Method for additionally mounting control augmentation system on flight control system of amphibious aircraft

Abstract

The invention discloses a basic principle of additionally mounting a control augmentation system on a mechanical hydraulic assisted operating system of an amphibious aircraft with an autopilot and an implementation method thereof. The control augmentation system is additionally mounted on the basis of the original mechanical power and the autopilot so as to form a mechanical control augmentation flight control system with the autopilot; and except for necessary equipment, such as a display control panel, a control augmentation computer, a sensor and a control augmentation steering engine, of the system, the control augmentation system is additionally mounted only by changing one common rocker arm behind an autopilot steering engine and in front of a hydraulic booster into a composite rocker arm and connecting the composite rocker arm with an output of the control augmentation steering engine in parallel. According to the basic principle of additionally mounting the control augmentation system on the mechanical hydraulic assisted operating system of the amphibious aircraft with the autopilot and the implementation method thereof, the change is minimum, the weight cannot be increased too much, and the additionally mounted control augmentation system can be compatible with the existing autopilot; therefore, no matter whether the autopilot is put through or not, the control augmentation system can be put through to work so that a full-time control augmentation function is realized. Through adoption of the embodiment, the improving problems of controllabitity and stability of the amphibious aircraft can be effectively solved, the flying quality of the amphibious aircraft can improved and the compatibility between the control augmentation system and the original system can be guaranteed.

Description

technical field [0001] The invention relates to the field of aircraft flight control system design, in particular to the basic principle and implementation method of adding a control and stability enhancement system to an amphibious aircraft with an autopilot mechanical-hydraulic power-assisted control system. Background technique [0002] The existing flight control system of amphibious aircraft is a mechanical hydraulic power-assisted control system with an autopilot. When it performs general flight tasks, its handling and ride quality are acceptable. However, when it takes off and lands in harsh water conditions or performs special flights For tasks such as fire extinguishing and water throwing, sea search and rescue, and low-altitude and low-speed circling, etc., its maneuverability and stability are often insufficient, while the mechanical control system only relies on the pilot's driving skills and experience to control the flight, and its requirements for the pilot's c...

AI Technical Summary

Problems solved by technology

[0002] The existing flight control system of amphibious aircraft is a mechanical hydraulic power-assisted control system with an autopilot. When it performs general flight tasks, its handling and ride quality are acceptable. However, when it takes off and lands in harsh water conditions or performs special flights For tasks such as fire extinguishing and water throwing, sea search and rescue, and low-altitude and low-speed circling, etc., its maneuverability and stability are often insufficient, while the mechanical control system only relies on the pilot's driving skills and experience to control the flight, and its requirements for the pilot's control are high. The flight quality cannot be guaranteed. In addition, the autopilot system of the amphibious aircraft has a narrow envelope and low control authority, so it cannot perform automatic flight tasks in special flight environments

In addition, in order to further improve the water take-off and landing performance of the amphibious aircraft, reduce the water take-off and landing speed, and increase the anti-wave height, it will also adopt the flap blowing boundary layer to control the increased lift technology, and the aircraft will use the boundary surface when taking off and landing. With layer-blown air-increasing lift technology, the aerodynamic focus may move forward, which will also lead to insufficient longitudinal static stability of the aircraft, and because the aircraft is flying at a low speed and high angle of attack during takeoff and landing, the longitudinal dynamic stability and damping characteristics of the aircraft will decrease. Ultimately, the control quality of the existing flight control system deteriorates

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