CN203623971U - Single-power multi-shaft aircraft - Google Patents
Single-power multi-shaft aircraft Download PDFInfo
- Publication number
- CN203623971U CN203623971U CN201320714543.0U CN201320714543U CN203623971U CN 203623971 U CN203623971 U CN 203623971U CN 201320714543 U CN201320714543 U CN 201320714543U CN 203623971 U CN203623971 U CN 203623971U
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- power
- shaft
- axis aircraft
- spur
- propeller
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Abstract
The utility model relates to a multi-shaft aircraft driven by only single power. The multi-shaft aircraft mainly comprises a gear box (1), carbon fiber brackets (2), propeller pitch adjusting mechanisms (3), steering engines (4), straight spur gear transmission mechanisms (5), straight bevel gear transmission mechanisms (6) and propellers (7). A central power device transmits power to each propeller through a gear transmission mechanism and a shaft transmission mechanism so as to achieve the same rotating speed of all the propellers and opposite rotating directions of adjacent propellers; the propeller pitch of each propeller is changed by the steering engine to adjust pull force generated by the propellers so as to control the posture of the aircraft.
Description
Technical field
The utility model relates to a kind of single-power multi-axis aircraft, and the power transmission and the flight that are mainly used in the power operated Multi-axis aircraft of single oil machine are controlled.
Background technology
The application of unmanned vehicle in agricultural is in the fast-developing stage, and unmanned vehicle is engaged in agriculture, the operation flight of forestry, animal husbandry, fish production and rescue and relief work.Be mainly agriculturally Agricultural Information collection, sowing, fertilising, weeding, control the operations such as worm.Aircraft has the irreplaceable advantages such as strong adaptability, efficiency is high, energy consumption is low with respect to common ground Work machine.Other aircraft such as the relative fixed-wing of unmanned Multi-axis aircraft have the advantages such as the high and turn radius of fixed point flight performance, stability is little, but the stepless time adjustment of many power must be used multiple electrical motors, owing to limited by the power of battery, the torque of electrical motor is less than normal, is difficult for realizing high load-carrying flying for long time.Although and oil machine power is large, multiple oil machines are difficult to guarantee that power output is consistent, therefore cannot directly replace motor by oil machine.But adopt single oil machine power to output to the aircraft of multiaxis, less demanding to power speed adjustment, can regulate lift by the pitch of propeller blades.This device can be realized single-power and stable power is provided and obtain good flight control ability to the each screw propeller of Multi-axis aircraft, provides necessary condition for Multi-axis aircraft adopts single oil machine dynamical stability flight.
Summary of the invention
The purpose of this utility model is just to provide a kind of single oil machine power driven Multi-axis aircraft, realize the requirement of high load-carrying stabilized flight, this power can be provided by the engine installation of multiple high torque (HT), realize the accurate transfer of rotating speed and torque by multiple gear drive and shaft transmission, and the lift that regulates each screw propeller to produce by steering wheel, realize the high load-carrying of Multi-axis aircraft, stable flight.
Technical solutions of the utility model are such:
The utility model is made up of gear case (1), carbon fiber support (2), oar pitch adjustment mechanism (3), steering wheel (4), spur gear transmission mechanism (5), Straight Bevel Gear Drive mechanism (6), screw propeller (7) etc.Power passes to each prop shaft by center shaft accurately by gear drive and shaft transmission, regulates pitch to realize the attitude control of Multi-axis aircraft by steering wheel, realizes stabilized flight.
Screw propeller is arranged on each axle, be connected with steering wheel by pull bar, support is connected with gear adapter plate, and transmission shaft is fixed in support tube, by spur bevel gear wheel mechanism and spur wheel mechanism etc., the motion of each axle is connected, keep each transverse tube of support in same level simultaneously.
Between main shaft and power take-off shaft, adopt coupler to be connected, make the replacing of engine installation convenient.
Bracing frame is fixed on transmission tube, to be conducive to the stable landing of aircraft, avoids blade to contact with ground simultaneously, play the effect of protection blade.
accompanying drawing explanation
Fig. 1 is structural representation of the present utility model
Fig. 2 is the structural representation of gear case
Fig. 3 is the structure diagram of gear case
Fig. 4 is the structural representation of propeller pitch adjustment means
In Fig. 1,1. gear case, 2. carbon fiber support, 3. screw propeller distance regulating mechanism, 4. steering wheel, 5. spur gear transmission mechanism, 6. Straight Bevel Gear Drive mechanism, 7. screw propeller.
the specific embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail with enforcement:
One, overall
Concrete structure of the present invention as shown in Figure 1, power is delivered to main shaft gearbox (1) by coupler, two center disk gears are rotated, drive four spur gear transmission mechanisms (5) around to rotate, pass to transverse axis by spur bevel gear wheel (6) again, by driven off by shaft mode, power is passed to four screw propellers (7).Due to the opposite direction of adjacent spur gear transmission mechanism (5) installation, make to pass to the direction of rotation of each adjacent prop shaft, drive the pitch of screw propeller apart from control apparatus (3) propeller blades (7) by the pull bar being connected with steering wheel (4) simultaneously, change the lift that screw propeller (7) produces, realize Multi-axis aircraft stabilized flight and flight attitude control.
Two, each parts
As Fig. 2, Fig. 3, gear case (1), spur wheel mechanism (5) and spur bevel gear wheel mechanism (6) connect and compose central transmission, by adjacent diaxon and the positive and negative installation of center shaft gears in mesh group, make to be transferred to the direction of rotation on adjacent shaft, the anti-twisted power that payment screw propeller produces.
As Fig. 4, pull bar drives linear bearing up-and-down movement, then drives pitch of propeller regulating mechanism (3) to rotate a certain angle by connecting rod, thereby changes pitch, and the different lift producing in the situation that rotating speed is certain, to control the attitude of aircraft.
Claims (4)
1. a single-power multi-axis aircraft, formed by gear case (1), carbon fiber support (2), oar pitch adjustment mechanism (3), steering wheel (4), spur gear transmission mechanism (5), Straight Bevel Gear Drive mechanism (6), screw propeller (7) etc., power passes to each prop shaft by center shaft, realizes the attitude control of Multi-axis aircraft by the pitch of steering wheel propeller blades.
2. according to the single-power multi-axis aircraft described in claims 1, it is characterized in that, by spur wheel mechanism and spur bevel gear wheel mechanism, the power transmission of center shaft is arrived to each axle, the rotating speed of realizing each prop shaft is identical, the switched in opposite between adjacent shaft.
3. according to the single-power multi-axis aircraft described in claims 1, it is characterized in that, by Liang Ge center fluted disc respectively with coaxial spur wheel and the positive and negative installation of spur bevel gear wheel mechanism, realize the direction of rotation of adjacent diaxon.
4. according to the single-power multi-axis aircraft described in claims 1, it is characterized in that regulating the pitch of each screw propeller to realize each axle under same rotational speed by steering wheel produces different lift, realize the control to Multi-axis aircraft attitude.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320714543.0U CN203623971U (en) | 2013-11-10 | 2013-11-10 | Single-power multi-shaft aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320714543.0U CN203623971U (en) | 2013-11-10 | 2013-11-10 | Single-power multi-shaft aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203623971U true CN203623971U (en) | 2014-06-04 |
Family
ID=50810470
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320714543.0U Expired - Fee Related CN203623971U (en) | 2013-11-10 | 2013-11-10 | Single-power multi-shaft aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203623971U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104627375A (en) * | 2013-11-10 | 2015-05-20 | 华中农业大学 | Single-power multi-shaft aircraft |
| CN106884970A (en) * | 2017-04-28 | 2017-06-23 | 湖南省库塔科技有限公司 | A kind of gearbox body and unmanned plane |
| CN108275279A (en) * | 2018-04-10 | 2018-07-13 | 辽宁壮龙无人机科技有限公司 | Unmanned plane transmission component and unmanned plane |
-
2013
- 2013-11-10 CN CN201320714543.0U patent/CN203623971U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104627375A (en) * | 2013-11-10 | 2015-05-20 | 华中农业大学 | Single-power multi-shaft aircraft |
| CN106884970A (en) * | 2017-04-28 | 2017-06-23 | 湖南省库塔科技有限公司 | A kind of gearbox body and unmanned plane |
| CN108275279A (en) * | 2018-04-10 | 2018-07-13 | 辽宁壮龙无人机科技有限公司 | Unmanned plane transmission component and unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140604 Termination date: 20161110 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |