CN114440710B - Damage assessment-oriented heterogeneous fine missile before-group-launching collaborative planning method - Google Patents
Damage assessment-oriented heterogeneous fine missile before-group-launching collaborative planning method Download PDFInfo
- Publication number
- CN114440710B CN114440710B CN202210068554.XA CN202210068554A CN114440710B CN 114440710 B CN114440710 B CN 114440710B CN 202210068554 A CN202210068554 A CN 202210068554A CN 114440710 B CN114440710 B CN 114440710B
- Authority
- CN
- China
- Prior art keywords
- fine
- missile
- time
- guided
- launching
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G3/00—Aiming or laying means
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention discloses a damage evaluation-oriented heterogeneous fine missile before-group-launching collaborative planning method. The invention carries out collaborative planning before guided launch in space and time on the projectile group from the position of the target, the medicament launching point position and the predicted flight time of each kind of fine missile, the self detection load condition of the missile, and the like, determines reasonable launching time and sequence according to the difference of the penetration and damage prevention capability, the maneuvering capability, the damage capability and the detection load of each missile, ensures the penetration and damage prevention effect of the whole projectile group and the quality of the obtained damage evaluation information, provides detailed data for the effect evaluation of the cooperative operation of heterogeneous fine guided projectile groups, and can effectively improve the subsequent evaluation precision.
Description
Technical Field
The invention relates to the technical field of heterogeneous fine missile group collaborative planning, in particular to a damage evaluation-oriented heterogeneous fine missile group pre-launching collaborative planning method.
Background
The heterogeneous fine missile group collaborative planning mainly realizes the preset targets of improving the missile defense penetration probability, reducing the miss distance of the missile and the like through reasonable pre-shooting collaborative planning and the on-board planning promotion in the flight process, and improves the overall operational efficiency of the missile group. According to different strike tasks, the pre-shooting collaborative planning of the heterogeneous fine guidance projectile group needs to be adjusted to a certain extent, and the strike time and the position of each node in the projectile group are ensured to meet the requirements of the strike tasks.
The damage effect evaluation on the complex target is mainly divided into four parts of research contents, namely target analysis, physical damage effect analysis, mapping relation analysis and functional damage effect aggregate analysis. The target analysis is the basis of damage effect evaluation, provides data support for subsequent physical damage and functional damage, and mainly analyzes the structure and characteristics of a target and the function expressed by the structure characteristics. The physical damage effect analysis refers to evaluating the damage condition of a target in a physical sense, and factors such as battlefield environment, firepower strength, target characteristics and the like need to be comprehensively considered. The mapping relationship from physical damage to functional damage is the most difficult problem in the evaluation process, the physical damage degree, the battlefield environment, the structure of a building, the personnel composition in the building, the psychological quality and the like are comprehensively considered, the relationship is generally described by the fuzzy mathematics theory, but an accurate conclusion is difficult to be obtained. The aggregate analysis of the function damage effect is to aggregate the function damage of a single target upwards on the basis of target analysis to finally obtain the reduction degree of the whole function.
The research content needs to be deeply analyzed based on the existing experimental damage data of the weaponry and the detected damage condition of the target. The more the missile-borne sensors acquire and transmit the more target damage information, the more accurate damage evaluation results can be obtained, and therefore, how to obtain more target damage information in one cooperative hitting process becomes a key problem for improving damage evaluation efficiency.
Disclosure of Invention
The invention provides a damage evaluation-oriented heterogeneous smart guided missile group pre-launching collaborative planning method based on a typical scene of multiple heterogeneous smart guided missiles with great differences in penetration capability, damage capability and maneuverability and oriented to complex target damage evaluation, so as to realize efficient damage image acquisition of a hit target as a task target.
The invention relates to a damage evaluation-oriented heterogeneous fine missile before-group-shooting collaborative planning method, which comprises the following steps of:
step 3, dividing the ammunitions in the heterogeneous fine guided ammunitions according to the penetration prevention capability, the damage capability and the maneuvering capability to obtain H-type fine guided ammunitions with strong penetration prevention capability, D-type fine guided ammunitions with strong damage capability and F-type fine guided ammunitions with strong maneuvering capability;
step 4, determining the launching time windows of various ammunitions:
s41, determining the launching time window of the F-type fine-guided ammunition as
Wherein, t 0 A start time that is a predetermined striking period for the target; t is t d A target hitting time window for the heterogeneous fine missile group;
d D the detection distance of the class F fine guided ammunition is obtained, and V is the average flight speed of the class F fine guided ammunition tail section;
s42, determining the hit time window of the H-type fine-guided ammunition as
Then, the emission time window is reversely deduced from the hit time window; wherein, T F The pharmacological thinking trajectory flight time of the class F fine missile;
s43, determining that the hit time window of the D-type fine-guided ammunition is a subset of the hit time window of the H-type fine-guided ammunition, and then reversely deducing the launching time window of the D-type fine-guided ammunition from the hit time window;
step 5, determining the launching time of each fine-guided ammunition:
equally dividing the launching time windows of other types of fine missile medicines except the F type fine missile medicine to obtain launching time and hit time of each batch;
for class F fine missile medicine, the hit time is the time obtained by subtracting the hit time of other fine missile medicines
And then the transmission time is deduced reversely from the hit time.
Preferably, in the step 4, the target time period of other types of fine missile medicines except the H-type fine missile medicine, the D-type fine missile medicine and the F-type fine missile medicine in the heterogeneous fine missile group is obtained according to the tactical planning, and the launching time period is reversely deduced according to the target time period.
Preferably, in the step 5, the method further comprises the following step of adjusting the hit time of the type F smart ammunition:
after the hit time of other fine guided ammunitions is obtained, determining the hit time window of the F-class fine guided ammunition wave number corresponding to the hit time ti for each hit time ti
The hit time of the wave-order F-class fine-guided ammunition is divided into a hit time window; wherein, Δ t 1 And Δ t 2 Are empirical values.
Preferably, in step 43, the arrival time of the 1 st D type guided ammunition is at the same time or after the kth wave H type guided ammunition, wherein k is greater than 1; the arrival time of the last D-type fine guided ammunition is the same as or before the arrival of the last H-type fine guided ammunition.
Preferably, the firing time window of the D-type fine-guided ammunition is
Wherein N is the total striking frequency of H-type fine-guide ammunition; k is the beating wave number of the class H fine missile medicine; t is D The time length of the class D fine missile pharmacology ideal trajectory flight is shown.
Preferably, the number of the F-class fine missile medicines is proportionally distributed according to the proportion of the number of the missiles at each predicted time point.
Preferably, in the step 2, the pre-planned path points of the missiles launched in the same batch cannot be overlapped, and certain safety distances exist between the trajectories of different missiles; the routes of the missiles launched by the same launching platform can be overlapped, but the condition that the routes are crossed pairwise is not allowed to occur; missile routes launched by different launching platforms are not allowed to be overlapped, and route sections are not allowed to intersect pairwise.
Has the advantages that:
the research field of heterogeneous smart projectile group cooperative combat belongs to the more advanced and novel research field in the global scope at present, related theoretical researches are less, and the research directions of specific theories and related technologies are not clear yet. And the collaborative pre-shooting planning of the heterogeneous fine guidance missile groups is the basis and the premise for realizing the on-line planning of the missile groups, and the reasonable design must be carried out according to the actual missile performance parameters and the requirement of the hitting task. The invention provides a damage evaluation-oriented heterogeneous fine missile group before-launching collaborative planning method based on various constraint conditions in practical engineering application situations, and aims to guarantee the damage effect of a missile and improve the quality of acquired target damage information. The method specifically comprises the following steps:
1. the typical scene of the cooperative damage assessment of the bullet group is provided, and the cooperative planning method before the group launching of the heterogeneous smart guided missiles for the damage assessment is provided. In the collaborative planning process, the method fully considers the missile pre-launching constraints in space and time, outputs the launching time of each missile, and ensures that the safe flying distance among the missiles can be kept in the flying process of the missiles.
2. The method of the invention fully considers the flight performance parameters of various missiles and the trajectory characteristics of various missiles, can ensure that a plurality of detection angles which accord with different trajectory characteristics exist simultaneously in the striking process, realizes the multi-angle damage image acquisition of the target, and effectively improves the damage information acquisition amount and the damage information quality.
