CN105416601B - A kind of helicopter engine parameter display system - Google Patents

A kind of helicopter engine parameter display system Download PDF

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Publication number
CN105416601B
CN105416601B CN201510762131.8A CN201510762131A CN105416601B CN 105416601 B CN105416601 B CN 105416601B CN 201510762131 A CN201510762131 A CN 201510762131A CN 105416601 B CN105416601 B CN 105416601B
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itt
idle
esi
oeic
oeil
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CN105416601A (en
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李昊晗
罗道国
檀婧杰
罗和顺
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Harbin Aircraft Industry Group Co Ltd
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Harbin Aircraft Industry Group Co Ltd
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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
    • B64D43/00—Arrangements or adaptations of instruments

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combined Controls Of Internal Combustion Engines (AREA)

Abstract

The invention belongs to helicopter design field, and in particular to a kind of helicopter engine parameter display system and method, for improving man-machine efficacy.Existing helicopter uses traditional engine parameter interface display, and display interface is single, and the warning information of display is independently of display system, and parameters display device is completely independent, once situations such as transmission signal interruption occur, does not back up display function.The present invention is on the basis of the configuration of cockpit display system is made full use of, it is contemplated that on the premise of security of system, and restructuring optimization has been carried out to engine parameter, has mitigated driving difficulty, while making the display interface of engine parameter become apparent from, succinctly.

Description

A kind of helicopter engine parameter display system
Technical field
The invention belongs to helicopter design field, and in particular to a kind of helicopter engine parameter display system and method, For improving man-machine efficacy.
Background technology
Existing helicopter uses traditional engine parameter interface display, and display interface is single, and the warning information of display is only Display system is stood on, parameters display device is completely independent, once situations such as transmission signal interruption occur, does not back up display Function.
The content of the invention
The technical problems to be solved by the invention are：The present invention on the basis of the configuration of cockpit display system is made full use of, On the premise of in view of security of system, restructuring optimization is carried out to engine parameter, has mitigated driving difficulty, while making to start The display interface of machine parameter becomes apparent from, succinctly.
The technical scheme is that：
Abbreviation is explained
ESI engine conditions are indicated
ESIIDLEESI limitations under IDLE state
ESIMCPESI limitations under MCP states
ESIIDLEESI limitations under IDLE state
ESITOPESI limitations under TOP states
ESIAEOESI limitations under AEO states
ESIOEICESI limitations under OEIC states
ESIOEIHESI limitations under OEIH states
ESIOEILESI limitations under OEIL states
MCP continous maximum ratings
NG engine gas secondary speeds
NGIDLENG limitations under IDLE state
NGMCPNG limitations under MCP states
NGTOPNG limitations under TOP states
NGAEONG limitations under AEO states
NGIDLE@OEING limitations under OEI state idling ratings
NGOEICNG limitations under OEIC states
NGOEIHNG limitations under OEIH states
NF engine free secondary speeds
NR rotor rotating speeds
IDLE engine idling ratings
Slow train power under IDLE@OEI OEI states
OEI single-shots do not work
OEIC OEI are maximum continuous
OEIH OEI height limitations
OEIL OEI lower limits
ITT engine interior turbine temperatures
ITTIDLEITT limitations under IDLE state
ITTMCPITT limitations under MCP states
ITTTOPITT limitations under TOP states
ITTAEOITT limitations under AEO states
ITTIDLE@OEIITT limitations under OEI idling ratings
ITTOEICITT limitations under OEIC states
ITTOEILITT limitations under OEIL states
ITTOEIHITT limitations under OEIH states
TOP take-off powers
TQ engine torques
TQIDLETQ limitations under IDLE state
TQMCPTQ limitations under MCP states
TQAEOTQ limitations under AEO states
TQOEICTQ limitations under OEIC states
NGOEILNG limitations under OEIL states
TQOEIHTQ limitations under OEIH states
TQIDLE@OEITQ limitations under OEI state idling ratings
TQTOPTQ limitations under TOP states
TQTOPTorque value under maximum take-off power
ISA normal atmospheric pressures
System is constituted
The helicopter parameter display system of the present invention mainly includes engine sensor, electricity tune, computing device and display dress Put.
