阅读说明：本技术 一种电动飞机防除冰装置及方法 (Electric airplane deicing and preventing device and method ) 是由 林剑 于 2019-10-12 设计创作，主要内容包括：本申请提供一种电动飞机防除冰装置,所述装置包括油盒1、燃烧装置2、传输管路4以及预设位置5,其中:油盒1为存储燃烧介质的装置,油盒1与燃烧装置2连接,用于向燃烧装置2提供燃烧介质；燃烧装置2通过传输管路4与电动飞机防除冰预设位置5连接,以便燃烧装置2产生的热量通过传输管路4传输至电动飞机防除冰预设位置5实现防除冰。(The application provides an electric airplane deicing and anti-icing device, which comprises an oil box 1, a combustion device 2, a transmission pipeline 4 and a preset position 5, wherein the oil box 1 is used for storing combustion media, and the oil box 1 is connected with the combustion device 2 and used for providing the combustion media for the combustion device 2; the combustion device 2 is connected with the electric airplane deicing prevention and protection preset position 5 through the transmission pipeline 4, so that heat generated by the combustion device 2 is transmitted to the electric airplane deicing prevention and protection preset position 5 through the transmission pipeline 4 to realize deicing prevention.)

1. The utility model provides an electric aircraft deicing device that prevents which characterized in that, the device includes oil box (1), burner (2), transmission line (4) and preset position (5), wherein:

the oil box (1) is a device for storing combustion media, and the oil box (1) is connected with the combustion device (2) and is used for providing the combustion media for the combustion device (2);

the combustion device (2) is connected with the preset position (5) through the transmission pipeline (4), so that heat generated by the combustion device (2) is transmitted to the electric flying preset position (5) through the transmission pipeline (4) to achieve ice prevention and removal.

2. An electrically powered aircraft de-icing apparatus as defined in claim 1 wherein: the device also comprises a power device (3), one end of the power device (3) is connected with the combustion device (2), and the other end of the power device is connected with the transmission pipeline (4).

3. An electrically powered aircraft de-icing apparatus as defined in claim 2 wherein: the power device (3) comprises a fan and a pump.

4. An electrically powered aircraft de-icing apparatus as defined in claim 1 wherein: burner (2) are connected with electric aircraft preset position (5) through transmission line (4), specifically include:

an outlet of the combustion device (2) is connected with an interface at one end of a transmission pipeline (4), a transmission part of the transmission pipeline (4) is connected with a preset position (5) of the electric airplane, and an interface at the other end of the transmission pipeline (4) is connected with an inlet of the combustion device (2);

or the outlet of the combustion device (2) is connected with an interface at one end of the transmission pipeline (4), and the transmission part and the interface at the other end of the transmission pipeline (4) are connected with the preset position (5) of the electric airplane.

5. An electrically powered aircraft de-icing apparatus as defined in claim 1 wherein: the electric airplane preset position (5) comprises airplane wings, a tail wing and windshield glass.

6. An electric aircraft anti-icing method, characterized in that the method comprises:

the method comprises the steps that a combustion medium is prestored on the electric airplane, and heat is generated by combusting the combustion medium;

and transmitting the heat to a preset position (5) of the electric airplane through a transmission pipeline (4) on the electric airplane to realize ice prevention and removal.

7. The method according to claim 6, wherein the transferring of the heat to the electric aircraft preset position (5) through a transfer pipe (4) on the electric aircraft comprises:

and transmitting the heat to a preset position (5) of the electric airplane through a transmission pipeline (4) on the electric airplane by using a power device (3).

8. The method according to claim 6, characterized in that the power means (3) comprises a fan and a pump.

Technical Field

The invention relates to the field of electric airplane deicing design, in particular to a combustion-based electric airplane deicing and ice preventing device.

Background

The traditional airplane deicing and anti-icing system mainly comprises a mechanical deicing and anti-icing system and an electric heating deicing and anti-icing system, and the energy source of the traditional airplane deicing and anti-icing system is a turbine or a piston engine. If the engine is an electric engine, a conventional mechanical deicing system cannot be used. And if an electrothermal type ice preventing and removing system is adopted, a large burden is caused on a battery of the electric airplane, so that the performance of the airplane is reduced sharply.

Disclosure of Invention

The problems to be solved by the invention are as follows: provided is an airplane anti-icing device based on combustion, which meets the anti-icing requirements of an electric airplane and does not affect the performance of the electric airplane.

In a first aspect, the present application provides an electric aircraft deicing device that includes oil box 1, burner 2, transmission line 4 and preset position 5, wherein:

the oil box 1 is a device for storing combustion media, and the oil box 1 is connected with the combustion device 2 and used for providing the combustion media for the combustion device 2;

the combustion device 2 is connected with the electric airplane anti-icing preset position 5 through the transmission pipeline 4, so that heat generated by the combustion device 2 is transmitted to the electric airplane anti-icing preset position 5 through the transmission pipeline 4 to achieve anti-icing.

Optionally, the device further comprises a power device 3, wherein one end of the power device 3 is connected with the combustion device 2, and the other end of the power device 3 is connected with the transmission pipeline 4.

Optionally, the power means 3 comprises a fan and a pump.

Optionally, the combustion apparatus 2 is connected with the preset position 5 of the electric aircraft through the transmission pipeline 4, and specifically includes:

an outlet of the combustion device 2 is connected with an interface at one end of a transmission pipeline 4, a transmission part of the transmission pipeline 4 is connected with a preset position 5 of the electric airplane, and an interface at the other end of the transmission pipeline 4 is connected with an inlet of the combustion device 2;

or the outlet of the combustion device 2 is connected with one end interface of the transmission pipeline 4, and the transmission part and the other end interface of the transmission pipeline 4 are connected with the preset position 5 of the electric airplane.

Optionally, the electric airplane preset position 5 comprises airplane wings, a tail wing and a windshield.

In a second aspect, the present application provides a method of deicing electric aircraft, the method comprising:

the method comprises the steps that a combustion medium is prestored on the electric airplane, and heat is generated by combusting the combustion medium;

and transmitting the heat to a preset position 5 of the electric airplane through a transmission pipeline on the electric airplane to realize ice prevention and removal.

Optionally, the transmitting the heat to the preset position 5 of the electric aircraft through the transmission pipeline on the electric aircraft specifically includes:

transmitting the heat to a preset position 5 of the electric airplane through a transmission pipeline on the electric airplane by using a power device

Optionally, the power device 3 comprises a fan and a pump.

The invention has the advantages that: the energy obtained by combustion is used for preventing and removing ice, the energy conversion efficiency is far higher than that of an electric ice preventing and removing mode, and the performance of the electric airplane can be effectively improved.

Drawings

FIG. 1 is a schematic diagram of the present invention;

wherein: 1-oil box 2-combustion device 3-power device 4-transmission pipeline 5-preset position.

Detailed Description

The present invention is described in further detail below. The invention relates to an anti-icing and deicing device, which comprises an oil box 1, a combustion device 2, a power device 3, a transmission pipeline 4 and a preset position 5. The oil box 1 is a container that can be used to contain a combustion medium, but also a structure of the aircraft itself. The combustion apparatus 2 is an apparatus that generates heat by burning a combustion medium, and can transfer the generated heat to a fluid medium. The power device 3 can be in different power forms according to different fluid media, and can be a fan or a pump or other forms. The transfer line 4 is used for transferring any medium capable of transferring heat, and can be of a circulating structure or a unidirectional non-circulating structure. The predetermined location 5 is a location where the aircraft requires heat for ice protection, and may be an aircraft wing or empennage or windshield or other location.

In one embodiment of the present invention, the oil box 1 is welded from stainless steel for supplying combustion oil to the combustion apparatus 2. The combustion device 2 burns the combustion oil provided by the oil box 1 and transfers heat to the air in the transmission pipeline 4, and the power device 3 sends the air to the preset position 5 for the fan. The predetermined location 5 is the leading edge of the wing, and the heat of the air is used for preventing ice by heat exchange. The air passing behind the wing is directly discharged to the atmosphere and is not circulated.