CN107489531B - Hypersonic jets fuel supply rate curve design method based on semi-integral and gain-adaptive - Google Patents
Hypersonic jets fuel supply rate curve design method based on semi-integral and gain-adaptive Download PDFInfo
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- CN107489531B CN107489531B CN201710743902.8A CN201710743902A CN107489531B CN 107489531 B CN107489531 B CN 107489531B CN 201710743902 A CN201710743902 A CN 201710743902A CN 107489531 B CN107489531 B CN 107489531B
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- fuel supply
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- supply rate
- rate curve
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Classifications
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- 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
- F02C9/26—Control of fuel supply
- F02C9/44—Control of fuel supply responsive to the speed of aircraft, e.g. Mach number control, optimisation of fuel consumption
-
- 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
- F05D2270/00—Control
- F05D2270/70—Type of control algorithm
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Feedback Control In General (AREA)
Abstract
The hypersonic jets fuel supply rate curve design method based on semi-integral and gain-adaptive that the invention discloses a kind of, by the flying speed for measuring hypersonic aircraft, be compared to form error with desired speed, then by engine acceleration be divided into fast acceleration, it is slow accelerate at the uniform velocity or deceleration three phases.In the above three stage, design the compound fuel supply rate curve of different gain-adaptive fuel supply rate curve and non-linear fuel supply rate curve composition, especially decelerating phase introducing semi-integral measurement is obtained in average rate, it solves the problems, such as that aircraft slows down as caused by inertia and is precisely controlled difficulty, to realize the accurate tracking to desired speed.Method provided by the invention based on semi-integral solves the problems, such as that at the uniform velocity cruise section speed overshoot is big, and due to the introducing of integral, the precision of speed control is also higher.The present invention only needs measuring speed simultaneously, the derivative of measuring speed is needed rather than traditional PID control, therefore this method has very high engineering practical value.
Description
Technical field
The invention belongs to control technology field more particularly to a kind of hypersonic hairs based on semi-integral and gain-adaptive
Motivation fuel supply rate curve design method.
Background technique
Hypersonic aircraft refers to that speed is greater than 5 Mach of aircraft, due to its potential military and Value of Science & Technology, mesh
The preceding close attention for worldwide causing power.
China is also expanding key project research, difficulty and meaning no less than Lunar Probe Project nearly ten years.It is high at present
One of the difficulty of supersonic speed control is engine, and the design difficulty of engine is other than concentrating on thrust and generating, fuel feeding
New problem is also faced with speed control.Mainly hypersonic aircraft and conventional low aircraft the difference is that its
The efficiency of engine is serious by the coupling influence of state of flight, therefore realizes accurately speed control, also setting to fuel supply rate curve
More stringent requirements are proposed for meter.And due to inertia and the delay of the big inertia of high speed bring and oil supply system itself, so that
When using traditional PI D fuel supply rate curve, when being transferred at the uniform velocity cruising phase by acceleration, necessarily cause biggish speed overshoot.
Summary of the invention
In order to achieve the above object, the present invention provides a kind of hypersonic jets based on semi-integral and gain-adaptive
Fuel supply rate curve design method, and then one is overcome caused by the limitation and defect due to the relevant technologies at least to a certain extent
Or multiple problems.
The technical scheme adopted by the invention is that a kind of sent out based on the hypersonic aircraft of semi-integral and gain-adaptive
Motivation fuel supply rate curve design method, follows the steps below:
Step 1 measures the flying speed of aircraft and constructs velocity error according to flying speed；
Step 2 designs the fuel supply rate curve of the first accelerating sections according to the size of the velocity error；
Step 3 designs the fuel supply rate curve of the second accelerating sections according to the size of the velocity error；
Step 4, at the uniform velocity or the fuel supply rate curve of braking section according to the design of the size of the velocity error.
Further, the step 1 includes:
Velocity error e is constructed using the speed V of pitot meter measurement aircraft, and according to the speed V of the aircraftV；Its
In: eV=Vd- V, VdFor the desired speed of aircraft.
Further, the step 2 includes:
The initial velocity error for enabling aircraft is eV0, as velocity error eV> f1eV0When, the change of the first accelerating sections of design increases
The non-linear fuel supply rate curve ψ of benefit1, in which:
kv1、kv3、ε1The parameter being positive；f1Be positive parameter, and selection range is 0 < f1< 1；
kv2Using adaptive updating rule, in which:
For kv2Derivative；kv2a、kv2a1、kv2a2Be positive parameter.
Further, the step 3 includes:
As 0 < eV< f1eV0When, design the varying-gain nonlinear fuel supply rate curve ψ of the second accelerating sections2, in which:
kv12、kv32、ε12The parameter being positive；kv22Using adaptive updating rule, in which:
For kv22Derivative, kv2bBe positive parameter.
Further, the step 4 includes:
As velocity error eVWhen < 0, the fuel supply rate curve ψ of design speed or braking section3, in which:
kv13、kv33、ε13、kv4The parameter being positive；SeFor error semi-integral, in which:
And have:
kv23Using adaptive updating rule, in which: For kv23Lead
Number, kv2cBe positive parameter.
A kind of hypersonic jets fuel supply rate curve design method based on semi-integral and gain-adaptive of the present invention, passes through
The flying speed for measuring hypersonic aircraft, is compared to form error with desired speed, is then divided into engine acceleration
It is fast accelerate, it is slow accelerate at the uniform velocity or deceleration three phases.In the above three stage, different gain-adaptive fuel supply rate curves is designed
With the compound fuel supply rate curve of non-linear fuel supply rate curve composition, decelerating phase introducing semi-integral measurement especially is obtained in average rate, is solved
Aircraft slows down as caused by inertia is precisely controlled difficult problem, to realize the accurate tracking to desired speed.This
The method based on semi-integral provided is provided, solves the problems, such as that at the uniform velocity cruise section speed overshoot is big, and due to integral
It introduces, the precision of speed control is also higher.The present invention only needs measuring speed simultaneously, needs measuring speed rather than traditional PID control
Derivative, therefore this method have very high engineering practical value.Further, method provided by the present invention has robustness
Good, precision is high, the small advantage of overshoot, to have very high engineering practical value.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
It obtains other drawings based on these drawings.
Fig. 1 is that a kind of hypersonic jets fuel supply rate curve based on semi-integral and gain-adaptive provided by the invention is set
Count functional block diagram.
Fig. 2 is that the hypersonic aircraft speed tracing of the desired speed 2691 of institute of embodiment of the present invention providing method is bent
Line.
Fig. 3 is the motor power curve of the desired speed 2691 of institute of embodiment of the present invention providing method.
Fig. 4 is the aircraft resistance curve of the desired speed 2691 of institute of embodiment of the present invention providing method.
Fig. 5 is that the hypersonic aircraft speed tracing of the desired speed 2491 of institute of embodiment of the present invention providing method is bent
Line.
Fig. 6 is the motor power curve of the desired speed 2491 of institute of embodiment of the present invention providing method.
Fig. 7 is the aircraft resistance curve of the desired speed 2491 of institute of embodiment of the present invention providing method
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
The invention discloses a kind of hypersonic jets fuel supply rate curve design side based on semi-integral and gain-adaptive
Method, refering to what is shown in Fig. 1, can be compared to form mistake with desired speed by the flying speed of measurement hypersonic aircraft
Difference, then by engine acceleration be divided into fast acceleration, it is slow accelerate at the uniform velocity or deceleration three phases.In the above three stage, design
The compound fuel supply rate curve of different gain-adaptive fuel supply rate curves and non-linear fuel supply rate curve composition, especially obtains deceleration in average rate
Stage introduces semi-integral measurement, solves the problems, such as that aircraft slows down as caused by inertia and is precisely controlled difficulty, to realize
Accurate tracking to desired speed.
Further, a kind of to be designed based on the hypersonic aircraft engine oil rule of semi-integral and gain-adaptive
Method may comprise steps of:
Step 1: measuring the flying speed of aircraft and constructs velocity error according to flying speed.
Using the speed of pitot meter measurement aircraft, which is denoted as V, and the velocity measurement required precision is not
Height, error operate in 5% range.Assuming that the desired speed of aircraft is Vd, then the measured value and true value of aircraft speed
Between error be defined as eV=Vd-V。
Step 2: the fuel supply rate curve of the first accelerating sections is designed according to the size of velocity error
Assuming that the speed initial error of aircraft is eV0, as velocity error eV> f1eV0When, design the change of the first accelerating sections
Nonlinear gain fuel supply rate curve ψ1, in which:
kv1、kv3、ε1The parameter being positive；f1Be positive parameter, and selection range is 0 < f1< 1；
kv2Using adaptive updating rule, in which:
For kv2Derivative；kv2a、kv2a1、kv2a2Be positive parameter.
Step 3: the fuel supply rate curve of the second accelerating sections is designed according to the size of velocity error
As 0 < eV< f1eV0When, design the varying-gain nonlinear fuel supply rate curve ψ of the second accelerating sections2, in which:
kv12、kv32、ε12The parameter being positive；kv22Using adaptive updating rule, in which:
For kv22Derivative, kv2bBe positive parameter.
Step 4: at the uniform velocity or the fuel supply rate curve of braking section according to the design of the size of velocity error
As velocity error eVWhen < 0, the fuel supply rate curve ψ of design speed or braking section3, in which:
kv13、kv33、ε13、kv4The parameter being positive；SeFor error semi-integral, in which:
And have:
Therefore, seOnly work when slowing down；
kv23Using adaptive updating rule, in which:
WhereinFor kv23Derivative, kv2cBe positive parameter.
By above-mentioned four step, that is, realize the hypersonic hair of the non-linear variable gain based on semi-integral provided by the present invention
Motivation fuel supply rate curve.
Step 5: the simplified model that engine and aircraft accelerate is established
In order to ensure the parameter of the controller into step 4 of above-mentioned steps one is chosen rationally, can be imitated with by computer simulation
Genuine means are programmed, so that the engine accelerating performance of controlled device hypersonic aircraft pitch channel is simulated, thus
Facilitate and carries out speed control parameter adjustment.It demonstrates and illustrates by taking certain a kind of hypersonic aircraft engine mockup as an example herein,
Pitch channel can be indicated using following Differential Equation Modeling:
Wherein,For the velocity derivatives of aircraft；
M is vehicle mass, and selection is detailed in case study on implementation hereinafter；
α is Aircraft Angle of Attack, and selection is detailed in case study on implementation hereinafter；
G is acceleration of gravity, and selection is detailed in case study on implementation hereinafter；
γ is Flight Vehicle Trajectory inclination angle, and selection is detailed in case study on implementation hereinafter；
T is motor power,
Wherein,S is aircraft feature area；ρ is atmosphere
Density；β is engine oil parameter, it is considered herein that inertial delay, meets following transmission function with the relationship of fuel feeding factor ψ:
Wherein, s is the differential operator of transmission function, ε and ωfBe positive parameter, and selection is detailed in case study on implementation hereinafter；
D is aircraft resistance, and calculation is as follows:CD=0.645 α2+0.0043378α+0.003772。
Step 6: engine speed control parameter debugging
The normal parameter in above-mentioned model is subjected to numerical value setting first, it is necessary to meet the physical significance of dummy vehicle, in detail
Thin setting is implemented referring to case hereinafter.
Then the adjustment for carrying out speed control parameter, successively carries out according to three phases involved in step 2 three or four, point
Following three step:
The first step is to the k in step 2v1、kv3、ε1、f1、kv2a、kv2a1、kv2a2It is debugged；
Second step is to the k in step 3v12、kv32、ε12、kv2bIt is debugged；
Third step is to the k in step 4v13、kv33、ε13、kv4It is debugged.
Finally, the parameter good by above-mentioned debugging, carries out simulation analysis, according to the tracking of rate curve and speed desired value
Effect is further adjusted, and is worth obtaining preferable speed control effect, so that it is determined that final fuel feeding restrains parameter.Tool
Body simulation curve is shown in the result that case is implemented.
By above-mentioned six step, that is, realize hypersonic aircraft engine oil rule design side provided by the present invention
Method.
In step 1, the speed desired value V of hypersonic aircraft is setd=2691, setting speed initial value is V=
2391。
In step 2, f is set1=0.1, kv1=0.01, kv3=0.0001, ε1=30, kv2a=0.01, kv2a1=5,
kv2a2=3.
In step 3, k is setv12=0.02, kv32=0.005, ε12=10, kv2b=0.02.
In step 4, k is setv2c=10, kv13=0.2, kv33=0.001, ε13=3, kv4=2.
Hypersonic aircraft quality m=4352.3 is set in step 5；
Atmospheric density ρ is chosen for ρ=0.0125.
Aircraft Angle of Attack α=1/57.3；
For gravity acceleration g=9.8；
Flight Vehicle Trajectory tilt angle gamma=0.1/57.3；
Aircraft feature area S=334.7,
Atmospheric density ρ=0.0125.
Engine parameter ε=0.5, ωf=150；
It is emulated according to the parameter setting of above-mentioned steps one to step 5, obtains simulation curve and see Fig. 2 to Fig. 7.
By simulation curve it is found that the given speed of aircraft is unfavorable be arranged it is smaller, or setting it is larger, the present invention can
Preferably complete the task that aircraft speed is precisely controlled.Illustrate that method provided by the present invention has good applicability, even if
For the speed control of large-scale accelerator, small-scale speed is also suitble to be precisely controlled.
The increase process of speed has obviously been divided into quick accelerator, at a slow speed it can be seen from velocity-response curve simultaneously
Accelerator, and the final process steadily at the uniform velocity controlled, embody the thought of expected design completely, are accelerating to realize
Turn stationary process, the lesser expected purpose of speed control overshoot.
The above two o'clock illustrates that method provided by the present invention has robustness good, and precision is high, the small advantage of overshoot, to have
There is very high engineering practical value.
It should be noted that, in this document, relational terms such as first and second and the like are used merely to a reality
Body or operation are distinguished with another entity or operation, are deposited without necessarily requiring or implying between these entities or operation
In any actual relationship or order or sequence.Moreover, the terms "include", "comprise" or its any other variant are intended to
Non-exclusive inclusion, so that the process, method, article or equipment including a series of elements is not only wanted including those
Element, but also including other elements that are not explicitly listed, or further include for this process, method, article or equipment
Intrinsic element.In the absence of more restrictions, the element limited by sentence "including a ...", it is not excluded that
There is also other identical elements in process, method, article or equipment including the element.
Each embodiment in this specification is all made of relevant mode and describes, same and similar portion between each embodiment
Dividing may refer to each other, and each embodiment focuses on the differences from other embodiments.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the scope of the present invention.It is all
Any modification, equivalent replacement, improvement and so within the spirit and principles in the present invention, are all contained in protection scope of the present invention
It is interior.
Claims (5)
1. a kind of hypersonic aircraft engine oil rule design method based on semi-integral and gain-adaptive, feature
It is, follows the steps below:
Step 1 measures the flying speed of aircraft and constructs velocity error according to flying speed；
Step 2 designs the varying-gain nonlinear fuel supply rate curve of the first accelerating sections according to the size of the velocity error；
Step 3 designs the varying-gain nonlinear fuel supply rate curve of the second accelerating sections according to the size of the velocity error；
Step 4 designs at the uniform velocity or slows down according to the size of adaptive updating rule, error semi-integral and the velocity error
The fuel supply rate curve of section.
2. hypersonic aircraft engine oil rule design method according to claim 1, which is characterized in that described
Step 1 includes:
Velocity error e is constructed using the speed V of pitot meter measurement aircraft, and according to the speed V of the aircraftV；Wherein: eV
=Vd- V, VdFor the desired speed of aircraft.
3. hypersonic aircraft engine oil rule design method according to claim 2, which is characterized in that described
Step 2 includes:
The initial velocity error for enabling aircraft is eV0, as velocity error eV> f1eV0When, the variable-gain for designing the first accelerating sections is non-
Linear fuel supply rate curve ψ1, in which:
kv1、kv3、ε1The parameter being positive；f1Be positive parameter, and selection range is 0 < f1< 1；
kv2Using adaptive updating rule, in which:
For kv2Derivative；kv2a、kv2a1、kv2a2Be positive parameter.
4. hypersonic aircraft engine oil rule design method according to claim 3, which is characterized in that described
Step 3 includes:
As 0 < eV< f1eV0When, design the varying-gain nonlinear fuel supply rate curve ψ of the second accelerating sections2, in which:
kv12、kv32、ε12The parameter being positive；kv22Using adaptive updating rule, in which:
For kv22Derivative, kv2bBe positive parameter.
5. hypersonic aircraft engine oil rule design method according to claim 4, which is characterized in that described
Step 4 includes:
As velocity error eVWhen < 0, the fuel supply rate curve ψ of design speed or braking section3, in which:
kv13、kv33、ε13、kv4The parameter being positive；SeFor error semi-integral, in which:
And have:
kv23Using adaptive updating rule, in which: For kv23Derivative, kv2c
Be positive parameter.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710743902.8A CN107489531B (en) | 2017-08-25 | 2017-08-25 | Hypersonic jets fuel supply rate curve design method based on semi-integral and gain-adaptive |
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| CN201710743902.8A CN107489531B (en) | 2017-08-25 | 2017-08-25 | Hypersonic jets fuel supply rate curve design method based on semi-integral and gain-adaptive |
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| CN107489531B true CN107489531B (en) | 2019-04-16 |
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| CN111734536B (en) * | 2020-07-02 | 2021-11-30 | 中国人民解放军海军工程大学 | Engine stable oil supply method adopting adaptive fractional order differential |
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| US3357177A (en) * | 1966-06-02 | 1967-12-12 | Gen Electric | Gas turbine engine fuel control system |
| IL94506A (en) * | 1989-05-30 | 1993-07-08 | United Technologies Corp | Acceleration control for a gas turbine engine with duct pressure loss compensation |
| FR2942272B1 (en) * | 2009-02-16 | 2011-05-06 | Snecma | METHOD AND SYSTEM FOR CONTROLLING GAS TURBINE AND GAS TURBINE HAVING SUCH A SYSTEM |
| CN105649782B (en) * | 2015-12-31 | 2017-09-26 | 西北工业大学 | A kind of micro-/miniature jet engine fuel control system and control method |
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