CN106892122B - The control method of cockpit temperature control system under a kind of aircraft engine transition status - Google Patents
The control method of cockpit temperature control system under a kind of aircraft engine transition status Download PDFInfo
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- CN106892122B CN106892122B CN201510969037.XA CN201510969037A CN106892122B CN 106892122 B CN106892122 B CN 106892122B CN 201510969037 A CN201510969037 A CN 201510969037A CN 106892122 B CN106892122 B CN 106892122B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
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- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention belongs to Aircraft Cabin Temperature control technology field, it is related to a kind of control method of cockpit temperature control system under aircraft engine transition status.When engine is converted from idling rating to normal condition, cold air duct regulating valve is opened at full speed, and temperature control valve is closed with certain speed, after cold air duct regulating valve standard-sized sheet, temperature control valve are closed, adjusts cabin temperature with pid algorithm；When engine is converted from normal condition to idling rating, the received control amount of cold air duct regulating valve is 2-4 times that normal pid algorithm calculates output, the received control amount of temperature control valve is 2-5 times that normal pid algorithm calculates output, cold air duct regulating valve close entirely and temperature control valve standard-sized sheet after, or it after cabin air supply line temperature reaches its target value, is adjusted with pid algorithm.Cabin temperature controls overshoot, cabin air supply pipeline overtemperatute when solving engine condition switching, enhances the stability of system control.
Description
Technical field
The invention belongs to Aircraft Cabin Temperature control technology field, it is related to cockpit temperature under a kind of aircraft engine transition status
The control method of control system.
Background technique
With the development of domestic and international engine, engine performance is greatly improved, start function moment complete from
The switching of slow train and normal condition causes ring control bleed air system outlet temperature transient changing, is since ring control cabin temperature controls
System is big inertial control system, to guarantee that system stability, each execution unit adjustment speed are relatively slow.However engine condition
System is adjusted according to normal condition when conversion, and system, which responds, must not catch up with the variation of engine condition, is bound to cause and is
System control overshoot, supply air line overtemperature or even system temperature control are unstable.Solving the problems, such as this both at home and abroad mostly is in engine
When state is converted, by fan pumping and ring control air-conditioning system gas mixing, the method can bring system weight to increase, noise is big
The problem of.
Summary of the invention
Present invention solves the technical problem that: providing one kind prevents engine condition conversion from causing cabin air supply temperature unstable
Control method.
The technical solution of the present invention is as follows: under a kind of aircraft engine transition status cockpit temperature control system control method,
It is characterized in that the method are as follows:
When engine is converted from idling rating to normal condition, cold air duct regulating valve is opened at full speed, temperature control valve with
Certain speed is closed, and after cold air duct regulating valve standard-sized sheet, temperature control valve are closed, adjusts cabin temperature with pid algorithm；
When engine is converted from normal condition to idling rating, the received control amount of cold air duct regulating valve is normal PID
Algorithm calculates 2-4 times of output, and the received control amount of temperature control valve is 2-5 times that normal pid algorithm calculates output, cold air duct
Regulating valve close entirely and temperature control valve standard-sized sheet after or after cabin air supply line temperature reaches its target value, carried out with pid algorithm
It adjusts.
As a kind of improvement of the technical program, when detecting engine speed ξ < λ1, bleed air system outlet temperature TPNU
< κ1DEG C, then engine is in idling rating, and engine enters idling rating after a certain period of time, if detecting bleed outlet temperature
Continuous t seconds of change rate is greater than σ, then engine is converted from idling rating to normal condition.
As a kind of improvement of the technical program, when detecting engine speed ξ > λ2, bleed air system outlet temperature TPNU
> κ2DEG C, then engine is in normal condition, and engine enters normal condition after a certain period of time, if detecting bleed outlet temperature
Continuous t seconds of change rate is less than-μ, then engine is converted from normal condition to idling rating.
As a kind of improvement of the technical program, bleed outlet temperature change rate is calculated according to the following formula,
Delt_T=[TPNU(k)-TPNU(k-1)]/T
Delt_T is bleed outlet temperature change rate, TPNUIt (k) is current time bleed outlet temperature, TPNUIt (k-1) is one
Bleed outlet temperature before a control period, T are that system controls the period.
The invention has the benefit that the present invention proposes that a kind of improved control method, the method switch in launch state
When, by control temperature control valve and the aperture of cold air duct regulating valve, to change environmental control system refrigeration, heated condition, with more
The variation of bleed outlet air condition is mended to affect.Cabin temperature controls overshoot, cabin air supply when solving engine condition switching
Pipeline overtemperatute enhances the stability of system control.
Specific embodiment
The technical program is described in further detail below with reference to embodiment.
It is a kind of to prevent engine condition from converting the control method for causing cabin air supply temperature unstable, it is described to prevent engine
State conversion causes the control method of cabin air supply overtemperature to be based on Aircraft Cabin Temperature Control System Design.Temperature control valve control
Cabin air supply temperature, cold air duct regulating valve control control compressor delivery temperature, this method are become by detection bleed outlet temperature
Change, engine speed variation, whether judgement starts to switch between idling rating and fast car state.To optimize temperature control
Valve, cold air duct regulating valve control algolithm guarantee cabin air supply not overtemperature when ensuring cabin temperature normal control.
The operating procedure of the method is as follows:
Step 1:
Engine speed ξ is obtained from engine system；
Bleed air system outlet temperature T is acquired by temperature sensorPNU；
Cabin air supply line temperature T is acquired by temperature sensorSPP；
Compressor delivery temperature T is acquired by temperature sensorCOMP；
Step 2:
Bleed outlet temperature change rate is calculated, formula is as follows:
Delt_T=[TPNU(k)-TPNU(k-1)]/T
Delt_T is bleed outlet temperature change rate, TPNUIt (k) is current time bleed outlet temperature, TPNUIt (k-1) is one
Bleed outlet temperature before a control period, T are that system controls the period.
Step 3:
Judge engine condition switching judging.
2.1 ought detect engine speed ξ < λ1And bleed air system outlet temperature TPNU< κ1DEG C, then judge engine at this time
In idling rating；When engine enters idling rating after a certain period of time, the time is true according to the adjustment speed of temperature control valve
Fixed, generally 2 to 8 minutes, if detecting, continuous t seconds of bleed outlet temperature change rate is greater than σ, judged engine condition by slow
Car state is converted to normal condition.λ1To start idling rating revolving speed critical value.κ1Start idling rating critical speed is corresponding to draw
Gas system outlet temperature, σ be engine idling rating to normal condition when bleed outlet temperature change rate decision threshold, time t
It is determined according to engine condition switch speed.
2.2 ought detect engine speed ξ > λ2And bleed air system outlet temperature TPNU>κ2DEG C, then judge engine at this time
In normal condition；It is generally 1 to 5 minutes after a certain period of time when engine enters normal condition, which controls according to temperature
The adjustment speed of valve determines, if detect continuous t second of bleed outlet temperature change rate less than-μ, then judge engine condition by
Normal condition is converted to idling rating.λ2To mobilize normal condition revolving speed critical value, κ2To start normal condition critical speed corresponding
Bleed air system outlet temperature.- μ be engine idling rating to normal condition when bleed outlet temperature change rate decision threshold,
Time t is determined according to engine condition switch speed.
Step 4:
When engine condition is converted from idling rating to normal condition:
Cold air duct regulating valve is opened at full speed, and temperature control valve is with speed υ closing.When cold air duct regulating valve standard-sized sheet and temperature control
After valve processed is closed, cold air duct regulating valve and temperature control valve are adjusted according to normal pid algorithm.
Since cold air duct control valve opening causes compressor delivery temperature response slower, temperature control valve aperture causes to calm the anger
Machine outlet temperature responds more as early as possible, so speed υ cannot be too fast, it is necessary to assure compressor delivery temperature not overtemperature, speed υ can be with
It is obtained by test.
Step 5:
When engine condition is converted from normal condition to idling rating:
It is that normal pid algorithm calculates 2 times exported, system control that system controller, which is exported to the control amount of cold air duct regulating valve,
It is that normal pid algorithm calculates 3 times exported that device processed, which is exported to the control amount of temperature control valve,.When cold air duct regulating valve Quan Guan and temperature
After degree control valve standard-sized sheet or after cabin air supply line temperature reaches its target value, cold air duct regulating valve and temperature control valve according to
Normal pid algorithm is adjusted.
Claims (4)
1. the control method of cockpit temperature control system under a kind of aircraft engine transition status, it is characterised in that the method are as follows:
When engine is converted from idling rating to normal condition, cold air duct regulating valve is opened at full speed, and temperature control valve is with certain
Speed is closed, and after cold air duct regulating valve standard-sized sheet, temperature control valve are closed, adjusts cabin temperature with pid algorithm；
When engine is converted from normal condition to idling rating, the received control amount of cold air duct regulating valve is normal pid algorithm
2-4 times of output is calculated, the received control amount of temperature control valve is 2-5 times that normal pid algorithm calculates output, and cold air duct is adjusted
Valve close entirely and temperature control valve standard-sized sheet after or after cabin air supply line temperature reaches its target value, adjusted with pid algorithm
Section.
2. the control method of cockpit temperature control system under a kind of aircraft engine transition status according to claim 1, special
Sign are as follows: when detecting engine speed ξ < λ1, bleed air system outlet temperature TPNU<κ1DEG C, then engine is in idling rating, starts
Machine enters idling rating after a certain period of time, if detecting, continuous t seconds of bleed outlet temperature change rate is greater than σ, and engine is by slow
Car state is converted to normal condition, λ1To start idling rating revolving speed critical value.κ1Start idling rating critical speed is corresponding to draw
Gas system outlet temperature, σ be engine idling rating to normal condition when bleed outlet temperature change rate decision threshold.
3. the control method of cockpit temperature control system under a kind of aircraft engine transition status according to claim 1, special
Sign are as follows: when detecting engine speed ξ > λ2, bleed air system outlet temperature TPNU>κ2DEG C, then engine is in normal condition, starts
Machine enters normal condition after a certain period of time, if detecting, continuous t seconds of bleed outlet temperature change rate is less than-μ, and engine is by just
Normal state is converted to idling rating, λ2To mobilize normal condition revolving speed critical value, κ2To start normal condition critical speed corresponding
Bleed air system outlet temperature ,-μ be engine idling rating to normal condition when bleed outlet temperature change rate decision threshold.
4. the control method of cockpit temperature control system under a kind of aircraft engine transition status according to claim 2 or 3,
Feature are as follows: bleed outlet temperature change rate is calculated according to the following formula,
Delt_T=[TPNU(k)-TPNU(k-1)]/T
Delt_T is bleed outlet temperature change rate, TPNUIt (k) is current time bleed outlet temperature, TPNUIt (k-1) is a control
Bleed outlet temperature before period processed, T are that system controls the period.
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| CN114152446B (en) * | 2020-09-08 | 2023-07-25 | 中国航发商用航空发动机有限责任公司 | Bleed air control system and method |
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| JP3915263B2 (en) * | 1998-08-20 | 2007-05-16 | 株式会社島津製作所 | Air conditioner for aircraft |
| US20140109603A1 (en) * | 2011-12-29 | 2014-04-24 | Embraer S.A. | Integrated environmental control systems and methods for controlling environmental temperature of an enclosed space |
| US9676484B2 (en) * | 2013-03-14 | 2017-06-13 | Rolls-Royce North American Technologies, Inc. | Adaptive trans-critical carbon dioxide cooling systems |
| CN203528824U (en) * | 2013-10-11 | 2014-04-09 | 周坦胜 | Flight deck temperature adjusting system based on PID cascade control |
| CN105059552B (en) * | 2015-08-19 | 2017-03-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of Aircraft Cabin Temperature control method based on three-wheel high pressure water separation regenerative air cycle cooling system system |
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