CN108536951B - A kind of sort method of operational aircraft battlc damagc spare parts different degree - Google Patents
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- 238000000034 method Methods 0.000 title claims abstract description 26
- 230000002147 killing effect Effects 0.000 claims abstract description 78
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- 230000001665 lethal effect Effects 0.000 claims abstract description 54
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- 231100001160 nonlethal Toxicity 0.000 claims description 34
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 29
- 239000002828 fuel tank Substances 0.000 claims description 22
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Abstract
The present invention provides a kind of sort method of operational aircraft battlc damagc spare parts different degree, comprising the following steps: the direction attacked according to aircraft, the initial parameter of definition component killing；Determine the killing probability after each component is hit by n times and survival probability；Determine aircraft is individually present state j and aircraft by the probability of happening for being respectively individually present state after n times strike；The given system performance a for being respectively individually present state jj；Determine the Griffith different degree WI of each remaining lethal components of aircraft1 G(i)；Sequence.Advantage are as follows: the battlc damagc spare parts importance sorting method that the present invention provides, the intermediate state for not only allowing for aircraft also contemplates the performance of aircraft, finally provide the sequence of aircraft battlc damagc spare parts, ranking results are more objective and accurate, after carrying out importance sorting to aircraft battlc damagc spare parts, facilitate the spare parts demand of more simple and quick determination damaged aircraft.
Description
Technical field
The invention belongs to aviation operational aircraft battlc damagc spare parts technical fields, and in particular to a kind of operational aircraft battlc damagc spare parts weight
The sort method to be spent.
Background technique
Battle injury abbreviation war wound refers to aircraft during operational exertion, due to the attack by local weapon system
Make its component wreck or function degradation and influence a kind of state of effective utilization.For damaged aircraft reparation and
Troubleshooting, most rapidly, effectively method is exactly to change part.By the spare part of fast supply abundance, guarantee quickly setting out for aircraft
It is set out with high intensity.It is determined according to aircraft components war wound rule and needs the component that backs up and reasonable spare part amount, it not only can be with
Guarantee that aircraft has enough repairing spare parts in war wound, it is ensured that repair the smooth development of work, and can be to avoid due to standby
Part deposit it is excessive and caused by waste.
In order to solve the type and quantity of spare part needed for wartime, the later period eighties, United States Air Force using computer simulation with
The method that live shell combines, the working hour repaired according to different operation scenes to war wound situation, the war wound of different model aircraft and people
Power and required spare part are studied.The research achievement can neatly analyze various operation scenes, war wound situation, and certainly
Determine wartime spares provisioning requirement, it is highly beneficial to spare part needed for guaranteeing supply in time.United States Air Force uses in robbing repairing type design
One war wound simulator, a war wound repair data library and a repair data memory.The input data packet of war wound simulator
The detailed data of aircraft, missile armament and fuse is included, output data is the survival rate and war wound distribution system of each operational aircraft
Count table.Air force, China formulated " Aircraft Battlefield Repair research program " after 1994, and content includes rational approach etc., it is desirable that
It establishes my army to advocate war machine battle injury prediction model, the research war wound regularity of distribution and war damage, the evaluation criteria of war wound, estimation are existing
Generationization war condition is got off the plane the ratio of war wound and war damage, prediction spare parts consumption etc..
Many scholars proposed and performance-relevant different degree in recent years.System performance is improved for analysis component
It influences, the detailed concept for describing system performance of Griffith.Wu and Chan defines a kind of new different degree utility function,
And introduce the optimal method of the performance function of system polymorphic.In terms of the scholars such as Zio determine railway using different degree method
Order of priority, so as to improve the performance of railway network.The Hu Yifan of Northwestern Polytechnical University is in " aircraft battlc damagc spare parts demand mould
Type " it is middle in conjunction with anti-terrorism system threat characteristic, component war wound probability and spare part type, it has obtained single and has gone out dynamic component war wound
Probability, the method for then using probability theory, establishes the demand model of aircraft battlc damagc spare parts, according to demand model, provides aircraft
The quantity required of battlc damagc spare parts.
To guarantee the Combat readiness of aircraft and continuing fatigue resistance out, need scientifically to determine that the spare part of damaged aircraft needs
It asks.All kinds of battlc damagc spare parts demands provided at present determine method, and the factor of consideration is less, lead to that very cumbersome calculation need to be used
Method just can determine that battlc damagc spare parts demand.
Summary of the invention
In view of the defects existing in the prior art, the present invention provides a kind of sequence side of operational aircraft battlc damagc spare parts different degree
Method can effectively solve the above problems.
The technical solution adopted by the invention is as follows:
The present invention provides a kind of sort method of operational aircraft battlc damagc spare parts different degree, comprising the following steps:
Step 1: establishing the battlc damagc spare parts model of aircraft, comprising:
Aircraft components are divided into lethal components and non-lethal component；Lethal components are further divided into remaining cause
Life property component and non-remaining lethal components；Wherein, remaining lethal components and non-lethal component belong to war wound to be sorted
Spare part；
Assuming that the quantity of remaining lethal components is x, successively it is denoted as: C1、C2,…,Cx；X is even number, also, component C1
With component C2Remaining component each other, component C3With component C4Remaining component each other ..., component Cx-1With component CxRemaining portion each other
Part；
Determine the minimal cut set of remaining lethal components are as follows: { { C1、C2}、{C3、C4},…,{Cx-1、Cx}}；It is caused according to remaining
The minimal cut set of life property component draws aircraft killing tree；
Assuming that the quantity of non-lethal component is y, successively it is denoted as: Cx+1、Cx+2,…,Cx+y；
Step 2: threatening environment when executing task according to aircraft determines the direction that aircraft is attacked；Wherein, aircraft executes
When task threatening environment include: the horizontal distance of aircraft flight speed, flight flying height, aircraft and ack-ack, aircraft with
The offset distance of ack-ack and by the supplementary angle of direction of attack and aircraft direction of advance angle；
Step 3: the direction attacked according to aircraft, the initial parameter of definition component killing；The initial parameter includes: winged
I-th of component C of cycle N and aircraft that machine is subjected in a subtaskiThe probability killedWherein, i ∈ (1,
2,…,x,…,x+y)；In, P indicates that probability, subscript k indicate killing, and i indicates unit number；
Step 4: determining the killing probability after each component is hit by n times and survival probability, comprising:
Aircraft is hit at random by n times, determines that each component meets with the life after n times strike in aircraft using binomial approach
Deposit probability are as follows:
Wherein:Indicate i-th of component C of aircraftiSurvival probability after meeting with n times strike；In, P indicates probability, s table
Show existence, N indicates that the cycle that aircraft is subjected in a subtask, i indicate unit number；
Killing probability of the aircraft by n times strike back part are as follows:
Wherein:Indicate i-th of component C of aircraftiKilling probability after meeting with n times strike；In, P indicates probability, k table
Show killing, N indicates that the cycle that aircraft is subjected in a subtask, i indicate unit number；
The initial parameter that step 3 determines is brought into formula (1) and formula (2), each remaining mortality portion is calculated
Part and each non-lethal component hit by n times after killing probability and survival probability；
For remaining lethal components, after executing step 5, step 6 and step 7, then step 8 is executed；For non-lethal
Component, directly execution step 8；
Step 5: determine aircraft is individually present state j and aircraft by the generation for being respectively individually present state after n times strike
Probability；Wherein j=1,2 ..., M respectively represent aircraft and are respectively individually present state；
Specifically, all killing states of aircraft are determined using permutation and combination method, due to sharing x remaining mortality portion
Part, therefore, the total state that is individually present of aircraft share 2xKind, respectively the status merging for causing aircraft to kill, only aircraft is raw
Deposit and component kill when just consider battlc damagc spare parts, thus obtain aircraft be respectively individually present state n times hit after probability value；
Wherein, for x remaining lethal components, exist with get off the plane existence and component killing be individually present state:
1st kind, only one remaining lethal components are killed, it is assumed that only component CvIt is killed, other x-1 component is complete
Good, aircraft is individually present probability value of the state after n times strike at this time are as follows: component CvKilling probability after being hit by n times
With the product of survival probability of other x-1 intact components after n times strike；
2nd kind, the component that only two remaining lethal components are killed, also, killed is not the component of remaining each other,
Assuming that only component CvWith component CuIt is killed, other x-2 component is intact, and aircraft is individually present state after n times strike at this time
Probability value are as follows: component CvKilling probability after being hit by n timesComponent CuKilling probability after being hit by n timesWith
The product of survival probability of other x-2 intact components after n times strike；
The rest may be inferred
Xth/2-1 kind, the component that only x/2-1 remaining lethal components are killed, also, killed is not remaining portion
Part, at this time aircraft be individually present state n times strike after probability value are as follows: it is each hit by killing component by n times after kill
Hurt the product of the survival probability after probability is hit with each intact component by n times；
Step 6: the given system performance a for being respectively individually present state jj；
Step 7: determining the Griffith different degree of each remaining lethal components of aircraft
Aircraft is making prewar, i-th of component C of aircraftiAvailability Pi1=1；
The state space of remaining lethal components is { 0,1 }, wherein 0 indicates killing state, 1 indicates survival condition；Aircraft
State space is { 0,1,2 ..., M }, i-th of component C of aircraftiGriffith different degreeIt is determined by formula (3):
Wherein: PrN(Φ(1i, X) and=j) it indicates as i-th of component CiWhen in serviceable condition, aircraft is that jth kind is independently deposited
In shape probability of state；PrN(Φ(0i, X) and=j) indicate i-th of component CiWhen killing state, aircraft is that jth kind is individually present state
Probability；Wherein Pr indicates that probability, N indicate the cycle that aircraft is subjected in a subtask, and 1 indicates intact, and 0 indicates to kill
Wound, X indicate component vector, Φ (1i, X) and indicate that aircaft configuration function, j indicate that j-th of aircraft is individually present state；ajIt indicates
System energy；M indicates that aircraft is individually present state sum；
Wherein: PrN(Φ(1i, X)=j) calculation method are as follows: assuming that jth kind is individually present in state, have at X1 component
In serviceable condition, there is x-X1 component to be in killing state, then: for the component of serviceable condition, after enabling it hit by n times
Survival probability is 1, and the killing probability after enabling it hit by n times is 0；For killing the component of state, after meeting with n times strike
Survival probability calculated by formula 1, the killing probability after hitting by n times is calculated by formula 2, is updated to step
Aircraft in 5 is individually present state in the calculation formula of the probability value after n times strike, and calculated result is PrN(Φ(1i,X)
=j)；
PrN(Φ(01, X)=j) calculation method are as follows: assuming that jth kind is individually present in state, there is X1 component to be in
Good state has x-X1 component to be in killing state, then: the component for killing state, the existence after enabling it hit by n times
Probability is 0, and the killing probability after enabling it hit by n times is 1；Life for the component of serviceable condition, after meeting with n times strike
It deposits probability to calculate by formula 1, the killing probability after hitting by n times is calculated by formula 2, is updated in step 5
Aircraft be individually present state n times strike after probability value calculation formula in, calculated result is PrN(Φ(01, X)=
j)；
Step 8: by step 7, obtaining the Griffith different degree of each remaining lethal componentsIt presses
Griffith different degreeIt is worth descending sequence, as sequence row of the remaining lethal components by different degree from high to low
Column；Then, the killing probability after being hit for each non-lethal component that step 3 is calculated by n times, by by n times
The descending each non-lethal component of sequence of killing probability value after strike, as non-lethal component by different degree from height to
Low sequence arrangement；Finally, the different degree of non-lethal component is below the different degree of remaining lethal components, it as a result, will be non-
Lethal components are arranged in behind all remaining lethal components, thus obtain the ranking results of final each component.
Preferably, in step 1, remaining lethal components include: flight control computer 1, flight control computer 2, left fuel oil
Case, right fuel tank, Left Hand Engine and right engine；Wherein, flight control computer 1 and flight control computer 2 remaining component each other；
Left fuel tank and right fuel tank remaining component each other；Left Hand Engine and right engine remaining component each other；
Non-lethal component includes left air intake duct and right air intake duct.
A kind of sort method of operational aircraft battlc damagc spare parts different degree provided by the invention has the advantage that
The battlc damagc spare parts importance sorting method that the present invention provides, not only allow for aircraft intermediate state also contemplate it is winged
The performance of machine finally provides the sequence of aircraft battlc damagc spare parts, and ranking results are more objective and accurate, is carrying out weight to aircraft battlc damagc spare parts
After spending sequence, facilitate the spare parts demand of more simple and quick determination damaged aircraft.
Detailed description of the invention
Fig. 1 is a kind of flow diagram of the sort method of operational aircraft battlc damagc spare parts different degree provided by the invention.
Fig. 2 is that direction of attack provided by the invention definition is schemed, in figure: AAA is 35mm ack-ack position, and l is aircraft phase
For the horizontal distance of cannon, a is offset distance of the aircraft relative to cannon, and β is aircraft under fire direction and aircraft advance side
To the supplementary angle of angle；
Fig. 3 is simplified aircraft model top view provided by the invention；In figure: symbol B, C, D, F, G, H, I, J, K are winged
The component of machine, wherein B indicates that radar, C indicate that flight control computer 1, D indicate that flight control computer 2, F indicate left air intake duct, G
Indicate that right air intake duct, H indicate that left fuel tank, I indicate that right fuel tank, J indicate that Left Hand Engine, K indicate right engine；
Fig. 4 is to simplify aircraft killing tree.
Specific embodiment
In order to which the technical problems, technical solutions and beneficial effects solved by the present invention is more clearly understood, below in conjunction with
Accompanying drawings and embodiments, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein only to
It explains the present invention, is not intended to limit the present invention.
The battlc damagc spare parts importance sorting method that the present invention provides, not only allow for aircraft intermediate state also contemplate it is winged
The performance of machine finally provides the sequence of aircraft battlc damagc spare parts, and ranking results are more objective and accurate, is carrying out weight to aircraft battlc damagc spare parts
After spending sequence, facilitate the spare parts demand of more simple and quick determination damaged aircraft.
The present embodiment is to illustrate that complicated each component of system polymorphic proposed by the present invention is based on synthesis by taking certain type fighter plane as an example
The battlc damagc spare parts importance sorting of different degree and Griffith different degree.
The present embodiment is to illustrate that complicated each component of system polymorphic proposed by the present invention is based on by taking aircraft as an example
The battlc damagc spare parts importance sorting method of Griffith different degree.
Step 1: establishing the battlc damagc spare parts model of aircraft.
For existing aircraft model, battlc damagc spare parts are determined.Model aircraft such as 3 institute of attached drawing simplified in the present embodiment
Show, aircraft components are divided into lethal components and non-lethal component；Wherein, lethal components are respectively radar B, fly control meter
No. 1 C of calculation machine, No. 2 D of flight control computer, left fuel tank H, right fuel tank I, Left Hand Engine J, right engine K.Non-lethal component
For left air intake duct F, right air intake duct G.Since radar B is non-remaining component, ruined once killing will lead to flight and be urged, therefore, no
Need to consider the sequencing problem to radar.No. 2 D of No. 1 C of flight control computer and flight control computer remaining component each other, left fuel tank H
With right fuel tank I remaining component each other, Left Hand Engine J and right engine K remaining component each other, left air intake duct F and right air intake duct G
Remaining component each other.Determine the battlc damagc spare parts of aircraft, i.e. remaining lethal components and non-lethal component.Battlc damagc spare parts are to fly control
No. 1 C of computer, No. 2 D of flight control computer, left fuel tank H, right fuel tank I, Left Hand Engine J, right engine K, left air intake duct F,
Right air intake duct G.In battlc damagc spare parts, the killing of non-lethal component not will lead to the killing of aircraft, therefore, non-lethal component
Sequence is located at behind all remaining lethal components.
The minimal set that all components for causing aircraft to kill are determined according to remaining lethal components, since remaining component kills
Wound will lead to aircraft killing, and when remaining component all kill just will lead to aircraft and kill, therefore the minimal cut set in the present embodiment
Are as follows: { C, { H, I }, { J, K } } draws aircraft killing tree according to minimal cut set, that is, provides the logical relation of component He the aircraft,
Such as attached drawing 4.
Step 2: threatening environment when executing task according to aircraft determines the direction that aircraft is attacked；Appoint assuming that aircraft executes
Threatening environment is as shown in Figure 2 when business, comprising: ack-ack implements fixed fire to the target aircraft of high 100m, speed 300m/s.In figure
AAA is 35mm ack-ack position, and l is horizontal distance of the aircraft relative to cannon, and a is offset distance of the aircraft relative to cannon
From.β is the supplementary angle in aircraft under fire direction and aircraft direction of advance angle.
Step 3: the direction attacked according to aircraft, the initial parameter of definition component killing.
In the present embodiment, i-th of component C when threatening strike aircraft is giveniKilling probability
Each componentValue is as shown in table 1.
Each component of table 1Value
The range of i is 1~8 in the present embodiment；The cycle N=20 that given aircraft is subjected in this subtask.
Step 4: determining the killing probability after each component is hit by n times and survival probability.
Aircraft is hit at random by n times, the life of aircraft encounter n times strike back part i is determined using binomial approach
Deposit probability are as follows:
In formula (1),Indicate i-th of component C of aircraftiSurvival probability after meeting with n times strike；In, P indicates general
Rate, s indicate existence, and N indicates the cycle that aircraft is subjected in a subtask, and the killing of component i is general when threatening strike aircraft
RateMiddle P indicates probability, and in subscript: k indicates killing, and i indicates unit number.
Killing probability of the aircraft by n times strike back part i are as follows:
In formula (2),Indicate i-th of component C of aircraftiKilling probability after meeting with n times strike；In, P indicates general
Rate, k indicate killing, and N indicates the cycle that aircraft is subjected in a subtask, and the killing of component i is general when threatening strike aircraft
RateMiddle P indicates probability, and in subscript: k indicates killing, and i indicates unit number.
Corresponding data in table 2 is brought into formula (1) and formula (2), each remaining lethal components and each are obtained
Non-lethal component hit by n times after killing probability and survival probability, as shown in table 2.
The each component of table 2 hit by n times after killing probability and survival probability
For remaining lethal components, after executing step 5, step 6 and step 7, then step 8 is executed；For non-lethal
Component, directly execution step 8；
Step 5: determining that be individually present state j and the aircraft of aircraft are respectively individually present state hair by described after n times strike
Raw probability.All existences of aircraft are determined using permutation and combination method, that is, arrange and combine all states being likely to occur, this
In embodiment, aircraft has eight battlc damagc spare parts, wherein there are six lethal components, for six lethal components, aircraft is total
The state of being individually present shares 26=64 kinds.
According to permutation and combination, a component killing, two components killings, three components killings and three or more are respectively obtained
The state of component killing.The component C and D of remaining each otherIt is worth identical, component C, the calculating side of component D can be only considered when analysis
Method is identical as D.
Respectively cause aircraft kill status merging, only aircraft existence and component kill when just consideration battlc damagc spare parts,
It finally obtains and considers that the self-existent state of aircraft of battlc damagc spare parts has 18, i.e. j=1,2 ..., 18.Provide each aircraft
Probability value of the self-existent state after n times strike, as shown in table 3.
Probability value of each state of table 3 after n times strike
Step 6: analysis determines the system performance a for being respectively individually present statej, j=1 therein, 2 ..., M, the present embodiment
In, the j has respectively represented the self-existent 18 kinds of states of aircraft, therefore j=1, and 2 ..., 18.It is independently deposited at described 18 kinds
In the status, system is in the entirely ineffective intermediate state between serviceable condition, therefore 0 < aj≤1.Due to flight control computer 1
Number No. 2 D of C and flight control computer remaining component each other, left fuel tank H and right fuel tank I remaining component each other, Left Hand Engine J and
Right engine K remaining component each other determines that the performance number of each state of system is as shown in table 4 after analyzing.
Step 7: determining the Griffith different degree of each remaining lethal components of aircraft
Determine that Griffith different degree is the killing probability of each component by obtaining, it is true using formula (3) and formula (4)
It is fixed.
The state space of remaining lethal components is { 0,1 }, wherein 0 indicates killing state, 1 indicates survival condition；Aircraft
State space is { 0,1,2 ..., M }, i-th of component C of aircraftiGriffith different degreeIt is determined by formula (3):
In formula (3), PrN(Φ(1i, X) and=j) it indicates as i-th of component CiWhen in serviceable condition, aircraft is that jth kind is only
The probability of vertical existence；PrN(Φ(0i, X) and=j) indicate i-th of component CiWhen killing state, aircraft is that jth kind is individually present
Shape probability of state；Wherein Pr indicates that probability, N indicate the cycle that aircraft is subjected in a subtask, and 1 indicates intact, and 0 indicates
Killing, X indicate component vector, Φ (1i, X) and indicate that aircaft configuration function, j indicate that j-th of aircraft is individually present state；ajTable
Show system energy；M indicates that aircraft is individually present state sum；
It determines the killing probability of No. 1 C of flight control computer: for No. 1 C of flight control computer, calculating PrN(Φ(11, X) and=j) when
Probability existing for each state, then enable in table 2 when being No. 1 C of flight control computer intactThen the killing probability of C is 0 in table 2,
Survival probability is 1, No. 2 D of flight control computer, left fuel tank H, right fuel tank I, Left Hand Engine J and right engine KValue is not
Become, i.e., the killing probability of remaining each component in addition to No. 1 C of flight control computer and survival probability are still the value in table 2, these
Value, which brings table 3 into, can be obtained PrN(Φ(11, X) and=j), as shown in table 4 below.
And PrN(Φ(01, X) and=j) indicate probability existing for each state when No. 1 C killing of flight control computer, then it is enabled in table 1Then the killing probability of No. 1 C of flight control computer is 1 in table 2, survival probability 0, remaining each componentBe worth it is constant, i.e.,
The killing probability and survival probability of remaining each component in addition to No. 1 C of flight control computer are still the value in table 2, its described
Remaining each componentValue brings table 3 into, obtains each state value Pr of No. 1 C of flight control computerN(Φ(01, X) and=j), as shown in table 4.
Each state value calculated result of No. 1 C of 4 flight control computer of table
Based on the identical thought for each state value for determining No. 1 C of flight control computer, each state value of remaining each component is determined,
Determining result is as shown in table 5~9.
Each state value calculated result of No. 2 D of 5 flight control computer of table
Each state value calculated result of the left fuel tank H of table 6
Each state value calculated result of the right fuel tank I of table 7
Each state value calculated result of 8 Left Hand Engine J of table
Each state value calculated result of the right engine K of table 9
Above-mentioned related data is substituted into formula (3), Griffith different degree and the sequence for obtaining each component are as shown in table 10.
The Griffith different degree and sequence of each component of table 10
Step 8: by step 7, obtaining the Griffith different degree of each remaining lethal componentsIt presses
Griffith different degreeIt is worth descending sequence, as sequence row of the remaining lethal components by different degree from high to low
Column；Then, the killing probability after being hit for each non-lethal component that step 3 is calculated by n times, by by n times
The descending each non-lethal component of sequence of killing probability value after strike, as non-lethal component by different degree from height to
Low sequence arrangement；Finally, the different degree of non-lethal component is below the different degree of remaining lethal components, it as a result, will be non-
Lethal components are arranged in behind all remaining lethal components, thus obtain the ranking results of final each component.
In the present embodiment, the different degree of battlc damagc spare parts is respectively Left Hand Engine J, right engine K, right fuel tank from high to low
I, left fuel tank H, No. 1 C or No. 2 D of flight control computer, left air intake duct F, right air intake duct G.
A kind of sort method of operational aircraft battlc damagc spare parts different degree provided by the invention has the advantage that
The battlc damagc spare parts importance sorting method that the present invention provides, not only allow for aircraft intermediate state also contemplate it is winged
The performance of machine finally provides the sequence of aircraft battlc damagc spare parts, and ranking results are more objective and accurate, is carrying out weight to aircraft battlc damagc spare parts
After spending sequence, facilitate the spare parts demand of more simple and quick determination damaged aircraft.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
Depending on protection scope of the present invention.
Claims (1)
1. a kind of sort method of operational aircraft battlc damagc spare parts different degree, which comprises the following steps:
Step 1: establishing the battlc damagc spare parts model of aircraft, comprising:
Aircraft components are divided into lethal components and non-lethal component；Lethal components are further divided into remaining mortality
Component and non-remaining lethal components；Wherein, remaining lethal components and non-lethal component belong to battlc damagc spare parts to be sorted；
Assuming that the quantity of remaining lethal components is x, successively it is denoted as: C1、C2,…,Cx；X is even number, also, component C1The portion and
Part C2Remaining component each other, component C3With component C4Remaining component each other ..., component Cx-1With component CxRemaining component each other；
Determine the minimal cut set of remaining lethal components are as follows: { { C1、C2}、{C3、C4},…,{Cx-1、Cx}}；According to remaining mortality
The minimal cut set of component draws aircraft killing tree；
Assuming that the quantity of non-lethal component is y, successively it is denoted as: Cx+1、Cx+2,…,Cx+y；
Step 2: threatening environment when executing task according to aircraft determines the direction that aircraft is attacked；Wherein, aircraft executes task
When threatening environment include: the horizontal distance of aircraft flight speed, flight flying height, aircraft and ack-ack, aircraft and air defense
The offset distance of cannon and by the supplementary angle of direction of attack and aircraft direction of advance angle；
Step 3: the direction attacked according to aircraft, the initial parameter of definition component killing；The initial parameter includes: that aircraft exists
I-th of the component C of cycle N and aircraft being subjected in one subtaskiThe probability killedWherein, i ∈ (1,2 ...,
x,…,x+y)；In, P indicates that probability, subscript k indicate killing, and i indicates unit number；
Step 4: determining the killing probability after each component is hit by n times and survival probability, comprising:
Aircraft is hit at random by n times, and the existence for determining that each component is met with after n times strike in aircraft using binomial approach is general
Rate are as follows:
Wherein:Indicate i-th of component C of aircraftiSurvival probability after meeting with n times strike；In, P indicates that probability, s indicate life
It deposits, N indicates that the cycle that aircraft is subjected in a subtask, i indicate unit number；
Killing probability of the aircraft by n times strike back part are as follows:
Wherein:Indicate i-th of component C of aircraftiKilling probability after meeting with n times strike；In, P indicates probability, and k expression is killed
Wound, N indicate that the cycle that aircraft is subjected in a subtask, i indicate unit number；
By step 3 determine initial parameter bring into formula (1) and formula (2), be calculated each remaining lethal components with
And each non-lethal component hit by n times after killing probability and survival probability；
For remaining lethal components, after executing step 5, step 6 and step 7, then step 8 is executed；For non-lethal component,
Directly execute step 8；
Step 5: determine aircraft is individually present state j and aircraft by the probability of happening for being respectively individually present state after n times strike；
Wherein j=1,2 ..., M respectively represent aircraft and are respectively individually present state；
Specifically, all killing states of aircraft are determined using permutation and combination method, due to sharing x remaining lethal components, because
This, the total state that is individually present of aircraft shares 2xKind, respectively the status merging for causing aircraft to kill, only aircraft existence and portion
Battlc damagc spare parts are just considered when part kills, and are thus obtained aircraft and are respectively individually present probability value of the state after n times strike；
Wherein, for x remaining lethal components, exist with get off the plane existence and component killing be individually present state:
1st kind, only one remaining lethal components are killed, it is assumed that only component CvIt is killed, other x-1 component is intact, at this time
Aircraft is individually present probability value of the state after n times strike are as follows: component CvKilling probability after being hit by n timesWith other x-
The product of survival probability of 1 intact component after n times strike；
2nd kind, the component that only two remaining lethal components are killed, also, killed is not the component of remaining each other, it is assumed that
Only component CvWith component CuIt is killed, other x-2 component is intact, and aircraft is individually present probability of the state after n times strike at this time
Value are as follows: component CvKilling probability after being hit by n timesComponent CuKilling probability after being hit by n timesWith other
The product of survival probability of the x-2 intact components after n times strike；
The rest may be inferred
Xth/2-1 kind, the component that only x/2-1 remaining lethal components are killed, also, killed is not remaining component, this
Shi Feiji be individually present state n times strike after probability value are as follows: it is each hit by killing component by n times after killing probability
The product of survival probability after being hit with each intact component by n times；
Step 6: the given system performance a for being respectively individually present state jj；
Step 7: determining the Griffith different degree of each remaining lethal components of aircraft
Aircraft is making prewar, i-th of component C of aircraftiAvailability Pi1=1；
The state space of remaining lethal components is { 0,1 }, wherein 0 indicates killing state, 1 indicates survival condition；Aircraft state
Space is { 0,1,2 ..., M }, i-th of component C of aircraftiGriffith different degreeIt is determined by formula (3):
Wherein: PrN(Φ(1i, X) and=j) it indicates as i-th of component CiWhen in serviceable condition, aircraft is that jth kind is individually present shape
Probability of state；PrN(Φ(0i, X) and=j) indicate i-th of component CiWhen killing state, aircraft is that jth kind is individually present the general of state
Rate；Wherein Pr indicates that probability, N indicate the cycle that aircraft is subjected in a subtask, and 1 indicates intact, and 0 indicates killing, X table
Show component vector, Φ (1i, X) and indicate that aircaft configuration function, j indicate that j-th of aircraft is individually present state；ajIndicate system
Energy；M indicates that aircraft is individually present state sum；
Wherein: PrN(Φ(1i, X)=j) calculation method are as follows: assuming that jth kind is individually present in state, there is X1 component to be in
Good state has x-X1 component to be in killing state, then: the existence for the component of serviceable condition, after enabling it hit by n times
Probability is 1, and the killing probability after enabling it hit by n times is 0；For killing the component of state, the life after meeting with n times strike
It deposits probability to calculate by formula 1, the killing probability after hitting by n times is calculated by formula 2, is updated in step 5
Aircraft be individually present state n times strike after probability value calculation formula in, calculated result is PrN(Φ(1i, X)=
j)；
PrN(Φ(01, X)=j) calculation method are as follows: assuming that jth kind is individually present in state, there is X1 component to be in intact shape
State has x-X1 component to be in killing state, then: the component for killing state, the survival probability after enabling it hit by n times
It is 0, the killing probability after enabling it hit by n times is 1；For the component of serviceable condition, the existence after meeting with n times strike is general
Rate is calculated by formula 1, and the killing probability after hitting by n times is calculated by formula 2, is updated in step 5 and is flown
Machine is individually present state in the calculation formula of the probability value after n times strike, and calculated result is PrN(Φ(01, X) and=j)；
Step 8: by step 7, obtaining the Griffith different degree of each remaining lethal componentsBy Griffith weight
It spendsIt is worth descending sequence, as sequence arrangement of the remaining lethal components by different degree from high to low；Then, right
Killing probability after each non-lethal component that step 3 is calculated is hit by n times, by killing after being hit by n times
Hurt the descending each non-lethal component of sequence of probability value, as sequence row of the non-lethal component by different degree from high to low
Column；Finally, the different degree of non-lethal component is below the different degree of remaining lethal components, as a result, by non-lethal component
It is arranged in behind all remaining lethal components, thus obtains the ranking results of final each component；
Wherein, in step 1, remaining lethal components include: flight control computer 1, flight control computer 2, left fuel tank, right combustion
Fuel tank, Left Hand Engine and right engine；Wherein, flight control computer 1 and flight control computer 2 remaining component each other；Left fuel oil
Case and right fuel tank remaining component each other；Left Hand Engine and right engine remaining component each other；Non-lethal component include it is left into
Air flue and right air intake duct.
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