CN112208772A

CN112208772A - Full-automatic low-energy-consumption deicing control system

Info

Publication number: CN112208772A
Application number: CN202010937238.2A
Authority: CN
Inventors: 刘红光
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-09-08
Filing date: 2020-09-08
Publication date: 2021-01-12

Abstract

The invention belongs to the technical field of aircraft deicing, and particularly relates to a full-automatic low-energy-consumption deicing control system which comprises a power supply, a first mechanical temperature control switch, a humidity sensor, a detection controller, a second mechanical temperature control switch and a carbon heating unit, wherein the power supply is installed in the front end of a machine body; the power supply is connected with the first mechanical temperature control switch, the detector-controller, the second mechanical temperature control switch and the carbon heating unit in series by virtue of wires, the detector-controller is also connected with a humidity dew condensation sensor, and the signal output end of the humidity dew condensation sensor is connected with the detector-controller; the system is accurately started and closed without manual operation, so that the deicing efficiency is improved, the heating time is accurately controlled, and the energy consumption is reduced.

Description

Full-automatic low-energy-consumption deicing control system

Technical Field

The invention belongs to the technical field of aircraft deicing, and particularly relates to a full-automatic low-energy-consumption deicing control system.

Background

The problem that a surface layer is easy to freeze in the flying process of high-altitude aircrafts such as airplanes and unmanned aerial vehicles is solved. In the process, the starting of the deicing system depends on the visual field of a pilot, if the deicing system is frozen at a position which cannot be observed by the pilot, the deicing is difficult to carry out, and the closing of the deicing system after the deicing is finished also depends on the observation of the pilot, so that the waste is easily caused by long-time heating.

Disclosure of Invention

In order to solve the problems in the prior art, the invention provides a full-automatic low-energy-consumption deicing control system, which can realize full-automatic electrothermal deicing and starts to work when the temperature and the humidity reach the condition of icing; when the heating is carried out to a certain temperature, the icing condition is not met, and the power supply of the system is automatically cut off.

The invention adopts the specific technical scheme that: full-automatic low energy consumption deicing control system, the key is: the device comprises a power supply, a first mechanical temperature control switch, a humidity dew sensor, a detector-controller, a second mechanical temperature control switch and a carbon heating unit, wherein the carbon heating unit is arranged in a wing, a tail wing and an airspeed tube; the power with the help of the electric wire with first mechanical temperature detect switch, examine accuse ware, second machinery temperature detect switch and carbon heating unit series connection, the accuse ware of examining still be connected with humidity dewfall sensor, humidity dewfall sensor signal output part with examine the controller and be connected.

The carbon heating units are symmetrically arranged in the wings, the empennage and the airspeed tube.

The invention has the beneficial effects that: when the temperature reaches the icing condition, the first mechanical temperature control switch is closed, the second mechanical temperature control switch is closed, the power-on system of the detection and control device starts to work, the detection and control device firstly detects the dew point of the current air by virtue of the humidity dew condensation sensor after being powered on to work, if no dew condensation exists, no current is output to the carbon heating unit, and otherwise, the heating is started when the current temperature and the current humidity are both icing environments; when the whole system is heated to a certain temperature and ice formation conditions are not met, the second temperature control switch is disconnected, and the second temperature control switch is automatically disconnected from the power supply to be electrified; the system is accurately started and closed without manual operation, so that the deicing efficiency is improved, the heating time is accurately controlled, the energy consumption is reduced, and accidents of aircrafts such as unmanned aerial vehicles and airplanes due to icing are avoided.

The aircraft deicing system has the advantages that the design structure is simple, the number of parts is small, safety and reliability are realized, the aircraft has high heat dissipation speed due to high airflow during flying, namely, energy consumption is high during deicing, the system has zero current in the whole system when acting on a non-icing environment through the mechanical temperature control 1, and the heating unit can automatically save energy through the series connection of the mechanical temperature control.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is an enlarged view of a portion of the present invention;

in the attached drawing, the device comprises a pitot tube 1, a pitot tube 2, a power supply 3, a first mechanical temperature control switch 4, a humidity dew sensor 5, a detection controller 6, a second mechanical temperature control switch 7 and a carbon heating unit.

Detailed Description

The invention will be further described with reference to the following drawings and specific embodiments:

full-automatic low energy consumption deicing control system, the key is: the device comprises a power supply 2, a first mechanical temperature control switch 3, a humidity dew sensor 4, a detection controller 5, a second mechanical temperature control switch 6 and a carbon heating unit 7, wherein the carbon heating unit 7 is arranged in a wing, a tail wing and a pitot tube 1; power 2 with the help of the electric wire with first mechanical temperature detect switch 3, examine controller 5, second machinery temperature detect switch 6 and carbon heating element 7 series connection, the detector 5 still be connected with

humidity dewfall sensor

4, 4 signal output parts of humidity dewfall sensor are connected with examining controller 5.

The carbon heating units 7 are symmetrically arranged in the wings, the empennage and the airspeed head 1.

In the embodiment shown in fig. 1, the first mechanical temperature-controlled switch 3 controls whether to energize the detector 5, the current is 1A, and the temperature switch parameters are: below 2 ℃ of conduction, second machinery temperature detect switch 6 establishes ties in heating power supply unit, is heavy current temperature detect switch, and the electric current sets up according to heating element's electric current size, and the temperature switch parameter is: the temperature is closed at the temperature of more than 2 ℃, the carbon heating unit is made of carbon heating carbon fiber ultra-light high-strength conductive materials, the carbon heating carbon fiber ultra-light high-strength conductive materials are preset and synthesized in the wing skin during the forming of composite materials in the aircraft manufacturing process, and the detector 5 is formed by connecting parts such as a humidity condensation detection module and a relay trigger module.

In the flight process of the aircraft, when the temperature of a flight environment is lower than 2 ℃, the first mechanical temperature control switch 3 receives a temperature signal and is closed, the second mechanical temperature control switch 6 is closed, the detector and controller 5 is powered on to start working, the humidity dew condensation sensor 4 connected with the detector and controller 5 after being powered on starts detecting whether the humidity of the current flight environment has an icing condition, when the dew condensation sensor has dew condensation, the humidity dew condensation sensor 4 outputs a signal to the detector and controller 5, the detector and controller 5 controls a circuit connected with the carbon heating unit 7 to be powered on, the second mechanical temperature control switch 6 is in a closed state, and the carbon heating units 7 at wings and airspeed tubes work; the second mechanical temperature control switch 6 receives an external temperature signal, when the temperature of the monitoring point of the second mechanical temperature control switch 6 is higher than 2 ℃, ice melts, the second mechanical temperature control switch 6 is automatically powered off, and the effect of automatic power on and automatic power off is achieved.

As shown in fig. 1, the carbon heating units 7 are symmetrically arranged in the wing, the empennage and the pitot tube 1.

Carbon heating unit 7 is rationally set up on the aircraft, makes aircraft such as unmanned aerial vehicle, aircraft can both heat the deicing everywhere.

Claims

1. Full-automatic low energy consumption deicing control system, its characterized in that: the device comprises a power supply (2), a first mechanical temperature control switch (3), a humidity dew sensor (4), a detection controller (5), a second mechanical temperature control switch (6) and a carbon heating unit (7), wherein the carbon heating unit (7) is arranged in a wing, a tail wing and an airspeed tube (1); power (2) with the help of the electric wire with first mechanical temperature detect switch (3), examine controller (5), second machinery temperature detect switch (6) and carbon heating unit (7) series connection, examine controller (5) still be connected with humidity dewfall sensor (4), humidity dewfall sensor (4) signal output part is connected with examining controller (5).

2. The fully automatic, low energy consumption deicing control system of claim 1, wherein: the carbon heating units (7) are symmetrically arranged in the wings, the empennage and the airspeed head (1).