Vertical take-off and landing unmanned aerial vehicle adopting two sets of helicopter mechanisms and two sets of propellers
阅读说明：本技术 采用两套直升机机构和两套螺旋桨的垂直起降无人机 (Vertical take-off and landing unmanned aerial vehicle adopting two sets of helicopter mechanisms and two sets of propellers ) 是由 钱永贵 田正冲 李旭 于 2019-11-06 设计创作，主要内容包括：一种采用两套直升机机构和两套螺旋桨的垂直起降无人机,它包括机身(3),其特征是所述的机身的前部对称设有前左机翼(2)和前右机翼(4),机身的后部设有后左机翼(9)和后右机翼(7),机身的尾部设有垂直尾翼(8),在前左机翼(2)和前右机翼(4)上分别安装有一套直升机机构,在后左机翼(9)和后右机翼(7)上分别安装一套螺旋桨机构；本发明在大幅度提升无人机性能的同时,相比于全部采用四套直升机机构作为动力的机型成本下降1/5以上。(A vertical take-off and landing unmanned aerial vehicle adopting two sets of helicopter mechanisms and two sets of propellers comprises a fuselage (3) and is characterized in that the front part of the fuselage is symmetrically provided with a front left wing (2) and a front right wing (4), the rear part of the fuselage is provided with a rear left wing (9) and a rear right wing (7), the tail part of the fuselage is provided with a vertical tail wing (8), the front left wing (2) and the front right wing (4) are respectively provided with one set of helicopter mechanism, and the rear left wing (9) and the rear right wing (7) are respectively provided with one set of propeller mechanism; the invention greatly improves the performance of the unmanned aerial vehicle, and reduces the cost by more than 1/5 compared with the model which totally adopts four sets of helicopter mechanisms as power.)
1. A vertical take-off and landing unmanned aerial vehicle adopting two sets of helicopter mechanisms and two sets of propellers comprises a fuselage (3) and is characterized in that the front part of the fuselage is symmetrically provided with a front left wing (2) and a front right wing (4), the rear part of the fuselage is provided with a rear left wing (9) and a rear right wing (7), the tail part of the fuselage is provided with a vertical tail wing (8), the front left wing (2) and the front right wing (4) are respectively provided with one set of helicopter mechanism, and the rear left wing (9) and the rear right wing (7) are respectively provided with one set of propeller mechanism; during taking off, the two sets of helicopter mechanisms and the two sets of propeller mechanisms simultaneously provide upward lift force, after the two sets of helicopter mechanisms and the two sets of propeller mechanisms rise to a certain height, the two sets of propeller mechanisms at the back start to slowly tilt forwards, the upward lift force provided by the two sets of helicopter mechanisms is gradually converted into forward tension force, and meanwhile, the two sets of helicopter mechanisms at the front adjust the total pitch according to balance requirements, change the periodic pitch and generate certain forward force; after the unmanned aerial vehicle is converted into a fixed wing mode, the wing lift force reaches a certain value, the front two sets of helicopter mechanisms are tilted into forward tension, and the four sets of propellers provide the forward tension; when descending, the two sets of helicopter mechanisms in the front slowly rotate towards the vertical direction, the two sets of propellers at the back rotate back to the vertical direction after stabilization, the unmanned aerial vehicle is controlled to descend vertically, and the landing positions of the two sets of helicopter mechanisms in the front can be adjusted through periodic variable pitch at the moment.
2. An unmanned aerial vehicle according to claim 1, wherein the two sets of helicopter mechanisms are respectively a left helicopter mechanism and a tilting mechanism (1) and a right helicopter mechanism and a tilting mechanism (5), which are symmetrically arranged along the fuselage (3).
3. An unmanned aerial vehicle according to claim 1, wherein the two sets of propeller mechanisms are a left propeller mechanism and a tilt mechanism (10) and a right propeller mechanism and a tilt mechanism (6) which are symmetrically arranged along the fuselage (3).
4. The unmanned aerial vehicle of claim 1, wherein the front left wing (2), the front right wing (4), the rear left wing (9) and the rear right wing (7) are fixed wing wings, and are provided with ailerons.
Technical Field
The invention relates to an unmanned aerial vehicle, in particular to a special fixed wing unmanned aerial vehicle, and specifically relates to a vertical take-off and landing unmanned aerial vehicle adopting two sets of helicopter mechanisms and two sets of propellers.
Background
At present, in order to guarantee the power and the speed of the fixed-wing unmanned aerial vehicle, people mostly make articles in the aspect of power. However, no matter how the power is improved, a certain risk exists in the conversion process of lifting and flat flying, the stalling phenomenon can occur, and particularly the stalling phenomenon is easier to occur under severe meteorological conditions.
In order to improve power and flexibility, the eagle helicopter in the U.S. provides a more ideal lifting and advancing scheme, but the applicant finds that the larger potential safety hazard still exists by only depending on two sets of helicopter mechanisms and tilting mechanisms which are symmetrically arranged left and right to provide lifting and advancing power, the risk of falling high or stalling can occur, and the problem is basically the continuous reason of accidents of the machine type in recent years. If two sets of auxiliary helicopter mechanisms are added, the lift force of forward flight is provided before the main tilting mechanism tilts, the fuselage is ensured not to descend basically in the tilting forward flight conversion process, and the problem can be solved better. However, the applicant believes that this would greatly increase the manufacturing cost and the complexity of the mechanism and the difficulty of control of the drone, for which no good solution is currently available.
Disclosure of Invention
The invention aims to design a vertical take-off and landing unmanned aerial vehicle adopting two sets of helicopter mechanisms and two sets of propellers, aiming at the problem that an accident is caused by insufficient lift force easily generated in the process of conversion from lifting to forward flying of the existing vertical take-off unmanned aerial vehicle.
The technical scheme of the invention is as follows:
a vertical take-off and landing unmanned aerial vehicle adopting two sets of helicopter mechanisms and two sets of propellers comprises a fuselage 3 and is characterized in that the front part of the fuselage is symmetrically provided with a front left wing 2 and a front right wing 4, the rear part of the fuselage is provided with a rear left wing 9 and a rear right wing 7, the tail part of the fuselage is provided with a vertical tail wing 8, the front left wing 2 and the front right wing 4 are respectively provided with one set of helicopter mechanism, and the rear left wing 9 and the rear right wing 7 are respectively provided with one set of propeller mechanism; during taking off, the two sets of helicopter mechanisms and the two sets of propeller mechanisms simultaneously provide upward lift force, after the two sets of helicopter mechanisms and the two sets of propeller mechanisms rise to a certain height, the two sets of propeller mechanisms at the back start to slowly tilt forwards, the upward lift force provided by the two sets of helicopter mechanisms is gradually changed into forward tension force, and meanwhile, the two sets of helicopter mechanisms at the front adjust the total pitch according to balance requirements and simultaneously change the periodic pitch to generate certain forward force; after the unmanned aerial vehicle is converted into a fixed wing mode, the wing lift force reaches a certain value, and then the front two sets of helicopter mechanisms are tilted into forward tension; when descending, earlier two sets of helicopter mechanisms in the front slowly rotate toward the vertical direction, after being stable, two sets of propellers in the back rotate back to the vertical direction, and the unmanned aerial vehicle is controlled to descend vertically, and the landing positions of the two sets of helicopter mechanisms in the front can be adjusted through periodic variable pitch at the moment.
The two sets of helicopter mechanisms are respectively a left helicopter mechanism and a
The two sets of propeller mechanisms are a left propeller mechanism and a
The front left wing 2, the front right wing 4, the rear left wing 9 and the rear right wing 7 are all fixed wings which are all provided with ailerons.
The invention has the beneficial effects that:
the invention can make the whole transformation process of lifting and forward flying relatively stable and reliable, and the multiple propellers provide forward tension when flying horizontally, thus ensuring higher forward flying speed of the unmanned aerial vehicle; the device can realize take-off and landing under various complex terrains and complex meteorological conditions; and no redundant mechanism exists in two flight states, so that the energy efficiency is effectively improved.
The invention greatly improves the performance of the unmanned aerial vehicle, and reduces the cost by more than 1/5 compared with the model which totally adopts four sets of helicopter mechanisms as power.
The invention has simple structure, easy realization and convenient manufacture, installation and control.
Drawings
Fig. 1 is a schematic structural diagram of a takeoff state of an unmanned aerial vehicle.
Fig. 2 is a schematic diagram of the structure of the invention when two propellers are tilted to provide forward flying power.
Fig. 3 is a schematic structural view of the two helicopter mechanisms and the two propeller mechanisms of the present invention both providing forward flight power.
Detailed Description
The invention is further described below with reference to the figures and examples.
As shown in fig. 1-3.
A vertical take-off and landing unmanned aerial vehicle adopting two sets of helicopter mechanisms and two sets of propellers comprises a fuselage 3, wherein the fuselage is symmetrically provided with four fixed wing wings, namely a front left wing 2 and a front right wing 4 at the front part of the fuselage, a rear left wing 9 and a rear right wing 7 at the rear part of the fuselage, the tail part of the fuselage is provided with a vertical tail wing 8, the four wings are respectively provided with corresponding ailerons for changing flight postures, and the structures and the designs of the ailerons are completely the same as those of the prior art, so that the description is omitted. A set of helicopter mechanisms is respectively arranged on the front left wing 2 and the front right wing 4, namely: the helicopter mechanism comprises a left helicopter mechanism and
The working principle of the invention is as follows: during taking off, the two sets of helicopter mechanisms and the two sets of propeller mechanisms simultaneously provide upward lift force (as shown in figure 1), after the helicopter mechanisms rise to a certain height, the two sets of propeller mechanisms at the back start to slowly tilt forwards, the upward lift force is gradually changed into forward tension force (as shown in figure 2), and meanwhile, the two sets of helicopter mechanisms at the front adjust the total pitch according to the balance requirement, and simultaneously change the periodic pitch to generate certain forward force. After the unmanned aerial vehicle is converted into a fixed wing mode, the wing lift force reaches a certain value, and then the front two sets of helicopter mechanisms are tilted into forward tension (as shown in fig. 3). When descending, the two sets of helicopter mechanisms in the front slowly rotate towards the vertical direction, the two sets of propellers at the back rotate back to the vertical direction after stabilization, the unmanned aerial vehicle is controlled to descend vertically, and the landing positions of the two sets of helicopter mechanisms in the front can be adjusted through periodic variable pitch at the moment.
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