阅读说明：本技术 一种飞行器用组合传动机构 (Combined transmission mechanism for aircraft ) 是由 陈永红 任宏喜 张康军 王竟 于 2021-10-21 设计创作，主要内容包括：本发明公开一种飞行器用组合传动装置,涉及伺服系统传动技术领域,解决现有分体式或组合式传动装置,行程小、工艺性差,装配难度大,可靠性差的技术问题。包括交错设置的驱动丝杠与舵轴和止转板；驱动丝杠包括丝杠螺杆和丝杠螺母；丝杠螺母安装在丝杠螺杆上,丝杠螺母上设置的固定柱与舵轴朝向丝杠螺杆的一侧的导向槽,组合连接,丝杠螺母远离舵轴的一侧设置有定位柱,止转板沿丝杠螺杆的长度方向设置,其中部设置有定位槽,定位柱位于定位槽内,外界驱动装置驱动丝杠螺杆转动,丝杠螺母沿丝杠螺杆长度方向运动,丝杠螺母上的固定柱带动舵轴摆动。上述飞行器用组合传动装置结构简单,组装方便,行程大,传输稳定,可靠性高,具有很高的实用性。(The invention discloses a combined transmission device for an aircraft, relates to the technical field of servo system transmission, and solves the technical problems of small stroke, poor manufacturability, high assembly difficulty and poor reliability of the conventional split type or combined type transmission device. Comprises a driving screw rod, a rudder shaft and a rotation stopping plate which are arranged in a staggered manner; the driving screw comprises a screw rod and a screw nut; the screw nut is installed on the screw rod, the fixed column and the steering shaft which are arranged on the screw nut face the guide groove on one side of the screw rod, the screw nut is connected in a combined mode, one side, away from the steering shaft, of the screw nut is provided with a positioning column, the rotation stopping plate is arranged along the length direction of the screw rod, the positioning column is located in the positioning groove, the external driving device drives the screw rod to rotate, the screw nut moves along the length direction of the screw rod, and the fixed column on the screw nut drives the steering shaft to swing. The combined transmission device for the aircraft is simple in structure, convenient to assemble, large in stroke, stable in transmission, high in reliability and high in practicability.)

1. A compound transmission for an aircraft, comprising: the steering mechanism comprises a rudder shaft, a driving screw rod and a rotation stopping plate, wherein the driving screw rod and the rudder shaft are arranged in a staggered manner;

the driving lead screw comprises a lead screw rod and a lead screw nut; the steering mechanism is characterized in that the screw nut is mounted on the screw rod, a fixing column is arranged on the screw nut, a guide groove is formed in one side, facing the screw rod, of the steering shaft, when the steering shaft is combined with the screw nut, the fixing column is located in the guide groove, a positioning column is arranged on one side, away from the steering shaft, of the screw nut, the rotation stopping plate is arranged along the length direction of the screw rod, a positioning groove is formed in the middle of the rotation stopping plate, the positioning column is located in the positioning groove, an external driving device drives the screw rod to rotate, the screw nut moves along the length direction of the screw rod, and the fixing column on the screw nut drives the steering shaft to swing.

2. The compound transmission for an aircraft according to claim 1, wherein the drive screw further comprises a drive bearing;

the two driving bearings are arranged at the positions, close to the two ends, of the screw rod, and the screw rod is arranged in the shell through the driving bearings.

3. The compound transmission for an aircraft as defined in claim 1, wherein the drive screw further comprises a drive gear;

the driving gear is fixedly connected with one end of the screw rod and is in transmission connection with the driving device.

4. The compound transmission for an aircraft according to claim 3, wherein the drive screw further comprises a lock nut;

the screw rod is provided with a fixing column with a non-circular cross section at one end facing the driving gear, a mounting hole matched with the fixing column is formed in the middle of the driving gear, the driving gear is inserted into the fixing column, threads are formed in one end, far away from the screw nut, of the fixing column, and the locking nut is mounted on the fixing column.

5. The cluster transmission of claim 1, wherein the rudder shaft comprises a first bearing, a second bearing and a shaft fork;

the rotating shaft shifting fork comprises a rotating shaft and a shifting fork, the shifting fork is installed on the rotating shaft, the first bearing and the second bearing are installed at two ends of the rotating shaft, and the guide groove is formed in the position, facing the shifting fork, of one end of the screw rod.

6. The transmission assembly as claimed in claim 5, wherein the fork is U-shaped, the end of the fork remote from the screw rod is mounted on the shaft, the guide groove is formed in a side arm of the fork facing the end of the screw rod, when the rudder shaft is mounted with the driving screw, the screw nut is located in the two side arms of the fork, and the fixing post is located in the guide groove.

7. The transmission according to claim 6, wherein the shift fork has guide grooves formed on both side arms thereof, and the guide grooves are symmetrically formed on both side arms of the shift fork.

8. The combined transmission device for the aircraft according to claim 7, wherein the number of the fixed columns is two, the two fixed columns are symmetrically arranged on two sides of the screw nut, and when the rudder shaft and the driving screw are assembled, the two fixed columns are located in the corresponding guide grooves.

9. The assembly transmission of claim 8, wherein a line connecting two of said fixed posts is perpendicular to a centerline of said positioning post.

10. The compound transmission device for an aircraft according to claim 5, wherein a center line of the rotation shaft is perpendicular to a center line of the lead screw rod.

Technical Field

The invention relates to the technical field of servo system transmission, in particular to a combined transmission mechanism for an aircraft.

Background

The steering engine is used as a servo control system and is mainly applied to control of the attitude angle of the steering engine in the flying process of a guided weapon, a control plane corner control instruction is received, and the corner control of a control plane is finally realized by controlling the rotating speed of a motor and gradually increasing the torque through an intermediate transmission mechanism. At present, an electric steering engine gradually occupies the research gravity center of a guided weapon, and the steering engine and a transmission system are also diversified, such as: worm and gear transmission, gear transmission and lead screw transmission. But the lightweight, miniaturization and intellectualization of the steering engine are the characteristics which must be possessed at present, and higher requirements are provided for each link of a steering engine system. The transmission system is used as a main component of the steering engine, and a transmission mechanism with small volume, simple structure and reliable transmission performance is urgently needed to be designed so as to improve the overall performance of the steering engine. However, most of the existing transmission devices are split and combined in aerospace products, and have the problems of small stroke and poor manufacturability, and are high in assembly difficulty and poor in reliability.

Disclosure of Invention

The invention aims to provide a combined transmission device for an aircraft, which is used for solving the technical problems of small stroke, poor manufacturability, high assembly difficulty and poor reliability of the existing split type or combined type transmission device.

In order to achieve the above purpose, the invention provides the following technical scheme:

provided is a combined transmission device for an aircraft, comprising: the steering mechanism comprises a rudder shaft, a driving screw rod and a rotation stopping plate, wherein the driving screw rod and the rudder shaft are arranged in a staggered manner;

the driving lead screw comprises a lead screw rod and a lead screw nut; the steering mechanism is characterized in that the screw nut is mounted on the screw rod, a fixing column is arranged on the screw nut, a guide groove is formed in one side, facing the screw rod, of the steering shaft, when the steering shaft is combined with the screw nut, the fixing column is located in the guide groove, a positioning column is arranged on one side, away from the steering shaft, of the screw nut, the rotation stopping plate is arranged along the length direction of the screw rod, a positioning groove is formed in the middle of the rotation stopping plate, the positioning column is located in the positioning groove, an external driving device drives the screw rod to rotate, the screw nut moves along the length direction of the screw rod, and the fixing column on the screw nut drives the steering shaft to swing.

Compared with the prior art, the driving screw and the rudder shaft in the combined transmission device for the aircraft are installed in a staggered mode, the space occupied by the transmission mechanism is effectively reduced by adopting the staggered installation mode, the size is smaller, the driving screw and the rudder shaft are not only separated, but also are a unified whole, and the assembly is more convenient; the rudder shaft and the screw rod are vertically arranged, so that the rudder shaft can stably rotate and can rapidly respond in the process that the screw rod nut moves up and down along the screw rod, the rudder shaft is uniformly stressed and does not incline when the screw rod nut pushes the rudder shaft, and the screw rod nut can not rotate in the process of moving up and down and has better transmission effect due to the arranged rotation stopping plate; the screw nut moves along the screw rod, and the screw rod is not shielded, so that the movement stroke of the screw nut is improved to the maximum extent. The combined transmission device for the aircraft is simple in structure, convenient to assemble, large in stroke, stable in transmission, high in reliability and high in practicability.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 is a schematic diagram of the components of a combined transmission for an aircraft according to an embodiment of the invention;

FIG. 2 is a schematic combination diagram of the combination transmission for the aircraft of FIG. 1;

fig. 3 is a side view of the compound transmission of fig. 1 for the aircraft.

Reference numerals:

1. a rudder shaft; 1-1, a first bearing; 1-2, a rotating shaft shifting fork; 1-3, a second bearing; 2. driving a lead screw; 2-1, locking a nut; 2-2, driving a gear; 2-3, driving a bearing; 2-4, a screw rod and a screw rod; 2-5, screw nut; 3. and a rotation stopping plate.

Detailed Description

In order to make the technical problems, technical solutions and advantageous effects to be solved by the present invention more clearly apparent, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or be indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or be indirectly connected to the other element.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise. The meaning of "a number" is one or more unless specifically limited otherwise.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, 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; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

As shown in fig. 1 to 3, the present invention provides a combined transmission device for an aircraft, including: the rudder shaft 1, the driving screw 2 and the rotation stopping plate 3, wherein the driving screw 2 and the rudder shaft 1 are arranged in a staggered manner;

the driving screw 2 comprises a screw rod 2-4 and a screw rod nut 2-5; the screw rod nut 2-5 is arranged on the screw rod 2-4, the screw rod nut 2-5 is provided with a fixed column, one side of the rudder shaft 1 facing the screw rod 2-4 is provided with a guide groove, when the rudder shaft 1 is combined with the screw rod nut 2-5, the fixed column is positioned in the guide groove, one side of the screw rod nut 2-5 far away from the rudder shaft 1 is provided with a positioning column, the rotation stopping plate 3 is arranged along the length direction of the screw rod 2-4, the middle part of the rotation stopping plate is provided with a positioning groove, the positioning column is positioned in the positioning groove, an external driving device drives the screw rod 2 to rotate, the screw rod nut 2-5 moves along the length direction of the screw rod 2-4, and the fixed column on the screw rod nut 2-5 drives the rudder shaft 1 to swing.

In the specific implementation:

a rudder shaft 1 and a driving screw 2 of the combined transmission device for the aircraft are used as main components, and a first bearing 1-1 and a second bearing 1-3 are arranged at the left end and the right end of a rotating shaft shifting fork 1-2 to form a rudder shaft 1 structure; the driving screw 2 is mainly characterized in that the driving gear 2-2 is coaxially and fixedly connected with a screw rod 2-4 through a locking nut 2-1, driving bearings 2-3 are installed at two ends of the screw rod 2-4, and the screw rod 2-4 is matched with a screw nut 2-5. The screw nut 2-5 and the shifting fork 1-2 are also intermediate links for connecting the rudder shaft 1 and the driving screw 2, the screw nut 2-5 is driven to move up and down through the screw rod 2-4, and the screw nut 2-5 pushes the shifting fork 1-2 to realize a preset rotation angle so as to realize final control surface rotation angle control. The function of the rotation stopping plate 3 is to ensure that the nut does not rotate axially when the nut is subjected to moment.

Compared with the prior art, the driving screw and the rudder shaft in the combined transmission device for the aircraft are installed in a staggered mode, the space occupied by the transmission mechanism is effectively reduced by adopting the staggered installation mode, the size is smaller, the driving screw and the rudder shaft are not only separated, but also are a unified whole, and the assembly is more convenient; the rudder shaft and the driving screw are vertically arranged, so that the rudder shaft can stably rotate and can rapidly respond in the process that the screw nut moves up and down along the screw rod, the rudder shaft can be uniformly stressed and cannot incline when the screw nut pushes the rudder shaft, and the screw nut can not rotate in the process of moving up and down and has better transmission effect due to the arranged rotation stopping plate; the screw nut moves along the screw rod, and the screw rod is not shielded, so that the movement stroke of the screw nut is improved to the maximum extent. The combined transmission device for the aircraft is simple in structure, convenient to assemble, large in stroke, stable in transmission, high in reliability and high in practicability.

As an embodiment, the driving screw 2 further comprises a driving bearing 2-3; the number of the driving bearings 2-3 is two, the two driving bearings 2-3 are arranged at the positions, close to the two ends, of the screw rod 2-4, and the screw rod 2-4 is arranged in the shell through the driving bearings 2-3.

The arrangement of the driving bearings 2-3 facilitates the rotation of the screw rod 2-4 driven by an external driving device, reduces the friction force during rotation, and meanwhile, the driving bearings 2-3 are arranged at the two ends of the screw rod 2-4, so that the large stroke of the screw nut 2-5 during the movement on the screw rod 2-4 is ensured to the greatest extent, and the range of the adjustable angle of the rudder shaft 1 is increased.

As an embodiment, the driving screw 2 further includes a driving gear 2-2; the driving gear 2-2 is fixedly connected with one end of the screw rod 2-4 and is in transmission connection with an external driving device.

The driving gear 2-2 is arranged, can be in transmission connection with a driving device which provides power with the outside better, and transmits the output power of the driving device to the screw rod 2-4, so as to drive the screw rod nut 2-5 to move along the length direction of the screw rod 2-4, and thus the adjustment of the angle of the rudder shaft 1 is realized. The power transmission is more stable by adopting the transmission form of the driving gear 2-2. Further, the driving device and the driving gear 2-2 may be combined by a driving wheel set to provide a larger output torque.

As an embodiment, the driving screw 2 further comprises a lock nut 2-1; one end of the screw rod 2-4, facing the driving gear 2-2, is provided with a fixing column with a non-circular cross section, the middle part of the driving gear 2-2 is provided with a mounting hole matched with the fixing column, the driving gear 2-2 is inserted into the fixing column, one end of the fixing column, far away from the screw nut 2-5, is provided with a thread, and the locking nut 2-1 is mounted on the fixing column.

The driving gear 2-2 is installed in a mode that the installation columns are matched with the installation holes, when the driving gear 2-2 is installed and disassembled, the installation is simpler and more convenient, the fixed installation of the driving gear 2-2 is realized through the arrangement of the locking nut 2-1, the situation that the driving gear 2-2 falls off from the screw rod 2-4 is avoided, and the combined installation and the maintenance are more convenient.

As an implementation mode, the rudder shaft 1 comprises a first bearing 1-1, a second bearing 1-3 and a rotating shaft shifting fork; the rotating shaft shifting fork comprises a rotating shaft and a shifting fork, the shifting fork is arranged on the rotating shaft, the first bearing 1-1 and the second bearing 1-3 are arranged at two ends of the rotating shaft, and the guide groove is formed in one end, facing the screw rod 2-4, of the shifting fork.

The rudder shaft 1 composed of the first bearing 1-1, the second bearing 1-3 and the rotating shaft shifting fork 1-2 is in transmission connection with the rudder surface, when the screw nut 2-5 drives the rotating shaft shifting fork 1-2 to swing, the adjustment of the rotating angle of the rudder surface can be better realized, the form of bearing installation is adopted, the resistance of the rotating shaft shifting fork 1-2 during rotation is reduced, the power transmission is more stable, and the response is more rapid.

As an implementation mode, the shifting fork is of a U-shaped structure, one end, far away from the lead screw rod 2-4, of the shifting fork is installed on the rotating shaft, the guide groove is formed in a side arm, facing the end of the lead screw rod 2-4, of the shifting fork, when the rudder shaft 1 and the driving lead screw 2 are installed in a combined mode, the lead screw nuts 2-5 are located in the two side arms of the shifting fork, and the fixing column is located in the guide groove.

One end of a shifting fork with a U-shaped structure is fixedly connected with a rotating shaft, the shifting fork is matched with a first bearing 1-1 and a second bearing 1-3 to rotate, the position of the rotating shaft is fixed, the shifting fork only swings under the driving of a screw nut 2-5, two side arms at the other end of the shifting fork are provided with guide grooves, fixing columns are located in the guide grooves, the fixing columns are located on the innermost side of the guide grooves when the shifting fork is opposite to the screw rod 2-4 in positive phase, the fixing columns gradually move to the positions of the openings of the guide grooves along with the swinging of a rudder shaft 1, and the fixing columns cannot be separated from the guide grooves when the screw nut 2-5 moves to the positions of the two ends of the screw rod 2-4, so that the shifting fork is in a controllable range and the adjustable angle is larger in the whole process of the screw nut 2-5. In the whole control process, the screw nuts 2-5 and the screw rods 2-4 are positioned in the two side arms of the shifting fork, and the distance between the screw rods 2-4 and the rotating shaft cannot be changed, so that the transmission mechanism is more compact in structure and smaller in occupied space.

As an implementation mode, the two side arms of the shifting fork are provided with guide grooves, and the two guide grooves are symmetrically arranged on the two side arms of the shifting fork. Furthermore, the number of the fixing columns is two, the two fixing columns are symmetrically arranged on two sides of the screw nuts 2-5, and when the rudder shaft 1 and the driving screw 2 are installed in a combined mode, the two fixing columns are located in the corresponding guide grooves.

When the single fixing column is adopted, the fixing column is positioned in the guide groove in the single side arm, and when the side wall goes wrong, the fixing column can be replaced into another guide groove, so that the service life of the shifting fork is prolonged to a certain extent, and the maintenance cost is saved. When the rudder shaft 1 swings, the two fixing columns are symmetrically arranged on two sides of the screw nut 2-5, and the two fixing columns are also symmetrically arranged in the guide groove, so that the two side arms of the shifting fork are stressed more uniformly, the two side arms of the shifting fork cannot incline, and the stability of the rudder shaft 1 during swinging is ensured.

As an implementation mode, a connecting line between the two fixed columns is perpendicular to a central line of the positioning column.

The connecting line between the fixed columns is perpendicular to the central line of the positioning columns, so that the integrity of the screw nuts 2-5 is stronger, the rotation stopping plates 3 and the shifting forks are respectively positioned at two sides of the screw bolts 2-4 after being installed, the spatial positions of the screw nuts 2-5, the rotation stopping plates 3 and the like are more reasonable, and the installation and maintenance are more convenient. When the structures of the rotation stopping plate 3, the driving bearings 2-3 and the like are installed and used, the positions are fixed and unchanged, and any position change cannot occur along with the movement of the screw nuts 2-5.

As an implementation mode, the central line of the rotating shaft is perpendicular to the central line of the screw rod screw 2-4.

The central line of the rotating shaft is vertical to the central lines of the lead screw rods 2-4, so that the rudder shaft 1 and the driving lead screw 2 are vertically and alternately connected, the whole structure of the transmission mechanism is more compact, the real space is smaller, and the assembly and the processing are easier.

In the foregoing description of embodiments, the particular features, structures, materials, or characteristics may be combined in any suitable manner in any one or more embodiments or examples.

The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.