CN114313251B - Combined type aircraft active tilting structure and aircraft - Google Patents
Combined type aircraft active tilting structure and aircraft Download PDFInfo
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- CN114313251B CN114313251B CN202210201229.6A CN202210201229A CN114313251B CN 114313251 B CN114313251 B CN 114313251B CN 202210201229 A CN202210201229 A CN 202210201229A CN 114313251 B CN114313251 B CN 114313251B
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Abstract
The invention discloses an active tilting structure of a combined aircraft and the aircraft, which comprise a transmission part, a transmission wheel, a tilting shaft, a connecting piece and a rotor wing assembly, wherein the transmission wheel is arranged on the transmission part; the two ends of the transmission piece are rotatably connected with the transmission wheels; the circle center of the driving wheel is fixedly connected with one end of the tilting shaft; the other end of the tilting shaft is fixedly connected with the connecting piece, and a plurality of rotor wing assemblies are fixedly mounted on one side of the connecting piece; two connecting pieces at the two ends of the transmission piece are in a lever relationship, and when the rotating speeds of the rotor wing assemblies at the two ends of the transmission piece are different, the two connecting pieces rotate in the same direction. Not only realized initiatively verting, reduced the rotor subassembly moreover, simplified the aircraft structure for the whole occupation of land size of aircraft reduces.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a combined type aircraft active tilting structure and an aircraft.
Background
The statements in this section merely provide background information related to the present disclosure and may not constitute prior art.
The existing aircraft tilting structure consists of a steering engine, a screw rod, hydraulic pressure and other devices, and has more parts, so that the weight and the cost of the aircraft are increased; in addition, once the aircraft tilting structure fails, the aircraft can be out of control; moreover, the rotor wing subassembly that current aircraft initiatively verts the structure is more for the whole occupation of land size of aircraft is great.
Disclosure of Invention
In order to solve the problems, the invention provides the combined type aircraft active tilting structure and the aircraft, which not only realize active tilting, but also reduce rotor wing assemblies, drive mechanisms such as a steering engine and the like, simplify the structure of the aircraft, and reduce the overall occupied space of the aircraft.
In order to achieve the purpose, the invention adopts the following technical scheme:
the first aspect of the invention provides an active tilting structure of a combined aircraft, which comprises a transmission part, a transmission wheel, a tilting shaft, a connecting piece and a rotor wing assembly;
the two ends of the transmission piece are rotatably connected with the transmission wheels;
the circle center of the driving wheel is fixedly connected with one end of the tilting shaft;
the other end of the tilting shaft is fixedly connected with the connecting piece, and a plurality of rotor wing assemblies are fixedly arranged on one side of the connecting piece; when the two connecting pieces do not tilt, the two connecting pieces at the two ends of the transmission piece and the rotor wing assembly fixedly arranged on the two connecting pieces are symmetrical about the vertical plane of the transmission piece;
two connecting pieces at two ends of the transmission piece are in a lever relationship, and when the pulling force between the rotor wing assemblies at two ends of the transmission piece is different, the two connecting pieces rotate in the same direction.
In a second aspect, a vertical take-off and landing aircraft is provided, which includes a cabin, and the combined aircraft active tilting structure of the first aspect connected to the cabin.
Compared with the prior art, the invention has the beneficial effects that:
the active tilting structure of the combined aircraft not only realizes active tilting through the tension difference between the rotor wing groups at the two ends of the transmission part, but also does not need driving mechanisms such as a steering engine and the like during tilting, and due to the adoption of the lever structure, the rotor wing assemblies are reduced, the aircraft structure is simplified, and the overall occupied area of the aircraft is reduced.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the application and, together with the description, serve to explain the application and are not intended to limit the application.
FIG. 1 is a schematic view of an active tilting structure of a combined aircraft with a connecting rod as a transmission member according to an embodiment of the present disclosure;
FIG. 2 is a schematic view of an active roll configuration of a combined aircraft with a belt transmission according to one disclosed embodiment;
fig. 3 is a schematic view of the active tilting structure of the combined aircraft disclosed in the second embodiment;
FIG. 4 is a schematic view of an active tilting structure of the third disclosed embodiment of the combined aircraft;
FIG. 5 is a schematic view of the VTOL aerial vehicle disclosed in the fourth embodiment;
FIG. 6 is a schematic illustration of the VTOL aerial vehicle disclosed in example five;
FIG. 7 is a schematic view of a VTOL aerial vehicle of the sixth disclosed embodiment.
Wherein: 1. the aircraft comprises a supporting mechanism, 2, a tilting shaft, 3, a swing arm, 4, a rotor wing assembly, 5, a driving wheel, 6, a connecting rod, 7, a brake, 8, an engine room, 9, a sheet wing, 10, a rectangular wing, 11 and a belt.
Detailed Description
The invention is further described with reference to the following figures and examples.
It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the disclosure. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an", and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
In the present invention, terms such as "fixedly connected", "connected", and the like are to be understood in a broad sense, and mean either a fixed connection or an integrally connected or detachable connection; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be determined according to specific situations by persons skilled in the relevant scientific or technical field, and are not to be construed as limiting the present invention.
Example one
In the embodiment, a combined type aircraft active tilting structure is disclosed, which comprises a transmission part, a transmission wheel, a tilting shaft, a connecting piece, a rotor wing assembly, a brake and a supporting mechanism.
Both ends of the transmission piece are rotatably connected with transmission wheels; the centre of a circle of drive wheel and the one end fixed connection of tilting shaft, the axis of tilting shaft is perpendicular with the wheel face of drive wheel. The other end of the tilting shaft is fixedly connected with the connecting piece. When two connecting pieces do not incline, two connecting pieces at the two ends of the transmission piece and the rotor assemblies fixedly installed on the two connecting pieces are symmetrical about the vertical plane of the transmission piece, and the connecting pieces are far away from one side of the vertical plane of the transmission piece, and a plurality of rotor assemblies are fixedly installed on one side of the vertical plane of the transmission piece. Two connecting pieces at the two ends of the transmission piece are in lever relation, and when the tension between the rotor wing assemblies at the two ends of the transmission piece is different, the two connecting pieces rotate in the same direction (namely clockwise rotation or anticlockwise rotation occurs around the axis of the tilting shaft at the same time).
The shaft hole has all been seted up at supporting mechanism's both ends, and the centre of a circle fixed connection of shaft hole and drive wheel is passed to the one end of tilting shaft.
The both ends of supporting mechanism all fixed mounting have the brake, and the brake sets up in one side of drive wheel, and two brake pads of the brake of every one end of supporting mechanism all set up on the two sides of drive wheel for pin drive wheel or unblock drive wheel. Specifically, the brakes at the two ends of the supporting mechanism are arranged on one side of the driving wheel at the same end of the supporting mechanism.
The rotor wing assembly is a ducted rotor wing assembly, an air jet rotor wing assembly or a motor and a propeller. When the rotor subassembly adds the screw for the motor, the rotor subassembly includes the motor and sets up the screw on the motor follows the output shaft. The motor of rotor subassembly is connected with the electricity accent, and electricity is transferred and is connected with flying the accuse, and electricity is transferred and is used for driving motor, flies the accuse and is used for controlling motor speed or control rotor subassembly pitch. The brake is connected with an independent driving mechanism which can be a servo motor, and the flight control is connected with the driving mechanism and used for controlling the brake to lock the driving wheel or unlock the driving wheel.
Each end of the transmission part comprises a plurality of rotor wing assemblies, each rotor wing assembly of each end of the transmission part forms a rotor wing group, and the two ends of the transmission part comprise a rotor wing group.
Specifically, the brake is a hydraulic brake.
The active tilting structure of the combined aircraft disclosed in this embodiment, as shown in fig. 1 and fig. 2, includes a supporting mechanism 1, two tilting shafts 2, two connecting members, four rotor assemblies 4, two driving wheels 5, a driving member, and two brakes 7.
