Spaceflight launching station fixed-point selection method and system

Abstract

The invention relates to the technical field of spaceflight launch site design, and discloses a spaceflight launch station fixed point selection method and system, and the method comprises the steps: primarily selecting a launch point as a fixed point according to the development planning information of a spaceflight launch site, and setting a safety range with the fixed point as a circle center and different safety distances as radiuses, whether the requirements for no other spaceflight launching stations, no other spaceflight launching station launching area building facilities, no personnel activity area facilities and no preset important protection facilities are met in the safety range or not is judged in sequence, and whether the launching station adaptive carrier rocket common launching direction determined based on the fixed point meets the preset landing area safety index requirement or not is judged; and when any one is not satisfied, reselecting the fixed point. According to the method, development planning of the spaceflight launching site is fully considered, the safety of testees and facilities is fully guaranteed, meanwhile, other protection targets such as a personnel gathering area close to the launching site are not greatly influenced, and convenience is provided for safe and smooth implementation of spaceflight launching tasks.

Description

Technical Field

[0001] The present invention relates to the technical field of space launch site design, and particularly relates to a method and system for determining a fixed point of a space launch station. Background Art

[0002] A space launch site is a place where launch vehicles and spacecraft are assembled, tested, and fueled for launch, and is the home port for all spacecraft to enter space. A space launch station is the core facility of a space launch site, and specifically implements the test launch of launch vehicles and spacecraft. Currently, space launch missions mainly rely on conventional space launch capabilities. According to the planned requirements, relying on the pre-planned and constructed space launch stations, various civilian, military, and commercial spacecraft are safely and reliably sent into space to complete spacecraft deployment and space infrastructure construction. The fixed point of a space launch station directly affects the long-term development plan of a space launch site and influences the economic development of the flight path and landing area involved in space launches. In the prior art, the selection of the fixed point of a space launch station mainly considers issues such as confidentiality and safety, and does not fully combine the long-term development plan of the space launch site to select the fixed point of the launch station. There is insufficient estimation of possible situations such as the addition of stations and the expansion of facilities in the future launch site, resulting in the inability to meet the synergistic relationship of comprehensive benefits. Summary of the Invention

[0003] In view of this, the present invention provides a method and system for determining a fixed point of a space launch station to solve the deficiencies in the method of determining the fixed point of a space launch station in the prior art.

[0004] In a first aspect, the present invention provides a method for determining a fixed point of a space launch station, the method comprising:

[0005] S1, initially select a launch point as the fixed point according to the development plan information of the space launch site;

[0006] S2, set a first safety range with the fixed point as the center and the first safety distance as the radius, and determine whether the first safety range satisfies that there is no other space launch station within its range; if not, return to S1 to reselect the fixed point, and if so, enter S3;

[0007] S3, set a second safety range with the fixed point as the center and the second safety distance as the radius, and determine whether the second safety range satisfies that there are no building facilities in the launch area of other space launch stations within its range; if not, return to S1 to reselect the fixed point, and if so, enter S4;

[0008] S4, set a third safety range with the fixed point as the center and the third safety distance as the radius, and determine whether the third safety range satisfies that there are no area facilities where people are active during the launch mission within its range; if not, return to S1 to reselect the fixed point, and if so, enter S5;

[0009] S5. With the fixed point as the center and the fourth safety distance as the radius, a fourth safety range is set in the sector area formed by the boundary deviating from the preset angle with the common firing direction of the launch position as the reference. Determine whether there are no preset important protection facilities within the fourth safety range. If not, return to S1 to reselect the fixed point. If so, proceed to S6;

[0010] S6. Determine whether the common firing direction of the launch vehicle adapted to the launch position determined by the fixed point meets the requirements of the preset safety index for the flight and landing area. If not, return to S1 to reselect the fixed point. If so, determine the fixed point as the fixed point of the space launch position.

[0011] The method for selecting the fixed point of the space launch position provided by the embodiment of the present invention conducts a preliminary selection based on the development plan information of the space launch site at the beginning of the fixed point selection, fully considering factors such as the future development direction, scale expansion, and function expansion of the launch site, ensuring that the selected fixed point can adapt to the overall layout and development strategy of the launch site both currently and in the long term in the future, avoiding subsequent repeated construction or renovation caused by unreasonable fixed points. At the same time, it strictly judges the safety index of the flight and landing area of the common firing direction of the launch vehicle adapted to the launch position, ensuring the safety of the flight and landing area during the rocket launch process, avoiding unnecessary damage to the ground, improving the comprehensive benefits of space launch, and having little impact on other protection targets such as the personnel gathering area near the launch point while fully ensuring the safety of the personnel and facilities participating in the test, providing convenience for the safe and smooth implementation of the space launch mission.

