CN212172525U - Foldable unmanned aerial vehicle transmission system - Google Patents
Foldable unmanned aerial vehicle transmission system Download PDFInfo
- Publication number
- CN212172525U CN212172525U CN201922116457.XU CN201922116457U CN212172525U CN 212172525 U CN212172525 U CN 212172525U CN 201922116457 U CN201922116457 U CN 201922116457U CN 212172525 U CN212172525 U CN 212172525U
- Authority
- CN
- China
- Prior art keywords
- shaft
- aerial vehicle
- unmanned aerial
- clutch
- bearing
- 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
Images
Landscapes
- Arrangement Of Transmissions (AREA)
Abstract
The utility model relates to a folding unmanned aerial vehicle transmission system, include: the device comprises an engine, a clutch, a transmission mechanism, a main transmission shaft, a universal coupling, a driven shaft and a right-angle reversing gear box; the output shaft of the engine is connected with the clutch, and when the clutch is connected, power is transmitted to the main transmission shaft through the transmission mechanism; the two ends of the main transmission shaft are provided with universal couplings, the universal couplings are connected with the driven shaft, power is transmitted to the right-angle reversing gear box, and the output shaft of the right-angle reversing gear box is the rotor shaft.
Description
Technical Field
The utility model relates to a rotor unmanned aerial vehicle transmission system belongs to aviation aircraft design field, especially oil moves many rotor unmanned aerial vehicle, tandem bispin unmanned helicopter and verts rotor unmanned aerial vehicle's transmission system design.
Background
The rotor type unmanned aerial vehicle has no take-off site and runway requirements, can take off and land vertically, especially can hover freely, and flexible flexibility is good, does benefit to and accomplishes various tasks. At present, the rotor type unmanned aerial vehicle mainly has single rotor with tail rotor layout, coaxial dual rotor layout, and these two types of unmanned helicopter technical maturity, market share is very high. In recent years, along with the development of battery technology and control technology, the electric multi-rotor unmanned aerial vehicle is rapidly developed, the electric multi-rotor unmanned aerial vehicle is powered by a battery in a centralized manner, a transmission system is not needed, but the electric multi-rotor unmanned aerial vehicle is limited by the capacity of the battery, the load, the flight time and the flight range of the electric multi-rotor unmanned aerial vehicle are short, the flight time is generally not more than 30min, and the flight range is also dozens of kilometers. In order to improve flight time and range, a gasoline-electric hybrid multi-rotor unmanned aerial vehicle and a hydrogen-fuel multi-rotor unmanned aerial vehicle are developed in succession, and the upgrading of the two power systems can obviously increase the flight time and range, but the carrying capacity is very small.
With the demand for large payload, long endurance of multi-rotor drones in fields such as agricultural plant protection, aerial geophysical prospecting and military. In order to expand the application field of the multi-rotor unmanned aerial vehicle, the oil-driven multi-rotor unmanned aerial vehicle becomes a research and development hotspot. The current oil moves many rotor unmanned aerial vehicle and has the type such as single-shot-belt drive, and multiple direct drive, the former transmission system is too complicated, and the latter does not need transmission system, but needs four at least engines.
SUMMERY OF THE UTILITY MODEL
The utility model provides a technical problem be: overcome prior art's not enough, provide a folding rotor unmanned aerial vehicle's transmission system.
The utility model provides a technical scheme be: a foldable unmanned aerial vehicle transmission system, characterized in that includes: the device comprises an engine, a clutch, a transmission mechanism, a main transmission shaft, a universal coupling, a driven shaft and a right-angle reversing gear box; the output shaft of the engine is connected with the clutch, and when the clutch is connected, power is transmitted to the main transmission shaft through the transmission mechanism; the two ends of the main transmission shaft are provided with universal couplings, the universal couplings are connected with the driven shaft, power is transmitted to the right-angle reversing gear box, and the output shaft of the right-angle reversing gear box is the rotor shaft.
Preferably, the clutch install on the clutch shaft and spacing through the retaining ring of both ends installation, the outside installation bearing of retaining ring, one side bearing carries out axial spacing through the ladder that sets up on the clutch shaft, and the other side bearing is spacing through installing the circlip on the clutch shaft, the bearing all seals through the bearing cap, the clutch shaft passes through elastic coupling and is connected with the output shaft of engine.