As an embodiment, as shown in fig. 1, the transmission member is a connecting rod 6, the transmission wheel 5 is a turntable, and the two turntables are respectively and rotatably connected with two ends of the connecting rod 6 at the same position of the edge, so as to realize the connection and mutual transmission of the two turntables. Specifically, the shaft holes have been seted up at the edge of two carousels, and the shaft hole of two carousels is seted up in same position, and the shaft hole has also been seted up at the both ends of connecting rod 6, and the pivot passes shaft hole on the carousel and the shaft hole of connecting rod 6, makes the carousel pass through pivot connection connecting rod 6. The length of the connecting rod 6 is d +2r, wherein d is the closest distance between the two turntables, and r is the radius of the transmission wheel 5.
As an embodiment, as shown in fig. 2, the transmission component is a belt 11, the transmission wheel 5 is a belt pulley, the two belt pulleys are in transmission connection through the belt 11, specifically, two ends of the belt 11 are respectively sleeved on outer surfaces of the two belt pulleys, the outer surface of the belt pulley is provided with a plurality of teeth, the inner surface of the belt 11 is provided with a plurality of teeth, and the teeth on the outer surface of the belt pulley are engaged with the teeth on the inner surface of the belt 11, so that the connection and the transmission of the two belt pulleys are realized.
The shaft hole has all been seted up at the both ends of supporting mechanism 1, and the centre of a circle fixed connection of shaft hole on the supporting mechanism 1 and drive wheel 5 is passed to the one end of tilting shaft 2. Specifically, one end of each of the two tilting shafts 2 respectively penetrates through the shaft holes at the two ends of the supporting mechanism 1 and is fixedly connected with the circle centers of the two driving wheels 5.
Both ends of the supporting mechanism 1 are fixedly provided with brakes 7, and the brakes 7 are arranged on one side of the driving wheel 5 and used for locking or unlocking the driving wheel.
The axis of the supporting mechanism 1, the axis of the tilting shaft 2 and the circle center connecting line of the two driving wheels 5 are positioned on the same plane.
The other end and the connecting piece fixed connection of the axle that verts when two connecting pieces do not take place to vert, two connecting pieces at driving medium both ends and last fixed mounting's rotor subassembly are about the well vertical plane symmetry of driving medium, and the connecting piece is keeping away from one side fixed mounting of the well vertical plane of driving medium has a plurality of rotor subassemblies. Specifically, as shown in fig. 1 and 2, the connecting member includes a swing arm 3 and a motor base. The other end of the tilting shaft 2 is fixedly connected with one end of the swing arm 3, when the two connecting pieces do not tilt, the end of the swing arm 3 is close to the vertical plane of the transmission piece, the swing arm 3 and the tilting shaft 2 form an angle, and the angle between the swing arm 3 and the tilting shaft 2 is equal to 90 degrees or more than 90 degrees; the other end of swing arm 3 and the middle part fixed connection of motor cabinet, when two connecting pieces do not take place to vert, the well vertical plane of driving medium is kept away from to the other end of swing arm 3, and rotor assembly of equal fixed mounting in two ends of motor cabinet, it is specific, the motor of rotor assembly of equal fixed mounting in two ends of motor cabinet. The axis of swing arm 3 and the axis of tilting shaft 2 are located the coplanar, and the axis of motor cabinet is perpendicular with this plane. The axis of rotor subassembly with on the axis of motor cabinet.
In fig. 1 and 2, when one swing arm 3 of the two connecting members is lifted by applying a force to the other swing arm 3, the swing arm 3 of the other connecting member is lowered, or if the upward lifting force of one swing arm 3 is greater than that of the other swing arm 3, the swing arm 3 with a large upward lifting force is raised, and the other swing arm 3 is lowered.
