CN106446362B - A kind of avionics system Key Performance Indicator analysis method based on OODA loop - Google Patents
A kind of avionics system Key Performance Indicator analysis method based on OODA loop Download PDFInfo
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Abstract
The avionics system Key Performance Indicator analysis method based on OODA loop that the invention discloses a kind of comprising the steps of: 1: being directed to a certain combat duty of aircraft platform, carries out OODA loop analysis, chooses each link parameter；2: determining autocontrol terminal point capture destination probability requirement and missile dispersion error；3: determining the navigation error for meeting guided missile acquisition probability requirement；4: determining the sensor target position error for meeting guided missile acquisition probability requirement；5: determining the fire control attack error met the requirements；6: navigation error, sensor target position error, fire control attack error are subjected to error estimate formula, calculate guided missile out of bound probability, it verifies whether to meet war skill index " hit rate " requirement, completes the closed-Loop Analysis entirely based on OODA loop avionics system Key Performance Indicator.The present invention not only increases system design efficiency, reduces system complexity, can effectively support avionics system comprehensive design, and can shorten the development cycle, saves development cost.
Description
Technical field
The invention belongs to avionics field, in particular to a kind of avionics system key performance based on OODA loop
The method of index analysis.
Background technique
Avionics system Key Performance Indicator is one group of parameter of quantitative description avionics system important feature, it is avionics system
Demonstration stage according to operation needs, puts forward in conjunction with technical level at that time, is design and the main foundation for examining avionics system.
Precision analysis and error distribution are in order to improve Integrated Avionics System performance and to carry out science to the factor for influencing its precision
The method of analysis, it is to carry out system schema examination and Performance Evaluation through each stage of avionics system development, sizing
Effective means.In system top design, it is most concerned with the weapon Fire control precision of Integrated Avionics System.
As shown in Fig. 2, " OODA " that United States Air Force colonel foundes (Obsersve observation, Orient judgement, Decide determines
Plan, Action action) theory have been widely used for business war (such as Dell, Zara) and sophisticated weapons (such as F15, F16,
C4ISR in development).Wherein, observation, which refers to, collects and attempts to solve the problems, such as related information, mentions for the analysis decision of next step
For necessary material；Judgement the characteristics of referring to according to gained information, and to solve the problems, such as or purpose to be achieved, establish solution
Certainly model carries out comprehensive process to information；Decision, which refers to, selects the various decisions made by Resolving probiems model, selects
Facilitate the decision of Resolving probiems；Action, which refers to, carries out feedback guidance according to the result taken action, adjusting and optimizing observation as soon as possible,
The method of judgement makes wiser decision, in order to faster than opponent, obtain preferably as a result, being formed in turn good
" OODA " ring.In air weapon, OODA is described as data acquisition (observation), situation cognition (judgement), tactics respectively
Decision (decision), plan execute (action).
In view of this, the present invention provides a kind of avionics system Key Performance Indicator analysis method based on OODA loop,
The performance for the key function that the war skill index " hit rate " of operational aircraft task level is converted into avionics system level can be referred to
Mark requires, and supports the precision analysis and assessment of the Key Performance Indicators such as avionics system navigator fix, target acquisition, fire control attack,
Reference and foundation are provided to carry out avionics system comprehensive design, system design efficiency can be improved, shorten the development cycle, save exploitation
Cost.
Summary of the invention
In order to find the reasonable approach for improving avionics system performance, goal of the invention of the invention is to provide one kind
Avionics system Key Performance Indicator analysis method based on OODA loop, by the war skill index " hit of operational aircraft task level
Rate " be converted to the key function of avionics system level performance indicator requirement, support avionics system navigator fix, target acquisition,
Fire control attack etc. Key Performance Indicators precision analysis and assessment, thus for carry out avionics system comprehensive design provide reference and according to
According to, and system design efficiency is improved, shorten the development cycle, saves development cost.
