A launch vehicle separation body impact area automatic planning method

Abstract

The application provides a launch vehicle separation body fall area automatic planning method, which comprises the following steps: determining an initial launch point, obtaining a relative position between a fall area center point of each stage separation body and the initial launch point, and obtaining a trajectory line of an arrow down point; taking a current calculated landing point of any stage separation body as a starting point, translating the fall area of the stage separation body, and identifying a safety element in the fall area of the stage by using geographic information technology. The application adopts the geographic information technology to establish a safety element information base, obtains the fall area information of each stage separation body through trajectory calculation, automatically identifies and counts the geographic information in the automatic tour of each stage fall area, compares and optimizes each flight fall area scheme by using a decision support technology, selects an optimal flight fall area scheme, and determines a suitable launch point, so that the fall area automatic planning of the separation body is completed under any launch point condition, and the taskless demand of the fall area is met.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of launch vehicle general and trajectory, and particularly relates to a launch vehicle separation body landing area automatic planning method. BACKGROUND

[0002] The safety of the landing area is an important factor affecting the launch task of the launch vehicle, and is related to the selection of the launch site, the design of the trajectory, and the like, so that the acquisition, analysis and selection of the safety situation of the landing area are important contents of the safety plan for the implementation of the launch task. For the launch task of an arbitrary launch site, the selection of the landing area of the separation body becomes more complex. In recent years, the rapid development of the social economy in the traditional landing area region, the continuous expansion of the spacecraft orbit and task, and the great changes in the internal and external safety environment of the space launch have increased the difficulty of the safety identification, planning and evaluation of the landing area, and the traditional landing area survey method is not feasible. The current analysis and planning method is mainly manual work on the map, which is difficult to comprehensively and dynamically reflect the actual situation of the involved elements, the tools and drawings are not uniform, the analysis results lack comparability, and the landing area planning cannot be quickly adjusted. Moreover, the collection of related information is more difficult, and the safety analysis of the landing area has increasingly become an important factor affecting the selection of the launch scheme.

[0003] When the launch point is fixed, the theoretical landing area needs to be surveyed before each launch to ensure that the safety situation in the landing area of the separation body is good or the population in the landing area of the separation body is cleared before the launch. For the launch task of an arbitrary launch site, the launch preparation time is generally short, and it is difficult to realize the field landing area survey, which cannot meet the task-free demand of the landing area. SUMMARY

[0004] In view of the existing launch vehicle separation body landing area planning technology, a launch vehicle separation body landing area automatic planning method is proposed, which can automatically evaluate the safety situation of the landing area and automatically plan a reasonable separation body landing area scheme under the condition of an arbitrary launch point, complete the automatic planning of the separation body landing area, and meet the task-free demand of the landing area.

[0005] To achieve the above purpose, the launch vehicle separation body landing area automatic planning method proposed by the present application is characterized by comprising the following steps:

[0006] An initial launch point is determined, target trajectory information, general parameters, launch point longitude and latitude parameters are input for trajectory calculation, the relative positions of the center points of the landing areas of each stage separation body and the initial launch point are obtained, and the trajectory line of the launch point and the point under the rocket are obtained.

[0007] The current calculated landing point of any one of the separation bodies at any level is taken as the starting point, and the landing area of the level is translated, and in the automatic cruising process of the landing area of the level, the safety elements in the landing area of the level are identified by using geographic information technology; whether the safety situation of the landing area of the level meets the requirements is judged according to the safety element weight distribution, if it meets the requirements, the landing area of other level separation body or the landing point of other level separation body and the trajectory line of the landing point of the arrow are determined according to the landing point position of the level separation body, and whether the safety situation of the landing area of other level separation body or the landing point of other level separation body and the trajectory line of the landing point of the arrow meets the requirements is judged, if they all meet the requirements, the first landing area scheme is determined; the next landing area scheme is found by continuous cruising; if the safety situation of the landing area of the level or the landing area of other level separation body or the landing point of other level separation body and the trajectory line of the landing point of the arrow does not meet the requirements, the cruising is continued until the landing area scheme meeting the requirements is found; the safety element information in the landing area range of each level separation body and the launch point is judged to select a plurality of landing area schemes meeting the safety situation requirements of the landing area.

