CN109466763B - Aircraft with retractable rotor wing and flight mode - Google Patents
Aircraft with retractable rotor wing and flight mode Download PDFInfo
- Publication number
- CN109466763B CN109466763B CN201811482111.5A CN201811482111A CN109466763B CN 109466763 B CN109466763 B CN 109466763B CN 201811482111 A CN201811482111 A CN 201811482111A CN 109466763 B CN109466763 B CN 109466763B
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- rotor
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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
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/50—Blades foldable to facilitate stowage of aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
The invention belongs to the field of flying products, and particularly discloses an aircraft with foldable rotor wings, which comprises an aircraft body, rotor wings and a jet engine, wherein the jet engine is arranged at the tail part of the aircraft body; meanwhile, the invention also discloses a flight mode of the aircraft. The rotor wing can rotate to be parallel or vertical to the horizontal plane in the flying process, and the rotor wing blades can be unfolded and folded, so that the vertical taking-off and landing and hovering capabilities of a common tilting aircraft are reserved, the wind resistance generated by the rotor wing blades in the advancing process is overcome, and the flying speed of the aircraft is improved.
Description
Technical Field
The invention belongs to the field of flight products, and particularly relates to an aircraft with a foldable rotor wing and a flight mode.
Background
The tilt rotor aircraft is a novel aircraft integrating a fixed-wing aircraft and a helicopter, and has the capability of vertical take-off and landing and hovering in the air, and the capability of higher-speed cruising flight like a propeller aircraft. Tilt rotor aircraft have a unique set of rotatable rotor tilt system assemblies, which are typically mounted at the tips of two wings similar to the wings of a fixed wing aircraft, with the rotor shaft perpendicular to the ground during vertical takeoff and landing, in a cross-helicopter flight state, and capable of hovering, flying fore and aft, and flying sideways in the air. After the tilt rotor aircraft takes off and reaches a certain speed, the rotor shaft can tilt forward by 90 degrees and is in a horizontal state, the rotor is used as a tension propeller, and at the moment, the tilt rotor aircraft can fly remotely at a higher speed like a fixed-wing aircraft. However, even if the rotor shaft is rotated to the horizontal state to fly in the propeller aircraft, the speed thereof is still low relative to the jet engine aircraft speed due to the shape and size limitations of the rotor itself and the characteristics of the propeller aircraft itself.
Disclosure of Invention
Aiming at the existing problems, the invention provides an aircraft with a foldable rotor wing and also provides a flight mode of the aircraft, and the specific technical scheme is as follows.
The utility model provides an aircraft of rotor can be drawn in, includes aircraft body, rotor and jet engine, jet engine installs in aircraft body afterbody, the rotor is respectively through the rotatable both sides of installing in the aircraft body of rotation axis, the rotor includes rotor shaft, rotor blade and base, the base includes fixing base and rotation piece, rotate piece and fixing base swing joint, it can be rotatory around its self axis to rotate the piece, the rotor blade is connected with rotating the piece through the gyration pin, the rotor blade can rotate around the axis of gyration pin to draw in to laminating with rotor shaft surface. The rotor wing and the rotor wing blades can rotate in different states, the rotor wing and the horizontal plane are converted into a state that the rotor wing and the horizontal plane vertically drive the aircraft to ascend during take-off, or the rotor wing and the horizontal plane are parallel during flight and drive the aircraft to advance in a propeller mode, or power is provided by a jet engine during acceleration, and the spiral blades are folded to reduce resistance during flight.
Further, rotor shaft outer surface fixedly connected with is used for assisting the fixed fastening device of rotor blade, the fixed slot has been seted up at the fastening device middle part, the shape and the groove width of fixed slot are corresponding with the shape and the thickness of rotor blade. The rotor blades are folded and retracted, and the fastening mechanism fixes the rotor blades, so that the flying process is more stable.
Optionally, the number of the rotor blades is two, and the two rotor blades are symmetrically distributed; the rotor blades are arranged in an upper-lower mode and are vertical to the horizontal plane before being folded.
Optionally, the number of the rotor blades is three, and an angle of 120 ° is formed between adjacent rotor blades; and before the rotor blades are folded, the position of the rotor blades is that any one rotor blade is vertical to the horizontal plane.
Optionally, the number of the rotor blades is four, and a 90-degree angle is formed between adjacent rotor blades; before the rotor blades are folded, the position of the rotor blades is that any one rotor blade forms an angle of 45 degrees with the horizontal plane.
A flying mode of an aircraft with a retractable rotor wing,
during taking off, the rotor wing is vertical to the horizontal plane, the rotor wing blades are in an unfolded state and are in an inclined state, the jet engine is in a closed state, the rotor wing blades rotate to drive the aircraft to ascend, and when the aircraft reaches a certain height in the air, the rotor wing rotates by 90 degrees to be parallel to the horizontal plane, so that the aircraft is driven to fly in a propeller aircraft mode;
after taking off, the jet engine is started, the rotor blade stops rotating, the rotating piece rotates around the axis of the rotating piece until the rotor blade is parallel to the advancing direction of the aircraft, and then the rotor blade rotates around the axis of the rotating pin until the rotor blade is attached to the outer surface of the rotor shaft;
when descending, the aircraft slows down, the rotor blade is expanded to operating condition and begins to rotate by the state of drawing in, jet engine power reduces gradually to closing, passes through rotor drive aircraft by jet engine drive aircraft this moment, the rotor is rotatory 90 to perpendicular with the horizontal direction, begins to descend.
Meanwhile, the aircraft can take off by the power provided by the jet engine, the rotor wing is always kept parallel to the horizontal plane in the flying process, the rotor wing blades are folded and attached to the outer surface of the rotor wing shaft, and the jet engine still provides the power after taking off.
Has the advantages that: the aircraft has the capability of vertical take-off and landing and hovering in the air of a common tilting aircraft, and the rotor blades of the aircraft can move around the rotating pin to be attached to the outer surface of the rotor shaft after taking off, so that the jet engine provides power, the wind resistance generated by the rotor blades in the advancing process is overcome, and the speed of the aircraft is greatly improved.
Drawings
FIG. 1 is a schematic illustration of an aircraft in an exemplary embodiment during takeoff;
FIG. 2 is a schematic view of a rotor of an exemplary embodiment shown rotated 90 after takeoff;
FIG. 3 is a schematic view of a rotor blade of an exemplary embodiment of an aircraft shown in a state rotated parallel to a forward direction after takeoff;
FIG. 4 is a schematic illustration of a stowed rotor of the aircraft after takeoff in an exemplary embodiment;
FIG. 5 is a schematic diagram of a base in an embodiment.
Reference numerals; 1-a jet engine; 2-a rotor shaft; 3-a fastening mechanism; 4-rotor blades; 5-a base; 6-a rotation pin; 7-a fixed seat; 8-rotating part.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the scope of protection of the present invention.
As shown in fig. 1, an aircraft capable of retracting a rotor wing comprises an aircraft body, rotor wings and a jet engine 1, wherein the jet engine 1 is installed at the tail part of the aircraft body, the rotor wings are respectively installed at two sides of the aircraft body, the rotor wings are connected with the aircraft body through rotating shafts and can rotate around the rotating shafts, the rotor wings comprise rotor wing shafts 2, rotor wing blades 4 and bases 5, the bases 5 comprise fixing bases 7 and rotating parts 8, the rotating parts 8 are movably connected with the fixing bases 7, the rotating parts 8 can rotate around the axes of the rotating parts, the rotor wing blades 4 are respectively connected with the corresponding rotating parts 8 through rotating pins 6, the rotor wing blades 4 can rotate around the axes of the rotating pins 6 and are folded to be attached to the outer surface of the rotor wing shafts 2, fastening mechanisms 3 are welded to the outer surface of the rotor wing shafts 2, the fastening mechanisms 3 are used for assisting the fixing of the rotor wing blades 4 after the rotor wing blades 4, the middle of the fastening mechanism 3 is provided with a fixing groove, and the shape and the groove width of the fixing groove correspond to the shape and the thickness of the rotor blade 4.
In the present embodiment, the number of the rotor blades 4 is preferably three, an angle formed between adjacent rotor blades 4 is 120 °, and any one of the rotor blades 4 is perpendicular to the horizontal plane before furling, so as to prevent interference caused by overlapping with the aircraft body during furling.
Flight mode of the aircraft: as shown in fig. 1, during takeoff, the jet engine 1 is in a closed state, the rotor is perpendicular to the horizontal plane, the rotor blades 4 are unfolded, and the rotor blades 4 are in an inclined state, the aircraft is driven to ascend by the rotation of the rotor blades 4 to realize vertical takeoff, after the aircraft takes off to reach a certain height, as shown in fig. 2, the rotor rotates by 90 degrees to be parallel to the horizontal plane, and at the moment, the aircraft is driven to advance by the rotation of the rotor blades 4; after taking off, the jet engine 1 is started, as shown in fig. 3, when speed change is required, the rotor blades 4 stop rotating, one rotor blade 4 is vertical to the horizontal plane, the rotating member 8 rotates around the axis of the rotating member 8 to the state that the rotor blade 4 is parallel to the advancing direction of the aircraft, as shown in fig. 4, the rotor blade 4 rotates around the axis of the rotating pin 6 to the furled state attached to the outer surface of the rotor shaft 2, and the rotor blade 4 is fixed in the fixing groove; when descending, reduce jet engine 1's power and make the aircraft slow down, rotor blade 4 is expanded to operating condition and begins to rotate by the state of drawing in, and jet engine 1 reduces power gradually and until closing, and the aircraft passes through rotor drive aircraft by jet engine 1 drive aircraft this moment, and then the rotor is rotatory 90 to perpendicular with the horizontal plane, and the rethread reduces rotor blade 4's rotational speed and makes the aircraft descend.
Meanwhile, the aircraft can take off by the power provided by the jet engine 1, the rotor wing is always kept parallel to the horizontal plane in the flying process, the rotor wing blades 4 are folded and attached to the outer surface of the rotor wing shaft 2, and the jet engine 1 still provides power after taking off.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. An aircraft with retractable rotor, comprising an aircraft body, a rotor and a jet engine (1), characterized in that: the jet engine (1) is arranged at the tail part of the aircraft body; the rotor wings are respectively rotatably installed on two sides of the aircraft body through rotating shafts, each rotor wing comprises a rotor wing shaft (2), rotor wing blades (4) and a base (5), each base (5) comprises a fixed seat (7) and a rotating part (8), each rotating part (8) is movably connected with the corresponding fixed seat (7), each rotating part (8) can rotate around the axis of the corresponding rotating part, each rotor wing blade (4) is connected with each rotating part (8) through a rotating pin (6), and each rotor wing blade (4) can rotate around the axis of the corresponding rotating pin (6) and is folded to be attached to the outer surface of the corresponding rotor wing shaft (2);
the flight mode of the aircraft comprises:
during takeoff, the rotor wing is vertical to the horizontal plane, the rotor wing blades (4) are in an unfolded state, the rotor wing blades (4) are in an inclined state, the jet engine (1) is in a closed state, the rotor wing blades (4) rotate to drive the aircraft to ascend, and when the aircraft reaches a certain height in the air, the rotor wing rotates by 90 degrees to be parallel to the horizontal plane, so that the aircraft is driven to fly in a propeller aircraft mode;
after taking off, the jet engine (1) starts, the rotor blade (4) stops rotating, the rotating piece (8) rotates around the axis of the rotating piece (8) until the rotor blade (4) is parallel to the advancing direction of the aircraft, and then the rotor blade (4) rotates around the axis of the rotating pin (6) until the rotor blade is attached to the outer surface of the rotor shaft (2).
2. A stowable rotor craft according to claim 1 wherein: the rotor shaft (2) outer fixed surface is connected with and is used for assisting fixed fastening device (3) of rotor blade (4), the fixed slot has been seted up at fastening device (3) middle part, the shape and the groove width of fixed slot are corresponding with the shape and the thickness of rotor blade (4).
3. A stowable rotor craft according to claim 2 wherein: the number of the rotor blades (4) is two, and the two rotor blades are symmetrically distributed; the rotor blades (4) are arranged in an upper-lower mode before being folded and are vertical to the horizontal plane.
4. A stowable rotor craft according to claim 2 wherein: the number of the rotor blades (4) is three, and an angle of 120 degrees is formed between every two adjacent rotor blades (4); before the rotor blades (4) are folded, any one rotor blade (4) is vertical to the horizontal plane.
5. A stowable rotor craft according to claim 2 wherein: the number of the rotor blades (4) is four, and a 90-degree angle is formed between every two adjacent rotor blades (4); before the rotor blades (4) are folded, the position of any rotor blade (4) forms an angle of 45 degrees with the horizontal plane.
6. A flying mode of a retractable rotor aircraft according to any one of claims 1 to 5, wherein:
during takeoff, the rotor wing is vertical to the horizontal plane, the rotor wing blades (4) are in an unfolded state, the rotor wing blades (4) are in an inclined state, the jet engine (1) is in a closed state, the rotor wing blades (4) rotate to drive the aircraft to ascend, and when the aircraft reaches a certain height in the air, the rotor wing rotates by 90 degrees to be parallel to the horizontal plane, so that the aircraft is driven to fly in a propeller aircraft mode;
after taking off, the jet engine (1) is started, the rotor blades (4) stop rotating, the rotating piece (8) rotates around the axis of the rotating piece (8) until the rotor blades (4) are parallel to the advancing direction of the aircraft, and then the rotor blades (4) rotate around the axis of the rotating pin (6) until the rotating piece is attached to the outer surface of the rotor shaft (2);
when descending, the aircraft slows down, rotor blade (4) are expanded to operating condition and begin to rotate by the state of drawing in, jet engine (1) power reduces gradually to closing, passes through rotor drive aircraft by jet engine (1) drive aircraft this moment, the rotor is rotatory 90 to perpendicular with the horizontal direction, begins to descend.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811482111.5A CN109466763B (en) | 2018-12-05 | 2018-12-05 | Aircraft with retractable rotor wing and flight mode |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811482111.5A CN109466763B (en) | 2018-12-05 | 2018-12-05 | Aircraft with retractable rotor wing and flight mode |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109466763A CN109466763A (en) | 2019-03-15 |
| CN109466763B true CN109466763B (en) | 2021-06-25 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811482111.5A Active CN109466763B (en) | 2018-12-05 | 2018-12-05 | Aircraft with retractable rotor wing and flight mode |
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| Country | Link |
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| CN (1) | CN109466763B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1326652A (en) * | 1971-02-16 | 1973-08-15 | Westland Aircraft Ltd | Aircraft |
| US4691878A (en) * | 1985-11-06 | 1987-09-08 | The United States Of America As Represented By The Secretary Of The Navy | Tilt-rotor wing fold mechanism and method |
| CN201800916U (en) * | 2010-10-12 | 2011-04-20 | 徐延宇 | Lifting folding propeller |
| CN205022861U (en) * | 2015-09-06 | 2016-02-10 | 长沙鸿浪自动化科技有限公司 | VTOL fixed wing aircraft |
| CN206552260U (en) * | 2017-03-02 | 2017-10-13 | 北京天宇新超航空科技有限公司 | A kind of efficient vertically taking off and landing flyer |
| CN107856854A (en) * | 2017-09-22 | 2018-03-30 | 珠海佰家科技有限公司 | A kind of unmanned plane propeller and its unmanned plane |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9156545B1 (en) * | 2013-05-22 | 2015-10-13 | Bell Helicopter Textron Inc. | Folding of rotorcraft rotor blades |
| US10414483B2 (en) * | 2016-09-21 | 2019-09-17 | Bell Helicopter Textron, Inc. | Tiltrotor articulated wing extension |
-
2018
- 2018-12-05 CN CN201811482111.5A patent/CN109466763B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1326652A (en) * | 1971-02-16 | 1973-08-15 | Westland Aircraft Ltd | Aircraft |
| US4691878A (en) * | 1985-11-06 | 1987-09-08 | The United States Of America As Represented By The Secretary Of The Navy | Tilt-rotor wing fold mechanism and method |
| CN201800916U (en) * | 2010-10-12 | 2011-04-20 | 徐延宇 | Lifting folding propeller |
| CN205022861U (en) * | 2015-09-06 | 2016-02-10 | 长沙鸿浪自动化科技有限公司 | VTOL fixed wing aircraft |
| CN206552260U (en) * | 2017-03-02 | 2017-10-13 | 北京天宇新超航空科技有限公司 | A kind of efficient vertically taking off and landing flyer |
| CN107856854A (en) * | 2017-09-22 | 2018-03-30 | 珠海佰家科技有限公司 | A kind of unmanned plane propeller and its unmanned plane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109466763A (en) | 2019-03-15 |
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