CN107489531A - 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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- CN107489531A CN107489531A CN201710743902.8A CN201710743902A CN107489531A CN 107489531 A CN107489531 A CN 107489531A CN 201710743902 A CN201710743902 A CN 201710743902A CN 107489531 A CN107489531 A CN 107489531A
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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
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- 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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- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Feedback Control In General (AREA)
Abstract
The invention discloses a kind of hypersonic jets fuel supply rate curve design method based on semi-integral and gain-adaptive, by the flying speed for measuring hypersonic aircraft, error is formed compared with desired speed, then by engine accelerate to be divided into fast acceleration, it is slow accelerate with 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 decelerating phase introducing semi-integral measurement is obtained in average rate, solve the problems, such as that aircraft is precisely controlled difficulty due to slowing down caused by inertia, it is achieved thereby that the accurate tracking to desired speed.Method provided by the invention based on semi-integral, solve the problems, such as that at the uniform velocity cruise section speed overshoot is big, and because the introducing of integration, the precision of speed control are 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 hair based on semi-integral and gain-adaptive
Motivation fuel supply rate curve design method.
Background technology
Hypersonic aircraft refers to that speed is more 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 nearly ten years, and its difficulty is no less than Lunar Probe Project with meaning.It is high at present
One of difficulty of supersonic speed control is engine, and the design difficulty of engine is in addition to concentrating on thrust generation, its fuel feeding
New problem is also faced with speed control.Mainly hypersonic aircraft and conventional low aircraft except 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
Meter proposes higher requirement.And due to the big inertia that hyper tape comes, and oil supply system inertia in itself and delay so that
During using traditional PI D fuel supply rate curves, when being transferred at the uniform velocity cruising phase by acceleration, necessarily cause larger speed overshoot.
The content 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 at least overcome caused by the limitation of correlation technique and defect to a certain extent
Or multiple problems.
The technical solution adopted in the present invention is, a kind of to be sent out based on the hypersonic aircraft of semi-integral and gain-adaptive
Motivation fuel supply rate curve design method, is followed the steps below：
Step 1, measure the flying speed of aircraft and velocity error is built according to flying speed；
Step 2, the fuel supply rate curve of the first accelerating sections is designed according to the size of the velocity error；
Step 3, the fuel supply rate curve of the second accelerating sections is designed according to the size of the velocity error；
Step 4, according to the size of the velocity error design at the uniform velocity or braking section fuel supply rate curve.
Further, the step 1 includes：
Velocity error e is built 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 making 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, wherein：
kv1、kv3、ε1For positive parameter；f1For positive parameter, its selection range is 0 ＜ f1＜ 1；
kv2Using adaptive updating rule, wherein：
For kv2Derivative；kv2a、kv2a1、kv2a2For positive parameter.
Further, the step 3 includes：
As 0 ＜ eV＜ f1eV0When, the varying-gain nonlinear fuel supply rate curve ψ of the second accelerating sections of design2, wherein：
kv12、kv32、ε12For positive parameter；kv22Using adaptive updating rule, wherein：
For kv22Derivative, kv2bFor positive parameter.
Further, the step 4 includes：
As velocity error eVDuring ＜ 0, the fuel supply rate curve ψ of design speed or braking section3, wherein：
kv13、kv33、ε13、kv4For positive parameter；SeFor error semi-integral, wherein：
And have：
kv23Using adaptive updating rule, wherein： For kv23Lead
Number, kv2cFor 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 of hypersonic aircraft is measured, error is formed compared with desired speed, then accelerates to be divided into by engine
It is fast accelerate, it is slow accelerate with 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 is due to the problem of being precisely controlled difficulty of slowing down caused by inertia, it is achieved thereby that 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 integration
Introduce, the precision of speed control is also higher.The present invention only needs measuring speed simultaneously, and measuring speed is needed rather than traditional PID control
Derivative, therefore this method has very high engineering practical value.Further, method provided by the present invention has robustness
Well, the advantages of precision is high, and overshoot is small, so as to have very high engineering practical value.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, can be with
Other accompanying drawings are obtained according to these accompanying 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 theory diagram.
Fig. 2 is that the hypersonic aircraft speed tracing for the desired speed 2691 that the embodiment of the present invention provides method is bent
Line.
Fig. 3 is the motor power curve for the desired speed 2691 that the embodiment of the present invention provides method.
Fig. 4 is the aircraft resistance curve for the desired speed 2691 that the embodiment of the present invention provides method.
Fig. 5 is that the hypersonic aircraft speed tracing for the desired speed 2491 that the embodiment of the present invention provides method is bent
Line.
Fig. 6 is the motor power curve for the desired speed 2491 that the embodiment of the present invention provides method.
Fig. 7 is the aircraft resistance curve for the desired speed 2491 that the embodiment of the present invention provides method
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, rather than whole embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art are obtained every other under the premise of creative work is not made
Embodiment, belong to the scope of protection of the invention.
The invention discloses a kind of hypersonic jets fuel supply rate curve design side based on semi-integral and gain-adaptive
Method, with reference to shown in figure 1, mistake can be formed compared with desired speed by measuring the flying speed of hypersonic aircraft
Difference, then by engine accelerate to be divided into fast acceleration, it is slow accelerate with 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 is precisely controlled difficulty due to slowing down caused by inertia, it is achieved thereby that
Accurate tracking to desired speed.
Further, it is 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：Measure the flying speed of aircraft and velocity error is built according to flying speed.
Using the speed of pitot meter measurement aircraft, the velocity measurement is designated as V, and the velocity measurement required precision is not
Height, error are operated in the range of 5%.Assuming that the desired speed of aircraft is Vd, then the measured value and actual 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, wherein：
kv1、kv3、ε1For positive parameter；f1For positive parameter, its selection range is 0 ＜ f1＜ 1；
kv2Using adaptive updating rule, wherein：
For kv2Derivative；kv2a、kv2a1、kv2a2For 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, the varying-gain nonlinear fuel supply rate curve ψ of the second accelerating sections of design2, wherein：
kv12、kv32、ε12For positive parameter；kv22Using adaptive updating rule, wherein：
For kv22Derivative, kv2bFor positive parameter.
Step 4：According to the size of velocity error design at the uniform velocity or braking section fuel supply rate curve
As velocity error eVDuring ＜ 0, the fuel supply rate curve ψ of design speed or braking section3, wherein：
kv13、kv33、ε13、kv4For positive parameter；SeFor error semi-integral, wherein：
And have：
Therefore, seOnly worked when slowing down；
kv23Using adaptive updating rule, wherein：
WhereinFor kv23Derivative, kv2cFor 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 accelerates with aircraft is established
Choose rationally, can be imitated with by computer simulation in order to ensure the parameter of the controller into step 4 of above-mentioned steps one
Genuine means are programmed, so as to simulate the engine accelerating performance of controlled device hypersonic aircraft pitch channel, so as to
It is convenient to carry out speed control parameter adjustment.Demonstrate and illustrate by taking certain a kind of hypersonic aircraft engine mockup as an example herein, its
Pitch channel can use following Differential Equation Modeling to represent：
Wherein,For the velocity derivatives of aircraft；
M is vehicle mass, and its selection refers to case study on implementation hereinafter；
α is Aircraft Angle of Attack, and its selection refers to case study on implementation hereinafter；
G is acceleration of gravity, and its selection refers to case study on implementation hereinafter；
γ is Flight Vehicle Trajectory inclination angle, and its selection refers to case study on implementation hereinafter；
T is motor power,
Wherein,S is aircraft feature area；ρ is air
Density；β is engine oil parameter, it is considered herein that inertial delay, itself and the fuel feeding factor ψ relation meet following transmission function：
Wherein, s is the differential operator of transmission function, ε and ωfFor positive parameter, its selection refers to 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 is debugged
The normal parameter in above-mentioned model is subjected to setting value 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 of speed control parameter is carried out, is carried out successively according to the three phases involved by step 2 three or four, point
Following three step：
The first step is to the k in step 2v1、kv3、ε1、f1、kv2a、kv2a1、kv2a2Debugged；
Second step is to the k in step 3v12、kv32、ε12、kv2bDebugged；
3rd step is to the k in step 4v13、kv33、ε13、kv4Debugged.
Finally, by the good parameter of above-mentioned debugging, simulation analysis are carried out, according to the tracking of rate curve and speed desired value
Effect, further adjusted, be worth obtaining preferable speed control effect, so that it is determined that final fuel feeding rule 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；
Emulated according to the parameter setting of above-mentioned steps one to step 5, obtain simulation curve and see Fig. 2 to Fig. 7.
From simulation curve, it is to set smaller that the given speed of aircraft is unfavorable, or sets 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, the speed for also being adapted for small range is precisely controlled.