3. The method ensures that the missiles can strike in batches within a preset striking time period through reasonable batch design of the missile groups; meanwhile, a certain type of fine missile medicine with strong maneuverability is used as a main damage image acquisition node, so that the high maneuverability of the fine missile medicine is fully exerted; the image acquisition time of the type of precisely guided ammunition is distributed at intervals in a preset striking time period, the acquisition amount of the damage image is increased, and the full-flow continuous damage image acquisition in the striking process is realized.
Drawings
Fig. 1 is a diagram of the ideal effect of cooperative planning before projectile shooting.
Fig. 2 is a schematic diagram of the coordinated planning of the time before the projectile is shot.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a damage evaluation-oriented heterogeneous fine missile before-launching collaborative planning method, which is used for carrying out spatial and temporal guided launch before-launching collaborative planning on a missile group according to the position of a strike target, the launching point position and the predicted flight time of various fine missile types, the self-detection load condition of a missile and the like under the condition that the attack target and the preset strike time of the missile group are set. The collaborative planning method before guided launch in space mainly comprises two parts of contents: firstly, the missile preset drop point area must be highly coincided with the position of a damaged target to ensure that the missile can hit the target; and secondly, the trajectory of each missile is required to be ensured to be not coincident in the flying process of each missile, so that the flying safety of each missile is ensured. The cooperative planning method before guided launch in time mainly requires that reasonable launch time and sequence are determined according to different missile penetration abilities, maneuvering abilities, damage abilities and detection loads so as to ensure the penetration and damage effects of the whole missile group and the quality of acquired damage assessment information.
In particular, the method comprises the following steps of,
before the missile is subjected to the cooperative planning before shooting, the direction S of a target hit by a missile group must be set according to strategic tactical requirements T (x T ,y T ,z T ) And a predetermined striking time T to the target des Meanwhile, the existing fire control system of the missile is utilized to calculate and obtain the launching position of the missile. After the target hitting position, the missile launching position and the target hitting time are determined, the damage assessment-oriented missile before-launching collaborative planning is carried out. According toThe difference of the penetration capability, the damage capability and the maneuvering capability of each missile in the heterogeneous fine missile groups divides the missile groups to obtain H-type fine missile medicines with stronger penetration capability, D-type fine missile medicines with stronger damage capability and F-type fine missile medicines with stronger maneuvering capability. Suppose that the heterogeneous fine missile group comprises r H-type fine missile medicines with stronger penetration and prevention capability, s D-type fine missile medicines with stronger damage capability and t F-type fine missile medicines with stronger maneuvering capability.
Firstly, performing pre-shooting time collaborative planning on heterogeneous fine guidance projectile groups. In order to improve the overall penetration prevention and striking effect of the bullet group, the H-type fine missile medicines with strong penetration prevention capability are firstly used for damaging the target, then the D-type fine missile medicines with strong damage capability are used for striking, and finally the F-type fine missile medicines with strong maneuvering capability are used for carrying out cooperative damage evaluation in order to improve the overall damage evaluation efficiency of the bullet group. In order to meet the requirement of the multi-angle detection damage effect of the collaborative damage assessment, in the later stage of saturation attack, it is still required to ensure that the fine guided missiles with different ballistic characteristics provide damage images with different detection angles. Therefore, each missile in the three types of missiles has a certain time difference when hitting the target, and the launching time needs to be planned before launching. The ideal effect of cooperative planning before the group shot is shown in fig. 1.
And performing pre-launching space collaborative planning on the missile groups to realize conflict resolution of the planned trajectories of all the missiles and obtain the planned trajectories of all the missiles.
When the guided missiles are intensively launched and hit, certain safety distance needs to be ensured among the guided missiles, and the flying safety of the guided missiles is ensured. In addition, in the actual combat process, due to changes in the natural environment and the battlefield situation, an obstacle area may be generated. Fine missile medicines flying at high altitude, represented by ballistic missiles and gliding missiles, can directly and suddenly prevent threat areas in the actual combat process due to high flying height and high flying speed. Therefore, only a certain safety distance between different missiles needs to be ensured in the actual pre-shooting collaborative planning process. The influence of natural terrains such as islands and the like needs to be considered for the fine guided ammunition flying at low altitude and sea skimming, represented by the flying missile, and the flying speed is relatively low but the maneuvering capability is strong during flying, so that the path planning can be carried out on the fine guided ammunition before shooting, and the known obstacle area is avoided.
