CN204473135U - A kind of change wing formula unmanned plane - Google Patents
A kind of change wing formula unmanned plane Download PDFInfo
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- CN204473135U CN204473135U CN201420845446.XU CN201420845446U CN204473135U CN 204473135 U CN204473135 U CN 204473135U CN 201420845446 U CN201420845446 U CN 201420845446U CN 204473135 U CN204473135 U CN 204473135U
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Abstract
A kind of wing formula unmanned plane that becomes comprises a fuselage; Two wings, every described wing is arranged at described fuselage symmetrically; And at least three screw propellers, every described screw propeller is arranged at described fuselage and every described wing respectively, and the described screw propeller being wherein arranged at every described wing is able to the axial motion of seat relative to described fuselage.
Description
Technical field
The utility model relates to a kind of unmanned plane, and particularly one becomes wing formula unmanned plane, and wherein said change wing formula unmanned plane can need based on different flight, adjusts state of flight.
Background technology
Along with the development of ecommerce, express transportation becomes more and more important.
As everyone knows, in express transportation, vital two factors are exactly time and safety.
When user have purchased commodity, may be eager to take commodity very much.Even without demand eager especially, if see that the commodity delivered in time are also the somethings be in a cheerful frame of mind.In addition on the one hand, the safety of transportation is also most important, and occurred damaged if user sees by the thing sent here, can infer, the mood of user should be not too joyful.
Another kind of situation, user is when posting some smallclothes things or some vital documents, and the requirement for the time can be higher, may need within the extremely short time, deliver to the other side place.Based on posting many-sided factors such as the basic procedure of part, the configuration of human resources and traffic conditions, no matter be carrying the commodity bought or the object of being eager mailing, always the time has no idea to accomplish immediately.
For such present situation, each large-scale express company is devoted to the research of unmanned plane transport.Namely existing various Multi-axis aircraft is the trial in unmanned plane transport.In general, the structure of Multi-axis aircraft is, by multiple cross-coupled axle, forms flight wing.The end of each wing arranges a screw propeller, as actuating unit.Wing cross connection position i.e. center-of-gravity position are as carrying cargo position.But due to the constructional feature of himself, there are problems in this Multi-axis aircraft.
Due to the structure of Multi-axis aircraft sub-circular, do not meet aerodynamic Streamline Design, make it in flight course, the resistance be subject to is larger, the power that take-off process needs is also comparatively large, and the electric energy therefore consumed is more, there is the distinct disadvantage that cruise duration is short, voyage is short.
Correspondingly, for such problem, also occur imitating large aircraft and the three axle unmanned planes that design.Existing three axle unmanned planes, general structure adopts canard configuration, and comprise a main wing and two groups of canards, two groups of canards are vertically connected at main wing side by side.Such unmanned plane is relative to Multi-axis aircraft, in structure, two kinds of new shapes of identical scale, the resistance that canard configuration is subject to relative to Multi-axis aircraft is less, more meet air to take offence principle, therefore, under the condition with identical power source, flying power and the voyage of three axle unmanned planes of canard configuration have relative improvement.Three axle unmanned planes of existing canard configuration improve some aspect, but still there is a lot of problem.
First, although Multi-axis aircraft structure does not have stream line pattern, due to its multiaxis feature, a screw propeller is installed as propulsion source in the end of each axle, therefore multiaxis also just has more propulsion source, therefore three axle unmanned planes of canard configuration are adopted, due to the change of its structure, meeting on aerodynamic basis, the position can installing screw propeller is less, and the size of lift is relevant by the size of aircraft taxi process medium velocity, therefore must have certain to slide place, make it reach certain speed, can take off.On the other hand, the air resistance in the flight course structurally reduced, the propulsion source that can be to provide reduces, in cruise duration and voyage, therefore still there is the place had much room for improvement.
On the other hand, the unmanned plane of existing a kind of canard configuration, install screw propeller in canard both sides as propulsion source, as noted earlier, such unmanned plane, the propulsion source provided is less, is taking off and is all having more highly difficult in flight course.
In addition, in order to snap catch, in prior art, there is a kind of change wing formula unmanned plane, screw propeller is arranged on canard both sides, and the both sides of canard can be rotated in certain angle.Taking off, flight, and in the process of landing, canard is in different states, thus change the direction that screw propeller provides power, therefore improve the performance of the unmanned plane of canard configuration to a certain extent., there is the problem of several aspect in this change wing formula unmanned plane equally.
First, helicopter and Multi-axis aircraft are because its propulsion source installed is generally all directly over fuselage, therefore can take off in less distance and can realize vertical takeoff and landing in other words, the unmanned plane of this canard configuration, due to the position of its propulsion source provided and the fuselage shape of elongation, makes it must have certain coasting distance, it is made to arrive certain speed, there is provided lift just can take off by wing, therefore can not realize vertical takeoff and landing, be unsuitable for the flight of little place.
Secondly, the aircraft of this canard configuration is insensitive for course control.That is, changed course by the speed of the screw propeller changing wing both sides, the speed of adjustment is comparatively slow, affects the particularity of vector.
3rd, the aircraft of this canard configuration can not realize the pitch control subsystem of end.That is, in the change of vertical flying height, adjustable scope is very little, and may arrive after a certain flying height carries out, need flying height or the heading of flip-flop aircraft, this situation is then difficult to realize.
The merits and faults that the various small aircrafts existed in comprehensive prior art exist, the utility model is started with from above-mentioned each side Problems existing, expects to obtain a kind of unmanned plane being more suitable for application in small freight transport.
Utility model content
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, and wherein said change wing formula unmanned plane can need based on different flight, adjusts state of flight.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, and wherein said change wing formula unmanned plane can carry out landing in any place being suitable for landing, to expand the range of use of described change wing formula unmanned plane.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, and wherein said change wing formula unmanned plane has longer flying power, is suitable for the flight of long distance to make described change wing formula unmanned plane.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, relative to the aircraft of prior art, described change wing formula unmanned plane can have the flight characteristic of the distinctive stability of Multi-axis aircraft, when also can have a long boat, the flight characteristic of the Fixed Wing AirVehicle such as long-distance flight and high pneumatic efficiency, thus, described change wing formula unmanned plane is not needing, under the prerequisite increasing deadweight, to have good state of flight.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, wherein said change wing formula unmanned plane can adjust state of flight rapidly, the adjustment especially described change wing formula unmanned plane can realize rapidly from level flight condition to hovering flight state.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, wherein said change wing formula unmanned plane provides multiple screw propeller, by the cooperation of every described screw propeller, the state of flights such as described change wing formula unmanned plane can realize such as turning, dive, new line, and the flight alerting ability of described change wing formula unmanned plane can be ensured effectively.Such as, the turning of described change wing formula unmanned plane can be realized by the differential (speed discrepancy, namely every described screw propeller has different rotating speeds) of every described screw propeller.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, the described screw propeller being wherein installed on a fuselage of described change wing formula unmanned plane can be a contrarotating propeller, like this, the performance of having a smooth flight of described change wing formula unmanned plane accesses guarantee, to guarantee the flight safety of described change wing formula unmanned plane.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, and the layout of wherein said change wing formula unmanned plane is similar to the spatial layout feature of traditional canard vehicle, and its performance of having a smooth flight accesses and effectively ensures.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, and wherein said change wing formula unmanned plane, under high-incidence condition, has higher anti-stall ability.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, and wherein said change wing formula unmanned plane is particularly suitable for the air transport of shipping parcels.
An object of the present utility model is that providing a kind of becomes wing formula unmanned plane, wherein load can act on the lower position of described change wing formula unmanned plane center of gravity, have higher hovering degree of stability, by such mode, the flight safety of described change wing formula unmanned plane is ensured.
An object of the present utility model is to provide a kind of and becomes wing formula unmanned plane, and the described change wing formula unmanned plane wherein more than two framves or two framves can collaborative work, to realize the transport of the goods of the large scale of construction.In other words, become wing formula unmanned plane described in multi rack and can have good cooperative ability.
In order to achieve the above object, the utility model provides a kind of and becomes wing formula unmanned plane, and it comprises:
One fuselage;
Two wings, every described wing is arranged at described fuselage symmetrically; And
At least three screw propellers, every described screw propeller is arranged at described fuselage and every described wing respectively, and the described screw propeller being wherein arranged at every described wing is able to seat and does axial motion relative to described fuselage.
According to a preferred embodiment of the present utility model, described change wing formula unmanned plane also comprises an engine installation, and described engine installation is arranged at described fuselage, and every described screw propeller is respectively coupled to described engine installation.
According to a preferred embodiment of the present utility model, described change wing formula unmanned plane also comprises a toter, described toter is arranged at described fuselage, and the center of the described toter point of action and described fuselage that act on described fuselage is in same vertical direction.
According to a preferred embodiment of the present utility model, described change wing formula unmanned plane also comprises a lifting gear, and described lifting gear is arranged at the below of described fuselage.
According to a preferred embodiment of the present utility model, every described screw propeller is optionally arranged at middle part or the end of described wing.
According to a preferred embodiment of the present utility model, every described wing comprises a connecting wing and an adjustment wing respectively, every described connecting wing is arranged at described fuselage, and every described adjustment wing is arranged at every described connecting wing rotationally, and every described screw propeller is arranged at every described connecting wing respectively.
According to a preferred embodiment of the present utility model, every described wing comprises a connecting wing and an adjustment wing respectively, every described connecting wing is arranged at described fuselage, and every described adjustment wing is arranged at every described connecting wing rotationally, and every described screw propeller is arranged at every described adjustment wing respectively.
According to a preferred embodiment of the present utility model, every described screw propeller is had speed discrepancy.
According to a preferred embodiment of the present utility model, the described screw propeller being arranged at described fuselage is a contrarotating propeller.
According to a preferred embodiment of the present utility model, every described screw propeller comprises at least one blade respectively, and every described blade has a bow oar face and a face of blade respectively, and the curvature in described bow oar face is greater than the curvature of described face of blade.
According to an aspect of the present utility model, it also provides a kind of and becomes wing formula unmanned plane, and it comprises:
One fuselage;
At least two screw propellers; And
Two wings, every described wing comprises a connecting wing and an adjustment wing respectively, wherein every described connecting wing is arranged at described fuselage symmetrically, every described adjustment wing is arranged at every described connecting wing respectively rotationally, and every described screw propeller is optionally arranged at every described connecting wing or every described adjustment wing.
According to a preferred embodiment of the present utility model, a described screw propeller is arranged at described fuselage, and described screw propeller is a contrarotating propeller.
According to a preferred embodiment of the present utility model, every described screw propeller is had speed discrepancy.
According to a preferred embodiment of the present utility model, every described screw propeller comprises at least one blade respectively, and every described blade has a bow oar face and a face of blade respectively, and the curvature in described bow oar face is greater than the curvature of described face of blade.
According to a preferred embodiment of the present utility model, described change wing formula unmanned plane also comprises an engine installation, and described engine installation is arranged at described fuselage, and every described screw propeller is respectively coupled to described engine installation.
According to a preferred embodiment of the present utility model, described change wing formula unmanned plane also comprises a toter, described toter is arranged at described fuselage, and the center of the described toter point of action and described fuselage that act on described fuselage is in same vertical direction.
According to a preferred embodiment of the present utility model, described change wing formula unmanned plane also comprises a lifting gear, and described lifting gear is arranged at the below of described fuselage.
According to an aspect of the present utility model, it also provides a kind of flying method becoming wing formula unmanned plane, described change wing formula unmanned plane comprises a fuselage and is arranged at a wing of described fuselage symmetrically, wherein said method comprises the screw propeller making to be arranged at respectively every described wing and adjusts in the horizontal direction and between vertical direction, to change the state of flight of described change wing formula unmanned plane.
According to a preferred embodiment of the present utility model, in the above-mentioned methods, also comprise step:
A () provides the connecting wing being arranged at described fuselage symmetrically;
B () provides the adjustment wing being arranged at every described connecting wing rotationally, every described connecting wing and every described adjustment wing form every described wing respectively, and every described screw propeller is optionally arranged at every described connecting wing or every described adjustment wing; And
C () makes every described adjustment wing in described horizontal direction and the adjustment of described vertical direction.
According to a preferred embodiment of the present utility model, in the above-mentioned methods, a described screw propeller is set in described fuselage, and described screw propeller is a contrarotating propeller.
According to a preferred embodiment of the present utility model, in the above-mentioned methods, every described screw propeller is made to produce speed discrepancy.
According to a preferred embodiment of the present utility model, in the above-mentioned methods, every described screw propeller is made to produce speed discrepancy.
According to a preferred embodiment of the present utility model, every described screw propeller comprises at least one blade respectively, and every described blade has a bow oar face and a face of blade respectively, and the curvature in described bow oar face is greater than the curvature of described face of blade.
Accompanying drawing explanation
Fig. 1 is the schematic perspective view according to a preferred embodiment of the present utility model.
Fig. 2 is the schematic perspective view according to an above preferred embodiment of the present utility model variant embodiment.
Fig. 3 is the schematic perspective view at a visual angle according to another preferred embodiment of the present utility model.
Fig. 4 is the schematic perspective view at the another visual angle according to above preferred embodiment of the present utility model.
Fig. 5 is the landing view of the change wing formula unmanned plane according to above preferred embodiment of the present utility model.
Fig. 6 is the floating state schematic diagram of the change wing formula unmanned plane according to above preferred embodiment of the present utility model.
Fig. 7 is the adjustment process schematic diagram of the state of change wing formula unmanned plane from hovering flight to horizontal flight according to above preferred embodiment of the present utility model.
Fig. 8 is the level flight condition schematic diagram of the change wing formula unmanned plane according to above preferred embodiment of the present utility model.
Fig. 9 A and Fig. 9 B is at the schematic diagram of state of bowing, face upward respectively according to the change wing formula unmanned plane of above preferred embodiment of the present utility model.
Figure 10 is according to the change wing formula unmanned plane of the above preferred embodiment of the present utility model schematic diagram at side steering state.
Figure 11 is the schematic diagram of a kind of operational mode of change wing formula unmanned plane according to above preferred embodiment of the present utility model.
Figure 12 is the schematic diagram of a kind of mode of change wing formula unmanned plane according to above preferred embodiment of the present utility model.
Detailed description of the invention
Below describe and realize the utility model for disclosing the utility model to enable those skilled in the art.Preferred embodiment in below describing only as an example, it may occur to persons skilled in the art that other apparent modification.The groundwork of the present utility model defined in the following description can be applied to other embodiments, deformation program, improvement project, equivalent and not deviate from the other technologies scheme of spirit and scope of the present utility model.
The change wing formula unmanned plane according to a preferred embodiment of the present utility model as shown in Figure 1, it can be applied to the multiple different industries such as such as logistics transportation, because described change wing formula unmanned plane can need to adjust between different states based on flight, thus described change wing formula unmanned plane can improve efficiency and the safety of goods transportation.Those skilled in the art should be appreciated that according to actual needs, and described change wing formula unmanned plane can also be applied to other industry and field, therefore, can not being regarded as the restriction to content of the present utility model and scope at above-mentioned lifted example.
Specifically, described change wing formula unmanned plane comprises the component of fuselage 10, two wing 20, at least two screw propeller 30 and other necessity, wherein every described wing 20 is arranged at described fuselage 10 symmetrically, and every described screw propeller 30 is arranged at described fuselage 10 and every described wing 20 respectively.Such as, in this embodiment of the present utility model, the quantity of described screw propeller 30 may be implemented as three, wherein every described screw propeller 30 can be respectively set at described fuselage 10 and every described wing 20, by such mode, the balance quality of described change wing formula unmanned plane under state of flight accesses and effectively ensures, thus, guarantee the flight safety of described change wing formula unmanned plane.
It is worth mentioning that, in other example, described change wing formula unmanned plane can also comprise two aileron 210 and empennages 220, wherein every described aileron 210 is arranged at the front portion of described fuselage 10 symmetrically, described empennage 220 is arranged at the rear portion of described fuselage 10, and every described aileron 210 and every described wing 20 have identical bearing of trend, to make every described aileron 210, every described wing 20 and described fuselage 10 form the agent structure of described change wing formula unmanned plane, by such mode, in embodiments more of the present utility model, described change wing formula unmanned plane can have the structure of traditional aircraft, such as, described change wing formula unmanned plane can have canard configuration's structure, to guarantee that described change wing formula unmanned plane has good balance and stability when flying, thus ensure the safety of flight.Preferably, described empennage 220 is arranged on the upside of the afterbody of described fuselage 10, to balance the momentum of described change wing formula unmanned plane.
It is worth mentioning that, every described aileron 210 is arranged at the front portion of described fuselage 10, every described wing 20 is arranged at the rear portion of described fuselage 10, and the size of every described aileron 210 is less than the size of every described wing 20, thus, when described change wing formula unmanned plane is in state of flight, every described aileron 210 can be used in collaborative every described wing 20 and provides lift to described change wing formula unmanned plane.
Further, in embodiments more of the present utility model, every described wing 20 has upper side 201 and a downside 202, the curvature of wherein said upper side 201 is preferably greater than the curvature of described downside 202, in other words, the degree of convexity of described upper side 201 is greater than the degree of convexity of described downside 202, by such mode, on the one hand, the resistance of air for the described change wing formula unmanned plane be under state of flight can be reduced, thus, described change wing formula unmanned plane is made to have the speed of a ship or plane and farther flying distance faster, on the other hand, every described wing 20 can also be made to have better lift.It is worth mentioning that, every described aileron 210 also can have the structure of every described wing 20, thus, make described change wing formula unmanned plane during flying safer, reliable.
Generally, the formalness of aircraft and its state of flight have close relevance, such as, the configuration of aircraft and layout can be related to flight characteristic and the airworthiness of aircraft, traditionally, needs time in order to meet different, the formalness of dissimilar aircraft can be different, such as, in this embodiment of the present utility model, described change wing formula unmanned plane can form traditional canard configuration's structure, by such mode, described change wing formula unmanned plane can be made to do such as facing upward of large intensity, during the action of the manoevreabilitys such as tight spiral, the every described aileron 210 of described change wing formula unmanned plane and every described wing 20 all can produce and make described change wing formula unmanned plane ambient air form powerful eddy current, intercoupling between the eddy current of varying strength can strengthen its lift produced.Especially under the state being in At High Angle of Attack at described change wing formula unmanned plane, every described aileron 210 needs reduce generation lift can make described change wing formula aircraft produce nose-down pitching moment, thus, effectively ensure the controllability of the suppressed excessive new line of described change wing formula unmanned plane be under At High Angle of Attack state.Therefore, in specific embodiment of the present utility model, adopt the described change wing formula unmanned plane of canard configuration can make it have better controllability.
However, those skilled in the art should be appreciated that described change wing formula unmanned plane can also have the layout of other types, to meet different flight needs in other embodiment of the present utility model.Therefore, adopt the described change wing formula unmanned plane of canard configuration only to describe the advantage of described change wing formula unmanned plane as an example, it is not as the restriction to content of the present utility model and scope.
As shown in Figure 1, it is the described change wing formula unmanned plane according to a preferred embodiment of the present utility model, the described screw propeller 30 being wherein arranged at described fuselage 10 is defined as a fuselage screw propeller 31, accordingly, the every described screw propeller 30 being arranged at every described wing 20 is defined as a wing screw propeller 32, is understandable that, in various embodiments, described fuselage screw propeller 31 can be consistent with the type of every described wing screw propeller 32, also can be inconsistent.Such as, in this embodiment, every described wing screw propeller 32 can have the structure of traditional screw propeller, and described fuselage screw propeller 31 is implemented as a contrarotating propeller 31, to strengthen the airworthiness of described change wing formula unmanned plane.
Wherein every described wing screw propeller 32 is arranged at every described wing 20 respectively rotationally, can do axial motion relative to described fuselage 10 to make every described wing screw propeller 32.Specifically, setting described fuselage 10 direction is horizontal direction, setting height direction is vertical direction, in this embodiment of the present utility model, every described wing screw propeller 32 can adjust between described horizontal direction and described vertical direction, to change the state of flight of described change wing formula unmanned plane, thus, realize described change wing formula unmanned plane and adjust between horizontal flight and the state of hovering flight.That is, in the utility model, the every described screw propeller 30 being arranged at every described wing 20 is done the axial motion relative to described fuselage 10, when being in described horizontal direction to make every described screw propeller 30, described change wing formula unmanned plane can fly rapidly with level flight condition, when every described screw propeller 30 is in described vertical direction, described change wing formula unmanned plane can fly with hovering flight state.Relative to the aircraft of prior art, described change wing formula unmanned plane has significant progress.
It is worth mentioning that, in this embodiment as described in Figure 1, every described wing screw propeller 32 can be arranged at the end of every described wing 20; In this embodiment as described in Figure 2, every described wing screw propeller 32 can also be arranged at the middle part of every described wing 20.In other words, every described wing screw propeller 32 optionally can be arranged at end or the middle part of every described wing 20, like this, the topology layout of described change wing formula unmanned plane can be made can be selected based on needs.Should be understood that, every described wing screw propeller 32 in other examples, can also be arranged at other any can effective position, and guarantee that every described wing screw propeller 32 can adjust in described horizontal direction and described vertical direction.
It is worth mentioning that, by the differential (speed discrepancy of described fuselage screw propeller 31 and every described wing screw propeller 32, namely every described screw propeller 30 can have different rotating speeds), described change wing formula unmanned plane can also be made easily to realize the adjustment of state of flights such as such as turning to, to improve the alerting ability of described change wing formula unmanned plane under state of flight.
Be the change wing formula unmanned plane according to another preferred embodiment of the present utility model as shown in Figure 3 and Figure 4, relative to above preferred embodiment, described change wing formula unmanned plane can realize the adjustment of the state from the state of horizontal flight to hovering flight rapidly.
Specifically, every described wing 20 comprises connecting wing 21 and an adjustment wing 22 respectively, wherein every described connecting wing 21 is arranged at described fuselage 10, every described adjustment wing 22 is connected to every described connecting wing 21 respectively rotationally, such as, in this embodiment, every described connecting wing 21 is every described wing 20 parts near described fuselage 10, and every described adjustment wing 22 is every described wing 20 parts away from described fuselage 10.By adjusting the direction of every described adjustment wing 22, described change wing formula unmanned plane can be enable to realize the fast speed adjustment of the state from the state of horizontal flight to hovering flight, described change wing formula unmanned plane also can be enable to realize the adjustment of the state from the state of hovering flight to horizontal flight.In embodiments more of the present utility model, every described wing screw propeller 32 can be arranged at every described connecting wing 21, by driving every described wing screw propeller 32 to adjust to described vertical direction with every described adjustment wing 22 from described horizontal direction respectively, described change wing formula unmanned plane can be enable to realize the fast speed adjustment of the state from the state of horizontal flight to hovering flight.In other embodiments of the present utility model, every described wing screw propeller 32 can also be arranged at every described adjustment wing 22, like this, every described wing screw propeller 32 can be synchronously driven to adjust to described vertical direction with every described adjustment wing 22 from described horizontal direction, to enable the state of flight of described change wing formula unmanned plane faster and adjusted more easily, thus improve controllability and the alerting ability of described change wing formula unmanned plane.
Preferably, every described wing screw propeller 32 is parallel with the every described adjustment wing 22 of correspondence position respectively, and specifically, when every described wing screw propeller 32 is in described horizontal direction, every described adjustment wing 22 is also positioned at described horizontal direction; Correspondingly, when every described wing screw propeller 32 is in described vertical direction, every described adjustment wing 22 is also positioned at described vertical direction, because every described wing screw propeller 32 is arranged at every described adjustment wing 22, when driving every described adjustment wing 22 to rotate, every described wing screw propeller 32 can automatically rotate, in other words, and the synchronized movement of every described wing screw propeller 32 and every described adjustment wing 22.
Further, every described screw propeller 30 also comprises at least one blade 33, the every described screw propeller 30 that every described blade 33 is formed can form an axle simultaneously, to make every described blade 33 can both with described axle for axle rotates, it is worth mentioning that, the described screw propeller 30 of diverse location can have the every described blade 33 of identical quantity and same structure combination, also can have the every described blade 33 of varying number or different structure combination.Such as, in this example shown in Fig. 3 and Fig. 4, the quantity of the described blade 33 of described fuselage screw propeller 31 can be six, wherein every two described blades 33 are arranged overlappingly, to form the starching of described fuselage screw propeller 31 and lower slurry, the quantity of the described blade 33 of every described wing screw propeller 32 can be two, thus, make described fuselage screw propeller 31 and every described wing screw propeller 32 can have different functions.Those skilled in the art are to be understood that, the explanation of the type of described fuselage screw propeller cited by above-mentioned example 31 and every described wing screw propeller 32 only exemplarily property, in other examples, described fuselage screw propeller 31 and every described wing screw propeller 32 can also have other structure, therefore, it can not be regarded as the restriction to content of the present utility model and scope.
Described change wing formula unmanned plane also comprises an engine installation 40, described engine installation 40 is arranged at described fuselage 10, propulsion source is provided for for described change wing formula unmanned plane, wherein every described screw propeller 30 can be coupled to described engine installation 40, in the process of described change wing formula unmanned plane during flying, described engine installation 40 is by driving the rotation of every described screw propeller 33, to realize the different state of flight of described change wing formula unmanned plane, be understandable that, the flight that described engine installation 40 is similarly described change wing formula unmanned plane provides propulsion source.Especially, described engine installation 40 can make every described screw propeller 33 have different rotating speeds to make to produce velocity contrast between every described screw propeller 32 respectively, to form the differential between every described screw propeller 30, such as, by changing the rotating speed of described fuselage screw propeller 31, described change wing formula unmanned plane can be made to make the flare maneuver coming back or dive, by making every described wing screw propeller 32, there is different rotating speeds, described change wing formula unmanned plane can be assisted to perform corresponding actions such as turning, by such mode, the state of flight that described change wing formula unmanned plane is different can be adjusted, thus, improve the alerting ability of described change wing formula unmanned plane.
