CN113511334A - Vector control VTOL unmanned aerial vehicle - Google Patents
Vector control VTOL unmanned aerial vehicle Download PDFInfo
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- CN113511334A CN113511334A CN202110617893.4A CN202110617893A CN113511334A CN 113511334 A CN113511334 A CN 113511334A CN 202110617893 A CN202110617893 A CN 202110617893A CN 113511334 A CN113511334 A CN 113511334A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
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Abstract
The application provides a vector control vertical take-off and landing unmanned aerial vehicle, wherein an energy source part is arranged in a vehicle body; the power part is arranged in the machine body; the main lifting wings are symmetrically arranged on two sides of the fuselage; the main propellers are respectively arranged at the main lift wings at the two sides of the machine body, and the rotating shafts of the main propellers are parallel to the length direction of the machine body; the vector attitude control propeller is arranged at the head of the fuselage, and the orientation of the rotating shaft of the vector attitude control propeller is adjustable. The vertical landing gear is arranged on the fuselage. Through such a mode, can realize unmanned aerial vehicle's VTOL to the head is equipped with vector attitude control screw, takes off at unmanned aerial vehicle and falls to the ground the in-process and be in the biggest pulling force state, and anti-wind ability reinforce. Because the vector posture with the adjustable angle of the head controls the suspension function formed by the pulling force provided by the propeller and has the function of adjusting the direction, the whole machine has the capacity of rising and falling on a moving naval vessel and a moving automobile. Therefore, the vertical take-off and landing of the unmanned aerial vehicle can be reliably realized.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicles, in particular to a vector control VTOL unmanned aerial vehicle.
Background
Unmanned aerial vehicles, i.e., unmanned aircraft, fly in a remote control or autonomous program piloting manner. At present, due to the fact that unmanned planes are small in size, low in manufacturing cost and free of personnel injury risks, the trend that an unmanned plane platform is adopted to replace a manned plane to perform military and civil tasks such as investigation, surveying and mapping and communication is more and more obvious.
Nowadays, most unmanned aerial vehicles adopt a fixed wing horizontal landing mode with a conventional layout, although the load is large, the unmanned aerial vehicles are limited by airports and can only take off and land in limited regions. Some airplanes use catapult takeoff and vertical parachuting to avoid the limitation of airports.
The vertical take-off and landing has the advantages that a special airport is not needed, the conventional fixed wing aircraft cannot be replaced, but the power load in the vertical take-off state is obviously lower than that of the fixed wing aircraft, so that the load is small, the oil consumption is high, the horizontal flying speed is low, most of the existing popular multi-axis aircraft can only be served at one time, and the development of the existing multi-axis aircraft is obviously restricted.
Disclosure of Invention
An object of the embodiment of the application is to provide a vector control VTOL unmanned aerial vehicle to realize unmanned aerial vehicle's VTOL.
In order to achieve the above object, embodiments of the present application are implemented as follows:
in a first aspect, an embodiment of the present application provides a vector control vertical take-off and landing unmanned aerial vehicle, which includes a vehicle body, an energy source portion, a power portion, a main lift wing, a main propeller, a vector attitude control propeller, and a vertical landing gear, wherein the energy source portion is arranged in the vehicle body and is used for providing energy; the power part is arranged in the machine body and used for providing power; the main lifting wings are symmetrically arranged on two sides of the fuselage; the even number of the main propellers are respectively arranged at the main lift wings at two sides of the machine body, and the rotating shafts of the main propellers are parallel to the length direction of the machine body; the vector attitude control propeller is arranged at the head of the machine body, the direction of a rotating shaft of the vector attitude control propeller can be adjusted, and when the vector attitude control propeller is in an initial state, the rotating shaft of the vector attitude control propeller is parallel to the length direction of the machine body; perpendicular undercarriage sets up on the fuselage, just during vector control VTOL unmanned aerial vehicle VTOL, perpendicular undercarriage and the ground contact of take-off and landing point, so that vector control VTOL unmanned aerial vehicle stands on the subaerial of take-off and landing point, just the head of fuselage is towards the sky.
