CN111470037A - Helicopter without tail rotor - Google Patents
Helicopter without tail rotor Download PDFInfo
- Publication number
- CN111470037A CN111470037A CN202010338279.XA CN202010338279A CN111470037A CN 111470037 A CN111470037 A CN 111470037A CN 202010338279 A CN202010338279 A CN 202010338279A CN 111470037 A CN111470037 A CN 111470037A
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- CN
- China
- Prior art keywords
- blades
- helicopter
- double
- shaft
- adjustable
- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
Abstract
The invention discloses a helicopter without tail rotor, the helicopter body comprises: the double-shaft double-speed output transmission is positioned in the center of the airframe; the engine is connected with a double-shaft double-speed output transmission; the upper shaft of the double-shaft double-speed output transmission is connected with a main rotor, and the lower shaft of the double-shaft double-speed output transmission is connected with a fan propeller; adjustable yaw blades are radially distributed in a duct wind ring of the fan propeller; 80% of the counter-torque force generated by the rotation of the main rotor wing is offset by the connected fan propeller rotating reversely at high speed on the same speed changer, and the other 20% of the counter-torque force is offset by the force generated when the downward air flow generated by the high-speed rotation of the fan propeller flows through the ducted air ring framework; the ducted wind ring is internally distributed with angle-adjustable blades, and the angle between the movable yaw blades and the plane of the ducted wind ring is adjusted to realize the yaw turning of the helicopter; and the plane of the main rotor is parallel to the plane of the fan propeller, so that the loss of the helicopter is reduced.
Description
Technical Field
The invention relates to the technical field of aviation aircrafts and mechanical designs, in particular to a helicopter without a tail rotor.
Background
The helicopter is widely applied to the fields of environmental survey, scientific research experiments, pesticide spraying, mountain forest fire fighting and the like, and brings great convenience to people, but due to the structural principle of the helicopter, a huge rotor wing can generate counter-torque force when rotating, in order to offset the counter-torque force to keep a stable machine body, the traditional helicopter must be provided with a tail beam and a tail rotor, the yawing of the helicopter is realized by adjusting the pitch of the tail rotor rotating at high speed, and because the tail rotor is far away from the power of an engine and has high rotating speed, the helicopter with the tail rotor vibrates, the structure is large, the maintenance and repair are difficult, the consumed power is poor in economy, the tail rotor rotating at high speed causes damage to ground personnel and articles, the failure rate of the tail rotor is high, the failure rate of the tail rotor generally accounts for 30% of the failure of the whole airplane, and the consumed.
People have appeared two kinds of tailless helicopters for 80 years in order to overcome the defects of the traditional helicopters, one kind is the double-propeller coaxial helicopter invented by former Soviet union Carmoff, because two rotors with equal size, equal rotating speed and same rotating speed and opposite rotating directions are adopted, the counter torque force is mutually counteracted, the tail propeller is cancelled, the coaxial helicopter yaw is realized by the differential change of the pitch of the upper rotor and the lower rotor, the operation is difficult because the pitch is very small when the airplane flies downwards from high altitude at a large angle, a larger vertical tail wing is needed to help realize the yaw, a tail beam is not really cancelled, the height of the helicopter is greatly increased in order to avoid the collision of the two rotors, and the total pitch and the variable pitch structure of the double rotors are complicated and. The second helicopter without tail rotor is Md520 helicopter without tail rotor from McTan company, which moves the tail rotor forward to the front end of tail beam to jet out the airflow generated by propeller through the opening on tail tube, and uses coanda effect to offset the counter torque generated by rotor.
Disclosure of Invention
In order to solve the technical problem, the invention provides a helicopter without a tail rotor.
The invention is realized by the following technical scheme:
this scheme provides a no tail-rotor helicopter, and the helicopter mainly includes: a double-shaft double-speed output speed changer positioned in the center of the machine body, a fan propeller, a yawing blade adjusting mechanism, a traditional main rotor system, an engine and the like,
the engine is connected with a double-shaft double-speed output transmission; the upper shaft of the double-shaft double-speed output transmission is connected with a main rotor, the lower shaft of the double-speed output transmission is connected with at least one fan propeller, and yaw blades with adjustable angles are radially distributed in a duct wind ring of the fan propeller.
The working principle of the scheme is as follows: the helicopter has no tail rotor and tail beam and consists of double-shaft double-speed output speed reducer, fan propeller, duct ring, fuselage, cabin, etc. The lower shaft of the double-shaft double-speed output speed reducer is connected with a fan propeller and is positioned at the lower part of the helicopter body (two fan propellers can be longitudinally arranged along the helicopter body according to design requirements and are both parallel to the main rotor wing), the fan propeller is parallel to the upper rotor wing, the rotating speed of the upper shaft is lower than that of the lower shaft, and adjustable yawing blades are radially distributed in a duct wind ring of the fan propeller; during flight, the counter-torque force generated by the rotation of the main rotor can be offset by 80% by the lower fan propeller which rotates reversely at high speed, and when the downward-flowing air generated by the high-speed rotation of the fan propeller flows through the framework of the duct wind ring, namely the fixed blades, the counter-torque force opposite to the main rotor can be generated, and the counter-torque force is enough to offset the remaining 20% of the counter-torque force generated by the rotation of the main rotor; besides fixed blades, the wind ring of the duct is also distributed with yaw blades with adjustable angles, the tangent plane of the yaw blades is similar to that of the main rotor, the high-speed downward-flowing airflow generated by the fan propeller flows through the yaw blades to generate lift force similar to that of the main rotor, and the yaw blades are radially distributed in the duct, so that the lift force is yaw moment, and the yaw moment direction can be adjusted by synchronously adjusting the angles of the yaw blades (just like adjusting the total pitch of the main rotor), so that the yaw turning of the helicopter is realized.
It is further preferred that the plane of the main rotor is parallel to the plane of the fan propeller.
The traditional single-rotor helicopter is provided with a tail rotor and a tail beam to balance the counter-torque force generated by the rotation of a main rotor, and the plane of the tail rotor arranged on the tail beam is vertical to the plane of the main rotor, so that the tail rotor only can play a role of balancing the counter-torque force and cannot provide lift force for the helicopter at the same time; the plane of the main rotor is parallel to the plane of the fan propeller, so that the loss of the helicopter can be reduced.
It is further preferred that the upper and lower shafts of the two-shaft, two-speed output transmission are counter-rotating.
Further preferably, the lower shaft speed of the double-shaft two-speed output transmission is 3 times of the upper shaft speed.
The upper shaft of the double-shaft double-speed output transmission is connected with a main rotor, and the counter-torque force generated by the rotation of the main rotor can be offset by more than 80% by the counter-phase high-speed rotation of a fan propeller connected with the lower shaft.
Further preferably, the number of the angle-adjustable blades in the adjustable yaw blades is at least 2 times of the number of the fixed blades, and the specific number can be determined according to the size of the main rotor and the length of the yaw blades
Further preferably, the fixed blades in the yawing blades are radially and symmetrically distributed along the duct wind ring
Further preferred scheme is, the fixed blade is connected with the circular face of duct wind by an angle, and the inclination angle of the angle-adjustable blade to the clockwise direction or the anticlockwise direction is at least 10 degrees.
Further preferred scheme is, adjustable driftage blade still includes adjusting rope and adjusting roller, and adjustable driftage blade still includes adjusting device, and adjusting device controls adjustable driftage blade and deflects to clockwise or anticlockwise.
Further preferably, the yaw blade section and the main rotor section are similar in shape.
Offset the rotatory contained angle that produces of main rotor as required and set up fixed blade and duct wind circle disc, make fixed blade evenly distributed in the duct wind circle, fixed blade and duct wind circle fixed connection have constituted the skeleton of driftage blade, angle deflection for adjustable angle blade provides solid basis, at the adjusting blade angle in-process, duct wind circle and fixed blade can be as the strong point, the both ends of adjustable blade are being supported to the inner ring outer loop of duct wind circle, through dragging the regulation rope, just can drive the adjustable angle blade among the driftage blade and carry out clockwise or anticlockwise deflection, adjust the rope simultaneously and still connect on the fixed blade at the interval in the middle of the adjustable angle blade, can not appear dragging when dragging the regulation rope and lead to the excessive phenomenon of deflection of adjustable angle blade.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. the helicopter without the tail rotor provided by the invention completely cancels the tail rotor and the tail beam, has no power consumption and resistance of the tail rotor, has low failure rate and high reliability, and greatly improves the efficiency and the economy; and a transmission shaft and a tail rotor which rotate at a high speed and transmit long-distance power are not arranged, so that the vibration reduction effect of the machine body is obvious.
2. According to the helicopter without the tail rotor, in the flying process, the counter torque force generated by the rotation of the main rotor wing is offset by 80% of the fan propeller which is connected and rotates in a high speed on the same speed changer, and the remaining 20% of the counter torque force is offset by the counter torque force opposite to the main rotor wing generated when the downward air flow generated by the high-speed rotation of the fan propeller flows through the framework of the ducted air ring, namely the fixed blades; the wind ring of the duct is distributed with yaw blades with adjustable angles, the angles of the movable yaw blades are adjusted, and when the downward air leakage flows through the yaw blades, enough yaw moment can be generated, so that the yaw turning of the helicopter is realized; and the plane of the main rotor is parallel to the plane of the fan propeller, so that the loss of the helicopter is obviously reduced.
3. The helicopter without the tail rotor provided by the invention has the advantages of simple structure, convenience in maintenance and small volume; because the fan propeller and the main rotor are in parallel planes, the fan propeller generates a yaw force and a lift force, and therefore the main rotor can be shorter under the condition of the same takeoff weight.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
FIG. 1 is a schematic view of the structure of the present invention.
Fig. 2 is a front view of the helicopter model of the present invention.
Fig. 3 is a side view of a helicopter model of the present invention.
Fig. 4 is a structural schematic view of the ducted air ring.
FIG. 5 is a cross-sectional view of a yaw blade.
Reference numbers and corresponding part names in the drawings:
1-fan propeller, 2-main rotor, 3-engine, 4-double-shaft double-speed output transmission, 5-adjustable yaw blade, 6-transmission upper shaft, 7-transmission lower shaft, 8-fan propeller duct, 9-cabin shell, 10-undercarriage, 11-fan propeller duct wind ring, 12-fixed blade, 13-adjustable angle blade, 14-adjusting rope, 15-adjusting roller, 16-air, 17-main rotor rotation direction and 18-fan propeller rotation direction.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1
As shown in fig. 1, a helicopter without tail rotor, the fuselage comprising: the aircraft comprises a fan propeller 1, a main rotor 2, an engine 3 and a double-shaft double-speed output transmission 4 positioned in the center of an aircraft body;
the engine 3 is connected with a double-shaft double-speed output transmission 4; an upper shaft of the double-shaft double-speed output speed changer 4 is connected with a main rotor 2, a lower shaft of the double-shaft double-speed output speed changer 4 is connected with a fan propeller 1, and adjustable yawing blades 5 are radially distributed in a duct wind ring of the fan propeller.
The plane of the main rotor 2 is parallel to the plane of the fan propeller 1.
The upper shaft steering and the lower shaft steering of the double-shaft two-speed output transmission 4 are opposite.
The lower shaft speed of the dual shaft two speed output transmission 4 is 3 times the upper shaft speed.
The adjustable yaw blades 5 comprise fixed blades 12 and adjustable angle blades 13, and the number of the adjustable angle blades 13 is at least 2 times of the number of the fixed blades 12.
The fixed blades 12 are uniformly distributed along the radial direction of the ducted wind ring, and at least 2 adjustable-angle blades 13 are arranged between every two fixed blades 12.
The fixed blades 12 are connected with the circular surface of the ducted wind at an angle, and the inclination angle of the angle-adjustable blades 13 towards the clockwise direction or the anticlockwise direction is at least 10 degrees.
The adjustable yaw blades 5 further comprise adjusting ropes 14 and adjusting rollers 15, the adjusting rollers are installed at the same positions of each fixed blade, and the adjusting ropes pass through each angle-adjustable blade in a surrounding manner and are wound on the adjusting rollers of the fixed blades.
The cross sections of the fixed blades 12 and the angle-adjustable blades 13 are varied in unequal diameters, and the widest diameter is located on the side close to the fan propeller 1.
Example 2
As shown in fig. 2 and fig. 3, this embodiment is a helicopter model made of a helicopter without tail rotor according to the present invention, the model is made by connecting an engine 3 to a dual-shaft two-speed output transmission 4, an upper shaft of the dual-shaft two-speed output transmission 4 is connected to a main rotor, a lower shaft of the dual-shaft two-speed output transmission 4 is connected to a fan propeller 1, adjustable yaw blades 5 are radially distributed in a ducted wind ring of the fan propeller, and the dual-speed output transmission 4 is disposed in the center of a fuselage in a cabin shell.
The main rotor 3 is a traditional helicopter pitch and collective system, and the main rotor 3 and the fan propeller 1 rotate in opposite directions; the structure that the adjustable yawing blades 5 are radially distributed in the ducted wind ring of the fan propeller is shown in fig. 4, 6 fixed blades 12 are arranged in the ducted wind ring of the fan propeller of the helicopter model, and the 6 fixed blades are vertical to the circular surface of the ducted wind ring to form a framework of the adjustable yawing blades; the 2 adjustable angle blades 13 are arranged between the fixed blades 12, each adjustable angle blade 13 is connected through an adjusting rope 14 (here, a steel wire rope), meanwhile, the adjusting rope 14 is wound on an adjusting roller 15 on the fixed blades 12, and the adjusting ropes 14 are connected together after being wound on all the yawing blades. In the running process of the helicopter, the movable yaw blades 13 can be synchronously adjusted by controlling the pulling of the steel wire ropes of the yaw blades, so that the movable yaw blades 13 change the angle with the circular surface of the ducted wind ring, and when downward-flowing airflow generated by the high-speed rotation of the fan propeller 1 flows between the angle-adjustable blades 13 of the ducted wind ring, enough yaw moment is generated, and the yaw turning of the helicopter is realized.
The sectional view of the angle-adjustable blades 13 is shown in fig. 5, the radius of the section of each angle-adjustable blade is unevenly distributed, the steel wire rope penetrates through the holes of the angle-adjustable blades 13, and the steel wire rope drives the angle-adjustable blades to change the angle so as to realize yaw turning.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (9)
1. A tailless helicopter having a fuselage comprising: the aircraft comprises a fan propeller (1), a main rotor (2), an engine (3) and a double-shaft double-speed output transmission (4) positioned in the center of an aircraft body;
the engine (3) is connected with a double-shaft double-speed output transmission (4); the upper shaft of the double-shaft double-speed output transmission (4) is connected with the main rotor (2), the bottom shaft of the double-shaft double-speed output transmission (4) is connected with at least one fan propeller (1), and adjustable yawing blades (5) are radially distributed in a duct wind ring of the fan propeller (1).
2. A helicopter without tail rotor according to claim 1, characterized in that the plane of the main rotor (2) is parallel to the plane of the fan propeller (1).
3. A helicopter without tail rotor according to claim 1, characterized in that the upper shaft of the two-shaft two-speed output transmission (4) is turned opposite to the lower shaft.
4. A helicopter without tail rotor according to claim 1, characterized in that the lower shaft speed of the two-shaft two-speed output transmission (4) is 3 times the upper shaft speed.
5. A helicopter according to claim 1, characterized in that said adjustable yaw blades (5) comprise fixed blades (12) and adjustable angle blades (13), the number of adjustable angle blades (13) being at least 2 times the number of fixed blades (12).
6. A helicopter without tail rotor according to claim 5, characterized in that the fixed blades (12) are evenly distributed along the radial direction of the ducted wind ring, and at least 2 blades (13) with adjustable angle are arranged between every two fixed blades (12).
7. A helicopter according to claim 6, characterised in that the fixed blades (12) are angularly connected to the circular plane of the ducted wind, and that the angle of inclination of the adjustable angle blades (13) to the clockwise or anticlockwise direction is at least 10 degrees.
8. A helicopter according to claim 6, characterized in that the adjustable yaw blades (5) further comprise adjustment means controlling the deflection of the adjustable yaw blades (5) in a clockwise or counter-clockwise direction.
9. A helicopter without tail rotor according to claim 6, characterized in that the section of the fixed blades (12) and of the adjustable angle blades (13) varies in unequal diameter, the widest diameter being located on the side close to the fan propeller (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010338279.XA CN111470037A (en) | 2020-04-26 | 2020-04-26 | Helicopter without tail rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010338279.XA CN111470037A (en) | 2020-04-26 | 2020-04-26 | Helicopter without tail rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111470037A true CN111470037A (en) | 2020-07-31 |
Family
ID=71756093
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010338279.XA Pending CN111470037A (en) | 2020-04-26 | 2020-04-26 | Helicopter without tail rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111470037A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113942653A (en) * | 2021-11-19 | 2022-01-18 | 中国直升机设计研究所 | Method for controlling variable rotor rotation speed of double-engine high-speed helicopter |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2112585U (en) * | 1991-02-13 | 1992-08-12 | 韩明 | Helicopter without tail surface |
| CN1065433A (en) * | 1991-12-30 | 1992-10-21 | 王福生 | Long-range and high-speed rotor helicopter |
| GB2360752A (en) * | 2000-04-01 | 2001-10-03 | Glyn Jones | Helicopter without tail rotor |
| CN1439575A (en) * | 2003-04-09 | 2003-09-03 | 王雪松 | Culvert style elevating fan of hlicopter without tail propeller |
| US20110272519A1 (en) * | 2005-10-27 | 2011-11-10 | Douglas Challis | Aircraft with Helicopter Rotor, Thrust Generator and Assymetric Wing Configuration |
| CN109911185A (en) * | 2019-04-17 | 2019-06-21 | 成都航空职业技术学院 | A kind of high speed single rotor helicopter without tail surface |
-
2020
- 2020-04-26 CN CN202010338279.XA patent/CN111470037A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2112585U (en) * | 1991-02-13 | 1992-08-12 | 韩明 | Helicopter without tail surface |
| CN1065433A (en) * | 1991-12-30 | 1992-10-21 | 王福生 | Long-range and high-speed rotor helicopter |
| GB2360752A (en) * | 2000-04-01 | 2001-10-03 | Glyn Jones | Helicopter without tail rotor |
| CN1439575A (en) * | 2003-04-09 | 2003-09-03 | 王雪松 | Culvert style elevating fan of hlicopter without tail propeller |
| US20110272519A1 (en) * | 2005-10-27 | 2011-11-10 | Douglas Challis | Aircraft with Helicopter Rotor, Thrust Generator and Assymetric Wing Configuration |
| CN109911185A (en) * | 2019-04-17 | 2019-06-21 | 成都航空职业技术学院 | A kind of high speed single rotor helicopter without tail surface |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113942653A (en) * | 2021-11-19 | 2022-01-18 | 中国直升机设计研究所 | Method for controlling variable rotor rotation speed of double-engine high-speed helicopter |
| CN113942653B (en) * | 2021-11-19 | 2023-04-25 | 中国直升机设计研究所 | Variable rotor rotation speed control method for double-engine high-speed helicopter |
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