CN114030587A - Ducted power device and dish-shaped body hinged two-body omnidirectional aircraft - Google Patents
Ducted power device and dish-shaped body hinged two-body omnidirectional aircraft Download PDFInfo
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- CN114030587A CN114030587A CN202111374359.1A CN202111374359A CN114030587A CN 114030587 A CN114030587 A CN 114030587A CN 202111374359 A CN202111374359 A CN 202111374359A CN 114030587 A CN114030587 A CN 114030587A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- B64D27/40—
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
Abstract
A kind of ducted power plant and disk body articulated two-body omnidirectional aircraft, including the fuselage of the disk body, ducted power plant and power hinge air drain; the dish-shaped body can generate pneumatic lift force during high-speed flight; a vertical air inlet through hole is formed in the center of the dish-shaped body; the air inlet through hole is connected with the ducted power device through the power hinge air passage; a disc-shaped functional load bin is erected above the air inlet through hole, and a vane is arranged above the functional load bin; the vector included angle between the ducted power device and the dish-shaped body can be changed by adjusting the turning angle of the air passage of the power hinge so as to generate momentum moment and constant moment; the ducted power device comprises an outer cylinder, a jet engine and a pneumatic control surface; the jet engine is positioned in the outer cylinder, and the air inlet end of the outer cylinder is communicated with the air outlet end of the power hinge air passage; the pneumatic control surface is arranged inside the opening of the outer cylinder body at the side of the air outlet of the jet engine; the thrust vector of the jet engine can be changed by adjusting the deflection angle of the pneumatic control surface so as to generate pneumatic torque.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a two-body omnidirectional aircraft with a ducted power device hinged with a disk body.
Background
In recent years, the unmanned aerial vehicle technology has been rapidly developed, and by carrying various functional loads on the unmanned aerial vehicle, the unmanned aerial vehicle is applied in various fields and replaces a manned aircraft to complete various specific tasks.
Unmanned aerial vehicle mainly divide into fixed wing unmanned aerial vehicle and rotor unmanned aerial vehicle according to the difference of structure type. For the fixed wing unmanned aerial vehicle, although it has fast, the long, the strong advantage of mobility of journey, still have the shortcoming of being restricted by the place of taking off and landing, when taking off, or need the runway, or need launch the track, when descending, or adopt the smooth landing, or adopt the parachuting, lead to fixed wing unmanned aerial vehicle's the security of taking off and landing and flexibility all relatively poor. For a rotor unmanned aerial vehicle, although the unmanned aerial vehicle has the advantages of capability of vertically taking off and landing, hovering in the air and low requirement on a taking-off and landing site, the unmanned aerial vehicle has the defects of low flying speed, short endurance and poor maneuverability.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a two-body omnidirectional aircraft with a ducted power device hinged with a dish-shaped body, which has the advantages of high navigational speed, long navigation range and strong maneuverability, and also has the advantages of capability of taking off and landing vertically, hovering in the air and low requirement on taking-off and landing sites, thereby not only meeting the requirement of low-altitude low-speed flight, but also meeting the requirement of high-speed high-maneuvering flight, and having the capability of omnidirectional flight.
In order to achieve the purpose, the invention adopts the following technical scheme: a kind of ducted power plant and disk body articulated two-body omnidirectional aircraft, including the fuselage of the disk body, ducted power plant and power hinge air drain; the upper surface of the body of the said disc-shaped body is the cambered surface, the lower surface of the body of the disc-shaped body is the cambered surface or level, and when the lower surface of the body of the disc-shaped body is the cambered surface, the radian of the upper surface of the body of the disc-shaped body is greater than the radian of the lower surface of the body of the disc-shaped body; a vertical air inlet through hole is formed in the center of the disc-shaped body; the power hinge air passage is positioned below the disc-shaped body, and the air inlet end of the power hinge air passage is communicated with the lower orifice of the air inlet through hole; the ducted power device is connected with the air outlet end of the power hinge air passage.
A functional load bin is arranged right above the air inlet through hole, the functional load bin is of a disc-shaped structure and is arranged on the upper surface of the dish-shaped body through a support rod fixing frame, and an air inlet gap is reserved between the functional load bin and the dish-shaped body.
And a gyroscope, an accelerometer, a magnetometer and a satellite navigator are arranged in the functional load bin.
And a vane is arranged right above the functional load bin, and an airspeed tube, an attack angle sensor and a sideslip angle sensor are arranged in the vane.
The bending angle range of the power hinge air passage is 90-180 degrees.
The vector included angle between the ducted power device and the dish-shaped body is changed by adjusting the turning angle of the power hinge air passage so as to generate momentum moment and constant moment.
The ducted power device comprises an outer cylinder, a jet engine and a pneumatic control surface; the outer cylinder body is of a cylindrical structure, and the air inlet end of the outer cylinder body is communicated with the air outlet end of the power hinge air passage; the jet engine is coaxially fixed in the outer cylinder body, and an air inlet of the jet engine is adjacent to the power hinge air passage; the pneumatic control surface is arranged inside the opening of the outer cylinder body at the side of the air outlet of the jet engine; an air filter is installed at an air inlet of the jet engine.
The number of the aerodynamic control surfaces is three or four, and the plurality of the aerodynamic control surfaces are uniformly distributed in the circumferential direction in the outer cylinder body in a radial mode.
The deflection angle range of the pneumatic control surface is-45 degrees.
And the thrust vector of the jet engine is changed by adjusting the deflection angle of the pneumatic control surface so as to generate aerodynamic moment.
The invention has the beneficial effects that:
the ducted power device and the disk-shaped body hinged two-body omnidirectional aircraft have the advantages of high navigational speed, long range and strong maneuverability, can take off and land vertically, hover in the air and have low requirements on taking off and landing sites, not only meet the requirements of low-altitude and low-speed flight, but also meet the requirements of high-speed and high-maneuvering flight and have the capability of omnidirectional flight.
Drawings
FIG. 1 is a front view of a two-body omnidirectional aircraft with a ducted power plant and a disk body articulated (the turning angle of the power hinge air passage is 180 °) according to the present invention;
FIG. 2 is a top view of a two-body omnidirectional aircraft with a ducted power plant articulated with a dish of the present invention;
FIG. 3 is a partial view of the ducted power plant of the present invention;
FIG. 4 is a front view of a two-body omnidirectional aircraft with a ducted power plant articulated with a dish (the turning angle of the power hinge air duct is 180 degrees with a Cartesian coordinate system attached) according to the present invention;
FIG. 5 is a front view of a two-body omnidirectional aircraft with a ducted power plant and a disk body articulated (the turning angle of the power hinge air passage is 180 degrees, and simultaneously, the stress analysis in a low-speed flight mode is attached);
FIG. 6 is a front view of a two-body omnidirectional aircraft with a ducted power plant and a disk body articulated (the turning angle of the power hinge air passage is 80 degrees, and meanwhile, the stress analysis in a high-speed flight mode is attached);
FIG. 7 is a top view of a two-body omnidirectional aircraft with a ducted power plant and a disk body articulated (the turning angle of the power hinge air passage is 80 degrees, and simultaneously, the power hinge air passage is accompanied with a force analysis in a high-speed flight mode);
in the figure, 1-dish-shaped body, 2-ducted power device, 3-power hinge air passage, 4-air inlet through hole, 5-functional load bin, 6-support rod, 7-vane, 8-pneumatic control surface and GQuality of foodAircraft center of mass, FPush away-vector thrust, FLifting of wineAerodynamic lift force, FResistance deviceAir resistance, MBow downPitching moment, MDeflectionYaw moment, MRoller-roll torque.
Detailed Description
The invention is described in further detail below with reference to the figures and the specific embodiments.
As shown in fig. 1 to 7, a two-body omnidirectional aircraft with a ducted power device hinged with a disk-shaped body comprises a disk-shaped body 1, a ducted power device 2 and a power hinge air passage 3; the upper surface of the disc-shaped body 1 is an arc surface, the lower surface of the disc-shaped body 1 is an arc surface or a plane, and when the lower surface of the disc-shaped body 1 is an arc surface, the radian of the upper surface of the disc-shaped body 1 is larger than that of the lower surface of the disc-shaped body 1; a vertical air inlet through hole 4 is formed in the center of the disc-shaped body 1; the power hinge air passage 3 is positioned below the disc-shaped body 1, and the air inlet end of the power hinge air passage 3 is communicated with the lower orifice of the air inlet through hole 4; the ducted power device 2 is connected with the air outlet end of the power hinge air passage 3.
A functional load bin 5 is arranged right above the air inlet through hole 4, the functional load bin 5 is of a disc-shaped structure, the functional load bin 5 is fixedly arranged on the upper surface of the disc-shaped body 1 through a support rod 6, and an air inlet gap is reserved between the functional load bin 5 and the disc-shaped body 1.
And a gyroscope, an accelerometer, a magnetometer, a satellite navigator and the like are arranged in the functional load bin 5.
A vane 7 is arranged right above the functional load bin 5, and an airspeed tube, an attack angle sensor and a sideslip angle sensor are arranged in the vane 7.
The bending angle range of the power hinge air passage 3 is 90-180 degrees.
The vector included angle between the ducted power device 2 and the dish-shaped body 1 is changed by adjusting the turning angle of the power hinge air passage 3 so as to generate momentum moment and constant moment.
The ducted power device 2 comprises an outer cylinder, a jet engine and a pneumatic control surface 8; the outer cylinder body is of a cylindrical structure, and the air inlet end of the outer cylinder body is communicated with the air outlet end of the power hinge air passage 3; the jet engine is coaxially fixed in the outer cylinder, and an air inlet of the jet engine is adjacent to the power hinge air passage 3; the pneumatic control surface 8 is arranged inside the opening of the outer cylinder body at the side of the air outlet of the jet engine; an air filter is installed at an air inlet of the jet engine.
The number of the aerodynamic control surfaces 8 is three or four, and the plurality of the aerodynamic control surfaces 7 are uniformly distributed in a radial shape in the circumferential direction in the outer cylinder.
The deflection angle range of the pneumatic control surface 8 is-45 degrees to 45 degrees.
The thrust vector of the jet engine is changed by adjusting the deflection angle of the aerodynamic control surface 8 so as to generate aerodynamic moment.
A mark point A is defined at the edge of the dish-shaped body 1, and the mass center point of the dish-shaped body 1 is defined as O1Point at, add O1The connecting line of the point-pointing mark point A is positioned as X1Axis positioning the velocity vector of the aircraft in the horizontal direction as XVIs mixing X1Axis and velocity vector XVThe angle between them is defined as the sideslip angle beta, X1The included angle between the axis and the north direction is defined as the body azimuth psi, the direction is positive to the right, and the speed azimuth is defined as psiVThen velocity azimuth ΨVThe body azimuth angle psi + the sideslip angle beta, and the range of sideslip angle beta is-180 ~ 180, therefore the aircraft has the ability of omnidirectional flight.
When the aircraft is in a vertical take-off and landing stage, the speed is low, the aerodynamic influence is not large, and the force of the aircraft in the vertical direction is provided by the thrust of the jet engine in the ducted power device 2, so that the controllable take-off and landing can be met.
After the aircraft enters a low-speed flight mode, the thrust vector of the jet engine can be changed by adjusting the deflection angle of the pneumatic control surface 8 so as to generate aerodynamic moment; meanwhile, the vector included angle between the ducted power device 2 and the dish-shaped body 1 is changed by adjusting the turning angle of the power hinge air passage 3 so as to generate momentum moment and watch constant moment; after the aircraft enters a high-speed flight mode, the pitching moment, the rolling moment and the yawing moment of the aircraft can be changed through the matching of the aerodynamic moment and the momentum moment guarding constant moment, and finally the attitude adjustment of the aircraft under the high maneuvering performance is realized.
The stress of the aircraft is analyzed by combining the attached drawings.
Firstly, establishing a Cartesian coordinate system of each part of the aircraft, namely an inertia coordinate system, a dish-shaped body coordinate system, a speed coordinate system and a ducted power device coordinate system in sequence.
In the inertial frame, OgThe point is any point on the ground plane, and OgXgThe coordinates point in the north direction, OgZgCoordinate perpendicular to the ground plane, OgYgAccording with the right-hand rule.
In the dish-shaped body coordinate system, O1The point is the centroid point of the body of the dish-shaped body, O1X1Coordinate pointing mark points A, O1Z1Coordinate perpendicular to O in the longitudinal plane1X1Coordinate, O1Y1According with the right-hand rule.
In the velocity coordinate system, OvThe point being the centre of mass, O, of the aircraftvXvThe coordinates being directed in the direction of movement of the centre of mass, O, of the aircraftvZvCoordinate is at XvOvZvIn-plane perpendicular to OvXvCoordinate, OvYvAccording with the right-hand rule.
In the ducted power plant coordinate system, O2The point is the center of mass point, O, of the ducted power plant2X2The coordinates being directed in the normal-axis direction, O, of the jet engine2Z2Coordinate is at X2O2Z2In-plane perpendicular to O2X2Coordinate, O2Y2According with the right-hand rule.
The relationship between the inertial coordinate system and the dish-shaped body coordinate system is as follows:
in the formula, psi is the body azimuth angle, theta is the pitch angle, and gamma is the roll angle.
The relation between the coordinate system of the dish-shaped body and the coordinate system of the ducted power device is as follows:
in the formula, λ1To wind around O1Z1Joint angle of rotation of coordinate axes, λ2To wind around O1X1Joint angle of rotation of the coordinate axes.
The relationship between the speed coordinate system and the dish-shaped body coordinate system is as follows:
in the formula, alpha is an attack angle, and beta is a sideslip angle.
When the aircraft is in a low-speed flight mode, because the flight speed is very low, the aerodynamic force can be ignored, the aerodynamic torque is controlled through the aerodynamic control surface 8, the momentum moment keeper constant torque is controlled through the power hinge air passage 3, the attitude of the aircraft is adjusted through the cooperation of the aerodynamic torque and the momentum moment keeper constant torque, and in the low-speed flight process, the lift force of the dish-shaped body 1 is provided by the vertical component of the vector thrust of the jet engine. Specifically, the aircraft has the following stress when flying at low speed: the vertical force is the vertical component of gravity and vector thrust, and the horizontal force is the horizontal component of air resistance and vector thrust. In addition, the yawing moment is generated through the differential motion of the aerodynamic control surface 8, the aerodynamic moment is controlled through adjusting the deflection angle of the aerodynamic control surface 8, and when the aerodynamic moment is matched with the momentum conservation moment, the pitching moment and the rolling moment can be generated.
When the aircraft is in a high-speed flight mode, the aircraft is simultaneously under the action of gravity, aerodynamic force and vector thrust, the included angle between the dish-shaped body fuselage 1 and the jet engine is controlled through the power hinge air passage 3, the vector thrust of the jet engine provides flight thrust for the aircraft, the lift force of the aircraft is mainly provided by the aerodynamic lift force generated by the dish-shaped body fuselage 1 during high-speed flight, and the vertical component of the vector thrust of the jet engine only provides a small amount of lift force. When the vector thrust of the jet engine is not larger than the gravity center of the aircraft, the aircraft can generate a head-up moment, in order to balance the influence of asymmetric external force and external force distance on the aircraft, the aircraft can change the aerodynamic moment by controlling the aerodynamic control surface 8, and after the aerodynamic moment is matched with the momentum moment conservation moment, the flight attitude of the aircraft can be changed, so that the stability of the aircraft in high-speed flight is kept. Specifically, the aircraft is stressed at high speed flight: the vertical force is the vertical component of gravity and lift force, the horizontal force is the component of air resistance and vector thrust in the motion direction, and the normal force is the horizontal component of lift force, lateral air resistance and vector thrust. In addition, the roll moment is generated through the differential motion of the aerodynamic control surface 8, the aerodynamic moment is controlled through adjusting the deflection angle of the aerodynamic control surface 8, and when the aerodynamic moment is matched with the momentum conservation moment, the yaw moment and the pitching moment can be generated.
The embodiments are not intended to limit the scope of the present invention, and all equivalent implementations or modifications without departing from the scope of the present invention are intended to be included in the scope of the present invention.
Claims (10)
1. The utility model provides a duct formula power device and two somatic omnidirectional aircraft of dish body articulated which characterized in that: comprises a disc-shaped body, a duct-type power device and a power hinge air passage; the upper surface of the body of the said disc-shaped body is the cambered surface, the lower surface of the body of the disc-shaped body is the cambered surface or level, and when the lower surface of the body of the disc-shaped body is the cambered surface, the radian of the upper surface of the body of the disc-shaped body is greater than the radian of the lower surface of the body of the disc-shaped body; a vertical air inlet through hole is formed in the center of the disc-shaped body; the power hinge air passage is positioned below the disc-shaped body, and the air inlet end of the power hinge air passage is communicated with the lower orifice of the air inlet through hole; the ducted power device is connected with the air outlet end of the power hinge air passage.
2. The omnidirectional aircraft with two bodies and a ducted power device hinged with a disk body as claimed in claim 1, wherein: a functional load bin is arranged right above the air inlet through hole, the functional load bin is of a disc-shaped structure and is arranged on the upper surface of the dish-shaped body through a support rod fixing frame, and an air inlet gap is reserved between the functional load bin and the dish-shaped body.
3. The omnidirectional aircraft with two bodies and the ducted power device hinged with the disk body as claimed in claim 2, wherein: and a gyroscope, an accelerometer, a magnetometer and a satellite navigator are arranged in the functional load bin.
4. The omnidirectional aircraft with two bodies and the ducted power device hinged with the disk body as claimed in claim 2, wherein: and a vane is arranged right above the functional load bin, and an airspeed tube, an attack angle sensor and a sideslip angle sensor are arranged in the vane.
5. The omnidirectional aircraft with two bodies and a ducted power device hinged with a disk body as claimed in claim 1, wherein: the bending angle range of the power hinge air passage is 90-180 degrees.
6. The omnidirectional aircraft with two bodies and a ducted power device hinged with a disk body as claimed in claim 5, wherein: the vector included angle between the ducted power device and the dish-shaped body is changed by adjusting the turning angle of the power hinge air passage so as to generate momentum moment and constant moment.
7. The omnidirectional aircraft with two bodies and a ducted power device hinged with a disk body as claimed in claim 1, wherein: the ducted power device comprises an outer cylinder, a jet engine and a pneumatic control surface; the outer cylinder body is of a cylindrical structure, and the air inlet end of the outer cylinder body is communicated with the air outlet end of the power hinge air passage; the jet engine is coaxially fixed in the outer cylinder body, and an air inlet of the jet engine is adjacent to the power hinge air passage; the pneumatic control surface is arranged inside the opening of the outer cylinder body at the side of the air outlet of the jet engine; an air filter is installed at an air inlet of the jet engine.
8. The omnidirectional aircraft with two bodies and a ducted power device hinged with a disk body as claimed in claim 7, wherein: the number of the aerodynamic control surfaces is three or four, and the plurality of the aerodynamic control surfaces are uniformly distributed in the circumferential direction in the outer cylinder body in a radial mode.
9. The omnidirectional aircraft with two bodies and a ducted power device hinged with a disk body as claimed in claim 7, wherein: the deflection angle range of the pneumatic control surface is-45 degrees.
10. The omnidirectional aircraft with a ducted power plant and a hinged dish as claimed in claim 9, wherein: and the thrust vector of the jet engine is changed by adjusting the deflection angle of the pneumatic control surface so as to generate aerodynamic moment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111374359.1A CN114030587B (en) | 2021-11-19 | 2021-11-19 | Two-body omnidirectional aircraft with ducted power device hinged with disc-shaped body |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111374359.1A CN114030587B (en) | 2021-11-19 | 2021-11-19 | Two-body omnidirectional aircraft with ducted power device hinged with disc-shaped body |
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| CN114030587A true CN114030587A (en) | 2022-02-11 |
| CN114030587B CN114030587B (en) | 2023-11-07 |
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| US20030098388A1 (en) * | 2001-08-08 | 2003-05-29 | Walmsley Eric Ronald | Circular vertical take off & landing aircraft |
| DE102007051993A1 (en) * | 2007-10-31 | 2009-05-07 | Viacheslav Pavlikov | Aircraft, has circular wings arranged in air channels, where air is reduced over upper surfaces of upper sphere for forming additional buoyancy when ventilator system or turbo-blower system or other drive systems is operated |
| CN103935517A (en) * | 2014-05-09 | 2014-07-23 | 张培贵 | Aircraft |
| 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 |
| CN107380428A (en) * | 2017-09-04 | 2017-11-24 | 广西悟空科技有限公司 | Dish-style rotor craft |
| CN208134626U (en) * | 2018-03-29 | 2018-11-23 | 兰贤才 | An a kind of axis disc-shaped flying craft |
| CN110641695A (en) * | 2019-09-20 | 2020-01-03 | 南京航空航天大学 | Power system suitable for small vertical take-off and landing fixed wing aircraft |
-
2021
- 2021-11-19 CN CN202111374359.1A patent/CN114030587B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030098388A1 (en) * | 2001-08-08 | 2003-05-29 | Walmsley Eric Ronald | Circular vertical take off & landing aircraft |
| DE102007051993A1 (en) * | 2007-10-31 | 2009-05-07 | Viacheslav Pavlikov | Aircraft, has circular wings arranged in air channels, where air is reduced over upper surfaces of upper sphere for forming additional buoyancy when ventilator system or turbo-blower system or other drive systems is operated |
| CN103935517A (en) * | 2014-05-09 | 2014-07-23 | 张培贵 | Aircraft |
| 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 |
| CN107380428A (en) * | 2017-09-04 | 2017-11-24 | 广西悟空科技有限公司 | Dish-style rotor craft |
| CN208134626U (en) * | 2018-03-29 | 2018-11-23 | 兰贤才 | An a kind of axis disc-shaped flying craft |
| CN110641695A (en) * | 2019-09-20 | 2020-01-03 | 南京航空航天大学 | Power system suitable for small vertical take-off and landing fixed wing aircraft |
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| CN114030587B (en) | 2023-11-07 |
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