In the embodiment of the application, the energy source part is arranged in the fuselage and is used for providing energy; the power part is arranged in the machine body and used for providing power; the main lifting wings are symmetrically arranged on two sides of the fuselage; the even number of main propellers are respectively arranged at the main lift wings at the two sides of the machine body, and the rotating shafts of the main propellers are parallel to the length direction of the machine body; the vector attitude control propeller is arranged at the head of the body and the direction of the rotating shaft thereof is adjustable, and when the vector attitude control propeller is in an initial state, the rotating shaft thereof is parallel to the length direction of the body. Perpendicular undercarriage sets up on the fuselage, and when vector control VTOL unmanned aerial vehicle VTOL, perpendicular undercarriage and the ground contact of take-off and landing point to make vector control VTOL unmanned aerial vehicle erect on the subaerial of take-off and landing point, and the head of fuselage is towards the sky. Through such a mode, can realize unmanned aerial vehicle's VTOL to the head is equipped with vector attitude control screw, takes off at unmanned aerial vehicle and falls to the ground the in-process and be in the biggest pulling force state, and anti-wind ability reinforce. Because the vector posture with the adjustable angle of the head controls the suspension function formed by the pulling force provided by the propeller and has the function of adjusting the direction, the whole machine has the capacity of rising and falling on a moving naval vessel and a moving automobile. Therefore, the vertical take-off and landing of the unmanned aerial vehicle can be reliably realized.
With reference to the first aspect, in a first possible implementation manner of the first aspect, the vector attitude control propeller is controlled by two control steering engines to adjust an included angle between a rotation axis of the vector attitude control propeller and a length direction of the fuselage.
In this implementation, the vector attitude control screw is controlled by two control steering wheels, can adjust the contained angle between the rotation axis of vector attitude control screw and the length direction of fuselage, can play the guide effect like this when unmanned aerial vehicle VTOL to and, at unmanned aerial vehicle flight in-process, carry out unmanned aerial vehicle's directional control.
With reference to the first aspect, in a second possible implementation manner of the first aspect, the energy source portion includes a power source and an oil tank, and correspondingly, the power portion is a hybrid power device.
In this implementation, the energy source includes a power source and an oil tank, which is equivalent to adding a secondary oil tank to the drone, which allows the drone to continue flying for a longer period of time. And, can set up the position of oil tank as required for unmanned aerial vehicle's focus is in the oil tank setting department.
With reference to the first aspect, in a third possible implementation manner of the first aspect, the vector control vertical take-off and landing drone further includes a horizontal running undercarriage, where the horizontal running undercarriage includes a front wheel and a rear wheel; the front wheel is arranged on the ventral side of the head of the body; the rear wheel is arranged on the ventral side of the tail of the machine body.
In the implementation mode, the horizontal running undercarriage is arranged at the bottom of the vector control vertical take-off and landing unmanned aerial vehicle, and the unmanned aerial vehicle can take off in a running take-off mode when an airport meets the running take-off condition. When the load is larger than the vertical taking-off and landing capacity, the liquid can adopt a horizontal short-distance taking-off and landing mode.
With reference to the third possible implementation manner of the first aspect, in a fourth possible implementation manner of the first aspect, the horizontal running undercarriage further includes a ground contact prevention support, when the vector control VTOL UAV is in horizontal running and landing, the ground contact prevention support faces the ground, a roller is arranged at an end of the ground contact prevention support, and a relative height between the roller and the ground is lower than a relative height between a blade tip of the main propeller and the ground.
In this implementation, through setting up the support of preventing touching ground, can support when unmanned aerial vehicle's front wheel or rear wheel became invalid and hold on ground, accomplish unmanned aerial vehicle's level take off and land. The relative height between the roller arranged at the end part of the anti-touch bracket and the ground is lower than the relative height between the tail end of the blade of the main propeller and the ground, so that the main propeller can be protected and the main propeller is prevented from touching the ground.
