Search

JP-2026075750-A - Control system and control system with aircraft

JP2026075750AJP 2026075750 AJP2026075750 AJP 2026075750AJP-2026075750-A

Abstract

[Problem] The problem is to provide a control system, aircraft, and control method that reduce the control load. [Solution] The control system 4 is a control system for use in a helicopter or an aircraft equipped with a tiltwing/tiltrotor mechanism, and is characterized by comprising an acquisition unit 15 that acquires wind information 17 including wind speed and/or wind direction at a predetermined distance from the aircraft from a detection unit 18, and a control unit 13 that controls the aircraft based on the wind information. The detection unit 18 is a LIDAR sensor. [Selection Diagram] Figure 3

Inventors

  • 森本 高広
  • 前田 巌

Assignees

  • スカイリンクテクノロジーズ株式会社

Dates

Publication Date
20260511
Application Date
20241023

Claims (6)

  1. A control system for use in a helicopter or an aircraft equipped with a tiltwing or tiltrotor mechanism, An acquisition unit that acquires wind information, including wind speed and/or wind direction, at a predetermined distance from the aircraft, A control system comprising a control unit that controls the aircraft based on the wind information.
  2. The control system according to claim 1, wherein the control unit controls the attitude of the aircraft during hovering, vertical takeoff and landing, or short takeoff and landing.
  3. The control system according to claim 1 or 2, wherein the detection unit is a LIDAR sensor.
  4. An aircraft consisting of a helicopter or an airplane having a tiltwing or tiltrotor mechanism, An aircraft equipped with the control system described in claim 3.
  5. Claim 4, wherein the detection unit is provided on the nose side of the aircraft and near the lower end. The aircraft described.
  6. A program for a control system used in a helicopter or an aircraft equipped with a tiltwing or tiltrotor mechanism, On the computer, The detection unit acquires wind information, including wind speed and/or wind direction, at a predetermined distance from the aircraft. A program that controls the aircraft to achieve a pre-registered flight state based on the wind information.

Description

This relates to helicopters or aircraft having tiltwing or tiltrotor mechanisms. In recent years, preparations have been underway for the necessary verifications to make vertical takeoff and landing (VTOL) aircraft a common mode of transportation. Patent Document 1 discloses a VTOL aircraft. Patent Document 2 describes a drone. This drone determines the rotation speed of each motor and the flight angle according to the wind speed and direction. Special Publication No. 2023-511703Japanese Patent Publication No. 2022-44557 This is a schematic perspective view showing one embodiment of an aircraft.This is a schematic diagram showing the behavior during horizontal flight, vertical takeoff and landing, or hovering.This is a functional block diagram showing one implementation of a control system.Figure 2 is a schematic diagram showing the wings and prop rotors of an airplane during vertical takeoff and landing or hovering, viewed from the side.This is a schematic diagram showing an example of the hardware configuration of the control unit.This is a flowchart illustrating one embodiment of the processing of a program used in a control system.Figure 7a is a schematic diagram showing the data structure of the wind information database, and Figure 7b is a schematic diagram showing the data structure of the control database.This is a schematic plan view showing the internal structure of an airplane. [1. Overview] <First Embodiment> Flying object (airplane) 1 An outline of an aircraft equipped with the control system 14 of the present invention (see Figure 3) will be explained using Figure 1. In this specification, STOL (Short Take-Off and Landing) aircraft and VTOL (Vertical Take-Off and Landing) aircraft are referred to as airplanes, and both airplanes and helicopters are collectively referred to as flying vehicles. The aircraft 1 shown in Figure 1 is a vertical take-off and landing (VTOL) aircraft. Broadly speaking, the aircraft 1 consists of a main body 2, a pair of tilt wings 3, 3 mounted on the main body, and prop rotors 4, 4 mounted on each of the left and right wings 3, 3. A tail rotor 29 is also provided at the rear of the main body 2. In this embodiment, horizontal stabilizers 5a extend to the left and right from the rear end of the main body 2. Vertical stabilizers 5b are provided at both ends of the horizontal stabilizers. In the following explanation, the direction in which the main body 2 extends will be considered the front-to-back direction (the direction in which the longitudinal axis extends), the direction in which the wings 3 extend will be considered the left-to-right direction, and the direction in which the vertical stabilizer 5b extends will be considered the up-to-down direction. The side of the main body 2 with the wings 3 is the front, the front side of the wings 3 in the diagram is the left, and the tip of the vertical stabilizer indicated by the symbol 5b is the top. These front-to-back, left-to-right, and up-to-down directions are indicated by arrows in the diagram. (Wings 3) A connecting section (not shown) is provided between the wing 3 and the main body 2. The connecting section connects the main body 2 to the left and right wings 3. The connecting section tilts the wings 3. In this embodiment, the wings 3 are tilted relative to the main body 2 by a tilt drive unit 19 (see Figure 2). Furthermore, the wing 3 is equipped with ailerons 16 (see Figure 4) for controlling the attitude of the aircraft 1. In addition, although not shown, the wing 3 is appropriately equipped with flaps and other devices, mainly for increasing or decreasing lift. (Prop Rotor 4) The prop rotor 4 is used, for example, in VTOL aircraft, and is a rotating mechanism equipped with aerodynamic wings that combine the functions of a fixed-wing aircraft propeller and a helicopter rotor. (Prop rotor 4, propeller shaft 4a, blades 4b) The prop rotor 4 is equipped with rotor blades 4b that rotate on the propeller shaft 4a. The blades 4b extend in a direction substantially perpendicular to the propeller shaft 4a, that is, in the radial direction of the plane of rotation on which the propeller rotates. (Tail rotor 29) The tail rotor 29 has a rotation axis parallel to the vertical direction. The tail rotor 29 allows for control of the aircraft's pitch. The tail rotor 29 comprises a rotor shaft 29a and rotor blades 29b that rotate around the rotor shaft 29a. The rotor blades 29b extend in a direction substantially perpendicular to the rotor shaft 29a, that is, in the radial direction of the plane of rotation of the propeller. (Horizontal stabilizer 5a, elevator 23) In this embodiment, horizontal stabilizers 5a extend to the left and right from the rear end of the main body 2. Elevators 23 are provided on the horizontal stabilizers 5a. (Vertical stabilizer 5b, rudder 24) In this embodiment, vertical stabilizers 5b are provided at both ends of the horizontal stabilizer. A rudder 24 is provided on the vertical stabilizer 5b. (Level f