Preferably, the tolerance of the position where the clutch bearing is installed is k6, and the tolerance of the position where the clutch is installed is j 6.
Preferably, the gap between the end of the clutch shaft and the inner side of the bearing cap is 2mm to 5 mm.
Preferably, the clutch is additionally provided with a small belt pulley, the transmission mechanism is a belt pulley, and the belt pulley is connected with an output shaft of the clutch and the main transmission shaft.
Preferably, the main transmission shaft and the universal coupling are connected through the following modes: main drive shaft one end sets up the internal spline, and universal joint's input sets up to the external spline, live the epaxial installation bearing of transmission, and it is spacing through the retaining ring between bearing and the universal joint, and the bearing is installed in main bearing seat one end, and main bearing seat fixes on the organism, and main bearing seat's the other end is as folding end, and universal joint's output sets up to the internal spline and is used for being connected with the driven shaft.
Preferably, the rotation axis of the folding end is coincident with the folding central line of the universal joint.
Preferably, the one end of driven shaft sets up to external splines and is used for being connected with universal joint's output, and the bearing is all installed at the both ends of driven shaft, and the bearing of external splines one end is installed in driven shaft bearing seat one end, driven shaft bearing seat be connected with main bearing seat's folding end, the driven shaft bearing seat other end is fixed with the outer connecting tube spare of suit at the driven shaft, driven shaft other end bearing is installed on right angle switching-over gear box connecting seat, driven shaft bearing seat and right angle switching-over gear box connecting seat be connected with connecting tube spare, pass through rigid coupling between the input shaft of driven shaft and right.
Preferably, the driven shaft is connected with the rigid coupling through a spline, and the rigid coupling is connected with the input shaft of the right-angle reversing gear box through a flat key.
Preferably, all install at the front and back both ends of unmanned aerial vehicle organism unmanned aerial vehicle transmission system, constitute a two oil drive four rotor unmanned aerial vehicle systems.
Compared with the prior art, the utility model beneficial effect be:
the utility model discloses a owner, constitute from transmission system, the centre is connected with universal joint, is convenient for fold. The transmission mechanism and the right-angle reversing gear box are adopted to transmit power, the efficiency is high, and two-stage speed reduction is realized. The utility model discloses a drive mechanism has the clutch, can switch on the rotor in the rotational speed scope of regulation, is of value to protection engine and rotor system.
The driven shaft in the transmission system of the utility model only transmits half of the power of the engine, thereby having light weight. The transmission system has simple structure and high reliability, and is a transmission system of the rotor aircraft with light weight, high strength, high efficiency and high reliability.
Based on the analysis, the utility model discloses a transmission system still has the characteristics that transmission route is direct, power loss is little, efficient, and can reduce empty quick-witted weight, improves transmission efficiency.
By integrating the characteristics, the transmission system is suitable for the tandem unmanned helicopter, and is particularly suitable for power transmission of the double-engine four-rotor unmanned helicopter.
Drawings
FIG. 1 illustrates an overall transmission profile according to an embodiment of the present invention;
fig. 2 shows a power take-off profile according to the invention, including a clutch;
FIG. 3 illustrates a main drive system according to the present invention;
FIG. 4 shows an external view of a driven shaft transmission system according to the present invention;
figure 5 gives according to the utility model discloses an example of using, a four rotor unmanned aerial vehicle are moved to oil.
Detailed Description
The present invention will be further explained with reference to the following examples.
In order to solve present many rotor unmanned aerial vehicle transmission system complicacy, transmission efficiency is low, the big difficult scheduling problem of transportation of size, the utility model discloses a basic aspect is exactly to provide a rotor unmanned aerial vehicle transmission system collapsible, simple structure, that transmission efficiency is high.
According to the utility model discloses further mainly be used for the unmanned helicopter of tandem formula, be particularly suitable for two oil engines to move four rotor unmanned aerial vehicle's transmission system for the power transmission of engine.
According to the utility model discloses an embodiment mainly is through making up rationally such as engine 1, clutch 2, drive mechanism 3, final drive shaft 4, universal joint 5, driven shaft 6 and right angle reversing gear case 7, has constituted one set of folding rotor unmanned aerial vehicle power transmission system (fig. 1). The transmission system mainly comprises three subsystems, namely a transmission mechanism assembly, a main transmission system and a driven shaft transmission system which are reasonably connected.
The transmission mechanism component comprises a clutch (with a small belt pulley), a synchronous toothed belt and a large belt pulley. The clutch is arranged on the engine, the clutch is attached with a small belt pulley, and when the engine rotates to reach a rated rotating speed, the clutch is connected; the large belt wheel is arranged on the main transmission shaft, and the large belt wheel and the small belt wheel are connected by a synchronous cog belt. The main transmission system comprises a main transmission shaft, a bearing and a main bearing seat. The main transmission shaft transfers power by a large belt wheel, bearings are arranged at two ends of the main transmission shaft, the bearings are arranged on a main bearing seat, and the main bearing seat is arranged on a machine frame. The driven shaft transmission system comprises a left set and a right set and comprises a driven shaft, a bearing, a driven bearing seat, a connecting pipe fitting and a right-angle reversing gear box connecting seat. Rolling bearings are installed on two sides of the driven shaft, one end of each bearing is installed on a driven bearing seat, the other end of each bearing is installed on a right-angle gear box connecting seat, and the two bearings are connected through a connecting pipe fitting. The driving shaft transmission system and the driven shaft transmission system are connected by a universal coupling and can be folded into 90 degrees during transportation, so that the transportation space is reduced. The right-angle gear box connecting seat is connected with the right-angle gear box through bolts, and the final process that the power is transmitted from the engine to the rotor wing is completed.
In fig. 2, a small pulley 1a1 is connected to a clutch 2, the clutch 2 is mounted on a clutch shaft 1a6 of a transmission mechanism and is limited by retaining rings 1a9 mounted at both ends, a bearing 1a8 is mounted outside the retaining ring 1a9, bearings 1a8 are mounted at both ends of the clutch shaft 1a6 in a mating manner, one bearing 1a8 is limited axially by a step provided on the clutch shaft, the other bearing 1a8 is limited by an elastic retaining ring 1a4 mounted on the clutch shaft, the bearings 1a8 are sealed by a bearing cover 1a10, the bearing cover 1a10 is fixed on a bearing seat 1a7 by a bolt 1a2, and the clutch 2 shaft is connected to an output shaft of an engine 1 by an elastic coupling 1a 5. The bearing 1a8 is mounted on the bearing seat 1a7, and the bearing seat 1a7 is mounted on the frame by the bearing seat fixing bolt 1a 3. Through the process, a complete power output system of the engine-clutch-transmission mechanism is formed.
The utility model provides a drive mechanism comes transmission power with the belt, and the clutch is centrifugal clutch, can replace the belt to transmit power with transmission shaft, gear box among the practical application, and other clutches such as clutch, drum clutch also the optional use replace.
In fig. 3, an external spline at an input end of a universal coupling 5 is connected with an internal spline of a driving shaft 4, bearings 1b5 are mounted at two ends of the driving shaft 4, the bearings 1b5 and the coupling are limited by retaining rings 1b4, a bearing 1b4 is mounted on a main bearing seat 1b3, a large belt pulley 1b7 is mounted on the driving shaft 4 and is limited axially by the retaining rings 1b6, two ends of the main bearing seat 1b3 are sealed by bearing covers 1b8, the bearing covers 1b8 and the main bearing seat 1b3 are fixed by bolts 1b1, the other end of the main bearing seat 1b3 is used as a folding end, an output end of the universal coupling 5 is arranged as an internal spline for connecting with a driven shaft 6, rotary bolts 1b2 are mounted above and below a main bearing seat 1b3 and connected with a driven shaft 1c5 to form a whole, center lines of the upper and lower rotary bolts 1b2 coincide, when the driven system is folded to 90 degrees around the rotary, convenient transportation and storage. Main bearing seat 1b3 installs in the unmanned aerial vehicle frame, the main drive system of unmanned aerial vehicle that constitutes.
