Unmanned plane longitudinal control system

Abstract

The invention discloses an unmanned plane longitudinal control system, and belongs to the technical field of unmanned plane control system. The system comprises an electric steering engine (1), a first switch rocking arm (2), a connection pull bar (3), a second switch rocking arm (4), a rotation shaft (5), a third switch rocking arm (6), and a driving pull bar (7). The electric steering engine (1) is arranged in a rear fuselage cabin. The first switch rocking arm (2) is hinged to the electric steering engine (1) and one end of the connection pull bar (3). The other end of the connection pull bar (3) is hinged to the second switch rocking arm (4). The second switch rocking arm (4) and the third switch rocking arm (6) are both fixedly connected to the rotation shaft (5). One end of the driving pull bar (7) is connected to the elevating rudder and the other end is hinged to the third switch rocking arm (6). The provided system solves the problem that when the installation space of the elevating rudder surface is limited and the strength of the structure next to the elevating rudder surface is insufficient, the electric transmission and mechanical control of an actuator can be realized, the output is reliable, and the plane weight is reduced.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicle control systems, and in particular relates to a longitudinal control system for unmanned aerial vehicles. Background technique [0002] As an important flight control system, the aircraft control system can seriously affect the safety of the aircraft whether it can work normally. At present, the development of medium-sized UAV platforms is less, and its longitudinal control system generally adopts fly-by-wire control, but this control method is limited to a certain extent by the installation space and the structural strength near the elevator rudder surface, so that the high-power steering gear Sometimes it cannot be installed near the control surface to directly drive the deflection of the rudder surface, which brings certain troubles to the design and production of the control system. [0003] The elevator of the aircraft longitudinal control system is located obliquely above th...

AI Technical Summary

Problems solved by technology

At present, the development of medium-sized UAV platforms is less, and its longitudinal control system generally adopts fly-by-wire control, but this control method is limited to a certain extent by the installation space and the structural strength near the elevator rudder surface, so that the high-power steering gear Sometimes it cannot be installed near the control surface to directly drive the deflection of the rudder surface, which brings some troubles to the design and production of the control system

[0003] The elevator of the aircraft longitudinal control system is located obliquely above the electric steering gear, and there is less space at the end. If it is directly driven by a linkage mechanism, for example, the first connecting rod is connected to the electric steering gear, the second connecting rod is connected to the elevator, and the first connecting rod is connected to the elevator. The second connecting rod is hinged by the rocker arm. Due to space problems, the rocker arm can only be installed at the bottom of the first connecting rod. At this time, the second connecting rod will interfere with the first connecting rod. Therefore, it is necessary to design a new structure to solve the above problems

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