Two connecting pieces at driving medium both ends and go up fixed mounting's rotor subassembly opposite direction setting, two connecting pieces at driving medium both ends are the relation for each other for the lever, the fulcrum is the axle 2 that verts that connects separately, pulling force between the rotor subassembly 4 at driving medium both ends is different, each other is the connecting piece of the big rotor subassembly 4 of connecting pulling force in two connecting pieces of lever receives the pulling force effect to rotate, another connecting piece syntropy rotates, syntropy rotation takes place for two connecting pieces, wherein, drive wheel 5 and driving medium play driven effect. The difference in tension between the rotor assemblies 4 at the two ends of the transmission member can be achieved by: keeping the pitch between the rotor wing groups at the two ends of the transmission part unchanged, and adjusting the rotating speed between the rotor wing groups at the two ends of the transmission part to be different; or the rotating speed between the rotor wing groups at the two ends of the transmission part is unchanged, and the blade pitches between the rotor wing groups at the two ends of the transmission part are adjusted to be different.
The rotating speed or the propeller pitch of the rotor wing assemblies 4 in the two rotor wing groups at the two ends of the transmission part are controlled, so that a rotating speed difference or a propeller pitch difference is formed between the two rotor wing groups at the two ends of the transmission part, a tension difference is generated, and the tilting control of the two rotor wing groups is realized. When the rotating speeds or the blade pitches of all the rotor wing assemblies at the two ends of the transmission part are the same, the pulling forces are the same, and the two rotor wing assemblies do not incline; the rotational speed or the pitch of all rotor subassemblies 4 in the rotor group of the one end of driving medium, be higher than the rotational speed or the pitch of all rotor subassemblies 4 in the rotor of the other end of driving medium, the pulling force of the rotor group of the high one end of rotational speed or the big one end of pitch is greater than the pulling force of the rotor group of the other end, the rotor group of the high one end of rotational speed or the big one end of pitch produces the pulling force to the connecting piece, the pulling force is transmitted to drive wheel 5 through tilting shaft 2, the connecting piece of the high one end of rotational speed or the big one end of pitch, tilting shaft 2 and drive wheel 5 syntropy rotate, the drive wheel 5 of the high one end of rotational speed or the big one end of pitch rotates and drives the drive wheel 5 syntropy of the other end through the driving medium, the drive wheel 5 of the other end rotates and drives tilting shaft 2 and connecting piece syntropy rotation of homodromour at the same end, finally, the connecting piece syntropy rotation at the driving medium both ends, make two rotor groups tilt forward or backward jointly. When verting to certain gesture and need not vert, it can to fly the same of accuse control driving medium both ends rotor group rotational speed or pitch.
Wherein, the brake is arranged in that when certain rotor group in the structure that verts is initiatively faced at the combination formula aircraft meets the air current alone and disturbs, pins the drive wheel at both ends, and then pins and vert the structure. When a certain rotor group of the aircraft is affected by airflow independently, and the aircraft ascends or sinks along the side where the rotor group is located, the tilting mechanism must be locked to prevent tilting, then each rotor assembly in the rotor group adjusts the rotating speed or the pitch, and the rotor group is pulled upwards or pressed downwards along the side where the rotor group is located, so that the attitude of the aircraft is corrected. The brake is also used for locking the driving wheels when the aircraft encounters airflow interference, and when the aircraft encounters airflow interference, the flight control sends an instruction to the electromagnetic driving mechanism to drive the four brakes to lock the driving wheels instantly, and meanwhile, the corresponding rotor wing assemblies are adjusted to increase or reduce the rotating speed or the propeller pitch to correct the attitude of the aircraft.
When a rotor assembly in a certain rotor group breaks down, other rotor assemblies in the rotor group continue to work, and the rotating speed or the propeller pitch of other rotor assemblies in the rotor group is controlled, so that the tension of the rotor group after the fault is unchanged compared with that before the fault.
The combined type aircraft active tilting structure of the embodiment realizes active tilting by the rotation speed difference or pitch difference between the rotor wing groups at the two ends of the transmission part, does not need driving mechanisms such as a steering engine when tilting, reduces the rotor wing assemblies, simplifies the aircraft structure and reduces the overall occupied space size of the aircraft.
Example two
In the embodiment, an active tilting structure of a combined aircraft is disclosed, and the difference from the first embodiment is that a connecting piece does not adopt a swing arm and a motor base, but adopts a sheet-shaped wing.
The active tilting structure of the combined aircraft disclosed in the embodiment, as shown in fig. 3, includes a supporting mechanism 1, two tilting shafts 2, two connecting members, four rotor assemblies 4, two driving wheels 5, a driving member, and two brakes 7.
The other end and the connecting piece fixed connection of the axle that verts when two connecting pieces do not take place to vert, two connecting pieces at driving medium both ends and last fixed mounting's rotor subassembly are about the well vertical plane symmetry of driving medium, and the connecting piece is keeping away from one side fixed mounting of the well vertical plane of driving medium has a plurality of rotor subassemblies. Specifically, as shown in fig. 3, the connection member is a flap wing 9. The other end of the tilting shaft 2 is fixedly connected with one end face of the sheet wing 9, the end face of the sheet wing 9 is perpendicular to the tilting shaft 2, and the middle longitudinal section of the sheet wing 9 is parallel to the axis of the tilting shaft 2; a plurality of wing ribs are arranged in the sheet-shaped wing 9, wherein at least two wing ribs extend out of the wing surface of the sheet-shaped wing 9, the wing rib of each wing surface extending out of the sheet-shaped wing 9 is fixedly connected with one rotor wing assembly 4, and the central axis of each rotor wing assembly is parallel to the middle longitudinal section of the sheet-shaped wing 9. Two sets of rotor assemblies in front and back of this embodiment combination formula initiative tilting structure are opposite direction setting, and when the vertical upwards of slice wing, a set of setting is in the left side of slice wing, and another group just sets up the right side at the slice wing. That is, when the two connecting members are not tilted, the plate-like wing 9 extends at least two wing ribs in parallel on the wing surface on the side far from the vertical plane of the transmission member, and is fixedly connected with the rotor assembly 4. In fig. 3, when one of the two linking members is lifted upwards by a force applied by the other linking member (here, the lifting upwards means that the side of the other linking member where the rotor assembly 4 is installed is rotated upwards), the other linking member is lowered downwards by the other linking member 9, or if the lifting force of one linking member 9 is greater than that of the other linking member 9, the linking member 9 with a large lifting force is raised upwards and the other linking member 9 is lowered.
Other structures in this embodiment are the same as those in the first embodiment, and are not described in detail here.
EXAMPLE III
In the embodiment, an active tilting structure of a combined aircraft is disclosed, and the difference from the second embodiment is that a connecting piece does not adopt a sheet-shaped wing, but adopts a rectangular wing formed by combining two sheet-shaped wings and a supporting sheet.
The active tilting structure of the combined aircraft disclosed in this embodiment, as shown in fig. 4, includes a supporting mechanism 1, two tilting shafts 2, two connecting members, four rotor assemblies 4, two driving wheels 5, a driving member, and two brakes 7.
The other end and the connecting piece fixed connection of the axle that verts when two connecting pieces do not take place to vert, two connecting pieces at driving medium both ends and last fixed mounting's rotor subassembly are about the well vertical plane symmetry of driving medium, and the connecting piece is keeping away from one side fixed mounting of the well vertical plane of driving medium has a plurality of rotor subassemblies. Specifically, as shown in fig. 4, the connecting member is a rectangular wing 10, the rectangular wing 10 includes two sheet wings and two supporting sheets, the two sheet wings are parallel to each other, the two supporting sheets are parallel to each other, two ends of the two sheet wings are both connected to end portions of the supporting sheets, and two ends of the two supporting sheets are both fixedly connected to end portions of the sheet wings. The other end of the tilting shaft 2 is fixedly connected with the middle of a supporting sheet of the rectangular wing 10, a plurality of rotor assemblies are arranged on the sheet wing connected with one end of the supporting sheet in parallel, and specifically, when the two connecting pieces do not tilt, a plurality of rotor assemblies are arranged on the sheet wing connected with one end, far away from the vertical plane of the transmission piece, of the supporting sheet in parallel. The support sheet is vertical to the axis of the tilting shaft 2, and the middle longitudinal section of the rectangular wing 10 is parallel to the axis of the tilting shaft 2. The central axis of the rotor assembly is parallel to the median longitudinal section of the rectangular wing 10. In fig. 4, two rectangular wings 10 are lever-coupled with each other, and when the wing with the rotor assembly mounted thereon in one rectangular wing 10 exerts a force, the wing with the rotor assembly mounted thereon in the other rectangular wing 10 is lifted upward, and then is lowered.
Other structures in this embodiment are the same as those in the embodiment, and are not described in detail here.
Example four
In this embodiment, a vtol aircraft is disclosed that includes a nacelle and a combined aircraft active tilter structure coupled to the nacelle.
The through-hole has been seted up to the equal symmetry in both sides at the front portion and the rear portion in cabin, and driving medium, drive wheel, brake and supporting mechanism all set up inside the cabin, and connecting piece and rotor subassembly all set up in the cabin outside, and the axle that verts runs through the through-hole.
The embodiment of the vertical take-off and landing aircraft comprises a cabin 8 and an embodiment of the combined aircraft active tilting structure connected with the cabin 8, as shown in fig. 5.
The four rotor groups of the aircraft disclosed by the embodiment do not tilt when the rotating speeds or the pitches are the same; when the speed is accelerated to a certain speed, the flying object flies off the ground; the rotating speed difference or the pitch difference of the four rotor wing groups is adjusted, so that when all the rotor wing groups of the two active tilting structures on the two sides of the aircraft tilt forwards, the aircraft flies forwards, and when all the rotor wing groups tilt backwards, the aircraft flies backwards; when the tilting angle of the right rotor wing group of the aircraft is larger than the left tilting angle and the rotating speed or the propeller pitch of the two right rotor wing groups is larger than the rotating speed or the propeller pitch of the two left rotor wing groups, the aircraft turns to the left, and otherwise turns to the right; when climbing, the two tilting structures on the left side and the right side of the aircraft tilt forwards together, and the aircraft climbs upwards in a horizontal posture; when the aircraft encounters airflow interference, the flight control sends an instruction to the electromagnetic driving mechanism to drive four brakes to lock the driving wheels instantly, and meanwhile, the corresponding rotor wing assemblies are adjusted to increase or reduce the rotating speed or the propeller pitch to correct the attitude of the aircraft.
EXAMPLE five
In the embodiment, a vertical take-off and landing aircraft is disclosed, which is different from the fourth embodiment in that:
the vtol aircraft disclosed in the present embodiment, as shown in fig. 6, includes a cabin 8, and an active tilt structure of a combined aircraft disclosed in the second embodiment, which is connected to the cabin 8.
Four slice wings 9 are located the left and right sides at 8 fronts in cabin and rear portion respectively, and two slice wings 9 around 8 left sides in cabin and the front and back pivot 2 fixed connection that incline of the structure of inclining initiatively on left side, two slice wings 9 around 8 right sides in cabin and the front and back pivot 2 of inclining initiatively on right side incline the structure of inclining also be fixed connection, and the connection relation is the terminal surface of the perpendicular slice wing 9 of axle 2 that inclines, and 2 rotations of the axle of inclining can drive rotor subassembly 4 and slice wing 9 and incline jointly. Rotor assemblies 4 mounted side-by-side on each of the laminar wings 9 of this embodiment are in back-up relation to each other. After the integral connection is completed, the flaky wings and the engine room are combined into an engine body with an I-shaped structure, and the flaky wings 9 on the left side and the right side can actively tilt through the tension difference of the front rotor wing group and the rear rotor wing group.
