CN207078323U - Microminiature can hover Fixed Wing AirVehicle - Google Patents
Microminiature can hover Fixed Wing AirVehicle Download PDFInfo
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- CN207078323U CN207078323U CN201721117135.1U CN201721117135U CN207078323U CN 207078323 U CN207078323 U CN 207078323U CN 201721117135 U CN201721117135 U CN 201721117135U CN 207078323 U CN207078323 U CN 207078323U
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- fuselage
- aircraft
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- fixed wing
- microminiature
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Abstract
It can be hovered Fixed Wing AirVehicle the utility model discloses a kind of microminiature, including fuselage and two horizontal rudder faces, two vertical tails, even number the set motor and propeller that are symmetrical with the setting of fuselage axis；After propeller described in the motor connection, installed in the head of the fuselage, described two horizontal rudder faces are hinged by hinge and the afterbody, described two vertical tails are vertically installed at the two sides of tail of the fuselage, and protruded relative to the fuselage upper and lower surface, the fuselage interior is provided with flight control system.Aircraft of the present utility model is taking off vertically, landed and the three-dimensional space direction of hovering phase is all controllable, increases in flight control system auxiliary under steady control, it is possible to achieve the sporting flying of aircraft in three dimensions.Wing body integrative-structure and thin-walled fuselage of the present utility model can realize the significantly diminution of aircraft body size, and aircraft of the present utility model is convenient for carrying, easy to use, compact structure, save manufacture material.
Description
Technical field
Aviation aircraft field is the utility model is related to, it is especially a kind of applied to the small of unmanned vehicle technology
Type can hover Fixed Wing AirVehicle.
Background technology
In recent years, with the rapid development of electronic technology, unmanned plane is in the communications after, environmental monitoring, forest fire protection, geology
More and more important role is play in the fields such as exploration, Aerial photography, power-line patrolling, distant sensor.Existing unmanned plane can
To be roughly divided into two kinds of two classes, i.e. multi-rotor aerocraft and Fixed Wing AirVehicle.Multi-rotor aerocraft is due to needing multiple electric motors
Work simultaneously to aircraft provide enough power realize hovering, it is flat the maneuver such as fly, exist energy consumption is big, the flight time is short,
The shortcomings that flying speed is slow；And although Fixed Wing AirVehicle is with good aerodynamic characteristic, the flight time is long, flying speed is fast
Advantage, but existing most of Fixed Wing AirVehicle size is larger, it is not readily portable.
Although having there is the solution of some microminiature Fixed Wing AirVehicles at present, lacked there is also certain
Point.A kind of minute vehicle is provided with rudder face of two elevons as aircraft in body trailing edge in the prior art, so as to
The three-dimensional motion of control in-flight.When two elevons deflect in the same direction, pitching moment is produced, controls aircraft pitch orientation
Motion, when two elevon reversing differentials deflect, rolling moment is produced, controls the rolling movement of aircraft.But this skill
Art is not provided with the yaw motion along minute vehicle heading, can only realize the two dimensional motion of three dimensions.So this
Kind of microminiature Fixed Wing AirVehicle needs to throw by human hand winged when taking off, easily made if throwing aircraft fault when taking off
Cause damage of contacting to earth into failure is taken off, and in landing, because volume and the weight of microminiature limit, it is impossible to which installation is reliable
Undercarriage, if landing wipe ground when ground out-of-flatness, equally easily cause the damage of aircraft；In addition, such microminiature is fixed
Rotor aircraft is in flight course, it is necessary to there is certain flying speed to provide lift necessary to flight, it is therefore, such
Microminiature Fixed Wing AirVehicle can not possibly keep air speed（Relative atmospheric speed）It is zero hovering, this is not easy to aircraft geo-stationary
Static target is observed using camera on ground.
Utility model content
The applicant is directed to the above-mentioned landing of aircraft in the prior art hardly possible, can not realize three-dimensional motion, not readily portable etc.
Shortcoming, there is provided a kind of microminiature of wing body one can hover Fixed Wing AirVehicle, can VTOL, easy to use, flying speed
Hurry up, can carry out hover peace fly, realize 3 D auto move.
Technical scheme is as follows used by the utility model：
A kind of microminiature can hover Fixed Wing AirVehicle, including fuselage and be symmetrical with two of the setting of fuselage axis
Horizontal rudder face, two vertical tails, even number set motor and propeller；After propeller described in the motor connection, installed in the fuselage
Head, described two horizontal rudder faces are hinged by hinge and the afterbody, and described two vertical tails are vertically installed at described
The two sides of tail of fuselage, and protruded relative to the fuselage upper and lower surface, the fuselage interior is provided with flight control system.
Further improvement as above-mentioned technical proposal：
Section of the fuselage in plane of symmetry position uses symmetrical above and below streamlined.
The microminiature can hover the wing of Fixed Wing AirVehicle and the fuselage uses integral type shaped structure.
The rotation direction of the even number propeller is that side is that side clockwise is counterclockwise.
Can the hover width of Fixed Wing AirVehicle of the microminiature is 20-30cm, length 15-25cm.
Described two horizontal rudder faces, which overlook the gross areas and account for the microminiature Fixed Wing AirVehicle that can hover, overlooks the gross area
20%-28%。
The single vertical tail side view area account for the microminiature can hover Fixed Wing AirVehicle overlook the gross area 4%-6%.
The vertical tail leading edge has angle of sweep, and the angle of sweep is 35 ° -50 °.
A diameter of 2-4 inches of the propeller.
Also include GPS, the GPS is connected with the flight control system.
The beneficial effects of the utility model are as follows：
The utility model can realize VTOL, easy to use, flying speed is fast, the peace that can carry out hovering flies, realizes three
Tie up the technique effect of free movement.The utility model uses to two motors and two hydroplanes the posture for facing aircraft simultaneously
It is controlled.Two horizontal rudder faces can either deflect the torque for producing and enabling aircraft to come back or bow in the same direction so that flight
Device is taking off vertically, landed and hovering phase pitch orientation is controllable；The enough differential deflection of two horizontal rudder face and cans simultaneously, production
Life makes the torque that aircraft rotates around aircraft body axis so that aircraft is taking off vertically, landed and hovering phase is diversion
The direction of row device body axis rotation is controllable.Aircraft with two motors is taking off vertically, landed and hovering phase,
It not only can directly overcome aircraft gravity by motor self power, realize that the power of aircraft meets the base that can be taken off vertically
This requirement, while differential rotation can also be carried out and produce the power that aircraft can be made to be rotated around the axle perpendicular to body plane
Square, therefore, aircraft are also controllable in this direction.So aircraft of the present utility model is taking off vertically, landing and hanged
The three-dimensional space direction for stopping the stage is all controllable, is increased in flight control system auxiliary under steady control, it is possible to achieve aircraft
Sporting flying in three dimensions.
Wing body integrative-structure and thin-walled fuselage of the present utility model can realize the significantly diminution of aircraft body size, this
The width of the aircraft of utility model is 20-30cm, length 15-25cm, can be convenient for carrying, easy to use, compact structure,
Save manufacture material.
Brief description of the drawings
Fig. 1 is stereogram of the present utility model；
Fig. 2 is front view of the present utility model；
Fig. 3 is Fig. 2 upward view；
Fig. 4 is Fig. 2 rearview；
Fig. 5 is Fig. 2 right view；
Fig. 6 is profile of the aircraft fuselage along A-A faces in Fig. 2.
In figure：1st, fuselage；2nd, horizontal rudder face；3rd, vertical tail；4th, motor；5th, propeller；6th, hinge.
Embodiment
Below in conjunction with the accompanying drawings, specific embodiment of the present utility model is illustrated.
As Figure 1-4, the microminiature of the present utility model Fixed Wing AirVehicle that can hover includes：Fuselage 1 and it is symmetrical with
Two horizontal 3, two sets of the vertical tail motors 4 of rudder face 2, two and propeller 5 that the axis of fuselage 1 is set；Described two motors 4 connect
After the propeller 5, installed in the head of the fuselage 1, described two horizontal rudder faces 2 pass through hinge 6 and the afterbody of fuselage 1
Be hinged, described two vertical tails 3 are vertically installed at the two sides of tail of the fuselage 1, and are protruded relative to the fuselage upper and lower surface,
The fuselage 1 is internally provided with flight control system.The flight control system is to described two horizontal 2, two motors 4 of rudder face
It is controlled, realizes the motion of each mechanism.
Aircraft of the present utility model is integrally symmetrical, and wing uses integral type shaped structure with the fuselage 1, referring to
Fig. 2, fuselage 1 are substantially in a rectangular shape, and side processing is received in both sides using the curved surface of sweeping curvature change, to improve aircraft
Aerodynamic characteristic.Reference picture 6, fuselage 1 are symmetrical above and below streamlined in the section of plane of symmetry position, pass through fairshaped arc knot
Structure, most lift needed for aircraft flight can be produced.The wall thickness of fuselage 1 is 0.5-2mm, and it is cavity that it is internal, empty
Cavity configuration provides enough appearances to equipment such as aircraft power, control, shootings under conditions of aircraft fundamental strength is ensured
Receive space.
The utility model has two horizontal rudder faces 2, can under the auxiliary of flight control system positioned at the trailing edge of fuselage 1
Deflection and differential deflection in the same direction are carried out, the function of aileron and elevator can be realized simultaneously.While in order to make aircraft real
Now hovering and VTOL function, the more general Fixed Wing AirVehicle of relative area of two horizontal rudder faces 2 is bigger, two hydroplanes
The gross area of face 2 accounts for the 20%-28% that the whole aircraft overlooks the gross area, increases controlled quentity controlled variable, and assisting in flying control system is completed
Hovering and VTOL.
Reference picture 5, vertical tail 3 of the present utility model is vertically installed at the two sides of tail of fuselage 1, and protrudes from the fuselage
Lower surface, wind-force regulation is carried out in the upper-lower position of aircraft, stable course is provided for aircraft.The side view of single vertical tail 3
Area accounts for the 4%-6% that the whole aircraft overlooks the gross area.Between the sweepback angular region of the leading edge of vertical tail 3 is 35 ° -50 °, improve
The shipping-direction stability and flying speed of aircraft.
Reference picture 1, Fig. 3, two motors 4 are installed on head of the present utility model, and two axis distances of motor 4 account for fuselage
The 45%-65% of 1 width, 4 a diameter of 9-13mm of motor, the weight of motor 4 are 4-10g.The propeller 5 selects two diameter 2-4
The propeller of inch, described two 5 one, propellers turn clockwise a rotate counterclockwise during normal flight.The motor 4
Single propeller maximum pull provides enough power for aircraft in more than 140g after coordinating with propeller 5.It is worth explanation
It is that the utility model is only a kind of embodiment using two motors and two propellers, when using three or odd number, wherein
One motor and propeller are arranged on head center, and remaining symmetrical expression is arranged on Handpiece Location, for provide power and
Change of flight device flight deflection direction, and desirable.When using four or even number, equal symmetrical expression is arranged on head position
Put, for providing power and change of flight device flight deflection direction, and can use.
Aircraft of the present utility model also includes GPS（Global Positioning System, global positioning system）,
The GPS is connected with the flight control system.After the equipment such as GPS are installed on board the aircraft, pass through the side of flight control system
Help, the line of flight of planning can be completed, independently judged to complete the overall process of flight by aircraft.
The following detailed description of the operation principle of aircraft described in the utility model.
1st, the operation principle for taking off vertically, landing and hovering：
Aircraft of the present utility model is taking off vertically, landed and hovering phase, and body axis is perpendicular to the ground, flight
Device is in head towards the state in day.In these stages, it is necessary to using to two motors 4 and two horizontal rudder faces 2 to aircraft
Posture be controlled.
Two horizontal rudder faces 2 can either deflect the torque for producing and making aircraft come back or bow in the same direction so that aircraft exists
Take off vertically, land and hovering phase pitch orientation is controllable；The enough differential deflection of two horizontal and cans of rudder face 2 simultaneously, is produced
The torque for making aircraft be rotated around aircraft body axis so that aircraft is taking off vertically, landed and hovering phase is around flight
The direction of device body axis rotation is controllable.
Aircraft with two motors 4 is taking off vertically, landed and hovering phase, can not only rely on motor 4 itself
Power directly overcomes aircraft gravity, realizes that the power of aircraft meets the basic demand that can be taken off vertically, while two motors
Differential rotation can also be carried out, the left and right ends of aircraft are pulled power difference and twisted, and can produce makes aircraft
Around the torque of the axle rotation perpendicular to body plane, therefore, aircraft is also controllable in this direction.
In summary, aircraft of the present utility model take off vertically, land and the three-dimensional space direction of hovering phase all
It is controllable, increases in flight control system auxiliary under steady control, it is possible to achieve the sporting flying of aircraft in three dimensions.
2nd, aircraft equals winged operation principle：
The flight that one aircraft can be stablized must is fulfilled for following 3 conditions：1st, enough lift is winged to overcome
The row device gravity of itself；2nd, enough power with overcome aircraft advance resistance；3rd, good maneuverability and stability.According to
Aerodynamic relevant knowledge, when an object has specific section shape and flat shape and relative atmospheric motion,
Air will produce lift on movement direction of object, while produce the resistance opposite with movement direction of object.This practicality
Aircraft in new installs two motors 4 in head section, by the optimized Selection to motor 4 and propeller 5, to ensure to fly
Row device can ensure that aircraft has a certain degree of air speed simultaneously in flat fly（Relative atmospheric speed）, there is provided enough liters
Power, and there is enough power to overcome air drag at such speeds.
With taking off vertically, landing and hovering phase is similar, aircraft is realized in the flat winged stage by two horizontal rudder faces 2 to fly
Control of the row device to level-flight attitude.To be produced when two horizontal rudder faces 2 deflects towards side simultaneously, on aircraft a new line or
Nose-down pitching moment so that aircraft is come back or bowed motion., will production on aircraft when two horizontal 2 differential motions of rudder face
A raw rolling moment so that aircraft carries out rolling movement.Under the auxiliary of flight control system, aircraft can be lifted
Maneuvering performance and stability so that aircraft such as can be completed to climb, glide, turn the maneuver in the flat winged stage.
The following detailed description of the course of work of aircraft described in the utility model.
1. take off vertically
Aircraft vertical take off before by human hand held, and cause aircraft body axis it is vertical with level ground, complete preparation
After work, given and instructed by ground staff, after two power of motor 4 are more than aircraft itself gross weight, aircraft is flying
Control system is to that under the control of flight attitude, can realize and take off vertically.
2. take off vertically to flat winged transition
After aircraft receives the conversion signal by the state of taking off vertically to flat winged state, turn on two horizontal rudder faces 2,
Aircraft is constantly bowed, until aircraft body axis is from being vertically changed into close to level, into the flat winged stage.In the process,
Aircraft altitude can decline, at this moment because the gravitional force of aircraft is converted into the kinetic energy of aircraft motion, there is provided maintain
Aircraft is flat to fly required flight airspeed so that enters that flat to fly over Cheng Gengwei round and smooth.
3. the flat winged stage
After aircraft enters the flat winged stage, aircraft is similar with the work of common Fixed Wing AirVehicle, can according to times
Business requires, quickly flies to task point.
4. flat fly the stage to vertical landing or the transition of hovering phase
When aircraft receives the flat winged stage to after the instruction of vertical landing or the transition of hovering phase, two horizontal rudder faces 2
Lower turn, aircraft constantly comes back, while climbs upwards, when aircraft axis from horizontal plane is almost parallel changes to and horizontal plane
When vertical, switch transition is completed, simultaneously because aircraft climbs upwards during coming back, the kinetic energy of aircraft is converted into gravitational potential
Can, aircraft airspeed gradually decreases to be close to zero.
5. hovering phase
Aircraft is completed to put down and flown to after the transition of hovering, maintains motor 4 total output size and aircraft itself total great
Cause equal, aircraft is under control of the flight control system to flight attitude, it is possible to achieve the hovering of aircraft.
6. the vertical decline stage
Aircraft is completed to put down and flown to after the transition of hovering, and aircraft increases in flight control system to the auxiliary of flight attitude
It is appropriate to reduce the power of motor 4, it is possible to so that aircraft slowly declines, and to land on the ground under steady control.
7. autonomous flight
After the equipment such as GPS are installed on board the aircraft, by the help of flight control system, it can complete to advise in earth station
The line of flight drawn, independently judged to complete by aircraft above-mentioned 1. to overall process 6..
Above description is to explanation of the present utility model, is not the restriction to utility model, without prejudice to the utility model
In the case of spirit, the utility model can make any type of modification.
Claims (10)
- The Fixed Wing AirVehicle 1. a kind of microminiature can hover, it is characterised in that including fuselage（1）And it is symmetrical with fuselage（1）In Two horizontal rudder faces that axis is set（2）, two vertical tails（3）, even number set motor（4）And propeller（5）；The motor（4）Even Connect the propeller（5）Afterwards, installed in the fuselage（1）Head, described two horizontal rudder faces（2）Pass through hinge（6）With institute State fuselage（1）Afterbody is hinged, described two vertical tails（3）It is vertically installed at the fuselage（1）Two sides of tail, and relative to described Fuselage（1）Upper and lower surface protrudes, the fuselage（1）It is internally provided with flight control system.
- The Fixed Wing AirVehicle 2. microminiature according to claim 1 can hover, it is characterised in that the fuselage（1）Right The section of title face position is using symmetrical above and below streamlined.
- The Fixed Wing AirVehicle 3. microminiature according to claim 1 can hover, it is characterised in that the microminiature can hover The wing of Fixed Wing AirVehicle and the fuselage（1）Using integral type shaped structure.
- The Fixed Wing AirVehicle 4. microminiature according to claim 1 can hover, it is characterised in that the even number propeller （5）Rotation direction be that side is that side clockwise is counterclockwise.
- The Fixed Wing AirVehicle 5. microminiature according to claim 1 can hover, it is characterised in that the microminiature can hover The width of Fixed Wing AirVehicle is 20-30cm, length 15-25cm.
- The Fixed Wing AirVehicle 6. microminiature according to claim 1 can hover, it is characterised in that described two horizontal rudder faces （2）Overlook the gross area account for the microminiature can hover Fixed Wing AirVehicle overlook the gross area 20%-28%.
- The Fixed Wing AirVehicle 7. microminiature according to claim 1 can hover, it is characterised in that single vertical tail（3）Side view Area account for the microminiature can hover Fixed Wing AirVehicle overlook the gross area 4%-6%.
- The Fixed Wing AirVehicle 8. microminiature according to claim 1 can hover, it is characterised in that the vertical tail（3）Leading edge With angle of sweep, the angle of sweep is 35 ° -50 °.
- The Fixed Wing AirVehicle 9. microminiature according to claim 1 can hover, it is characterised in that the propeller（5）'s A diameter of 2-4 inches.
- The Fixed Wing AirVehicle 10. microminiature according to claim 1 can hover, it is characterised in that described also including GPS GPS is connected with the flight control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721117135.1U CN207078323U (en) | 2017-09-01 | 2017-09-01 | Microminiature can hover Fixed Wing AirVehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721117135.1U CN207078323U (en) | 2017-09-01 | 2017-09-01 | Microminiature can hover Fixed Wing AirVehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207078323U true CN207078323U (en) | 2018-03-09 |
Family
ID=61419148
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721117135.1U Expired - Fee Related CN207078323U (en) | 2017-09-01 | 2017-09-01 | Microminiature can hover Fixed Wing AirVehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207078323U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499513A (en) * | 2017-09-01 | 2017-12-22 | 无锡翼鸥科技有限公司 | Microminiature can hover Fixed Wing AirVehicle |
| CN109178315A (en) * | 2018-10-30 | 2019-01-11 | 北京航空航天大学 | A kind of scouting operation miniature drone of absorption type |
-
2017
- 2017-09-01 CN CN201721117135.1U patent/CN207078323U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107499513A (en) * | 2017-09-01 | 2017-12-22 | 无锡翼鸥科技有限公司 | Microminiature can hover Fixed Wing AirVehicle |
| CN109178315A (en) * | 2018-10-30 | 2019-01-11 | 北京航空航天大学 | A kind of scouting operation miniature drone of absorption type |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180309 Termination date: 20190901 |