fan, the ducted fan of the multi-fan technology has higher efficiency and lower energy consumption, and can provide power for long-time work of the vertical take-off and landing aircraft.
Description
Technical Field
The invention belongs to the technical field of aircrafts, and particularly relates to a multi-element ducted fan for a vertical take-off and landing aircraft.
Background
The vertical take-off and landing aircraft refers to winged aircraft and wingless aircraft. The winged aircraft is a fixed-wing aircraft adopting a vertical take-off and landing mode, and is generally called a vertical take-off and landing unmanned aerial vehicle; wingless aircraft are actually flying transporters, which may be manned or unmanned, collectively referred to as flying vehicles.
The two types of vertical take-off and landing aircrafts are different from helicopters: the helicopter adopts one or more rotary wings to provide the lifting force of the aircraft and adopts inclined wings to provide the functions of forward flight, backward flight and side flight, and the lifting force and the flight power required by the vertical take-off and landing of the wingless aircraft and the midway flight are provided by ducted fans; the winged aircraft of the vertical take-off and landing aircraft utilizes the operation of the ducted fan in the short time of take-off and landing.
The existing vertical take-off and landing aircraft usually adopts a single-fan duct technology. The single-fan duct technology has been widely applied to many manned and unmanned aircrafts such as helicopter tail rotors, exhaust systems, single aircrafts and the like, and the efforts for years are mature. However, the efficiency of the single fan is affected by low air exhaust speed, small flow and low pressure difference, so that the jet air flow is diffused, and the energy consumption is overhigh. Meanwhile, the problem of other corollary equipment is brought, and the single fan is large in size, so that the adopted range is limited.
Disclosure of Invention
The invention provides a multi-element ducted fan for a vertical take-off and landing aircraft, aiming at solving the problems of low air flow exhaust speed, small flow, low pressure difference, jet air flow diffusion and overhigh energy consumption in the single-fan ducted technology in the prior art.
The invention adopts the following technical scheme for solving the technical problem.
A many first ducted fans for VTOL aircraft characterized in that: the multi-stage fan unit comprises a cylindrical duct shell, a vector grid plate, 2 or more than 2 fan units and a flow guide grid, wherein the vector grid plate is arranged at the bottom of the cylindrical duct shell and used for changing the airflow direction of a fan, the fan units are clamped on the inner wall of the cylindrical duct shell and are at certain intervals up and down, and the flow guide grid is arranged between the fan units and between a final-stage fan unit and the vector grid plate and used for adjusting airflow and keeping the airflow direction vertically downward; the fan units at all levels are non-coaxial fan units.
The non-coaxial fan units are respectively provided with an independent motor driving device, and each level of fan is non-coaxial and is respectively provided with a rotating shaft and is independently arranged on the ducted shell; the rotation speed and pitch of each stage of fan, especially the first stage of inlet and the last stage of outlet, are different, because the high-speed airflow needs different designs due to different shapes of inlet and outlet.
Each stage of fan unit comprises a fan, an independent motor driving device arranged at the center of the lower end of the plane of the fan, and a plurality of uniformly distributed fan fixing supports which are fixedly connected around the independent motor driving device and have one end connected with the independent motor driving device in the horizontal direction and the other end connected with the inner wall of the ducted shell; and one end of each stage of independent motor driving device is connected with the fan, the other end of each stage of independent motor driving device is connected with a central computer of the flight control system through a fixed support, and the independent motor driving devices are used for receiving a balance instruction of the central computer of the flight control system to control the rotating speed of each stage of fan so as to keep the aircraft flying in balance.
The independent motor driving device comprises a permanent magnet motor, a motor controller matched with the permanent magnet motor, a power regulator, a rotating speed sensor, a current sensor and a voltage sensor; the central computer controls the movement of the fans at all levels to synthesize a power system, and the central computer provides dynamic data for the fans at all levels to control task flight; the information of the rotating speed, the current and the voltage sensors is transmitted to a central computer for comprehensive processing, the central computer simultaneously receives the information fed back from the aircraft sensor and the atmospheric sensor, and after the two types of information are comprehensively processed, all fans are commanded to work by a motor controller and a power regulator of a motor driving device.
When the rotation directions of the upper fan and the lower fan are the same, the deflection directions of the flow guide grid plates are opposite, so that the air flow direction is kept vertically downward; when the rotation directions of the upper fan and the lower fan are opposite, the deflection angle of the flow guide grid plate is opposite to the rotation direction of the upper fan, so that the air flow direction is kept vertically downward.
Advantageous effects of the invention
The invention adopts more than two multi-fans, optimizes the air flow direction in a plurality of non-coaxial fan units by adopting non-coaxial fan units and independent motor driving devices and connecting a plurality of ducted fans with a central computer of a flight control system, and generates lifting force by downwards spraying air flow. Meanwhile, the vector grid plate is adopted to deflect the direction of the airflow so as to provide power for forward flight, backward flight and side flight. Compared with the conventional ducted fan, the ducted fan of the multi-fan technology has higher efficiency and lower energy consumption, and can provide power for the vertical take-off and landing aircraft to work for a long time.
Drawings
FIG. 1 is a schematic view of a multi-ducted fan according to the present invention, illustrating a structure of FIG. 1;
FIG. 2 is a structural diagram of a multi-ducted fan of the present invention 2;
FIG. 3 is a schematic view of a multi-ducted fan of the present invention 1;
FIG. 4 is a schematic view of a multi-ducted fan of the present invention shown in FIG. 2;
FIG. 5 is a schematic diagram of the operation of the air fence of the present invention;
FIG. 6 is a structural view of a fan unit of the present invention;
FIG. 7 is a schematic view of a relationship between a flight control system and a multi-ducted fan;
FIG. 8 is a schematic view of a multi-ducted fan for air surfing takeoff;
FIG. 9 is a schematic view of a multi-ducted fan for fixed point braking vertical landing;
FIG. 10 is a schematic view of a multi-ducted fan for use with an wingless aircraft.
In the figure: 1-1: a ducted enclosure; 1-2: a vector grid plate; 1-3: a fan unit; 1-4: a flow guiding grid;
1-3-1: a fan; 1-3-2: a motor drive device; 1-3-3: fixing support
Detailed Description
Design principle of the invention
1. The advantages of the multi-element ducted fan are as follows: the multi-element ducted fan technology adopts more than two multi-fans, achieves optimization by coordinating the direction of internal airflow through a plurality of devices, and generates lifting force by downwards spraying airflow. Meanwhile, the vector grid plate is adopted to deflect the direction of the airflow so as to provide power for forward flight, backward flight and side flight. The present document generally describes multi-ducted fan technology. By utilizing the high-rotating-speed, small-diameter and large-torsion fan blades, the ducted fan of the multi-fan technology has higher efficiency and lower energy consumption than the conventional ducted fan, and can provide power for long-time work of the vertical take-off and landing aircraft. The aerocar adopting the multi-ducted fan technology is suitable for operating in traffic jam, areas where the aerocar is difficult to run, river and lake areas, straits which are difficult to exceed and in climatic conditions which are not suitable for the flight of fixed wing aircrafts because the aerocar does not have wings.
2. Working principle of multi-element ducted fan
A. Supercharging and speed increasing principles: as shown in fig. 3 and 4, the first stage fan accelerates the m mass of air to mv1 kinetic energy while generating a pressure P1 higher than the external inlet pressure, which is caused by the mass m kinetic energy. M air at a pressure of P1, which continues to be pressurized by the second stage fan to P2, attains a higher velocity m2, resulting in a pressure P2 due to the greater kinetic energy v2m of the m mass of air. And continuing the fan acceleration and pressurization for n times to ensure that the mass m obtains kinetic energy and pressure far greater than those obtained by the first-stage fan. The kinetic energy of air driven by the high-speed motor of the n-grade fan is not simply increased to n times, a designed duct has the lifting capacity of the fan which is more than n times, the corresponding efficiency is improved, and the energy consumption is reduced. The guide plate inclined at a certain angle is adopted for guiding, and the deflection of the air flow accelerated by the fan can realize downward vertical spraying.
B. Guide plate principle: the function of the baffle is to direct the airflow in a vertically downward direction, as shown in fig. 5. When the rotation directions of the upper fan and the lower fan are the same, the airflow direction is not vertical downward, and if the deflection direction of the guide grid plate is opposite to the rotation direction of the upper fan, the deflected airflow can be neutralized, so that the airflow direction is adjusted to be vertical downward. When the rotation directions of the upper fan and the lower fan are opposite, the deflection direction of the flow guide grid plate is opposite to that of the upper fan, the deflection of the lower fan is adjusted by the corresponding flow guide plate, and each level of flow guide plate is only responsible for adjusting the airflow direction of the upper fan; when the screw pitches of the fans at all stages are different, the deflection angles of the fixed guide plates are different. The secondary fan may have two different directions of rotation: the same direction and the opposite direction can be adopted, but the design method is different, and the effect is different. After the first stage of acceleration, the air current enters the second stage of acceleration, and because the air current is higher than the first stage of outlet speed, the rotation speed and the blade deflection angle required by the second stage are different, and the air current can be accelerated again.
C. Principle of driving the fan: each stage of fan has its own driving motor, and each stage of fan is not coaxial, and each fan has its own pivot to independently install on duct shell structure. The rotation speed and the pitch of each stage of the fan are different, and of course, each stage of the fan can be the same. Especially the inlet first stage and the outlet last stage. Because the flow of the high-speed airflow needs different designs due to different shapes of the inlet and the outlet.
3. Flight control navigation and multi-duct fan relationship
As shown in fig. 7, block diagram, third row, left, and 1 st figure, aircraft balancing instructions from the central computer are issued to each fan to maintain aircraft balance. The central computer can control each fan respectively because each level of fan unit is not coaxial structure and is provided with independent motor driving device, and each motor driving device is communicated with the central computer independently.
Based on the invention principle, the invention designs the multi-element ducted fan for the vertical take-off and landing aircraft. A multi-element ducted fan for a vertical take-off and landing aircraft is shown in figures 1 and 2 and comprises a cylindrical ducted shell 1-1, a vector grid plate 1-2 arranged at the bottom of the cylindrical ducted shell 1-1 and used for changing the airflow direction of the fan, 2 or more than 2 fan units 1-3 at each level and clamped on the inner wall of the cylindrical ducted shell 1-1 and vertically spaced at a certain distance, and flow guide grids 1-4 arranged between the fan units 1-3 at each level and between the last fan unit 1-3 and the vector grid plate 1-2 and used for adjusting the airflow and keeping the airflow direction vertically downward; the fan units at all levels are non-coaxial fan units.
As shown in fig. 6, each of the non-coaxial fan units 1-3 has its own independent motor driving device 1-3-2, and each of the non-coaxial fans has its own rotating shaft and is independently installed on the ducted casing 1-1; the rotation speed and pitch of each stage of fan, especially the first stage of inlet and the last stage of outlet, are different, because the high-speed airflow needs different designs due to different shapes of inlet and outlet.
As shown in fig. 6, each stage of fan unit 1-3 comprises a fan 1-3-1, an independent motor driving device 1-3-2 arranged at the center of the lower end of the plane of the fan, and a plurality of uniformly distributed fan fixing supports 1-3-3 fixedly connected around the independent motor driving device 1-3-2 and having one end connected with the independent motor driving device in the horizontal direction and the other end connected with the inner wall of the ducted housing; one end of each stage of independent motor driving device 1-3-2 is connected with the fan 1-3-1, and the other end is connected with a central computer of the flight control system through the fixed support 1-3-3, and the independent motor driving devices are used for receiving a balance instruction of the central computer of the flight control system to control the rotating speed of each stage of fan so as to keep the aircraft flying in balance.
The independent motor driving device 1-3-2 comprises a permanent magnet motor, a motor controller matched with the permanent magnet motor, a power regulator, a rotating speed sensor, a current sensor and a voltage sensor; the central computer controls the movement of the fans at all levels to synthesize a power system, and the central computer provides dynamic data for the fans at all levels to control task flight; the information of the rotating speed, the current and the voltage sensors is transmitted to a central computer for comprehensive processing, the central computer simultaneously receives the information fed back from the aircraft sensor and the atmospheric sensor, and after the two types of information are comprehensively processed, all fans are commanded to work by a motor controller and a power regulator of a motor driving device.
As shown in fig. 1 and 6, when the rotation directions of the upper and lower fans are the same, the deflection directions of the flow guiding grids 1-2 are opposite, so that the air flow direction is kept vertically downward; when the rotation directions of the upper fan 1-3-1 and the lower fan 1-3-1 are opposite, the deflection angle of the flow guide grid plate 1-2 is opposite to the rotation direction of the upper fan 1-3-1, so that the air flow direction is kept vertically downward.
The first embodiment is as follows: multi-ducted fan for fixed wing VTOL unmanned aerial vehicle
As shown in fig. 8, for the fixed wing VTOL UAV, the ducted fan is only used in two stages of vertical take-off and landing. The service time is short and can not exceed 30-40 seconds, and the power consumption is little.
During taking off, the aircraft takes off in an 'air surfing' mode according to a diagram, the vertical rising height at the point 0 is only a few meters (according to the surrounding environment), and then the aircraft is accelerated to the lowest flying speed by a ducted fan, namely the aircraft flies by closing the power of the ducted fan and using a propulsion system as the power.
When landing, the aircraft normally slides down to the height of 50 meters above the ground, the ducted fan is started at the speed of about 100 kilometers per hour (different according to different models), the aircraft decelerates, and the aircraft lands at a fixed point by searching a designated landing point, the reverse thrust of the ducted fan and the height of a pneumatic brake meter-8 meters.
Example two: multi-element ducted fan for aerocar
As shown in fig. 9, the flying vehicle mainly depends on the ducted fan to provide power for flying, and obviously, the aerodynamic characteristics of the flying vehicles with different shapes are different in flying, and the aerodynamic force has different influences on the flying vehicle flying. For example: for the aerocar with the wings, the aerocar firstly needs to unfold the wings to enter normal flight in the takeoff process, and then becomes an air aerocar. However, for the flying vehicle without the wings to fly, the ducted fan is mainly relied on, and all balance and flight are different from the flying vehicle with the wings.
The ducted fan functions as follows:
and keeping the horizontal balance of the whole vehicle, and solidifying control software in a central computer without being influenced by any external factors.
-changing the direction of flight by operation of the vector grid of the ducted fan.
-varying the lift force using different powers of ducted fans to provide fly height control.
As shown in fig. 10, the flying vehicle adopting the multi-ducted fan technology has no wings, so that the flying vehicle is suitable for being operated in traffic jam, areas where the vehicle is difficult to run, river and lake areas, straits which are difficult to surmount and in climatic conditions which are not suitable for the flight of the fixed wing aircraft.
It should be emphasized that the described embodiments of the present invention are illustrative rather than limiting and, thus, the present invention includes embodiments that are not limited to those described in the detailed description.
Claims (3)
1. A many first ducted fans for VTOL aircraft characterized in that: the multi-stage fan unit comprises a cylindrical duct shell, a vector grid plate, 2 or more than 2 fan units and a flow guide grid, wherein the vector grid plate is arranged at the bottom of the cylindrical duct shell and used for changing the airflow direction of a fan, the fan units are clamped on the inner wall of the cylindrical duct shell and are at certain intervals up and down, and the flow guide grid is arranged between the fan units and between a final-stage fan unit and the vector grid plate and used for adjusting airflow and keeping the airflow direction vertically downward; each stage of fan unit is a non-coaxial fan unit;
two adjacent stages of fan units have two different directions of rotation: the same direction and the opposite direction; the deflection direction of the flow guide grid is opposite to the rotation direction of the previous stage fan unit, and each stage of flow guide grid is only responsible for adjusting the airflow direction of the previous stage fan unit.
2. The multi-ducted fan for a VTOL aircraft according to claim 1, wherein: the non-coaxial fan units are respectively provided with an independent motor driving device, and each level of fan unit is respectively provided with a rotating shaft and is independently arranged on the ducted shell; the first stage fan unit at the inlet and the last stage fan unit at the outlet have the same speed and pitch, but different speeds and pitches.
3. The multi-ducted fan for a VTOL aircraft according to claim 1, wherein: each stage of fan unit comprises a fan, an independent motor driving device arranged at the center of the lower end of the fan, and a plurality of uniformly distributed fan fixing supports which are fixedly connected around the independent motor driving device and have one end connected with the independent motor driving device in the horizontal direction and the other end connected with the inner wall of the ducted shell; and one end of each stage of independent motor driving device is connected with the fan, the other end of each stage of independent motor driving device is connected with a central computer of the flight control system through a fixed support, and the independent motor driving devices are used for receiving a balance instruction of the central computer of the flight control system to control the rotating speed of each stage of fan unit so as to keep the aircraft flying in balance.
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112360815B (en) * | 2020-11-10 | 2022-05-24 | 沈观清 | Adjustable stator mechanism for multistage ducted fan and control system of adjustable stator mechanism |
| CN112623132A (en) * | 2020-12-25 | 2021-04-09 | 山东科技大学 | Offshore platform capable of recycling unmanned aerial vehicle |
| CN113738533B (en) * | 2021-08-10 | 2022-11-18 | 中国电子科技集团公司第三十八研究所 | Independent driving turbofan system of series-connection supercharged electric turbine engine |
| CN113864084B (en) * | 2021-10-12 | 2022-08-16 | 中国电子科技集团公司第三十八研究所 | Stepped sectional turbofan system of series supercharged electric turbine engine |
| CN113847165B (en) * | 2021-10-12 | 2022-10-25 | 中国电子科技集团公司第三十八研究所 | Series connection supercharging type electric turbine engine double-output-shaft motor turbofan system |
Family Cites Families (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100417758B1 (en) * | 1999-11-16 | 2004-02-11 | 김창선 | propeller apparatus |
| GB2360752A (en) * | 2000-04-01 | 2001-10-03 | Glyn Jones | Helicopter without tail rotor |
| US6464166B1 (en) * | 2001-05-29 | 2002-10-15 | Romeo Yankee Ltd. | Ducted fan vehicles particularly useful as VTOL aircraft |
| US7658346B2 (en) * | 2005-02-25 | 2010-02-09 | Honeywell International Inc. | Double ducted hovering air-vehicle |
| WO2007099543A2 (en) * | 2006-03-01 | 2007-09-07 | Urban Aeronautics Ltd. | Ground effect vanes arrangement |
| WO2011019442A1 (en) * | 2009-08-10 | 2011-02-17 | Cornerstone Research Group, Inc. | Variable performance vaneaxial fan with high efficiency |
| US10427784B2 (en) * | 2011-12-05 | 2019-10-01 | Aurora Flight Sciences Corporation | System and method for improving transition lift-fan performance |
| US9045227B1 (en) * | 2011-12-19 | 2015-06-02 | William Dwight Gramling | Dual fan aerodynamic lift device |
| CN203428021U (en) * | 2013-06-28 | 2014-02-12 | 任思峰 | Ducted fan |
| US10107196B2 (en) * | 2014-08-08 | 2018-10-23 | Thomas International, Inc. | Adjustable size inlet system |
| CN105156225B (en) * | 2015-09-23 | 2017-03-22 | 海门韵田电气机械科技有限公司 | Three-level compressed-air ducted fan engine |
| CN105416573B (en) * | 2015-12-03 | 2017-05-17 | 北京航空航天大学 | Light efficient low-noise duct type two-stage electric fan propeller |
| CN105366060B (en) * | 2015-12-03 | 2017-03-29 | 北京航空航天大学 | A kind of efficient and light weight low noise culvert type level Four electric fan propeller |
| CN106114852A (en) * | 2016-06-29 | 2016-11-16 | 饶大林 | A kind of cross-arranging type dual-culvert vertical take-off and landing Spacecraft Attitude Control |
| CN106194498A (en) * | 2016-08-11 | 2016-12-07 | 南昌航空大学 | A kind of novel stacked combination type ducted fan |
| CN106240809B (en) * | 2016-08-23 | 2018-06-01 | 南京航空航天大学 | Flow controlling multi-rotor aerocraft and control method based on fanjet |
| CN206704537U (en) * | 2017-02-08 | 2017-12-05 | 北京正兴鸿业金属材料有限公司 | A kind of fixed-wing unmanned plane |
| TWI620688B (en) * | 2017-05-19 | 2018-04-11 | 林瑤章 | Lightweightaircraft |
| CN107244199B (en) * | 2017-06-23 | 2020-05-05 | 马德海 | Low-altitude aircraft |
| US20190061961A1 (en) * | 2017-08-22 | 2019-02-28 | General Electric Company | Aircraft propulsion system and method |
| CN108263620B (en) * | 2018-03-14 | 2024-06-21 | 中国空气动力研究与发展中心高速空气动力研究所 | Electric drive counter-rotating fan propeller for aircraft |
| CN109263885A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of shrouded propeller aircraft |
| CN109733598B (en) * | 2018-11-26 | 2024-04-09 | 丰翼科技(深圳)有限公司 | Air vehicle duct and duct type air vehicle |
| CN109606643A (en) * | 2018-12-13 | 2019-04-12 | 中国航发沈阳发动机研究所 | One kind is to turning lift fan |
-
2019
- 2019-11-29 CN CN201911203878.4A patent/CN110979661B/en active Active
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