CN108177771B - Variable mass distribution rotary-fixed wing composite aircraft - Google Patents
Variable mass distribution rotary-fixed wing composite aircraft Download PDFInfo
- Publication number
- CN108177771B CN108177771B CN201810015090.XA CN201810015090A CN108177771B CN 108177771 B CN108177771 B CN 108177771B CN 201810015090 A CN201810015090 A CN 201810015090A CN 108177771 B CN108177771 B CN 108177771B
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- Prior art keywords
- rotor
- fixed
- rotary
- composite aircraft
- motor
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Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
- B64C17/02—Aircraft stabilisation not otherwise provided for by gravity or inertia-actuated apparatus
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
Abstract
The invention provides a variable mass distribution rotary-fixed wing composite aircraft, which comprises a rotary-fixed wing composite aircraft main body structure, and a variable mass distribution device, a rotor wing system, a wheel motor and wheels which are distributed around the rotary-fixed wing composite aircraft main body structure; the variable mass distribution device is a magnetic field generating device or a motor driving device; the rotor device include rotor motor, rotor and duct, wherein, rotor motor includes rotor stator and rotor, rotor stator is fixed with the connecting plate, rotor is connected with rotor connecting device, rotor stator passes through the linking bridge and is connected with the duct, the duct is concentric with the rotor. The invention can be applied to the fields of attitude control of robots, attitude control of space solar power stations and the like, and can assist control of unmanned aerial vehicles through special variable mass distribution devices, thereby improving the controllability of the unmanned aerial vehicles.
Description
Technical Field
The invention relates to the field of aviation flight power machinery, in particular to a variable mass distribution rotary-fixed wing composite aircraft.
Background
At present, a four-rotor unmanned aerial vehicle is mainly driven by a motor, and the four-rotor unmanned aerial vehicle is subjected to attitude control by changing the rotating speeds of four motors; the fixed wing unmanned aerial vehicle drives the unmanned aerial vehicle to fly through the screw, and the attitude control is carried out on the fixed wing unmanned aerial vehicle by changing the control surface of the unmanned aerial vehicle. The four-rotor unmanned aerial vehicle and the fixed-wing unmanned aerial vehicle are widely applied to the fields of model plane performance, cargo distribution, high-altitude fire extinguishment, rescue and relief work and the like.
After the motor of the traditional four-rotor unmanned aerial vehicle fails, the unmanned aerial vehicle loses control, so that property loss is caused; the fixed wing aircraft has better endurance performance and speed performance, but does not have the capability of vertical take-off and landing. Therefore, a variable mass distribution rotary-fixed wing composite aircraft is required to be designed, the advantages of the four rotary wings and the fixed wings are combined, the control function of the traditional four rotary wing unmanned aerial vehicle is increased, and the unmanned aerial vehicle can better complete related tasks.
Disclosure of Invention
The invention aims to solve the problems in the prior art, provides a variable mass distribution rotary-fixed wing composite aircraft, can be applied to the fields of attitude control of robots, attitude control of space solar power stations and the like, and can assist in controlling unmanned aerial vehicles through special variable mass distribution devices so as to improve the controllability of the unmanned aerial vehicles.
The invention comprises a main body structure of the rotary-fixed-wing composite aircraft, a variable mass distribution device, a rotor system, a wheel motor and wheels, wherein the variable mass distribution device is used for distributing the periphery of the main body structure of the rotary-fixed-wing composite aircraft; the variable mass distribution device is a magnetic field generating device or a motor driving device; the rotor device comprises a rotor motor, a rotor and a duct, wherein the rotor motor comprises a rotor stator and a rotor, the rotor stator is fixed with the connecting plate, the rotor is connected with the rotor connecting device, the rotor stator is connected with the duct through a connecting bracket, and the duct is concentric with the rotor; the wheel motor comprises a wheel motor stator and a wheel motor rotor, wherein the wheel motor stator is connected with the main body structure of the rotary-fixed-wing composite aircraft, and the wheel motor rotor is connected with the wheel.
The magnetic field generating device comprises a variable mass distribution device platform, a magnet, an iron block and a coil. After the coil is electrified, a magnetic field is generated, electromagnetic force exists between the coil and the magnet, the motion state of the magnet is changed, and the relative position of the magnet relative to the main body structure is changed, so that the mass distribution of the composite aircraft is changed, the attitude angle of the composite aircraft is changed, and the attitude control of the composite aircraft is performed.
The motor driving device comprises a motor, a conveyor belt and a mass block, wherein the motor comprises a stator and a rotor, the stator is fixed with the main body structure of the rotary-fixed-wing composite aircraft, and the rotor is connected with the conveyor belt; the conveyor belt is connected with a mass block.
The main structure of the rotary-fixed-wing composite aircraft is provided with a vertical stabilizer and a rudder which are connected through a rudder connecting rod, so that the course stability and the course maneuvering performance of the variable-mass-distribution rotary-fixed-wing composite aircraft are enhanced.
The variable mass distribution device comprises an hourglass fixed on the main body structure of the rotary-fixed wing composite aircraft through an hourglass fixing device, the hourglass is connected with an hourglass driving motor, and the hourglass provides variable mass distribution capacity.
The landing gear is arranged at the bottom of the main body structure of the rotary-fixed-wing composite aircraft, and the landing gear plays a supporting role when the ground is parked.
The mobile base station is arranged at the bottom of the main body structure of the rotary-fixed-wing composite aircraft, and can provide communication service after the ground base station is damaged in a large scale.
The invention has the beneficial effects that:
1. combine together four rotor unmanned aerial vehicle and fixed wing unmanned aerial vehicle, richened unmanned aerial vehicle's function.
2. The variable mass distribution device is designed, so that the control capability of the rotary-fixed wing composite aircraft is enhanced, and the rotary-fixed wing composite aircraft is still controllable after the main rotor fails.
3. The rotary-fixed wing composite aircraft has larger space inside and outside the structure, can be designed secondarily, and has wide application prospect.
Drawings
FIG. 1 is a schematic view of a rotary-fixed wing composite aircraft.
FIG. 2 is a schematic illustration of a motor driven variable mass distribution device rotary-fixed wing composite aircraft.
FIG. 3 is a schematic view of an electromagnetically driven variable mass distribution device rotary-fixed wing composite aircraft.
Fig. 4 is a schematic diagram of an electromagnet structure.
Detailed Description
The invention is further described below with reference to the drawings and the detailed description.
The invention provides a variable mass distribution rotary-fixed wing composite aircraft, the structure of which is shown in figure 1, comprising a rotary-fixed wing composite aircraft main body structure 2, a variable mass distribution device 14, a rotor wing system 13, a wheel motor 22 and wheels 15, wherein the variable mass distribution device 14 is used for distributing the periphery of the rotary-fixed wing composite aircraft main body structure 2; the variable mass distribution device 14 is a magnetic field generating device 24 or a motor driving device; the rotor device comprises a rotor motor 8, a rotor 12 and a duct 5, wherein the rotor motor 8 comprises a rotor stator and a rotor 9, the rotor stator is fixed with a connecting plate 7, the rotor 10 is connected with a rotor connecting device 11, the rotor stator is connected with the duct 5 through a connecting bracket 6, and the duct 5 is concentric with the rotor 12; the wheel motor 22 comprises a wheel motor stator 21 and a wheel motor rotor 23, wherein the wheel motor stator 21 is connected with the main body structure 2 of the rotor-stator composite aircraft, and the wheel motor rotor 23 is connected with the wheel 15.
The motor driving device is shown in fig. 2 and comprises a motor 19, a conveyor belt 17 and a mass block 16, wherein the motor comprises a stator 18 and a rotor 20, the stator 18 is fixed with the main body structure 2 of the rotary-fixed wing composite aircraft, and the rotor 20 is connected with the conveyor belt 17; the conveyor 17 is connected to a mass 14.
The flight control method of the structure comprises the following steps:
step 1: the composite aircraft provides lift through the rotor system 13, so that the composite aircraft can vertically take off and land;
step 2: the rotor 20 of the mass distribution motor drives the conveyor belt 17 to move, and the relative position of the mass block 16 relative to the main body structure 2 is changed, so that the mass distribution of the composite aircraft is changed, the attitude angle of the composite aircraft is changed, and the attitude of the composite aircraft is controlled.
Step 3: during forward flight of the composite aircraft, the main body structure 2 can provide additional lift force, and energy loss of the rotor system 13 is reduced.
Step 4: the wheels 15 support the composite aircraft when the ground is parked. The composite aircraft can run on the ground by using the principle of a double-wheel self-balancing trolley through a control system.
The magnetic field generating device 24 comprises a variable mass distribution device platform 26, a magnet 25, an iron block 28 and a coil 27 as shown in fig. 3.
The flight control method of the structure comprises the following steps:
step 1: the composite aircraft provides lift through the rotor system 13, so that the composite aircraft can vertically take off and land;
step 2: as shown in fig. 4, after the coil 27 is energized, the magnetic field generating device 24 generates a magnetic field, and electromagnetic force exists between the magnetic field generating device and the magnet 25, so that the motion state of the magnet 25 is changed, the relative position of the magnet 25 relative to the main body structure 2 is changed, the mass distribution of the composite aircraft is changed, the attitude angle of the composite aircraft is changed, and the attitude of the composite aircraft is controlled.
Step 3: during forward flight of the composite aircraft, the main body structure 2 can provide additional lift force, and energy loss of the rotor system 13 is reduced.
Step 4: the wheels 15 support the composite aircraft when the ground is parked. The composite aircraft can run on the ground by using the principle of a double-wheel self-balancing trolley through a control system.
The main body structure 2 of the rotary-fixed-wing composite aircraft is provided with a vertical stabilizer 1 and a rudder 4 which are connected through a rudder connecting rod 3, so that the course stability and the course maneuvering performance of the variable-mass-distribution rotary-fixed-wing composite aircraft are enhanced.
The variable mass distribution device 14 comprises an hourglass fixed on the main body structure 2 of the rotary-fixed wing composite aircraft through an hourglass fixing device, wherein the hourglass is connected with an hourglass driving motor, and the hourglass provides variable mass distribution capability.
The landing gear is arranged at the bottom of the main body structure 2 of the rotary-fixed-wing composite aircraft, and the landing gear plays a supporting role when the ground is parked.
The mobile base station is arranged at the bottom of the main body structure 2 of the rotary-fixed-wing composite aircraft, and can provide communication service after the ground base station is damaged in a large scale.
The present invention has been described in terms of the preferred embodiments thereof, and it should be understood by those skilled in the art that various modifications can be made without departing from the principles of the invention, and such modifications should also be considered as being within the scope of the invention.
Claims (3)
1. A variable mass distribution rotary-fixed wing composite aircraft is characterized in that: the variable mass distribution device comprises a main body structure of the rotary-fixed-wing composite aircraft, a rotor wing system, a wheel motor and wheels, wherein the variable mass distribution device distributes the periphery of the main body structure of the rotary-fixed-wing composite aircraft; the variable mass distribution device is a magnetic field generating device or a motor driving device; the rotor system comprises a rotor motor, a rotor and a duct, wherein the rotor motor comprises a rotor stator and a rotor, the rotor stator is fixed with the connecting plate, the rotor is connected with the rotor connecting device, the rotor stator is connected with the duct through a connecting bracket, and the duct is concentric with the rotor; the wheel motor comprises a wheel motor stator and a wheel motor rotor, the wheel motor stator is connected with the main body structure of the rotary wing-fixed composite aircraft, and the wheel motor rotor is connected with the wheel; the magnetic field generating device comprises a variable mass distribution device platform, a magnet, an iron block and a coil; the motor driving device comprises a motor, a conveyor belt and a mass block, wherein the motor comprises a stator and a rotor, the stator is fixed with the main body structure of the rotary-fixed-wing composite aircraft, and the rotor is connected with the conveyor belt; the conveyor belt is connected with a mass block; the main body structure of the rotary-fixed-wing composite aircraft is provided with a vertical stabilizer and a rudder which are connected through a rudder connecting rod; the variable mass distribution device comprises an hourglass fixed on the main body structure of the rotary-fixed wing composite aircraft through an hourglass fixing device, and the hourglass is connected with an hourglass driving motor.
2. The variable mass distributed rotary-fixed wing composite aircraft of claim 1, wherein: the bottom of the main body structure of the rotary-fixed-wing composite aircraft is provided with a landing gear.
3. The variable mass distributed rotary-fixed wing composite aircraft of claim 1, wherein: the mobile base station is arranged at the bottom of the main body structure of the rotary-fixed-wing composite aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810015090.XA CN108177771B (en) | 2018-01-08 | 2018-01-08 | Variable mass distribution rotary-fixed wing composite aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810015090.XA CN108177771B (en) | 2018-01-08 | 2018-01-08 | Variable mass distribution rotary-fixed wing composite aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108177771A CN108177771A (en) | 2018-06-19 |
| CN108177771B true CN108177771B (en) | 2023-09-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810015090.XA Active CN108177771B (en) | 2018-01-08 | 2018-01-08 | Variable mass distribution rotary-fixed wing composite aircraft |
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| CN (1) | CN108177771B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110406655B (en) * | 2019-08-20 | 2021-03-02 | 哈尔滨工业大学（深圳） | Jumping robot with air posture adjusting function |
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|---|---|---|---|---|
| CN101643116A (en) * | 2009-08-03 | 2010-02-10 | 北京航空航天大学 | Tiltrotor controlled by double-propeller vertical duct |
| CN101795939A (en) * | 2007-08-29 | 2010-08-04 | 高级产品开发有限责任公司 | Oblique blended wing body aircraft |
| CN101879945A (en) * | 2010-07-05 | 2010-11-10 | 南昌航空大学 | Electric tilting rotor wing unmanned aerial vehicle |
| DE102009060804A1 (en) * | 2009-12-31 | 2011-07-07 | Seifert, Jost, Dr., 81927 | Device, particularly flight controller, for controlling or stabilizing aircraft, particularly rotor aircraft or fuselage or chassis frame, by utilizing gyro effect, has rotors, where outer torque is applied vertically to rotor rotating axis |
| CN103963959A (en) * | 2014-05-12 | 2014-08-06 | 北京理工大学 | Hovering type folding wing lifting body aircraft based on variable centroid technology |
| WO2016181044A1 (en) * | 2015-05-11 | 2016-11-17 | Christian Roger Rene Deslypper | Convertible airplane with exposable rotors |
| CN106379537A (en) * | 2016-09-26 | 2017-02-08 | 南京航空航天大学 | Jet self-rotation disc type aircraft capable of realizing vertical take-off and landing and working method |
| WO2017021391A1 (en) * | 2015-08-06 | 2017-02-09 | Seiwald Christian | Vtol aircraft having a movable mass for control |
-
2018
- 2018-01-08 CN CN201810015090.XA patent/CN108177771B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101795939A (en) * | 2007-08-29 | 2010-08-04 | 高级产品开发有限责任公司 | Oblique blended wing body aircraft |
| CN101643116A (en) * | 2009-08-03 | 2010-02-10 | 北京航空航天大学 | Tiltrotor controlled by double-propeller vertical duct |
| DE102009060804A1 (en) * | 2009-12-31 | 2011-07-07 | Seifert, Jost, Dr., 81927 | Device, particularly flight controller, for controlling or stabilizing aircraft, particularly rotor aircraft or fuselage or chassis frame, by utilizing gyro effect, has rotors, where outer torque is applied vertically to rotor rotating axis |
| CN101879945A (en) * | 2010-07-05 | 2010-11-10 | 南昌航空大学 | Electric tilting rotor wing unmanned aerial vehicle |
| CN103963959A (en) * | 2014-05-12 | 2014-08-06 | 北京理工大学 | Hovering type folding wing lifting body aircraft based on variable centroid technology |
| WO2016181044A1 (en) * | 2015-05-11 | 2016-11-17 | Christian Roger Rene Deslypper | Convertible airplane with exposable rotors |
| WO2017021391A1 (en) * | 2015-08-06 | 2017-02-09 | Seiwald Christian | Vtol aircraft having a movable mass for control |
| CN106379537A (en) * | 2016-09-26 | 2017-02-08 | 南京航空航天大学 | Jet self-rotation disc type aircraft capable of realizing vertical take-off and landing and working method |
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| Publication number | Publication date |
|---|---|
| CN108177771A (en) | 2018-06-19 |
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