CN216332748U - Electric vertical take-off and landing manned aircraft - Google Patents
Electric vertical take-off and landing manned aircraft Download PDFInfo
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- CN216332748U CN216332748U CN202122513372.2U CN202122513372U CN216332748U CN 216332748 U CN216332748 U CN 216332748U CN 202122513372 U CN202122513372 U CN 202122513372U CN 216332748 U CN216332748 U CN 216332748U
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- 229910052739 hydrogen Inorganic materials 0.000 claims description 6
- 239000001257 hydrogen Substances 0.000 claims description 6
- 230000005484 gravity Effects 0.000 claims description 4
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 3
- 239000000446 fuel Substances 0.000 claims description 3
- 229910052744 lithium Inorganic materials 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
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Abstract
The utility model discloses an electric vertical take-off and landing manned aircraft, belonging to the field of aviation; the utility model comprises a lower wing arranged at the lower end of the front part of a fuselage, motor fairings arranged at two ends of the lower wing, and two pairs of front rotary wings arranged above the fairings; the upper end of the rear part of the fuselage is provided with an upper wing, two ends of the upper wing are provided with vertical tails, and the tops of the vertical tails are provided with a pair of rear rotary wings; the diameter of the rotor wing of the rear rotor wing is larger than that of the front rotor wing, and the front rotor wing and the rear rotor wing are bilaterally symmetrical; the utility model realizes that all power systems of the whole machine are provided by electric energy, has the advantages of capability of taking off and landing vertically, low requirement on taking off and landing and the like which are the same as those of a helicopter, and has great advantages in short-distance transportation. The electric vertical take-off and landing manned aircraft can be widely applied to various scene fields such as urban passenger transport, regional passenger transport, freight transport, personal aircraft, emergency medical service and the like. The utility model belongs to the field of aviation, and has wide application prospect along with the opening of the future countries to the low-altitude field.
Description
Technical Field
The utility model belongs to the field of aviation, and particularly relates to an electric vertical take-off and landing manned aircraft.
Background
In recent years, with the rapid development of cities and the rapid increase of the number of people in large cities, the existing manned vehicles cannot meet the requirements of people at present. In daily life, short-distance transportation or passenger transportation usually adopts the form of ground transportation, such as passenger cars, trucks and the like, and the transportation modes are often limited by ground roads and the condition of vehicle congestion often occurs; in the aspect of aircrafts, few manned aircrafts are suitable for short-distance traffic, and although helicopters have the advantages of capability of taking off and landing vertically, low requirements on taking off and landing, and the like, problems of high oil consumption, safe operation and the like of civil helicopters make the manned aircrafts not be widely applied to daily life of people. Therefore, electric VTOL aircrafts are receiving more and more attention.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides an electric vertical take-off and landing manned aircraft. As a manned aircraft, the left rotor system is composed of the rear rotor and the front rotor on the left side, the right rotor system is composed of the rear rotor and the front rotor on the right side, the rotating directions of the rotors in the systems are the same, the rotating directions of the left rotor system and the right rotor system are opposite, respective counter torques are balanced, the manned aircraft has great advantages in short-distance transportation, and all power systems of the whole aircraft are provided by electric energy.
The utility model is realized by the following steps:
an electric vertical take-off and landing manned aircraft comprises an aircraft body, wherein the lower end of the front part of the aircraft body is provided with a lower wing, two ends of the lower wing are provided with motor fairings, and two pairs of front rotary wings are arranged above the fairings; the upper end of the rear part of the fuselage is provided with an upper wing, two ends of the upper wing are provided with vertical tails, and the tops of the vertical tails are provided with a pair of rear rotors; the diameter of the rotor wing of the rear rotor wing is larger than that of the front rotor wing, and the two pairs of front rotor wings and the two pairs of rear rotor wings are bilaterally symmetrical; the tail part of the machine body is provided with a propeller, and the propeller is arranged on the symmetrical plane of the machine body; the rear rotor wing, the front rotor wing and the propeller are all connected with the motor, and the motor drives the rear rotor wing, the front rotor wing and the propeller to rotate.
Further, the motor utilizes the group battery to provide the electric energy, the group battery place in fuselage rear portion, and the group battery can be used for balancing the centre of gravity position.
Further, the battery pack comprises one of a lithium battery, a hydrogen fuel cell, or a lithium-hydrogen hybrid battery.
Furthermore, the left rotor system is formed by the left rear rotor and the front rotor, the right rotor system is formed by the right rear rotor and the front rotor, the rotating directions of the rotors in all the systems are the same, and the rotating directions of the left rotor system and the right rotor system are opposite to balance respective reactive torques.
Furthermore, a skid landing gear is arranged at the bottom of the machine body.
Furthermore, the rear rotor and the front rotor are two blades, the propeller has three blades, and the blade pitch is variable.
The beneficial effects of the utility model and the prior art are as follows:
the utility model has the following advantages: 1) the operation mode is simple: compared with the conventional mechanical operation, the fly-by-wire operation has the advantages of simple operation and high safety. 2) The occupied area is small: the utility model has small volume and low storage requirement. 3) And the application range is wide: the utility model can be widely applied to various scene fields of urban passenger transport, regional passenger transport, freight transport, personal aircrafts, emergency medical services and the like. 4) And the flight cost is low: compared with other aircrafts or automobiles, the utility model has the advantages of low full-electric energy consumption and high safety margin.
As a manned aircraft, the utility model realizes that all power systems of the whole aircraft are provided by electric energy, has the advantages of capability of taking off and landing vertically, low requirement on taking off and landing and the like which are the same as those of a helicopter, and has great advantages in short-distance transportation. The electric vertical take-off and landing manned aircraft can be widely applied to various scene fields such as urban passenger transport, regional passenger transport, freight transport, personal aircraft, emergency medical service and the like. The utility model belongs to the field of aviation, and has wide application prospect along with the opening of the future countries to the low-altitude field.
Drawings
FIG. 1 is an isometric view of an electric VTOL manned aircraft in an embodiment of the present invention;
FIG. 2 is a top view of an electric VTOL manned aircraft in an embodiment of the present invention;
FIG. 3 illustrates a propeller operating mechanism in an embodiment of the present invention;
wherein, 1-fuselage, 2-back rotor, 3-vertical tail, 4-upper wing, 5-propeller, 6-skid landing gear, 7-front rotor, 8-lower wing, 9-motor, 10-battery pack.
Detailed Description
In order to make the objects, technical solutions and effects of the present invention more clear, the present invention is further described in detail by the following examples. It should be noted that the specific embodiments described herein are merely illustrative of the utility model and are not intended to limit the utility model.
As shown in fig. 1 to 3, an electric vertical take-off and landing manned aircraft according to the present invention includes: the aircraft comprises an aircraft body 1, a rear rotor 2, a vertical tail 3, an upper wing 4, a propeller 5, a skid landing gear 6, a front rotor 7 and a lower wing 8.
The lower wing 8 is located in the front of the fuselage 1, the two ends of the lower wing 8 are provided with motor fairings, two pairs of front rotors 7 are respectively arranged above the fairings, the upper wing 4 is located in the rear of the fuselage 1, the two ends of the upper wing 4 are respectively provided with a vertical tail 3, the top of the vertical tail 3 is respectively provided with a pair of rear rotors 2, the diameter of the rotor of each rear rotor 2 is slightly larger than that of the front rotor 7, the tail of the fuselage 1 is provided with propellers 5, the front rotors 7 and the rear rotors 2 are bilaterally symmetrical, and the propellers 5 are arranged on the symmetrical plane of the fuselage. And a skid type undercarriage 6 is arranged at the bottom of the machine body 1.
The left rotor system is composed of the rear rotor 2 and the front rotor 7 on the left side of the electric vertical take-off and landing manned aircraft, the right rotor system is composed of the rear rotor 2 and the front rotor 7 on the right side, the rotating directions of the rotors in all the systems are the same, and the rotating directions of the left rotor system and the right rotor system are opposite to balance respective reactive torques.
The screw operating mechanism includes: rear rotor 2, front rotor 7, screw 5, motor 9, battery 10. The rear rotor wing 2, the front rotor wing 7 and the propeller 5 are connected with a motor, the motor 9 drives the rear rotor wing 2, the front rotor wing 7 and the propeller 5 to rotate, the battery pack 10 is used for providing electric energy for the motor 9, and the battery pack 10 is placed at the rear part of the fuselage and used for balancing the gravity center position. The battery pack 10 includes one of a lithium battery or a hydrogen fuel cell, or a lithium-hydrogen hybrid. The rear rotor wing 2 and the front rotor wing 7 are 2 blades, and the propeller 3 is provided with 3 blades which can change the propeller pitch.
The propeller structure in the utility model is only indicated for the convenience of writing, and the utility model is still applicable to the rotor wing.
The working process of the utility model is as follows:
as shown in fig. 1, when the aircraft is in the vertical mode, the front rotor 7 and the rear rotor 2 rotate to generate lift force, and the lift force of the rotors is changed by changing the rotation speed of the motor. When the lift force is equal to the gravity force, the aircraft is in a hovering state.
When the aircraft is in a forward flight mode, the propeller 5 mounted at the rear part of the aircraft body generates thrust, the propeller 5 can adjust the thrust according to actual flight conditions in a mode of changing the rotating speed or the total distance, at the moment, the upper wing 4 and the lower wing 8 generate relative motion with air, upward lift force is generated, the rotors can be unloaded, and the rotating speeds of the front rotor 7 and the rear rotor 2 are reduced.
When the aircraft is in rolling motion, the rotating speed and the total distance of the left rotor system and the right rotor system can be adjusted, so that the lift difference exists between the rotors of the two systems, and the flying attitude of the aircraft is changed to roll.
When the aircraft is in yawing motion, the left rotor system and the right rotor system can generate yawing moment through opposite periodic variable distances, so that the aircraft rotates around the center of mass.
When the aircraft flies in a short distance, a pilot vertically takes off at a designated place, the aircraft flies to the designated place to start decelerating and vertically landing, and the aircraft takes off and returns to the original position to wait for the next task after the task target is finished.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that modifications can be made by those skilled in the art without departing from the principle of the present invention, and these modifications should also be construed as the protection scope of the present invention.
Claims (5)
1. An electric vertical take-off and landing manned aircraft comprises an aircraft body (1) and is characterized in that the lower end of the front part of the aircraft body (1) is provided with a lower wing, two ends of the lower wing (8) are provided with motor fairings, and two pairs of front rotors (7) are arranged above the fairings; the upper end of the rear part of the fuselage (1) is provided with an upper wing (4), two ends of the upper wing (4) are provided with vertical tails (3), and the tops of the vertical tails (3) are provided with a pair of rear rotors (2); the diameter of the rotor wing of the rear rotor wing (2) is larger than that of the front rotor wing (7), and the two pairs of front rotor wings (7) and the two pairs of rear rotor wings (2) are bilaterally symmetrical;
the tail part of the machine body (1) is provided with a propeller (5), and the propeller (5) is arranged on the symmetrical plane of the machine body;
the rear rotor (2), the front rotor (7) and the propeller (5) are all connected with a motor (9), and the motor (9) drives the rear rotor (2), the front rotor (7) and the propeller (5) to rotate; the motor (9) utilizes a battery pack (10) to provide electric energy, the battery pack (10) is placed at the rear part of the machine body, and the battery pack (10) can be used for balancing the gravity center position.
2. The electric VTOL manned aircraft of claim 1, wherein the battery pack (10) is one of a lithium battery or a hydrogen fuel cell, or a lithium-hydrogen hybrid.
3. An electric VTOL manned vehicle according to claim 1, characterized in that, the left rotor system is composed of the left rear rotor (2) and the front rotor (7), the right rotor system is composed of the right rear rotor (2) and the front rotor (7), the rotation direction of the rotors in each system is the same, and the rotation direction of the left rotor system is opposite to that of the right rotor system, so as to balance the respective reaction torque.
4. An electric VTOL manned aircraft according to claim 1, characterized in that skid landing gear (6) is installed at the bottom of the fuselage (1).
5. The electric VTOL manned vehicle of claim 1, characterized in that, the rear rotor (2) and the front rotor (7) are two blades, the propeller (5) has three blades, the pitch is variable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122513372.2U CN216332748U (en) | 2021-10-19 | 2021-10-19 | Electric vertical take-off and landing manned aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122513372.2U CN216332748U (en) | 2021-10-19 | 2021-10-19 | Electric vertical take-off and landing manned aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216332748U true CN216332748U (en) | 2022-04-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122513372.2U Active CN216332748U (en) | 2021-10-19 | 2021-10-19 | Electric vertical take-off and landing manned aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216332748U (en) |
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2021
- 2021-10-19 CN CN202122513372.2U patent/CN216332748U/en active Active
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