CN205931249U - Unmanned aerial vehicle mobility promotes advancing device - Google Patents

Abstract

The utility model discloses an unmanned aerial vehicle mobility promotes advancing device, including battery, control module, first rotor module, second rotor module, third rotor module and fourth rotor module, control module, its characterized in that are all connected to first rotor module, second rotor module, third rotor module, fourth rotor module, battery: still include head rod, second connecting rod, third connecting rod, fourth connecting rod, first rotor seat, second rotor seat, third rotor seat, fourth rotor seat, first fixing base, second fixing base, third fixing base and fourth fixing base, the utility model discloses a modularized design can conveniently be loaded and unloaded to realize unmanned aerial vehicle mobility promotes advancing device's installation, the fixed -wing aircraft that can match multiple model, size.

Description

UAV Maneuver lifts propulsion plant

Technical field

The utility model is related to a kind of UAV Maneuver lifting propulsion plant.

Background technology

Existing quadrotor technology is more ripe, it is possible to achieve relatively stable flight effect, four rotor flyings Device adopts four rotors as the direct driving force source of flight, rotor be symmetrically distributed in body around four direction, four Rotor is in sustained height plane, and the structure of four rotors is all identical with radius, rotor 1 and rotor 3 rotate counterclockwise, rotor 2 and rotor 4 turn clockwise, four motors are symmetrically installed on the bracket end of aircraft, support intermediate space lay flight control Computer processed and external equipment.Progress with four rotor technology and maturation, existing fixed-wing unmanned plane also can assemble four rotations The wing, fixed-wing four rotor composite aircraft (compound four rotors) is a kind of latest developments successfully new vertical takeoff and landing vehicle, Simple and effective VTOL solution is obtained using four rotors and fixed wing aircraft platform combination, there is many-side Advantage it is contemplated that having preferable development prospect.During existing fixed wing aircraft installs four rotors additional, there is problems that Four rotors install that structure is complex additional, and the fixed wing aircraft of different model, size cannot be mated.

Utility model content

The purpose of this utility model is to overcome above-mentioned deficiency present in prior art, and provides a kind of structure design to close Reason, installs that structure is relatively simple additional, and can mate the UAV Maneuver lifting of the fixed wing aircraft of Multiple Type, size and push away Enter device.

The technical scheme in the invention for solving the above technical problem is：

A kind of UAV Maneuver lifts propulsion plant, including battery, control module, the first rotor module, the second rotation Wing module, the 3rd rotor module and the 4th rotor module, the first rotor module, the second rotor module, the 3rd rotor module, Four rotor module, battery be all connected with control module it is characterised in that：Also include head rod, the second connecting rod, the 3rd company Extension bar, the 4th connecting rod, the first rotor seat, the second rotor seat, the 3rd rotor seat, the 4th rotor seat, the first fixed seat, second solid Reservation, the 3rd fixed seat and the 4th fixed seat, the first rotor module, the second rotor module, the 3rd rotor module, the 4th rotor mould Block be separately fixed at the first rotor seat, the second rotor seat, the 3rd rotor seat, on the 4th rotor seat, the first rotor seat, the second rotor Seat, the 3rd rotor seat, the 4th rotor seat, the first fixed seat, the second fixed seat, the 3rd fixed seat, the 4th fixed seat all offer Adjustment hole is installed, the two ends of described head rod respectively penetrate the peace installing adjustment hole and the first fixed seat of the first rotor seat Debug knothole, the two ends of described second connecting rod respectively penetrate the installation installing adjustment hole and the second fixed seat of the second rotor seat Adjustment hole, the two ends of described 3rd connecting rod respectively penetrate the installation tune installing adjustment hole and the 3rd fixed seat of the 3rd rotor seat Knothole, the two ends of described 4th connecting rod respectively penetrate the installation regulation installing adjustment hole and the 4th fixed seat of the 4th rotor seat Hole, the first rotor seat, the second rotor seat, the 3rd rotor seat, the 4th rotor seat, the first fixed seat, the second fixed seat, the 3rd fixation All offer on seat and the 4th fixed seat for adjusting, to installation, the screwed hole that in the hole is screwed into the first fixed screw, first is fixing It is fixed with fixing for being screwed into second in the fuselage to unmanned plane in seat, the second fixed seat, the 3rd fixed seat and the 4th fixed seat The installing hole of screw.

