Electronic system for minimal control of aircrafts in difficulty
Patent Information
- Application Number
- RO2017000838
- Authority / Receiving Office
- RO · RO
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2017-10-18
- Publication Date
- 2026-07-30
- Estimated Expiration
- 2037-10-18
AI Technical Summary
Existing aircraft flight control systems are vulnerable to failure when mechanical, hydraulic, or electric components are severed, leading to loss of control during emergencies, as they rely on centralized power and connection systems.
The implementation of wing-mounted actuators driven by accumulators charged by photovoltaic cells, with remote-controlled mini-control surfaces allowing pilots to manually steer the aircraft using a smartphone-sized device, independent of traditional power sources and systems.
Enables controlled, slow maneuvers for emergency landings even when primary control systems fail, providing a backup means of orientation and landing, and allowing satellite or parallel aircraft control in extreme situations.
Abstract
Description
ELECTRONIC SYSTEM FOR MINIMUM FLIGHT CONTROL OF AIRS IN DIFFICULTY The field of application of aircraft flight control systems. A number of aircraft flight control solutions are known. One solution is to have the control surfaces (depth, drift, flaps, ailerons) operated by flexible steel cables in the cockpit. Another solution is to have these control surfaces operated by a hydraulic system and another to be operated by electric actuators powered by electric cables. The disadvantages of these solutions are that an accidentally detached part of the engine (turbine or compressor disc) can completely segment all mechanical cable systems, hydraulic pipes or electric power supply cables at a time when the aircraft can no longer be controlled. The technical solution according to the present invention consists in the arrangement of wings-control surfaces on the wings, the horizontal and vertical impingement which are directly driven by actuators with built-in reducer actuated by accumulators permanently charged by photovoltaic cells located nearby on the wings and the control surfaces. The control mini-surfaces are operated by remote control from a small device the size of a mobile phone in the possession of each pilot. The construction of the mini-control surfaces and how to use them for the control of the aircraft are the subject of patent no ......... The advantage and originality of the present invention is that in the case of segmentation of all the current command lines of the normal flight control surfaces, the pilots have remote controls that offer a last chance to slowly orient the aircraft to a nearby runway or land. slightly injured suitable for forced landing by controlled movement of the mini control surfaces. The second advantage is that this system is independent from all points of view of the aircraft (power supply, interconnections with other aircraft systems, etc.). The third advantage is that in special cases when the pilots can no longer control the aircraft in the cabin, it can be controlled by satellite or an aircraft flying in parallel with it. The following is an example of embodiment of the invention, in connection with FIGS. 1 ... 4, which represents: • fig. 1-View of an aircraft indicating the positioning of the groom-control surfaces; fig.2-Section through the wing showing the system components; . fig.3- View of the remote control of the system; • fig.4-Electrical diagram of the system. The electronic system for the minimum flight control of the aircraft in difficulty according to the present invention (fig.2) consists of the control module 1, the antenna 2, the battery pack 3, the solar cells 4 placed on the wing surfaces, the horizontal and vertical docking, the conductors 5 , the servomotors 6 placed in the wings 7 (fig.1), the horizontal 8 and vertical damping 9 of the aircraft 10, and the remote control in fig.3 from which the movement of the control surfaces 11 is commanded (fig.1,2). The electronic control system for the position of the minimal flight control surfaces of the aircraft in difficulty according to the present invention works as follows: PRESIDENT GENERAL DIRECTOR Dr. Eng. Valentin SIL -1 to 2017 00838 10 / 18 / 2017 When all the control systems of the aircraft fall, the pilot takes control of the aircraft through the remote control in his possession. By operating the remote control, the pilot indicates the minisurface and its rotation degrees from the buttons shown in fig.3. The command is received by the antenna 2 (fig.2), which sends the command to the control module 1, which controls the actuation of the actuator 6, which rotates the control surfaces 11 with respect to the level of the wing surfaces, the horizontal or vertical gear depending on the desired evolution. Only slow maneuvers to return and steer the aircraft to a nearby landing strip or an appropriate landing field that are suitable for a forced landing are possible.
Claims
The mechanical system and the control surfaces for the minimum control of the aircraft according to the present invention which consists (fig.2) of the electronic module 1, antenna 2, battery battery 3, photovoltaic cells 4, conductors 5, servomotors with reducer 6. which operate mini - control surfaces 11.