Goal of the invention of the invention is achieved through the following technical solutions:
A kind of avionics system Key Performance Indicator analysis method based on OODA loop comprising the steps of:
Step 1: being directed to a certain combat duty of aircraft platform, carry out OODA loop analysis, choose navigation positioning error conduct
The error of data acquisition link, comprehensive missing of the sensor target position error as data acquisition link and situation cognition link
The composition error that error executes link as tactical decision and plan is attacked in difference, fire control；
Step 2: " self-contained guidance+final homing guidance " used according to avionics weapon system in aircraft platform combat duty
Two-part guidance system, using equal distribution method will fight skill index " hit rate " distribution to self-contained guidance section autocontrol terminal point capture
Destination probability PbWith the hit probability P of the guided missile in the case where autocontrol terminal point normally captures targetd；Missile dispersion error is calculated again,
The missile dispersion error includes that height spreads σdwyError and lateral spreading σdwzError；
Step 3: capturing destination probability P according to autocontrol terminal pointbWith missile dispersion error, navigation error TRANSFER MODEL is established,
By platform navigation error propagation to target error and guided missile error, the navigation error for meeting guided missile acquisition probability requirement is determined；
Step 4: capturing destination probability P according to autocontrol terminal pointbWith missile dispersion error, target location error transmitting mould is established
Missile dispersion error is distributed to carrier aircraft sensor Detection location error, determines the sensing for meeting guided missile acquisition probability requirement by type
Device target location error；
Step 5: according to autocontrol terminal point capture destination probability requirement and missile dispersion error, establishing the task fire control meter of guided missile
Mathematical model is calculated, while analyzing influence target component calculates and the error component of guided missile self-control terminal dispersion, using Monte Carlo
Method is emulated, and determines the fire control attack error met the requirements；
Step 6: navigation error, sensor target position error, fire control the attack error determined in step 3~5 is carried out
Error estimate formula calculates guided missile out of bound probability, verifies whether to meet war skill index " hit rate " requirement, completes entirely to be based on OODA ring
The closed-Loop Analysis of road avionics system Key Performance Indicator.
According to features described above, computed altitude spreads σ in the step 2dwyError and lateral spreading σdwzThe method of error are as follows:
(1) destination probability P is captured in autocontrol terminal pointbIn the case where determination, guided missile acquisition domain is equivalent to rectangle, using etc.
Probability assignments method calculates self-contained guidance section height acquisition probability P in conjunction with gaussian distribution tablebyWith lateral acquisition probability Pbz, capture
The height that point allows spreads σbyWith lateral spreading σbz；
(2) in hit probability PdIn the case where determination, guided missile acquisition domain is equivalent to rectangle, using equiprobability distribution method,
In conjunction with gaussian distribution table, terminal guidance section height hit probability P is calculateddyWith lateral hit probability Pdz, the point of impact allow height dissipate
Cloth σdyWith lateral spreading σdz；
(3) equiprobability distribution method is used, the height that capture point is allowed spreads σbyWith lateral spreading σbzIt is evenly distributed to mesh
It marks on position error and other error sources, calculates height and spread σdwyError and lateral spreading σdwzError.
According to features described above, the step 3 specifically includes:
(1) principle of stacking is transmitted according to navigation error, establishes navigation error TRANSFER MODEL, aircraft platform navigation error is folded
It is added on missile position error and target location error；
(2) destination probability P is captured with the autocontrol terminal point of guided missile self-contained guidance sectionbAs the binding target of navigation error, build
Vertical Missile Terminal Guidance joins probabilistic mathematical models, and calculating meets guided missile capture destination probability PbNavigation error.
According to features described above, the step 4 specifically includes:
(1) height in step 2 is spread by σ using equal distribution methoddwyError and lateral spreading σdwzError is distributed to carrier aircraft
Sensor detecting error, while Error Propagation Model is established, calculate sensor distance measurement error σR, orientation detection error σμ
And pitching detecting error σv；
(2) use equal distribution method by range measurement error σR, orientation detection error σμAnd pitching detecting error σvContinue to distribute
To the radar system, electro-optical system and electronic warfare system to carrier aircraft, war skill index and guided missile capture target are calculated while met
The sensor target position error of probability, the sensor target position error include that the target range of each sensor subsystem is surveyed
Measure error σ1R, object position-sensitive detecting error σ1μAnd target pitch detecting error σ1v。
The invention has the benefit that a kind of avionics system Key Performance Indicator based on OODA loop proposed by the present invention
Analysis method can carry out the analysis and simulation calculation of science, by aircraft platform to the factor for influencing avionics system precision
The war skill index " hit rate " of task level is converted to the performance indicator requirement of the key function of avionics system level, supports avionics
The error analysis and assessment of the Key Performance Indicators such as system navigator fix, target acquisition, fire control attack, the system of not only increasing are set
Efficiency is counted, system complexity is reduced, can effectively support avionics system comprehensive design, and the development cycle can be shortened, is saved
About development cost.
Detailed description of the invention
Fig. 1 is a kind of flow diagram of avionics system Key Performance Indicator analysis method based on OODA loop；
Fig. 2 is that OODA recycles schematic diagram；
Fig. 3 is that guided missile error propagation is superimposed schematic diagram；
Fig. 4 is error estimate formula flow chart.
Specific implementation
Present pre-ferred embodiments are provided with reference to the accompanying drawing, in order to explain the technical scheme of the invention in detail.
As shown in the illustrated embodiment of fig. 1, the method for the present invention is started with from top layer war skill index " hit rate ", is appointed in conjunction with airborne combat
Business feature and OODA loop theory (as shown in Figure 2) are chosen the avionics system critical performance parameters in OODA loop, are then used
The method distributed paragraph by paragraph carries out precision analysis, determines navigation positioning error, sensor target position error, fire control attack error etc.
Key Performance Indicator；The required precision of each performance indicator is finally subjected to error estimate formula again, verifies whether to meet war skill index,
Realize the closed-Loop Analysis that error estimate formula is assigned to from error.Steps are as follows for the realization of the embodiment:
Step 1: being directed to a certain combat duty of aircraft platform, OODA ring task process is data acquisition (O), situation recognizes
(O), tactical decision (D), plan execute (A).The representative key performance indicator chosen in OODA ring carries out precision analysis, in this example
Navigation positioning error, sensor target position error, fire control attack error are chosen as analysis target；Wherein, navigator fix misses
Difference is the error of data acquisition (O) link, and sensor target position error is data acquisition link (O) and situation recognizes link
(D) composition error, it is the composition error that tactical decision (certainly D) and plan execute (A) link that error is attacked in fire control.
Step 2: " self-contained guidance+final homing guidance " used according to avionics weapon system in aircraft platform combat duty
Two-part guidance system, the precision of self-contained guidance section influences capture of the guided missile to target, and the precision of terminal guidance section directly affects
Hit of the guided missile to target.
(1) war skill index " hit rate " P is distributed to the autocontrol terminal point capture of guided missile self-contained guidance section using equal distribution method
Destination probability PbWith the hit probability P of the guided missile in the case where autocontrol terminal point normally captures targetd, while assuming that missile dispersion takes
From normal distribution；
(2) destination probability P is captured in guided missile self-contained guidance sectionbIn the case where determination, guided missile capture point allows to spread master
To depend on the acquisition domain of guided missile.Guided missile acquisition domain is equivalent to rectangle, equiprobability distribution method is equally used, in conjunction with normal distribution
Table calculates self-contained guidance section height acquisition probability PbyWith lateral acquisition probability Pbz, the height distribution σ of capture point permissionbyWith it is lateral
Spread σbz；
(3) in Missile Terminal Guidance section hit probability PdIn the case where determination, principle calculates terminal guidance section height and drags out a miserable existence with (2)
Middle probability PdyWith lateral hit probability Pdz, the height distribution σ of point of impact permissiondyWith lateral spreading σdz；
(4) missile dispersion error σdwIt is to influence guided missile self-contained guidance section capture destination probability PbMain error source, use
Equiprobability distribution method, the height that guided missile self-contained guidance section capture point is allowed spread σbyWith lateral spreading σbzIt is evenly distributed to mesh
It marks on position error and other error sources, missile dispersion error can be calculated, missile dispersion error includes that height spreads σdwyError
With lateral spreading σdwzError；
Step 3: capturing destination probability P according to autocontrol terminal pointbWith missile dispersion error, analysis generates the main of navigation error
Navigation error TRANSFER MODEL is established in source, and by platform navigation error propagation to target error and guided missile error, determination meets guided missile
The navigation error that acquisition probability requires.Specifically:
(1) principle of stacking is transmitted according to navigation error, shown in schematic diagram 3, establishes navigation error TRANSFER MODEL, aircraft is put down
Platform navigation error is added on missile position error and target location error.
(2) destination probability P is captured with the autocontrol terminal point of guided missile self-contained guidance sectionbAs the binding target of navigation error, build
Vertical Missile Terminal Guidance joins probabilistic mathematical models, and calculating meets guided missile capture destination probability PbNavigation error.
Step 4: being required according to guided missile capture destination probability and missile dispersion error, analysis generate the master of target location error
Source is wanted, target location error TRANSFER MODEL is established, the missile dispersion error determined according to war skill index " hit rate " is distributed
To carrier aircraft sensor Detection location error, determine that the carrier aircraft sensor Detection location error for meeting guided missile acquisition probability requirement is wanted
It asks.The main error for wherein influencing target location error has carrier aircraft sensor Detection location error, target data transmission delay to miss
Difference, solution of fire control error, carrier aircraft stability error and missile borne system position error etc., selective analysis carrier aircraft sensor detects here
Position error.
(1) the missile dispersion error σ that will be calculated in step 2 using equal distribution methoddwyAnd σdwzDistribution to carrier aircraft senses
Device detecting error, while Error Propagation Model is established, sensor distance measurement error σ can be calculatedR, orientation detection error σμ
And pitching detecting error σv；
(2) use equal distribution method by sensor distance measurement error σ calculated in (1)R, orientation detection error σμAnd it bows
Face upward detecting error σvContinue to be assigned to the radar system, electro-optical system and electronic warfare system of carrier aircraft, calculates while meeting war
The target location error of skill index and guided missile capture destination probability, including each sensor subsystem (i.e. radar system, electro-optical system
And electronic warfare system) target distance measurement error σ1R, object position-sensitive detecting error σ1μAnd target pitch detecting error σ1v。
Step 5: being required and missile dispersion error, analyzing influence task Fire control calculation precision according to guided missile capture destination probability
Principal element, establish the task Fire control calculation mathematical model of guided missile, while analyzing influence target component calculates and guided missile automatic control
The error component of end-point distribution, is emulated using Monte Carlo method, and determination meets navigation error, sensor target position error
It is required that fire control attack error requirements.The main error of influence task Fire control calculation precision has sensor parameters measurement error, bullet
Road handles error, display position error, pilot's aim bias, boresight error etc., and this example selective analysis sensor parameters are surveyed
The influence that amount error attacks fire control indicates that precision is attacked in fire control with the azimuth-range error of guided missile self-control terminal dispersion.
According to Ground-attack by Helicopter principle, task Fire control calculation mathematical model is established, utilizes mesh calculated in step 4
Mark position error σ1R、σ1μAnd σ1v, the azimuth-range error of guided missile self-control terminal dispersion can be calculated, i.e. fire control attack misses
Difference.
Step 6: by step 1~5 determine navigation error, sensor target position error (including sensor distance survey
Measure error, orientation detection error and pitching detecting error), fire control attack error (orientation including guided missile self-control terminal dispersion and
Range error) required precision carry out error estimate formula, calculate guided missile out of bound probability, verify whether meet war skill index " hit rate "
It is required that how to meet, then above-mentioned each Key Performance Indicator requires to can be used as the foundation for instructing avionics system comprehensive design；If discontented
Foot, then need again iteration to be calculated.Error estimate formula flow chart is as shown in Figure 4.
It, can according to the technique and scheme of the present invention and its hair it is understood that for those of ordinary skills
Bright design is subject to equivalent substitution or change, and all these changes or replacement all should belong to the guarantor of appended claims of the invention
Protect range.
Claims (4)
1. a kind of avionics system Key Performance Indicator analysis method based on OODA loop comprising the steps of:
Step 1: being directed to a certain combat duty of aircraft platform, carry out OODA loop analysis, choose navigation positioning error as data
Obtain the error of link, composition error of the sensor target position error as data acquisition link and situation cognition link, fire
Control attack error executes the composition error of link as tactical decision and plan；
Step 2: according to the two of " self-contained guidance+final homing guidance " that avionics weapon system in aircraft platform combat duty uses
War skill index " hit rate " is distributed to the autocontrol terminal point of self-contained guidance section using equal distribution method and captures target by segmentation guidance system
Probability PbWith the hit probability P of the guided missile in the case where autocontrol terminal point normally captures targetd, then missile dispersion error is calculated, it is described
Missile dispersion error includes that height spreads σdwyError and lateral spreading σdwzError；
Step 3: capturing destination probability P according to autocontrol terminal pointbWith missile dispersion error, navigation error TRANSFER MODEL is established, by platform
Navigation error is transmitted to target error and guided missile error, determines the navigation error for meeting guided missile acquisition probability requirement；
Step 4: capturing destination probability P according to autocontrol terminal pointbWith missile dispersion error, target location error TRANSFER MODEL is established, it will
Missile dispersion error is distributed to carrier aircraft sensor Detection location error, determines the sensor target for meeting guided missile acquisition probability requirement
Position error；
Step 5: according to autocontrol terminal point capture destination probability requirement and missile dispersion error, establishing the task Fire control calculation number of guided missile
Learn model, while analyzing influence target component calculate and guided missile self-control terminal dispersion error component, using Monte Carlo method into
Row emulation determines the fire control attack error met the requirements；
Step 6: navigation error, sensor target position error, fire control the attack error determined in step 3~5 is subjected to error
Synthesis calculates guided missile out of bound probability, verifies whether to meet war skill index " hit rate " requirement, completes entirely to navigate based on OODA loop
The closed-Loop Analysis of electric system Key Performance Indicator.
2. a kind of avionics system Key Performance Indicator analysis method based on OODA loop according to claim 1, special
Sign is in the step 2 that computed altitude spreads σdwyError and lateral spreading σdwzThe method of error are as follows:
(1) destination probability P is captured in autocontrol terminal pointbIn the case where determination, guided missile acquisition domain is equivalent to rectangle, using equiprobability
Distribution method calculates self-contained guidance section height acquisition probability P in conjunction with gaussian distribution tablebyWith lateral acquisition probability Pbz, capture point permit
Perhaps height spreads σbyWith lateral spreading σbz；
(2) in hit probability PdIn the case where determination, guided missile acquisition domain is equivalent to rectangle, using equiprobability distribution method, in conjunction with just
State distribution table calculates terminal guidance section height hit probability PdyWith lateral hit probability Pdz, the height distribution σ of point of impact permissiondyWith
Lateral spreading σdz；
(3) equiprobability distribution method is used, the height that capture point is allowed spreads σbyWith lateral spreading σbzIt is fixed to be evenly distributed to target
In position error and other error sources, calculates height and spread σdwyError and lateral spreading σdwzError.
3. a kind of avionics system Key Performance Indicator analysis method based on OODA loop according to claim 1, special
Sign is that the step 3 specifically includes:
(1) principle of stacking is transmitted according to navigation error, establishes navigation error TRANSFER MODEL, aircraft platform navigation error is added to
In missile position error and target location error；
(2) destination probability P is captured with the autocontrol terminal point of guided missile self-contained guidance sectionbAs the binding target of navigation error, guided missile is established
Terminal guidance joins probabilistic mathematical models, and calculating meets guided missile capture destination probability PbNavigation error.
4. a kind of avionics system Key Performance Indicator analysis method based on OODA loop according to claim 1, special
Sign is that the step 4 specifically includes:
(1) height in step 2 is spread by σ using equal distribution methoddwyError and lateral spreading σdwzError is distributed to carrier aircraft and is sensed
Device detecting error, while Error Propagation Model is established, calculate sensor distance measurement error σR, orientation detection error σμAnd it bows
Face upward detecting error σv；
(2) use equal distribution method by range measurement error σR, orientation detection error σμAnd pitching detecting error σvContinue to be assigned to load
Radar system, electro-optical system and the electronic warfare system of machine, calculate while meeting war skill index and guided missile captures destination probability
Sensor target position error, the sensor target position error include the target distance measurement error of each sensor subsystem
σ1R, object position-sensitive detecting error σ1μAnd target pitch detecting error σ1v。
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| CN107065566B (en) * | 2017-05-19 | 2020-04-24 | 北京理工大学 | Missile control system each link error distribution method |
| CN108413985B (en) * | 2018-03-05 | 2020-03-03 | 北京润科通用技术有限公司 | System and method for acquiring boresight data and carrying equipment |
| CN108920827A (en) * | 2018-07-03 | 2018-11-30 | 中国人民解放军陆军装甲兵学院 | Burst-firing hit rate test method |
| CN109871634B (en) * | 2019-03-04 | 2022-12-02 | 中国人民解放军海军航空大学 | Method for calculating bullet-taking demand under conventional attack mode of unmanned aerial vehicle group missile |
| CN114353827A (en) * | 2021-12-09 | 2022-04-15 | 中国空间技术研究院 | Method for analyzing matching of space-based information timeliness and accurate guidance parameters |
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| CN102495622A (en) * | 2011-11-30 | 2012-06-13 | 电子科技大学 | Position loop performance test method of positional servo system and test system thereof |
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