[0012] In an optional implementation manner, the first safety distance is determined according to the shock wave overpressure safety distance determined by the maximum filling volume of the launch vehicle. When the rockets are not erected simultaneously at adjacent launch positions, it is the distance corresponding to the first preset value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle; when the rockets are erected simultaneously at adjacent launch positions, it is the distance corresponding to the second value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle, where the first value is greater than the second value.

[0013] The embodiment of the present invention takes into account the two different working conditions of simultaneous and non-simultaneous erection of rockets at adjacent launch positions, and sets different shock wave overpressure safety distances respectively, which can more accurately perform safety protection for the actual possible situations. Because when the rockets are erected simultaneously, once an accident such as an explosion occurs, the influence range and harm degree are different from those when the rockets are not erected simultaneously, which can ensure that the safety risks can be controlled within an acceptable range in various situations. Through this differential safety distance setting, on the basis of ensuring safety, it can better balance the relationship between safety and the utilization of site resources, optimize the allocation of various resources of the space launch site, and improve the overall operation efficiency and economic benefits.

[0014] In an alternative embodiment, the second safety distance is determined based on the maximum filling amount of the launch vehicle to obtain the shock wave overpressure safety distance, which is the distance corresponding to the third preset value of the shock wave overpressure generated when the launch vehicle explodes in place. The third preset value is greater than the second preset value and less than the first preset value.

[0015] In the embodiment of the present invention, the second safety distance ensures that there are no other buildings such as launch area facilities of other space launch sites within this range, which can prevent the shock wave from damaging the surrounding launch area facilities in the event of an accidental explosion during rocket launch, safeguard the integrity and safety of the launch area facilities, and avoid problems such as launch mission delays and equipment losses caused by facility damage. The third preset value is greater than the second preset value when rockets are erected simultaneously at adjacent launch sites and less than the first preset value when rockets are not erected simultaneously at adjacent launch sites. This setting is a balance under different safety scenario requirements. Compared with determining the safety distance based on the first preset value, using the third preset value makes the safety range relatively smaller. While ensuring a certain degree of safety, it can more reasonably utilize the space resources of the space launch site, without causing excessive space waste due to excessive pursuit of safety, improving the space utilization efficiency of the launch site, and being conducive to the overall planning and layout of the launch site.

[0016] In an alternative embodiment, the third safety distance is obtained by determining the shock wave overpressure safety distance based on the maximum filling amount of the launch vehicle, which is the distance corresponding to the second preset value of the shock wave overpressure generated when the launch vehicle explodes in place.

[0017] In the embodiment of the present invention, the third safety distance is determined by the distance corresponding to the second preset value of the shock wave overpressure generated when the launch vehicle explodes in place, which can fully consider the maximum hazard situation that may occur during rocket launch. Ensure that there are no area facilities where people are active within this range, thus effectively avoiding the shock wave generated by extreme situations such as rocket explosion from causing harm to people, and maximizing the protection of the lives of the staff.

[0018] In an alternative embodiment, the shock wave overpressure is determined based on the explosive equivalent of the propellant of the launch vehicle and the distance from the fixed point of the launch site, where the explosive equivalent of the propellant is the sum of the filling amounts of the propellants of the rocket and the spacecraft.

[0019] In an embodiment of the present invention, the sum of the propellant filling amounts of the rocket and the spacecraft is used as the calculation basis for the propellant explosion equivalent, which can comprehensively consider all possible sources of explosion energy in the launch system. The spacecraft also carries a certain amount of propellant, which may also participate in the explosion reaction in certain accidental situations. Such a calculation method avoids the risk of only considering the rocket propellant and ignoring the spacecraft propellant, making the assessment of the explosion equivalent more accurate, and then calculating the shock wave overpressure more precisely, providing a more reliable basis for determining the safety distance and ensuring the launch safety to the greatest extent.

[0020] In an optional embodiment, both the deviation from the preset angle and the fourth safety distance are determined based on the preset safety design criteria for the space launch site.

[0021] The parameters determined based on the safety design criteria in the embodiments of the present invention help to reasonably plan the layout of the launch site facilities. An appropriate deviation from the preset angle and a sufficient fourth safety distance can avoid damage to the infrastructure of the launch site caused by the high temperature, high pressure, vibration, etc. generated during rocket launch, and ensure the integrity and reliability of the launch site facilities.

[0022] In a second aspect, the present invention provides a system for selecting a fixed point for a space launch station, the system includes:

[0023] A fixed-point preliminary selection module, configured to preliminarily select a launch point as the fixed point according to the space launch site development plan information;

[0024] A first safety distance judgment module, configured to set a first safety range with the fixed point as the center and the first safety distance as the radius, and judge whether the first safety range satisfies that there is no other space launch station within its range; if not, return to the fixed-point preliminary selection module to reselect the fixed point, and if satisfied, enter the second safety distance judgment module;

[0025] A second safety distance judgment module, configured to set a second safety range with the fixed point as the center and the second safety distance as the radius, and judge whether the second safety range satisfies that there are no building facilities in the launch area of other space launch stations within its range; if not, return to the fixed-point preliminary selection module to reselect the fixed point, and if satisfied, enter the third safety distance judgment module;

[0026] A third safety distance judgment module, configured to set a third safety range with the fixed point as the center and the third safety distance as the radius, and judge whether the third safety range satisfies that there are no area facilities where people are active during the launch mission within its range; if not, return to the fixed-point preliminary selection module to reselect the fixed point, and if satisfied, enter the fourth safety distance judgment module;

[0027] The fourth safety distance judgment module uses the fixed point as the center and the fourth safety distance as the radius. With the common firing direction of the launch position as the reference, a sector area formed by the boundary deviating from the preset angle is set as the fourth safety range, and it is judged whether there are no preset important protection facilities within the fourth safety range. If not, it returns to the fixed point primary selection module to reselect the fixed point. If satisfied, it enters the flight landing area safety judgment module;

[0028] The flight landing area safety judgment module judges whether the common firing direction of the launch vehicle adapted to the launch position determined by the fixed point meets the requirements of the preset flight landing area safety index. If not, it returns to the fixed point primary selection module to reselect the fixed point. If satisfied, it determines the fixed point as the fixed point of the space launch position.

[0029] In a third aspect, the present invention provides a computer device, including: a memory and a processor, which are communicatively connected to each other. The memory stores computer instructions, and the processor executes the computer instructions to execute the space launch position fixed point selection method according to the first aspect or any corresponding embodiment thereof.

[0030] In a fourth aspect, the present invention provides a computer-readable storage medium, on which computer instructions are stored. The computer instructions are used to cause a computer to execute the space launch position fixed point selection method according to the first aspect or any corresponding embodiment thereof.

[0031] In a fifth aspect, the present invention provides a computer program product, including computer instructions, which are used to cause a computer to execute the space launch position fixed point selection method according to the first aspect or any corresponding embodiment thereof. Description of the Drawings

[0032] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings required for use in the description of the specific embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0033] Figure 1 It is a flowchart of the space launch position fixed point selection method according to an embodiment of the present invention;

[0034] Figure 2 Schematic diagrams of each safety range according to an embodiment of the present invention;

[0035] Figure 3 It is a structural block diagram of the space launch position fixed point selection system according to an embodiment of the present invention;

[0036] Figure 4It is a schematic diagram of the hardware structure of the computer device according to an embodiment of the present invention. Detailed implementation manners

[0037] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some but not all of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0038] To overcome the deficiencies of the prior art, an embodiment of the present invention provides a method for selecting a fixed point for a space launch site. Figure 1 It is a flowchart of the method for selecting a fixed point for a space launch site according to an embodiment of the present invention. As Figure 1 shown, the process includes the following steps:

[0039] S1. According to the development planning information of the space launch site, initially select a launch point as the fixed point.

[0040] In the initial stage of fixed point selection, the embodiment of the present invention makes an initial selection based on the development planning information of the space launch site, fully considering factors such as the future development direction, scale expansion, and function expansion of the launch site, ensuring that the selected fixed point can adapt to the overall layout and development strategy of the launch site both currently and in the long term in the future, and avoiding subsequent repeated construction or renovation caused by unreasonable fixed points.

[0041] S2. Set a first safety range with the fixed point as the center and the first safety distance as the radius, and determine whether the first safety range meets the condition that there is no other space launch site within it; if not, return to S1 to reselect the fixed point, and if so, enter S3.

