CN212501016U - Coaxial helicopter rotor system - Google Patents
Coaxial helicopter rotor system Download PDFInfo
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- CN212501016U CN212501016U CN202021369839.XU CN202021369839U CN212501016U CN 212501016 U CN212501016 U CN 212501016U CN 202021369839 U CN202021369839 U CN 202021369839U CN 212501016 U CN212501016 U CN 212501016U
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Abstract
The utility model belongs to the technical field of coaxial helicopter, concretely relates to coaxial helicopter rotor system. This coaxial helicopter rotor system includes: the rotary wing type aircraft comprises an outer shaft, a pair of lower rotary wings rotating along with the outer shaft, a fisheye bearing arranged on the outer shaft, a tilting disk matched with the fisheye bearing, and a first driving mechanism for driving the tilting disk to rotate; the tilting disk is linked with the pair of lower rotary wings through two groups of lower rotary wing pull rod assemblies respectively; the first driving mechanism drives the tilting tray to swing along the fisheye bearing, and each lower rotor pull rod assembly drives the corresponding lower rotor to change the pitch periodically so as to adjust the overall steering of the coaxial helicopter. The utility model discloses a coaxial helicopter rotor system, first actuating mechanism drive swash plate along the fisheye bearing swing, each lower rotor pull rod subassembly drives corresponding lower rotor periodic variation distance respectively to the holistic regulation that turns to of coaxial helicopter only just can realize whole the regulation that turns to through one set of swash plate, and the structure is more succinct.
Description
Technical Field
The utility model belongs to the technical field of coaxial helicopter, concretely relates to coaxial helicopter rotor system.
Background
Coaxial helicopters, also known as coaxial contra-rotor helicopters, share a single drive shaft with the double rotors, but rotate in opposite directions, not only to balance out the unidirectional rotational yawing moment, but also to provide "pre-compression" to the second layer by the first layer, and to provide a greater "volume of intake/exhaust" and "airflow density" to the second layer.
The existing coaxial helicopter controls the integral steering of the coaxial helicopter through two sets of tilting disks, and has the disadvantages of complex structure, high manufacturing cost and inconvenient maintenance.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a coaxial helicopter rotor system only can realize the regulation that wholly turns to through one set of swash plate, and the structure is more succinct.
In order to solve the technical problem, the utility model provides a coaxial helicopter rotor system, include:
the rotary wing type aircraft comprises an outer shaft, a pair of lower rotary wings rotating along with the outer shaft, a fisheye bearing arranged on the outer shaft, a tilting disk matched with the fisheye bearing, and a first driving mechanism for driving the tilting disk to rotate; the tilting disk is linked with the pair of lower rotary wings through two groups of lower rotary wing pull rod assemblies respectively; the first driving mechanism drives the tilting tray to swing along the fisheye bearing, and each lower rotor pull rod assembly drives the corresponding lower rotor to change the pitch periodically so as to adjust the overall steering of the coaxial helicopter.
Further, the coaxial helicopter rotor system further comprises: the upper rotor wing comprises an inner shaft matched with the outer shaft, a pair of upper rotor wings rotating along with the inner shaft, and a mandril penetrating through the inner shaft; one end of the ejector rod is fixedly connected with a guide block; two sides of the guide block are linked with the upper rotary wings through upper rotary wing pull rod assemblies respectively; the other end of the ejector rod is provided with a second driving mechanism; the second driving mechanism is suitable for driving the ejector rods to move up and down, so that the guide blocks pull the upper rotary wing pull rod assemblies to drive the corresponding upper rotary wings to change the pitch respectively.
Further, the first drive mechanism includes: the three lower rotor wing servo steering engines are arranged on the end face of the upper cover plate of the gear box, the three extension rods are annularly arranged on the tilting disk base, and the first swing rods are respectively arranged on the lower rotor wing servo steering engines; the tilting disk base is rotatably connected with the tilting disk; each lower rotor wing is hinged with each extension rod through a lower rotor wing connecting rod by a first swing rod on the servo steering engine; each lower rotor is suitable for the corresponding first pendulum rod swing of drive with servo steering engine, and each lower rotor connecting rod drives corresponding extension rod swing to make the tilting disk along the fisheye bearing swing.
Further, a first limiting column is arranged on the tilting disk base; a vertical plate is arranged on the end face of the upper cover plate of the gear box; a first sliding groove for moving the first limiting column is formed in the vertical plate.
Further, the lower rotor tie assembly includes: the lower rotor pull rod is respectively hinged with the tilting disk and the lower rotor; when the tilting disk swings along the fisheye bearing, the tilting disk drives the lower rotor pull rod to pull the lower rotor to change the pitch along with the tilting disk periodically.
Further, the second driving mechanism includes: the servo steering engine for the upper rotor wing, the fixed seat fixed at the bottom of the lower cover plate of the gear box, the second swing rod arranged on the servo steering engine for the upper rotor wing and the telescopic rod hinged with the second swing rod are arranged on the upper rotor wing; two sides of the fixed seat, two sides of the ejector rod and two sides of the telescopic rod are sequentially hinged with a transverse connecting piece; and the servo steering engine for the upper rotor wing is suitable for driving the second swing rod to rotate so that the telescopic rod drives the transverse connecting piece to pull the ejector rod to move up and down.
Further, the upper tie rod assembly includes: the upper rotary wing pull rod is respectively hinged with the guide block and the upper rotary wing; when the guide block moves up and down along with the ejector rod, the guide block pulls the upper rotary wing pull rod to drive the corresponding upper rotary wing to change the pitch.
Further, a hollow upright post sleeved on the outer wall of the inner shaft is arranged on a bearing seat of the inner shaft; two sides of the guide block are provided with second limiting columns in an extending mode; and each second limiting column is provided with a second sliding groove for moving.
The beneficial effects of the utility model are that, the utility model discloses a coaxial helicopter rotor system, a actuating mechanism drive tilt disc along the fisheye bearing swing, each lower rotor pull rod subassembly drives corresponding lower rotor periodic variation distance respectively to the holistic turning to of coaxial helicopter of adjustment just can realize the whole regulation that turns to of coaxial helicopter through one set of tilt disc, and the structure is more succinct, and the effectual cost of having practiced thrift.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Figure 1 is a schematic view of a coaxial helicopter rotor system of the present invention;
figure 2 is a partial view of the coaxial helicopter rotor system of the present invention;
figure 3 is a schematic view of a coaxial helicopter rotor system embodying the limiting relationship of the present invention;
figure 4 is a partial rear view of the coaxial helicopter rotor system of the present invention.
In the figure:
the device comprises an outer shaft 1, a lower rotary wing 2, a fisheye bearing 3, an inclined disc 4, a first driving mechanism 5, a servo steering engine 501 for the lower rotary wing, an extension rod 502, a first swing rod 503, a lower rotary wing connecting rod 504, a lower rotary wing pull rod assembly 6, a lower rotary wing pull rod 601, an inner shaft 7, an upper rotary wing 8, a top rod 9, a guide block 10, a second limiting column 1001, an upper rotary wing pull rod assembly 11, an upper rotary wing pull rod 1101, a second driving mechanism 12, a servo steering engine 1201 for the upper rotary wing, a fixed seat 1202, a second swing rod 1203, a telescopic rod 1204, a transverse connecting piece 1205, an inclined disc base 13, a first limiting column 1301, a vertical plate 14, a first chute 1401, a bearing seat 15, a hollow upright column 16 and a second chute 1601.
Detailed Description
To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Example 1
As shown in fig. 1 and 2, the present embodiment provides a coaxial helicopter rotor system comprising: the rotary wing type aircraft comprises an outer shaft 1, a pair of lower rotary wings 2 rotating along with the outer shaft 1, fisheye bearings 3 arranged on the outer shaft 1, a tilting disk 4 matched with the fisheye bearings 3, and a first driving mechanism 5 driving the tilting disk 4 to rotate; the tilting disk 4 is linked with the pair of lower rotors 2 through two groups of lower rotor pull rod assemblies 6 respectively; the first driving mechanism 5 drives the tilting disk 4 to swing along the fisheye bearing 3, and each lower rotor pull rod assembly 6 drives the corresponding lower rotor 2 to change the distance periodically so as to adjust the overall steering of the coaxial helicopter. The adjustment of the integral steering of the coaxial helicopter can be realized only by one set of tilting disk, and the structure is simpler.
In this embodiment, the coaxial helicopter rotor system further comprises: an inner shaft 7 matched with the outer shaft 1, a pair of upper rotors 8 rotating along with the inner shaft 7, and a mandril 9 penetrating through the inner shaft 7; one end of the ejector rod 9 is fixedly connected with a guide block 10; two sides of the guide block 10 are linked with the upper rotary wings 8 through upper rotary wing pull rod assemblies 11 respectively; the other end of the ejector rod 9 is provided with a second driving mechanism 12; the second driving mechanism 12 is adapted to drive the carrier rod 9 to move up and down, so that the guide blocks 10 pull the upper rotor pull rod assemblies 11 to drive the corresponding upper rotors 8 to change the pitch. The second driving mechanism 12 drives the jacking rods 9 to move up and down, so that the guide blocks 10 pull each upper rotor pull rod assembly 11 to drive the corresponding upper rotor 8 to change the attack angle respectively, and the lifting force of the coaxial helicopter is provided.
Optionally, the first driving mechanism 5 includes: the three lower rotor wing servo steering engines 501 are arranged on the end face of the upper cover plate of the gear box, the three extension rods 502 are annularly arranged on the tilting disk base 13, and the first swing rods 503 are respectively arranged on the lower rotor wing servo steering engines 501; the tilting disk base 13 is rotationally connected with the tilting disk 4; the first swing rod 503 on each lower rotor servo steering engine 501 is hinged with each extension rod 502 through a lower rotor connecting rod 504; each lower rotor servo steering engine 501 is adapted to drive the corresponding first swing link 503 to swing, and each lower rotor connecting rod 504 drives the corresponding extending rod 502 to swing, so that the tilting disk 4 swings along the fisheye bearing 3. The servo steering engines 501 for the lower rotors drive the corresponding first swing rods 503 to swing, then the lower rotor connecting rods 504 drive the corresponding extension rods 502 to swing, so that the tilting disk base 13 swings, the tilting disk 4 can swing along the fisheye bearing 3, and the first driving mechanisms 5 are uniformly distributed on the circumference, so that the integral structure of the coaxial helicopter is more compact and attractive.
As shown in fig. 3, a first limiting column 1301 is arranged on the tilting tray base 13; a vertical plate 14 is arranged on the end face of the upper cover plate of the gear box; the vertical plate 14 is provided with a first sliding slot 1401 for moving the first limit column 1301. The first chute 1401 is arranged to limit the tilting disk base 13 so that the tilting disk base cannot rotate and can only swing, thereby ensuring that the tilting disk 4 can swing along the fisheye bearing 3.
Optionally, the lower rotor tie rod assembly 6 includes: a lower rotor pull rod 601 hinged with the tilting disk 4 and the lower rotor 2 respectively; when the tilting disk 4 swings along the fisheye bearing 3, the tilting disk 4 drives the lower rotor pull rod 601 to pull the lower rotor 2 to change the pitch along with the tilting disk 4 periodically. When the tilting disk 4 swings along the fisheye bearing 3, the lower rotor pull rod 601 pulls the corresponding lower rotor 2 to change the pitch along with the tilting disk 4, the structure is simple, and the transmission effect is good.
As shown in fig. 4, the second drive mechanism 12 includes: the servo steering engine 1201 for the upper rotor wing, a fixed seat 1202 fixed at the bottom of a lower cover plate of the gear box, a second swing rod 1203 arranged on the servo steering engine 1201 for the upper rotor wing, and a telescopic rod 1204 hinged with the second swing rod 1203; two sides of the fixed seat 1202, two sides of the ejector rod 9 and two sides of the telescopic rod 1204 are sequentially hinged with a transverse connecting piece 1205; the servo steering engine 1201 for the upper rotor wing is suitable for driving the second swing rod 1203 to rotate, so that the telescopic rod 1204 drives the transverse connecting piece 1205 to pull the ejector rod 9 to move up and down. Be suitable for the drive second pendulum rod 1203 to rotate through last rotor with servo steering engine 1201 to make telescopic link 1204 drive transverse connection 1205 and pull ejector pin 9 and reciprocate, and then guaranteed the mobility of ejector pin 9.
Optionally, the upper tie rod assembly 11 includes: an upper wing pull rod 1101 respectively hinged with the guide block 10 and the upper wing 8; when the guide block 10 moves up and down along with the mandril 9, the guide block 10 pulls the upper rotary wing pull rod 1101 to drive the corresponding upper rotary wing 8 to change the pitch. The upper rotor pull rod 1101 is pulled by the guide block 10 to drive the corresponding upper rotor 8 to swing, so that the attack angles of the two upper rotors 8 are changed to provide the lift force of the coaxial helicopter.
In this embodiment, a hollow upright column 16 sleeved on the outer wall of the inner shaft 7 is arranged on the bearing seat 15 of the inner shaft 7; two sides of the guide block 10 are provided with second limiting columns 1001 in an extending manner; the hollow upright column 16 is provided with second sliding grooves 1601 for moving the second limiting posts 1001. Through set up second spout 1601 on hollow column 16 to reciprocate ejector pin 9 and carry out spacingly, restrict last rotor 8 displacement promptly, thereby make last rotor 8 only provide lift, can not adjust and turn to.
To sum up, in the coaxial helicopter rotor system of the present invention, the first driving mechanism 5 drives the tilting disk 4 to swing along the fisheye bearing 3, and each lower rotor pull rod assembly 6 drives the corresponding lower rotor 2 to periodically change the pitch, so as to adjust the overall steering of the coaxial helicopter, and the overall steering of the coaxial helicopter can be adjusted only by one set of tilting disk, so that the structure is more concise, and the cost is effectively saved; the second driving mechanism 12 drives the jacking rods 9 to move up and down, so that the guide blocks 10 pull each upper rotor pull rod assembly 11 to drive the corresponding upper rotor 8 to change the attack angle respectively, and the lifting force of the coaxial helicopter is provided.
The components selected for use in the present application (components not illustrated for specific structures) are all common standard components or components known to those skilled in the art, and the structure and principle thereof can be known to those skilled in the art through technical manuals or through routine experimentation.
In the description of the embodiments of the present invention, unless explicitly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In light of the foregoing, it will be apparent to those skilled in the art from this disclosure that various changes and modifications can be made without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.
Claims (8)
1. A coaxial helicopter rotor system, comprising:
the rotary wing type aircraft comprises an outer shaft, a pair of lower rotary wings rotating along with the outer shaft, a fisheye bearing arranged on the outer shaft, a tilting disk matched with the fisheye bearing, and a first driving mechanism for driving the tilting disk to rotate;
the tilting disk is linked with the pair of lower rotary wings through two groups of lower rotary wing pull rod assemblies respectively;
the first driving mechanism drives the tilting tray to swing along the fisheye bearing, and each lower rotor pull rod assembly drives the corresponding lower rotor to change the pitch periodically so as to adjust the overall steering of the coaxial helicopter.
2. The coaxial helicopter rotor system of claim 1,
the coaxial helicopter rotor system further comprises: the upper rotor wing comprises an inner shaft matched with the outer shaft, a pair of upper rotor wings rotating along with the inner shaft, and a mandril penetrating through the inner shaft;
one end of the ejector rod is fixedly connected with a guide block;
two sides of the guide block are linked with the upper rotary wings through upper rotary wing pull rod assemblies respectively;
the other end of the ejector rod is provided with a second driving mechanism;
the second driving mechanism is suitable for driving the ejector rods to move up and down, so that the guide blocks pull the upper rotary wing pull rod assemblies to drive the corresponding upper rotary wings to change the pitch respectively.
3. The coaxial helicopter rotor system of claim 1,
the first drive mechanism includes: the three lower rotor wing servo steering engines are arranged on the end face of the upper cover plate of the gear box, the three extension rods are annularly arranged on the tilting disk base, and the first swing rods are respectively arranged on the lower rotor wing servo steering engines;
the tilting disk base is rotatably connected with the tilting disk;
each lower rotor wing is hinged with each extension rod through a lower rotor wing connecting rod by a first swing rod on the servo steering engine;
each lower rotor is suitable for the corresponding first pendulum rod swing of drive with servo steering engine, and each lower rotor connecting rod drives corresponding extension rod swing to make the tilting disk along the fisheye bearing swing.
4. The coaxial helicopter rotor system of claim 3,
a first limiting column is arranged on the tilting disk base;
a vertical plate is arranged on the end face of the upper cover plate of the gear box;
a first sliding groove for moving the first limiting column is formed in the vertical plate.
5. The coaxial helicopter rotor system of claim 4,
the lower rotor tie rod assembly includes: the lower rotor pull rod is respectively hinged with the tilting disk and the lower rotor;
when the tilting disk swings along the fisheye bearing, the tilting disk drives the lower rotor pull rod to pull the lower rotor to change the pitch along with the tilting disk periodically.
6. The coaxial helicopter rotor system of claim 2,
the second drive mechanism includes: the servo steering engine for the upper rotor wing, the fixed seat fixed at the bottom of the lower cover plate of the gear box, the second swing rod arranged on the servo steering engine for the upper rotor wing and the telescopic rod hinged with the second swing rod are arranged on the upper rotor wing;
two sides of the fixed seat, two sides of the ejector rod and two sides of the telescopic rod are sequentially hinged with a transverse connecting piece;
and the servo steering engine for the upper rotor wing is suitable for driving the second swing rod to rotate so that the telescopic rod drives the transverse connecting piece to pull the ejector rod to move up and down.
7. The coaxial helicopter rotor system of claim 6,
the upper rotor tie rod assembly includes: the upper rotary wing pull rod is respectively hinged with the guide block and the upper rotary wing;
when the guide block moves up and down along with the ejector rod, the guide block pulls the upper rotary wing pull rod to drive the corresponding upper rotary wing to change the pitch.
8. The coaxial helicopter rotor system of claim 7,
a hollow upright post sleeved on the outer wall of the inner shaft is arranged on a bearing seat of the inner shaft;
two sides of the guide block are provided with second limiting columns in an extending mode;
and each second limiting column is provided with a second sliding groove for moving.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021369839.XU CN212501016U (en) | 2020-07-13 | 2020-07-13 | Coaxial helicopter rotor system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021369839.XU CN212501016U (en) | 2020-07-13 | 2020-07-13 | Coaxial helicopter rotor system |
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| Publication Number | Publication Date |
|---|---|
| CN212501016U true CN212501016U (en) | 2021-02-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021369839.XU Active CN212501016U (en) | 2020-07-13 | 2020-07-13 | Coaxial helicopter rotor system |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815851A (en) * | 2021-10-28 | 2021-12-21 | 湖南韬讯航空科技有限公司 | Rotor wing direction-changing propelling device, helicopter and control method |
-
2020
- 2020-07-13 CN CN202021369839.XU patent/CN212501016U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815851A (en) * | 2021-10-28 | 2021-12-21 | 湖南韬讯航空科技有限公司 | Rotor wing direction-changing propelling device, helicopter and control method |
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