CN213200097U - Fixed wing aircraft with vertical take-off and landing function - Google Patents
Fixed wing aircraft with vertical take-off and landing function Download PDFInfo
- Publication number
- CN213200097U CN213200097U CN202020468232.0U CN202020468232U CN213200097U CN 213200097 U CN213200097 U CN 213200097U CN 202020468232 U CN202020468232 U CN 202020468232U CN 213200097 U CN213200097 U CN 213200097U
- Authority
- CN
- China
- Prior art keywords
- rotor
- wing
- auxiliary
- fuselage
- aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 26
- 230000007246 mechanism Effects 0.000 claims description 38
- 238000011084 recovery Methods 0.000 claims description 26
- 239000006096 absorbing agent Substances 0.000 claims description 20
- 230000035939 shock Effects 0.000 claims description 20
- 238000002485 combustion reaction Methods 0.000 claims description 12
- 229910000831 Steel Inorganic materials 0.000 claims description 10
- 239000010959 steel Substances 0.000 claims description 10
- 230000005540 biological transmission Effects 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 9
- 230000008878 coupling Effects 0.000 claims description 8
- 238000010168 coupling process Methods 0.000 claims description 8
- 238000005859 coupling reaction Methods 0.000 claims description 8
- 230000009471 action Effects 0.000 claims description 4
- 230000007704 transition Effects 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
Images
Landscapes
- Toys (AREA)
Abstract
A fixed-wing aircraft with vertical take-off and landing functions. The aircraft comprises an aircraft body, tilting wings, a main tilting rotor, an auxiliary tilting rotor, a horizontal tail rudder, a vertical tail rudder, a front undercarriage, a rear undercarriage, a power battery system and a flight control system. The aircraft is in a conventional fixed wing layout; the tilting wings are slightly arranged at two ends of a wing of the airplane body, main tilting rotors are arranged on the tilting wings, the main tilting rotors can rotate between the vertical direction and the forward direction, auxiliary tilting rotors can also rotate between the vertical direction and the forward direction, and the auxiliary tilting rotors are arranged at the tail of the airplane; the aircraft is transitionable between a forward flight mode and a vertical takeoff and landing flight mode and has a tiltrotor aircraft that operates in response to autonomous flight controls, remote flight controls, on-board pilot controls, and/or combinations thereof. The aircraft has the high-efficiency flat flight performance of a fixed wing aircraft and the vertical take-off, landing and hovering functions of a tilt rotor aircraft.
Description
Technical Field
The present invention relates generally to aircraft having transitions between forward flight modes and vertical takeoff and landing flight modes, and in particular to tiltrotor aircraft having operation responsive to autonomous flight control, remote flight control, onboard pilot control, and/or combinations thereof.
Background
For fixed wing aircraft, the lift is derived from the forward motion of the wings deflecting the air downwards to support the aircraft in flight, so that during its takeoff and landing phases, a runway is usually required to reach a minimum ground clearance speed or to reduce its speed to land.
Unlike fixed wing aircraft, VTOL aircraft do not require a runway. In contrast, a vertical take-off and landing aircraft is capable of taking-off, hovering, and landing vertically. Such as a helicopter, having one or more rotors that provide lift and thrust to an aircraft, which not only provides hover and vertical take-off and landing, but also provides forward, backward, and sideways flight. These attributes make helicopters useful in areas where fixed wing aircraft cannot take off and land. However, the helicopter has low flat flight efficiency and short flight range.
Another example of a vertical takeoff and landing aircraft is a tiltrotor aircraft that generates lift and propulsion using a propulsion rotor, which is typically coupled to the end of a fixed wing. The rotation of the rotor relative to the fixed wing enables the aircraft to have the capability for vertical takeoff, hovering and landing, thereby enabling the tiltrotor aircraft to have the vertical takeoff and landing capability of a helicopter and the high-efficiency level flight capability of the fixed wing. However, tiltrotor aircraft are inefficient at vertical take-off and landing due to disturbances caused by the fixed-wing airfoils, and control is also made difficult.
Yet another example of a VTOL aerial vehicle is a tilt wing aerial vehicle, which features rotatable wings. The propellers are coupled to the rotating wings to provide the required vertical thrust for takeoff and landing, and the required forward thrust during forward flight to generate lift from the wings. The tilt wing design enables slipstream from the propeller to impact the wing on its minimum size, thus, the tilt wing aircraft improves vertical thrust efficiency compared to tilt wing aircraft. However, since the wing side area that vertically tilts is large, it is affected by wind force seriously, and is difficult to control during hovering. And when the tilt wing aircraft transits from vertical flight and hovering to forward flight, the initial attack angle of the wing is large, so that large-area turbulence is generated in airflow, and control difficulty is caused.
Disclosure of Invention
The utility model aims at overcoming the drawback of current aircraft, providing one kind and having the high efficiency of fixed wing class aircraft and take off and land, hover the function of tilting rotor class aircraft, but the aircraft of the shortcoming of the inefficiency when not having tilting rotor class aircraft to take off and land perpendicularly, hover.
