CN119047135A - Online identification method for operating efficiency of swing spray pipe - Google Patents

Online identification method for operating efficiency of swing spray pipe Download PDF

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Publication number
CN119047135A
CN119047135A CN202410983848.4A CN202410983848A CN119047135A CN 119047135 A CN119047135 A CN 119047135A CN 202410983848 A CN202410983848 A CN 202410983848A CN 119047135 A CN119047135 A CN 119047135A
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aircraft
flight
state quantity
flight state
operating efficiency
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黄以鑫
夏斌
金一欢
谢伟
历磊
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Shanghai Aerospace Control Technology Institute
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    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/17—Mechanical parametric or variational design
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/10—Numerical modelling
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    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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  • Automation & Control Theory (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

一种摆动喷管操纵效率在线辨识方法，包括：根据发动机地面试车获得的不同工作温度状态下发动机工作推力曲线计算理论飞行轨迹；根据得到的所述理论飞行轨迹，确定飞行过程中飞行器总体参数与关键飞行状态量的关系；根据所述飞行器总体参数与关键飞行状态量的关系，拟合出飞行器总体参数随关键飞行状态量变化的函数；计算不同工作温度状态下飞行器弹性模态频率变化规律，以此为依据设计滤波器对飞行过程中测量的过载信息进行滤波处理；建立摆动喷管操纵效率随关键飞行状态量变化的数学模型，从而实现摆动喷管操纵效率的在线辨识。本发明提高了飞行器对摆动喷管操纵效率离散性差异的适应能力和飞行控制品质。

A method for online identification of swing nozzle control efficiency includes: calculating a theoretical flight trajectory based on the engine working thrust curve under different working temperature states obtained from the engine ground test; determining the relationship between the overall parameters of the aircraft and the key flight state quantity during the flight according to the obtained theoretical flight trajectory; fitting the function of the overall parameters of the aircraft changing with the key flight state quantity according to the relationship between the overall parameters of the aircraft and the key flight state quantity; calculating the change law of the elastic modal frequency of the aircraft under different working temperature states, and designing a filter based on this to filter the overload information measured during the flight; establishing a mathematical model of the swing nozzle control efficiency changing with the key flight state quantity, thereby realizing the online identification of the swing nozzle control efficiency. The present invention improves the adaptability of the aircraft to the discrete differences in the swing nozzle control efficiency and the flight control quality.

