Hanging frame for helicopter to deliver aircraft at low speed and aircraft attitude control method

Abstract

The invention discloses a hanging frame for a helicopter to deliver an aircraft at the low speed and an aircraft attitude control method. The hanging frame comprises a main steel cable, hanging frame steel cables, damping plates, a hanging frame main structure, a stable umbrella, compressing components and separation release components. One end of the main steel cable is connected with the helicopter, and the other end of the main steel cable is connected with the hanging frame main structure through the hanging frame steel cables; the damping plates are used for reducing left-and-right swing of the hanging frame; the stable umbrella is used for removing front-and-back swing of the hanging frame and rotating, around the main steel cable, of the hanging frame; each compressing component comprises a compressing switch and an adjustable compressing foot, and used for separating signal detection; and the aircraft is hung below the hanging frame main structure through the separation release components. The aircraft attitude control method includes the following steps that the aircraft performs separation signal detection based on a reliable separation signal detection circuit formed by the compressing switches; before separation, open-loop control over a longitudinal channel and a heading channel of the aircraft is carried out, and close-loop control over a roll angle of a transverse channel is carried out; after separation, close-loop control over the pitch angle and normal acceleration of the longitudinal channel of the aircraft is carried out, and close-loop control over the roll angle of the transverse channel is carried out; and close-loop control over lateral acceleration of the heading channel is carried out.

Description

technical field [0001] The invention relates to a pylon suitable for launching a non-powered lift aircraft at low speed by a helicopter and a method for controlling the attitude of the aircraft, belonging to the field of attitude control design of the aircraft. Background technique [0002] Orbital reentry or suborbital reentry lift aircraft can achieve horizontal landing by relying on aerodynamic force and gravity, and do not necessarily need to use or configure complex active power systems, such as space shuttle, X-37B, SpaceShipTwo, Dream Chaser, etc. Since no active propulsion system is used or configured, this type of aircraft needs to use other carrier platforms for hanging and mooring tests and launching flight tests during the development process, such as transport aircraft or helicopters, to verify the low-speed aerodynamic characteristics of the aircraft and the approach and landing guidance control technology. Early American space shuttles used modified Boeing 7...

AI Technical Summary

Problems solved by technology

The above technical solutions have obvious disadvantages, and the scope of application is limited

For example, ALFLEX pylons are complex in composition and difficult to operate in practice; X-40A and Dream Chaser are greatly affected by high-altitude winds in the mounted state, and this suspension scheme requires the aircraft to have good static stability and be able to tolerate interference; Phoenix The impact of the carrier aircraft is more significant, and the three steel cables are prone to entanglement, so there are strict requirements for the flight of the carrier aircraft

In addition, the aircraft attitude control scheme included in the above technical solutions also has disadvantages, for example, it is difficult to obtain the angle of attack signal that needs to be used accurately, and it is difficult to ensure the stability of the attitude after separation without using the feedback control of pitch angle and roll angle at the same time

Images