CN209972782U - Aircraft power unit and aircraft layout - Google Patents
Aircraft power unit and aircraft layout Download PDFInfo
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- CN209972782U CN209972782U CN201920325836.7U CN201920325836U CN209972782U CN 209972782 U CN209972782 U CN 209972782U CN 201920325836 U CN201920325836 U CN 201920325836U CN 209972782 U CN209972782 U CN 209972782U
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Abstract
The utility model provides an aircraft power unit, including organism (1), still include rotary power structure (20), rotating-structure, cylindrical wind wheel (2), rotary power structure (20), cylindrical wind wheel (2), rotating-structure all are connected with organism (1), rotary power structure (20) still are connected with cylindrical wind wheel (2), organism (1) is equipped with air current import (3) and main jet (4), air current import (3) and main jet (4) all set up along cylindrical wind wheel (2) axis direction, the advantage is applicable to the wingless aircraft, simple structure; the aircraft power unit is adopted, the wingless aircraft can be realized, and the structure is simple.
Description
Technical Field
The utility model relates to an aircraft technical field specifically says an aircraft power pack and aircraft overall arrangement.
Background
At present, the structure of the aircraft power unit mainly includes two types, namely a propeller type and an air injection type, wherein the propeller type comprises an electric propeller, the air injection type is mainly a turbine engine, and a cross flow fan adopted by a wing-wing aircraft is novel, but the aircraft power units are mainly used for wing aircraft, and can be used for helicopters for the propeller type, but the helicopters also need empennages, and the other types are similar to a Dajiang unmanned aerial vehicle, are also used for the propeller type and are not provided with wings.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem of overcoming the defects of the prior art and providing an aircraft power unit which is suitable for an aircraft without wings and has simple structure; the aircraft power unit is adopted, the wingless aircraft can be realized, and the structure is simple.
In order to solve the technical problem, the utility model provides an aircraft power unit, which comprises a machine body, a rotary power structure, a rotating structure and a cylindrical wind wheel, wherein the rotary power structure, the cylindrical wind wheel and the rotating structure are all connected with the machine body;
the rotary power structure is used for driving the cylindrical wind wheel to rotate;
the cylindrical wind wheel is used for sucking air flow from the air flow inlet, accelerating the air flow and then spraying the air flow from the main nozzle;
the rotating structure is used for rotating the body to adjust the direction of the main nozzle.
After adopting above-mentioned scheme, compare with prior art, the utility model has the advantages of it is following: the air flow accelerated by the cylindrical wind wheel is sprayed out from the main nozzle, and the lifting of the aircraft is realized by the reverse acting force of the sprayed air flow, so that the gliding principle of the wings is not used, in addition, when the direction of the main nozzle is adjusted, i.e. with a certain inclination, then lateral and vertical components will be generated, so that the height of the aircraft can be maintained to some extent by means of the vertical component, while the transverse component realizes the forward movement or the backward movement, in a word, the utility model is suitable for a wingless aircraft, has simple structure, the method is very suitable for application environments with limited landing site size, such as express delivery of unmanned aerial vehicles in cities, forest disaster relief and the like, and can also be used for refitting automobiles, the automobile becomes an automobile capable of flying, and in addition, the automobile has certain advantages in cost due to the simple structure, and has good prospects in large-scale application.
As an improvement, the machine body is also provided with an openable and closable propelling nozzle, so that the transverse component is increased, the machine body can advance or retreat more quickly, and the machine body can be opened and closed, and is more flexible to use.
As an improvement, the propelling nozzles and the main nozzles are vertically crossed and distributed, so that a preferable distribution structure is provided, and the functions of the propelling nozzles and the main nozzles are better played.
As the improvement, the structural arrangement of the cylindrical wind wheel comprises two conditions, wherein one condition is that the cylindrical wind wheel comprises one cylindrical wind wheel, the rotary power structure is arranged at one end of the cylindrical wind wheel, the other condition is that the cylindrical wind wheel comprises two cylindrical wind wheels, and the rotary power structure is arranged between the two cylindrical wind wheels.
As the improvement, the position setting of rotating-structure includes two kinds of condition, one kind of condition is, rotating-structure sets up the one end at the organism, another kind of condition is including two cylindrical wind wheels, and rotating-structure sets up between these two cylindrical wind wheels, and like this, the structure is further optimized, provides optional structure, and two kinds of condition can be adopted according to the selection of practical application environment, provides certain basis for follow-up development.
As an improvement, the rotating structure comprises a connecting part and a planetary gear driving mechanism, the planetary gear driving mechanism comprises a planet wheel, a sun wheel and an electric motor or a hydraulic motor, the electric motor or the hydraulic motor is connected with the planet wheel, the number of the electric motors or the hydraulic motors is consistent with that of the planet wheel, the sun wheel is fixedly connected with the machine body, the machine body is rotatably connected with the connecting part, and the electric motor or the hydraulic motor is fixedly arranged on the connecting part; or, revolution mechanic includes connecting portion and planetary gear drive mechanism, and connecting portion include support piece, and organism fixed mounting is in this support piece, and planetary gear drive mechanism includes planet wheel, sun gear and motor or hydraulic motor, and motor or hydraulic motor are connected with the planet wheel, and the quantity of motor or hydraulic motor is unanimous with the quantity of planet wheel, sun gear and support piece fixed connection, support piece and connecting portion body rotatable coupling, motor or hydraulic motor fixed mounting are in connecting portion, and like this, simple structure, stability, reliable.
As the improvement, the connecting part comprises a left part and a right part which are detachably connected, the left part is provided with a bearing mounting hole, and the right part is provided with an electric motor or a hydraulic motor mounting part, so that the connecting part is convenient to manufacture and assemble, and is beneficial to improving the production efficiency and further reducing the cost.
In order to solve the technical problem, the utility model provides an aircraft overall arrangement, this aircraft overall arrangement include the fuselage, and a plurality of aircraft power pack are installed to fuselage both sides or circumference.
After adopting above-mentioned scheme, compare with prior art, the utility model has the advantages of it is following: can realize the wingless aircraft and has simple structure.
As the improvement, the aircraft further comprises a steering structure, the steering structure is connected with the aircraft body, or the aircraft further comprises a propelling structure, and the propelling structure is connected with the aircraft body, or the steering structure and the propelling structure are arranged at the same time, so that the aircraft can be steered flexibly by the steering structure, the flexibility of the aircraft is improved, and compared with the propelling structure which only has a propelling nozzle, the forward or backward speed of the aircraft can be greatly improved, and the practicability of the aircraft is improved.
As an improvement, the aircraft body is provided with a buoyancy structure, so that the requirement on the output power of the power unit of the aircraft can be reduced, the energy-saving purpose is achieved, and the aircraft can take off more easily.
Drawings
Fig. 1 is a front view (not including a rotating structure) of the aircraft power unit of the present invention.
Figure 2 is a rear view of figure 1 (with the cylindrical rotor removed).
Fig. 3 is a left side view of fig. 1.
Figure 4 is a cross-sectional view of a cylindrical wind wheel.
FIG. 5 is a left side view of the main nozzle of FIG. 1 looking vertically downward.
Fig. 6 is a front view of the aircraft power unit of the present invention, which adopts a cylindrical wind wheel and the rotating structure is arranged at one end of the cylindrical wind wheel.
Fig. 7 is a schematic structural view related to the supporting member.
Fig. 8 is a front view of the aircraft power unit of the present invention, which adopts two cylindrical wind wheels and the rotating structure is arranged at one end of the cylindrical wind wheel.
Fig. 9 is a front view of fig. 8 without the rotating structure.
Fig. 10 is a front view of fig. 8 with the shroud installed at the airflow inlet.
Fig. 11 is a front view of the aircraft power unit of the present invention, when two cylindrical wind wheels are adopted, and the rotating structure is disposed between the two cylindrical wind wheels.
Fig. 12 is a front view of fig. 11 with a connector for connecting to a fuselage.
Fig. 13 is a top view of the first inventive aircraft layout.
Fig. 14 is a plan view of a second inventive aircraft layout.
Figure 15 is a top view of a third inventive aircraft layout.
Fig. 16 is a top view of a fourth inventive aircraft layout.
Fig. 17 is a plan view of a fifth inventive aircraft layout.
Shown in the figure are 1, a machine body, 2, a cylindrical wind wheel, 3, an airflow inlet, 4, a main nozzle, 5, a jet nozzle for propulsion, 6, a cover plate, 7, a planet wheel, 8, a sun wheel, 9, an electric motor or a hydraulic motor, 10, a support piece, 11, a left part, 12, a right part, 13, a bearing, 14, a sealing cover, 15, a machine body, 16, an aircraft power unit, 17, a propeller thruster, 18, an aircraft power unit for propulsion, 19, a double-output-shaft electric motor, 20, a rotary power structure, 21, an annular bulge for axial limiting, 22, a protective cover, 23, a connecting piece, 24, a rotating shaft, 25 and a blade.
Detailed Description
The following is a more detailed description of the present invention:
the utility model relates to an aircraft power unit's basic structure does, including organism 1, still include rotary power structure 20, rotating structure, cylindrical wind wheel 2, rotary power structure 20, cylindrical wind wheel 2, rotating structure all are connected with organism 1, rotary power structure 20 still is connected with cylindrical wind wheel 2, organism 1 is equipped with air current import 3 and main jet 4, air current import 3 and main jet 4 all set up along 2 axial directions of cylindrical wind wheel;
the rotary power structure 20 is used for driving the cylindrical wind wheel 2 to rotate;
the cylindrical wind wheel 2 is used for sucking air flow from an air flow inlet 3, accelerating the air flow and then spraying the air flow from a main nozzle 4;
the rotating structure is used to rotate the body 1 to adjust the direction of the main nozzle 4.
The direction indicated by the arrow in the figure is the direction of the air jet.
The utility model discloses an aircraft power unit has lifted three embodiment, specifically as follows:
example one, with reference to figures 1 to 7:
comprises a cylindrical wind wheel 2, and a rotary power structure 20 is arranged at one end of the cylindrical wind wheel 2. The rotary power structure 20 uses an electric motor as rotary power to drive the cylindrical wind wheel 2.
The cylindrical wind wheel 2 comprises a rotating shaft 24 and blades 25, and the blades 25 are spirally distributed around the rotating shaft 24.
The machine body 1 is further provided with an openable propulsion nozzle 5, the openable and closable operation is realized by a cover plate 6 provided on the machine body 1, the openable and closable cover plate 6 controls the opening and closing of the propulsion nozzle 5, and the size of the opening of the propulsion nozzle 5 can be controlled by controlling the opening degree. The specific opening and closing structure can be opened and closed by adopting the gear transmission of a motor, and can also be opened and closed by adopting a hydraulic rod, and the detailed description is omitted for the prior art.
The propulsion nozzle 5 and the main nozzle 4 are arranged to intersect each other perpendicularly, and the perpendicular may be substantially perpendicular, and need not be strictly perpendicular, but may be strictly perpendicular to each other.
The rotating structure is arranged at one end of the machine body 1.
The rotating structure comprises a connecting part and a planetary gear driving mechanism, the connecting part comprises a supporting part 10, the machine body 1 is fixedly installed on the supporting part 10, the planetary gear driving mechanism comprises a planetary wheel 7, a sun wheel 8 and an electric motor or a hydraulic motor 9, the electric motor or the hydraulic motor 9 is connected with the planetary wheel 7, the number of the electric motor or the hydraulic motor 9 is consistent with that of the planetary wheel 7, the sun wheel 8 is fixedly connected with the supporting part 10, the supporting part 10 is rotatably connected with the connecting part body, and the electric motor or the hydraulic motor 9 is fixedly installed on the connecting part.
The connecting part comprises a left part and a right part which are detachably connected, a bearing mounting hole is formed in the left part 11, and the right part 12 is a mounting part of the motor or the hydraulic motor 9.
The bearing mounting hole is provided with a step which is axially limited towards the right side, the bearing mounting hole is used for mounting a bearing 13, the bearing 13 is used for rotatably supporting the supporting piece 10, and in addition, the bearing is further limited in the bearing mounting hole through a mounting cover 14.
In order to facilitate the connection of the machine body 1, the supporting member 10 is divided into two parts, which are joined left and right and detachably connected by flanges.
In the second embodiment, refer to fig. 8 to 10, and refer to fig. 1 to 7 for the same parts as in the first embodiment:
comprising two cylindrical wind wheels 2, between which cylindrical wind wheels 2 a rotational power structure 20 is arranged. The two cylindrical wind wheels 2 can be driven by one rotary power structure 20 at the same time, or the two rotary power structures 20 can be respectively arranged so as to correspond to the two cylindrical wind wheels 2 one by one, so that the power can be increased, and in the embodiment, the two cylindrical wind wheels 2 share one rotary power structure 20.
The rotating structure comprises a connecting portion and a planetary gear driving mechanism, the planetary gear driving mechanism comprises a planetary wheel 7, a sun wheel 8 and an electric motor or a hydraulic motor 9, the electric motor or the hydraulic motor 9 is connected with the planetary wheel 7, the number of the electric motor or the hydraulic motor 9 is consistent with that of the planetary wheel 7, the sun wheel 8 is fixedly connected with the machine body 1, the machine body 1 is rotatably connected with the connecting portion, and the electric motor or the hydraulic motor 9 is fixedly installed on the connecting portion. That is, if the body 1 is strong enough, the support member 10 may not be needed.
In order to axially limit the machine body 1 at the right side, an annular protrusion 21 for axial limiting is provided at the right part of the machine body 1.
In order to avoid that foreign objects entering from the airflow inlet 3 damage the cylindrical wind wheel 2, the airflow inlet 3 is provided with a protective cover 22, such as a mesh-like protective net.
In a third embodiment, refer to fig. 11 to 12, and refer to fig. 1 to 10 for the same parts as the second embodiment:
rotating-structure adopts two play axle motor 19, is connected to the fuselage 15 of aircraft through connecting piece 23, and connecting piece 23 one end is connected with two play axle motor 19 promptly, and the other end then is used for being connected with fuselage 15, and these two connections are fixed connection, and the adoption can be referred to the conventional fixed connection in machinery field, belongs to the prior art category, does not add the perplexing.
In the third embodiment, since the double-output-shaft motor 19 is provided, the double-output-shaft motor 19 divides the machine body 1 into the left and right parts for the convenience of manufacture and assembly, and the double-output-shaft motor 19 and the left and right parts can be connected through flanges.
It is only above the utility model discloses aircraft power unit's preferred embodiment, the event all rely on the utility model discloses a patent application scope structure, characteristic and principle do equivalent change or modification, all include in the utility model discloses in the patent application scope.
Utilize the utility model discloses an aircraft power pack still provides an aircraft overall arrangement, and five embodiments have been lifted to the aircraft overall arrangement, specifically as follows:
aircraft layout embodiment one, refer to fig. 13:
the aircraft layout comprises a fuselage 15, a plurality of aircraft power units 16 are uniformly arranged on two sides of the fuselage 15, in this example, two aircraft power units 16 are arranged on each side, and the aircraft power units 16 specifically adopt the structure of the first embodiment of the aircraft power units 16, and of course, the rotating structure of the aircraft power units 16 is arranged at one end of the fuselage 1.
And a steering structure connected with the body 15, in this case a propeller 17.
The working principle of the plane-type aircraft is that during takeoff, the main nozzles 4 are vertically downward, when the plane-type aircraft reaches a certain height and advances, the two main nozzles 4 on the front side are firstly gradually inclined so as to provide a certain transverse component, and in the process that the two main nozzles 4 on the front side are gradually inclined, the two main nozzles 4 on the rear side are also gradually inclined so as to provide a certain transverse component so as to achieve a certain acceleration purpose, and when suspension stop is required, the plane-type aircraft reversely operates and provides a reverse transverse component to achieve deceleration through reverse inclination. In summary, the principle of generating two components by tilting can be utilized to realize certain flight function without wings.
When steering is needed, the propeller 17 is turned on, the direction indicated by the arrow in the figure is the air flow jet direction, and clockwise or anticlockwise steering torque can be generated according to the air flow jet direction, so that the steering purpose is realized.
If a conventional automobile structure is used as the body 15, the automobile can be made into a flying automobile by adding the above structure.
Aircraft layout example two, refer to fig. 14:
and the steering mechanism is provided with a steering structure and a propelling structure, the steering structure is connected with the machine body 15, and the propelling structure is connected with the machine body 15.
The steering structure adopts a propeller 17, the propelling structure adopts a propelling aircraft power unit 18, namely, a main nozzle 4 of the propelling aircraft power unit 18 sprays airflow transversely to form propelling force, and the propelling aircraft power unit 18 adopts the structure of the third embodiment of the aircraft power unit 16 in the embodiment.
The present example has stronger propelling capability and faster acceleration and deceleration.
Aircraft layout example three, refer to fig. 15:
the aircraft layout comprises a fuselage 15, a plurality of aircraft power units 16 are uniformly distributed and installed on the circumference of the fuselage 15, in this example, one aircraft power unit 16 is arranged on each side, and the aircraft power units 16 specifically adopt the structure of the third embodiment of the aircraft power unit 16, and of course, the rotating structure of the aircraft power unit 16 arranged between two cylindrical wind wheels 2 can be adopted.
The present embodiment can fly in different directions without a steering structure, that is, the two aircraft power units 16 located at the front and the rear can be used to realize the transverse movement in the front or the rear direction, and the two aircraft power units 16 located at the two sides can be used to realize the transverse movement in the two directions towards the two sides, and the transverse movement uses the transverse component generated by the inclination of the main nozzle 4.
Aircraft layout example four, refer to figure 16:
the aircraft layout comprises a fuselage 15, a plurality of aircraft power units 16 are uniformly arranged on two sides of the fuselage 15, in this example, one aircraft power unit 16 is arranged on the front side and the rear side, and the aircraft power unit 16 specifically adopts the structure of the third embodiment of the aircraft power unit 16, and of course, the rotating structure of the aircraft power unit 16 arranged between two cylindrical wind wheels 2 can be adopted.
In the embodiment, the two sides are provided with steering structures, namely, the two sides are respectively provided with one propeller thruster 17, and compared with the third layout embodiment of the aircraft, the steering is mainly realized by the propeller thrusters 17.
Aircraft layout example five, refer to figure 16:
the aircraft body 15 is streamlined, the shape of the aircraft is similar to that of an airship, a plurality of aircraft power units 16 are uniformly distributed on two sides of the aircraft body 15, namely two aircraft power units 16 are respectively arranged on two sides of the aircraft body 15, the aircraft power units 16 specifically adopt the structure of the first embodiment of the aircraft power units 16, and of course, the aircraft power units 16 arranged on one end of the aircraft body 1 can be rotated.
The body 15 of this example is provided with a steering structure, i.e. two propeller thrusters 17 are respectively arranged on both sides, and the steering is mainly realized by matching the two propeller thrusters 17 at the oblique angles.
The fuselage 15 of this example is provided with a buoyancy structure, such as a buoyancy structure of an airship, and the specific structure may be the prior art, which is not described herein.
It is only above the utility model discloses the preferred embodiment of aircraft overall arrangement, the event all rely on the utility model discloses a patent application scope structure, characteristic and principle do equivalent change or modification, all include in the utility model discloses in the patent application scope.
Claims (10)
1. An aircraft power unit comprises a machine body (1), and is characterized by further comprising a rotary power structure (20), a rotating structure and a cylindrical wind wheel (2), wherein the rotary power structure (20), the cylindrical wind wheel (2) and the rotating structure are all connected with the machine body (1), the rotary power structure (20) is also connected with the cylindrical wind wheel (2), the machine body (1) is provided with an airflow inlet (3) and a main nozzle (4), and the airflow inlet (3) and the main nozzle (4) are both arranged along the axial direction of the cylindrical wind wheel (2);
the rotary power structure (20) is used for driving the cylindrical wind wheel (2) to rotate;
the cylindrical wind wheel (2) is used for sucking air flow from the air flow inlet (3), accelerating the air flow and then spraying the air flow from the main nozzle (4);
the rotating structure is used for rotating the machine body (1) to adjust the direction of the main nozzle (4).
2. Aircraft power unit according to claim 1, characterised in that the airframe (1) is further provided with an openable and closable propulsion nozzle (5).
3. Aircraft power unit according to claim 2, characterised in that the propulsion nozzles (5) are arranged perpendicularly across the main nozzles (4).
4. Aircraft power unit according to claim 1, characterized in that the structural arrangement of the cylindrical wind wheel (2) comprises two cases, one case comprising one cylindrical wind wheel (2) with the rotary power structure (20) arranged at one end of the cylindrical wind wheel (2) and the other case comprising two cylindrical wind wheels (2), the rotary power structure (20) being arranged between the two cylindrical wind wheels (2).
5. Aircraft power unit according to claim 1, characterised in that the positional arrangement of the swivel structure comprises two cases, one case in which the swivel structure is arranged at one end of the airframe (1) and the other case in which it comprises two cylindrical wind wheels (2), between which cylindrical wind wheels (2) the swivel structure is arranged.
6. The aircraft power unit of claim 1, characterized in that the rotating structure comprises a connection and a planetary gear drive mechanism, the planetary gear drive mechanism comprises planet wheels (7), a sun wheel (8) and an electric or hydraulic motor (9), the electric or hydraulic motor (9) is connected with the planet wheels (7), the number of the electric or hydraulic motors (9) is the same as the number of the planet wheels (7), the sun wheel (8) is fixedly connected with the machine body (1), the machine body (1) is rotatably connected with the connection, and the electric or hydraulic motor (9) is fixedly mounted at the connection; or, the rotating structure comprises a connecting part and a planetary gear driving mechanism, the connecting part comprises a supporting part (10), the machine body (1) is fixedly installed on the supporting part (10), the planetary gear driving mechanism comprises planet wheels (7), a sun wheel (8) and an electric motor or a hydraulic motor (9), the electric motor or the hydraulic motor (9) is connected with the planet wheels (7), the number of the electric motor or the hydraulic motor (9) is consistent with that of the planet wheels (7), the sun wheel (8) is fixedly connected with the supporting part (10), the supporting part (10) is rotatably connected with the connecting part body, and the electric motor or the hydraulic motor (9) is fixedly installed on the connecting part.
7. Aircraft power unit according to claim 6, characterised in that the connection comprises two detachably connected left and right parts, the left part (11) being provided with bearing mounting holes and the right part (12) being an electric or hydraulic motor (9) mounting.
8. An aircraft arrangement with an aircraft power unit according to any one of claims 1-7, which aircraft arrangement comprises a fuselage (15), characterized in that a plurality of aircraft power units (16) are mounted on both sides or circumferentially of the fuselage (15).
9. The aircraft arrangement of claim 8, further comprising a steering structure connected to the fuselage (15), or further comprising a propulsion structure connected to the fuselage (15), or both.
10. The aircraft layout according to claim 8, characterized in that the fuselage (15) is provided with a buoyant structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920325836.7U CN209972782U (en) | 2019-03-13 | 2019-03-13 | Aircraft power unit and aircraft layout |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920325836.7U CN209972782U (en) | 2019-03-13 | 2019-03-13 | Aircraft power unit and aircraft layout |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209972782U true CN209972782U (en) | 2020-01-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920325836.7U Active CN209972782U (en) | 2019-03-13 | 2019-03-13 | Aircraft power unit and aircraft layout |
Country Status (1)
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|---|---|
| CN (1) | CN209972782U (en) |
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- 2019-03-13 CN CN201920325836.7U patent/CN209972782U/en active Active
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