Description

Online identification method for operating efficiency of swing spray pipe
Technical Field
The invention relates to an on-line identification method for the operating efficiency of a swing spray pipe, and belongs to the field of flight control.
Background
The swing spray pipe generates a control moment by deviating the thrust from the axis of the aircraft, the control moment is mainly influenced by the swing angle and the thrust of the spray pipe, and the overall parameters such as mass center, moment of inertia and the like can also influence the spray pipe operating efficiency. Under different engine working temperature states, the engine thrust and working time are different, and meanwhile, the total parameters such as mass, mass center and rotational inertia are strong in discretization along with time change, so that the swing spray pipe operation in the flight process needs to be identified, and the control quality of the whole flight stage is improved.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and designs an on-line identification method for the operating efficiency of the swing spray pipe by analyzing the relevance between the overall parameters and the flight state of the aircraft based on the theoretical flight trajectory, so that the adaptability of the aircraft to the discrete difference of the operating efficiency of the swing spray pipe and the flight control quality are improved.
The invention adopts the technical scheme that:
An on-line identification method for the operating efficiency of a swing spray pipe comprises the following steps:
step one, calculating a theoretical flight track according to engine working thrust curves under different working temperature states obtained by engine ground test;
determining the relation between the overall parameters of the aircraft in the flight process and key flight state quantities according to the obtained theoretical flight track, wherein the overall parameters of the aircraft comprise the mass, mass center, moment of inertia and thrust of the aircraft, and the key flight state quantities comprise flight altitude, mach number, flight attack angle, dynamic pressure and acceleration;
Fitting a function of the overall parameters of the aircraft along with the change of the key flight state quantity according to the relation between the overall parameters of the aircraft and the key flight state quantity;
calculating the change rule of the elastic modal frequency of the aircraft under different working temperature states, and designing a filter according to the change rule to filter overload information measured in the flight process;
And fifthly, establishing a mathematical model of the swing spray pipe operating efficiency changing along with the key flight state quantity, so as to realize online identification of the swing spray pipe operating efficiency.
Further, the theoretical flight trajectory includes changes in flight altitude, mach number, angle of attack, dynamic pressure, mass and moment of inertia during flight.
Further, the determining the relationship between the overall parameters of the aircraft and the critical flight state quantity in the flight process according to the obtained theoretical flight trajectory specifically comprises:
and respectively establishing fitting functions of the flight state quantity and the overall parameters of the aircraft, wherein the fitting functions are linear functions, comparing the fitting functions, and selecting the flight state quantity with the highest linearity and fitting degree with the overall parameters of the aircraft as a key flight state quantity.
Further, according to the relationship between the overall parameters of the aircraft and the critical flight state quantity, a function of the overall parameters of the aircraft, which changes along with the critical flight state quantity, is fitted, specifically:
Xg=k1×Ma+m1
Jz=k2×Ma+m2
Mass=k3×Ma+m3
Ca=k4×Ma+m4
Wherein the aircraft centroid Xg, moment of inertia Jz, mass, and drag coefficient Ca are fitted by mach number Ma, where k i、mi is the result of the parameters of the fit, i=1, 2,3,4.
Further, according to the overall parameters and the resistance coefficient obtained by the function of the overall parameters of the aircraft along with the change of the key flight state quantity, the Thrust is obtained through calculation by combining the real axial acceleration Ax obtained by the measurement of the aircraft.
Further, calculating the change rule of the elastic modal frequency of the aircraft under different working temperature states, and designing a filter based on the change rule to filter the real axial acceleration Ax measured in the flight process, wherein the method specifically comprises the following steps:
design of notch filter G(s):
Wherein T 1、T2 is a filtering time constant, and ζ 1、ζ2 is a damping coefficient of the structural filter;
The filter time constant T 1、T2 is adjusted by the Mach number Ma to make the change of the filter center frequency consistent with the change of the elastic mode frequency.
Further, the filter time constant T 1、T2:
T1＝1/(m5+k5×Ma)
T2＝1/(m6+k6×Ma)
Wherein m 5、m6、k5、k6 is a parameter result obtained by fitting.
Further, a mathematical model of the swing nozzle manipulation efficiency changing along with the key flight state quantity is established, so that the on-line identification of the swing nozzle manipulation efficiency a 3bp is realized, specifically:
Thrust=Ca×Q×S+Mass×Ax
a3bp=Thrust×(L-Xg)/Jz
wherein S is the characteristic area of the aircraft, L is the length of the aircraft, and Q is the dynamic pressure in real time in flight.
In a second aspect, the present invention also proposes a non-volatile storage medium comprising a computer program product which, when executed, performs the swing nozzle manipulation efficiency online identification method.
In a third aspect, the present invention also proposes a computer program product which, when executed by a processor, implements the steps of the method for online identification of operating efficiency of a swinging nozzle.
Compared with the prior art, the invention has the beneficial effects that:
(1) According to the invention, the flight state quantity with strong correlation of the overall parameters such as the thrust, the mass center, the rotational inertia and the like of the engine is analyzed and confirmed according to the theoretical flight trajectory, a mathematical model of the swing spray pipe operating efficiency changing along with the key flight state quantity is established, and a series of problems caused by the thrust characteristics of the aircraft engine under different temperature work are solved by on-line identification of the influence of the swing spray pipe operating efficiency on the improvement of the thrust discrete characteristics.
(2) According to the invention, theoretical flight trajectories under different engine working states are analyzed, the selected key flight state quantity is used as a basis for identification, the physical concept is clear, and in order to restrain the influence of elastic vibration in the flight process, a filter is designed according to the rule that the elastic mode is regulated along with the key flight state, so that the adaptability to the elastic vibration characteristics of the engine under different working states is good.
Drawings
FIG. 1 is a flow chart of the method of the present invention;
FIG. 2 is a diagram of theoretical flight trajectories of an aircraft under different engine operating conditions calculated from a flight mission;
FIG. 3 is a schematic diagram of Mach number versus overall aircraft parameters.
Detailed Description
The invention discloses an on-line identification method for the operating efficiency of a swing jet pipe by using a solid rocket engine, which is characterized in that a theoretical flight track is calculated according to the ground test result of the engine, the relevance of overall parameters such as the thrust, the mass center, the rotational inertia and the like of an aircraft under the condition of high and low normal temperature and different flight states is analyzed, so that a mathematical model of the operating efficiency of the swing jet pipe changing along with the key flight state quantity is established, and the on-line identification of the operating efficiency is completed.
As shown in FIG. 1, the invention provides an on-line identification method for the operating efficiency of a swing spray pipe, which comprises the following steps:
step one, calculating a theoretical flight track according to engine working thrust curves under different working temperature states obtained by engine ground test;
The theoretical flight trajectory comprises the changes of flight altitude, mach number, attack angle, dynamic pressure, mass and rotational inertia in the flight process.
Determining the relation between the overall parameters of the aircraft in the flight process and key flight state quantities according to the obtained theoretical flight track, wherein the overall parameters of the aircraft comprise the mass, mass center, moment of inertia and thrust of the aircraft, and the key flight state quantities comprise flight altitude, mach number, flight attack angle, dynamic pressure and acceleration;
And respectively establishing fitting functions of the flight state quantity and the overall parameters of the aircraft, wherein the fitting functions are linear functions, comparing the fitting functions, and selecting the flight state quantity with the highest linearity and fitting degree with the overall parameters of the aircraft as a key quantity.
Fitting a function of the overall parameters of the aircraft along with the change of the key flight state quantity according to the relation between the overall parameters of the aircraft and the key flight state quantity, wherein the function comprises the following specific steps:
Xg=k1×Ma+m1
Jz=k2×Ma+m2
Mass=k3×Ma+m3
Ca=k4×Ma+m4
Wherein the aircraft centroid Xg, moment of inertia Jz, mass, and drag coefficient Ca are fitted by mach number Ma, where k i、mi is the result of the parameters of the fit, i=1, 2,3,4.
And according to the overall parameters and the resistance coefficient obtained by the function of the overall parameters of the aircraft along with the change of the key flight state quantity, combining the real axial acceleration Ax measured by the aircraft, and calculating to obtain the Thrust.
Calculating the change rule of the elastic modal frequency of the aircraft under different working temperature states, and designing a filter according to the change rule to filter overload information measured in the flight process;
The filter is designed according to the method to carry out filter processing on the real axial acceleration Ax measured in the flying process, and the method specifically comprises the following steps:
design of notch filter G(s):
Wherein T 1、T2 is a filtering time constant, and ζ 1、ζ2 is a damping coefficient of the structural filter;
The filter time constant T 1、T2 is adjusted by the Mach number Ma to make the change of the filter center frequency consistent with the change of the elastic mode frequency.
Filter time constant T 1、T2:
T1＝1/(m5+k5×Ma)
T2＝1/(m6+k6×Ma)
Wherein m 5、m6、k5、k6 is a parameter result obtained by fitting.
And fifthly, establishing a mathematical model of the swing spray pipe operating efficiency changing along with the key flight state quantity, so as to realize online identification of the swing spray pipe operating efficiency.
The on-line identification of the swing spray pipe operating efficiency a 3bp is realized, and specifically:
Thrust=Ca×Q×S+Mass×Ax
a3bp=Thrust×(L-Xg)/Jz
wherein S is the characteristic area of the aircraft, L is the length of the aircraft, and Q is the dynamic pressure in real time in flight.
Examples:
according to the flight tasks, theoretical flight trajectories under different engine working temperature states are calculated respectively, as shown in fig. 2, and each piece of flight trajectory data comprises the change condition of data such as flight altitude, mach number, attack angle, dynamic pressure, mass, rotational inertia and the like in the flight process.
By analyzing the theoretical flight trajectory, the Mach number is selected as a key flight state quantity in the embodiment, as shown in fig. 3, the correlation between the thrust and the Mach number is poor, and the correlation between the aircraft mass, the centroid, the moment of inertia, the resistance and the Mach number is strong and the linearity is good in the embodiment. According to the dynamic relationship of the projectile, the axial resultant force born by the aircraft can be similar to the resultant force of the thrust and the resistance of the engine, so that the axial acceleration information measured by the aircraft is also required to be introduced to participate in the identification of the operating efficiency of the swing jet pipe.
The aircraft centroid Xg, moment of inertia Jz, mass and drag coefficient Ca are fitted using mach number Ma as shown in equation 1. Where k i(i＝1,2,3,4…),mi (i=1, 2,3, 4.) is the result of the parameters obtained by fitting.
Xg=k1×Ma+m1
Jz=k2×Ma+m2
Mass=k3×Ma+m3
Ca=k4×Ma+m4 (1)
According to the overall parameters and the resistance coefficient obtained in the formula 1, the Thrust can be obtained through calculation according to the real axial acceleration Ax measured by the aircraft. Since there may be elastic vibration in the axial acceleration Ax obtained by actual measurement, if it is not filtered, it may affect the accuracy of a 3bp identification, so a notch filter is designed, and the expression of the filter is as shown in the formula (2).
Since the elastic mode frequency is directly related to the Mass of the aircraft, and the relation between Mass and Ma is shown in formula 1, the filter time constant can be adjusted by Ma, so that the change of the filter center frequency is consistent with the change of the elastic mode frequency.
Wherein T 1、T2 is a filtering time constant, and ζ 1、ζ2 is a damping coefficient of the structural filter.
T1＝1/(m5+k5×Ma)
T2＝1/(m6+k6×Ma) (3)
And then the identification of the swing nozzle manipulation efficiency a 3bp is completed as shown in formula 4.
Thrust=Ca×Q×S+Mass×Ax
a3bp=Thrust×(L-Xg)/Jz (4)
Wherein S is the characteristic area of the aircraft, L is the length of the aircraft, and Q is the dynamic pressure in real time in flight.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.
The invention is not described in detail in the field of technical personnel common knowledge.

Claims (10)

1. An on-line identification method for the operating efficiency of a swing spray pipe is characterized by comprising the following steps:
calculating a theoretical flight track according to engine working thrust curves under different working temperature states obtained by engine ground test;
Determining the relation between the overall parameters of the aircraft in the flight process and key flight state quantities according to the obtained theoretical flight track, wherein the overall parameters of the aircraft comprise the mass, mass center, rotational inertia and thrust of the aircraft, and the key flight state quantities comprise flight altitude, mach number, flight attack angle, dynamic pressure and acceleration;
fitting a function of the overall parameters of the aircraft along with the change of the key flight state quantity according to the relation between the overall parameters of the aircraft and the key flight state quantity;
Calculating the change rule of the elastic modal frequency of the aircraft under different working temperature states, and designing a filter according to the change rule to filter overload information measured in the flight process;
and establishing a mathematical model of the swing spray pipe operating efficiency changing along with the key flight state quantity, thereby realizing the on-line identification of the swing spray pipe operating efficiency.
2. The method for on-line identification of swing nozzle operating efficiency as set forth in claim 1, wherein said theoretical flight path comprises changes in flight altitude, mach number, angle of attack, dynamic pressure, mass and moment of inertia during flight.
3. The method for identifying the operating efficiency of the swing nozzle on line according to claim 1, wherein the determining the relationship between the overall parameters of the aircraft and the critical flight state quantity in the flight process according to the obtained theoretical flight trajectory is specifically as follows:
and respectively establishing fitting functions of the flight state quantity and the overall parameters of the aircraft, wherein the fitting functions are linear functions, comparing the fitting functions, and selecting the flight state quantity with the highest linearity and fitting degree with the overall parameters of the aircraft as a key flight state quantity.
4. The method for identifying the operating efficiency of the swing nozzle on line according to claim 3, wherein the fitting of the function of the overall aircraft parameter according to the change of the key flight state quantity according to the relation between the overall aircraft parameter and the key flight state quantity is specifically as follows:
Xg=k1×Ma+m1
Jz=k2×Ma+m2
Mass=k3×Ma+m3
Ca=k4×Ma+m4
Wherein the aircraft centroid Xg, moment of inertia Jz, mass, and drag coefficient Ca are fitted by mach number Ma, where k i、mi is the result of the parameters of the fit, i=1, 2,3,4.
5. The method for on-line identification of swing nozzle operating efficiency as set forth in claim 4, wherein said method is characterized by obtaining said Thrust by combining said overall parameters and said drag coefficient obtained as a function of said overall parameters of said aircraft as a function of said critical flight state quantity with said actual axial acceleration Ax measured by said aircraft.
6. The method for on-line identification of swing nozzle operating efficiency as set forth in claim 5, wherein the method is characterized by calculating the change rule of the frequency of the elastic mode of the aircraft at different operating temperatures, and performing filtering processing on the real axial acceleration Ax measured during the flight according to a design filter, and specifically comprises the following steps:
design of notch filter G(s):
Wherein T 1、T2 is a filtering time constant, and ζ 1、ζ2 is a damping coefficient of the structural filter;
The filter time constant T 1、T2 is adjusted by the Mach number Ma to make the change of the filter center frequency consistent with the change of the elastic mode frequency.
7. The method for on-line identification of operating efficiency of a swing nozzle as defined in claim 6, wherein the filter time constant T 1、T2 is:
T1＝1/(m5+k5×Ma)
T2＝1/(m6+k6×Ma)
Wherein m 5、m6、k5、k6 is a parameter result obtained by fitting.
8. The method for on-line identification of swing nozzle manipulation efficiency as set forth in claim 7, wherein a mathematical model of the swing nozzle manipulation efficiency varying with the critical flight state quantity is established to realize on-line identification of the swing nozzle manipulation efficiency a 3bp, specifically:
Thrust=Ca×Q×S+Mass×Ax
a3bp=Thrust×(L-Xg)/Jz
wherein S is the characteristic area of the aircraft, L is the length of the aircraft, and Q is the dynamic pressure in real time in flight.
9. A non-volatile storage medium comprising a computer program product which when executed performs the swing nozzle manipulation efficiency online identification method of any one of claims 1-8.
10. A computer program product, characterized in that the computer program product, when being executed by a processor, implements the steps of the method for online identifying operating efficiency of a swing nozzle according to any one of claims 1 to 8.
CN202410983848.4A 2024-07-22 2024-07-22 Online identification method for operating efficiency of swing spray pipe Pending CN119047135A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN119337511A (en) * 2024-12-23 2025-01-21 北京宇航系统工程研究所 An incremental aerodynamic characteristics design method for an exposed large nozzle layout configuration

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN119337511A (en) * 2024-12-23 2025-01-21 北京宇航系统工程研究所 An incremental aerodynamic characteristics design method for an exposed large nozzle layout configuration

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