Specifically, on the aspect of engineering implementation, the missile plans a flight trajectory by setting path points, and realizes the pre-shooting collaborative planning of the trajectory, so that the process is constrained under the following constraint conditions:
1) The pre-planned path points of the missiles launched in the same batch cannot be superposed, and certain safety distance d exists between the tracks of different missiles safe I.e. by
In the formula, M ik (x, y, z) refers to the position of a certain missile at a certain moment, wherein i represents the number of the missile, k represents the launching batch for launching the missile, (x, y, z) represents the longitude, latitude and altitude of the position of the missile respectively, and t represents the real time.
Furthermore, the larger the distance Δ d between the positions of different missiles, the better.
max(Δd＝|M ik (x,y,z)-M (i+m)k (x,y,z)| t ),i＝1,2,3,…,k＝1,2,3,…,m＝1,2,3,…
2) For missiles launched successively by the same launching platform, the air paths can be overlapped, but the situation that every two air paths are crossed is not allowed.
In the formula, sigma M ijk (x, y, z) refers to a sequence of positions of a missile, i.e., the trajectory of the missile; j represents the platform number that launched the missile.
3) For missile routes launched by different launching platforms, overlapping and pairwise intersection of route sections are not allowed.
∑M ijk (x,y,z)≠∑M (i+m)(j+n)(k+p) (x,y,z),i＝1,2,3,…,j＝1,2,3,…,k＝1,2,3,…,m＝1,2,3,…,n＝1,2,3,…,p＝0,1,2,3,…
In order to improve the missile defense-outburst probability, all the missiles in the missile group carry out saturation attack on the target, namely all the missiles in the missile group hit the target in a short time period. The lower limit value of the time period is the launching time interval of the isomorphic bombs, the time interval can be regarded as 0s when the launching platform is sufficient, and the upper limit value of the time period can be regarded as the maximum communication distance d of each node of the group of bombs in the subnet c The difference between the target-hit times of the first and last target-hit missiles of the group. The values of class H, class D and class F fine missile drugs can be expressed as:
in the formula, V F 、V H 、V D Respectively represents the average flight speed of class F, class H and class D fine missile medicines.
Thus the predicted hit time window t for the entire heterogeneous shot d Has a maximum value of min (Δ t) F ,Δt H ,Δt D ) The specific value can be set according to the task requirement.
Assuming that the pharmacological ideal trajectory flight time of class H fine missile is T H And the pharmacological thinking trajectory flight time of the D-class fine missile is T D And the pharmacological thinking trajectory flight time of the class F fine missile is T F . From t 0 When the first F type fine guided ammunition is launched at the moment, the expected Hit time point Hit _ time of the guided ammunition F1 Is composed of
Hit_time F1 ＝t 0 +T F
According to the cooperative detection requirement, part of H-class fine guided ammunition and D-class fine guided ammunition hit the aircraft carrier, the F-class fine guided ammunition finishes the detection task, and the flight time is t Fdet Can be determined by the detection distance d of class F fine missile medicines D And the end segment average flying speed V obtains:
therefore, the first class H fine guided missile medicine is predicted to Hit at the time point Hit _ time H1 In the range of
Hit_time H1 ∈(t 0 +T F -t Fdet ,t 0 +T F )
In the formula, the subscript H indicates that the missile is H-type guided ammunition, and the subscript 1 indicates that the missile is H-type guided ammunition hitting the target 1 st.
It transmits a time point Launch _ time H1 In the range of
Launch_time H1 ∈(t 0 +T F -t Fdet -T H ,t 0 +T X -T H )
Setting the distance between the first class-F fine missile medicine and the target when the first class-H fine missile medicine is hit by the target
And at the moment, a plurality of F-type guided ammunitions and not less than 1 gliding or D-type guided ammunition are positioned in a detection mission area (generally determined according to the effective detection distance of a sensor). Therefore, the predicted Hit time Hit _ time of the first H-type guided ammunition can be obtained H1 The time is the predicted hit time point T of the first missile in the heterogeneous missile group des ，
The transmission time point is
The last missile of the heterogeneous missile group hitting the target is an F-class fine missile medicament, and the predicted Hit time point Hit _ time of the missile is Ft Is composed of
In the formula, the subscript F indicates that the missile is F-type guided ammunition, and the subscript t indicates that the missile is t-th targeted F-type guided ammunition, i.e., the last guided ammunition.
Its transmission time point Launch _ time Ft Is composed of
The class F fine missile medicine provides the damage condition that the last class H fine missile medicine hits the target, so the optimal image acquisition time delta t is required to be within 2 Then the target is hit, so when the last H-class fine missile is set to hit the target, the last F-class fine missile is set to be away from the target d D The remaining flight time is t Fdet . The predicted Hit time point Hit _ time of the last type H smart lead ammunition Hr Is composed of
In the formula, the subscript H indicates that the missile is H-type guided ammunition, and the subscript r indicates that the missile is the r-th H-type guided ammunition hitting a target, i.e., the last one.
Backward deducing to obtain its Launch time point Launch _ time Hr Is composed of
At the moment, the projectile group launching time windows of the F-type fine guided ammunition and the H-type fine guided ammunition are determined. Launch time window Launch _ time of class F fine guided missile ammunition F Is composed of
Launch time window Launch _ time of class H fine missile ammunition group H Is composed of
According to the striking requirement, the class-H fine missile medicines arrive in N waves, the specific wave times N are set according to the striking task requirement, the N waves are evenly distributed in a launching time window, and the principle is explained according to the condition that the striking wave times are 5. The number of H-class fine guided ammunition in each wave can be expressed as P = (P) 1 ,p 2 ,…,p N ) Wherein p is i Is [0,1 ]]The number of missiles per wave can be expressed as a value obtained by multiplying the number of the class-H missiles by the proportion sequence P and rounding.
When the K (k =1,2, \ 8230;, N) wave times H class fine missile medicines are Hit, D class fine missile medicines start to arrive one by one, and the first D class fine missile medicine is expected to Hit at the time point Hit _ time D1 Is composed of
Backward deducing to obtain Launch time point Launch _ time D1 Is composed of
Same settingWhen the last D class fine missile medicine hits the target, the last F class fine missile medicine is far away from the target D D The remaining flight time is t Fdet . The last D-class fine guided ammunition and the last H-class fine guided ammunition arrive at the same time, and the Hit time point Hit _ time is predicted Ds Is composed of
The same back-stepping obtains the emission time point of
Then the Launch time window Launch _ time of the class D fine missile ammunition group D Is composed of
So far, the launch time windows and expected hit time windows for all missiles have been obtained as follows:
TABLE 1 time window of launch and predicted time of hit for various classes of missiles
The D-class fine missile medicine is also set to arrive in N waves, and P = (P) 1 ,p 2 ,…,p N ) Wherein p is i Is [0,1 ]]The number of missiles per wave can be expressed as a value obtained by multiplying the number of D-type missiles by the proportion sequence P and rounding. The N wavenumbers are distributed evenly in the emission time window. The predicted hit time points of all D-class fine missile medicines and H-class fine missile medicines are counted to be at most (2N-2), and the predicted hit time points of different batches of partial different classes of fine missile medicines can be repeated.
Number Num of class H fine guided missiles of ith wave Hi The number of the componentsPer Hi And a corresponding predicted Hit time point Hit _ time Hi Can be respectively expressed as
Num Hi ＝round(r·p i ),i＝1,2,…N,
Where round denotes rounding the numbers.
Similarly, the number Num of class D fine guided missiles of the ith wave Di Per in amount Di And a corresponding predicted Hit time point Hit _ time Di Can be respectively expressed as
Num Di ＝round(s·p i ),i＝1,2,…N
And proportionally distributing the number of the F-class fine missile medicines according to the proportion of the number of the missiles at each predicted time point. After each predicted hit time point is determined, the optimal image acquisition time is Δ t before the target is hit by the missile due to damage assessment 1 Δ t after second 2 Second and duration of flight t Fdet Setting the distance target of each class F fine guided missile medicine when acquiring the image
A remaining flight time of
Due to the actual flight duration and ideal trajectory of each missileThe time length has a certain difference, the actual hitting time points of the H-type fine guided ammunition and the D-type fine guided ammunition can be considered to be normally distributed according to the expected hitting time point, and the maximum difference of the expected hitting time point is delta t (delta t is less than or equal to 10 s). Accordingly, the corresponding task time periods of the F-class fine guided missiles can be obtained. It is worth noting that due to the requirement of the saturation striking time, partial overlapping of each task time period may exist, and at the time, damage assessment tasks of the same batch of H-type/D-type fine missile medicines are allowed to be completed cooperatively by different batches of F-type fine missile medicines.
Per is the ratio of the quantity of class F fine missile medicines according to the z wave order Fz The number Num can be obtained Fz And a corresponding task period Dec _ time Fz Can be respectively expressed as
Per Fz ＝Per Hi Or Per Du ,i＝1,2,…N,u＝1,2,…N,z＝1,2,…(2N-2)
Num Fz ＝round(t·Per Fz ),z＝1,2,…(2N-2)
Or
In the formula, the wave number z of the F-type guided ammunition is the sum of the wave numbers of the H-type guided ammunition and the D-type guided ammunition, namely z = i + u.
And F-class fine guided ammunition is properly shared to execute the detection task, so that the F-class fine guided ammunition in each corresponding task time period is set to be evenly distributed on the expected hit time sequence. Therefore, the expected hit time point corresponding to each class F fine missile medicine can be determined, and the expected trajectory flight time T can be determined according to the class F fine missile pharmacology F And (5) obtaining an F-class fine guided missile medicine launching time sequence by reverse pushing.
In practical engineering application, after the launching sites and the planned trajectories of all missile nodes in a missile group are determined, a real missile group launching time sequence can be determined according to the predicted flight time of each missile, and the original time plan is finely adjusted. And finishing the cooperation planning before shooting of the heterogeneous fine guidance projectile group. A schematic diagram of the time collaborative planning before the group shot is shown in fig. 2.
In addition, if other types of fine guided ammunitions exist in the heterogeneous fine guided ammunition group besides the H-type fine guided ammunition, the D-type fine guided ammunition and the F-type fine guided ammunition, the hit time period is obtained according to the tactical planning, and then the launching time period is reversely deduced according to the hit time period.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A damage assessment-oriented heterogeneous smart missile before-launching collaborative planning method is characterized by comprising the following steps:
step 1, setting a target hitting direction of a group of bullets and preset target hitting time according to strategic tactical requirements, and calculating to obtain a launching position of the ammunition;
step 2, carrying out space planning before shooting on the ammunition group to obtain a planned track of each ammunition;
step 3, dividing the ammunitions in the heterogeneous fine guided ammunitions according to the penetration prevention capability, the damage capability and the maneuvering capability to obtain H-type fine guided ammunitions with strong penetration prevention capability, D-type fine guided ammunitions with strong damage capability and F-type fine guided ammunitions with strong maneuvering capability;
step 4, determining the launching time windows of various ammunitions:
s41, determining the launching time window of the F-type fine-guided ammunition as
Wherein, t 0 A start time that is a predetermined striking period for the target; t is t d Is different fromA hit time window of the refinement missile group to the target;
d D the detection distance of the class F fine guided ammunition is obtained, and V is the average flight speed of the class F fine guided ammunition tail section;
s42, determining the hit time window of the H-type fine-guided ammunition as
Then, the emission time window is reversely deduced from the hit time window; wherein, T F The pharmacological thinking trajectory flight time of the class F fine missile;
s43, determining that the hit time window of the D-type fine-guided ammunition is a subset of the hit time window of the H-type fine-guided ammunition, and then reversely deducing the launching time window of the D-type fine-guided ammunition from the hit time window; the hit time of the 1 st D type guided ammunition is the same time or later than the kth wave H type guided ammunition, wherein k is more than 1; the hit time of the last D-type fine guided ammunition is the same as or before the arrival of the last H-type fine guided ammunition;
the firing time window of the D-type fine ammunition is
Wherein N is the total striking frequency of H-type fine-guide ammunition; k is the beating wave number of the class H fine missile medicine; t is D The pharmacological thinking trajectory flight time of the D-class fine missile;
step 5, determining the launching time of each fine-guided ammunition:
for other types of fine missile medicines except the F type fine missile medicine, the emission time windows of the fine missile medicines are equally divided to obtain the emission time and the hit time of each batch;
for class F fine missile medicine, the hit time is the time obtained by subtracting the hit time of other fine missile medicines
Then the transmission time is deduced reversely by the hit time.
2. The damage evaluation-oriented heterogeneous fine missile group pre-launching collaborative planning method according to claim 1, wherein in the step 4, other types of fine missile medicines except for H-type fine missile medicines, D-type fine missile medicines and F-type fine missile medicines in the heterogeneous fine missile group are obtained according to tactical planning, and the launching time period is reversely deduced according to the hitting time period.
3. The damage evaluation-oriented collaborative planning method for heterogeneous guided missile group before launching as claimed in claim 1, wherein the step 5 further comprises the adjustment of the hit time of the type F guided ammunition:
after the hit time of other fine guided ammunition is obtained, aiming at each hit time ti, determining the hit time window of the F-class fine guided ammunition wave number corresponding to the hit time ti as
The hit time of the wave-order F-class fine-guided ammunition is divided into a hit time window; wherein, Δ t 1 And Δ t 2 Are empirical values.
4. The damage-assessment-oriented collaborative planning method for heterogeneous fine missile pre-launching according to claim 1, wherein the number of F-class fine missile medicines is proportionally distributed according to the proportion of the number of missiles at each predicted time point.
5. The damage evaluation-oriented collaborative planning method before group launching of heterogeneous smart missiles according to claim 1, wherein in the step 2, pre-planned path points of missiles launched in the same batch cannot be overlapped, and certain safe distances exist between trajectories of different missiles; the routes of the missiles launched by the same launching platform in sequence can be overlapped, but the condition that the routes are crossed pairwise is not allowed to occur; missile routes launched by different launching platforms are not allowed to overlap, and route sections are not allowed to intersect pairwise.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210068554.XA CN114440710B (en) | 2022-01-20 | 2022-01-20 | Damage assessment-oriented heterogeneous fine missile before-group-launching collaborative planning method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210068554.XA CN114440710B (en) | 2022-01-20 | 2022-01-20 | Damage assessment-oriented heterogeneous fine missile before-group-launching collaborative planning method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114440710A CN114440710A (en) | 2022-05-06 |
| CN114440710B true CN114440710B (en) | 2022-11-25 |
Family
ID=81367366
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210068554.XA Active CN114440710B (en) | 2022-01-20 | 2022-01-20 | Damage assessment-oriented heterogeneous fine missile before-group-launching collaborative planning method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114440710B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114818545A (en) * | 2022-06-01 | 2022-07-29 | 中国人民解放军海军工程大学 | Weapon system coordination optimization method based on underwater continuous emission multiphase flow influence |
| CN115660444B (en) * | 2022-12-02 | 2023-08-15 | 中国兵器科学研究院 | Defensive control method and device, electronic equipment and storage medium |
| CN115879327B (en) * | 2023-02-24 | 2023-05-30 | 山东捷瑞数字科技股份有限公司 | Digital twinning-based damage efficiency evaluation method, device, equipment and medium |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB591803A (en) * | 1938-06-25 | 1947-08-29 | Marian Poraj Jankowski | Range computing device for artillery co-operating with aerial observation |
| US6474592B1 (en) * | 2001-05-25 | 2002-11-05 | Tadiran Spectralink Ltd. | System and method for munition impact assessment |
| US9779191B1 (en) * | 2014-02-20 | 2017-10-03 | Raytheon Company | Method for non-kinetic performance assessment |
| CN108509728A (en) * | 2018-04-04 | 2018-09-07 | 西北工业大学 | One kind weighing design method to extra large cooperation aircraft viability |
| CN110017729A (en) * | 2019-04-18 | 2019-07-16 | 西安交通大学 | A kind of more guided missile time coordination method of guidance with impingement angle constraint |
| CN110163502A (en) * | 2019-05-21 | 2019-08-23 | 北京壹氢科技有限公司 | A kind of more bullet collaboration multistage target assignment methods |
| CN112902767A (en) * | 2021-01-28 | 2021-06-04 | 西安交通大学 | Multi-missile time collaborative missile guidance method and system |
-
2022
- 2022-01-20 CN CN202210068554.XA patent/CN114440710B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB591803A (en) * | 1938-06-25 | 1947-08-29 | Marian Poraj Jankowski | Range computing device for artillery co-operating with aerial observation |
| US6474592B1 (en) * | 2001-05-25 | 2002-11-05 | Tadiran Spectralink Ltd. | System and method for munition impact assessment |
| US9779191B1 (en) * | 2014-02-20 | 2017-10-03 | Raytheon Company | Method for non-kinetic performance assessment |
| CN108509728A (en) * | 2018-04-04 | 2018-09-07 | 西北工业大学 | One kind weighing design method to extra large cooperation aircraft viability |
| CN110017729A (en) * | 2019-04-18 | 2019-07-16 | 西安交通大学 | A kind of more guided missile time coordination method of guidance with impingement angle constraint |
| CN110163502A (en) * | 2019-05-21 | 2019-08-23 | 北京壹氢科技有限公司 | A kind of more bullet collaboration multistage target assignment methods |
| CN112902767A (en) * | 2021-01-28 | 2021-06-04 | 西安交通大学 | Multi-missile time collaborative missile guidance method and system |
Non-Patent Citations (2)
| Title |
|---|
| 巡航导弹协同作战任务规划需求;张勇志等;《飞航导弹》;20120615(第06期);第32-36页 * |
| 飞航导弹协同作战信息化体系构建及分布式仿真;万建平;《教练机》;20111215(第04期);第20-24页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114440710A (en) | 2022-05-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114440710B (en) | Damage assessment-oriented heterogeneous fine missile before-group-launching collaborative planning method | |
| CN109740876A (en) | Target threat judgment method | |
| CN109708537B (en) | Unmanned aerial vehicle group joint search attack route planning method | |
| CN114442666B (en) | Heterogeneous fine guidance projectile group collaborative damage assessment method | |
| CN111649624A (en) | Space miniature precise guided weapon control method | |
| Gordon | The Vulture and the Snake: Counter-Guerrilla Air Warfare: The War in Southern Lebanon | |
| Bertram | New Conventional Weapons and East-West Security | |
| RU2775903C1 (en) | Method for destruction of underground targets by missiles separated from launch vehicle | |
| DE69717488T2 (en) | METHOD FOR THE FLIGHT TRACK CORRECTION OF A BULLET OF A PROTECTOR, A MORTAR OR A ROCKET LAUNCHER OR THE LIKE | |
| Banasik | Trends in the Development of Russian Precision-Guided Weapons | |
| GULYÁS | Ground surveillance and target acquisition system in the Royal Artillery | |
| RU2280836C1 (en) | Method for protection of flight vehicles against guided missiles and system for its realization | |
| Cernat | The Potential of Hypersonic Weapons and the Great Military Powers Strategy regarding their Production–Case Study– | |
| Swietochowski et al. | Modernization of the Missile Forces and Artillery | |
| Bronk | 6 How ground-based air defences have shaped the air war over Ukraine | |
| Pan et al. | A Certain Naval Gun on Empty Firing Command Decision Research | |
| Szabo | South African responses to new Soviet air defence systems in Angola in the 1980s | |
| RU42302U1 (en) | MISSILE DEFENSE SYSTEM | |
| Weiss | Comparative Cost and Effectiveness of Manned Aircraft and Guided Missiles in Air Defense | |
| Augustine | Land Warfare | |
| Jefferson | Current and future implications of missile defence effectiveness on air strike missions | |
| Fisher Jr | “One China” and the Military Balance on the Taiwan Strait | |
| Rosier | The Implications for Air Power of Developments in Aircraft and Weapon Technology (I): The Operational View | |
| Loomis et al. | THE FIRE-FIGHT ASSESSMENT IN THE GROUND COMBAT CONFRONTATION (GCC) MODEL | |
| Riggins et al. | Brilliant Attack: The Need for Autonomous Standoff Weapons in Airfield Attack Missions |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |