CN209225395U - A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure - Google Patents
A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure Download PDFInfo
- Publication number
- CN209225395U CN209225395U CN201821748429.9U CN201821748429U CN209225395U CN 209225395 U CN209225395 U CN 209225395U CN 201821748429 U CN201821748429 U CN 201821748429U CN 209225395 U CN209225395 U CN 209225395U
- Authority
- CN
- China
- Prior art keywords
- mounting rod
- fuselage
- wing
- unmanned plane
- central axes
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a kind of fixed-wing unmanned planes that hung down with multiple groups quadrotor structure, it include fuselage, it is connected to fuselage side and a symmetrically arranged left side, starboard wing, it is left, the first mounting rod and the second mounting rod are respectively connected with below starboard wing, landing motor is provided on two first mounting rods and two second mounting rods, symmetric screw propeller is respectively connected on the output shaft of each landing motor, the central axes of landing motor output shaft form the acute angle towards fuselage with the central axes of corresponding first mounting rod on every first mounting rod, the central axes of landing motor output shaft are formed with the central axes of corresponding second mounting rod towards the obtuse angle of fuselage on every second mounting rod.The utility model is provided with symmetric screw propeller and provides the pulling force of unmanned plane VTOL and increase the yaw control moment of unmanned plane, fixed-wing provides lift when unmanned plane follow-on mission, the power of tail undercarriage generation flight forward, can be achieved unmanned plane without the quick landing of runway, long endurance, quickly, smooth flight.
Description
Technical field
The utility model relates to air vehicle technique field, specifically a kind of fixed-wing that hung down with multiple groups quadrotor structure
Unmanned plane.
Background technique
With the development of unmanned air vehicle technique, the fixed-wing Development of UAV of traditional technology at can VTOL fixed-wing without
It is man-machine, due to VTOL fixed-wing unmanned plane have both fixed-wing unmanned plane cruise duration is long, the high and more rotor of flying speed without
The characteristics of man-machine VTOL, such fixed-wing unmanned plane are widely applied in unmanned plane field.
VTOL fixed-wing unmanned plane can substantially be divided into composite wing formula, tailstock formula and the dynamical type that verts according to working principle
Three kinds of forms.Wherein, composite wing vertical take-off and landing drone is to increase Vertical Dynamic dress on the basis of traditional fixed-wing unmanned plane
It sets, in high-speed flight, according to fixed-wing mode flight, fixed-wing provides flight lift, the forward spiral of pulling force for unmanned plane
Paddle provides the thrust of flight；It in VTOL and low-speed operations, flies according to more rotor modes, multiple propellers provide nobody
The upward pulling force of machine is to overcome gravity and aerodynamic drag to fly.Composite wing vertical take-off and landing drone is simple with its structure,
It has a smooth flight, advantage easy to operate becomes the hot spot that unmanned plane researches and develops field.
But compared with multi-rotor unmanned aerial vehicle, composite wing unmanned plane increases the components such as fuselage, wing and tail, significantly
The weight of unmanned plane is increased, at the same time, yaw rotation inertia also increases with it, and composite wing unmanned plane exists partially at present
The relatively low problem of control ability of navigating, this will lead to the attitude control accuracy decline even aircraft accident of unmanned plane.
Utility model content
What the technical problem to be solved by the present invention is to provide a kind of with multiple groups quadrotor structure hung down fixed-wing without
It is man-machine, the advantages of sufficiently combining fixed-wing and rotor, the symmetric screw propeller of setting provide unmanned plane VTOL pulling force and
Increase unmanned plane yaw control moment, fixed-wing provide unmanned plane follow-on mission when lift, it can be achieved that unmanned plane without race
The quick landing in road, long endurance, quick, smooth flight.
The technical solution of the utility model are as follows:
A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure, include fuselage, be connected to fuselage side and
Symmetrically arranged left and right wing is respectively connected with the first mounting rod disposed in parallel and the second peace below the left and right wing
Bar is filled, the first mounting rod below left and right wing is symmetrical along the central axes of fuselage, the second mounting rod edge below left and right wing
The central axes of fuselage are symmetrical, the central axes of two first mounting rods and two second mounting rods with the axis parallel of fuselage,
Landing motor, the output shaft that each landing motor upwardly extends are provided on two first mounting rods and two second mounting rods
On be respectively connected with symmetric screw propeller, the central axes of landing motor output shaft and corresponding first mounting rod on every first mounting rod
Central axes form the acute angle towards fuselage, and the central axes of landing motor output shaft are installed with corresponding second on every second mounting rod
The central axes of bar are formed towards the obtuse angle of fuselage.
Landing motor there are two being respectively provided on first mounting rod and the second mounting rod, the output of each landing motor
Be respectively connected with corresponding symmetric screw propeller on axis, the central axes of every first mounting rod respectively with two on corresponding first mounting rod
The central axes of landing motor output shaft are respectively formed the acute angle towards fuselage, and the angle of acute angle is identical, every second mounting rod
Central axes are respectively formed the obtuse angle towards fuselage with the central axes of two landing motor output shafts on corresponding second mounting rod respectively, and
The angle at obtuse angle is identical.
Second mounting rod is located at the outside of the first mounting rod, i.e. the first mounting rod is located at fuselage and the second mounting rod
Between.
The afterbody is provided with tail portion motor, is connected with tail portion spiral on the horizontal-extending output shaft of tail portion motor
Paddle.
The left and right trailing edge is equipped with aileron, and left and right wing is using straight wing structure and has certain upper counterangle, left,
The wing tip of starboard wing is winglet structure.
The rear end of the fuselage is provided with tail, and tail includes horizontal tail and vertical fin, and vertical fin end is connected by a hinge partially
Navigate rudder face, and horizontal tail end is connected by a hinge pitching rudder face.
Pitot is provided at the front fuselage, the fuselage interior is provided with parachute.
The bottom end of the fuselage is connected with the undercarriage of front three-point wheeled construction.
The advantages of the utility model:
The utility model has taken into account the advantages of fixed-wing unmanned plane and rotor wing unmanned aerial vehicle, is provided with symmetric screw propeller and provides nothing
The pulling force of man-machine VTOL and the yaw control moment for increasing unmanned plane, fixed-wing provide liter when unmanned plane follow-on mission
Power, the tail undercarriage of afterbody generate the power of flight forward, it can be achieved that unmanned plane without the quick landing of runway, long boat
When, quickly, smooth flight.The utility model takes off, lands not by site requirements, and operation is simpler, and unmanned plane is equipped with
The undercarriage of front three-point wheeled construction has the function of during VTOL that damping increases steady and had both sliding race landing mould
Formula.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
See that Fig. 1, a kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure include fuselage 1, are connected to fuselage
1 side and symmetrically arranged left and right wing 2, the tail portion motor for being set to afterbody, to be connected to tail portion motor horizontal-extending
Tail undercarriage 3, the aileron for being set to left and right 2 rear of wing on output shaft, are set to the tail for being set to 1 rear end of fuselage
Pitot 4 at 1 front end of fuselage, the parachute (feelings occurred for guaranteeing unmanned plane in various failures being set to inside fuselage 1
Remain to safe falling under condition, once unmanned plane is out of control, eject parachute automatically, unmanned plane is sent to ground slowly), connection
Shock loading when bearing UAV Landing is used in the undercarriage 5(of the front three-point wheeled construction of 1 bottom end of fuselage and can be put down
It is steady to absorb collision energy and guarantee that unmanned plane be run on the ground with free skating), the lower section of left and right wing 2 is respectively connected with flat
The first mounting rod 6 and the second mounting rod 7 of row setting, the second mounting rod 7 are located at the outside of the first mounting rod 6, i.e., the first installation
Bar 6 is located between fuselage 1 and the second mounting rod 7, and the first mounting rod 6 of left and right 2 lower section of wing is symmetrical along the central axes of fuselage 1,
Second mounting rod 7 of left and right 2 lower section of wing is symmetrical along the central axes of fuselage 1, two first mounting rods 6 and two second installations
Axis parallel of the central axes of bar 7 with fuselage 1, is respectively provided with that there are two rise on every first mounting rod 6 and the second mounting rod 7
Motor is dropped, is respectively connected with corresponding symmetric screw propeller 8, the axis of every first mounting rod 6 on the output shaft of each landing motor
Line is respectively formed the acute angle towards fuselage 1 with the central axes of two landing motor output shafts on corresponding first mounting rod 6 respectively, and sharp
The angle at angle is identical, the central axes of every second mounting rod 7 respectively with two landing motor output shafts on corresponding second mounting rod 7
Central axes be respectively formed the obtuse angle towards fuselage 1, and the angle at obtuse angle is identical.
Wherein, left and right wing 2 using straight wing structure and has certain upper counterangle, and the wing tip of left and right wing 2 is that wingtip is small
Wing structure slackens wing tip vortices breakdown for stopping left and right 2 lower surface of wing streaming around upper surface, reduces air drag,
To effectively increase effective aspect ratio of left and right wing 2；Tail includes horizontal tail 9 and vertical fin 10, and 10 end of vertical fin is connected by hinge
Connect yaw rudder face, 9 end of horizontal tail is connected by a hinge pitching rudder face.
The utility model is provided with the symmetric screw propeller 8 of responsible vertical direction, and landing motor on every first mounting rod 6
The central axes of the central axes of output shaft and corresponding first mounting rod 6 form the acute angle towards fuselage 1, on every second mounting rod 7
The central axes of landing motor output shaft are formed with the central axes of corresponding second mounting rod 7 towards the obtuse angle of fuselage 1, are balanced at eight
During propeller 8 works, the component to 1 left and right side of fuselage is generated, when unmanned plane is flat to fly, symmetric screw propeller 8 is produced
Raw component to the left and to the right offsets each other, to keep the lateral balance of fuselage 1；By the pulling force for changing eight weighing apparatus propellers 8
Rolling control moment and pitch control torque needed for providing, or yawing, yaw are provided by adjusting yaw rudder face angle
Direction controlling ability is improved.
While there has been shown and described that the embodiments of the present invention, for the ordinary skill in the art,
It is understood that these embodiments can be carried out with a variety of variations in the case where not departing from the principles of the present invention and spirit, repaired
Change, replacement and variant, the scope of the utility model is defined by the appended claims and the equivalents thereof.
Claims (8)
1. a kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure, includes fuselage, is connected to fuselage side and right
Claim the left and right wing of setting, it is characterised in that: the first installation disposed in parallel is respectively connected with below the left and right wing
Bar and the second mounting rod, the first mounting rod below left and right wing is symmetrical along the central axes of fuselage, and below left and right wing
Two mounting rods are symmetrical along the central axes of fuselage, and the central axes of two first mounting rods and two second mounting rods are and in fuselage
Axis is parallel, and landing motor is provided on two first mounting rods and two second mounting rods, and each landing motor prolongs upwards
Symmetric screw propeller is respectively connected on the output shaft stretched, the central axes of landing motor output shaft and corresponding on every first mounting rod
The central axes of one mounting rod form the acute angle towards fuselage, on every second mounting rod the central axes of landing motor output shaft with it is right
The central axes of the second mounting rod are answered to be formed towards the obtuse angle of fuselage.
2. a kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure according to claim 1, it is characterised in that:
It is respectively provided on first mounting rod and the second mounting rod there are two landing motor, is connected on the output shaft of each landing motor
Be connected to corresponding symmetric screw propeller, the central axes of every first mounting rod respectively with two landing motors on corresponding first mounting rod
The central axes of output shaft are respectively formed the acute angle towards fuselage, and the angle of acute angle is identical, the central axes point of every second mounting rod
The obtuse angle towards fuselage, and the angle at obtuse angle are not respectively formed with the central axes of two landing motor output shafts on corresponding second mounting rod
It spends identical.
3. a kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure according to claim 1, it is characterised in that:
Second mounting rod is located at the outside of the first mounting rod, i.e., the first mounting rod is between fuselage and the second mounting rod.
4. a kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure according to claim 1, it is characterised in that:
The afterbody is provided with tail portion motor, is connected with tail undercarriage on the horizontal-extending output shaft of tail portion motor.
5. a kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure according to claim 1, it is characterised in that:
The left and right trailing edge is equipped with aileron, and left and right wing is using straight wing structure and has certain upper counterangle, left and right wing
Wing tip is winglet structure.
6. a kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure according to claim 1, it is characterised in that:
The rear end of the fuselage is provided with tail, and tail includes horizontal tail and vertical fin, and vertical fin end, which is connected by a hinge, yaws rudder face, puts down
Tail end is connected by a hinge pitching rudder face.
7. a kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure according to claim 1, it is characterised in that:
Pitot is provided at the front fuselage, the fuselage interior is provided with parachute.
8. a kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure according to claim 1, it is characterised in that:
The bottom end of the fuselage is connected with the undercarriage of front three-point wheeled construction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821748429.9U CN209225395U (en) | 2018-10-26 | 2018-10-26 | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821748429.9U CN209225395U (en) | 2018-10-26 | 2018-10-26 | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209225395U true CN209225395U (en) | 2019-08-09 |
Family
ID=67500973
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821748429.9U Active CN209225395U (en) | 2018-10-26 | 2018-10-26 | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209225395U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319110A (en) * | 2018-10-26 | 2019-02-12 | 安徽云翼航空技术有限公司 | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure |
| CN112810812A (en) * | 2021-01-25 | 2021-05-18 | 西北工业大学 | Combined type VTOL long-endurance electric unmanned aerial vehicle |
-
2018
- 2018-10-26 CN CN201821748429.9U patent/CN209225395U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319110A (en) * | 2018-10-26 | 2019-02-12 | 安徽云翼航空技术有限公司 | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure |
| CN112810812A (en) * | 2021-01-25 | 2021-05-18 | 西北工业大学 | Combined type VTOL long-endurance electric unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105083551B (en) | One kind can tiltrotor and its control method | |
| CN105539834B (en) | A kind of composite wing vertical take-off and landing drone | |
| CN108298064B (en) | Unconventional yaw control system | |
| CN109319110A (en) | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure | |
| CN107933909A (en) | A kind of high-speed and high-efficiency tilting wing unmanned vehicle | |
| CN106828915A (en) | A kind of tilted propeller can VTOL high-speed aircraft and its flight control method | |
| CN205273862U (en) | Composite wing VTOL unmanned aerial vehicle | |
| CN108001679A (en) | Three shrouded propeller power modes can VTOL fixed-wing unmanned vehicle | |
| CN205327411U (en) | Composite wing aircraft | |
| CN106143895B (en) | Thrust type tilt rotor aircraft | |
| CN205022862U (en) | Power device and fixed wing aircraft with mechanism of verting | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN108045575A (en) | A kind of short takeoff vertical landing aircraft | |
| CN105000174A (en) | Tiltrotor mixed multi-state aircraft with operational control surfaces | |
| CN105109680A (en) | Vertical take-off and landing unmanned airplane | |
| CN205998126U (en) | A kind of unmanned plane during flying system | |
| CN113371190A (en) | Combined type high-speed helicopter based on conventional rotor wing configuration | |
| CN105173076B (en) | A kind of vertical take-off and landing drone | |
| CN206187340U (en) | Aircraft | |
| CN209225395U (en) | A kind of fixed-wing unmanned plane that hung down with multiple groups quadrotor structure | |
| CN105151295A (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN111348183A (en) | Aircraft with a flight control device | |
| GB2508023A (en) | Aerofoil with leading edge cavity for blowing air | |
| CN111942581B (en) | Distributed lift force duck-type layout vertical take-off and landing unmanned aerial vehicle and control method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |