CN112591114A - Cross double-rotor unmanned helicopter and power system thereof - Google Patents
Cross double-rotor unmanned helicopter and power system thereof Download PDFInfo
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- CN112591114A CN112591114A CN202110234224.9A CN202110234224A CN112591114A CN 112591114 A CN112591114 A CN 112591114A CN 202110234224 A CN202110234224 A CN 202110234224A CN 112591114 A CN112591114 A CN 112591114A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 132
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- 238000012423 maintenance Methods 0.000 abstract description 5
- 230000000694 effects Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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Abstract
The invention discloses a crossed double-rotor unmanned helicopter and a power system thereof, wherein the power system comprises a power source, two rotor shafts and a transmission mechanism, only one power source is arranged, and the power source is in transmission connection with the transmission mechanism; the transmission mechanism is provided with two power output ends, a first power output end is used for transmitting power from the power source to two rotor shafts, a second power output end is used for transmitting power from the power source to the tail rotor shafts, and the first power output end, the second power output end and the tail rotor shafts are located on the same axis. The power system is simple and reliable in structure, compact in arrangement, capable of saving space and reducing maintenance cost.
Description
Technical Field
The invention relates to the technical field of helicopters, in particular to a crossed double-rotor unmanned helicopter and a power system thereof.
Background
The existing unmanned helicopter mainly comprises a single rotor and coaxial dual rotors, and the number of the crossed dual-rotor unmanned helicopters is relatively small.
The power system of the existing cross twin-rotor unmanned helicopter is complex in structure, large in occupied space in arrangement, not compact enough, and correspondingly, high in maintenance cost.
Disclosure of Invention
The invention aims to provide a crossed double-rotor unmanned helicopter and a power system thereof.
In order to solve the technical problem, the invention provides a power system of a crossed double-rotor unmanned helicopter, which comprises a power source, two rotor shafts and a transmission mechanism, wherein only one power source is arranged, and the power source is in transmission connection with the transmission mechanism; the transmission mechanism is provided with two power output ends, a first power output end is used for transmitting power from the power source to two rotor shafts, a second power output end is used for transmitting power from the power source to the tail rotor shafts, and the first power output end, the second power output end and the tail rotor shafts are located on the same axis.
The power system of the cross double-rotor unmanned helicopter is only provided with one power source, the power of the power source is transmitted to the transmission mechanism, the transmission mechanism is provided with two power output ends, and the power is transmitted to the two rotor shafts and the tail rotor shaft respectively, wherein the two power output ends and the tail rotor shaft are positioned on the same axis, so that one power source synchronously drives the two rotor shafts and can also provide power for the tail rotor shaft, the structure of the transmission mechanism can be simplified, the number of parts is reduced, and the maintenance cost is reduced; meanwhile, two power output ends and a tail rotor shaft of the transmission mechanism are arranged on one axis, so that the whole power system is compact in layout, small in occupied space and high in transmission efficiency, and the performance of the helicopter is favorably improved.
The power system of the cross twin-rotor unmanned helicopter further comprises a tail transmission shaft group, wherein the input end of the tail transmission shaft group is in transmission connection with the second power output end through a flexible coupling, and the output end of the tail transmission shaft group is in transmission connection with the tail rotor shaft; and the axis of the tail drive shaft group is coincident with the axis of the tail propeller shaft.
According to the power system of the cross twin-rotor unmanned helicopter, the tail transmission shaft group comprises more than two tail transmission shafts in transmission connection, and at least one transmission connection part of each transmission connection part of the tail transmission shaft group and the tail propeller shaft is in transmission connection through a spline.
According to the power system of the cross twin-rotor unmanned helicopter, the power source is positioned above the tail transmission shaft group and at one end of the tail transmission shaft group far away from the tail rotor shaft.
According to the power system of the cross twin-rotor unmanned helicopter, the axis of the output shaft of the power source and the axis of the tail transmission shaft group are in the same vertical plane.
The power system of the crossed dual-rotor unmanned helicopter is characterized in that the rotor shaft is supported by the support frame, the support frame comprises a support seat and at least two support rods, the rotor shaft penetrates through the support seat and can be opposite to the support seat in a rotating mode, one end of each support rod is fixedly connected with the support seat, and each support rod surrounds the rotor shaft and is arranged, and the support rods are opposite to the rotor shaft in an inclined mode.
According to the power system of the cross twin-rotor unmanned helicopter, the supporting seats of the two supporting frames are fixedly connected through the connecting rod; and/or the extension lines of one ends of the support rods fixedly connected with the support seats are intersected at one point, and the intersection point is positioned on the axis of the rotor shaft.
The power system of the cross twin-rotor unmanned helicopter comprises a first transmission shaft, a first main bevel gear, a second transmission shaft, a first slave bevel gear, two second main bevel gears and two second slave bevel gears; the first main bevel gear is fixedly sleeved at one end of the first transmission shaft, the first slave bevel gear is fixedly sleeved at the middle part of the second transmission shaft, the two second main bevel gears are respectively fixedly sleeved at two ends of the second transmission shaft, and the two second slave bevel gears are respectively fixedly sleeved at the bottom ends of the two rotor shafts;
the power source is in transmission connection with the first transmission shaft, the first main bevel gear is meshed with the first slave bevel gear, and the two second main bevel gears are respectively meshed with the two second slave bevel gears;
the first transmission shaft and the second transmission shaft are vertically arranged, and the axis of the first transmission shaft is superposed with the axis of the tail rotor shaft; the first main bevel gear is the first power output end, and the other end of the first transmission shaft is the second power output end.
According to the power system of the cross twin-rotor unmanned helicopter, the power source is connected with the transmission mechanism through the one-way clutch.
The invention also provides a cross double-rotor unmanned helicopter which comprises a helicopter body and a power system arranged on the helicopter body, wherein the power system is any one of the power systems, and the transmission mechanism is connected with the helicopter body through an elastic support.
Because the power system has the technical effects, the crossed double-rotor unmanned helicopter comprising the power system also has the same technical effects, and the detailed description is omitted.
Drawings
Fig. 1 is a schematic structural diagram of a power system of a cross twin-rotor unmanned helicopter according to an embodiment of the present invention;
FIG. 2 is a schematic structural view of the transmission and rotor shaft system of FIG. 1;
FIG. 3 is an enlarged partial view of the junction of two tail drive shafts of a tail drive shaft set in an exemplary embodiment.
Description of reference numerals:
a power source 10;
the transmission mechanism 20, a first transmission shaft 21, a first main bevel gear 22, a second transmission shaft 23, a first slave bevel gear 24, a second main bevel gear 25, a second slave bevel gear 26, a driving gear 27 and a driven gear 28;
a rotor shaft 30;
a support frame 40, a support seat 41, a support rod 42 and a connecting rod 43;
a tail transmission shaft set 50, a tail transmission shaft 51, a flexible coupling 52 and a spline 53;
Detailed Description
In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
For simplicity of understanding and description, the following description is provided in conjunction with a cross twin-rotor unmanned helicopter and its power system, and the beneficial effects will not be repeated.
Referring to fig. 1, fig. 1 is a schematic structural diagram of a power system of a cross twin-rotor unmanned helicopter according to an embodiment of the present invention.
The cross dual-rotor unmanned helicopter comprises a helicopter body and a power system arranged on the helicopter body, wherein in the embodiment, the power system comprises a power source 10, two rotor shafts 30 and a transmission mechanism 20, wherein only one power source 10 is arranged, and the power source 10 is in transmission connection with the transmission mechanism 20; the transmission mechanism 20 has two power outputs, a first power output for transmitting power from the power source 10 to the two rotor shafts 30, a second power output for transmitting power from the power source 10 to the tail rotor shaft 61 of the tail rotor 60, the first power output, the second power output and the tail rotor shaft 61 being on the same axis.
The crossed dual-rotor unmanned helicopter is provided with two rotor shafts 30, the two rotor shafts 30 are arranged on two sides of the helicopter body in a crossed mode, it can be understood that extension lines of the two rotor shafts 30 can intersect at a virtual point, and two rotors on the two rotor shafts 30 rotate in opposite directions synchronously.
The power transmitted from the first power output end of the transmission mechanism 20 can be transmitted to the two rotor shafts 30 through the transmission structure, so that the two rotor shafts 30 synchronously rotate in opposite directions.
After the arrangement, the power system is only provided with one power source 10, the two rotor shafts 30 are synchronously driven by the power source 10, and power can be provided for the tail rotor shaft 61, so that the structure of the transmission mechanism 20 can be simplified, the number of parts can be reduced, and the maintenance cost can be reduced; meanwhile, two power output ends of the transmission mechanism 20 and the tail rotor shaft 61 are arranged on the same axis, so that the whole power system is more compact in layout, small in occupied space and high in transmission efficiency, and the performance of the helicopter is favorably improved.
The power source 10 is usually an engine, but may be other components capable of increasing power in practice.
Referring also to fig. 2, fig. 2 is a schematic structural view of the transmission and rotor shaft system of fig. 1.