In this embodiment of the utility model, described fuselage screw propeller 31 may be implemented as described contrarotating propeller 31 equally, wherein said contrarotating propeller 31 is coupled to described engine installation 40, described engine installation 40 can drive described contrarotating propeller 31 to rotate, and described engine installation 40 can control the rotating speed of described contrarotating propeller 31.In other words, by described engine installation 40, described fuselage screw propeller 31 and every described wing screw propeller 32 that can make to be implemented as described contrarotating propeller 31 have identical or different rotating speed, adjust the state of flight of described change wing formula unmanned plane synergistically, thus, strengthen the performance such as such as flight alerting ability, having a smooth flight property, flight safety of described change wing formula unmanned plane.
It is worth mentioning that, by adjusting the position of every described screw propeller 30 and every described adjustment wing 22, described change wing formula unmanned plane can be made to have different state of flights, in the example such as shown in Fig. 5 to Figure 10, the utility model is arranged at this specific embodiment of every described adjustment wing 22 with every described wing screw propeller 32, describe every described wing screw propeller 32 and the particular case of every described adjustment wing 22 under different states, to content of the present utility model and advantage, there is further understanding to make those skilled in the art.
In the utility model, when every described adjustment wing 22 and every described wing screw propeller 32 are adjusted to described vertical direction from described horizontal direction and adjusted to described horizontal direction from described vertical direction, described change wing formula unmanned plane has different states.Such as, in an embodiment of the present utility model, when the every described adjustment wing 22 of described change wing formula unmanned plane and every described wing screw propeller 32 start flight course to be in described horizontal direction into inceptive direction, the process that described change wing formula unmanned plane experiences can be but be not limited on " ground-take off-horizontal flight-come back or bow-side direction turning-hovering-horizontal flight-landing-ground "; Accordingly, when the every described adjustment wing 22 of described change wing formula unmanned plane and every described wing screw propeller 32 start flight course to be in described vertical direction into inceptive direction, the process that described change wing formula unmanned plane experiences can be but be not limited on " ground-take off-hover-horizontal flight-bow or come back-side direction turning-hovering-landing-ground ".Be understandable that, no matter described change wing formula unmanned plane starts flight with which kind of state, and described change wing formula unmanned plane can adjust, to meet different flight needs in the process of flight between horizontal flight and the state of hovering flight.Those skilled in the art are to be understood that, with the described change wing formula unmanned plane that different initial condition carries out flying, different requirements is had for place, such as, when described change wing formula unmanned plane flies into initial condition with described vertical direction with the described adjustment wing 22 and described wing screw propeller 32, described change wing formula unmanned plane can realize vertical taking off, certainly, described change wing formula unmanned plane also can realize vertical landing, like this, the landing action of described change wing formula unmanned plane can be subject to the restriction of flying field as few as possible, it allows the action of taking off on little place and landing.
In describing below of the present utility model, be described in detail by with the every described adjustment wing 22 of described change wing formula unmanned plane and every described wing screw propeller 32 to be in described vertical direction into the flight course of inceptive direction to described change wing formula unmanned plane and to disclose.
As shown in Figure 5, when described change wing formula unmanned plane need by stop at ground take off vertically time, namely described change wing formula unmanned plane with described vertical direction into inceptive direction start to perform flare maneuver time, first every described adjustment wing 22 and every described wing screw propeller 32 can be adjusted to described vertical direction from described horizontal direction, now, every described adjustment wing 22 can perpendicular to every described connecting wing 21, and described engine installation 40 can drive the every described blade 33 of described fuselage screw propeller 31 and every described wing screw propeller 32 to rotate respectively.
Such as, the space defined residing for described change wing formula unmanned plane is XYZ axis, and wherein definition X axis and Y-axis are described horizontal direction, and definition Z-axis direction is described vertical direction.When described change wing formula unmanned plane needs to produce flare maneuver upwards, the described adjustment wing 22 and every described wing screw propeller 32 are all in described vertical direction, accordingly, the every described blade 33 of described fuselage screw propeller 31 and every described wing screw propeller 32 can with described axle for axle rotates in described horizontal direction.In the process of every described blade 33 high speed rotating of described fuselage screw propeller 31 and every described wing screw propeller 32, the front slurry face of every described blade 33 and rear slurry face can be subject to the antagonistic force from air respectively, in the utility model, front slurry face and the rear slurry face of every described blade 33 have different curvature, the curvature in the front slurry face of such as every described blade 33 is preferably greater than the curvature in rear slurry face, now, the air rate in the front slurry face of every described blade 33 can be greater than the air rate in the rear slurry face of corresponding described blade 33, thus, the air pressure that the rear slurry face that the air pressure that the front slurry face of every described blade 33 is subject to is greater than corresponding described blade 33 is subject to, before every described blade 33, slurry face and rear slurry face can form the difference that upwards pressure forward, and this difference of pressure can based on upwards, thus provide lift forward and upwards to described change wing formula unmanned plane, substantially vertical take-off process is realized to drive described change wing formula unmanned plane.And in this process, the starching of described fuselage screw propeller 31 and lower slurry rotate with contrary direction under the driving of described engine installation 40, provide lift upwards to described change wing formula unmanned plane with collaborative every described wing screw propeller 32.
In addition, in this process, the every described adjustment wing 22 being in described vertical direction can be subject to the air resistance of described horizontal direction, be understandable that, because the increase of area of thrust surface, every described adjustment wing 22 can be greater than its air resistance be subject in described horizontal direction at the air resistance that described vertical direction is subject to.
Specifically, after analyzing the stressing conditions of described change wing formula unmanned plane in whole process, those skilled in the art should know, when every described adjustment wing 22 is in described vertical direction, lift obliquely, simultaneously described change wing formula unmanned plane that described change wing formula unmanned plane is mainly subject to described fuselage screw propeller 31 and every described wing screw propeller 31 and provides are subject to the air resistance of described horizontal direction and have gravity because of the deadweight of described change wing formula unmanned plane.When the rotating speed adjusting described fuselage screw propeller 31 and every described wing screw propeller 32 changes lift obliquely, the air resistance of the described horizontal direction that described change wing formula unmanned plane is subject to also can change accordingly.In this process, after lift obliquely decomposes, the power of described horizontal direction and described change wing formula unmanned plane be subject to balance each other at the air resistance of described horizontal direction and be greater than the gravity of described change wing formula unmanned plane in the power of described vertical direction time, described change wing formula unmanned plane can vertically upward movement, thus described change wing formula unmanned plane can realize taking off vertically.
As shown in Figure 7, at described change wing formula unmanned plane in the state of flight, when the every described adjustment wing 22 of described change wing formula unmanned plane and every described wing screw propeller 32 are adjusted to described horizontal direction by the described vertical direction from initial condition, now, every described adjustment wing 22 can be consistent with the direction of every described connecting wing 21, equally, described engine installation 40 still can drive described fuselage screw propeller 31 and every described wing screw propeller 32 to rotate.
Specifically, in this process, the every described adjustment wing 22 and every described wing screw propeller 32 of described change wing formula unmanned plane are adjusted to described horizontal direction by from described vertical direction, and now, the every described blade 33 of described wing screw propeller 32 can in described vertical direction high speed rotating.More particularly, in the process of every described blade 33 high speed rotating of every described wing screw propeller 32, the front slurry face of every described blade 33 and rear slurry face all can be subject to the pressure of the air of relevant position.It is same because the curvature in the front slurry face of every described blade 33 is greater than the curvature in the rear slurry face of corresponding described blade 33, the air rate in the front slurry face of every described blade 33 is greater than the air rate in the rear slurry face of corresponding described blade 33, thus, the air pressure that the front slurry face of every described blade 33 is subject to can be greater than the air pressure in the rear slurry face of corresponding described blade 33, now, can starch between face and rear slurry face before every described blade 33 and form difference of pressure downward backward, and based on backward.In this process, described change wing formula unmanned plane can be subject to air effect in the antagonistic force of every described blade 33, to provide described change wing formula unmanned plane power forward.And in this process, the starching of described fuselage screw propeller 31 and lower slurry rotate with contrary direction under the driving of described engine installation 40, provide lift upwards to described change wing formula unmanned plane with collaborative every described wing screw propeller 32.
It is worth mentioning that, in this process, every described connecting wing 21 and the every described adjustment wing 22 being in described horizontal direction are mainly subject to the lift of described vertical direction.
Specifically, after analyzing the stressing conditions of described change wing formula unmanned plane in whole process, those skilled in the art should know, when every described adjustment wing 22 is in described horizontal direction, described change wing formula unmanned plane is mainly subject to the gravity that lift upwards that every described wing 20 provides, described change wing formula unmanned plane can be subject to the air resistance of described horizontal direction, described change wing formula unmanned plane can be subject to air forward antagonistic force and described change wing formula unmanned plane can be subject to described vertical direction.Mainly change the application force of described horizontal direction at the every described wing screw propeller 32 of adjustment, adjust after described fuselage screw propeller 31 changes lift obliquely, the resistance of the described horizontal direction that described change wing formula unmanned plane is subject to also can change accordingly.And when the force balance of the described horizontal direction that described change wing formula unmanned plane is subject to and described vertical direction, described change wing formula unmanned plane can keep horizontal flight.
Those skilled in the art should know, when every described adjustment wing 22 and every described wing screw propeller 32 are in described level attitude, described fuselage screw propeller 31 can provide more propulsion source, and every described wing screw propeller 32 also can provide auxiliary propulsion source, to enable described change wing formula unmanned plane realize the longer time, fly more at a distance, and described change wing formula unmanned plane can be made to have higher pneumatic efficiency.It is worth mentioning that, in this state, especially described change wing formula unmanned plane is when the flight of At High Angle of Attack, every described aileron 210 can prior to the stall of every described wing 20, now, the front portion of described fuselage 10 can automatic nutation, therefore, relative to traditional Fixed Wing AirVehicle, described change wing formula unmanned plane has higher anti-stall ability.
Accordingly, in the state of flight of described change wing formula unmanned plane in the process adjusted from horizontal flight to hovering flight, every described adjustment wing 22 and every described wing screw propeller 32 can be adjusted to described vertical direction from described horizontal direction, now, the described adjustment wing 22 can perpendicular to described connecting wing 21.The every described blade 33 of described wing screw propeller 32 can rotate in described horizontal direction, and in the process of every described blade 33 high speed rotating, the front slurry face of every described blade 33 and rear slurry face all can be subject to the pressure of air.And because the curvature of starching face before every described blade 33 is greater than the curvature in rear slurry face, therefore, the air pressure that every described blade 33 front slurry face is subject to or be greater than the air pressure in rear slurry face of corresponding described blade 33, thus, the difference that upwards pressure forward is formed between slurry face and rear slurry face before described blade 33, and based on upwards, to provide described change wing formula unmanned plane lift forward and upwards.
In addition, in this process, the every described adjustment wing 22 being in described vertical direction can be subject to the air resistance of described horizontal direction, is understandable that, every described adjustment wing 22 can be greater than its air resistance be subject in described horizontal direction at the air resistance that described vertical direction is subject to.
Specifically, after analyzing the stressing conditions of described change wing formula unmanned plane in whole process, those skilled in the art should know, when every described adjustment wing 22 is in described vertical direction, described change wing formula unmanned plane is mainly subject to the lift obliquely that described fuselage screw propeller 31 and every described wing screw propeller 31 provide, described change wing formula unmanned plane can be subject to the air resistance of described horizontal direction and have gravity because of the deadweight of described change wing formula unmanned plane.When the rotating speed adjusting described fuselage screw propeller 31 and every described wing screw propeller 32 changes lift obliquely, the air resistance of the described horizontal direction that described change wing formula unmanned plane is subject to also can change accordingly.After lift obliquely decomposes, the power of described horizontal direction and described change wing formula unmanned plane be subject to balance each other at the air resistance of described horizontal direction and balance each other in the power of described vertical direction and the gravity of the described change wing formula unmanned plane time, described change wing formula unmanned plane can not move to any direction, thus, described change wing formula unmanned plane is made to realize the state of flight of hovering flight, as shown in Figure 6.
It is worth mentioning that, at every described adjustment wing 22 from described horizontal direction to the process that described vertical direction adjusts, the air resistance that every described adjustment wing 22 is subject to can increase due to the increase of area of thrust surface, now, the flying speed of described change wing formula unmanned plane can be greatly affected, to such an extent as to enable described change wing formula unmanned plane be adjusted to the state of flight of low speed rapidly from state of flight at a high speed, and finally realize hovering flight, thus, make described change wing formula unmanned plane have stable flight characteristic.Relative to the Multi-axis aircraft of prior art, described change wing formula unmanned plane has significant progress.
As shown in fig. 9 a and fig. 9b, when the state of flight of described change wing formula unmanned plane is adjusted to from hovering flight the state of flight coming back or bow, now, action up or down can be made in the front portion of the described fuselage 10 of described change wing formula unmanned plane, when described change wing formula unmanned plane is in hovering flight state, by adjusting the rotating speed of described fuselage screw propeller 31 and every described wing screw propeller 32, to make described fuselage screw propeller 31 and every described wing screw propeller 32, there is different rotating speeds, thus between described fuselage screw propeller 31 and every described wing screw propeller 32, there is relative differential, make described change wing formula unmanned plane in described vertical direction by force unbalance, to make resultant direction up or down, thus, described change wing formula unmanned plane is made to realize bowing and nose-up pitching moment, now, described change wing formula unmanned plane can realize flight up and down.
Such as, when described fuselage 10 needs to produce moment upwards, described fuselage screw propeller 31 and every described wing screw propeller 32 is made to have different rotating speeds by described engine installation 40, it is made to occur unbalanced rotor differential, as, increase the rotating speed of described fuselage screw propeller 31, keep the rotating speed of described wing screw propeller 32 constant, can nose-up pitching moment be produced; Or keep the rotating speed of fuselage screw propeller 31 constant, reduce the rotating speed of described wing screw propeller 32, produce nose-up pitching moment equally; Or adjust the rotating speed of described fuselage screw propeller 31 and described wing screw propeller 32 simultaneously, make the relative velocity of the described fuselage screw propeller 31 being positioned at described fuselage 10 front portion be greater than the relative velocity of the every described wing screw propeller 32 being positioned at described fuselage 10 rear portion, thus make described fuselage 10 produce nose-up pitching moment upwards.
Correspondingly, when described fuselage 10 needs to produce downward moment, the rotating speed of described fuselage screw propeller 31 and described wing screw propeller 32 is regulated by described engine installation 40, it is made to occur unbalanced rotor differential, as, reduce the rotating speed of described fuselage screw propeller 31, keep the rotating speed of every described wing screw propeller 32 constant, produce nose-down pitching moment; Or keep the rotating speed of described fuselage screw propeller 31 constant, increase the rotating speed of every described wing screw propeller 32, produce nose-down pitching moment equally; Or adjust the rotating speed of described fuselage screw propeller 31 and every described wing screw propeller 32 simultaneously, make the relative velocity of the described fuselage screw propeller 31 being positioned at described fuselage 10 front portion be less than the relative velocity of the described wing screw propeller 32 being positioned at described fuselage 10 rear portion, thus make described fuselage 10 produce downward nose-up pitching moment.
Described change wing formula unmanned plane state of flight by bow or new line state is adjusted to turning flight state time, described fuselage screw propeller 31 works in coordination with the action of every described wing screw propeller 32, realizes the turning flight of described change wing formula unmanned plane.Specifically, adjust the relative velocity of described fuselage screw propeller 31 and every described wing screw propeller 32, make to occur differential in side direction, thus the front portion of described fuselage 10 is turned to side.Such as, keep the velocity of rotation of described fuselage screw propeller 31 constant, change the speed of the wherein wing screw propeller 32 described in any one in every described wing screw propeller 32, described fuselage 10 there will be side moment, thus realizes turning to side.Those skilled in the art are appreciated that differential comes across described fuselage screw propeller 31 and every described wing screw propeller 32 when described change wing formula unmanned plane is in the state of flight of bowing or coming back, and now, the rotating speed of every described wing screw propeller 32 is consistent; When described change wing formula unmanned plane is in side direction turn condition, differential comes across between described fuselage screw propeller 31 and every described wing screw propeller 32, and now, the rotating speed between every described wing screw propeller 32 is also inconsistent.
As shown in Figure 10, when the state of flight of described change wing formula unmanned plane is adjusted to vertical decline state from side direction turn condition, by adjusting the relative velocity of described fuselage screw propeller 31 and every described wing screw propeller 32, and adjust the direction of every described adjustment wing 22, every described adjustment wing 22 is made to be adjusted to described vertical direction with every described wing screw propeller 32 from described horizontal direction, accordingly, adjust described fuselage screw propeller 31 and every described wing screw propeller 32 and change lift obliquely, the air resistance of described horizontal direction also can change accordingly.After described lift obliquely decomposes when the power of described horizontal direction and described change wing formula unmanned plane to balance each other at the air resistance that described horizontal direction is subject to and be less than described gravity in the power of described vertical direction, described change wing formula unmanned plane vertically can do descending motion, thus, achieve the vertical landing of described change wing formula unmanned plane.
Described change wing formula unmanned plane can also comprise a toter 50, described toter 50 can be optionally arranged at inside or the below of described fuselage 10, wherein said toter 50 can be used for being contained in transported article etc., when described change wing formula unmanned plane is in the state of flight, the point of action that described toter 50 and the article being installed in described toter 50 inside act on described fuselage 10 is positioned at the described center of gravity of fuselage 10 or the below of center of gravity, like this, the flight safety of described change wing formula unmanned plane can be guaranteed.Such as, in this example of such as Figure 11, described change wing formula unmanned planes more than two framves or two framves can also work in coordination with to deliver article, specifically, wing formula unmanned plane is become when delivering article by described toter 50 described in multi rack, article act on the point of action of described fuselage 10 by described toter 50 can immediately below the center-of-gravity position of described fuselage 10, that is, article act on the point of action of described fuselage 10 and the center of gravity of described fuselage 10 same vertical direction (namely the described article center of gravity that acts on the point of action of described fuselage 10 and described fuselage 10 by described toter 50 is coaxial) by described toter 50, thus, guarantee that described change wing formula unmanned plane is in the process of shipping goods, it has good having a smooth flight property, to guarantee the flight safety of described change wing formula unmanned plane further.
Described change wing formula unmanned plane can also comprise a lifting gear 60, wherein said lifting gear 60 is arranged at the bottom of described fuselage 10, for auxiliary described change wing formula unmanned plane landing, as shown in Figure 3, described lifting gear 60 may be implemented as a landing frame in a concrete example, however, those skilled in the art are to be understood that, in other embodiment of the present utility model, described lifting gear 60 also may be implemented as lifting wheel or similar device in other examples, therefore, the type of described lifting gear 60 can not be regarded as the restriction to content of the present utility model and scope.
As shown in figure 12, described change wing formula unmanned plane can also be controlled by a control setup 70, specifically, described engine installation 40 can be connected in described control setup 70 communicatedly, operating personal can utilize described control setup 70 to control rotating speed and the state of every described screw propeller 30 by the Energy transmission controlling described engine installation 40, thus, make to realize the switching of described change wing formula unmanned plane under different state of flights by producing differential between every described screw propeller 30.Such as, in the utility model, operating personal can utilize described control setup 70 to increase the rotating speed of the described screw propeller 30 being implemented as described fuselage screw propeller 31, has the flare maneuver of new line to make described change wing formula unmanned plane.However, those skilled in the art are to be understood that, described control setup 70 can also to the Automated condtrol of described change wing formula unmanned plane, that is, can in described control setup 70 setting program, operate with the state of flight of alternative operating personal to described change wing formula unmanned plane.
Accordingly, the utility model also provides a kind of flying method becoming wing formula unmanned plane, and wherein relative to Fixed Wing AirVehicle and the Multi-axis aircraft of prior art, the described flying method of described change wing formula unmanned plane has significant progress.Specifically, described method comprises makes the every described screw propeller 30 being arranged at every described wing 20 respectively adjust between described horizontal direction and described vertical direction, to change the state of flight of described change wing formula unmanned plane.
Preferably, described method also comprises step.
A () provides the described connecting wing 21 being arranged at described fuselage 10 symmetrically.
B () provides the described adjustment wing 22 being arranged at every described connecting wing 21 rotationally, every described connecting wing 21 and every described adjustment wing 22 form every described wing 20 respectively, and every described screw propeller 30 is optionally arranged at every described connecting wing 21 or every described adjustment wing 22.It is worth mentioning that, in this embodiment as shown in Figure 3 of the present utility model, the every described screw propeller 33 being implemented as described wing screw propeller 32 is arranged at the described adjustment wing 22, with make every described wing screw propeller 32 can with the synchronized movement of every described adjustment wing 22.However, those skilled in the art are to be understood that, even if be arranged in this embodiment of described connecting wing 21 at described wing screw propeller 32, by adjusting described wing screw propeller 32 and the position of the described adjustment wing 22 respectively, also same object can be reached.
C () makes every described adjustment wing 22 adjust between described horizontal direction and described vertical direction.By such mode, described change wing formula unmanned plane is in follow-up flight course, and its state of flight can be changed neatly.
It is worth mentioning that, in the above-mentioned methods, by making to produce speed discrepancy between every described screw propeller 30, described change wing formula unmanned plane can be made to adjust between different state of flights, such as, the flight courses such as described change wing formula unmanned plane can realize such as coming back, bow, turning, thus, the alerting ability of described change wing formula unmanned plane can be increased.
One skilled in the art will understand that the embodiment of the present utility model shown in foregoing description and accompanying drawing only limits the utility model as an example and not.The purpose of this utility model is complete and effectively realize.Function of the present utility model and structural principle are shown in an embodiment and are illustrated, do not deviating under described principle, embodiment of the present utility model can have any distortion or amendment.
Claims (10)
1. become a wing formula unmanned plane, it is characterized in that, comprising:
One fuselage;
Two wings, every described wing is arranged at described fuselage symmetrically; And
At least three screw propellers, every described screw propeller is arranged at described fuselage and every described wing respectively, and the described screw propeller being wherein arranged at every described wing is done the axial motion relative to described fuselage.
2. change wing formula unmanned plane as claimed in claim 1, wherein said change wing formula unmanned plane also comprises an engine installation, and described engine installation is arranged at described fuselage, and every described screw propeller is respectively coupled to described engine installation.
3. change wing formula unmanned plane as claimed in claim 1, wherein said change wing formula unmanned plane also comprises a toter, described toter is arranged at described fuselage, and the center of the described toter point of action and described fuselage that act on described fuselage is in same vertical direction.
4. change wing formula unmanned plane as claimed in claim 1, wherein said change wing formula unmanned plane also comprises a lifting gear, and described lifting gear is arranged at the below of described fuselage.
5., as the change wing formula unmanned plane as described in arbitrary in Claims 1-4, wherein every described screw propeller is optionally arranged at middle part or the end of described wing.
6. as the change wing formula unmanned plane as described in arbitrary in Claims 1-4, wherein every described wing comprises a connecting wing and an adjustment wing respectively, every described connecting wing is arranged at described fuselage, every described adjustment wing is arranged at every described connecting wing rotationally, and every described screw propeller is optionally arranged at every described connecting wing or every described adjustment wing respectively.
7. change wing formula unmanned plane as claimed in claim 6, wherein every described screw propeller is had speed discrepancy.
8. change wing formula unmanned plane as claimed in claim 7, the described screw propeller being wherein arranged at described fuselage is a contrarotating propeller.
9. change wing formula unmanned plane as claimed in claim 8, wherein every described screw propeller comprises at least one blade respectively, and every described blade has a bow oar face and a face of blade respectively, and the curvature in described bow oar face is greater than the curvature of described face of blade.
10. become a wing formula unmanned plane, it is characterized in that, comprising:
One fuselage;
At least two screw propellers; And
Two wings, every described wing comprises a connecting wing and an adjustment wing respectively, wherein every described connecting wing is arranged at described fuselage symmetrically, every described adjustment wing is arranged at every described connecting wing respectively rotationally, and every described screw propeller is optionally arranged at every described connecting wing or every described adjustment wing.
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| CN201420845446.XU CN204473135U (en) | 2014-12-26 | 2014-12-26 | A kind of change wing formula unmanned plane |
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| CN201420845446.XU CN204473135U (en) | 2014-12-26 | 2014-12-26 | A kind of change wing formula unmanned plane |
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| CN204473135U true CN204473135U (en) | 2015-07-15 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539781A (en) * | 2015-12-07 | 2016-05-04 | 广州丰谱信息技术有限公司 | Axial orthogonal adjustable propeller array-based underwater unmanned detector |
| CN105775121A (en) * | 2014-12-26 | 2016-07-20 | 深圳智航无人机有限公司 | Wing-variable type unmanned aerial vehicle and method thereof |
| CN105818980A (en) * | 2016-05-06 | 2016-08-03 | 刘行伟 | Novel large-lift-force vertical take-off and landing aircraft |
| CN106143870A (en) * | 2015-07-28 | 2016-11-23 | 英华达（上海）科技有限公司 | Unmanned vehicle |
| CN106516099A (en) * | 2015-09-11 | 2017-03-22 | 空客直升机德国有限公司 | Compound helicopter |
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2014
- 2014-12-26 CN CN201420845446.XU patent/CN204473135U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775121A (en) * | 2014-12-26 | 2016-07-20 | 深圳智航无人机有限公司 | Wing-variable type unmanned aerial vehicle and method thereof |
| CN106143870A (en) * | 2015-07-28 | 2016-11-23 | 英华达（上海）科技有限公司 | Unmanned vehicle |
| CN106516099A (en) * | 2015-09-11 | 2017-03-22 | 空客直升机德国有限公司 | Compound helicopter |
| CN106516099B (en) * | 2015-09-11 | 2019-12-10 | 空客直升机德国有限公司 | Composite rotor craft |
| CN105539781A (en) * | 2015-12-07 | 2016-05-04 | 广州丰谱信息技术有限公司 | Axial orthogonal adjustable propeller array-based underwater unmanned detector |
| CN105818980A (en) * | 2016-05-06 | 2016-08-03 | 刘行伟 | Novel large-lift-force vertical take-off and landing aircraft |
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Effective date of registration: 20160310 Address after: 518108 Guangdong city of Shenzhen province Baoan District Shiyan Street Tangtou way Yuntai Technology Industrial Park 1 East Building 6 floor Patentee after: SHENZHEN SMART DRONE UAV CO., LTD. Address before: 518000 Virtual University Park, Nanshan Science Park, Shenzhen, Guangdong 502A Patentee before: Jin Liang |