[0042] By setting the first safety range, the embodiment of the present invention ensures that sufficient safety distances are maintained between different launch sites, avoiding serious impacts on adjacent sites caused by accidents such as explosions and shock waves during the launch of one site, greatly reducing the risk of major accidents caused by mutual interference between sites, and ensuring the safety of the overall operation of the launch site.

[0043] S3. Set a second safety range with the fixed point as the center and the second safety distance as the radius, and determine whether the second safety range meets the condition that there is no building facility in the launch area of other space launch sites within it; if not, return to S1 to reselect the fixed point, and if so, enter S4.

[0044] In the embodiment of the present invention, through the setting of the second safety range, other building facilities in the launch area are excluded from the dangerous area, preventing damage to surrounding important building facilities such as launch towers and measurement and control equipment rooms during the launch process of the launch station, ensuring the integrity and continuous availability of these facilities, and providing a solid foundation for the stable development of the launch mission.

[0045] S4. Set a third safety range with the fixed point as the center and the third safety distance as the radius, and determine whether the third safety range meets the requirement that there are no personnel activity area facilities during the launch mission within its range. If not, return to S1 to reselect the fixed point. If it meets, enter S5;

[0046] In the embodiment of the present invention, through the setting of the third safety range, the area facilities with personnel activities during the launch mission (such as the non-technical area, office area, and living area) are separated from the launch station, effectively avoiding casualties caused by launch accidents to personnel, protecting the lives of staff, technicians, and surrounding residents, and reflecting the high attention to personnel safety.

[0047] S5. Set a fourth safety range with the fixed point as the center, the fourth safety distance as the radius, and form a sector area with the common launch direction of the launch station as the reference and deviating from the preset angle. Determine whether the fourth safety range meets the requirement that there are no preset important protection facilities within it. If not, return to S1 to reselect the fixed point. If it meets, enter S6;

[0048] In the embodiment of the present invention, the fourth safety range is used to protect the preset important protection facilities, avoiding damage to key facilities such as historical relics, important military facilities, and large communication base stations caused by launch activities, and maintaining the safety of important assets at the national and social levels.

[0049] S6. Determine whether the common launch direction of the launch station adapted to the launch vehicle determined by the fixed point meets the requirements of the preset flight landing area safety index. If not, return to S1 to reselect the fixed point. If it meets, determine the fixed point as the fixed point of the space launch station.

[0050] In the embodiment of the present invention, strict judgment is made on the flight landing area safety index of the common launch direction of the launch station adapted to the launch vehicle to ensure that it meets the preset requirements and satisfies the safety needs in multiple aspects. This not only ensures the safety of the flight landing area during the rocket launch process and avoids unnecessary damage to the ground. At the same time, when selecting the location of the launch station, it is also necessary to consider as much as possible to meet the requirements of high launch efficiency, wide launch direction range, being conducive to ecological protection, and meeting the requirements of rocket and spacecraft transportation, testing, launch, measurement, recovery, etc., to ensure high comprehensive launch efficiency.

[0051] The method for fixed-point selection of a space launch station provided by the embodiments of the present invention fully considers the development plan of the space launch site. While fully ensuring the safety of the personnel and facilities participating in the test, it does not cause a great impact on other protection targets such as the personnel gathering area near the launch point, providing convenience for the safe and smooth implementation of the space launch mission.

[0052] In the embodiments of the present invention, the first safety distance, the second safety distance, the third safety distance, and the fourth safety distance are all determined according to the shock wave overpressure safety distance determined by the maximum filling amount of the launch vehicle.

[0053] In one embodiment, the first safety distance in step S2 is determined according to the shock wave overpressure safety distance determined by the maximum filling amount of the launch vehicle. When the rockets are not erected simultaneously at adjacent launch stations, it is the distance corresponding to the first preset value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle; when the rockets are erected simultaneously at adjacent launch stations, it is the distance corresponding to the second value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle, where the first value is greater than the second value. For example, when the rockets are erected simultaneously, the shock wave overpressure safety distance is the distance corresponding to a shock wave overpressure of 0.015 MPa generated by the in-situ explosion of the launch vehicle; when the rockets are erected simultaneously, the shock wave overpressure safety distance is the distance corresponding to a shock wave overpressure of 0.003 MPa generated by the in-situ explosion of the launch vehicle.

[0054] The embodiments of the present invention consider the two different working conditions of simultaneous and non-simultaneous erection of rockets at adjacent launch stations, and set different shock wave overpressure safety distances respectively, which can more accurately perform safety protection for the actual possible situations. When the rockets are erected simultaneously at adjacent launch stations, due to the increase in the number of rockets, the hazards such as shock waves generated by the explosion may be superimposed on each other, and the influence range is larger. At this time, setting a relatively large safety distance can effectively reduce the risk of the chain reaction of an accident at one station to another station and avoid the expansion of the accident. Through this differential safety distance setting, on the basis of ensuring safety, it is possible to better balance the relationship between safety and the utilization of site resources, optimize the allocation of various resources in the space launch site, and improve the overall operation efficiency and economic benefits.

[0055] In one embodiment, the second safety distance in step S3 is determined according to the shock wave overpressure safety distance determined by the maximum filling amount of the launch vehicle. It is the distance corresponding to the third preset value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle, where the third preset value is greater than the second preset value and less than the first preset value. For example, it is the distance corresponding to a shock wave overpressure of 0.0062 MPa generated by the in-situ explosion of the launch vehicle.

[0056] The overpressure of the shock wave generated when the rocket explodes at the launch site has different impacts on the surrounding area under different circumstances. The third preset value corresponding to the second safety distance is determined based on the actual possible risk scenarios. In this scenario, both the safety of the facilities at the launch site itself and the relative positional relationship with the surrounding buildings such as facilities in the launch area need to be considered. Determining the safety distance based on this specific overpressure value can more precisely adapt to this risk scenario and provide more targeted safety protection for the launch activity. By clarifying this specific safety distance, a series of risks that may be caused by the shock wave can be effectively reduced, such as economic losses due to facility damage and the impact of facility failures on subsequent launch missions. Ensuring that there are no relevant buildings within this distance range can greatly reduce the possibility of these risks occurring and ensure the smooth progress of space launch activities and the safe operation of the entire launch site.

[0057] In one embodiment, the third safety distance in step S4 is obtained by determining the shock wave overpressure safety distance according to the maximum filling amount of the launch vehicle. It is the distance corresponding to the second preset value of the shock wave overpressure generated when the launch vehicle explodes at the launch site. For example, it is the distance corresponding to the shock wave overpressure of 0.003 MPa generated when the launch vehicle explodes at the launch site.

[0058] The embodiment of the present invention determines the third safety distance based on the distance corresponding to the second preset value of the shock wave overpressure generated when the launch vehicle explodes at the launch site, which can fully consider the maximum harmful situation that may occur during the rocket launch process. Ensure that within this range, there are no area facilities where people are active, thereby effectively avoiding the harm caused by the shock wave generated by extreme situations such as rocket explosions to personnel and maximizing the protection of the lives of the staff.

[0059] It should be noted that the shock wave overpressure is a relational expression between the TNT equivalent (propellant explosion equivalent) of the launch vehicle and the distance from the fixed point of the launch site. When 1 ≤ R / W 13 ≤ 15, the expression of the shock wave overpressure ΔP r is:

[0060]

[0061] where ΔP r is the shock wave overpressure generated at a place where the distance from the center point of the diversion trough is R when the launch vehicle explodes at the launch site; W is the explosion equivalent (TNT equivalent, unit: kg); R is the distance from the center point of the diversion trough (unit: m).

[0062] When R / W 1 / 3 > 15, the expression of the shock wave overpressure is:

[0063]

[0064] In an embodiment of the present invention, according to the types of propellants for each stage of the rocket, the maximum filling amount of the rocket, the propellant equivalent coefficient of the rocket, the types of propellants for the spacecraft, the maximum filling amount of the spacecraft, and the propellant equivalent coefficient of the spacecraft, the TNT equivalent W when a single rocket is launched is calculated. From a safety perspective, in the embodiments of the present invention, regardless of whether high-energy propellants are used in the launch vehicle, they are all calculated by superposition. That is, according to the types of propellants, weights, and corresponding equivalent coefficients of the rocket and the spacecraft, the propellant amounts of the launch vehicle and the spacecraft are calculated separately, and then added together. The formula is expressed as:

[0065]

[0066] In the formula: W represents the overall calculated propellant amount (TNT equivalent), in kg; W i represents the propellant weight of the i-th stage of the launch vehicle, in kg; k i represents the propellant equivalent coefficient of the i-th stage of the launch vehicle; W j represents the propellant weight of the j-th spacecraft, in kg; k j represents the propellant equivalent coefficient of the j-th spacecraft.

[0067] In an embodiment of the present invention, the sum of the propellant filling amounts of the rocket and the spacecraft is used as the basis for calculating the propellant explosion equivalent, which can comprehensively consider all possible sources of explosion energy in the launch system. The spacecraft also carries a certain amount of propellants, which may also participate in the explosion reaction in some accidental situations. Such a calculation method avoids the risk of only considering the rocket propellants and ignoring the spacecraft propellants, making the assessment of the explosion equivalent more accurate, and then calculating the shock wave overpressure more precisely, providing a more reliable basis for determining the safety distance. Combining with the distance from the fixed point of the launch position to determine the shock wave overpressure can reflect the differences in the explosion effects at different positions. The farther away from the launch position, the smaller the shock wave overpressure usually is. Through this correlation, the safety levels of different regions can be accurately determined, providing a scientific basis for the layout of the facilities around the launch site and the demarcation of the personnel activity range.

[0068] In one embodiment, both the deviation from the preset angle and the fourth safety distance in step S5 are determined based on the preset safety design criteria for the space launch site. In the embodiments of the present invention, according to the requirements of the "Safety Design Criteria for Space Launch Sites", as Figure 2 shown, taking the common launch direction of the launch position as the reference, the fan-shaped area formed by the boundaries deviating by ±18°, and the fourth safety distance is not less than 5 km.

[0069] In the embodiments of the present invention, by considering the common launch directions of the launch positions and setting the preset angular boundary sector regions, it helps to select a fixed point that can achieve high launch efficiency and a wide launch direction range. A reasonable launch direction range can better meet the launch requirements of different types of spacecraft, improve the flexibility and adaptability of rocket launches, while increasing the launch efficiency, reducing the launch cost, and enhancing the economic benefits of space launches.

[0070] In this embodiment, a system for selecting a fixed point of a space launch position is also provided. This system is used to implement the above-mentioned embodiments and preferred implementation manners, and those that have been described will not be repeated. As used hereinafter, the term "module" can be a combination of software and / or hardware that can achieve a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, implementation in hardware, or a combination of software and hardware is also possible and contemplated.

[0071] Embodiments of the present invention provide a system for selecting a fixed point of a space launch position, as Figure 3 shown, including:

[0072] A fixed point preliminary selection module, configured to preliminarily select a launch point as the fixed point according to the development planning information of the space launch site;

[0073] A first safety distance judgment module, configured to set a first safety range with the fixed point as the center and the first safety distance as the radius, and judge whether the first safety range satisfies that there is no other space launch position within its range; if not, return to the fixed point preliminary selection module to reselect the fixed point, and if satisfied, enter the second safety distance judgment module;

[0074] A second safety distance judgment module, configured to set a second safety range with the fixed point as the center and the second safety distance as the radius, and judge whether the second safety range satisfies that there are no building facilities in the launch area of other space launch positions within its range; if not, return to the fixed point preliminary selection module to reselect the fixed point, and if satisfied, enter the third safety distance judgment module;

[0075] A third safety distance judgment module, configured to set a third safety range with the fixed point as the center and the third safety distance as the radius, and judge whether the third safety range satisfies that there are no area facilities where people are active during the launch mission within its range; if not, return to the fixed point preliminary selection module to reselect the fixed point, and if satisfied, enter the fourth safety distance judgment module;

[0076] A fourth safety distance judgment module, configured to set a fourth safety range with the fixed point as the center, the fourth safety distance as the radius, and the common launch direction of the launch position as the reference, and the boundary formed by deviating from the preset angle to form a sector region, and judge whether the fourth safety range satisfies that there are no preset important protection facilities within it; if not, return to the fixed point preliminary selection module to reselect the fixed point, and if satisfied, enter the safety judgment module of the reentry area;

[0077] The flight landing area safety judgment module judges whether the common launch directions of the launch vehicle adapted to the launch site determined by the fixed point meet the requirements of the preset flight landing area safety index. If not, it returns to the fixed point preliminary selection module to reselect the fixed point. If it meets the requirements, it determines the fixed point as the space launch site fixed point.

[0078] In some alternative embodiments, the first safety distance is determined according to the shock wave overpressure safety distance determined by the maximum fuel filling amount of the launch vehicle. When the adjacent launch sites do not erect rockets simultaneously, it is the distance corresponding to the first preset value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle. When the adjacent launch sites erect rockets simultaneously, it is the distance corresponding to the second value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle, where the first value is greater than the second value.

[0079] In some alternative embodiments, the second safety distance is determined according to the shock wave overpressure safety distance determined by the maximum fuel filling amount of the launch vehicle. It is the distance corresponding to the third preset value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle, and the third preset value is greater than the second preset value and less than the first preset value.

[0080] In some alternative embodiments, the third safety distance is obtained according to the shock wave overpressure safety distance determined by the maximum fuel filling amount of the launch vehicle. It is the distance corresponding to the second preset value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle.

[0081] In some alternative embodiments, the shock wave overpressure is determined according to the propellant explosion equivalent of the launch vehicle and the distance from the fixed point of the launch site, where the propellant explosion equivalent is the sum of the fuel filling amounts of the rocket and the spacecraft.

[0082] In some alternative embodiments, both the deviation from the preset angle and the fourth safety distance are determined based on the preset space launch site safety design criteria.

[0083] The further function descriptions of the above-mentioned various modules and units are the same as those in the corresponding embodiments above, and will not be elaborated here.

[0084] The method and device for selecting the fixed point of the space launch site in this embodiment are presented in the form of functional units. Here, the unit refers to an ASIC (Application Specific Integrated Circuit) circuit, a processor and a memory that execute one or more software or fixed programs, and / or other devices that can provide the above functions.

[0085] The embodiment of the present invention also provides a computer device having the above Figure 3 shown space launch site fixed point selection system.

[0086] Please refer to Figure 4 , Figure 4 which is a schematic structural diagram of a computer device provided by an alternative embodiment of the present invention. As Figure 4 shown, the computer device includes: one or more processors 10, a memory 20, and interfaces for connecting various components, including a high-speed interface and a low-speed interface. Each component communicates with each other using different buses and can be installed on a common motherboard or installed in other ways as needed. The processor can process instructions executed within the computer device, including instructions stored in the memory or on the memory to display graphical information of a GUI on an external input / output device (such as a display device coupled to the interface). In some alternative embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories. Similarly, multiple computer devices can be connected, and each device provides some necessary operations (for example, as a server array, a set of blade servers, or a multi-processor system). Figure 4 In

[0087]

[0088]

[0089]

[0090] The memory 20 stores instructions executable by at least one processor 10, so that at least one processor 10 executes the method shown in the above embodiments.

[0090] The memory 20 may include volatile memory, such as random access memory; the memory may also include non-volatile memory, such as flash memory, a hard disk, or a solid state drive; the memory 20 may further include a combination of the above kinds of memories.

[0091] The computer device further includes a communication interface 30 for the computer device to communicate with other devices or a communication network.

[0092] An embodiment of the present invention further provides a computer-readable storage medium. The method according to the embodiment of the present invention can be implemented in hardware, firmware, or be implemented as computer code that can be recorded on a storage medium, or be implemented as computer code that is originally stored in a remote storage medium or a non-transitory machine-readable storage medium and will be stored in a local storage medium and downloaded through a network, so that the method described herein can be stored in such software processing on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only memory, a random access memory, a flash memory, a hard disk, or a solid state drive, etc.; further, the storage medium can also include a combination of the above kinds of memories. It can be understood that a computer, a processor, a microprocessor controller, or programmable hardware includes a storage component that can store or receive software or computer code, and when the software or computer code is accessed and executed by the computer, the processor, or the hardware, the method shown in the above embodiment is implemented.

[0093] A part of the present invention can be applied as a computer program product, such as computer program instructions, which when executed by a computer, can call or provide the method and / or technical solution according to the present invention through the operation of the computer. Those skilled in the art should be able to understand that the forms of existence of computer program instructions in a computer-readable medium include, but are not limited to, source files, executable files, installation package files, etc. Correspondingly, the ways for computer program instructions to be executed by a computer include, but are not limited to: the computer directly executes the instructions, or the computer compiles the instructions and then executes the corresponding compiled program, or the computer reads and executes the instructions, or the computer reads and installs the instructions and then executes the corresponding installed program. Herein, the computer-readable medium can be any available computer-readable storage medium or communication medium accessible by the computer.

[0094] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A method for fixed-point selection of a space launch site, characterized in that, Including: S1. According to the development planning information of the space launch site, initially select a launch point as the fixed point; S2. Set a first safety range with the fixed point as the center and the first safety distance as the radius, and determine whether there are no other space launch workstations within the first safety range; if not, return to S1 to re-select the fixed point, and if so, proceed to S3; S3. Set a second safety range with the fixed point as the center and the second safety distance as the radius, and determine whether there are no building facilities in the launch area of other space launch workstations within the second safety range; If not, return to S1 to re-select the fixed point, and if so, proceed to S4; S4. Set a third safety range with the fixed point as the center and the third safety distance as the radius, and determine whether there are no area facilities where no personnel are active during the launch mission within the third safety range; if not, return to S1 to re-select the fixed point, and if so, proceed to S5; S5. Set a fourth safety range with the fixed point as the center, the fourth safety distance as the radius, and with the common launch direction of the launch workstation as the reference, and the sector area formed by the boundary deviating from the preset angle; determine whether there are no preset important protection facilities within the fourth safety range; if not, return to S1 to re-select the fixed point, and if so, proceed to S6; S6. Determine whether the common launch direction of the launch workstation determined by the fixed point is suitable for the preset safety index requirements of the flight path and landing area; if not, return to S1 to re-select the fixed point, and if so, determine the fixed point as the fixed point of the space launch workstation.

2. The method according to claim 1, characterized in that, The first safety distance is determined according to the safety distance of the shock wave overpressure determined by the maximum filling amount of the launch vehicle. When the adjacent launch workstations do not erect rockets simultaneously, it is the distance corresponding to the first preset value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle; when the adjacent launch workstations erect rockets simultaneously, it is the distance corresponding to the second value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle, where the first value is greater than the second value.

3. The method according to claim 1, wherein The second safety distance is determined according to the safety distance of the shock wave overpressure determined by the maximum filling amount of the launch vehicle. It is the distance corresponding to the third preset value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle, and the third preset value is greater than the second preset value and less than the first preset value.

4. The method according to claim 1, wherein The third safety distance is obtained according to the safety distance of the shock wave overpressure determined by the maximum filling amount of the launch vehicle. It is the distance corresponding to the second preset value of the shock wave overpressure generated by the in-situ explosion of the launch vehicle.

5. The method according to any one of claims 2 to 4, characterized in that, The shock wave overpressure is determined according to the explosion equivalent of the propellant of the launch vehicle and the distance from the fixed point of the launch workstation, where the explosion equivalent of the propellant is the sum of the filling amounts of the propellants of the rocket and the spacecraft.

6. The method according to claim 1, wherein The deviation from the preset angle and the fourth safety distance are both determined based on the preset safety design criteria of the space launch site.

7. A fixed-point selection system for a space launch site, characterized in that, The system includes: A fixed point initial selection module, configured to initially select a launch point as the fixed point according to the development planning information of the space launch site; The first safety distance judgment module is used to set a first safety range with the fixed point as the center and the first safety distance as the radius, and judge whether there are no other space launch sites within the first safety range; if not, return to the fixed point preliminary selection module to reselect the fixed point, and if so, enter the second safety distance judgment module; The second safety distance judgment module sets a second safety range with the fixed point as the center and the second safety distance as the radius, and judges whether there are no building facilities in the launch area of other space launch sites within the second safety range; if not, return to the fixed point preliminary selection module to reselect the fixed point, and if so, enter the third safety distance judgment module; The third safety distance judgment module sets a third safety range with the fixed point as the center and the third safety distance as the radius, and judges whether the third safety range meets the requirement that there are no area facilities where people are active during the launch mission within it. If not, return to the fixed point preliminary selection module to reselect the fixed point, and if so, enter the fourth safety distance judgment module; The fourth safety distance judgment module sets a fourth safety range with the fixed point as the center, the fourth safety distance as the radius, and the common launch direction of the launch site as the reference, and the boundary formed by deviating from the preset angle. Judge whether the fourth safety range meets the requirement that there are no preset important protection facilities within it. If not, return to the fixed point preliminary selection module to reselect the fixed point, and if so, enter the flight landing area safety judgment module; The flight landing area safety judgment module judges whether the common launch direction of the launch vehicle adapted to the launch site determined by the fixed point meets the requirements of the preset flight landing area safety index. If not, return to the fixed point preliminary selection module to reselect the fixed point, and if so, determine the fixed point as the fixed point of the space launch site.

8. A computer device, characterized in that, It includes: A memory and a processor, which are communicatively connected to each other. The memory stores computer instructions, and the processor executes the computer instructions to execute the method for selecting a fixed point of a space launch site according to any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, Computer instructions are stored on the computer-readable storage medium, and the computer instructions are used to cause a computer to execute the method for selecting a fixed point of a space launch site according to any one of claims 1 to 6.

10. A computer program product, characterized in that, It includes computer instructions, and the computer instructions are used to cause a computer to execute the method for selecting a fixed point of a space launch site according to any one of claims 1 to 6.

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