[0008] The landing area information of the plurality of landing area schemes is collected, classified and managed, the safety situation, the trajectory scheme, the arrival time from the current position of the initial launch point to the target launch point of each landing area scheme are compared and analyzed by using decision support technology, and the most reasonable scheme is selected.

[0009] Further, the landing point currently calculated by the current calculation of any one of the separation bodies at any level is taken as the starting point, and any one of the separation bodies is preferably a second level separation body.

[0010] The landing area of other level separation body or the landing point of other level separation body, wherein the landing area of other level separation body is a first level separation body landing area, and the landing point of other level separation body is a third level separation body landing point.

[0011] Further, the safety elements include: expressways, national highways, railways, cities, train stations, airports, offshore drilling platforms, scenic spots, strategic facilities, lakes, wind power plants, water power stations, regional population, overseas land and islands.

[0012] Further, the geographic information technology refers to storing the data information of each safety element into a database according to the geographic information characteristics of different types of safety elements, and when analyzing the safety elements of the landing area, the database can be directly called to acquire, count and analyze the information;

[0013] The storage principle of domestic safety elements is:

[0014] A data is stored every 10km of road or railway (the interval can be widened for approximately straight roads, and the data of road turning needs to be encrypted);

[0015] The latitude and longitude of the storage center point of each county, city and scenic area and the corresponding radius data;

[0016] The latitude and longitude of the storage center point of each township and the corresponding population number;

[0017] At the same time, since the falling area at all levels cannot fall on foreign land and needs to be more than 200 km away from the foreign coastline, the following processing is done on the boundary and each land and coastline of foreign countries and stored in the information database:

[0018] For the boundary line, a coordinate point is stored every 50 km;

[0019] For the foreign coastline, the coastline is extrapolated 200 km, and a coordinate point is stored every 50 km;

[0020] After the above database information is complete, geographic information recognition and statistics are performed to achieve the following purposes:

[0021] For a given falling area range, the safety factor information within the area can be identified and counted;

[0022] For a given three-level falling point, it can be determined whether it is more than 200 km away from the foreign coastline;

[0023] For a given arrow falling point trajectory, it can determine the large cities and prefecture-level cities it passes through, and give the name of the city and the distance between the arrow falling point trajectory and the city center position;

[0024] Give the route planning graph from the initial launch point to each feasible launch point, and calculate the length of different types of roads in each route scheme.

[0025] Further, the selection of a plurality of falling area schemes that meet the safety situation requirements of the falling area includes the rejection of falling area schemes that do not meet the safety situation requirements of the falling area:

[0026] The existence of railways, cities, train stations, airports, offshore drilling platforms, strategic facilities and more than 100,000 people in the falling area of the first and second level separation body is a rejection item;

[0027] The first, second and third level separation bodies on foreign land or within 200 km of the foreign coastline are rejection items;

[0028] The arrow falling point trajectory passes through a large city, which is a rejection item;

[0029] The above rejection items indicate that if the above rejection items exist in the falling area, the falling area scheme is a falling area scheme that does not meet the safety situation requirements of the falling area.

[0030] Further, the security element weight distribution refers to evaluating the security situation in each level of separation body according to the percentage system, 90 and above indicating that the security situation in the falling area is good, 80-90 including 80 indicating that the security situation in the falling area is excellent, 70-80 indicating that the security situation in the falling area is general, and below 70 indicating that the security situation in the falling area is poor.

[0031] Each security element belongs to the reduction item, and the basic score is distributed according to the specific characteristics of each security element, and then the weight distribution of each security element is distributed. (See Table 1 for the basic score and weight distribution of each security element in the falling area.)

[0032] The security element score statistics formula of the first two levels of falling area is as follows:

[0033] y lq =100-(f1·x1+f2·x2+f3·x3+…+f n ·x n )………………(1)

[0034] In the formula:

[0035] y lq —The total score of the security element in the falling area;

[0036] f1, f2, f3, …, f n —The weight distribution value of each security element, taking the value of 0-1;

[0037] x1, x2, x3, …, x n —The basic score of each security element, taking the value of 0-30;

[0038] The third level of separation body is in the form of falling point, and only needs to ensure that it is not in the area within 200km of the foreign coastline;

[0039] (See Table 2 for the weight distribution of the security element of the arrow falling point trajectory.) The security element score statistics formula of the arrow falling point trajectory is as follows:

[0040] y hj =100-(g1·z1+g2·z2+g3·z3+…+g n ·z n )………(2)

[0041] In the formula:

[0042] y hj —The total score of the security element of the arrow falling point trajectory;

[0043] g1, g2, g3, …, g n —The weight distribution value of each security element, taking the value of 0-1;

[0044] z1, z2, z3, …, z n— the basic score of each security element, with a value of 0-30;

[0045] Statistical analysis is performed on the security elements of each separation zone and the trajectory of the impact point, to determine the security situation.

[0046] Further, the decision support technology refers to evaluating and comparing and selecting the optimal security situation of the landing zone, including

[0047] The security situation of each landing zone scheme is comprehensively evaluated, and the security situation evaluation formula is as follows:

[0048] y k =(P1×y lq1jk +P2×y lq2jk +P3×y hjk ) / 3……………………(3)

[0049] In the formula:

[0050] k represents the landing zone scheme k;

[0051] P1, P2, P3 represent the weight distribution of the first separation body, the second separation body, and the trajectory of the impact point, respectively;

[0052] y lq1jk , y lq2jk , y hjk are the statistical results of the security element scores of the first separation body, the second separation body, and the trajectory of the impact point, respectively;

[0053] y k represents the statistical score of the security situation of scheme k, with a value of 0-100.

[0054] The higher the statistical score of the security situation, the safer the landing zone scheme.

[0055] The comparison and selection of the landing zone scheme not only needs to consider the security situation of the landing zone scheme, but also needs to consider the arrival time from the current position of the initial launch point to the target launch point and the ground conditions of the target launch point. The route map from the initial launch point to the target launch point of each scheme is obtained, and the length of the highway route (Lgs k , unit: km), the length of the national and provincial road route (Lgdsd k , unit: km) in each arrival route is obtained, and the driving time of each scheme is obtained:

[0056]

[0057] In the formula:

[0058] V1, V2 are the driving speeds of the launch vehicle on the highway and the national road, respectively.

[0059] The advantages and disadvantages of each landing area scheme can be obtained.

[0060] Q k =y k -q·H k (5)

[0061] In the formula:

[0062] Q k The landing area scheme statistics result of scheme k, taking the value 0-100;

[0063] q - the route time length weight, taking the value 0-1.

[0064] Q k The greater the value, the better the landing area scheme, so that the optimal landing area scheme can be selected.

[0065] The application also provides a computer readable storage medium, characterized in that the computer readable storage medium comprises a stored program, wherein the program executes the above-mentioned automatic planning method for the landing area of a launch vehicle separated body.

[0066] An electronic device is also provided, comprising a memory and a processor, the memory storing a computer program, and the processor being configured to execute the automatic planning method for the landing area of a launch vehicle separated body through the computer program.

[0067] Compared with the prior art, the above technical scheme conceived by the application can achieve the following beneficial effects:

[0068] The application uses geographic information technology to establish a safety factor information library, obtains the landing area information of each separated body through trajectory calculation, performs automatic identification and statistics of geographic information in the automatic cruising process of each landing area, compares and optimizes each landing area scheme by using decision support technology, selects the optimal landing area scheme, and determines the appropriate launch site, so as to complete the automatic planning of the landing area of the separated body under the condition of any launch site and meet the task-free requirement of the landing area. BRIEF DESCRIPTION OF DRAWINGS

[0069] Figure 1 The application provides an automatic planning flowchart for the landing area of a launch vehicle separated body. DETAILED DESCRIPTION

[0070] With reference to the accompanying drawings, the technical solutions in the embodiments of the present application will be clearly and completely described in the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments of the present application, all the other embodiments obtained by a person of ordinary skill in the art without creative effort belong to the protection scope of the present application.

[0071] The embodiments of the present application provide a liquid rocket gust load time domain calculation method, as shown in the following formula: Figure 1

[0072] The following steps are included:

[0073] Step S1

[0074] It is determined that the current location of the launch vehicle is the initial launch point, and the target trajectory information, overall parameters, launch point longitude, latitude and sea level height (referred to as longitude and latitude height) and other parameters are input for trajectory calculation, so as to obtain the relative position of the center point of the falling area of each stage separation body and the initial launch point. The trajectory line of the point under the rocket is the normal projection line of the trajectory of the rocket in the air on the ground.

[0075] Step S2

[0076] The falling point of any stage separation body calculated at present is taken as the starting point, and the falling area of the second stage separation body is translated in the present example. During the automatic tour of the second stage separation body falling area, the safety elements in the second stage separation body falling area are identified by using geographic information technology. Generally, according to the size of the safety falling area frame, the larger the better, and it is considered as the starting point of the tour, i.e. automatic translation. The safety falling area frame of the second stage separation body falling point is larger.

[0077] According to the weight distribution of the safety elements, it can be judged whether the safety situation of the second stage separation body falling area meets the requirements. If it meets the requirements, the falling area of the first stage separation body, the third stage falling point and the trajectory line of the point under the rocket can be determined according to the position of the second stage separation body falling point. Then it is judged whether the safety situation of the falling area of the first stage separation body, the third stage falling point and the trajectory line of the point under the rocket meets the requirements. If all of them meet the requirements, it is determined as the first scheme of the navigation falling area. Then the next navigation falling area scheme is searched by continuing to tour. The searching method is to move the second stage separation body falling point, and according to the length of time required to move the second stage separation body falling point, it is determined to search within a square range of how many kilometers, i.e. according to the length of the driving time of the launch vehicle. If the safety situation of the second stage separation body falling area or the falling area of the first stage separation body, the third stage falling point and the trajectory line of the point under the rocket does not meet the requirements, the tour is continued until the navigation falling area scheme meeting the requirements is found. Generally, the falling area of the first stage separation body is taken as the object of attention, the falling point of the third stage separation body is taken as the object of attention, and the trajectory line of the point under the rocket is taken as the object of attention.​

[0078] By judging the safety factor information in each landing area range and the launch point, a plurality of landing area schemes meeting the safety situation requirements of the landing area can be selected, generally within five, and the landing area cruising range of the secondary separation body is not more than 500km, or 300km. If the population is large, a landing area meeting the safety situation requirements cannot be found, and it must be expanded to 400km.

[0079] Step S3

[0080] The landing area information of each landing area scheme is collected, classified and managed, and the safety situation, trajectory scheme, driving cost from the current position of the launch point to the target launch point, etc. of each scheme are comprehensively compared and analyzed by using decision support technology, and the most reasonable scheme is selected. Then, the launch vehicle is driven to the selected launch point according to the planned route to implement the launch task.

[0081] In step S1:

[0082] For any task of the launch point, a small solid carrier rocket is generally selected, and the launch vehicle can be used as a mobile and launch platform. The current position of the launch vehicle is taken as the initial launch point.

[0083] In step S1:

[0084] The small solid carrier rocket generally has a plurality of separation bodies, such as a first separation body, a second separation body, and a third separation body. The first separation body and the second separation body can be analyzed by shooting according to their position, speed deviation when separating from the carrier rocket, and disturbance during flight, etc. Then, according to the shooting result, a certain range is determined to judge whether the safety situation meets the requirements. The third separation body only needs to judge its landing point position because it has a high separation height, experiences aerodynamic thermal ablation and decomposition during flight, and the landing area is generally overseas. Among them, the first separation body and the second separation body may deviate from the landing point center position due to various reasons, and the area composed of each deviated landing point center position is called the landing area, that is, the relative position of the landing area center point and the launch point. The points in this area may be the position of the landing point relative to the initial launch point when separating.

[0085] In step S2:

[0086] Taking a small solid carrier rocket as an example, the carrier rocket has a first separation body, a second separation body and a third separation body, and the landing area of the second separation body is the primary concern. If there is only one or two separation bodies, one of them is selected as the primary concern.

[0087] In step S2:

[0088] The security elements include highways, national roads, railways, cities, railway stations, airports, offshore drilling platforms, scenic spots, strategic facilities, lakes, wind power plants, hydroelectric power stations, regional population, overseas land and islands, etc.

[0089] The geographic information technology refers to storing the data information of each security element into a database according to the geographic information characteristics of different types of security elements, and directly calling the database to obtain, count and analyze the information when analyzing the security elements in the area.

[0090] The storage principle of the security elements in China is as follows:

[0091] A data is stored every 10 km of road or railway (the interval can be widened for the approximately straight road, and the data of the turning road needs to be encrypted);

[0092] The central point longitude and latitude and the corresponding circle radius data of each county, city and scenic spot are stored (to ensure that the circle can surround the county or city);

[0093] The central point longitude and latitude and the corresponding population of each township are stored.

[0094] Since the security elements at all levels cannot fall on the foreign land, and need to be more than 200 km away from the foreign coastline, the following processing is performed on the border and each land and coastline of the foreign country, and then stored in the information database:

[0095] For the border line (the intersection line of China and foreign land), a coordinate point is stored every 50 km (the interval can be widened for the approximately straight border, and the data of the turning border needs to be encrypted);

[0096] For the foreign coastline, the coastline is extrapolated 200 km, and a coordinate point is stored every 50 km (the interval can be widened for the approximately straight coastline, and the data of the turning border needs to be encrypted).

[0097] After the above database information is complete, the geographic information recognition and counting can be performed, and the following functions can be realized:

[0098] The security element information in the given area of the falling area can be recognized and counted;

[0099] Whether the given three-level falling point is more than 200 km away from the foreign coastline can be judged;

[0100] The large city and prefecture city through which the given arrow falling point trajectory passes can be judged, and the name of the city and the distance between the arrow falling point trajectory and the city center are given;

[0101] The route planning chart from the launching vehicle to each feasible launching point can be given (the expressway, national highway and provincial highway in the route can be classified), and the length of different types of road in each route scheme can be calculated.

[0102] In step S2:

[0103] The existence of railway, city, railway station, airport, offshore drilling platform, strategic facility and population over 100,000 in the first, second and third separated body fall zone is a veto item.

[0104] The first, second and third separated body on foreign land or within 200 km from the foreign coastline is a veto item.

[0105] The trajectory of the arrow point passes through a large city (first-tier city, within 20 km) is a veto item.

[0106] The above veto items mean that if the above veto items exist in the fall zone, the fall zone scheme is not feasible.

[0107] In step S2:

[0108] The safety element weight distribution refers to the evaluation of the safety situation in the first, second and third separated body fall zone according to the percentage system. 90 and above indicates that the fall zone safety situation is good, 80-90 (including 80) indicates that the fall zone safety situation is excellent, 70-80 indicates that the fall zone safety situation is general, and below 70 indicates that the fall zone safety situation is poor.

[0109] Each safety element is a deduction item, and the basic score is distributed according to the specific characteristics of each safety element, and then the weight distribution of each safety element is distributed. The basic score and weight distribution of each safety element in the fall zone are shown in Table 1. The basic score is 1-30 points.

[0110] The safety element score calculation formula of the first two levels of fall zone is as follows:

[0111] y lq =100-(f1·x1+f2·x2+f3·x3+…+f n ·x n )………………(1)

[0112] In the formula:

[0113] y lq —The total score of the fall zone safety element statistics;

[0114] f1, f2, f3, …, f n —The weight distribution of each safety element, the value is 0-1;

[0115] x1, x2, x3, …, x n —The basic score of each safety element, the value is 0-30.

[0116] The third separation body is in the form of a landing point, and only needs to ensure that it is not within 200 km of a foreign coastline.

[0117] Table 1 Weight distribution of each safety element of the landing area

[0118]

[0119]

[0120] The third separation body is in the form of a landing point, and only needs to ensure that it is not within 200 km of a foreign coastline.

[0121] The weight distribution of the arrow landing point trajectory safety element is shown in Table 2. The arrow landing point trajectory safety element score calculation formula is as follows:

[0122] y hj = 100-(g1·z1+g2·z2+g3·z3+…+g n ·z n )………(2)

[0123] In the formula:

[0124] y hj —The total score of the arrow landing point trajectory safety element statistics;

[0125] g1, g2, g3, …, g n —Weight distribution of each safety element, taking values from 0 to 1;

[0126] z1, z2, z3, …, z n —The basic score of each safety element, taking values from 0 to 30.

[0127] Table 2 Weight distribution of the arrow landing point trajectory safety element

[0128]

[0129] The safety elements of each separation body landing area and the arrow landing point trajectory can be statistically analyzed to determine the safety situation. That is, these safety elements are quantified, and the safety of the landing area is evaluated using data.

[0130] Further, in the step S3:

[0131] The decision support technology refers to evaluating and comparing the safety situation of the landing area.

[0132] The safety situation of each landing area scheme is comprehensively evaluated. The safety situation evaluation formula is as follows:

[0133] y k =(P1×y lq1jk +P2×ylq2jk + P3 x y hjk ) / 3 … … (3)

[0134] In the formula:

[0135] k —— represents the landing area scheme k;

[0136] P1, P2, P3 —— respectively represent the weight distribution of the first separation body, the second separation body, and the arrow point trajectory;

[0137] y lq1jk , y lq2jk , y hjk respectively are the safety element score statistical results of the first separation body, the second separation body, and the arrow point trajectory;

[0138] y k —— represents the safety situation statistical score of scheme k, taking values from 0 to 100.

[0139] The higher the safety situation statistical score, the safer the landing area scheme.

[0140] The landing area scheme comparison and optimization needs to consider not only the safety situation of the landing area scheme, but also the driving time from the current position of the launch vehicle to the target launch point (reflecting the road conditions), the ground conditions of the launch point, etc.

[0141] Statistical route map from the launch vehicle location to the launch point of each selected scheme, get the length of the highway route (Lgs k , unit: km), the length of the national road route (Lgdsdk, unit: km). Thus, the driving time of each scheme is obtained:

[0142]

[0143] In the formula:

[0144] V1, V2 —— respectively are the driving speed of the launch vehicle on the highway and the national road.

[0145] Thus, the advantages and disadvantages of each landing area scheme can be obtained:

[0146] Q k = y k -q · H k … (5)

[0147] In the formula:

[0148] Q k —— the landing area scheme statistical result of scheme k, taking values from 0 to 100;

[0149] q —— route time length weight, taking values from 0 to 1.

[0150] Q k The greater, the more optimal the landing area scheme is, thereby the optimal landing area scheme can be selected.

[0151] After the optimal scheme is selected, the launching point and the center landing point of the secondary separation body are taken as the latest input, and the launching vehicle is driven to the launching point to perform the launching task.

[0152] The following examples are given to embody the use effect of the method.

[0153] The specific weight distribution of each safety factor of the landing area is shown in Table 3. The specific weight distribution of the trajectory safety factor of the arrow landing point is shown in Table 4. The data in Table 3 and Table 4 are only examples, and each data needs to be selected according to experience and the importance of each safety factor.

[0154] Table 3: Specific weight distribution of each safety factor of the landing area

[0155]

[0156] Table 4: Specific weight distribution of the trajectory safety factor of the arrow landing point

[0157]

[0158]

[0159] Wherein P1=P3=0.8, P2=1, V1=80km / h, V2=60km / h, q=1.

[0160] Suppose the launching vehicle is in O place, and the trajectory calculation is performed with O place as the launching point, the distance and azimuth of each separation body from the launching point, and the trajectory information of the arrow landing point are obtained. The current secondary landing area is taken as the starting point, and the patrol is performed within a range of 300km. In the automatic patrol process of the secondary separation body landing area, the safety factors in the secondary landing area are identified by using geographic information technology.

[0161] According to the weight distribution of the safety factors, it can be judged whether the safety situation of the secondary separation body landing area meets the requirements. If it meets the requirements, the primary separation body landing area, the tertiary landing point and the trajectory of the arrow landing point can be determined according to the position of the secondary separation body landing point. Then it is judged whether the safety situation of the primary separation body landing area, the tertiary landing point and the trajectory of the arrow landing point meets the requirements. If all meet the requirements, it is determined as the landing area scheme A, and then the next landing area scheme is searched by continuing the patrol. If the safety situation of the secondary landing area or the primary separation body landing area, the tertiary landing point and the trajectory of the arrow landing point does not meet the requirements, the patrol is continued until the landing area scheme meeting the requirements is found.

[0162] According to Figure 1The shown launch vehicle separation body landing area automatic planning process can select three schemes meeting the safety requirements of the flight landing area in the range of 500km, and the specific information is shown in the following table 5.

[0163] According to the formula (1) to formula (5), the advantages and disadvantages of the three flight landing area schemes can be obtained, and from the data in the table, it can be known that the statistical score of scheme C is the highest, and the flight landing area scheme of scheme C can be selected. Then the launch vehicle can be driven to the launch point corresponding to scheme C to perform the launch task.

[0164] Table 5 Comparison of each scheme

[0165]

[0166]

[0167] On the other hand, the application also provides a computer readable storage medium, the computer readable storage medium comprises a stored program, wherein the program executes the above-mentioned launch vehicle separation body landing area automatic planning method.

[0168] The application also provides an electronic device comprising a memory and a processor, characterized in that the memory stores a computer program, and the processor is configured to execute the launch vehicle separation body landing area automatic planning method by using the computer program.

Claims

1. An automatic planning method for the landing area of ​​a launch vehicle's separation body, characterized in that, It comprises the following steps: determining an initial launching point, inputting target trajectory information, overall parameters, launching point longitude, latitude and sea level height parameters to perform trajectory calculation, obtaining a shooting direction, a submunition trajectory and a relative position between a center point of each stage submunition and the initial launching point; taking the currently calculated landing point of any stage submunition as a starting point, translating the landing area of the stage submunition, identifying safe elements in the landing area of the stage submunition in an automatic tour of the landing area of the stage submunition by using geographic information technology, judging whether the safety situation of the landing area of the stage submunition meets the requirements according to the weight distribution of the safe elements, determining the landing areas of other stage submunitions or the landing points of other stage submunitions and the submunition trajectory according to the landing point of the stage submunition if the safety situation meets the requirements, and judging whether the safety situation of the landing areas of other stage submunitions or the landing points of other stage submunitions and the submunition trajectory meets the requirements, and determining a first flight and landing area scheme if the safety situation meets the requirements, continuing to tour to find a next flight and landing area scheme, and continuing to tour until a flight and landing area scheme meeting the requirements is found if the safety situation of the landing area of the stage submunition or the landing areas of other stage submunitions or the landing points of other stage submunitions and the submunition trajectory does not meet the requirements; selecting multiple flight and landing area schemes meeting the safety situation requirements of flight and landing areas by judging the safe element information in the landing area ranges of the stage submunitions and the launching point; collecting, classifying and managing the flight and landing area information of the multiple flight and landing area schemes, and comparing and analyzing the safety situation, the trajectory scheme and the arrival time of the initial launching point to the target launching point of each flight and landing area scheme by using decision support technology to select the most reasonable scheme; the safety element weight distribution refers to evaluating the safety situation in the landing areas of the stage submunitions according to a percentage system, wherein 90 and above indicates that the landing area safety situation is good, 80-90 including 80 indicates that the landing area safety situation is excellent, 70-80 indicates that the landing area safety situation is general, and below 70 indicates that the landing area safety situation is poor; each safety element belongs to a deduction item, and the basic score is distributed according to the specific characteristics of each safety element, and then the weight distribution of each safety element is performed; the landing area safety element score statistical formula is as follows: y lq = 100 - (f1 x1 + f2 x2 + f3 x3 +... + fn xn) (1) n n ) (1)​ in the formula: y lq — the total score of the landing zone safety element statistics; f1, f2, f3...f n — Each security element weight distribution value, value 0-1; x1, x2, x3... x n Each security element base score, value 0-30; the third stage submunition is presented in the form of a landing point, and only needs to be ensured not to be in a region within 200 km of a foreign coastline; the submunition trajectory safety element score statistical formula is as follows: y hj = 100 - (gl - zl + g2 - z2 + g3 - z3 +... + gn - zn) (1) n = 100 - (gl - zl + g2 - z2 + g3 - z3 +... + gn - zn) (1) n )…………(2) in the formula: y hj - the total score of the statistical elements of the trajectory safety factor at the point below the arrow; g1, g2, g3...g n - each security element weight distribution item, taking values from 0 to 1; z1, z2, z3...z n Each security element base score, value 0~30; statistical analysis is performed on the safety elements of each submunition landing area and the submunition trajectory to judge the safety situation thereof; the decision support technology refers to evaluating and comparing and selecting the best flight and landing area safety situation, which comprises comprehensively evaluating the safety situation of each flight and landing area scheme, and the safety situation evaluation formula is as follows: y k = (P1 x y lq1jk + P2 x y lq2jk + P3 x y hjk ) / 3 … … (3) in the formula: k represents the flight and landing area scheme k; P1, P2 and P3 represent the weight distribution of the first stage submunition, the second stage submunition and the submunition trajectory respectively; y lq1jk , y lq2jk , y hjk are respectively the first-order separator, the second-order separator, and the safety element score statistical result of the point-under-arrow trajectory. y k — represents the security situation statistical score of scheme k, taking values from 0 to 100; the higher the safety situation statistical score is, the safer the flight and landing area scheme is; The comparison and optimization of the landing area scheme need to consider the safety situation of the landing area scheme, and also need to consider the arrival time from the current position of the initial shooting point to the target shooting point, and the ground situation of the target shooting point; the route map from the initial shooting point to the target shooting point of each selected scheme is counted, and the length of the highway route Lgs k , unit: km, the length of the national road and provincial road Lgdsd k , unit: km, so as to obtain the length of the arrival time of each scheme: in the formula: V1 and V2 are the driving speeds of the launching vehicle on the expressway and national road respectively; thus, the advantages and disadvantages of each flight and landing area scheme can be obtained: Q k = y k - q H k … (5) in the formula: Q k - the statistical result of the landing area scheme of scheme k, taking values from 0 to 100; q is the route time cost weight, and takes a value of 0-1; Q k The larger indicates that the landing area scheme is better, and thus the optimal landing area scheme is selected.

2. The launch vehicle separation body impact footprint automatic planning method of claim 1, wherein, the drop point of the separation body at any one of the levels is taken as the starting point, and the separation body at any one of the levels is the second-level separation body; the other-level separation body drop zone or other-level separation body drop point, wherein the other-level separation body drop zone is specifically the first-level separation body drop zone, and the other-level separation body drop point is the third-level separation body drop point.

3. The launch vehicle separation body impact footprint automatic planning method of claim 2, wherein, The security elements include highways, national roads, railways, cities, train stations, airports, offshore drilling platforms, scenic spots, strategic facilities, lakes, wind power plants, hydropower stations, regional population, overseas land and islands.

4. The launch vehicle separation body impact footprint automatic planning method of claim 3, wherein, The geographic information technology refers to, for different types of security elements, according to its geographic information characteristics, The security element data information is stored in the database, and when the drop zone security element analysis is performed, the database can be directly called to obtain, count and analyze the information; The storage principle of domestic security elements is: A data is stored every 10km on the road or railway; The central point longitude and latitude and the corresponding circle radius data of each county, city and scenic spot are stored; The central point longitude and latitude and the corresponding population of each township are stored; At the same time, since the drop zone at each level cannot be on foreign land, and needs to be more than 200km away from the foreign coastline, the following processing is performed on the border and each land and coastline of the foreign country before storage in the information database: For the border line, a coordinate point is stored every 50km; For the foreign coastline, the coastline is extrapolated 200km, and a coordinate point is stored every 50km; After the above database information is complete, geographic information recognition and statistics are performed to achieve the following purposes: For a given drop zone range, the security element information in the range can be recognized and counted; For a given third-level drop point, it can be judged whether it is more than 200km away from the foreign coastline; For a given arrow drop point trajectory, it can be judged which large cities and prefecture-level cities it passes through, and the name of the city and the distance between the arrow drop point trajectory and the city center position are given; The route planning diagram from the initial launch point to each feasible launch point is given, and the length of different types of roads in each route scheme is calculated.

5. The launch vehicle separation body impact footprint automatic planning method of claim 4, wherein, The selection of multiple flight drop zone schemes that meet the security situation requirements of the flight drop zone includes the rejection of flight drop zone schemes that do not meet the security situation requirements of the flight drop zone: The existence of railways, cities, train stations, airports, offshore drilling platforms, strategic facilities and a drop zone population exceeding 100,000 in the first and second-level separation body drop zone is a rejection; The first, second and third-level separation bodies on foreign land or within 200km of the foreign coastline are rejections; The arrow drop point trajectory passing through a large city is a rejection; The above rejections indicate that if the above rejections exist in the drop zone of the separation body at this level, the drop zone scheme of the separation body at this level is a flight drop zone scheme that does not meet the security situation requirements of the flight drop zone.

6. A computer readable storage medium, characterized in that, The computer-readable storage medium includes a stored program, wherein the program executes the launch vehicle separation body drop zone automatic planning method described in any one of claims 1 to 5. 7.An electronic device comprising a memory and a processor, the electronic device characterized by, The memory stores a computer program, and the processor is configured to execute the launch vehicle separation body drop zone automatic planning method described in any one of claims 1 to 5 through the computer program.

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