Preferably, also including the 5th rotor module and the 5th fixed seat, described 5th rotor module link control module.

Preferably, the first rotor seat, the second rotor seat all include rotor fixed seat and rotor wing rotation seat, the first rotor mould Block, the second rotor module be separately fixed at the rotor wing rotation seat of the first rotor seat, on the rotor wing rotation seat of the second rotor seat, rotor Rotating seat is rotatably installed in rotor fixed seat, and rotor fixed seat is fixed with the driving horse for driving rotor wing rotation seat to rotate Reach, described drive motor link control module.Rotated relative to rotor fixed seat by drive motor rotor wing rotation seat, thus The first rotor seat, the angle of the second rotor seat can be adjusted, thus realizing providing propulsive force forward, raising efficiency, strengthen no Man-machine wind resistance, the speed of a ship or plane and mobility.

Preferably, the 5th fixed seat includes rotor fixed seat and rotor wing rotation seat, the rotor wing rotation seat of the 5th rotor seat On, rotor wing rotation seat is rotatably installed in rotor fixed seat, and rotor fixed seat is fixed with for driving rotor wing rotation seat to rotate Drive motor, described drive motor link control module.

Preferably, head rod and the 3rd connecting rod are fixed, the second connecting rod and the 4th connecting rod are fixed.

The utility model compared with prior art, has advantages below and effect：The utility model adopts modularized design Can conveniently load and unload, be easy to carry, specifically due to adopting light foam material the fuselage of existing civilian amusement unmanned plane more, Screw can easily be screwed into the fuselage of unmanned plane, thus it is solid to realize the first fixed seat, the second fixed seat, the 3rd fixed seat and the 4th The fixation of reservation, thus realize the installation that UAV Maneuver lifts propulsion plant；The fixation of Multiple Type, size can be mated Wing aircraft, thus fixed-wing unmanned plane is improved to the unmanned plane possessing VTOL function；The position of rotor module is adjustable, from And go for the unmanned installation requirements of different shape size, the fixed wing aircraft of Multiple Type, size can be mated Install demand additional, specifically due to head rod, the second connecting rod, the 3rd connecting rod, the 4th connecting rod can respectively relatively First fixed seat, the second fixed seat, the 3rd fixed seat and the 4th fixed seat are slided, thus adjust respectively the first rotor module, the The position of two rotor module, the 3rd rotor module and the 4th rotor module；Possess independent battery, control module, disobey Relying the control device in unmanned plane, therefore can be, in installation process, the control system of original unmanned plane need not be made and to change, fall Low operation easier.

Brief description

Fig. 1 is the structural representation that the utility model embodiment UAV Maneuver lifts propulsion plant.

Fig. 2 is the knot being arranged on fixed-wing unmanned plane that the utility model embodiment UAV Maneuver lifts propulsion plant Structure schematic diagram one.

Fig. 3 is the knot being arranged on fixed-wing unmanned plane that the utility model embodiment UAV Maneuver lifts propulsion plant Structure schematic diagram two.

Fig. 4 is the utility model embodiment rotor fixed seat and the structural representation of rotor wing rotation seat assembling.

Specific embodiment

The utility model is described in further detail below in conjunction with the accompanying drawings and by embodiment, and following examples are right Of the present utility model explain and the utility model is not limited to following examples.

Referring to Fig. 1-Fig. 3, a kind of UAV Maneuver of the present embodiment lifted propulsion plant, including battery, control module, First rotor module 11, the second rotor module 12, the 3rd rotor module 13 and the 4th rotor module 14, the first rotor module 11st, the second rotor module 12, the 3rd rotor module 13, the 4th rotor module 14, battery are all connected with control module, unmanned plane machine Dynamic property lifting propulsion plant also include head rod 21, the second connecting rod 22, the 3rd connecting rod 23, the 4th connecting rod 24, the One rotor seat 31, the second rotor seat 32, the 3rd rotor seat 33, the 4th rotor seat 34, the first fixed seat 41, the second fixed seat 42, 3rd fixed seat 43 and the 4th fixed seat 44, the first rotor module 11, the second rotor module 12, the 3rd rotor module the 13, the 4th Rotor module 14 be separately fixed at the first rotor seat 31, the second rotor seat 32, the 3rd rotor seat 33, on the 4th rotor seat 34, One rotor seat 31, the second rotor seat 32, the 3rd rotor seat 33, the 4th rotor seat 34, the first fixed seat 41, the second fixed seat 42, 3rd fixed seat 43, the 4th fixed seat 44 all offer installation adjustment hole 51, and the two ends of described head rod 21 respectively penetrate The installation adjustment hole 51 installing adjustment hole 51 and the first fixed seat 41 of the first rotor seat 31, the two ends of described second connecting rod 22 Respectively penetrate the installation adjustment hole 51 installing adjustment hole 51 and the second fixed seat 42 of the second rotor seat 32, described 3rd connecting rod 23 two ends respectively penetrate the installation adjustment hole 51 installing adjustment hole 51 and the 3rd fixed seat 43 of the 3rd rotor seat 33, and described the The two ends of four connecting rods 24 respectively penetrate the installation adjustment hole installing adjustment hole 51 and the 4th fixed seat 44 of the 4th rotor seat 34 51, the first rotor seat 31, the second rotor seat 32, the 3rd rotor seat 33, the 4th rotor seat 34, the first fixed seat 41, second are fixing All offer in seat the 42, the 3rd fixed seat 43 and the 4th fixed seat 44 for being screwed into the first fixed screw into installation adjustment hole 51 52 screwed hole, the first fixed seat 41, the second fixed seat 42, the 3rd fixed seat 43 and the 4th fixed seat 44 are fixed with for It is screwed into the installing hole 53 of the second fixed screw in the fuselage of unmanned plane.

UAV Maneuver lifting propulsion plant also includes the 5th rotor module 35 and the 5th fixed seat 45, described 5th rotation Wing module 35 link control module.

In the present embodiment, head rod 21 and the 3rd connecting rod 23 are fixing, the second connecting rod 22 and the 4th connecting rod 24 Fixing.

As shown in figure 4, the structure in the present embodiment can improve as follows, the first rotor seat 31, the second rotor seat further 32 all include rotor fixed seat 61 and rotor wing rotation seat 62, and the first rotor module 11, the second rotor module 12 are separately fixed at On the rotor wing rotation seat 62 of one rotor seat 31, the rotor wing rotation seat 62 of the second rotor seat 32, rotor wing rotation seat 62 is rotatably installed in In rotor fixed seat 61, rotor fixed seat 61 is fixed with the drive motor for driving rotor wing rotation seat 62 to rotate, described driving Motor link control module.5th fixed seat 45 includes rotor fixed seat 61 and rotor wing rotation seat 62, the rotor of the 5th rotor seat On rotating seat 62, rotor wing rotation seat 62 is rotatably installed in rotor fixed seat 61, and rotor fixed seat 61 is fixed with for driving rotation The drive motor 63 that wing rotating seat 62 rotates, described drive motor 63 link control module.Drive motor is via first bevel gear 71st, second bevel gear 72, first gear 73, second gear 74 realize the rotation to rotor wing rotation seat, specifically, the second cone tooth Wheel, first gear are rotatably installed in rotor fixed seat 61, and first bevel gear is fixed in the drive shaft of drive motor, and described the Two gears are fixed on rotor wing rotation seat 62, and second bevel gear and first gear are fixed in same rotating shaft, described first cone tooth Wheel, second bevel gear engage each other, and first gear, second gear engage each other.Using this structure, it is possible to achieve drive horse Reach fore-and-aft direction arrangement, such that it is able to reduce structural volume, reduce windage.

It should be noted that because the technology of existing quadrotor, five rotor crafts is more ripe, this enforcement Battery, control module, the first rotor module 11, the second rotor module 12, the 3rd rotor module 13 and the 4th rotor in example The respective circuit structure of module 14 and its circuit connection structure each other, software control method all can adopt existing skill Art realize, the present embodiment subject matter to be solved be rotor module install assembling frame for movement problem, therefore for Battery, control module, the first rotor module 11, the second rotor module 12, the 3rd rotor module 13 and the 4th rotor module 14 respective circuit structure and its attachment structure each other, software control method are not described further, industry technology Personnel can realize the technical scheme of the present embodiment in conjunction with the prior art of the industry.

Above content described in this specification is only to the utility model example explanation.The utility model Person of ordinary skill in the field can make various modifications or supplement or adopt class to described specific embodiment As mode substitute, the content without departing from the utility model specification or surmount model defined in the claims Enclose, protection domain of the present utility model all should be belonged to.

Claims (5)

1. a kind of UAV Maneuver lifts propulsion plant, including battery, control module, the first rotor module, the second rotor Module, the 3rd rotor module and the 4th rotor module, the first rotor module, the second rotor module, the 3rd rotor module, the 4th Rotor module, battery be all connected with control module it is characterised in that：Also include head rod, the second connecting rod, the 3rd connection Bar, the 4th connecting rod, the first rotor seat, the second rotor seat, the 3rd rotor seat, the 4th rotor seat, the first fixed seat, the second fixation Seat, the 3rd fixed seat and the 4th fixed seat, the first rotor module, the second rotor module, the 3rd rotor module, the 4th rotor module Be separately fixed at the first rotor seat, the second rotor seat, the 3rd rotor seat, on the 4th rotor seat, the first rotor seat, the second rotor Seat, the 3rd rotor seat, the 4th rotor seat, the first fixed seat, the second fixed seat, the 3rd fixed seat, the 4th fixed seat all offer Adjustment hole is installed, the two ends of described head rod respectively penetrate the peace installing adjustment hole and the first fixed seat of the first rotor seat Debug knothole, the two ends of described second connecting rod respectively penetrate the installation installing adjustment hole and the second fixed seat of the second rotor seat Adjustment hole, the two ends of described 3rd connecting rod respectively penetrate the installation tune installing adjustment hole and the 3rd fixed seat of the 3rd rotor seat Knothole, the two ends of described 4th connecting rod respectively penetrate the installation regulation installing adjustment hole and the 4th fixed seat of the 4th rotor seat Hole, the first rotor seat, the second rotor seat, the 3rd rotor seat, the 4th rotor seat, the first fixed seat, the second fixed seat, the 3rd fixation All offer on seat and the 4th fixed seat for adjusting, to installation, the screwed hole that in the hole is screwed into the first fixed screw, first is fixing It is fixed with fixing for being screwed into second in the fuselage to unmanned plane in seat, the second fixed seat, the 3rd fixed seat and the 4th fixed seat The installing hole of screw.

2. UAV Maneuver according to claim 1 lifting propulsion plant it is characterised in that：Also include the 5th rotor mould Block and the 5th fixed seat, described 5th rotor module link control module.

3. UAV Maneuver according to claim 1 lifting propulsion plant it is characterised in that：First rotor seat, second Rotor seat all includes rotor fixed seat and rotor wing rotation seat, and the first rotor module, the second rotor module are separately fixed at the first rotation On the rotor wing rotation seat of wing seat, the rotor wing rotation seat of the second rotor seat, rotor wing rotation seat is rotatably installed in rotor fixed seat, rotation Wing fixed seat is fixed with the drive motor for driving rotor wing rotation seat to rotate, described drive motor link control module.

4. UAV Maneuver according to claim 2 lifting propulsion plant it is characterised in that：5th fixed seat includes revolving Wing fixed seat and rotor wing rotation seat, on the rotor wing rotation seat of the 5th rotor seat, rotor wing rotation seat is rotatably installed in rotor fixed seat On, rotor fixed seat is fixed with the drive motor for driving rotor wing rotation seat to rotate, described drive motor link control module.

5. UAV Maneuver according to claim 1 lifting propulsion plant it is characterised in that：Head rod and the 3rd Connecting rod is fixed, and the second connecting rod and the 4th connecting rod are fixed.