Combine the third possible implementation of the first aspect, in the fifth possible implementation of the first aspect, the perpendicular undercarriage includes two branches, and two branches symmetry sets up in the both sides of fuselage, when vector control VTOL unmanned aerial vehicle VTOL, the bottom of every branch with the outer edge of rear wheel all with ground contact, in order to support vector control VTOL unmanned aerial vehicle erects on ground.
In this implementation, perpendicular undercarriage includes two branches, and two branch symmetries set up in the both sides of fuselage, and when vector control VTOL unmanned aerial vehicle VTOL, the bottom and the ground contact of every branch to support vector control VTOL unmanned aerial vehicle and stand on ground. And, the outer edge of rear wheel also with ground contact, play the supporting role, stability when can guarantee that unmanned aerial vehicle is located the VTOL gesture.
With reference to the fifth possible implementation manner of the first aspect, in a sixth possible implementation manner of the first aspect, a gas boosting sleeve is provided on each strut.
In this implementation, be equipped with the gas boosting sleeve pipe on every branch, can realize unmanned aerial vehicle's internal combustion boosting overload vertical takeoff.
In combination with the first aspect, in a seventh possible implementation manner of the first aspect, the vector control VTOL UAV further includes fixed canard wings, the fixed canard wings are symmetrically disposed on two sides of the fuselage and located between the main lift wings and the head of the fuselage.
In the implementation mode, the fixed canard wing and the lower part of the aircraft body are fused, so that the lift force can be provided together, the wing load of the flat flight is reduced, the lift-drag ratio is increased, and the energy is saved.
With reference to the first aspect, in an eighth possible implementation manner of the first aspect, the vector control VTOL UAV further includes a vertical tail rudder, the vertical tail rudder is vertically disposed on a back side of the tail portion of the fuselage, and the vertical tail rudder is supported on the ground when the vector control VTOL UAV vertically takes off and lands.
In this implementation, the vertical tail vane is vertically arranged on the back side of the tail of the fuselage, and when the vector control vertical take-off and landing unmanned aerial vehicle vertically takes off and lands, the vertical tail vane is supported on the ground. The vertical tail is a fixed wing surface completely and is also used as a support frame when the vertical tail falls to the ground, so that the stability of the unmanned aerial vehicle in a vertical take-off and landing posture can be further ensured.
With reference to the eighth possible implementation manner of the first aspect, in the ninth possible implementation manner of the first aspect, the vector control VTOL UAV further comprises two elevators, the two elevators are symmetrically arranged on two sides of the tail of the fuselage, and one control steering engine controls an included angle between the two elevators and a horizontal plane.
In the implementation mode, the vector control vertical take-off and landing unmanned aerial vehicle further comprises two elevators, the two elevators are symmetrically arranged on two sides of the tail of the unmanned aerial vehicle body, and the two elevators are controlled by one control steering engine to form included angles with the horizontal plane. Therefore, the vector control VTOL unmanned aerial vehicle only has two active horizontal control planes (one is the control plane where the vector attitude control screw of head belongs, and the other is the control plane where the elevator belongs), can make unmanned aerial vehicle convenient operation, and simple structure is reliable, has stronger reliability.
In order to make the aforementioned objects, features and advantages of the present application more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments of the present application will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and that those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.
Fig. 1 is a schematic view of a vector control VTOL unmanned aerial vehicle provided by an embodiment of the present application under a frontal perspective.
Fig. 2 is a schematic diagram of a vector control vertical take-off and landing unmanned aerial vehicle in a horizontal running takeoff attitude, provided in an embodiment of the present application.
Fig. 3 is a schematic view of a vector control VTOL UAV in a VTOL attitude provided by an embodiment of the present application.
Icon: 100-vector control of a vertical take-off and landing unmanned aerial vehicle; 110-a fuselage; 120-energy department; 121-a power supply; 122-a fuel tank; 130-a power section; 140-a main lift wing; 150-a main propeller; 160-vector attitude control propeller; 170-vertical landing gear; 180-horizontal running landing gear; 181-front wheel; 182-rear wheels; 183-touchdown prevention support; 191-a gas boosting sleeve; 192-fixing duck wings; 193-vertical tail rudder.
Detailed Description
The technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application.
Referring to fig. 1 to 3, fig. 1 is a schematic view of a vector control vtol drone 100 provided in an embodiment of the present application at a front view angle; fig. 2 is a schematic diagram of a vector control vertical take-off and landing drone 100 in a horizontal running takeoff attitude according to an embodiment of the present application; fig. 3 is a schematic diagram of the vector control vtol drone 100 in a vtol attitude according to the embodiment of the present application.
In this embodiment, the vector control vtol drone 100 may include a fuselage 110, an energy section 120, a power section 130, main lift wings 140, main propellers 150, vector attitude control propellers 160, and vertical landing gear 170.
Illustratively, the energy source 120 may be disposed within the fuselage 110 for providing energy. For example, the energy source 120 may be disposed inside the fuselage 110 in a space between the nose and the tail of the fuselage 110.
For example, the power unit 130 may be disposed in the body 110 for providing power. For example, the power section 130 may be disposed within the fuselage 110 adjacent to the energy section 120.
Illustratively, the main lifting wings 140 may be symmetrically disposed on both sides of the fuselage 110, and are mainly used for providing lift for the flight of the drone.
Illustratively, an even number (e.g., two, four, etc.) of main propellers 150 are respectively disposed at the main lift wings 140 on both sides of the fuselage 110, and the rotation axis of the main propellers 150 is parallel to the length direction of the fuselage 110. Main propeller 150 is mainly used for providing power for the flight of unmanned aerial vehicle.
For example, the vector posture control propeller 160 may be provided at the head of the body 110, and the orientation of the rotation axis of the vector posture control propeller 160 may be adjusted, and the rotation axis of the vector posture control propeller 160 is parallel to the length direction of the body 110 when it is in the initial state. Vector attitude control screw 160 can provide power for unmanned aerial vehicle's flight on the one hand, and on the other hand, can also be the same as the direction of flight of adjusting unmanned aerial vehicle, adjusts unmanned aerial vehicle's gesture etc..
For example, the vertical landing gear 170 may be disposed on the fuselage 110, and when the vector control VTOL UAV 100 VTOL, the vertical landing gear 170 is in contact with the ground of the take-off and landing point, such that the vector control VTOL UAV 100 is standing on the ground of the take-off and landing point with the head of the fuselage 110 facing the sky.
Through such a mode, can realize unmanned aerial vehicle's VTOL to the head is equipped with vector attitude control screw 160, takes off at unmanned aerial vehicle and falls to the ground the in-process and be in the biggest pulling force state, and anti-wind ability reinforce. Due to the suspension function formed by the pulling force provided by the vector attitude control propeller 160 with the adjustable angle of the head and the direction adjusting function, the whole machine has the capacity of rising and falling on a moving naval vessel and a moving automobile. Therefore, the vertical take-off and landing of the unmanned aerial vehicle can be reliably realized.
In this embodiment, the vector attitude control propeller 160 may be controlled by two control steering engines (the two steering engines adjust different directions), so as to adjust an included angle between the rotation axis of the vector attitude control propeller 160 and the length direction of the fuselage 110. Can play the guide effect like this when unmanned aerial vehicle VTOL to and, at unmanned aerial vehicle flight in-process, realize unmanned aerial vehicle's directional control, unmanned aerial vehicle's attitude control etc.
In the present embodiment, the energy source part 120 may include a power source 121 and a fuel tank 122, and correspondingly, the power part 130 is a hybrid power device. For example, power supply 121 may be a battery, disposed on the belly of the drone, near the head of the drone, while fuel tank 122 may be disposed between power supply 121 and the tail of the drone, e.g., fuel tank 122 may be disposed adjacent power supply 121. This corresponds to adding a secondary fuel tank 122 to the drone, which allows the drone to continue flying for a longer period of time. And, can set up the position of oil tank 122 as required for unmanned aerial vehicle's focus is in oil tank 122 setting department.
In this embodiment, the vector control vtol drone 100 further comprises a horizontal running landing gear 180, the horizontal running landing gear 180 comprising a front wheel 181 and a rear wheel 182; the front wheel 181 is disposed on the ventral side of the head of the body 110; the rear wheels 182 are disposed on the ventral side of the tail of the fuselage 110.
The horizontal running undercarriage 180 is arranged at the bottom of the vector control vertical take-off and landing unmanned aerial vehicle 100, and can take off in a running take-off mode when the airport meets the running take-off condition. When the load is larger than the vertical taking-off and landing capacity, the liquid can adopt a horizontal short-distance taking-off and landing mode.
In this embodiment, the horizontal running landing gear 180 further includes a ground contact prevention bracket 183, the ground contact prevention bracket 183 faces the ground when the vector control vertical take-off and landing drone 100 is in horizontal running and landing, and the end of the ground contact prevention bracket 183 is provided with a roller, and the relative height between the roller and the ground is lower than the relative height between the tip of the blade of the main propeller 150 and the ground.
Through setting up the support 183 that contacts to ground, can support when unmanned aerial vehicle's front wheel 181 or rear wheel 182 became invalid and hold on ground, accomplish unmanned aerial vehicle's level take off and land. Since the rollers provided at the ends of the ground contact prevention bracket 183 have a lower relative height to the ground than the blade tips of the main propeller 150, it is also possible to protect the main propeller 150 from the ground contact of the main propeller 150.
In this embodiment, the vertical landing gear 170 includes two struts, and two struts symmetry set up in the both sides of fuselage 110, and when the vector control VTOL unmanned aerial vehicle 100 VTOL, the bottom of every strut all contacts with the ground along the outer edge of rear wheel 182 to support vector control VTOL unmanned aerial vehicle 100 and stand on ground. Therefore, branch and rear wheel 182 all can play the supporting role to further guarantee the stability when unmanned aerial vehicle is located the VTOL gesture.
In this embodiment, a gas boosting sleeve 191 is provided on each strut. For example, the gas boosting sleeve 191 may be disposed at the tail of the strut, which facilitates internal combustion boosting overload vertical takeoff of the drone.
In this embodiment, the vector control vtol drone 100 further includes fixed canard wings 192, and the fixed canard wings 192 are symmetrically disposed on both sides of the fuselage 110 and located between the main lift wing 140 and the head of the fuselage 110. For example, fixed duck wing 192 may be of the type NACA 23010. The fixed canard 192 and the lower part of the fuselage 110 are fused to provide lift force together, so that the wing load of the flat flight is reduced, and the lift-drag ratio is increased to save energy.
In the present embodiment, the vector control vertical take-off and landing drone 100 further includes a vertical tail rudder 193, the vertical tail rudder 193 is vertically disposed at a back side of a rear portion of the fuselage 110, and, when the vector control vertical take-off and landing drone 100 vertically takes off and lands, the vertical tail rudder 193 is supported on the ground. The vertical tail wing is a fixed wing surface and is also used as a support frame when the vertical tail wing falls to the ground vertically, so that the stability of the unmanned aerial vehicle in the vertical take-off and landing posture can be further ensured.
In this embodiment, the vector control VTOL UAV 100 further comprises two elevators, the two elevators are symmetrically arranged at two sides of the tail of the airframe 110, and the two elevators are controlled by one control steering engine to form an included angle with the horizontal plane.
Therefore, the vector control VTOL UAV 100 has only two active horizontal control planes (one is the control plane where the vector attitude control propeller 160 of the head is located, and the other is the control plane where the elevator is located), so that the UAV is convenient to operate, simple and reliable in structure and higher in reliability.
In addition, the vector control vertical take-off and landing unmanned aerial vehicle 100 can also realize a net landing function, and a fan-shaped landing net is arranged on a landing platform such as a ship or an automobile along the motion direction of the landing platform, so that net collision landing is realized. And, the vector control vtol drone 100 may also implement catapult takeoff, which is not limited herein.
To sum up, the embodiment of the present application provides a vector control vertical take-off and landing unmanned aerial vehicle 100, and the energy source part 120 is disposed in the fuselage 110 and is used for providing energy; the power part 130 is arranged in the body 110 and used for providing power; the main lift wings 140 are symmetrically arranged on both sides of the fuselage 110; an even number of main propellers 150 are respectively arranged at the main lift wings 140 at both sides of the body 110, and the rotation axis of the main propellers 150 is parallel to the length direction of the body 110; the vector posture control propeller 160 is provided at the head of the body 110 and the orientation of the rotation axis thereof is adjustable, and the rotation axis thereof is parallel to the length direction of the body 110 when the vector posture control propeller 160 is in the initial state. The vertical landing gear 170 is provided on the fuselage 110, and when the vector control VTOL UAV 100 VTOL, the vertical landing gear 170 is in contact with the ground of the take-off and landing point to cause the vector control VTOL UAV 100 to stand on the ground of the take-off and landing point with the head of the fuselage 110 facing the sky. Through such a mode, can realize unmanned aerial vehicle's VTOL to the head is equipped with vector attitude control screw 160, takes off at unmanned aerial vehicle and falls to the ground the in-process and be in the biggest pulling force state, and anti-wind ability reinforce. Due to the suspension function formed by the pulling force provided by the vector attitude control propeller 160 with the adjustable angle of the head and the direction adjusting function, the whole machine has the capacity of rising and falling on a moving naval vessel and a moving automobile. Therefore, the vertical take-off and landing of the unmanned aerial vehicle can be reliably realized.
In this document, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions.
The above description is only an example of the present application and is not intended to limit the scope of the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (10)
1. A vector control vertical take-off and landing unmanned aerial vehicle is characterized by comprising a vehicle body, an energy source part, a power part, a main lifting wing, a main propeller, a vector attitude control propeller and a vertical landing gear,
the energy source part is arranged in the machine body and is used for providing energy;
the power part is arranged in the machine body and used for providing power;
the main lifting wings are symmetrically arranged on two sides of the fuselage;
the even number of the main propellers are respectively arranged at the main lift wings at two sides of the machine body, and the rotating shafts of the main propellers are parallel to the length direction of the machine body;
the vector attitude control propeller is arranged at the head of the machine body, the direction of a rotating shaft of the vector attitude control propeller can be adjusted, and when the vector attitude control propeller is in an initial state, the rotating shaft of the vector attitude control propeller is parallel to the length direction of the machine body;
perpendicular undercarriage sets up on the fuselage, just during vector control VTOL unmanned aerial vehicle VTOL, perpendicular undercarriage and the ground contact of take-off and landing point, so that vector control VTOL unmanned aerial vehicle stands on the subaerial of take-off and landing point, just the head of fuselage is towards the sky.
2. The vector control VTOL UAV of claim 1, wherein the vector attitude control propeller is controlled by two control steering engines to adjust the angle between the rotation axis of the vector attitude control propeller and the length direction of the fuselage.
3. The vector control VTOL unmanned aerial vehicle of claim 1, wherein the energy portion comprises a power supply and an oil tank, and correspondingly, the power portion is an oil-electricity hybrid power device.
4. The vector control VTOL UAV of claim 1, further comprising a horizontal running landing gear,
the horizontal running undercarriage comprises a front wheel and a rear wheel;
the front wheel is arranged on the ventral side of the head of the body;
the rear wheel is arranged on the ventral side of the tail of the machine body.
5. The vector control VTOL UAV of claim 4, wherein the horizontal running landing gear further comprises a touchdown prevention bracket,
when the vector control vertical take-off and landing unmanned aerial vehicle runs and takes off and lands horizontally, the anti-ground-contact support faces the ground, the end part of the anti-ground-contact support is provided with a roller, and the relative height between the roller and the ground is lower than the relative height between the tail end of a blade of the main propeller and the ground.
6. The vector control VTOL UAV of claim 4, wherein the vertical landing gear comprises two struts,
two branch symmetries set up in the both sides of fuselage, when vector control VTOL unmanned aerial vehicle VTOL, the bottom of every branch with the outer edge of rear wheel all contacts with ground, in order to support vector control VTOL unmanned aerial vehicle stands on ground.
7. The vector control VTOL UAV of claim 6, wherein each strut is provided with a gas boosting sleeve.
8. The vector control VTOL UAV of claim 1, further comprising fixed canard wings symmetrically disposed on both sides of the fuselage and located between the main lift wing and the head of the fuselage.
9. The vector-controlled VTOL UAV of claim 1, wherein the vector-controlled VTOL UAV further comprises a vertical tail rudder,
the vertical tail rudder is vertically arranged on the back side of the tail part of the airplane body, and when the vector control VTOL unmanned aerial vehicle vertically takes off and lands, the vertical tail rudder is supported on the ground.
10. The vector control VTOL UAV of claim 9, further comprising two elevators,
the two elevators are symmetrically arranged on two sides of the tail of the machine body, and the included angle between the two elevators and the horizontal plane is controlled by one control steering engine.
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| CN202110617893.4A CN113511334A (en) | 2021-06-03 | 2021-06-03 | Vector control VTOL unmanned aerial vehicle |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105905295A (en) * | 2016-06-14 | 2016-08-31 | 临沂高新区翔鸿电子科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN105966612A (en) * | 2016-05-27 | 2016-09-28 | 东北师范大学 | Posture-changeable unmanned aerial vehicle capable of achieving vertical takeoff and landing |
| US20170008625A1 (en) * | 2015-07-10 | 2017-01-12 | Orville Olm | Vertical Takeoff and Landing Unmanned Aircraft System |
| CN210793660U (en) * | 2018-12-25 | 2020-06-19 | 连云港瑞云智能科技有限公司 | Single rotor tail seat type vertical take-off and landing unmanned aerial vehicle |
| CN111452969A (en) * | 2020-04-01 | 2020-07-28 | 北京航空航天大学 | Tailstock type flying wing layout unmanned aerial vehicle capable of taking off and landing vertically |
| CN211685607U (en) * | 2019-12-16 | 2020-10-16 | 宇领星际航空(苏州)有限公司 | But folding unmanned aerial vehicle of VTOL tail seat |
-
2021
- 2021-06-03 CN CN202110617893.4A patent/CN113511334A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170008625A1 (en) * | 2015-07-10 | 2017-01-12 | Orville Olm | Vertical Takeoff and Landing Unmanned Aircraft System |
| CN105966612A (en) * | 2016-05-27 | 2016-09-28 | 东北师范大学 | Posture-changeable unmanned aerial vehicle capable of achieving vertical takeoff and landing |
| CN105905295A (en) * | 2016-06-14 | 2016-08-31 | 临沂高新区翔鸿电子科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN210793660U (en) * | 2018-12-25 | 2020-06-19 | 连云港瑞云智能科技有限公司 | Single rotor tail seat type vertical take-off and landing unmanned aerial vehicle |
| CN211685607U (en) * | 2019-12-16 | 2020-10-16 | 宇领星际航空(苏州)有限公司 | But folding unmanned aerial vehicle of VTOL tail seat |
| CN111452969A (en) * | 2020-04-01 | 2020-07-28 | 北京航空航天大学 | Tailstock type flying wing layout unmanned aerial vehicle capable of taking off and landing vertically |
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Application publication date: 20211019 |