In fig. 4, the internal spline of the output end of the universal joint 5 is connected with the external spline of the driven shaft 6, the positioning rotating bolt 1b2 is used for connecting the main bearing seat 1b3 and the driven bearing seat 1c5, and in the ground parking state, the positioning rotating bolt can rotate 90 degrees around the axis of the positioning rotating bolt 1b2, the two ends of the driven shaft 6 are both provided with bearings 1c4, the bearings 1c4 at the two ends are axially limited by a retainer ring 1c2 and a retainer ring 1c10, the bearing 1c4 at one end is arranged on the driven bearing seat 1c5, the end surface of the bearing seat 1c5 is provided with a bearing cover 1c3 for sealing and is fixed on the driven bearing seat 1c5 by a screw 1c1, the bearing 1c4 at the other end is arranged on the right-angle reversing gear box connecting seat 1c8, the driven bearing seat 1c5 and the right-angle reversing gear box connecting seat 1c8 are connected by a connecting pipe 1c 42 and are fixed by a screw 1c 39 6 and are fixed into a right-, the right-angle reversing gear box connecting seat 1c8 and the right-angle reversing gear box 7 are connected into a whole by bolts 1c12, the output shaft 1c13 of the right-angle reversing gear box 7 is a rotor shaft, so that a driven shaft transmission system is formed, and the left and right sets of the right and left sets of.
Examples
The following describes embodiments of the present invention more specifically by way of an example:
example, double-engine four-rotor unmanned plane
As shown in fig. 5, a novel oil-driven quad-rotor unmanned aerial vehicle mainly comprises a rotor system f1, a transmission system f2, a power system f3, an unmanned aerial vehicle frame f4 and a control system f 5. The power system f3 is connected with the transmission system f2 through a belt and used for providing flight power; the transmission system f2 is connected with the left rotor system f1 and the right rotor system f1 and is used for transmitting the power of an engine; the rotor system f1 is used as a lifting surface, a control surface and a tension surface of the aircraft and is used for providing force and moment required by the flight and the control of the aircraft; the control system f5 is an integration of a programmable controller, a navigation attitude sensor and a control signal receiving device. The rotor system f1, the transmission system f2, the power system f3 and the control system f5 are all reasonably arranged on the unmanned aerial vehicle frame f4, and the novel oil-driven four-rotor unmanned aerial vehicle shown in the figure 5 is formed.
It should be understood that the foregoing description and the description of the present invention are illustrative and not restrictive, and that various changes, modifications and/or alterations may be made to the embodiments described above without departing from the scope of the present invention as defined by the appended claims.
The above description is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and should not be construed as excluding other similar embodiments. The technical scheme and the conception of the utility model are equivalent to change or replace, and are all covered in the protection scope of the utility model.
Claims (10)
1. A foldable unmanned aerial vehicle transmission system, characterized in that includes: the device comprises an engine, a clutch, a transmission mechanism, a main transmission shaft, a universal coupling, a driven shaft and a right-angle reversing gear box; the output shaft of the engine is connected with the clutch, and when the clutch is connected, power is transmitted to the main transmission shaft through the transmission mechanism; the two ends of the main transmission shaft are provided with universal couplings, the universal couplings are connected with the driven shaft, power is transmitted to the right-angle reversing gear box, and the output shaft of the right-angle reversing gear box is the rotor shaft.
2. The unmanned aerial vehicle drive system of claim 1, wherein: the clutch install on the clutch shaft and spacing through the retaining ring of both ends installation, the outside installation bearing of retaining ring, one side bearing carries out axial spacing through the ladder that sets up on the clutch shaft, and it is spacing that the other side bearing is through installing the epaxial circlip of clutch, the bearing all seals through the bearing cap, the clutch shaft passes through elastic coupling and the output shaft of engine.
3. The unmanned aerial vehicle drive system of claim 2, wherein: the tolerance of the position where the clutch shaft is installed on the bearing is k6, and the tolerance of the position where the clutch is installed is j 6.
4. The unmanned aerial vehicle drive system of claim 2, wherein: the gap between the end part of the clutch shaft and the inner side of the bearing cover is 2-5 mm.
5. The unmanned aerial vehicle drive system of claim 1, wherein: the clutch is attached with a small belt pulley, the transmission mechanism is a belt pulley, and the belt pulley is connected with an output shaft of the clutch and the main transmission shaft.
6. The unmanned aerial vehicle drive system of claim 1, wherein: the main transmission shaft and the universal coupling are connected in the following way: main drive shaft one end sets up the internal spline, and universal joint's input sets up to the external spline, live the epaxial installation bearing of transmission, and it is spacing through the retaining ring between bearing and the universal joint, and the bearing is installed in main bearing seat one end, and main bearing seat fixes on the organism, and main bearing seat's the other end is as folding end, and universal joint's output sets up to the internal spline and is used for being connected with the driven shaft.
7. The unmanned aerial vehicle transmission system of claim 6, wherein: and the rotating axis of the folding end is superposed with the folding central line of the universal coupling.
8. The unmanned aerial vehicle transmission system of claim 6 or 7, wherein: the one end of driven shaft sets up to the external splines be used for being connected with universal joint's output, and the bearing is all installed at the both ends of driven shaft, and the bearing of external splines one end is installed in driven shaft bearing seat one end, driven shaft bearing seat be connected with main bearing seat's folding end, the driven shaft bearing seat other end is fixed with the outer connecting pipe fitting of suit at the driven shaft, driven shaft other end bearing is installed on the connecting pipe fitting, through rigid coupling connection between the input shaft of driven shaft and right angle reversing gear case.
9. The unmanned aerial vehicle drive system of claim 8, wherein: the driven shaft is connected with the rigid coupling through a spline, and the rigid coupling is connected with the input shaft of the right-angle reversing gear box through a flat key.
10. The unmanned aerial vehicle drive system of claim 1, wherein: all install at the front and back both ends of unmanned aerial vehicle organism unmanned aerial vehicle transmission system, constitute a four rotor unmanned aerial vehicle system are moved to two oil generators.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922116457.XU CN212172525U (en) | 2019-11-29 | 2019-11-29 | Foldable unmanned aerial vehicle transmission system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922116457.XU CN212172525U (en) | 2019-11-29 | 2019-11-29 | Foldable unmanned aerial vehicle transmission system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212172525U true CN212172525U (en) | 2020-12-18 |
Family
ID=73764390
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922116457.XU Active CN212172525U (en) | 2019-11-29 | 2019-11-29 | Foldable unmanned aerial vehicle transmission system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212172525U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920876A (en) * | 2019-11-29 | 2020-03-27 | 彩虹无人机科技有限公司 | Foldable unmanned aerial vehicle transmission system |
| CN113443132A (en) * | 2021-07-29 | 2021-09-28 | 上海交通大学 | Miniature longitudinal reverse dual-rotor aircraft |
-
2019
- 2019-11-29 CN CN201922116457.XU patent/CN212172525U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920876A (en) * | 2019-11-29 | 2020-03-27 | 彩虹无人机科技有限公司 | Foldable unmanned aerial vehicle transmission system |
| CN113443132A (en) * | 2021-07-29 | 2021-09-28 | 上海交通大学 | Miniature longitudinal reverse dual-rotor aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3299290B1 (en) | Rotating proprotor arrangement for a tiltrotor aircraft | |
| CN212172525U (en) | Foldable unmanned aerial vehicle transmission system | |
| CN102656086B (en) | System for motorizing a wheel connected to a suspension | |
| US11312194B2 (en) | Land and aerial transportation vehicle and powertrain thereof | |
| CN210881561U (en) | Air-ground dual-purpose unmanned aerial vehicle | |
| US8702550B1 (en) | Aircraft electric taxi system with friction actuated, bi-directional clutch | |
| KR101340409B1 (en) | Hybrid Unmanned Aerial Vehicle | |
| US20160009383A1 (en) | Drive unit for aircraft running gear | |
| EP0861778A1 (en) | A snubber assembly for an unmanned aerial vehicle | |
| WO2016114851A1 (en) | Single engine, asymmetrical vertical take-off and landing (vtol) aircraft | |
| US6065718A (en) | Universal VTOL power and rotor system module | |
| CN101746507A (en) | Hybrid power for ducted fan unmanned aerial systems | |
| CN110920876A (en) | Foldable unmanned aerial vehicle transmission system | |
| US9382001B2 (en) | Torque transfer system for a rotorcraft | |
| CN105555663A (en) | Drive system for aircraft landing gear | |
| US9956864B1 (en) | Motor integration assembly | |
| CN104943868A (en) | Transmission system device of light unmanned helicopter | |
| CN112238719A (en) | Driving device of aerocar | |
| CN206125448U (en) | Oil moves coaxial many rotor unmanned aerial vehicle | |
| CN102431646A (en) | Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft | |
| CN106240800A (en) | A kind of unmanned plane folding wing | |
| AU784766B2 (en) | Universal VTOL power and rotor system module | |
| CN208915454U (en) | A kind of mechanical synchronizer | |
| CN114475118A (en) | Post-disaster air-land dual-purpose rescue robot | |
| EP2910467B1 (en) | Aircraft wheel driving system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |