CN106540460A - Quadrotor rotor characteristic integrated test system - Google Patents
Quadrotor rotor characteristic integrated test system Download PDFInfo
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- CN106540460A CN106540460A CN201510603252.8A CN201510603252A CN106540460A CN 106540460 A CN106540460 A CN 106540460A CN 201510603252 A CN201510603252 A CN 201510603252A CN 106540460 A CN106540460 A CN 106540460A
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Abstract
A kind of quadrotor rotor characteristic integrated test system of the present invention, including main body frame, empennage, landing gear, the mechanism for providing power and remote receiver, include the power of the first described motor while passing to the belt gear reduction gearing mechanism of the first propeller, the second propeller and tail propeller in the described mechanism that power is provided；Present invention achieves first motor drives the first propeller, the second propeller and tail propeller rotational simultaneously, eliminate two power motors, the weight of quadrotor rotor characteristic integrated test system itself is greatly reduced, so as to improve the mobility of quadrotor rotor characteristic integrated test system.
Description
Technical field
The present invention relates to a kind of electronic toy, more particularly, the present invention relates to a kind of quadrotor rotor characteristic integrated test system.
Background technology
As requirement of the people to quadrotor rotor characteristic integrated test system is improved constantly，Often require that quadrotor rotor characteristic integrated test system has good flying quality，To increase the interest for manipulating quadrotor rotor characteristic integrated test system，Far-reaching to the flying quality of quadrotor rotor characteristic integrated test system is the weight of quadrotor rotor characteristic integrated test system，Double oar quadrotor rotor characteristic integrated test systems complete power supply typically all by two first motors，It is also required to two sets of each independent actuating units，Tail propeller is also required to an independent motor to drive simultaneously，This makes quadrotor rotor characteristic integrated test system considerably increase weight，Therefore in order to mitigate the weight of quadrotor rotor characteristic integrated test system，Need to provide a kind of mechanism section parts that quadrotor rotor characteristic integrated test system offer power in prior art is provided to mitigate the quadrotor rotor characteristic integrated test system of whole quadrotor rotor characteristic integrated test system weight.
The content of the invention
The technical problem to be solved is provide can mitigate model plane own wt and reduces cost for the defect existing for above-mentioned prior art, can improve the quadrotor rotor characteristic integrated test system of model plane mobility again.
Solving the technical scheme that adopted of present invention problem is：A kind of quadrotor rotor characteristic integrated test system, including main body frame, with the back-connected empennage of main body frame, it is connected to support the landing gear of the main body frame with main body frame bottom, the mechanism of the offer power being arranged on the main body frame and empennage and the remote receiver of external control signal can be received, the mechanism of described offer power includes the first motor, power transmission shaft, through the rotary shaft of the power transmission shaft, the first propeller being arranged in rotary shaft, the second propeller being arranged on power transmission shaft and the tail propeller being arranged on tailing axle, and the power of the first described motor is passed to into the first propeller simultaneously, the belt gear reduction gearing mechanism of the second propeller and tail propeller.
The beneficial effects of the present invention is：Present invention achieves first motor drives the first propeller, the second propeller and tail propeller rotational simultaneously, significantly reduce the weight of quadrotor rotor characteristic integrated test system itself, so as to improve the mobility of quadrotor rotor characteristic integrated test system, while also reducing the manufacturing cost of quadrotor rotor characteristic integrated test system.
As the preferred implementation of quadrotor rotor characteristic integrated test system of the present invention, described belt gear reduction gearing mechanism includes the motor gear being fixed on motor output shaft, the one-level driven gear engaged with the motor gear, the one-level band gear coaxial with one-level driven gear, the two grades of driven gears for engaging with one-level driven gear and being connected with described power transmission shaft one end, the two grade band gears coaxial with two grades of driven gears, it is fixed on three-level band gear in rotary shaft, and it is connected level Four band gear with tailing axle, one-level band gear is connected with three-level band gear by level synchronization transporter, two grades of band gears are connected with level Four band gear by secondary synchronization transporter.
As another preferred implementation of quadrotor rotor characteristic integrated test system of the present invention, the described two grades both sides for being respectively placed in two grades of driven gears with gear and three-level with gear.
As another preferred implementation of quadrotor rotor characteristic integrated test system of the present invention, described belt gear reduction gearing mechanism also includes being arranged at described one-level pulley cover of the one-level with gear side, it is arranged at two grades of described with gear side two grades of pulley covers, it is arranged at described three-level pulley cover of the three-level with gear side, it is arranged at described level Four pulley cover of the level Four with gear side, described one-level pulley cover, three-level pulley cover is used to prevent level synchronization transporter from slipping, two grades of described pulley covers, level Four pulley cover is used to prevent secondary synchronization transporter from slipping.
As another preferred implementation of quadrotor rotor characteristic integrated test system of the present invention, described belt gear reduction gearing mechanism is additionally provided with the roller devices for making two grades of connection tensioning of the secondary synchronization transporter with gear with level Four with gear, the roller devices make secondary synchronization transporter be stretched on two grades of band gears and level Four band gear at any time, to prevent synchronous belt from sliding on two grades of band gears and level Four band gear.
As another preferred implementation of quadrotor rotor characteristic integrated test system of the present invention, which also includes front level controller and is arranged at the rear level controller of the empennage, described front level controller includes the swash plate that leans forward on power transmission shaft, front steering wheel, connect the front rod of front steering wheel and the swash plate that leans forward, leaning forward on main body frame and connects lean forward swash plate leading truck and the master link of swash plate of leaning forward at swash plate leading truck, described rear level controller includes the hypsokinesis swash plate on tailing axle, steering wheel afterwards, the slave connecting rod of steering wheel and hypsokinesis swash plate after connection, hypsokinesis swash plate leading truck on empennage frame and connect the secondary connecting rod of the hypsokinesis swash plate leading truck and hypsokinesis swash plate, it is main, rear level controller more neatly realizes the steering of quadrotor rotor characteristic integrated test system.
As another preferred implementation of quadrotor rotor characteristic integrated test system of the present invention, which also includes dynamic balancer, described dynamic balancer includes gimbal lever's union joint, the gimbal lever and is arranged at the balance weight at gimbal lever two ends, described dynamic balancer is arranged on the upper end of rotary shaft by gimbal lever's union joint, its whole body is balanced during the dynamic balancer quadrotor rotor characteristic integrated test system flight, make quadrotor rotor characteristic integrated test system more can safety and steady flight.
Below in conjunction with drawings and Examples, technical scheme is described in further detail.
Description of the drawings
Structural representations of the Fig. 1 for the quadrotor rotor characteristic integrated test system of a preferred embodiment of the present invention.
Specific embodiment
With reference now to Description of Drawings the preferred embodiments of the present invention,.
With reference to Fig. 1, quadrotor rotor characteristic integrated test system of the present invention include main body frame 1, and the back-connected empennage 2 of main body frame, and main body frame bottom be connected to support the landing gear 3 of the main body frame, the mechanism 4 of the offer power being arranged on the main body frame 1 and empennage 2, the remote receiver 5 that external control signal can be received on main body frame 1.
The mechanism 4 of described offer power includes the first motor、Power transmission shaft、Through the rotary shaft of the power transmission shaft、Installation the first propeller on the rotary shaft and the second propeller by back blades folder on power transmission shaft are pressed from both sides by primary blades，First motor is arranged on main body frame 1，Motor gear is installed on its output shaft，The one-level driven gear engaged with the motor gear，One-level driven gear is positioned on the bearing block of main body frame 1 by bearing，The one-level band gear coaxial with one-level driven gear，Side of the one-level with gear is additionally provided with one-level pulley cover，The two grades of driven gears for engaging with one-level driven gear and being connected with described power transmission shaft one end，Two grades of driven gears are positioned on the bearing block of main body frame 1 by bearing，The two grade band gears coaxial with two grades of driven gears，Two grades of sides with gear are additionally provided with two grades of pulley covers，Three-level band gear is fixed in rotary shaft,Rotary shaft lower end is positioned on the bearing block of main body frame 1 by bearing，Three-level band gear side is additionally provided with bearing three-level pulley cover，The level Four band gear side being connected with tailing axle is additionally provided with level Four pulley cover,One-level band gear is connected with three-level band gear by level synchronization transporter，Two grades of band gears are connected with level Four band gear by secondary synchronization transporter，Tail propeller is by caudal lobe piece folder on tailing axle，Tailing axle is positioned on the bearing block of tailstock by bearing，One-level pulley cover and bearing three-level pulley cover are used for the slippage for preventing the first belt pulley，Two grades of pulley covers and level Four pulley cover are used for the slippage for preventing the second belt pulley；Both sides near the second belt pulley on main body frame 1 are additionally provided with the adjustable roller devices for making belt pulley keep tensioning state at any time in position, and roller devices also can be replaced with other devices in other embodiments certainly.
The first described Motor drive is arranged on the rotation of the motor gear in its drive shaft, motor gear rotation rotates the one-level driven gear for engaging, so as to drive engage with one-level driven gear two grades of driven gear rotations, two grades of driven gear rotations rotate the power transmission shaft being fixed thereon, so as to drive the second propeller for being fixed on power transmission shaft to rotate;The rotation of one-level driven gear rotates the one-level band gear being coaxial therewith, and be rotated through first belt pulley of the one-level with gear passes to three-level band gear, and rotarily drive rotary shaft of the three-level with gear rotates, and rotary shaft rotarily drives the rotation of the first propeller being fixed thereon；Two grades of driven gear rotations make two grades of rotations with gear being coaxial therewith, two grades of second belt pulleys that are rotated through with gear pass on level Four band gear, the rotation that rotarily drive the tail propeller that with tail propeller 32 be fixed on tailing axle on of the level Four with gear.First motor is achieved in that while driving the rotation of the first propeller, the second propeller and tail propeller, two motors has been eliminated, is significantly reduced the weight of model plane itself, improve the flying quality of model plane, while also saving manufacturing cost.
Described quadrotor rotor characteristic integrated test system also includes front level controller and is arranged at the rear level controller of the empennage, described front level controller includes the swash plate that leans forward on power transmission shaft, front steering wheel, connect the front rod of front steering wheel and the swash plate that leans forward, lean forward and swash plate leading truck and connect lean forward swash plate leading truck and the master link of swash plate of leaning forward, described rear level controller includes the hypsokinesis swash plate on tailing axle, steering wheel afterwards, the slave connecting rod of steering wheel and hypsokinesis swash plate after connection, hypsokinesis swash plate leading truck and connect the secondary connecting rod of the hypsokinesis swash plate leading truck and hypsokinesis swash plate, the steering of level controller and rear level controller co- controlling quadrotor rotor characteristic integrated test system in front of this, make the steering of quadrotor rotor characteristic integrated test system more flexible.
The quadrotor rotor characteristic integrated test system also includes dynamic balancer, the dynamic balancer includes gimbal lever's union joint, the gimbal lever and is arranged at the balance weight at gimbal lever two ends, the gimbal lever is arranged on the upper end of rotary shaft by gimbal lever's union joint, the dynamic balancer makes to balance its whole body during quadrotor rotor characteristic integrated test system flight, make quadrotor rotor characteristic integrated test system more can safety and steady flight.
It is last be should be noted that; above example is only to illustrate technical scheme rather than limiting the scope of the invention; although being explained in detail to the present invention with reference to preferred embodiment; but it will be understood by those within the art that; technical scheme can be modified or equivalent, without deviating from the spirit and scope of technical solution of the present invention.
Claims (7)
1. a kind of quadrotor rotor characteristic integrated test system, it is characterised in that：Including main body frame、Empennage、Landing gear、Mechanism and the remote receiver of the offer power of the main body frame are provided，The mechanism of described offer power includes the first motor、Power transmission shaft、Through the rotary shaft of the power transmission shaft、The first propeller being arranged in rotary shaft、The second propeller being arranged on power transmission shaft and the tail propeller being arranged on tailing axle，The mechanism of described offer power is also included the power of the first described motor while passing to the first propeller、The belt gear reduction gearing mechanism of the second propeller and tail propeller，Described belt gear reduction gearing mechanism includes the motor gear being fixed on motor output shaft，The one-level driven gear engaged with the motor gear，The one-level band gear coaxial with one-level driven gear，The two grades of driven gears for engaging with one-level driven gear and being connected with described power transmission shaft one end，The two grade band gears coaxial with two grades of driven gears，The three-level band gear being fixed in rotary shaft，The level Four band gear being connected with tailing axle,One-level band gear is connected with three-level band gear by level synchronization transporter，Two grades of band gears are connected with level Four band gear by secondary synchronization transporter.
2. quadrotor rotor characteristic integrated test system as claimed in claim 1, it is characterised in that：Described belt gear reduction gearing mechanism also includes being arranged at described one-level pulley cover of the one-level with gear side, it is arranged at two grades of described with gear side two grades of pulley covers, described three-level pulley cover of the three-level with gear side is arranged at, described level Four pulley cover of the level Four with gear side is arranged at.
3. quadrotor rotor characteristic integrated test system as claimed in claim 2, it is characterised in that：Described belt gear reduction gearing mechanism is additionally provided with the device for making two grades of connection tensioning of the synchronous belt with gear with level Four with gear.
4. quadrotor rotor characteristic integrated test system as claimed in claim 3, it is characterised in that：The device of the synchronous belt tensioning is roller.
5. quadrotor rotor characteristic integrated test system as claimed in claim 1, it is characterised in that：Which also includes dynamic balancer, and described dynamic balancer includes gimbal lever's union joint, the gimbal lever and is arranged at the balance weight at gimbal lever two ends, and described dynamic balancer is arranged on the upper end of rotary shaft by gimbal lever's union joint.
6. quadrotor rotor characteristic integrated test system as claimed in claim 1, it is characterised in that：Which also includes front level controller and is arranged at the rear level controller of the empennage, described front level controller includes the swash plate that leans forward on power transmission shaft, front steering wheel, the front rod of steering wheel and the swash plate that leans forward before connection, leaning forward swash plate leading truck and is connected the master link of lean forward swash plate leading truck and the swash plate that leans forward, described rear level controller includes hypsokinesis swash plate on tailing axle, rear steering wheel, connect after the connecting rod of steering wheel and hypsokinesis swash plate, hypsokinesis swash plate leading truck and be connected the secondary connecting rod of the hypsokinesis swash plate leading truck and hypsokinesis swash plate.
7. quadrotor rotor characteristic integrated test system as claimed in claim 1, it is characterised in that：The first propeller folder is additionally provided with described rotary shaft, the first described propeller is clamping in the described rotary shaft by first propeller, the second propeller folder is provided with described power transmission shaft, the second described propeller is clamping on the power transmission shaft by second propeller, it is additionally provided with tail propeller folder on described tailing axle, described tail propeller is clamping on the described tailing axle by the tail propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510603252.8A CN106540460A (en) | 2015-09-20 | 2015-09-20 | Quadrotor rotor characteristic integrated test system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510603252.8A CN106540460A (en) | 2015-09-20 | 2015-09-20 | Quadrotor rotor characteristic integrated test system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106540460A true CN106540460A (en) | 2017-03-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510603252.8A Withdrawn CN106540460A (en) | 2015-09-20 | 2015-09-20 | Quadrotor rotor characteristic integrated test system |
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| CN (1) | CN106540460A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106552427A (en) * | 2015-09-25 | 2017-04-05 | 郑华耀 | Multiple stage gear reduction system model plane |
| CN106552426A (en) * | 2015-09-25 | 2017-04-05 | 郑华耀 | Multiple propeller propulsion system high-altitude flight device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5023791A (en) * | 1990-02-12 | 1991-06-11 | The Boeing Company | Automated test apparatus for aircraft flight controls |
| US6048247A (en) * | 1998-04-13 | 2000-04-11 | Spinmaster Toys, Ltd | Main wing positioning and release system for a toy aircraft |
| CN201370967Y (en) * | 2009-02-19 | 2009-12-30 | 林植锋 | Electric remote control propeller-driven aircraft |
| CN104787332A (en) * | 2015-03-10 | 2015-07-22 | 于潮 | Aeromodelling aircraft |
| CN106492476A (en) * | 2015-09-03 | 2017-03-15 | 马铿杰 | The high-altitude vehicle of tailspin oar control azimuth |
-
2015
- 2015-09-20 CN CN201510603252.8A patent/CN106540460A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5023791A (en) * | 1990-02-12 | 1991-06-11 | The Boeing Company | Automated test apparatus for aircraft flight controls |
| US6048247A (en) * | 1998-04-13 | 2000-04-11 | Spinmaster Toys, Ltd | Main wing positioning and release system for a toy aircraft |
| CN201370967Y (en) * | 2009-02-19 | 2009-12-30 | 林植锋 | Electric remote control propeller-driven aircraft |
| CN104787332A (en) * | 2015-03-10 | 2015-07-22 | 于潮 | Aeromodelling aircraft |
| CN106492476A (en) * | 2015-09-03 | 2017-03-15 | 马铿杰 | The high-altitude vehicle of tailspin oar control azimuth |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106552427A (en) * | 2015-09-25 | 2017-04-05 | 郑华耀 | Multiple stage gear reduction system model plane |
| CN106552426A (en) * | 2015-09-25 | 2017-04-05 | 郑华耀 | Multiple propeller propulsion system high-altitude flight device |
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Application publication date: 20170329 |