阅读说明：本技术 一种轨道曲线飞行自控器 (Track curve flight automatic controller ) 是由 杨复明 于 2021-08-17 设计创作，主要内容包括：本发明公开了一种轨道曲线飞行自控器,包括壳体,所述壳体内设置有控制器、气动阀、气动收放轴,所述气动收放轴为对称设置的两个,其输出端伸出所述壳体固定连接有方向叶,所述方向叶为对称设置的两个,其在所述气动收放轴的驱动下快速伸缩,所述气动阀为对称设置的两个,其通过气管与所述气动收放轴连通,所述气动阀与所述控制器电连接,所述控制器通过控制所述气动阀进而驱动所述气动收放轴的收放伸缩。本发明通过气动阀控制气动收放轴进行收放伸缩,进而调整设置在气动收放轴输出端的方向叶的位置,实现了对飞行器转向的控制。本发明操作简单,通过控制器自动控制飞行方向,自动化程度高,实用性强。(The invention discloses a track curve flight automatic controller which comprises a shell, wherein a controller, two pneumatic valves and two pneumatic retracting shafts are arranged in the shell, the two pneumatic retracting shafts are symmetrically arranged, the output ends of the two pneumatic retracting shafts extend out of the shell and are fixedly connected with two direction blades, the two direction blades are symmetrically arranged and are driven by the pneumatic retracting shafts to rapidly extend and retract, the two pneumatic valves are symmetrically arranged and are communicated with the pneumatic retracting shafts through air pipes, the pneumatic valves are electrically connected with the controller, and the controller controls the pneumatic valves to further drive the pneumatic retracting shafts to extend and retract. The invention controls the pneumatic retracting shaft to retract through the pneumatic valve, and further adjusts the position of the direction blade arranged at the output end of the pneumatic retracting shaft, thereby realizing the control of the steering of the aircraft. The invention has simple operation, high automation degree and strong practicability, and the flight direction is automatically controlled by the controller.)

1. The utility model provides an orbit curve flight automatic controller, a serial communication port, which comprises a housin, be provided with controller, pneumatic valve, pneumatic receipts in the casing and put the axle, pneumatic receipts are put two that the axle set up for the symmetry, and its output stretches out casing fixedly connected with direction leaf, two that the direction leaf set up for the symmetry, it is in quick flexible under the drive of pneumatic receipts axle, two that the pneumatic valve set up for the symmetry, it pass through the trachea with pneumatic receipts axle intercommunication, the pneumatic valve with the controller electricity is connected, the controller is through control pneumatic valve and then drive the receiving and releasing of axle is flexible.

2. An orbital curve flight self-controller as claimed in claim 1 wherein said controller has a timer counter disposed therein and said housing has an operating button disposed thereon, said operating button being electrically connected to said controller.

3. The orbital curve flight automatic controller according to claim 1, wherein the opposite side of the pneumatic retracting shaft is fixed by screws, the pneumatic retracting shaft extends and retracts under the control of the pneumatic valve to drive the direction vane to move, and the direction vane realizes steering control of the whole aircraft by changing the position of the vane.

4. The orbital curve flight self-controller of claim 1, wherein said controller is controlled and connected by direct current to avoid strong electromagnetic interference.

Technical Field

The invention relates to the technical field of curve flight, in particular to an orbit curve flight automatic controller.

Background

In modern war, missiles are an indispensable means of combating enemy targets. The existing missile is actually a parabola from the launch to the target. However, in order to avoid the back-guided interception, the missile must make an irregular curve advance.

Recently, russia develops a curve flying missile which can be attacked without a reverse guidance system, but the principle of controlling curve flight mainly depends on a navigation system, and the navigation system runs by means of weak current and is easily subjected to strong electromagnetic interference to influence the normal use of the navigation system.

Therefore, a rail flight self-controller free from external strong electromagnetic interference needs to be researched and solved.

Disclosure of Invention

In order to solve the technical problems, the technical scheme provided by the invention is as follows: the utility model provides an orbit curve flight automatic controller, includes the casing, be provided with controller, pneumatic valve, pneumatic receipts and releases the axle in the casing, pneumatic receipts are two that the symmetry set up for the axle, and its output stretches out casing fixedly connected with direction leaf, two that the direction leaf set up for the symmetry, it is in quick flexible under the drive of pneumatic receipts and releases the axle, two that the pneumatic valve set up for the symmetry, its pass through the trachea with pneumatic receipts and releases the axle intercommunication, the pneumatic valve with the controller electricity is connected, the controller is through control pneumatic valve and then drive the receiving and releasing of axle is flexible.

As an improvement, a timing counter is arranged in the controller, an operating button is arranged on the shell, and the operating button is electrically connected with the controller.

As an improvement, one side of the pneumatic folding and unfolding shaft opposite to the pneumatic folding and unfolding shaft is fixedly connected through screws, the pneumatic folding and unfolding shaft stretches and retracts under the control of the pneumatic valve so as to drive the direction blade to move, and the direction blade realizes steering control of the whole aircraft by changing the position of the blade.

As improvement, the controller adopts direct current control and connection, so that strong electromagnetic interference is avoided.

After adopting the structure, the invention has the following advantages: the invention controls the pneumatic retracting shaft to retract through the pneumatic valve, and further adjusts the position of the direction blade arranged at the output end of the pneumatic retracting shaft, thereby realizing the control of the steering of the aircraft. The flight control system is simple to operate, the flight direction is automatically controlled through the controller, the automation degree is high, the beneficial effect of automatically controlling and changing the flight direction is achieved, and the practicability is high.

Drawings

Fig. 1 is a schematic structural diagram of an orbital curve flight automatic controller of the invention.

As shown in the figure: 1. the device comprises a shell, 1.1, an operation button, 2, a controller, 3, a pneumatic valve, 4, a pneumatic folding and unfolding shaft, 5 and a direction blade.

Detailed Description

Combine figure 1, a track curve flight automatic controller, including casing 1, be provided with controller 2, pneumatic valve 3, pneumatic receipts in the casing 1 and put axle 4, pneumatic receipts are put two of axle 4 for the symmetry setting, and its output stretches out 1 fixedly connected with direction leaf 5 of casing, two of direction leaf 5 for the symmetry setting, it is in quick flexible under the drive of pneumatic receipts axle 4, pneumatic valve 3 is two of symmetry setting, its pass through the trachea with pneumatic receipts is put 4 intercommunications of axle, pneumatic valve 3 with 2 electricity of controller are connected, controller 2 is through control pneumatic valve 3 and then drive pneumatic receipts are put 3 receive and are put stretching out and drawing back.

As a preferred embodiment of this embodiment, a timing counter is disposed in the controller 2, an operation button 1.1 is disposed on the housing 1, and the operation button 1.1 is electrically connected to the controller 2.

As a preferred embodiment of the present embodiment, the opposite side of the pneumatic retracting shaft 4 is fixed by a screw connection, the pneumatic retracting shaft 4 extends and retracts under the control of the pneumatic valve 3 to drive the direction vane 5 to move, and the direction vane 5 realizes the steering control of the whole aircraft by changing the vane position.

As a preferred embodiment of this embodiment, the controller 2 is controlled and connected by a dc power, so as to avoid strong electromagnetic interference.

Finally, the above embodiments are only intended to illustrate the technical solutions of the present invention and not to limit the present invention, and although the present invention is described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions, and all of them should be covered in the claims of the present invention.