CN109665107A - A kind of leading edge of a wing ice prevention structure based on engine thermal lubricating oil - Google Patents

A kind of leading edge of a wing ice prevention structure based on engine thermal lubricating oil Download PDF

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Publication number
CN109665107A
CN109665107A CN201811479379.3A CN201811479379A CN109665107A CN 109665107 A CN109665107 A CN 109665107A CN 201811479379 A CN201811479379 A CN 201811479379A CN 109665107 A CN109665107 A CN 109665107A
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CN
China
Prior art keywords
leading edge
wing
temperature
engine
lubricating oil
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201811479379.3A
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Chinese (zh)
Inventor
王伟
徐鸣
徐一鸣
刘洋
叶志飞
杨天旗
王东
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AVIC Chengdu Aircraft Design and Research Institute
Original Assignee
AVIC Chengdu Aircraft Design and Research Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AVIC Chengdu Aircraft Design and Research Institute filed Critical AVIC Chengdu Aircraft Design and Research Institute
Priority to CN201811479379.3A priority Critical patent/CN109665107A/en
Publication of CN109665107A publication Critical patent/CN109665107A/en
Pending legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/02De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
    • B64D15/06Liquid application

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The present invention relates to a kind of leading edge of a wing ice prevention structures based on engine shell body heat source, including the leading edge of a wing, engine, heat exchanger, liquid pump, sensor and controller;There is cavity inside the leading edge of a wing, the cavity, liquid pump and heat exchanger are fluid circuit by pipeline series connection;Heat exchanger is fixed on motor body, by the heat exchange of motor body to the fluid media (medium) in fluid circuit;The sensor is used to detect the temperature of the fluid media (medium) and/or motor body, and temperature information is sent to controller, and the controller controls liquid pump according to temperature information and works.The present invention carries out anti-icing, guarantee Flight Safety to the leading edge of a wing;Reduce the burden of aircraft heat management system;It does not need from engine bleed air, so that engine real work efficiency is improved.

Description

A kind of leading edge of a wing ice prevention structure based on engine thermal lubricating oil
Technical field
The invention belongs to aircraft and anti-icing fields, anti-icing more particularly to a kind of leading edge of a wing based on engine thermal lubricating oil Structure.
Background technique
Aircraft wing icing is the major issue for jeopardizing Flight Safety.Wing is the most important lift generating unit of aircraft Point, when aircraft flies under ice-formation condition, once wing icing, the shape of wing changes, and airplane ascensional force may occur hold The variation received, jeopardizes flight safety.Therefore, it is the major issue for guaranteeing Flight Safety that aircraft wing is anti-icing.
Current ice control is generally divided into three classes.The first is using engine bleed as heat source, from engine pressure Mechanism of qi bleed is anti-icing using high-temperature gas to the leading edge of a wing, but this kind of method can reduce the working efficiency of engine;Second It is that anti-icing mixture is smeared in the position easily to freeze, but this method higher cost, it is difficult to engineer application;The third is to utilize Electric energy heating is anti-icing to realize, but is constrained to the factors such as electrical energy devices efficiency and electromagnetic interference, and this method is normally only used for sky The widgets such as fast pipe it is anti-icing.
Summary of the invention
The purpose of the present invention: how the method how to carry out aircraft anti-icing design using motor oil guides engine High temperature lubricating oil to wing heat it is anti-icing.
Technical solution of the present invention
A kind of leading edge of a wing ice prevention structure based on engine shell body heat source, including the leading edge of a wing, engine, lubricating oil are provided Circuit, heat exchanger, liquid pump, sensor and controller;There are cavity, the cavity, liquid pump and Re Jiao inside the leading edge of a wing Parallel operation is fluid circuit by pipeline series connection;The lubricating oil cabinet in lubricating oil circuit is fixed on motor body, motor body pair Lubricating oil in lubricating oil circuit is thermally conductive, lubricating oil circuit and the equal interchange heat exchanger of fluid circuit, and lubricating oil will be warm in a heat exchanger The fluid media (medium) that can be conducted in fluid circuit;The sensor for detect the temperature of fluid medium, oil temperature and/or The temperature of motor body, and temperature information is sent to controller, the controller controls liquid pump according to temperature information and works.
Further, the temperature of the sensor detection fluid media (medium).
Further, the temperature of the sensor detection motor body.
Further, the temperature of the sensor detection oil temperature.
Further, the controller is flight control system or engine control system.
Beneficial effects of the present invention: 1. pairs of leading edges of a wing carry out anti-icing, guarantee Flight Safety;2. reducing aircraft heat pipe The burden of reason system;3. not needing from engine bleed air, so that engine real work efficiency is improved.
Detailed description of the invention
Fig. 1 is the principle of the present invention figure;
Fig. 2 is wing profile figure;
Wherein: the 1- leading edge of a wing, 2- engine, 3- oil tank, 4- heat exchanger, 5- liquid pump, 6- controller.
Specific embodiment
Embodiment of the present invention is specifically explained below.
A kind of leading edge of a wing ice prevention structure based on engine shell body heat source, including the leading edge of a wing 1, engine 2, cunning are provided Oil return line, heat exchanger 4, liquid pump 5, sensor and controller 6;Have cavity inside the leading edge of a wing, the cavity, liquid pump and Heat exchanger is fluid circuit by pipeline series connection;3 body of oil tank in lubricating oil circuit is fixed on motor body, engine shell Body is thermally conductive to the lubricating oil in lubricating oil circuit, lubricating oil circuit and the equal interchange heat exchanger of fluid circuit, and lubricating oil in a heat exchanger By thermal energy conduction to the fluid media (medium) in fluid circuit;The sensor is for detecting the temperature of fluid medium, oil temperature And/or the temperature of motor body, and temperature information is sent to controller, the controller controls liquid pump according to temperature information Work.
Further, the temperature of the sensor detection fluid media (medium).
Further, the temperature of the sensor detection motor body.
Further, the temperature of the sensor detection oil temperature.
Further, the controller is flight control system or engine control system.

Claims (5)

1. a kind of leading edge of a wing ice prevention structure based on engine shell body heat source, including the leading edge of a wing, engine, lubricating oil circuit, Heat exchanger, liquid pump, sensor and controller;There is cavity inside the leading edge of a wing, the cavity, liquid pump and heat exchanger are logical Crossing pipeline series connection is fluid circuit;The lubricating oil cabinet in lubricating oil circuit is fixed on motor body, and motor body returns lubricating oil Lubricating oil in road is thermally conductive, lubricating oil circuit and the equal interchange heat exchanger of fluid circuit, and in a heat exchanger lubricating oil by thermal energy conduction To the fluid media (medium) in fluid circuit;The sensor is for detecting the temperature of fluid medium, oil temperature and/or engine The temperature of shell, and temperature information is sent to controller, the controller controls liquid pump according to temperature information and works.
2. a kind of leading edge of a wing ice prevention structure based on engine shell body heat source as described in claim 1, it is characterised in that: institute State the temperature of sensor detection fluid media (medium).
3. a kind of leading edge of a wing ice prevention structure based on engine shell body heat source as described in claim 1, it is characterised in that: institute State the temperature of sensor detection motor body.
4. a kind of leading edge of a wing ice prevention structure based on engine shell body heat source as described in claim 1, it is characterised in that: institute State the temperature of sensor detection oil temperature.
5. a kind of leading edge of a wing ice prevention structure based on engine shell body heat source as described in claim 1, it is characterised in that: institute Stating controller is flight control system or engine control system.
CN201811479379.3A 2018-12-05 2018-12-05 A kind of leading edge of a wing ice prevention structure based on engine thermal lubricating oil Pending CN109665107A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201811479379.3A CN109665107A (en) 2018-12-05 2018-12-05 A kind of leading edge of a wing ice prevention structure based on engine thermal lubricating oil

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201811479379.3A CN109665107A (en) 2018-12-05 2018-12-05 A kind of leading edge of a wing ice prevention structure based on engine thermal lubricating oil

Publications (1)

Publication Number Publication Date
CN109665107A true CN109665107A (en) 2019-04-23

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CN201811479379.3A Pending CN109665107A (en) 2018-12-05 2018-12-05 A kind of leading edge of a wing ice prevention structure based on engine thermal lubricating oil

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CN (1) CN109665107A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110641711A (en) * 2019-10-30 2020-01-03 西安京东天鸿科技有限公司 Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle
CN110963045A (en) * 2019-12-24 2020-04-07 南京航空航天大学 Automatic anti-icing and deicing device for fuel wing of aircraft and working method of automatic anti-icing and deicing device
CN112896498A (en) * 2021-03-12 2021-06-04 核工业二八0研究所 Unmanned aerial vehicle gamma energy spectrum measurement system
CN115367125A (en) * 2022-09-08 2022-11-22 北京微焓科技有限公司 Hybrid thermal management system and aircraft

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06206593A (en) * 1993-01-08 1994-07-26 Mitsubishi Heavy Ind Ltd Anti-icing and de-icing device for aircraft
CN202557799U (en) * 2011-12-27 2012-11-28 东南大学 Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device
WO2013140306A1 (en) * 2012-03-19 2013-09-26 Intertechnique Wing ice protection system based on a fuel cell system
EP3032045A1 (en) * 2014-12-08 2016-06-15 United Technologies Corporation Gas turbine engine nacelle anti-icing system
CN107985607A (en) * 2017-11-02 2018-05-04 成都飞机工业(集团)有限责任公司 A kind of unmanned plane icing protective device

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06206593A (en) * 1993-01-08 1994-07-26 Mitsubishi Heavy Ind Ltd Anti-icing and de-icing device for aircraft
CN202557799U (en) * 2011-12-27 2012-11-28 东南大学 Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device
WO2013140306A1 (en) * 2012-03-19 2013-09-26 Intertechnique Wing ice protection system based on a fuel cell system
EP3032045A1 (en) * 2014-12-08 2016-06-15 United Technologies Corporation Gas turbine engine nacelle anti-icing system
CN107985607A (en) * 2017-11-02 2018-05-04 成都飞机工业(集团)有限责任公司 A kind of unmanned plane icing protective device

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110641711A (en) * 2019-10-30 2020-01-03 西安京东天鸿科技有限公司 Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle
CN110641711B (en) * 2019-10-30 2021-08-03 西安京东天鸿科技有限公司 Unmanned aerial vehicle deicing system, deicing method and unmanned aerial vehicle
CN110963045A (en) * 2019-12-24 2020-04-07 南京航空航天大学 Automatic anti-icing and deicing device for fuel wing of aircraft and working method of automatic anti-icing and deicing device
CN110963045B (en) * 2019-12-24 2024-02-13 南京航空航天大学 Automatic deicing device for fuel wing of quoted aircraft and working method of automatic deicing device
CN112896498A (en) * 2021-03-12 2021-06-04 核工业二八0研究所 Unmanned aerial vehicle gamma energy spectrum measurement system
CN112896498B (en) * 2021-03-12 2022-11-22 核工业二八0研究所 Unmanned aerial vehicle gamma energy spectrum measurement system
CN115367125A (en) * 2022-09-08 2022-11-22 北京微焓科技有限公司 Hybrid thermal management system and aircraft

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Application publication date: 20190423