The four rotor wing groups of the aircraft do not tilt when the rotating speeds or the blade pitches are the same; accelerating to a certain speed and flying off the ground; the rotating speed difference or the pitch difference of the four rotor wing groups is adjusted, so that the two rotor wing groups of the active tilting structure tilt forwards gradually to drive the four flaky wings to tilt forwards gradually, the aircraft flies forwards, the flaky wings tilt forwards to be approximately horizontal after flying to a certain speed, the lift force is mainly provided by the flaky wings, the rotor wing groups mainly provide tension force, the aircraft flies backwards when tilting backwards together, the speed of the aircraft in the embodiment can be controlled not to be too high when the aircraft flies backwards, and the backward flying is only used for adjusting the landing position when taking off and landing; when the front fly turns to the left, the rotating speed or the propeller pitch of the front rotor wing group on the right side is increased, the pulling force is increased, the rotating speed or the propeller pitch of the rear rotor wing group is reduced, the pulling force is reduced, the amplitude of reduction is the same as the amplitude of increase, the tilting angle of the right active tilting structure is driven to be reduced, the front tilting angle of the front and rear sheet wings on the right side is driven to be reduced, the attack angle is increased, the rotating speed or the propeller pitch of the rear rotor wing group on the left side is increased, the pulling force is increased, the rotating speed or the propeller pitch of the front rotor wing group is reduced, the pulling force is reduced, the amplitude of reduction is the same as the amplitude of increase, the front tilting angle of the left active tilting structure is driven to be increased, the front tilting angle of the front and rear sheet wings on the left side is driven to be increased, the attack angle is reduced, the pulling force of the two rotor wing groups is reduced, and the aircraft turns to the left under the action of the difference of the lifting force and the difference of the left side, when turning to the right, the opposite action is executed; when the aircraft ascends, the front and rear sheet wings are controlled to jointly increase the attack angle and the tension of the four rotor wing groups, the aircraft ascends in the posture of a horizontal machine body, and when the aircraft descends, the attack angle and the tension of the four rotor wing groups are reduced, and the aircraft descends in the posture of the horizontal machine body; when the aircraft encounters airflow interference, the flight control sends an instruction to the electromagnetic driving mechanism to drive the four hydraulic brakes to lock the driving wheels instantly, and meanwhile, the corresponding rotor wing assemblies are adjusted to increase or reduce the rotating speed or the propeller pitch to correct the attitude of the aircraft.
The vertical take-off and landing aircraft disclosed by the embodiment can be vertically taken off and landed, the rotor wing group is reduced, the aircraft is simple in structure, the overall occupied area of the aircraft is reduced, driving mechanisms such as steering engines are not needed during tilting, active tilting is realized by the rotation speed difference or the pitch difference of the two rotor wing assemblies, the flaky wings capable of tilting are increased, when the aircraft takes off and accelerates to a certain speed gradually, the rotor wing group mainly provides pulling force and control direction, the lifting force is mainly provided by the flaky wings, the voyage and the voyage are greatly improved, the flaky wings can tilt and simultaneously play the role of a control surface, and the flight can be flexibly controlled.
EXAMPLE six
In the embodiment, a vertical take-off and landing aircraft is disclosed, which is different from the fourth embodiment in that:
the vtol aircraft disclosed in the present embodiment, as shown in fig. 7, includes a nacelle 8, and an active tilting structure of a combined aircraft disclosed in the third embodiment, which is connected to the nacelle 8.
The four rectangular wings 10 are symmetrically installed at the front part and the rear part of the cabin 8 respectively, the middle part of a supporting sheet close to the cabin 8 in each rectangular wing 10 is fixedly installed with a tilting shaft of an active tilting structure, the supporting sheet close to the cabin 8 in each rectangular wing 10 is equivalent to a swing arm of the active tilting structure, two ends of the supporting sheet are fixedly connected with two layers of sheet wings, and when the two connecting pieces do not tilt, a rotor wing assembly is fixedly installed on the sheet wing far away from the vertical plane of a transmission piece. After the integral connection is completed, the rectangular wings and the engine room form an engine body in an I-shaped structure, and the rectangular wings 10 on the left side and the right side can actively tilt through the rotating speed difference or the pitch difference of the front rotor wing group and the rear rotor wing group.
The control method of this embodiment is the same as that of the fifth embodiment, and will not be described in detail.
Compared with the fifth embodiment, the vertical take-off and landing aircraft disclosed by the fifth embodiment can generate the same amount of lift force and reduce the take-off and landing occupied area although the flaky wings are smaller.
It should be noted that: the front side, the rear side, the left side and the right side are referred to in the invention, when a person sits on the aircraft seat, the face faces to the front, the left-hand side is the left side, the right-hand side is the right side, and the back is the direction opposite to the front.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting the same, and although the present invention is described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: modifications and equivalents may be made to the embodiments of the invention without departing from the spirit and scope of the invention, which is to be covered by the claims.
Claims (10)
1. A combined type aircraft active tilting structure is characterized by comprising a transmission part, a transmission wheel, a tilting shaft, a connecting piece and a rotor wing assembly;
the two ends of the transmission piece are rotatably connected with the transmission wheels;
the circle center of the driving wheel is fixedly connected with one end of the tilting shaft;
the other end of the tilting shaft is fixedly connected with the connecting piece, and a plurality of rotor wing assemblies are fixedly arranged on one side of the connecting piece;
the two connecting pieces at the two ends of the transmission piece and the rotor wing assemblies fixedly arranged on the two connecting pieces are arranged in opposite directions, the two connecting pieces at the two ends of the transmission piece are in a lever relationship, and when the pulling force between the rotor wing assemblies at the two ends of the transmission piece is different, the two connecting pieces rotate in the same direction;
the transmission part and the transmission wheel are both used for being arranged inside the cabin, the connecting piece and the rotor wing assembly are both used for being arranged outside the cabin, and the other end of the tilting shaft extends out of the cabin and is fixedly connected with the connecting piece.
2. The aircraft active tilt assembly of claim 1 wherein the rotor assemblies at each end of the drive member are symmetrical about the vertical mid-plane of the drive member when the two connection members are not rotating.
3. The modular aircraft active tilting structure according to claim 1 and further comprising a support mechanism;
the support mechanism's both ends have all been seted up the shaft hole, the one end of tilting shaft passes the shaft hole with the centre of a circle fixed connection of drive wheel.
4. The active tilting structure of combined aircraft according to claim 3, wherein a brake is fixedly mounted at each end of the supporting mechanism, and the brake is disposed at one side of the transmission wheel and is used for locking or unlocking the transmission wheel.
5. The modular aircraft active tilt configuration of claim 1, wherein said rotor assembly is a ducted rotor assembly, or said rotor assembly is a jet rotor assembly, or said rotor assembly is a motor plus a propeller.
6. The modular aircraft active tilting structure according to claim 1 and wherein said connection comprises a swing arm and a motor mount;
the other end of the axle that verts with the one end fixed connection of swing arm, the swing arm becomes angle setting with the axle that verts, the other end of swing arm with the middle part fixed connection of motor cabinet, rotor subassembly of two equal fixed mounting in end of motor cabinet.
7. The modular aircraft active tilting structure according to claim 1 and wherein said connection member comprises a sheet wing;
the other end of the tilting shaft is fixedly connected with one end of the flaky wing, a plurality of wing ribs are arranged in the flaky wing, at least two wing ribs extend out of the wing surface of the flaky wing, and each wing rib extending out of the wing surface of the flaky wing is fixedly connected with one rotor assembly.
8. The modular aircraft active tilting structure according to claim 1 and wherein said connection member is a rectangular wing;
the rectangular wing comprises two flaky wings and two supporting pieces, the two flaky wings are parallel to each other, the two supporting pieces are parallel to each other, and two ends of the two supporting pieces are fixedly connected with the end parts of the flaky wings;
the other end of the tilting shaft is fixedly connected with the middle of a supporting sheet of the rectangular wing, and a plurality of rotor assemblies are arranged on the sheet wing connected with one end of the supporting sheet in parallel.
9. A vtol aerial vehicle comprising a nacelle and, connected thereto, an active tilt configuration of a modular aerial vehicle as claimed in any one of claims 1 to 8.
10. The vtol aerial vehicle of claim 9, wherein a through hole is formed at each of the front and rear portions of the nacelle, the transmission member and the transmission wheel are disposed inside the nacelle, the connecting member and the rotor assembly are disposed outside the nacelle, and the other end of the tilt shaft extends out of the nacelle through the through hole and is fixedly connected to the connecting member.
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| CN114802737B (en) * | 2022-04-27 | 2024-04-16 | 重庆大学 | Rotary wing aircraft with tilting mechanism driven by flexible steel wire |
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