The increase process of speed has substantially been divided into quick accelerator, at a slow speed it can be seen from velocity-response curve simultaneously
Accelerator, and the final steady process at the uniform velocity controlled, embody the thought of expected design, it is achieved thereby that accelerating completely
Turn stationary process, the less expected purpose of speed control overshoot.
2 points of the above illustrates that method provided by the present invention has the advantages of robustness is good, and precision is high, and overshoot is small, so as to have
There is very high engineering practical value.
It should be noted that herein, such as first and second or the like relational terms are used merely to a reality
Body or operation make a distinction with another entity or operation, and not necessarily require or imply and deposited between these entities or operation
In any this actual relation or order.Moreover, term " comprising ", "comprising" or its any other variant are intended to
Nonexcludability includes, so that process, method, article or equipment including a series of elements not only will including those
Element, but also the other element including being not expressly set out, or it is this process, method, article or equipment also to include
Intrinsic key element.In the absence of more restrictions, the key element limited by sentence "including a ...", it is not excluded that
Other identical element also be present in process, method, article or equipment including the key element.
Each embodiment in this specification is described by the way of related, identical similar portion between each embodiment
Divide mutually referring to what each embodiment stressed is the difference with other embodiment.
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 substitution and improvements made within the spirit and principles in the present invention etc., 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, its feature
It is, follows the steps below：
Step 1, measure the flying speed of aircraft and velocity error is built according to flying speed；
Step 2, the fuel supply rate curve of the first accelerating sections is designed according to the size of the velocity error；
Step 3, the fuel supply rate curve of the second accelerating sections is designed according to the size of the velocity error；
Step 4, according to the size of the velocity error design at the uniform velocity or braking section fuel supply rate curve.
2. hypersonic aircraft engine oil rule design method according to claim 1, it is characterised in that described
Step 1 includes：
Velocity error e is built 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, it is characterised in that described
Step 2 includes：
The initial velocity error for making 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, wherein：
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kv1、kv3、ε1For positive parameter；f1For positive parameter, its selection range is 0 ＜ f1＜ 1；
kv2Using adaptive updating rule, wherein：
For kv2Derivative；kv2a、kv2a1、kv2a2For positive parameter.
4. hypersonic aircraft engine oil rule design method according to claim 3, it is characterised in that described
Step 3 includes：
As 0 ＜ eV＜ f1eV0When, the varying-gain nonlinear fuel supply rate curve ψ of the second accelerating sections of design2, wherein：
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kv12、kv32、ε12For positive parameter；kv22Using adaptive updating rule, wherein：
For kv22Derivative, kv2bFor positive parameter.
5. hypersonic aircraft engine oil rule design method according to claim 4, it is characterised in that described
Step 4 includes：
As velocity error eVDuring ＜ 0, the fuel supply rate curve ψ of design speed or braking section3, wherein：
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kv23Using adaptive updating rule, wherein： For kv23Derivative, kv2c
For 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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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111734536A (en) * | 2020-07-02 | 2020-10-02 | 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 |
| JPH0318628A (en) * | 1989-05-30 | 1991-01-28 | United Technol Corp <Utc> | Acceleration control device for gas turbine engine |
| CN102317600A (en) * | 2009-02-16 | 2012-01-11 | 斯奈克玛 | Method and system for tuning a gas turbine and gas turbine including such a system |
| CN105649782A (en) * | 2015-12-31 | 2016-06-08 | 西北工业大学 | Micro/small jet engine fuel control system and control method |
-
2017
- 2017-08-25 CN CN201710743902.8A patent/CN107489531B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3357177A (en) * | 1966-06-02 | 1967-12-12 | Gen Electric | Gas turbine engine fuel control system |
| JPH0318628A (en) * | 1989-05-30 | 1991-01-28 | United Technol Corp <Utc> | Acceleration control device for gas turbine engine |
| CN102317600A (en) * | 2009-02-16 | 2012-01-11 | 斯奈克玛 | Method and system for tuning a gas turbine and gas turbine including such a system |
| CN105649782A (en) * | 2015-12-31 | 2016-06-08 | 西北工业大学 | Micro/small jet engine fuel control system and control method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111734536A (en) * | 2020-07-02 | 2020-10-02 | 中国人民解放军海军工程大学 | Engine stable oil supply method adopting adaptive fractional order differential |
| 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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|---|---|
| CN107489531B (en) | 2019-04-16 |
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