The invention relates to a fixed wing aircraft with vertical take-off and landing functions, which is characterized by comprising:
a fuselage (1); a tip (2) of a tilt wing, the tilt wing tip being mounted at both ends of a wing (102) of the fuselage, the tilt wing tip being rotatable between vertical and forward relative to the fuselage; the main tilt rotor wing (3) is provided with two rotor wings which are respectively arranged on the tilt wing tips (2), and the main tilt rotor wing (3) can rotate between a vertical lift force and a forward thrust force along with the tilt wing tips (2); an auxiliary tilt rotor (4) rotatably mounted below a vertical tail (104) of the fuselage, rotatable between a vertical lift and a forward thrust;
the vertical tail rudder (5) is arranged at a vertical tail wing (104) of the fuselage through a pin shaft and is driven by a vertical tail driving mechanism; the horizontal tail rudder (6) is arranged at a horizontal tail wing (105) of the fuselage through a pin shaft and is driven by a horizontal tail driving mechanism; a nose landing gear (7) mounted to the front of the fuselage (1); the rear landing gear (8) is mounted in the middle of the fuselage (1); the power system is composed of a battery system, an internal combustion engine generator set combination or at least one of the battery system, the internal combustion engine generator set combination and the internal combustion engine generator set combination, and at least comprises the battery system; a flight control system;
in the vertical lift state, the main tilt rotor (3) is approximately positioned on the same horizontal plane, and the rotation axis of the auxiliary tilt rotor (4) is parallel to the rotation axis of the main tilt rotor (3);
in the forward thrust state, the main tilting rotor (3) is located on the same vertical surface, the auxiliary tilting rotor (4) stops rotating, the blades are feathered by the variable pitch mechanism, and the two blades are in a horizontal state along the extension direction.
Further, the aircraft is characterized in that the fuselage (1) comprises: a cabin (101) located in front of the fuselage (1); a wing (102) in the form of an upper monowing, located in an upper part of the fuselage (1); a tail boom (103) connecting the cabin (101) with a horizontal tail wing (105), a vertical tail wing (104); a vertical tail wing (104) which is positioned at the tail part of the fuselage (1); a horizontal tail wing (105) which is positioned at the tail part of the fuselage (1); a second winglet (106) positioned aft of a cabin (101) of a fuselage; a seat (107) located within the cabin (101); an instrument desk (108) located at the front inside the cabin (101); a console (109) located at the front inside the cabin (101).
Further, the aircraft is characterized in that the main tiltrotor (3) comprises: a main blade (301); a main fairing (302); the variable-pitch mechanism (303) comprises a main propeller hub (30301), a variable-pitch rod (30302), a main variable-pitch connecting rod (30303), a main variable-pitch driver (30304) and a blade rocker arm (30305), wherein the main variable-pitch driver (30304) drives the variable-pitch rod (30302), and the blade rocker arm (30305) is driven by the main variable-pitch connecting rod (30303); a main drive motor (304) comprising a motor rotor (30401), a motor stator (30402), a driver; a shield (305); a rotor support member (306); the rotor driver (307) comprises a shell (30701), a worm wheel (30702), a worm (30703), a worm end gear (30704), a motor end gear (30705) and a motor (30706), wherein the motor (30706) drives the motor end gear (30705), the motor end gear (30705) drives the worm rod end gear (30704), and the worm rod end gear (30704) drives the worm wheel (30702); a rotor securing member (308); the right-angle coupling (309) comprises a transmission shaft (30901), a driving gear (30902) and a driven gear (30903);
the main blade (301) is mounted on the pitch mechanism (303); the variable pitch mechanism (303) is arranged on a rotor (30401) of the driving motor; the driving motor stator (30402) is fixedly connected to the rotor wing supporting part; the rotor wing fixing part (308) is fixedly connected to the end part of the wing (102) of the fuselage; the shell (30701) of the rotor driver (307) is connected with the rotor fixing part (308), and the worm wheel (30702) of the rotor driver (307) is connected with the rotor supporting part (306);
the rotor wing supporting component (306) is fixedly connected with an inclined rotating wing tip (2);
the motor rotor (30401) of main rotor (3) that verts is connected with driving gear (30902) of right angle shaft coupling (309), driven gear (30903) is connected to driving gear (30902), transmission shaft (30901) is connected to driven gear (30903), the transmission shaft (30901) other end is connected with driven gear (30903) of the other end, driven gear (30903) of the other end is connected with driving gear (30902) of the other end, driving gear (30902) of the other end is connected with motor rotor (30401) of the main rotor (3) that verts of the other end.
Further, the aircraft is characterized in that the auxiliary tiltrotor (4) comprises: a tilt actuator (401); a mounting flange (402); a tilting rocker arm (403); an auxiliary blade drive motor (404); an auxiliary paddle (405); an auxiliary cowl (406); a pitch member (407); an auxiliary pitch link (408); a pitch horn (409); an auxiliary pitch drive (410); an auxiliary hub (411);
the auxiliary tilting rotor (4) is installed on the fuselage (1) through an installation flange (402), one end of a tilting driver (401) is installed on the installation flange (402), the other end of the tilting rotor is installed on a tilting rocker arm (403), the middle part of the tilting rocker arm (403) is connected with a pin hole in the installation flange (402) through a pin shaft, a stator of an auxiliary blade driving motor (404) is installed on the other end of the tilting rotor, an auxiliary propeller hub (411) is installed on a rotor of the auxiliary blade driving motor (404), a variable pitch rocker arm (409) is installed on the auxiliary propeller hub (411), an auxiliary propeller blade (405) is installed on the variable pitch rocker arm (409), a variable pitch component (407) is connected on the auxiliary propeller driver (410), an auxiliary propeller changing connecting rod (408) is connected on the variable.
Further, the aircraft is characterized in that the rudder (5) comprises: a vertical fin control surface (501); a vertical tail driving mechanism (502); the vertical tail control surface (501) is connected to a vertical tail wing (104) of the fuselage (1) through a rotating pair, and the vertical tail driving mechanism (502) is connected to the vertical tail wing (104) and the vertical tail control surface (501) of the fuselage (1) through the rotating pair respectively.
Further, the aircraft is characterized in that the tail rudder (6) comprises: a horizontal tail rudder surface (601); a horizontal tail drive mechanism (602); the horizontal tail control surface (601) is connected to a horizontal tail (105) of the fuselage (1) through a revolute pair, and one end of the horizontal tail driving mechanism (602) is connected to the other end of the fuselage (1) and connected to the horizontal tail control surface (601).
Further, the aircraft is characterized in that the nose landing gear (7) comprises: a front tire (701); a front fork (702); a steering drive (703); an auxiliary shock absorber (704); an upper link (705); a secondary retraction drive (706); a lower beam (707); one end of the upper connecting rod (705) and one end of the auxiliary folding and unfolding driver (706) are hinged to the machine body (1), and the other end of the upper connecting rod is hinged to the auxiliary shock absorber (704); one end of the lower beam (707) is hinged to the machine body (1), the other end of the lower beam is hinged to a front fork (702), and the middle of the lower beam (707) is hinged to the other end of the auxiliary shock absorber (704); the shell of the steering drive (703) is fixedly connected to the lower beam (707), and the output end of the steering drive (703) is connected to the front fork (702); a front tire (701) is mounted on the front fork (702).
Further, the aircraft is characterized in that the rear landing gear (8) comprises: a rear tire (801); a tire link (802); a rear shock absorber (803); a first recovery link (804); a second recovery link (805); a wire rope (806); a rear retraction drive (807); a tension spring (808); a frame (809); a right-angle stand (810); a pulley (811); the tire connecting rod (802) is hinged with a rear shock absorber (803), a right-angle frame (810) and a rear tire (801); the other end of the rear shock absorber (803) is hinged to a right-angle frame (810); the right-angle frame (810) is hinged to the rack (809); the second recovery connecting rod (805) is hinged to the rack (809), a steel wire rope (806) and a tension spring (808) are connected to the second recovery connecting rod, and the first recovery connecting rod (804) is hinged to the second recovery connecting rod; the other end of the first recovery connecting rod (804) is hinged to the right-angle frame (810); the other end of the tension spring (808) is connected with the rack (809); the shell of the rear retractable driver (807) is fixed on the rack (809), and the action rod part of the rear retractable driver is connected with the steel wire rope (806); the steel wire rope (806) is connected to the second recovery connecting rod (805) through a pulley (811).
Further, the aircraft, wherein the flight control system further comprises at least one of a triple redundant flight control system; the flight control system is responsive to at least one of an onboard pilot flight control, a remote flight control, an autonomous flight control, and combinations thereof.
The utility model relates to an aircraft that can take off and land perpendicularly to flat flying of fixed wing mode. The aircraft comprises an aircraft body, tilting wings, a main tilting rotor, an auxiliary tilting rotor, a horizontal tail rudder, a vertical tail rudder, a front undercarriage, a rear undercarriage, a power battery system and a flight control system.
The aircraft body comprises a cabin, wings, a tail boom, a horizontal tail, a vertical tail, a second winglet, a seat, an instrument desk and a console, wherein the horizontal tail and the vertical tail are in T-shaped layout, and the aircraft body is preferably made of carbon fiber reinforced sandwich composite materials;
the tilting wings are slightly arranged at two ends of the wings of the fuselage, can rotate between vertical and horizontal forward directions under the action of the rotor driver, and are preferably made of carbon fiber reinforced sandwich composite materials;
the main tilting rotor wings are respectively arranged at the middle part of the tilting wing, and the left main tilting rotor wing and the right main tilting rotor wing are respectively provided with a blade, a fairing, a variable pitch mechanism, a rocker arm, a driving motor, a shield, a rotor wing supporting part, a rotor wing driver, a rotor wing fixing part and a right-angle coupler; the right-angle coupling drives the motor to synchronously rotate; during the vertical take-off and landing, forward flat flying and transition of the aircraft between the two states, the rotating planes of the paddle surfaces of the left main tilt rotor wing and the right main tilt rotor wing are as large as the same plane; the rotation directions of the left main tilting rotor wing and the right main tilting rotor wing are opposite.
The auxiliary tilting rotor wing is arranged at the tail part of the aircraft body and below the vertical tail wing; the auxiliary tilting rotor wing comprises a tilting driver, a mounting flange, a tilting rocker arm, a blade driving motor, a blade, a fairing, a variable pitch component, a variable pitch connecting rod, a variable pitch rocker arm, a variable pitch driver and a hub; during the vertical take-off and landing process and the transition period of the aircraft to horizontal forward flight, the rotation plane of the auxiliary tilt rotor is as large as being parallel to the rotation plane of the main tilt rotor; when the aircraft is in a forward flat flight state, the rotation axis of the auxiliary tilting rotor wing is horizontal and points to the rear of the aircraft, and the blade of the auxiliary tilting rotor wing is in a feathering state and is locked in the horizontal position.
The horizontal tail rudder is arranged on the machine body, and the horizontal tail rudder surface of the horizontal tail rudder is driven by a horizontal tail driving mechanism;
the vertical tail rudder is arranged on the machine body and driven by a vertical tail driving mechanism through a vertical tail rudder surface;
the nose landing gear is mounted on the front part of the fuselage;
the rear landing gear is arranged in the middle of the fuselage;
the power system consists of a battery system, an internal combustion engine generator set combination or at least one of the battery system, the internal combustion engine generator set combination and the internal combustion engine generator set combination, and at least comprises the battery system;
the flight control system receives various sensor information of an airborne pilot, a remote control, an automatic driving system and an aircraft, and the information is calculated by an airborne computer or a remote control computer to control the tilting wing tip, the main tilting rotor, the auxiliary tilting rotor, the tail-balancing rudder, the nose landing gear and the rear landing gear.
The utility model discloses the beneficial effect that can reach includes following arbitrary one:
1) the aircraft can vertically take off and land, hover and fly horizontally in a fixed wing mode;
2) the uniquely designed tilting wing tip and the main tilting rotor wing arranged on the tilting wing tip can enable the propeller slipstream to be always kept on the minimum area of the tilting wing tip during vertical take-off, landing and hovering, and the propeller slipstream cannot be made on a fixed wing surface, so that the take-off, landing and hovering efficiencies are high;
3) in a flat flying state, the main tilting rotor wing can tilt to play a role of an aileron;
4) the function of the variable pitch mechanism can lead the aircraft to adjust the pitch along with the airspeed when taking off, landing, hovering and flying, thereby leading the rotor wing to be kept at higher efficiency;
5) the aircraft is provided with the recoverable undercarriage, and can land in a sliding landing mode in an emergency state, so that the use safety is improved;
6) the main tilt rotor and the auxiliary tilt rotor are independent in driving system, so that the auxiliary tilt rotor can independently drive the aircraft to be in a flat flight state, and can complete a sliding and descending process, thereby increasing the use safety;
7) when the aircraft is in a flat flight state, the flight mode and the control mode of the aircraft are in a constant fixed wing mode, and the safety is high.
Drawings
For a more complete understanding of the features and advantages of the present invention, reference is now made to the detailed description taken in conjunction with the accompanying drawings, in which like reference numerals in the different figures refer to like parts, and in which:
fig. 1-4 are schematic diagrams of an aircraft (vertical takeoff and landing state) in accordance with an implementation of the present invention;
fig. 5-7 are schematic diagrams of an aircraft transitioning from vertical takeoff to forward flat flight in accordance with an embodiment of the present invention;
figures 8 to 11 are schematic illustrations of the fuselage;
figure 12 is a schematic view of a main tiltrotor rotor;
figure 13 is a schematic view of a pitch mechanism of a main tiltrotor;
figure 14 is a schematic view of rotor support components of a main tiltrotor;
figure 15 is a schematic view of a right angle coupling of a main tiltrotor;
figure 16 is a schematic view of a rotor drive for a main tiltrotor;
figure 17 is a schematic view of an auxiliary tiltrotor rotor;
FIG. 18 is a schematic view of a nose landing gear;
FIG. 19 is a rear landing gear schematic;
FIG. 20 is a schematic view of a horizontal tail rudder;
FIG. 21 is a schematic view of a vertical fin rudder;
fig. 22-25 are schematic views of an aircraft (level flight condition) according to an implementation of the present disclosure;
wherein:
1-fuselage, 2-tilt wing tip, 3-main tilt rotor, 4-auxiliary tilt rotor, 5-vertical tail rudder, 6-horizontal tail rudder, 7-front landing gear, 8-rear landing gear, 101-cabin, 102-wing, 103-tail boom, 104-vertical tail wing, 105-horizontal tail wing, 106-second winglet, 107-seat, 108-instrument desk, 109-console, 301-main blade, 302-main fairing, 303-pitch mechanism, 304-main drive motor, 305-shroud, 306-rotor support component, 307-rotor driver, 308-rotor fixing component, 309-right angle coupler, 30301-main hub, 30302-pitch rod, 30303-main rotor connecting rod, 30304-main rotor driver, 30305-blade rocker arm, 30401-motor rotor, 30402-motor stator, 30601-fixed shaft, 30602-connecting rod, 30701-shell, 30702-worm wheel, 30703-worm, 30704-worm rod end gear, 30705-motor end gear, 30706-motor, 30901-transmission shaft, 30902-driving gear, 30903-driven gear, 401-tilting driver, 402-mounting flange, 403-tilting rocker arm, 404-auxiliary driving motor, 405-auxiliary blade, 406-auxiliary fairing, 407-variable-pitch component, 408-auxiliary variable-pitch connecting rod, 409-variable-pitch rocker arm, 410-auxiliary variable-pitch driver, 411-auxiliary propeller hub, 501-vertical tail rudder surface, 502-vertical tail driving mechanism, 601-horizontal tail rudder surface, 602-horizontal tail driving mechanism, 701-front tire, 702-front fork, 703-steering drive, 704-front shock absorber, 705-upper connecting rod, 706-front retraction drive, 707-lower beam, 801-rear tire, 802-tire connecting rod, 803-rear shock absorber, 804-recovery connecting rod I, 805-recovery connecting rod II, 806-steel wire rope, 807-rear retraction drive, 808-tension spring, 809-frame, 810-right-angle frame and 811-pulley.
Detailed Description
The technical solution of the present invention is further described below by way of examples with reference to the accompanying drawings, but the scope of protection claimed is not limited thereto.
A fixed-wing aircraft having VTOL functionality, the aircraft comprising:
a fuselage (1); a tip (2) of a tilt wing, the tilt wing tip being mounted at both ends of a wing (102) of the fuselage, the tilt wing tip being rotatable between vertical and forward relative to the fuselage; the main tilt rotor wing (3) is provided with two rotor wings which are respectively arranged on the tilt wing tips (2), and the main tilt rotor wing (3) can rotate between a vertical lift force and a forward thrust force along with the tilt wing tips (2); an auxiliary tilt rotor (4) rotatably mounted below a vertical tail (104) of the fuselage, rotatable between a vertical lift and a forward thrust; the vertical tail rudder (5) is arranged at a vertical tail wing (104) of the machine body through a pin shaft and is driven by a vertical tail driving mechanism; the horizontal tail rudder (6) is arranged at a horizontal tail wing (105) of the fuselage through a pin shaft and is driven by a horizontal tail driving mechanism; a nose landing gear (7) mounted to the front of the fuselage (1); the rear landing gear (8) is mounted in the middle of the fuselage (1); the power system is composed of a battery system, an internal combustion engine generator set combination or at least one of the battery system, the internal combustion engine generator set combination and the internal combustion engine generator set combination, and at least comprises the battery system; a flight control system;
in the vertical lift state, the main tilt rotor (3) is approximately positioned on the same horizontal plane, and the rotation axis of the auxiliary tilt rotor (4) is parallel to the rotation axis of the main tilt rotor (3);
in the forward thrust state, the main tilting rotor (3) is located on the same vertical surface, the auxiliary tilting rotor (4) stops rotating, the blades are feathered by the variable pitch mechanism, and the two blades are in a horizontal state along the extension direction.
The aircraft being characterized in that the fuselage (1) comprises: a cabin (101) located in front of the fuselage (1); a wing (102) in the form of an upper monowing, located in an upper part of the fuselage (1); a tail boom (103) connecting the cabin (101) with a horizontal tail wing (105), a vertical tail wing (104); a vertical tail wing (104) which is positioned at the tail part of the fuselage (1); a horizontal tail wing (105) which is positioned at the tail part of the fuselage (1); a second winglet (106) positioned aft of a cabin (101) of a fuselage; a seat (107) located within the cabin (101); an instrument desk (108) located at the front inside the cabin (101); a console (109) located at the front inside the cabin (101).
Further, the aircraft is characterized in that the main tiltrotor (3) comprises: a main blade (301); a main fairing (302); the variable-pitch mechanism (303) comprises a main propeller hub (30301), a variable-pitch rod (30302), a main variable-pitch connecting rod (30303), a main variable-pitch driver (30304) and a blade rocker arm (30305), wherein the main variable-pitch driver (30304) drives the variable-pitch rod (30302), and the blade rocker arm (30305) is driven by the main variable-pitch connecting rod (30303); a main drive motor (304) comprising a motor rotor (30401), a motor stator (30402), a driver; a shield (305); a rotor support member (306); the rotor driver (307) comprises a shell (30701), a worm wheel (30702), a worm (30703), a worm end gear (30704), a motor end gear (30705) and a motor (30706), wherein the motor (30706) drives the motor end gear (30705), the motor end gear (30705) drives the worm rod end gear (30704), and the worm rod end gear (30704) drives the worm wheel (30702); a rotor securing member (308); the right-angle coupling (309) comprises a transmission shaft (30901), a driving gear (30902) and a driven gear (30903);
the main blade (301) is mounted on the pitch mechanism (303); the variable pitch mechanism (303) is arranged on a rotor (30401) of the driving motor; the driving motor stator (30402) is fixedly connected to the rotor wing supporting part; the rotor wing fixing part (308) is fixedly connected to the end part of the wing (102) of the fuselage; the shell (30701) of the rotor driver (307) is connected with the rotor fixing part (308), and the worm wheel (30702) of the rotor driver (307) is connected with the rotor supporting part (306);
the rotor wing supporting component (306) is fixedly connected with an inclined rotating wing tip (2);
the motor rotor (30401) of main rotor (3) that verts is connected with driving gear (30902) of right angle shaft coupling (309), driven gear (30903) is connected to driving gear (30902), transmission shaft (30901) is connected to driven gear (30903), the transmission shaft (30901) other end is connected with driven gear (30903) of the other end, driven gear (30903) of the other end is connected with driving gear (30902) of the other end, driving gear (30902) of the other end is connected with motor rotor (30401) of the main rotor (3) that verts of the other end.
Further, the aircraft is characterized in that the auxiliary tiltrotor (4) comprises: a tilt actuator (401); a mounting flange (402); a tilting rocker arm (403); an auxiliary blade drive motor (404); an auxiliary paddle (405); an auxiliary cowl (406); a pitch member (407); an auxiliary pitch link (408); a pitch horn (409); an auxiliary pitch drive (410); an auxiliary hub (411);
the auxiliary tilting rotor (4) is installed on the fuselage (1) through an installation flange (402), one end of a tilting driver (401) is installed on the installation flange (402), the other end of the tilting rotor is installed on a tilting rocker arm (403), the middle part of the tilting rocker arm (403) is connected with a pin hole in the installation flange (402) through a pin shaft, a stator of an auxiliary blade driving motor (404) is installed on the other end of the tilting rotor, an auxiliary propeller hub (411) is installed on a rotor of the auxiliary blade driving motor (404), a variable pitch rocker arm (409) is installed on the auxiliary propeller hub (411), an auxiliary propeller blade (405) is installed on the variable pitch rocker arm (409), a variable pitch component (407) is connected on the auxiliary propeller driver (410), an auxiliary propeller changing connecting rod (408) is connected on the variable.
Further, the aircraft is characterized in that the rudder (5) comprises: a vertical fin control surface (501); a vertical tail driving mechanism (502); the vertical tail control surface (501) is connected to a vertical tail wing (104) of the fuselage (1) through a rotating pair, and the vertical tail driving mechanism (502) is connected to the vertical tail wing (104) and the vertical tail control surface (501) of the fuselage (1) through the rotating pair respectively.
Further, the aircraft is characterized in that the tail rudder (6) comprises: a horizontal tail rudder surface (601); a horizontal tail drive mechanism (602); the horizontal tail control surface (601) is connected to a horizontal tail (105) of the fuselage (1) through a revolute pair, and one end of the horizontal tail driving mechanism (602) is connected to the other end of the fuselage (1) and connected to the horizontal tail control surface (601).
Further, the aircraft is characterized in that the nose landing gear (7) comprises: a front tire (701); a front fork (702); a steering drive (703); an auxiliary shock absorber (704); an upper link (705); a secondary retraction drive (706); a lower beam (707); one end of the upper connecting rod (705) and one end of the auxiliary folding and unfolding driver (706) are hinged to the machine body (1), and the other end of the upper connecting rod is hinged to the auxiliary shock absorber (704); one end of the lower beam (707) is hinged to the machine body (1), the other end of the lower beam is hinged to a front fork (702), and the middle of the lower beam (707) is hinged to the other end of the auxiliary shock absorber (704); the shell of the steering drive (703) is fixedly connected to the lower beam (707), and the output end of the steering drive (703) is connected to the front fork (702); an auxiliary tire (701) is mounted on the front fork (702).
Further, the aircraft is characterized in that the rear landing gear (8) comprises: a rear tire (801); a tire link (802); a rear shock absorber (803); a first recovery link (804); a second recovery link (805); a wire rope (806); a rear retraction drive (807); a tension spring (808); a frame (809); a right-angle stand (810); a pulley (811); the tire connecting rod (802) is hinged with a rear shock absorber (803), a right-angle frame (810) and a rear tire (801); the other end of the rear shock absorber (803) is hinged to a right-angle frame (810); the right-angle frame (810) is hinged to the rack (809); the second recovery connecting rod (805) is hinged to the rack (809), a steel wire rope (806) and a tension spring (808) are connected to the second recovery connecting rod, and the first recovery connecting rod (804) is hinged to the second recovery connecting rod; the other end of the first recovery connecting rod (804) is hinged to the right-angle frame (810); the other end of the tension spring (808) is connected with the rack (809); the shell of the rear retractable driver (807) is fixed on the rack (809), and the action rod part of the rear retractable driver is connected with the steel wire rope (806); the steel wire rope (806) is connected to the second recovery connecting rod (805) through a pulley (811).
Further, the aircraft, wherein the flight control system further comprises at least one of a triple redundant flight control system; the flight control system is responsive to at least one of an onboard pilot flight control, a remote flight control, an autonomous flight control, and combinations thereof.
Claims (9)
1. A fixed-wing aircraft having VTOL functionality, the aircraft comprising:
a fuselage (1); a tip (2) of a tilt wing, the tilt wing tip being mounted at both ends of a wing (102) of the fuselage, the tilt wing tip being rotatable between vertical and forward relative to the fuselage; the main tilt rotor wing (3) is provided with two rotor wings which are respectively arranged on the tilt wing tips (2), and the main tilt rotor wing (3) can rotate between a vertical lift force and a forward thrust force along with the tilt wing tips (2); an auxiliary tilt rotor (4) rotatably mounted below a vertical tail (104) of the fuselage, rotatable between a vertical lift and a forward thrust;
the vertical tail rudder (5) is arranged at a vertical tail wing (104) of the fuselage through a pin shaft and is driven by a vertical tail driving mechanism; the horizontal tail rudder (6) is arranged at a horizontal tail wing (105) of the fuselage through a pin shaft and is driven by a horizontal tail driving mechanism; a nose landing gear (7) mounted to the front of the fuselage (1); the rear landing gear (8) is mounted in the middle of the fuselage (1); the power system is composed of a battery system, an internal combustion engine generator set combination or at least one of the battery system, the internal combustion engine generator set combination and the internal combustion engine generator set combination, and at least comprises the battery system; a flight control system;
in said vertical lift condition, said main tiltrotors (3) are substantially in the same horizontal plane, and said auxiliary tiltrotors (4) are parallel to said main tiltrotors (3) rotation axis;
in the forward thrust state, the main tilt rotor (3) is approximately positioned on the same vertical plane, the auxiliary tilt rotor (4) stops rotating, the blades are feathered by the variable pitch mechanism, and the two blades are positioned in a horizontal state along the extension direction.