The engine sensor detection comes from the parameter information of engine；The electricity, which is adjusted, receives engine sensor Information and the parameter information and warning information for being converted into engine；Computing device is exclusively used in the calculating of ESI parameters；Display device is used In the parameter of display engine, include TQ, ITT, NG parameter of ESI parameters, engine, and engine warning information.
The computing device is sentenced by carrying out dimensionless calculating to current TQ, and being integrated according to the engine parameter detected Break and calculate and obtain ESI parameters, wherein, the current TQ ÷ TQ of TQ=TOP×100。
If the electricity adjusts output single-engine run information or any one engine NG rotating speed to be less than 50%, you can to confirm Helicopter is in single-engine operation state；Otherwise it is assumed that helicopter is in double hair working conditions.
During double hair working conditions
If NG when NG, ITT and TQ are no more than slow trainIDLE、ITTIDLEAnd TQIDLE, i.e. NG≤NGIDLEAnd ITT≤ ITTIDLEAnd TQ≤TQIDLE%, then：
RE=MIN { (TQIDLE-TQ)/TQIDLE, (NGIDLE-NG)/NGIDLE, (ITTIDLE-ITT)/ITTIDLE,
ESI=(1-RE) * ESIIDLE；
If NGMCP>NG>NGIDLEOr ITTMCP>ITT>ITTIDLEOr TQTOP>TQ>TQIDLE, and NG<NGTOPAnd ITT<ITTTOP And TQ<TQTOP, then：
RE=MIN { (TQMCP-TQ)/(TQMCP-TQIDLE), (NGMCP-NG)/(NGMCP-NGIDLE),
(ITTMCP-ITT)/(ITTMCP-ITTIDLE),
ESI=(1-RE) * ESIMCP+RE*ESIIDLE；
If NGTOP>NG>NGMCPOr ITTTOP>ITT>ITTMCPOr TQTOP>TQ>TQMCP, and NG<NGTOPAnd ITT<ITTTOPAnd TQ<TQTOP, then：
RE=MIN { (TQTOP-TQ)/(TQTOP-TQMCP), (NGTOP-NG)/(NGTOP-NGMCP),
(ITTTOP-ITT)/(ITTTOP-ITTMCP),
ESI=(1-RE) * ESITOP+RE*ESIMCP；
If NG>NGTOPOr ITT>ITTTOPOr TQ>TQTOP, then：
RE=MIN { (TQAEO-TQ)/(TQAEO-TQTOP), (NGAEO-NG)/(NGAEO-NGTOP),
(ITTAEO-ITT)/(ITTAEO-ITTTOP),
ESI=(1-RE) * ESIAEO+RE*ESITOP；
During single-engine operation state
If NG≤NGIDLE@OEIAnd ITT≤ITTIDLE@OEIAnd TQ≤TQIDLE@OEI, then：
RE=MIN { (TQIDLE@OEI-TQ)/TQIDLE@OEI, (NGIDLE@OEI-NG/NGIDLE@OEI,
(ITTIDLE@OEI- ITT)/ITT },
ESI=(1-RE) * ESIIDLE；
If NGOEIC>NG>NGIDLE@OEIOr ITTOEIC>ITT>ITTIDLE@OEIOr TQOEIC>TQ>TQIDLE@OEI；And NG<NGOEIC And ITT<ITTOEICAnd TQ<TQOEIC, then：
RE=MIN { (TQOEIC-TQ)/(TQOEIC-TQIDLE@OEI), (NGOEIC-NG)/(NGOEIC-NGIDLE@OEI),
(ITTOEIC-ITT)/(ITTOEIC-ITTIDLE@OEI),
ESI=(1-RE) * ESIOEIC+RE*ESIIDLE；
If NGOEIL>NG>NGOEICOr ITTOEIL>ITT>ITTOEICOr TQOEIL>TQ>TQOEIC；And NG<NGOEILAnd ITT< ITTOEILAnd TQ<TQOEIL, then：
RE=MIN { (TQOEIL-TQ)/(TQOEIL-TQOEIC), (NGOEIL-NG)/(NGOEIL-NGOEIC),
(ITTOEIL-ITT)/(ITTOEIL-ITTOEIL),
ESI=(1-RE) * ESIOEIL+RE*ESIOEIC；
If NG>NGOEILOr ITT>ITTOEILOr TQ>TQOEIL, then：
RE=MIN { (TQOEIH-TQ)/(TQOEIH-TQOEIL), (NGOEIH-NG)/(NGOEIH-NGOEIL),
(ITTOEIH-ITT)/(ITTOEIL-ITTOEIC)}
ESI=(1-RE) * ESIOEIH+RE*ESIOEIL。
The method shown according to above-mentioned helicopter engine parameter display system to helicopter engine parameter, in institute The page stated in display device is made up of three parts：Comprehensive parameters viewing area, rotating speed viewing area and engine parameter viewing area, Wherein
In comprehensive parameters viewing area
ESI parameters are indicated using 270 ° without graduation apparatus ring, and normal operation region is represented with green area in table ring, are used Amber/yellow area represents warning region, and warning zone, and the width of green area are represented with red area<It is amber/yellow The width in color region<The width of red area；Red area and the boundary of amber/yellow area are represented most by red radial line Big takeoff condition, the border of red area represents maximum instantaneous state by red symbols；In the table ring with solid and hollow Pointer represents the ESI parameters of left and right engine respectively；The parameter type and parameter of Left Hand Engine are shown in table ring lower left Value, the parameter type and parameter value of right engine are shown in table ring lower right；
In rotating speed viewing area
Intermediate region carries out scale by column pointer bar and shows that the column pointer bar has in upper and lower ends, from the inside to the outside Have symmetrical green area, amber/yellow area and red area, respectively represent normal operation region, warn region and Warning zone, and the width of green area<The width of amber/yellow area<The width of red area；Left and right NF parameters point Not Yong the spear pointer of column pointer bar arranged on left and right sides indicate that rotor rotating speed NR referred to using V-arrangement pointer on column pointer bar Show；Show the parameter type and parameter value of Left Hand Engine, rotor and right engine successively below rotating speed viewing area；
In engine parameter viewing area
Indicate alarm and represent engine parameter without graduation apparatus ring by 120 ° or other angles.
Inactive area is represented by grey on the table ring of comprehensive parameters viewing area.
Pointer in comprehensive parameters viewing area can be same color according to the colour switching of signified table ring region.
Red symbols in comprehensive parameters viewing area on table ring areShape.
When OEIH, OEIL, AEO30 state occurs in left/right engine, respectively in the table ring both sides of comprehensive parameters viewing area Shown with red glyphs, and the arranged on left and right sides above table ring uses the remaining time of red display OEIH states respectively, uses amber Color/yellow shows the remaining time of OEIL states.
The both sides of table ring may also display left and right engine pointer, and Left Hand Engine pointer in comprehensive parameters viewing area It is solid, right engine pointer is hollow.
Inactive area in rotating speed viewing area is shown using grey column-shape strip.
Red fire alarm " FIRE " letter of left and right enging cabin can be shown respectively in the cylindrical scale both sides of rotating speed viewing area Breath, when there is red " FIRE " information, " FIRE " inverse is shown, after driver certifying fault message, becomes normal bright display；Also Green " START ", " IDLE " information of left and right engine can be shown.
The present invention is applicable the helicopter of at least one engine, is readily applicable to other types aircraft, described herein ESI (Engine State indication) parameter be used for providing the power of engine and indicate, ESI parameters and engine Gas turbine rotating speed NG, engine exhaust temperature ITT, tri- parameter associations of engine torque TQ.That is ESI parameters be according to According to certain control rule, the dimensionless group calculated according to NG, ITT, TQ, the parameter closest to engine only with limiting Parameter be associated.
Not substituted NG, ITT, TQ instruction shown for engine parameter of ESI parameters in the present invention, but with NG, ITT, TQ indicate and deposit, indicated by an independent viewing area with table-like+numeric form shows NG, ITT, TQ respectively Parameter, three parameters can transmit real engine parameter to driver and indicate that these parameters are in different indication ranges The different color of display.
The free turbine rotating speed of left and right engine and the rotor rotating speed of helicopter are integrated in a column and shown by the present invention On device, under normal circumstances, free turbine rotating speed and the rotor rotating speed of left and right engine indicate it is consistent, can really show Show engine and the current working condition of helicopter.
The present invention engine warning information content is integrated in display area, can truly show engine OEIH, Remaining time that OEIL is used, and in the different periods, the work shape of engine can be shown by the display of continuous state State.
The beneficial effects of the invention are as follows：Introduced by ESI parameters, can effectively reduce the burden of driver.By to not With the determination of viewing area table ring thickness, the attention of driver can be caused enough when parameter enters warning, warning zone. The form that OEIH, OEIL are shown, can more drive the display that intuitively driver's transmission OEI limits remaining time.
Brief description of the drawings
Fig. 1 is ESI calculation flow charts of the present invention；
Fig. 2 is TQ, ITT, NG limitation exemplary plot of the double hair-like states in ISA sea level；
Fig. 3 is TQ, ITT, NG limitation exemplary plot of ISA sea level single-engine run；
Fig. 4 is comprehensive parameters display interface of the present invention；
Fig. 5 is rotating speed display interface of the present invention；
Fig. 6 is inventive engine parameter display interface；
Fig. 7 is the implementation result figure of inventive engine parameter display system.
Embodiment
Engine parameter is shown and is calculated and be shown using the cockpit display system of helicopter.Helicopter capsule display system System is made up of three pieces of displays, the left right PFD of PFD+MFD+.ESI parameters indicate to be shown in PFD lower left quarter, hair with three pin rotating speeds Motivation parameter is shown in MFD middle and lower part.ESI parameters are calculated by left and right PFD and MFD.
Left and right PFD and MFD gathers the bus message and sensor information for coming from electricity tune respectively, under normal circumstances, is used for The information that ESI calculating display and engine parameter are shown comes from electricity and adjusts the bus message exported, when the bus for coming from electricity tune When information fails or electricity adjusts the sensor failure for detecting electricity tune collection, the information of system automatic data collection engine sensor output Calculating for ESI parameters is shown.
ESI is calculated
ESI calculation process
Before flow chart starts, TQ need to be carried out to calculate without most guiding principle, computational methods：Current TQ value ÷ TQTOP×100。
ESI is calculated by Fig. 1 flows.
1. helicopter is double return be single-shot criterion
Helicopter single-shot criterion has two：
Electric operation dispatching system exports single-engine run information；
Any one engine NG rotating speed is less than 50%.
As long as meeting one of above-mentioned criterion, you can to confirm that helicopter is in single-engine operation state.
2. pair hair operation interval criterion
All three parameters (NG/ITT/TQ) are no more than slow train.
Criterion：NG≤NGIDLE% and ITT≤ITTIDLEDEG C and TQ≤TQIDLE%.
The maximum of three parameters is between slow train and MCP.
Criterion：NGMCP>NG>NGIDLE% or ITTMCP>ITT>ITTIDLEDEG C or TQTOP>TQ>TQIDLE%；
And NG<NGTOP&ITT<ITTTOP&TQ<TQTOP。
The maximum of three parameters (NG/ITT/TQ) is between maximum continuous and maximum is taken off.
Criterion：NGTOP>NG>NGMCPOr ITTTOP>ITT>ITTMCPOr TQTOP>TQ>TQMCP；
And NG<NGTOP&ITT<ITTTOP&TQ<TQTOP。
The maximum of three parameters (NG/ITT/TQ) is taken off more than maximum；
Criterion：NG>NGTOPOr ITT>ITTTOPOr TQ>TQTOP。
3. residing Interval Criteria during single-engine operation
All three parameters (NG/ITT/TQ) are no more than slow train
Criterion NG≤NGIDLE@OEI%＆ITT≤ITTIDLE@OEI℃&TQ≤TQIDLE@OEI%.
The maximum of three parameters is between slow train and MCP.
Criterion：NGOEIC>NG>NGIDLE@OEI% or ITTOEIC>ITT>ITTIDLE@OEIOr TQOEIC>TQ>TQIDLE@OEI%；
And NG<NGOEIC&ITT<ITTOEIC&TQ<TQOEIC。
The maximum of three parameters is between OEIC and OEIL.
Criterion：NGOEIL>NG>NGOEICOr ITTOEIL>ITT>ITTOEICOr TQOEIL>TQ>TQOEIC；
And NG<NGOEIL&ITT<ITTOEIL&TQ<TQOEIL。
The maximum of three parameters (NG/ITT/TQ) is more than OEIL.
Criterion：NG>NGOEILOr ITT>ITTOEILOr TQ>TQOEIL。
4.RE parameters are calculated
A parameter RE is set, RE values are calculated by company shown in flow chart.
5.ESI parameters are calculated
ESI parameters are calculated by flow chart calculation formula.
6. in the case of helicopter training
In single-shot training pattern, NG and ITT are not involved in ESI calculating, and ESI calculating is carried out using only training state TQ.
7. the implication of calculation formula
Compare the relative distance in respective bins with limitation point, nearest is most harsh limitation.Then existed according to parameter Relative position in interval, interpolation calculation is carried out to ESI.
The page is shown
The page indicated for engine parameter is made up of three parts：Comprehensive parameters viewing area, rotating speed viewing area and hair Motivation parameter display area
1. there are following features comprehensive parameters viewing area：
ESI parameters are indicated using 270 ° without graduation apparatus ring；
Table ring green area represents normal operation region, is represented with thin green arc (12)；Amber (or yellow) region table Show warning region, thick amber arc or yellow arc (2) represent in；Red area represents warning zone, with the thick thick arc (3) of red Represent；Inactive area (5) shows grey, and maximum takeoff condition shows red solid line, and maximum instantaneous status display is red (4)；
Represent left and right hair parameter respectively with solid, hollow pointer, pointer enters different restricted areas, become different Color；
Arranged on left and right sides below ESI table rings shows the title (7) of the specific engine parameter related to ESI respectively With numerical value (8)；
When OEIH, OEIL, AEO30 (11) state occurs in left or right engine, shown respectively in ESI table rings both sides, Arranged on left and right sides above table ring shows red OEIH, the remaining time (1) of amber (or yellow) OEIL states respectively；
OEIH states show that, when OEIH is less than 5 seconds using remaining time, numerical value is red using red glyphs+red value Chromatic flicker is shown, when being less than 0 second remaining time, shows the red glyphs " 0 " of flicker；
OEIL states are shown using amber (or yellow) character+amber (or yellow) numerical value, when OEIL uses residue When time is less than 5 seconds, numerical value red flickering display, when being less than 0 second remaining time, shows the red glyphs " 0 " of flicker；
Lower section display training Status Flag " TNG " (10) in EPSI table rings both sides；
Left and right pin of bristling with anger is shown in the both sides of EPSI table rings, shows that left side pin of bristling with anger is that solid (9), the right side pin of bristling with anger are empty The heart (6)；
When parameter is across maximum instantaneousAfterwards, former invalid camber line region with the change of pointer area become with across The red that jump limitation matches.
2. there are following features rotating speed viewing area：
Left and right NF and helicopter NR is integrated on a column pointer bar and shown；
Normally, warn, thick (2) in green thin (5), amber (or yellow), red thick shape is respectively adopted in warning zone Represent (4), inactive area is shown using grey column-shape strip (3)；Left and right NF ginsengs spear pointer (6) instruction, rotor rotating speed NR UsingShape pointer (7) is indicated；
Red fire alarm " FIRE " information (1) of left and right enging cabin can be shown respectively in the both sides of cylindrical scale, when When there is red " FIRE " information, " FIRE " inverse is shown, after driver certifying fault message, becomes normal bright display；Can be with Show green " START ", " IDLE " information of left and right engine.
NF, NR parameter values are shown in below column pointer (8), and centre shows NR parameters, and NR both sides are shown respectively The NF parameters of left and right engine.
3. there are following features engine parameter viewing area：
All engine parameters gather 120 ° or other angles (2) without graduation apparatus ring；
Table ring green area represents normal operation region, is represented with thin green arc；Amber (or yellow) region representation is warned Region, thick amber arc is represented in；Red area represents warning zone, is represented with thick red arc；Inactive area display ash Color, maximum takeoff condition shows red solid line, and maximum instantaneous status display is red
Left and right hair parameter is represented respectively with solid, hollow pointer；Shown respectively in the lower section of TQ, ITT, NG table both sides it is left, TQ, ITT, NG parameter (3) of right hair；When OEIH, OEIL, AEO30 state occurs in left or right engine, respectively in ENG regions Both sides show, while the region show OEIH, OEIL state remaining time (1)；Training state is shown below TQ tables Indicate " OEI TNG " (6)；Left and right pin of bristling with anger is shown in ENG viewing areas both sides, shows that left side pin of bristling with anger is solid, right pin of bristling with anger It is hollow；Arranged on left and right sides shows that the power of left and right hair checks the event of information and EECU buses respectively below ENG viewing areas Hinder information (4)；Underface in ENG viewing areas, shows the XPC information (5) of left and right engine；When parameter is across maximum wink WhenAfterwards, former invalid camber line region is with the color for becoming and jumping to limit and match of pointer area.
With reference to Fig. 2-3, it is exemplified below：
During double hair work
NG=101%, ITT=910 DEG C, TQ=91%, the NG read in being adjusted from electricityTop=102.41, NGMCP= 100.71%,
NG is between MCP and TOP；ITT is between MCP and TOP, and TQ is less than TOP, therefore may determine that engine Between MCP and TOP.
Utilize formula：
RE=MIN { (100-TQ)/7, (NGTOP-NG)/(NGTOP-NGMCP)；(942-ITT)/34 } it is Re=MIN {(100-91)/7；(121.41-101)/(102.41-100.71)；(942-910)/34 } Re=0.8294
Utilize formula：
ESI=(1-RE) * 100+RE*93；Calculate to obtain ESI=94.19.

Claims (1)

1. a kind of helicopter engine parameter display system, the parameter for providing optimization to driver is shown, including engine Sensor, electricity tune, computing device and display device, it is characterised in that：
The engine sensor detection comes from the parameter information of engine；The electricity adjusts the information for receiving engine sensor And it is converted into the parameter information and warning information of engine；Computing device is exclusively used in the calculating of ESI parameters；Display device is used to show Show the parameter of engine, include TQ, ITT, NG parameter of ESI parameters, engine, and engine warning information, herein ESI is that engine condition indicates that TQ is engine torque, and ITT is engine interior turbine temperature, and NG is engine gas turbine Rotating speed；
The computing device to current TQ by carrying out dimensionless calculating, and according to the engine parameter comprehensive descision detected simultaneously Calculating obtains ESI parameters, wherein, the current TQ ÷ TQ of TQ=TOP× 100, TQTOPIt is the torque value under maximum take-off power；
If the electricity adjusts output single-engine run information or any one engine NG rotating speed to be less than 50%, you can to confirm to go straight up to Machine is in single-engine operation state；Otherwise it is assumed that helicopter is in double hair working conditions；
During double hair working conditions
If NG when NG, ITT and TQ are no more than slow trainIDLE、ITTIDLEAnd TQIDLE, i.e. NG≤NGIDLEAnd ITT≤ITTIDLEAnd TQ≤TQIDLE, then：
RE=MIN { (TQIDLE-TQ)/TQIDLE, (NGIDLE-NG)/NGIDLE, (ITTIDLE-ITT)/ITTIDLE, ESI=(1-RE) * ESIIDLE；
NGIDLEIt is the NG limitations under IDLE state, ITTIDLEIt is the ITT limitations under IDLE state, TQIDLEUnder being IDLE state TQ is limited, ESIIDLEIt is the ESI limitations under IDLE state, IDLE is engine idling rating；
If NGMCP>NG>NGIDLEOr ITTMCP>ITT>ITTIDLEOr TQTOP>TQ>TQIDLE, and NG<NGTOPAnd ITT<ITTTOPAnd TQ< TQTOP, then：
RE=MIN { (TQMCP-TQ)/(TQMCP-TQIDLE), (NGMCP-NG)/(NGMCP-NGIDLE), (ITTMCP-ITT)/(ITTMCP- ITTIDLE),
ESI=(1-RE) * ESIMCP+RE*ESIIDLE；
NGMCPIt is the NG limitations under MCP states, ITTMCPIt is the ITT limitations under MCP states, NGTOPIt is the NG limits under TOP states System, ITTTOPIt is the ITT limitations under TOP states, TQMCPIt is the TQ limitations under MCP states, ESIMCPIt is the ESI limits under MCP states System, MCP is continous maximum rating, and TOP is take-off power；
If NGTOP>NG>NGMCPOr ITTTOP>ITT>ITTMCPOr TQTOP>TQ>TQMCP, and NG<NGTOPAnd ITT<ITTTOPAnd TQ< TQTOP, then：
RE=MIN { (TQTOP-TQ)/(TQTOP-TQMCP), (NGTOP-NG)/(NGTOP-NGMCP), (ITTTOP-ITT)/(ITTTOP- ITTMCP),
ESI=(1-RE) * ESITOP+RE*ESIMCP；
ESITOPIt is the ESI limitations under TOP states；
If NG>NGTOPOr ITT>ITTTOPOr TQ>TQTOP, then：
RE=MIN { (TQAEO-TQ)/(TQAEO-TQTOP), (NGAEO-NG)/(NGAEO-NGTOP), (ITTAEO-ITT)/(ITTAEO- ITTTOP),
ESI=(1-RE) * ESIAEO+RE*ESITOP；
TQAEOIt is the TQ limitations under AEO states, NGAEOIt is the NG limitations under AEO states, ITTAEOIt is the ITT limits under AEO states System, ESIAEOIt is the ESI limitations under AEO states；
During single-engine operation state
If NG≤NGIDLE@OEIAnd ITT≤ITTIDLE@OEIAnd TQ≤TQIDLE@OEI, then：
RE=MIN { (TQIDLE@OEI-TQ)/TQIDLE@OEI, (NGIDLE@OEI-NG)/NGIDLE@OEI, (ITTIDLE@OEI- ITT)/ITT },
ESI=(1-RE) * ESIIDLE；
NGIDLE@OEIIt is the NG limitations under OEI state idling ratings, ITTIDLE@OEIIt is the ITT limitations under OEI idling ratings, TQIDLE@OEIIt is the TQ limitations under OEI state idling ratings, OEI is that single-shot does not work；
If NGOEIC>NG>NGIDLE@OEIOr ITTOEIC>ITT>ITTIDLE@OEIOr TQOEIC>TQ>TQIDLE@OEI；And NG<NGOEICAnd ITT< ITTOEICAnd TQ<TQOEIC, then：
RE=MIN { (TQOEIC-TQ)/(TQOEIC-TQIDLE@OEI), (NGOEIC-NG)/(NGOEIC-NGIDLE@OEI), (ITTOEIC- ITT)/(ITTOEIC-ITTIDLE@OEI),
ESI=(1-RE) * ESIOEIC+RE*ESIIDLE；
NGOEICIt is the NG limitations under OEIC states, ITTOEICIt is the ITT limitations under OEIC states, TQOEICUnder being OEIC states TQ is limited, and OEIC is OEI maximum continuous；
If NGOEIL>NG>NGOEICOr ITTOEIL>ITT>ITTOEICOr TQOEIL>TQ>TQOEIC；And NG<NGOEILAnd ITT<ITTOEILAnd TQ<TQOEIL, then：
RE=MIN { (TQOEIL-TQ)/(TQOEIL-TQOEIC), (NGOEIL-NG)/(NGOEIL-NGOEIC), (ITTOEIL-ITT)/ (ITTOEIL-ITTOEIC),
ESI=(1-RE) * ESIOEIL+RE*ESIOEIC；
NGOEILIt is the NG limitations under OEIL states, ITTOEILIt is the ITT limitations under OEIL states, TQOEILUnder being OEIL states TQ is limited, ESIOEILIt is the ESI limitations under OEIL states, ESIOEICIt is the ESI limitations under OEIC states, OEIL is OEI lower bounds System, OEIC is OEI maximum continuous；
If NG>NGOEILOr ITT>ITTOEILOr TQ>TQOEIL, then：
RE=MIN { (TQOEIH-TQ)/(TQOEIH-TQOEIL), (NGOEIH-NG)/(NGOEIH-NGOEIL), (ITTOEIH-ITT)/ (ITTOEIL-ITTOEIC)}
ESI=(1-RE) * ESIOEIH+RE*ESIOEIL,
TQOEIHIt is the TQ limitations under OEIH states, NGOEIHIt is the NG limitations under OEIH states, ITTOEIHUnder being OEIH states ITT is limited, ESIOEIHIt is the ESI limitations under OEIH states, OEIH is OEI height limitations.
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