CN107269398A - Aircraft drop load starting is independently crosslinked control method - Google Patents
Aircraft drop load starting is independently crosslinked control method Download PDFInfo
- Publication number
- CN107269398A CN107269398A CN201710499380.1A CN201710499380A CN107269398A CN 107269398 A CN107269398 A CN 107269398A CN 201710499380 A CN201710499380 A CN 201710499380A CN 107269398 A CN107269398 A CN 107269398A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- engine
- load
- starting
- signal
- 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.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/85—Starting
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
The present invention relates to aircraft power design field, specifically provide a kind of aircraft drop load starting and be independently crosslinked control method, by airplane load, acc power is started to control with the autonomous crosslinking of engine oil regulation, increase Plain/plateau hydraulic pressure unloading conversion and control function, offloading functions are started to be crosslinked with wheel carrying signal, only when wheel carrying is effective, and Plain/plateau switch " plateau " effectively when, it is left, right start signal could drive the actuating of relay in starting Unloading Control box, unloader signal is exported to hydraulic system, when engine speed reaches setting speed or stream time reaches setting time, starter is disengaged automatically, recover hydraulic system normal pressure, hydraulic system realizes autonomous Loading Control ability, engine accelerates to engine idling rating by the combustion chamber ignition and rotor inertia of itself, complete altitude environment ground start function.
Description
Technical field
The present invention relates to aircraft power design field, more particularly to aircraft drop load starting is independently crosslinked controlling party
Method.
Background technology
The equipped gas turbine starter of air-combat maneuver Force system is when altitude environment works because air pressure, density subtract
Small, starter rotating ratio Plain is high, starts bicycle and motorcycle rotating speed to be automatically increased with the increase of airport height, starter itself is defeated
Go out power attenuation, the ability reduction with forwarding engine start.Gas turbine starter, engine cranking temperature are with airport height
Increase easily there is fuel-rich combustion and increase, if aircraft starting system does not make any adjustment, it is difficult to realize aircraft power fill
Put the ability of system plateau ground start.If not doing any work to engine and starter, it will there is problems with：
1st, aircraft starting control does not adjust, starter rotating speed delivery temperature increase, it is possible in fuel regulator most
Big combustion gas rotating speed delivery temperature limiter plays restriction effect, and gas turbine starter is cut automatically to stop aborting the start；
2nd, the power of starter output is low, causes the band sent out greatly to be walked around fast low, and fire speed when the big initiation of influence is dynamic influences
Starting process dump power is set up, and causes engine speed to set up the slow, starting time long, even result in engine start interrupt or
Automatic stopping；
If the 3, engine starts fuel feeding and do not adjusted, engine operating parameter and performance data change, and such as play dynamic temperature
Degree is higher, causes rich oil stall in starting process, the starting time is long, ultimately results in starting failure.
The content of the invention
To overcome at least one defect that above-mentioned prior art is present, the invention provides a kind of aircraft drop load starting certainly
Main crosslinking control method, for ground start of the aircraft under altitude environment, comprises the following steps：
Step one, aircraft fuel delivery is reduced, makes engine exhaust temperature less than setting safety value；
Step 2, when aircraft is in altitude environment, judges whether airplane wheel carrying is effective, starts if effectively and starts
Enabling signal is sent to Unloading Control module by machine, engine, and Unloading Control module is received after enabling signal and sent out to load system
Send unloader signal, load system receives after unloader signal and to unload hydraulic system；
Step 3, detects the continuous firing time and disengages rotating speed, when stream time reaches setting in real time
Between value or disengage rotating speed when reaching setting speed value, Unloading Control module record stream time value or disengage tachometer value, and
To load system send Load Signal, load system receive after Load Signal by hydraulic system recover to unloading before state；
It is preferred that, aircraft is provided with Plain/plateau change-over switch, by controlling Plain/plateau change-over switch to switch aircraft
The signal of local environment.
It is preferred that, it is also associated with setting in automatic starting device, automatic starting device between engine and Unloading Control module
Have relay and clock switch, for increase starter band forwarding motivation stream time with and improve starter with starting
The disengagement rotating speed of machine.
The aircraft drop load starting that the present invention is provided independently is crosslinked control method, has the advantages that：
1st, control technology is independently crosslinked using such a aircraft drop load starting, compared to the state for less making any adjustment, war
Bucket machine starts success rate under altitude environment and has an obvious increase, and engine and starter start exhaust temperature have it is bright
Aobvious reduction, is conducive to protecting the body construction of engine and starter；
2nd, effective to shorten the ground start time, in starting process, hydraulic system can have with the change of engine condition
There is the function of independently loading；
3rd, with System Fault Tolerance function, will not because of pilot due to maloperation cause hydraulic system can not normal work,
The flight safety of aircraft can be ensured, the use requirement that altitude environment is got off the plane is met.
Brief description of the drawings
Fig. 1 is the schematic diagram that aircraft drop load starting is independently crosslinked control method；
Fig. 2 is using the starting time contrast curve before and after the present invention；
Fig. 3 is using the starting delivery temperature contrast curve before and after the present invention.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.
It should be noted that：The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to for explaining this hair
It is bright, and be not considered as limiting the invention.In the accompanying drawings, same or similar label represents same or like from beginning to end
Element or element with same or like function.Described embodiment is a part of embodiment of the invention, rather than entirely
The embodiment in portion, in the case where not conflicting, the feature in embodiment and embodiment in the application can be mutually combined.It is based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under the premise of creative work is not made
Embodiment, belongs to the scope of protection of the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply meaning
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention guarantor
Protect the limitation of scope.
Control method is independently crosslinked the invention provides a kind of aircraft drop load starting, is not making what is adjusted greatly to engine
In the case of can effectively improve starting capability of the aircraft under altitude environment, ensure that aircraft floor starts success rate and flight peace
Entirely, so that reducing aircraft moves into the big technical risk of plateau ground start difficulty.The control method comprises the following steps：
A, increase aircraft floor start equipment compartment increase after hydraulic pressure Unloading Control function, aircraft and start Unloading Control box, increase
Increase former starting hydraulic pressure Unloading Control circuit, engine high-altitude aerodrome is realized in aircraft starting duty when reduction engine is started
Ground start hydraulic pressure is unloaded and pressure restoring control function；
B, left main cabin increase " Plain/plateau " hydraulic pressure unloading change-over switch, transition altitude is to preset height,
Airport i.e. below setting height, the airport that change-over switch is got to more than Plain shelves, setting height starts hydraulic pressure Unloading Control
Box is transferred to plateau shelves；
C, start offloading functions and left wheel carrying signal and be crosslinked, only when revolver carrying is effective, and Plain/plateau switch
When " plateau " is effective, left and right start signal could drive the actuating of relay in starting Unloading Control box, be unloaded to hydraulic system output
Information carrying number；
D, the adjustment for completing engine and gas turbine starter plateau starting fuel feeding, and starter plateau starting power
Adjustment, improves starting process work matching and starts success rate；
Increase relay and clock switch in e, automatic starting device, improve starter band forwarding motivation running hours
Between, the tach signal output of increase integrated full electric propulsion improves the disengagement rotating speed of starter and engine, and increase band turns the time,
Improve engine and start band and walk around speed, so that improving engine starts success rate；
F, the signal output that hydraulic pressure is unloaded into recovery and engine high pressure rotor speed are interlocked, when engine high pressure turn
It is automatic to disconnect hydraulic pump unloading magnetic valve when rotor speed reaches the rotating speed, the pressure spring of hydraulic pump is controlled by solenoid valve
Initial position is returned to, recovers hydraulic system normal pressure；
G, adjustment starter power output, the screw of the maximum oil condition of adjustment starter, increase starter power output；
H, optimization engine oil rule, outer stubborn main pump screw, which is reduced, starts leading portion fuel feeding, and outer stubborn main pump adjusting screw is excellent
Change and start back segment fuel feeding.
It is the concrete operation step of aircraft below, as shown in Figure 1：
When a, plateau (height above sea level be in preset height above airport), hydraulic pressure Unloading Control box is by Plain/plateau
Change-over switch gets to " plateau shelves " state, and cockpit hydraulic recovery is switched in position down；
B, aircraft cockpit engine oil door handle are placed in slow train position, press engine " starting " button, and engine is started
Control system carries out starting control by plateau logic；
C, when engine speed reaches setting speed or stream time reaches setting time, be defined by arriving first, rise
Motivation is disengaged automatically, and hydraulic pump unloading magnetic valve disconnects automatically, controls the pressure spring of hydraulic pump to return to just by solenoid valve
Beginning position, recover hydraulic system normal pressure, hydraulic system realizes autonomous Loading Control ability；
D, engine accelerate to engine idling rating by the combustion chamber ignition and rotor inertia of itself, complete plateau ring
Condition face start-up function；
When e, Plain (height above sea level be in preset airport below height), hydraulic pressure Unloading Control box is by Plain/plateau
Change-over switch gets to " Plain shelves " state, and cockpit hydraulic recovery switch presses Plain in upward position, engine start control system
State logic carries out starting control.
30~40 seconds starting times were shortened compared to state compared with before-improvement by the technological invention, engine exhaust temperature is reduced
30~50 DEG C, it disclosure satisfy that altitude environment is got off the plane the requirement of ground start, is improved engines ground and is started success rate.
The foregoing is only a specific embodiment of the invention, but protection scope of the present invention is not limited thereto, any
Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (3)
1. a kind of aircraft drop load starting is independently crosslinked control method, for ground start of the aircraft under altitude environment, it is special
Levy and be, comprise the following steps：
Step one, aircraft fuel delivery is reduced, makes engine exhaust temperature less than setting safety value；
Step 2, when aircraft is in altitude environment, judges whether airplane wheel carrying is effective, and engine is started if effectively,
Enabling signal is sent to Unloading Control module by engine, and Unloading Control module is received to send to load system after enabling signal and unloaded
Information carrying number, load system receives after unloader signal and to unload hydraulic system；
Step 3, detects the continuous firing time and disengages rotating speed, when stream time reaches setting time value in real time
Or rotating speed is disengaged when reaching setting speed value, Unloading Control module record stream time value or tachometer value is disengaged, and to negative
Loading system send Load Signal, load system receive after Load Signal by hydraulic system recover to unloading before state.
2. aircraft drop load starting according to claim 1 is independently crosslinked control method, it is characterised in that aircraft is provided with
Plain/plateau change-over switch, by controlling Plain/plateau change-over switch to switch the signal of aircraft local environment.
3. aircraft according to claim 1 drop load starting is independently crosslinked control method, it is characterised in that engine and unload
It is also associated with automatic starting device, automatic starting device being provided with relay and clock switch between load control module, for increasing
Plus the stream time of starter band forwarding motivation with and improve the disengagement rotating speed of starter and engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710499380.1A CN107269398B (en) | 2017-06-27 | 2017-06-27 | Aircraft drop load starting is independently crosslinked control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710499380.1A CN107269398B (en) | 2017-06-27 | 2017-06-27 | Aircraft drop load starting is independently crosslinked control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107269398A true CN107269398A (en) | 2017-10-20 |
| CN107269398B CN107269398B (en) | 2019-03-08 |
Family
ID=60068703
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710499380.1A Active CN107269398B (en) | 2017-06-27 | 2017-06-27 | Aircraft drop load starting is independently crosslinked control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107269398B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520234A (en) * | 2020-04-30 | 2020-08-11 | 中国直升机设计研究所 | Starting device and method for helicopter engine in plateau environment |
| CN111997761A (en) * | 2020-08-25 | 2020-11-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and system for improving plateau starting success rate of aeroengine |
| CN115875138A (en) * | 2023-02-06 | 2023-03-31 | 中国航发沈阳发动机研究所 | Method and device for controlling aviation gas turbine engine in different domains and different time |
| CN118327784A (en) * | 2024-04-08 | 2024-07-12 | 北京中航智科技有限公司 | A ground starting control method for aircraft engine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3672007B2 (en) * | 1999-01-19 | 2005-07-13 | 株式会社アイチコーポレーション | Boom automatic storage device for aerial work platforms |
| US20100300117A1 (en) * | 2005-05-19 | 2010-12-02 | Djamal Moulebhar | Aircraft with disengageable auxiliary power unit components |
| CN106777821A (en) * | 2017-01-23 | 2017-05-31 | 中国航发沈阳发动机研究所 | A kind of aviation turbofan engine plateau starting igniting oil mass computational methods |
-
2017
- 2017-06-27 CN CN201710499380.1A patent/CN107269398B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3672007B2 (en) * | 1999-01-19 | 2005-07-13 | 株式会社アイチコーポレーション | Boom automatic storage device for aerial work platforms |
| US20100300117A1 (en) * | 2005-05-19 | 2010-12-02 | Djamal Moulebhar | Aircraft with disengageable auxiliary power unit components |
| CN106777821A (en) * | 2017-01-23 | 2017-05-31 | 中国航发沈阳发动机研究所 | A kind of aviation turbofan engine plateau starting igniting oil mass computational methods |
Non-Patent Citations (1)
| Title |
|---|
| 李凡玉等: "改善发动机高原地面起动性能的实验研究", 《空军工程大学学报（自然科学版）》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111520234A (en) * | 2020-04-30 | 2020-08-11 | 中国直升机设计研究所 | Starting device and method for helicopter engine in plateau environment |
| CN111997761A (en) * | 2020-08-25 | 2020-11-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and system for improving plateau starting success rate of aeroengine |
| CN111997761B (en) * | 2020-08-25 | 2022-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Method and system for improving plateau starting success rate of aeroengine |
| CN115875138A (en) * | 2023-02-06 | 2023-03-31 | 中国航发沈阳发动机研究所 | Method and device for controlling aviation gas turbine engine in different domains and different time |
| CN118327784A (en) * | 2024-04-08 | 2024-07-12 | 北京中航智科技有限公司 | A ground starting control method for aircraft engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107269398B (en) | 2019-03-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3556659B1 (en) | Hybrid propulsion engines for aircraft | |
| EP2915749B1 (en) | System and method for operating a multi-engine aircraft in an auxiliary power unit mode | |
| KR101576640B1 (en) | A rotary wing aircraft having two main engines together with a less powerful secondary engine, and a corresponding method | |
| EP3770398B1 (en) | Hybrid gas turbine engine starting control | |
| CN107269398B (en) | Aircraft drop load starting is independently crosslinked control method | |
| RU2593317C2 (en) | Method of optimising specific consumption of twin-engine helicopter and a twin-engine structure with control system to this end | |
| US5343778A (en) | Multifunction secondary power system | |
| US20170226934A1 (en) | Hybridisation of the compressors of a turbojet | |
| CN111734537B (en) | Fuel control system and control method | |
| EP3736422B1 (en) | Systems and methods for transferring mechanical power in a turbine engine | |
| JP2017122452A (en) | Aircraft engine and associated method for driving fan with low pressure shaft during taxiing | |
| CN110155344B (en) | Hybrid unmanned helicopter energy control system and helicopter with the same | |
| CN106460660B (en) | Turboaxle motor, equipped with the Twin Engined Helicopter of this turboaxle motor, and the method for the super idling of zero energy for optimizing this Twin Engined Helicopter | |
| CN105593493A (en) | Method for optimising the specific consumption of a twin helicopter | |
| US11391203B2 (en) | Asymmetric propulsion system with heat recovery | |
| US12060834B2 (en) | Hybrid electric idle and braking for an aircraft | |
| US11840350B2 (en) | Method and system for controlling idle speed and drawing of power generated by an aircraft engine | |
| CN113597508A (en) | Power output from LP body and system for removing debris | |
| US9849997B2 (en) | Method for synchronising the engines of an airplane with dual intermediate state | |
| EP4174300A1 (en) | Hybrid electric single engine descent restart | |
| JP7511536B2 (en) | Aircraft Propulsion Systems | |
| US11867131B2 (en) | Hybrid electric single engine descent mode activation logic | |
| CN114651112A (en) | Method for quickly stopping rotor wing after helicopter landing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information | ||
| CB03 | Change of inventor or designer information |
Inventor after: Ma Song Inventor after: Bian Jing Inventor after: Chen Xuefang Inventor after: Lian Yongjiu Inventor after: Yu Xin Inventor before: Ma Song Inventor before: Chen Xuefang Inventor before: Wang Guanghao Inventor before: Huang Jinzhi Inventor before: Liu Fangxing |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |