CN212473887U

CN212473887U - Tandem double-paddle staggered wing structure of helicopter

Info

Publication number: CN212473887U
Application number: CN202021279974.5U
Authority: CN
Inventors: 黄权
Original assignee: Individual
Current assignee: Anhui Horizontal and Vertical Line Technology Co.,Ltd.
Priority date: 2020-07-02
Filing date: 2020-07-02
Publication date: 2021-02-05
Anticipated expiration: 2030-07-02

Abstract

The utility model discloses a wrong wing structure of column double-oar of helicopter relates to helicopter equipment field, has the blank problem in market to the different axle double-oar helicopter field of current compact, now proposes following scheme, and it includes the helicopter, the helicopter includes oar transmission structure, just oar transmission structure includes engine and cross axle, preceding oar pedestal is installed to the front end of helicopter, just back oar pedestal is installed to the rear end of helicopter, install preceding oar axle in the preceding oar pedestal, just the top of preceding oar axle runs through in preceding oar pedestal, preceding oar wing is installed on the top of preceding oar axle, just install back oar axle in the back oar pedestal, the top of back oar axle runs through in back oar pedestal, just back oar wing is installed on the top of back oar axle. The utility model discloses novel structure, and the device simple structure lightly and easy to maintain can realize the self-balancing state of helicopter simultaneously for the helicopter is easily controlled.

Description

Tandem double-paddle staggered wing structure of helicopter

Technical Field

The utility model relates to a helicopter equipment field especially relates to a staggered wing structure of tandem double-oar of helicopter.

Background

The existing helicopter blades are single-layer blades, the size of the helicopter is small, the power is not high, a small part of transportation tasks are met, a part of helicopters provide coaxial double-propeller helicopters for more sufficient power, the helicopter is generally applied to large helicopters, besides, the helicopter is also provided with a non-coaxial double-propeller helicopter, two rotating shaft horizontal devices are arranged on two sides of a machine body, the axle distance is far away, the helicopter is generally applied to heavy transporters, the helicopter which meets the power requirement and is compact in structure does not exist in the current market, and therefore, in order to fill the blank in the field, a vertical double-propeller staggered wing structure of the helicopter is provided.

SUMMERY OF THE UTILITY MODEL

The utility model provides a pair of staggered wing structure of tandem double-oar of helicopter has solved the different axle double-oar helicopter field of compact and has had the blank problem in market.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the utility model provides a staggered wing structure of tandem double-oar of helicopter, includes the helicopter, the helicopter includes oar transmission structure, just oar transmission structure includes engine and cross axle, preceding oar shaft post is installed to the front end of helicopter, just back oar shaft post is installed to the rear end of helicopter, install preceding oar axle in the preceding oar shaft post, just the top of preceding oar axle runs through in preceding oar shaft post, preceding oar wing is installed on the top of preceding oar axle, just back oar shaft is installed in the back oar shaft post, the top of back oar shaft runs through in back oar shaft post, just back oar wing is installed on the top of back oar shaft.

Preferably, the top ends of the front paddle shaft and the rear paddle shaft are provided with paddle heads.

Preferably, the engine is located in a helicopter cabin, an output shaft of the engine is horizontal, the output shaft of the engine penetrates through the engine, two ends of the output shaft of the engine are fixedly sleeved with driving gears, and the driving gears are symmetrically distributed around the engine.

Preferably, a cross shaft is installed at the top end of the engine, the cross shaft and the engine are in a horizontal shape, the two ends of the cross shaft are fixedly sleeved with the transfer gears, a first driven gear is fixedly sleeved on the circumferential side wall of the cross shaft and located between the transfer gears, and the first driven gear and the transfer gears are symmetrically distributed around the cross shaft.

Preferably, the driving gear is meshed with the first driven gear, the bottom ends of the front propeller shaft and the rear propeller shaft are fixedly connected with second driven gears, and the second driven gears are respectively meshed with the transfer gear.

Preferably, the front paddle wings are symmetrically distributed about the front paddle shaft, the rear paddle wings are symmetrically distributed about the rear paddle shaft, and the front paddle wings and the rear paddle wings are horizontal to each other.

The utility model has the advantages that: 1. the device realizes mechanical transmission through the driving gear, the first driven gear, the switching gear and the second driven gear which are symmetrically distributed, so that the stress of the cross shaft is balanced, the stress concentration is avoided from being damaged, the structure can allow the engine to have larger power output, and the device is simple, light and easy to maintain. 2. The transfer gear and the second driven gear of the device are mutually vertical, when the transfer gear is coaxial, synchronous and co-rotating, the two groups of second driven gears rotate in different shafts, synchronously and reversely, so that reactive torque forces generated by the front paddle wing and the rear paddle wing rotate are balanced and offset mutually, self balance can be realized, and the hovering performance is excellent.

In conclusion, the device is simple and light in structure and easy to maintain, and can realize the self-balancing state of the helicopter, so that the helicopter is easy to control.

Drawings

Fig. 1 is a side view of the helicopter of the present invention.

Fig. 2 is a top view of the paddle drive structure of the present invention.

Fig. 3 is a side view of the paddle drive structure of the present invention.

Wherein: 1. a helicopter; 2. a front propeller shaft post; 3. a rear propeller shaft post; 4. a front propeller shaft; 5. a paddle head; 6. a fore-wing; 7. a rear propeller shaft; 8. a rear airfoil; 9. an engine; 10. a drive gear; 11. a horizontal axis; 12. a first driven gear; 13. a transfer gear; 14. a second driven gear.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.

Referring to fig. 1-3, a tandem double-blade staggered wing structure of a helicopter comprises a helicopter 1, wherein the helicopter 1 comprises a blade transmission structure, the blade transmission structure comprises an engine 9 and a transverse shaft 11, a front blade shaft 2 is installed at the front end of the helicopter 1, a rear blade shaft 3 is installed at the rear end of the helicopter 1, a front blade shaft 4 is installed in the front blade shaft 2, the top end of the front blade shaft 4 penetrates through the front blade shaft 2, a front blade 6 is installed at the top end of the front blade shaft 4, a rear blade shaft 7 is installed in the rear blade shaft 3, the top end of the rear blade shaft 7 penetrates through the rear blade shaft 3, a rear blade 8 is installed at the top end of the rear blade shaft 7, a blade head 5 is installed at the top ends of the front blade shaft 4 and the rear blade shaft 7, the engine 9 is located in a cabin of the helicopter 1, and an output shaft of the engine 9 is horizontal, the output shaft of the engine 9 penetrates through the engine 9, both ends of the output shaft of the engine 9 are fixedly sleeved with driving gears 10, the driving gears 10 are symmetrically distributed about the engine 9, the top end of the engine 9 is provided with a transverse shaft 11, the transverse shaft 11 and the engine 9 are in a horizontal shape, both ends of the transverse shaft 11 are fixedly sleeved with adapter gears 13, the circumferential side wall of the transverse shaft 11 is fixedly sleeved with a first driven gear 12, the first driven gear 12 is positioned between the adapter gears 13, the first driven gear 12 and the adapter gears 13 are symmetrically distributed about the transverse shaft 11, the driving gears 10 are meshed with the first driven gear 12, the bottom ends of the front paddle shaft 4 and the rear paddle shaft 7 are fixedly connected with second driven gears 14, the second driven gears 14 are respectively meshed with the adapter gears 13, and the front paddle wings 6 are symmetrically distributed about the front paddle shaft 4, the rear paddles 8 are symmetrically distributed around a rear paddle shaft 7, and the front paddles 6 and the rear paddles 8 are mutually horizontal.

The device belongs to a novel different-shaft double-paddle transmission device, the basic transmission principle is that an engine 9 with two output shafts at two ends drives two groups of driving gears 10 to synchronously rotate in the same direction, the two groups of driving gears 10 synchronously drive two groups of first driven gears 12 to synchronously rotate in the same direction, the rotation of the two groups of first driven gears 12 drives a cross shaft 11 to rotate, the driving gears 10 and the first driven gears 12 are symmetrically distributed around the cross shaft 11, so that the stress of the cross shaft 11 is balanced, and the stress concentration is prevented from being damaged, the structure can allow the engine 9 to have larger power output, the cross shaft 11 drives switching gears 13 at two ends of the engine, the switching gears 13 drive second driven gears 14, the two groups of second driven gears 14 are respectively connected with a front paddle shaft 4 and a rear paddle shaft 7, so that the front paddle shaft 4 drives a front paddle wing 6 and the rear paddle shaft 7 drives a rear paddle 8 to rotate, the transmission mechanism has simple and portable structure;

the transfer gear 13 and the second driven gear 14 of the device are perpendicular to each other, when the transfer gear 13 is coaxial, synchronous and co-rotating, the two groups of second driven gears 14 are enabled to rotate in different axes, synchronously and reversely, so that the reactive torque force generated by the rotating front paddle wing 6 and the rotating rear paddle wing 8 is balanced and offset mutually, and self balance can be realized (the balance can be kept without the tail rotor of a single-paddle helicopter, and the self-rotation phenomenon cannot occur).

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims

1. The utility model provides a staggered wing structure of tandem double-oar of helicopter, includes helicopter (1), its characterized in that, helicopter (1) includes the oar transmission structure, just the oar transmission structure includes engine (9) and cross axle (11), preceding oar stull (2) are installed to the front end of helicopter (1), just back oar stull (3) are installed to the rear end of helicopter (1), install preceding oar axle (4) in preceding oar stull (2), just the top of preceding oar axle (4) is run through in preceding oar stull (2), preceding oar wing (6) are installed to the top of preceding oar (4), just back oar stull (7) are installed in back oar stull (3), the top of back oar axle (7) is run through in back oar stull (3), just back oar wing (8) are installed to the top of back oar axle (7).

2. The tandem double-oar staggered wing structure of a helicopter according to claim 1, characterized in that the top ends of the front oar shaft (4) and the rear oar shaft (7) are both provided with oar heads (5).

3. The structure of double-wing staggered wing in tandem of helicopter according to claim 1, characterized in that said engine (9) is located in the cabin of helicopter (1), and the output shaft of said engine (9) is horizontal, the output shaft of said engine (9) is through the engine (9), and both ends of the output shaft of said engine (9) are fixedly sleeved with driving gears (10), and said driving gears (10) are symmetrically distributed with respect to the engine (9).

4. The staggered wing structure of two vertical paddles of a helicopter of claim 1, characterized in that a cross shaft (11) is installed at the top end of the engine (9), the cross shaft (11) and the engine (9) are horizontal, adapter gears (13) are fixedly sleeved at both ends of the cross shaft (11), first driven gears (12) are fixedly sleeved on the circumferential side wall of the cross shaft (11), the first driven gears (12) are located between the adapter gears (13), and the first driven gears (12) and the adapter gears (13) are symmetrically distributed about the cross shaft (11).

5. The tandem double-oar staggered wing structure of the helicopter according to claim 3, characterized in that the driving gear (10) is meshed with a first driven gear (12), and the bottom ends of the front oar shaft (4) and the rear oar shaft (7) are fixedly connected with a second driven gear (14), and the second driven gears (14) are respectively meshed with the transfer gear (13).

6. The structure of double staggered blades in tandem for a helicopter according to claim 1, characterized in that said forward blades (6) are symmetrically distributed about the forward blade axis (4) and said aft blades (8) are symmetrically distributed about the aft blade axis (7), said forward blades (6) and said aft blades (8) being horizontal to each other.