2. The aircraft according to claim 1, characterized in that said fuselage (1) comprises: a cabin (101) located in front of the fuselage (1); a wing (102) in the form of an upper monowing, located in an upper part of the fuselage (1); a tail boom (103) connecting the cabin (101) with a horizontal tail wing (105), a vertical tail wing (104); a vertical tail wing (104) which is positioned at the tail part of the fuselage (1); a horizontal tail wing (105) which is positioned at the tail part of the fuselage (1); a second winglet (106) positioned aft of a cabin (101) of a fuselage; a seat (107) located within the cabin (101); an instrument desk (108) located at the front inside the cabin (101); a console (109) located at the front inside the cabin (101).
3. The aircraft according to claim 1, characterized in that said main tiltrotor (3) comprises: a main blade (301); a main fairing (302); the variable-pitch mechanism (303) comprises a main propeller hub (30301), a variable-pitch rod (30302), a main variable-pitch connecting rod (30303), a main variable-pitch driver (30304) and a blade rocker arm (30305), wherein the main variable-pitch driver (30304) drives the variable-pitch rod (30302), and the blade rocker arm (30305) is driven by the main variable-pitch connecting rod (30303); a main drive motor (304) comprising a motor rotor (30401), a motor stator (30402), a driver; a shield (305); a rotor support member (306); the rotor driver (307) comprises a shell (30701), a worm wheel (30702), a worm (30703), a worm end gear (30704), a motor end gear (30705) and a motor (30706), wherein the motor (30706) drives the motor end gear (30705), the motor end gear (30705) drives the worm rod end gear (30704), and the worm rod end gear (30704) drives the worm wheel (30702); a rotor securing member (308); the right-angle coupling (309) comprises a transmission shaft (30901), a driving gear (30902) and a driven gear (30903);
the main blade (301) is mounted on the pitch mechanism (303); the variable pitch mechanism (303) is arranged on a rotor (30401) of the driving motor; the driving motor stator (30402) is fixedly connected to the rotor wing supporting part; the rotor wing fixing part (308) is fixedly connected to the end part of the wing (102) of the fuselage; the shell (30701) of the rotor driver (307) is connected with the rotor fixing part (308), and the worm wheel (30702) of the rotor driver (307) is connected with the rotor supporting part (306);
the rotor wing supporting component (306) is fixedly connected with an inclined rotating wing tip (2);
the motor rotor (30401) of main rotor (3) that verts is connected with driving gear (30902) of right angle shaft coupling (309), driven gear (30903) is connected to driving gear (30902), transmission shaft (30901) is connected to driven gear (30903), the transmission shaft (30901) other end is connected with driven gear (30903) of the other end, driven gear (30903) of the other end is connected with driving gear (30902) of the other end, driving gear (30902) of the other end is connected with motor rotor (30401) of the main rotor (3) that verts of the other end.
4. The aircraft according to claim 1, characterized in that said auxiliary tiltrotor (4) comprises: a tilt actuator (401); a mounting flange (402); a tilting rocker arm (403); an auxiliary blade drive motor (404); an auxiliary paddle (405); an auxiliary cowl (406); a pitch member (407); an auxiliary pitch link (408); a pitch horn (409); an auxiliary pitch drive (410); an auxiliary hub (411);
the auxiliary tilting rotor (4) is installed on the fuselage (1) through an installation flange (402), one end of a tilting driver (401) is installed on the installation flange (402), the other end of the tilting rotor is installed on a tilting rocker arm (403), the middle part of the tilting rocker arm (403) is connected with a pin hole in the installation flange (402) through a pin shaft, a stator of an auxiliary blade driving motor (404) is installed on the other end of the tilting rotor, an auxiliary propeller hub (411) is installed on a rotor of the auxiliary blade driving motor (404), a variable pitch rocker arm (409) is installed on the auxiliary propeller hub (411), an auxiliary propeller blade (405) is installed on the variable pitch rocker arm (409), a variable pitch component (407) is connected on the auxiliary propeller driver (410), an auxiliary propeller changing connecting rod (408) is connected on the variable.
5. The aircraft of claim 1, characterized in that the vertical rudder (5) comprises: a vertical fin control surface (501); a vertical tail driving mechanism (502); the vertical tail control surface (501) is connected to a vertical tail wing (104) of the fuselage (1) through a rotating pair, and the vertical tail driving mechanism (502) is connected to the vertical tail wing (104) and the vertical tail control surface (501) of the fuselage (1) through the rotating pair respectively.
6. The aircraft of claim 1, characterized in that the tail rudder (6) comprises: a horizontal tail rudder surface (601); a horizontal tail drive mechanism (602); the horizontal tail control surface (601) is connected to a horizontal tail (105) of the fuselage (1) through a revolute pair, and one end of the horizontal tail driving mechanism (602) is connected to the other end of the fuselage (1) and connected to the horizontal tail control surface (601).
7. The aircraft according to claim 1, characterized in that said nose landing gear (7) comprises: a front tire (701); a front fork (702); a steering drive (703); an auxiliary shock absorber (704); an upper link (705); a secondary retraction drive (706); a lower beam (707); one end of the upper connecting rod (705) and one end of the auxiliary folding and unfolding driver (706) are hinged to the machine body (1), and the other end of the upper connecting rod is hinged to the auxiliary shock absorber (704); one end of the lower beam (707) is hinged to the machine body (1), the other end of the lower beam is hinged to a front fork (702), and the middle of the lower beam (707) is hinged to the other end of the auxiliary shock absorber (704); the shell of the steering drive (703) is fixedly connected to the lower beam (707), and the output end of the steering drive (703) is connected to the front fork (702); a front tire (701) is mounted on the front fork (702).
8. The aircraft of claim 1, characterized in that the rear landing gear (8) comprises: a rear tire (801); a tire link (802); a rear shock absorber (803); a first recovery link (804); a second recovery link (805); a wire rope (806); a rear retraction drive (807); a tension spring (808); a frame (809); a right-angle stand (810); a pulley (811); the tire connecting rod (802) is hinged with a rear shock absorber (803), a right-angle frame (810) and a rear tire (801); the other end of the rear shock absorber (803) is hinged to a right-angle frame (810); the right-angle frame (810) is hinged to the rack (809); the second recovery connecting rod (805) is hinged to the rack (809), a steel wire rope (806) and a tension spring (808) are connected to the second recovery connecting rod, and the first recovery connecting rod (804) is hinged to the second recovery connecting rod; the other end of the first recovery connecting rod (804) is hinged to the right-angle frame (810); the other end of the tension spring (808) is connected with the rack (809); the shell of the rear retractable driver (807) is fixed on the rack (809), and the action rod part of the rear retractable driver is connected with the steel wire rope (806); the steel wire rope (806) is connected to the second recovery connecting rod (805) through a pulley (811).
9. The aircraft of claim 1 wherein the flight control system further comprises at least one of a triple redundant flight control system; the flight control system is responsive to at least one of an onboard pilot flight control, a remote flight control, an autonomous flight control, and combinations thereof.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020468232.0U CN213200097U (en) | 2020-04-02 | 2020-04-02 | Fixed wing aircraft with vertical take-off and landing function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020468232.0U CN213200097U (en) | 2020-04-02 | 2020-04-02 | Fixed wing aircraft with vertical take-off and landing function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213200097U true CN213200097U (en) | 2021-05-14 |
Family
ID=75817638
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020468232.0U Active CN213200097U (en) | 2020-04-02 | 2020-04-02 | Fixed wing aircraft with vertical take-off and landing function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213200097U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117075527A (en) * | 2023-10-17 | 2023-11-17 | 成都天域航通科技有限公司 | Flight control system of large fixed wing freight unmanned aerial vehicle |
-
2020
- 2020-04-02 CN CN202020468232.0U patent/CN213200097U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117075527A (en) * | 2023-10-17 | 2023-11-17 | 成都天域航通科技有限公司 | Flight control system of large fixed wing freight unmanned aerial vehicle |
| CN117075527B (en) * | 2023-10-17 | 2023-12-26 | 成都天域航通科技有限公司 | Flight control system of large fixed wing freight unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11634222B2 (en) | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system | |
| EP3296202B1 (en) | Wing extension winglets for tiltrotor aircraft | |
| CN101559832B (en) | Fast hybrid helicopter with large range | |
| WO2019211875A1 (en) | Hybrid vertical takeoff and landing (vtol) aircraft with vehicle assist | |
| CN111332465B (en) | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode | |
| CN108639328A (en) | A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone | |
| KR20090054027A (en) | Taking off and landing airplane using variable rotary wings | |
| KR20100026130A (en) | Taking off and landing airplane using variable rotary wings | |
| US20230086655A1 (en) | Variable-sweep wing aerial vehicle with vtol capabilites | |
| CN113525679A (en) | Electric vertical take-off and landing aircraft structure and working method thereof | |
| CN115214881A (en) | Electric tilt rotor aircraft | |
| CN213200097U (en) | Fixed wing aircraft with vertical take-off and landing function | |
| CN111942581B (en) | Distributed lift force duck-type layout vertical take-off and landing unmanned aerial vehicle and control method | |
| CN110861770A (en) | Unmanned rotation gyroplane | |
| CN111762314A (en) | Rotor aircraft capable of vertically taking off and landing | |
| CN111532426A (en) | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout | |
| US8944366B2 (en) | Rotorcraft empennage mounting system | |
| CN115303479A (en) | Multi-rotor combined helicopter | |
| US20120111997A1 (en) | Rotorcraft empennage | |
| CN113942636A (en) | Composite rotor craft | |
| CN113002770A (en) | Rotor craft capable of attaching wings to fuselage | |
| RU2412869C1 (en) | Universal "push-pull" aircraft | |
| CN112009677A (en) | Variable-diameter unmanned tilt rotorcraft | |
| CN211253005U (en) | Unmanned rotation gyroplane | |
| CN219192548U (en) | V-tail single-push electric vertical take-off and landing composite wing aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220411 Address after: 054001 room 1003, unit 2, building 16, reconstruction of beiguozhuang old village, southwest corner of the intersection of Quanbei street and Guihua Ping'an Road, Xiangdu District, Xingtai City, Hebei Province Patentee after: Mate Technology (Xingtai) Co.,Ltd. Address before: 054402 No.100, Liangzhuang village, haoqiao Town, Nanhe County, Xingtai City, Hebei Province Patentee before: Xin Qiuling |