Anti-icing system of aircraft, aircraft including anti-icing system, program for controlling anti-icing system, and method for controlling anti-icing system

Patent metadata

Field	Value
Publication number	US-11292601-B2
Application number	US-201715456782-A
Country	US
Kind code	B2
Filing date	Mar 13, 2017
Priority date	Mar 24, 2016
Publication date	Apr 5, 2022
Grant date	Apr 5, 2022

Abstract

An anti-icing system at least includes: a precooler that exchanges heat between bleed air and outside air; and an anti-icing unit that receives the bleed air passed through the precooler. A bleed air flow rate adjusting section that adjusts a flow rate of the bleed air supplied to the anti-icing unit adjusts the flow rate of the bleed air to suppress pressure of the bleed air to a pressure upper limit or lower by using relationship r1 and relationship r2. The relationship r1 is a relationship between an altitude and a pressure upper limit of the bleed air. The relationship r2 is a relationship between the pressure upper limit and outside air temperature at which the temperature of the bleed air reaches allowable temperature of ducts and other members through which the bleed air flows. The relationship r2 is provided based on the altitude.

First claim

What is claimed is:

1. An anti-icing system of an aircraft, the anti-icing system preventing icing on the aircraft with use of bleed air heat-exchanged with outside air, the anti-icing system comprising:
a heat exchanger that is configured to exchange heat between the bleed air and the outside air;
a supply destination that is configured to receive the bleed air passed through the heat exchanger; and
a control section that is configured to adjust a flow rate of the bleed air passed through the heat exchanger and subsequently supplied to the supply destination, wherein
the control section includes a bleed air flow rate adjusting section that is configured to adjust the flow rate of the bleed air passed through the heat exchanger and subsequently supplied to the supply destination,
the bleed air flow rate adjusting section uses a first relationship and a second relationship, the first relationship being a relationship between an altitude and a pressure upper limit that is an upper limit of pressure of the bleed air, the second relationship being a relationship between outside air temperature at which temperature of the bleed air reaches allowable temperature of a member through which the bleed air flows and a pressure upper limit that is an upper limit of pressure of the bleed air, the second relationship being provided based on the altitude,
when outside air temperature is lower than outside air temperature at an intersection of the first relationship and the second relationship, the bleed air flow rate adjusting section is configured to adjust the flow rate of the bleed air while suppressing the pressure of the bleed air to the pressure upper limit or lower of the first relationship, and
when the outside air temperature is higher than the outside air temperature at the intersection of the first relationship and the second relationship, the bleed air flow rate adjusting section is configured to adjust the flow rate of the bleed air while suppressing the pressure of the bleed air to the pressure upper limit or lower of the second relationship.

2. The anti-icing system of the aircraft according to claim 1 , wherein
the bleed air flow rate adjusting section uses map data provided with the pressure upper limit, the pressure upper limit being a function of an altitude and outside air temperature, and
the pressure upper limit of the map data is determined based on the first relationship and the second relationship.

3. An anti-icing system of an aircraft, the anti-icing system preventing icing on the aircraft with use of bleed air heat-exchanged with outside air, the anti-icing system comprising:
a heat exchanger that is configured to exchange heat between the bleed air and the outside air;
a supply destination that is configured to receive the bleed air passed through the heat exchanger; and
a control section that is configured to adjust a flow rate of the bleed air passed through the heat exchanger and subsequently supplied to the supply destination, wherein
the control section includes a bleed air flow rate adjusting section that is configured to adjust the flow rate of the bleed air passed through the heat exchanger and subsequently supplied to the supply destination,
the bleed air flow rate adjusting section uses a first relationship and a temperature threshold, the first relationship being a relationship between an altitude and a pressure upper limit that is an upper limit of pressure of the bleed air, the temperature threshold being set lower by a predetermined value than allowable temperature of a member through which the bleed air flows,
when temperature of the bleed air is lower than the temperature threshold, the bleed air flow rate adjusting section is configured to adjust the flow rate of the bleed air to suppress the pressure of the bleed air to the pressure upper limit or lower of the first relationship, and
when the temperature of the bleed air is higher than the temperature threshold, the bleed air flow rate adjusting section is configured to adjust the flow rate of the bleed air to suppress the temperature of the bleed air to the allowable temperature or lower.

4. The anti-icing system of the aircraft according to claim 1 , wherein
an icing condition and an operating condition are assumed, the icing condition including an altitude and outside air temperature, and the operating condition encompassing the icing condition and being a range of an altitude and outside air temperature at which the aircraft is flyable, and
the member through which the bleed air flows is configured to be used such that a temperature of the member is maintained at the allowable temperature or lower under the operating condition.

5. The anti-icing system of the aircraft according to claim 3 , wherein
an icing condition and an operating condition are assumed, the icing condition including an altitude and outside air temperature, and the operating condition encompassing the icing condition and being a range of an altitude and outside air temperature at which the aircraft is flyable, and
the member through which the bleed air flows configured to be used such that a temperature of the member is maintained at the allowable temperature or lower under the operating condition.

6. An aircraft comprising the anti-icing system according to claim 1 .

7. An aircraft comprising the anti-icing system according to claim 3 .

8. A non-transitory computer readable storage medium storing a computer program having a bleed air flow rate adjusting module for controlling an anti-icing system of an aircraft to prevent icing on the aircraft with bleed air heat-exchanged with outside air by a heat exchanger, wherein execution of the computer program by a computer causes the computer to adjust a flow rate of the bleed air passed through the heat exchanger and subsequently supplied to a supply destination, wherein:
the bleed air flow rate adjusting section uses a first relationship and a second relationship the first relationship being a relationship between an altitude and a pressure upper limit that is an upper limit of pressure of the bleed air, the second relationship being a relationship between outside air temperature at which temperature of the bleed air reaches allowable temperature of a member through which the bleed air flows and a pressure upper limit that is an upper limit of pressure of the bleed air, the second relationship being provided based on the altitude,
when outside air temperature is lower than outside air temperature at an intersection of the first relationship and the second relationship, the bleed air flow rate adjusting section is configured to cause the computer to adjust the flow rate of the bleed air to suppress the pressure of the bleed air to the pressure upper limit or lower of the first relationship, and
when the outside air temperature is higher than the outside air temperature at the intersection of the first relationship and the second relationship, the bleed air flow rate adjusting section is configured to cause the computer to adjust the flow rate of the bleed air to suppress the pressure of the bleed air to the pressure upper limit or lower of the second relationship.

9. A non-transitory computer readable storage medium storing a computer program, the computer program having a bleed air flow rate adjusting module for controlling an anti-icing system of an aircraft to prevent icing on the aircraft with bleed air heat-exchanged with outside air by a heat exchanger, wherein execution of the computer program by a computer causes the computer to a flow rate of the bleed air passed through the heat exchanger and subsequently supplied to a supply destination, wherein
the bleed air flow rate adjusting section uses a first relationship

Assignees

• Mitsubishi Aircraft Corp

Inventors

• Uefuji Yoichi
• Morishita Masatoshi
• Ishida Toshiyuki
• Ichikawa Gento

Classifications

• B64D2013/0618

  with arrangements for reducing or managing bleed air, using another air source, e.g. ram air · CPC title

• B64D15/04 Primary

  Hot gas application · CPC title

• B64D2013/0607

  providing hot air or liquid for deicing aircraft parts, e.g. aerodynamic surfaces or windows · CPC title

• Y02T50/50

  On board measures aiming to increase energy efficiency · CPC title

• B64D15/20

  Means for detecting icing or initiating de-icing · CPC title