In this embodiment, the transmission mechanism 20 includes a first transmission shaft 21, a first master bevel gear 22, a second transmission shaft 23, a first slave bevel gear 24, two second master bevel gears 25, and two second slave bevel gears 26; the first main bevel gear 22 is fixedly sleeved at one end of the first transmission shaft 21, the first auxiliary bevel gear 24 is fixedly sleeved at the middle part of the second transmission shaft 23, the two second main bevel gears 25 are respectively fixedly sleeved at two ends of the second transmission shaft 23, and the two second auxiliary bevel gears 26 are respectively fixedly sleeved at the bottom ends of the two rotor shafts 30.
The first transmission shaft 21 is in transmission connection with the power source 10, the first main bevel gear 22 is meshed with the first driven bevel gear 24, and the two second main bevel gears 25 are respectively meshed with the two second driven bevel gears 26.
When the axis of the first main bevel gear 22 is perpendicular to the axis of the first slave bevel gear 24, that is, the first main bevel gear 22 and the first slave bevel gear 24 are orthogonally engaged with each other, the direction of the power from the power source 10 can be changed; it can be understood that, because the two rotor shafts 30 are arranged in a crossed manner, the engagement between the second slave bevel gear 26 fixedly sleeved on the rotor shafts 30 and the corresponding second master bevel gear 25 is a mutual oblique engagement, and the specific angle setting can be determined according to actual requirements.
In actual operation, the power of the power source 10 is transmitted to the first transmission shaft 21, the first main bevel gear 22 transmits the power to the first secondary bevel gear 24 and the second transmission shaft 23, and the second main bevel gears 25 at two ends of the second transmission shaft 23 respectively transmit the power to the two second secondary bevel gears 26, so that the power is transmitted to the two rotor shafts 30, and the purpose that one power source 10 synchronously drives the two rotors is achieved.
In a specific embodiment, the power system further includes a tail transmission shaft set 50, where the tail transmission shaft set 50 is configured to transmit power from the power source 10 to the tail rotor shaft 61, specifically, an input end of the tail transmission shaft set 50 is in transmission connection with a second power output end of the transmission mechanism 20, that is, the other end of the first transmission shaft 21, through a flexible coupling 52, and an output end of the tail transmission shaft set 50 is in transmission connection with the tail rotor shaft 61, as shown in fig. 1, an axis of the tail transmission shaft set 50 coincides with an axis of the tail rotor shaft 61, it can be understood that the tail transmission shaft set 50 and the tail rotor shaft 61 are coaxially and concentrically arranged, and thus, after the arrangement, the tail rotor 60 is a thrust tail rotor, which can improve performance of the helicopter.
The tail transmission shaft set 50 is connected with the first transmission shaft 21 through a flexible coupling 52, and angle compensation can be performed on the tail transmission shaft set 50.
When the tail transmission shaft group 50 is specifically arranged, the tail transmission shaft group comprises more than two tail transmission shafts 51, all the tail transmission shafts 51 are in transmission connection in sequence, and obviously, the axis of each tail transmission shaft 51 is coincident with the axis of the tail rotor shaft 61. Specifically, at least one of the transmission joints (the transmission joints of two adjacent tail transmission shafts 51) of the tail transmission shaft group 50 or the transmission joints of the tail transmission shaft group 50 and the tail rotor shaft 61 is in transmission connection through a spline 53, and the spline 53 is arranged to compensate the length of the tail transmission shaft group 50. As shown in fig. 3, there is shown a structure in which two tail drive shafts 51 are connected by a spline 53.
In the concrete scheme, the power source 10 is located above the tail transmission shaft group 50 and is arranged close to the position of the rotor shaft 30, namely, located at one end of the tail transmission shaft group 50 far away from the tail propeller shaft 61, more specifically, the axis of the output shaft of the power source 10 and the axis of the tail transmission shaft group 50 are located in the same vertical plane, so that the gravity distribution is relatively reasonable and uniform, and the performance of the helicopter is favorably improved.
As mentioned above, the axis of the first transmission shaft 21 coincides with the axis of the tail rotor shaft 61, that is, coincides with the axis of the tail transmission shaft group 50, the output shaft of the power source 10 is located above the tail transmission shaft group 50, and the axes of the two are located on the same vertical plane, that is, the output shaft of the power source 10 is parallel to the first transmission shaft 21, and the output shaft of the power source 10 is also located above the first transmission shaft 21.
In a specific scheme, the power source 10 is connected with the transmission mechanism 20 through a one-way clutch, so that power can be transmitted from the power source 10 to the transmission mechanism 20 in a one-way mode, power consumption is avoided, and operation is simpler.
In this embodiment, the rotor shaft 30 of the power system is supported by the support frame 40, corresponding to each rotor shaft 30, the support frame 40 is provided with a support seat 41 and at least two support rods 42, wherein the rotor shaft 30 passes through the corresponding support seat 41 and can rotate relative to the support seat 41, specifically, a bearing can be arranged between the rotor shaft 30 and the support seat 41, one end of each support rod 42 is fixedly connected with the support seat 41, each support rod 42 is arranged around the rotor shaft 30, and the support rods 42 are obliquely arranged relative to the rotor shaft 30, as shown in fig. 1 and fig. 2, one end of each support rod 42 fixedly connected with the support seat 41 is close to the rotor shaft 30, the other end of each support rod 42 is relatively far away from the rotor shaft 30, and when the support rods 42 are installed, the support rods 42 can be.
After the arrangement, the rotor shaft 30 is supported by the support frame 40, the lower end of the support frame 40 is connected with the fuselage, the vibration isolation effect is achieved on the rotor shaft 30, the alternating force and the alternating torque transmitted to the rotor rotation plane of the fuselage on the hub of the rotor mounted on the rotor shaft 30 can be effectively reduced, the structure is simple and reliable, and the maintenance cost is low.
In the scheme shown in the figure, each supporting seat 41 is correspondingly provided with two supporting rods 42, and it can be understood that the number and arrangement of the supporting rods 42 can be adjusted according to actual requirements during actual setting.
Specifically, the two support seats 41 of the two support frames 40 are further fixedly connected by the connecting rod 43, and the intersection point of the extension lines of the support rods 42 connected to each support seat 41 can be located on the axis of the rotor shaft 30, so as to further improve the support effect. It is understood that the intersection point of the extension lines of the support rods 42 is obviously the intersection point of the extension lines of the ends of the support rods 42 fixedly connected with the support base 41.
In a specific scheme, the transmission mechanism 20 of the power system is connected with the fuselage through an elastic support, and the rotor shaft 30 is connected with the fuselage through the support frame 40, so that the vertical frequency of the transmission mechanism 20 and the rotor system is high, and the swinging frequency of the intersection point of the extension lines of the support rods 42 around the support frame 40 is low, so that the vertical rigidity of the transmission mechanism 20 and the rotor system is ensured, and the transmission rate of exciting force or moment in the rotation plane of the rotor can be reduced.
The cross double-rotor unmanned helicopter and the power system thereof provided by the invention are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the method and its core concepts. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (10)
1. The power system of the cross double-rotor unmanned helicopter comprises a power source, two rotor shafts and a transmission mechanism, and is characterized in that only one power source is arranged, and the power source is in transmission connection with the transmission mechanism; the transmission mechanism is provided with two power output ends, a first power output end is used for transmitting power from the power source to two rotor shafts, a second power output end is used for transmitting power from the power source to the tail rotor shafts, and the first power output end, the second power output end and the tail rotor shafts are located on the same axis.
2. The power system of a cross twin rotor unmanned helicopter of claim 1 further comprising a tail driveshaft assembly, the input end of said tail driveshaft assembly being drivingly connected to said second power output end via a flexible coupling, the output end of said tail driveshaft assembly being drivingly connected to said tail rotor shaft; and the axis of the tail drive shaft group is coincident with the axis of the tail propeller shaft.
3. The power system of a cross twin rotor unmanned helicopter of claim 2 wherein the tail drive shaft set includes more than two tail drive shafts in drive connection, at least one of the drive connections of the tail drive shaft set and the tail rotor shaft being in splined drive connection.
4. The power system of a cross twin rotor unmanned helicopter of claim 2 wherein the power source is located above the set of tail drive shafts and at an end of the set of tail drive shafts distal from the tail rotor shaft.
5. The power system of a cross twin rotor unmanned helicopter of claim 4 where the output shaft axis of the power source is in the same vertical plane as the axis of the tail drive shaft set.
6. The power system of a cross twin rotor unmanned helicopter of any of claims 1 to 5 wherein the rotor shaft is supported by a support frame, the support frame comprising a support base and at least two support rods, the rotor shaft passing through the support base and being capable of rotating relative to the support base, one end of the support rods being fixedly connected to the support base, each support rod being disposed around the rotor shaft and the support rods being disposed in an inclined manner relative to the rotor shaft.
7. The power system of the unmanned helicopter of claim 6 wherein the supports of the two supports are fixedly connected by a connecting rod; and/or the extension lines of one ends of the support rods fixedly connected with the support seats are intersected at one point, and the intersection point is positioned on the axis of the rotor shaft.
8. The power system of a cross twin rotor unmanned helicopter of any one of claims 1 to 5 wherein the transmission includes a first drive shaft, a first master bevel gear, a second drive shaft, a first slave bevel gear, two second master bevel gears, and two second slave bevel gears; the first main bevel gear is fixedly sleeved at one end of the first transmission shaft, the first slave bevel gear is fixedly sleeved at the middle part of the second transmission shaft, the two second main bevel gears are respectively fixedly sleeved at two ends of the second transmission shaft, and the two second slave bevel gears are respectively fixedly sleeved at the bottom ends of the two rotor shafts;
the power source is in transmission connection with the first transmission shaft, the first main bevel gear is meshed with the first slave bevel gear, and the two second main bevel gears are respectively meshed with the two second slave bevel gears;
the first transmission shaft and the second transmission shaft are vertically arranged, and the axis of the first transmission shaft is superposed with the axis of the tail rotor shaft; the first main bevel gear is the first power output end, and the other end of the first transmission shaft is the second power output end.
9. The power system of a cross twin rotor unmanned helicopter of any of claims 1 to 5 wherein the power source is connected to the transmission by a one-way clutch.
10. The cross dual-rotor unmanned helicopter comprises a fuselage and a power system installed on the fuselage, and is characterized in that the power system is the power system of any one of claims 1 to 9, and the transmission mechanism is connected with the fuselage through an elastic support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110234224.9A CN112591114B (en) | 2021-03-03 | 2021-03-03 | Cross double-rotor unmanned helicopter and power system thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110234224.9A CN112591114B (en) | 2021-03-03 | 2021-03-03 | Cross double-rotor unmanned helicopter and power system thereof |
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| Publication Number | Publication Date |
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| CN112591114A true CN112591114A (en) | 2021-04-02 |
| CN112591114B CN112591114B (en) | 2021-07-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN106342057B (en) * | 2004-10-26 | 2007-06-20 | 南京航空航天大学 | A kind of depopulated helicopter |
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| CN209617467U (en) * | 2019-01-28 | 2019-11-12 | 乾美航空科技邢台有限公司 | A kind of unmanned helicopter of detachable tail pipe |
| CN111207923A (en) * | 2020-04-22 | 2020-05-29 | 北京清航紫荆装备科技有限公司 | Test bed for transmission device of cross dual-rotor unmanned helicopter |
| CN111204466A (en) * | 2020-04-22 | 2020-05-29 | 北京清航紫荆装备科技有限公司 | Cross double-rotor unmanned helicopter and gear transmission system thereof |
| CN211711095U (en) * | 2019-12-03 | 2020-10-20 | 中国人民解放军总参谋部第六十研究所 | Helicopter tail transmission shaft device |
| EP3733509A1 (en) * | 2019-04-30 | 2020-11-04 | Bell Textron Inc. | Rotorcraft anti-torque systems and methods therefor |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106342057C (en) * | 2004-10-26 | 2007-06-20 | 南京航空航天大学 | unmanned helicopter |
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2021
- 2021-03-03 CN CN202110234224.9A patent/CN112591114B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106342057B (en) * | 2004-10-26 | 2007-06-20 | 南京航空航天大学 | A kind of depopulated helicopter |
| CN101511676A (en) * | 2005-05-31 | 2009-08-19 | 西科尔斯基飞机公司 | Rotor drive and control system for a high speed rotary wing aircraft |
| CN203528823U (en) * | 2013-10-31 | 2014-04-09 | 无锡同春新能源科技有限公司 | Rice bacterial leaf blight preventing unmanned aerial vehicle with colored rice disease image identifier |
| CN209617467U (en) * | 2019-01-28 | 2019-11-12 | 乾美航空科技邢台有限公司 | A kind of unmanned helicopter of detachable tail pipe |
| EP3733509A1 (en) * | 2019-04-30 | 2020-11-04 | Bell Textron Inc. | Rotorcraft anti-torque systems and methods therefor |
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| CN111207923A (en) * | 2020-04-22 | 2020-05-29 | 北京清航紫荆装备科技有限公司 | Test bed for transmission device of cross dual-rotor unmanned helicopter |
| CN111204466A (en) * | 2020-04-22 | 2020-05-29 | 北京清航紫荆装备科技有限公司 | Cross double-rotor unmanned helicopter and gear transmission system thereof |
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