Space traffic transportation system modeling method

Abstract

The invention discloses a space traffic transportation system modeling method. The method comprises the following steps: obtaining key components and constraint conditions of space traffic transportation; constructing a collaborative model according to key components and constraint conditions of space transportation; and optimizing the collaborative model. The method solves the problems of fragmentation and one-sided evaluation, and supports the design of an efficient transportation system.

Description

Technical Field

[0001] This invention belongs to the field of space transportation technology and systems engineering technology, and in particular relates to a modeling method for space transportation systems. Background Technology

[0002] With the increasing frequency of human space exploration activities and the acceleration of commercialization, establishing an efficient, safe, and sustainable space transportation system has become a key element in achieving long-term space goals. A space transportation system refers to a "system of systems" connecting Earth, near-Earth space, the Moon, Mars, and other celestial bodies and space facilities outside the Earth's atmosphere. This system includes not only traditional launch vehicles and space launch vehicles, but also infrastructure such as launch sites, spaceports, orbital refueling stations, and landing sites on celestial surfaces, as well as operation and management systems such as traffic scheduling, navigation and positioning, and telemetry and communication.

[0003] With the advancement of missions such as lunar base construction and Mars exploration, space transportation has shifted from single-space-ground transportation to multi-node network transportation. Current domestic and international research on transportation systems primarily focuses on road traffic, rail transit (railways and subways), aviation, and maritime transport. Space transportation mainly revolves around the perception, monitoring, protection, and handling of space debris, and research in the field of aerospace transportation has not yet been explored. Furthermore, research and design in aerospace transportation, as well as space exploration and construction, face the following four shortcomings: First, the mismatch between launch vehicles and mission requirements leads to wasted capacity or excessive costs; second, the lack of scientific basis for refueling station layout increases on-orbit refueling time; third, the lack of coordinated optimization between launch scheduling and orbit selection reduces transportation efficiency; and fourth, evaluation focuses only on cost, neglecting the balance between reliability and efficiency. Existing technologies have not formed a complete solution of "collaborative modeling of core components + multi-objective evaluation," making it difficult to support the design of efficient transportation systems. Summary of the Invention

[0004] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a modeling method for spatial transportation systems, which solves the problems of fragmentation and one-sided evaluation, and supports the design of efficient transportation systems.

[0005] The objective of this invention is achieved through the following technical solution: a method for modeling a space transportation system, comprising: obtaining the key components and constraints of space transportation; constructing a collaborative model based on the key components and constraints of space transportation; and optimizing the collaborative model.

[0006] The aforementioned modeling method for spatial transportation systems also includes: implementing multi-objective evaluation based on the optimized collaborative model.

[0007] In the aforementioned modeling method for space transportation systems, the key components of space transportation include vehicle selection, refueling station setup, launch scheduling, and transfer orbit selection.

[0008] In the aforementioned modeling method for space transportation systems, the launch vehicle selection factors include launch vehicle type, key launch vehicle parameters, and launch vehicle selection principles. The launch vehicle type includes launch vehicles and orbital transfer vehicles, with orbital transfer vehicles including chemically propelled orbital transfer vehicles, electrically propelled orbital transfer vehicles, and nuclear-powered orbital transfer vehicles. The key launch vehicle parameters include carrying capacity, single launch cost, and number of reusable launches. The launch vehicle selection principles include: prioritizing launch vehicles for low Earth orbit missions and prioritizing orbital transfer vehicles for Earth-Moon transfers.

[0009] In the aforementioned modeling method for space transportation systems, the elements for setting up refueling stations include candidate nodes, key parameters, and principles for setting up refueling stations. Candidate nodes include low Earth orbit, Earth-Moon Lagrange L1 point, and Earth-Moon Lagrange L2 point. Key parameters include service radius, single refueling cost, and resupply cycle. Principles for setting up refueling stations include: Earth-Moon transportation requires a refueling station at the Earth-Moon Lagrange L2 point; near-Earth transportation requires a low Earth orbit refueling station as needed.

[0010] In the aforementioned modeling method for space transportation systems, launch scheduling elements include launch constraints and launch objectives; among them, launch constraints include the maximum number of launches per month at the launch site and the mission time window; launch objectives include ensuring that missions are executed within the time window.

[0011] In the aforementioned modeling method for space transportation systems, the transfer orbit selection elements include transfer orbit type, key parameters of transfer orbit, and transfer orbit selection principles. Among them, transfer orbit types include Earth-Moon transfer orbit and interplanetary Hohmann transfer orbit; key parameters of transfer orbit include orbital period and fuel consumption; and transfer orbit selection principles include: selecting high-speed orbits for personnel transportation and energy-saving orbits for cargo transportation.

[0012] In the above-mentioned modeling method for space transportation systems, the constraints for space transportation include efficiency, cost, and reliability; where efficiency is defined as a single mission cycle of ≤15 days; cost is defined as a unit mass transportation cost of ≤2000 USD / kg; and reliability is defined as a mission completion rate of ≥98%.

[0013] In the aforementioned modeling methods for space transportation systems, the collaborative models include a launch vehicle-orbit matching model, a refueling station-transportation link collaborative model, a launch scheduling-orbit window collaborative model, and a cost-efficiency collaborative model. Among these, the launch vehicle-orbit matching model establishes a matching table between carrying capacity and orbital fuel demand; the refueling station-transportation link collaborative model obtains the cost-effectiveness ratio based on the number of coverage links and construction costs; the launch scheduling-orbit window collaborative model prioritizes mission windows, with personnel transportation windows having higher priority than cargo transportation windows, and prioritizes high-priority missions; and the cost-efficiency collaborative model obtains the efficiency-cost ratio based on mission cycle and unit cost.

[0014] In the aforementioned modeling method for spatial transportation systems, the optimization of the collaborative model includes: vehicle optimization, refueling station optimization, track optimization, and target optimization. Among these, vehicle optimization involves reserving one reuse redundancy; refueling station optimization involves advancing the refueling cycle by 2 days; track optimization involves storing fuel at the design value + 5%; and target optimization involves achieving a mission completion rate ≥ 98% and a cost increase ≤ 8%.

[0015] Compared with the prior art, the present invention has the following advantages:

[0016] This invention focuses on four core aspects: launch vehicle selection, refueling station setup, launch scheduling, and orbit selection. It also provides a modeling and evaluation method that balances efficiency, cost, and reliability. For different mission scenarios such as constellation deployment, deep space exploration, Earth-Moon round trip, and high-orbit missions, it can analyze and optimize performance values ​​based on various parameters of the transportation system, solving the problems of fragmentation and one-sided evaluation in existing technologies, and supporting the design of efficient transportation systems. Attached Figure Description

[0017] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0018] Figure 1 This is a flowchart of the spatial transportation system modeling method provided in the embodiments of the present invention. Detailed Implementation

[0019] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present disclosure and to fully convey the scope of the disclosure to those skilled in the art. It should be noted that, unless otherwise specified, the embodiments and features described herein can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0020] Figure 1 This is a flowchart of the spatial transportation system modeling method provided in an embodiment of the present invention. Figure 1 As shown, the modeling method for the spatial transportation system includes: obtaining the key components and constraints of spatial transportation; constructing a collaborative model based on the key components and constraints of spatial transportation; and optimizing the collaborative model.

[0021] The modeling method for this spatial transportation system also includes: implementing multi-objective evaluation based on the optimized collaborative model.

[0022] Key components of space transportation include vehicle selection, refueling station setup, launch scheduling, and transfer orbit selection.

[0023] The launch vehicle selection factors include launch vehicle type, key launch vehicle parameters, and launch vehicle selection principles. The launch vehicle type includes launch vehicles and orbital transfer vehicles, with orbital transfer vehicles including chemically propelled orbital transfer vehicles, electrically propelled orbital transfer vehicles, and nuclear-powered orbital transfer vehicles. The key launch vehicle parameters include payload capacity, cost per launch, and number of reusable launches. The launch vehicle selection principles include: prioritizing launch vehicles for low Earth orbit missions and prioritizing orbital transfer vehicles for Earth-Moon transfers.

[0024] The elements for setting up refueling stations include candidate nodes, key parameters, and principles for setting up refueling stations. Candidate nodes include low Earth orbit, Earth-Moon Lagrange L1 point, and Earth-Moon Lagrange L2 point. Key parameters include service radius, cost per refueling, and resupply cycle. Principles for setting up refueling stations include: Earth-Moon transportation requires a refueling station at the Earth-Moon Lagrange L2 point, while near-Earth transportation requires a low Earth orbit refueling station as needed.

[0025] Launch scheduling elements include launch constraints and launch objectives; among them, launch constraints include the maximum number of launches per month at the launch site and the mission time window; launch objectives include ensuring that missions are executed within the time window.

[0026] The factors for selecting a transfer orbit include the type of transfer orbit, key parameters of the transfer orbit, and selection principles. Among them, the types of transfer orbits include the Earth-Moon transfer orbit and the interplanetary Hohmann transfer orbit; the key parameters of the transfer orbit include orbital period and fuel consumption; and the selection principles include: selecting high-speed orbits for personnel transportation and energy-saving orbits for cargo transportation.

[0027] Constraints on space transportation include efficiency, cost, and reliability; efficiency is defined as a single mission cycle of ≤15 days; cost is defined as a unit mass transportation cost of ≤2000 USD / kg; and reliability is defined as a mission completion rate of ≥98%.

[0028] The collaborative models include a launch vehicle-orbit matching model, a refueling station-transportation link collaborative model, a launch scheduling-orbit window collaborative model, and a cost-efficiency collaborative model. Among them, the launch vehicle-orbit matching model establishes a matching table between launch capacity and orbital fuel demand; the refueling station-transportation link collaborative model obtains the cost-effectiveness based on the number of coverage links and construction costs; the launch scheduling-orbit window collaborative model sorts tasks by priority, with personnel transportation windows having higher priority than cargo transportation windows, and prioritizes high-priority tasks; the cost-efficiency collaborative model obtains the efficiency-cost ratio based on the task cycle and unit cost.

[0029] The optimization of the collaborative model includes: vehicle optimization, refueling station optimization, track optimization, and target optimization. Among them, vehicle optimization is to reserve one reuse redundancy; refueling station optimization is to advance the refueling cycle by 2 days; track optimization is to reserve fuel at the design value + 5%; and target optimization is to achieve a mission completion rate of ≥98% and a cost increase of ≤8%.

[0030] Specifically, the method includes the following steps:

[0031] Step 1: Identify the key components and constraints of the space transportation system to lay the foundation for modeling. This specifically includes:

[0032] 1.1 Vehicle selection includes the following factors:

[0033] Types: Launch vehicles (such as Long March 5, 7, 8, 9, 10, etc.), orbital transfer vehicles (chemical propulsion / electric propulsion / nuclear power, etc.);

[0034] Key parameters: payload capacity (tons), cost per launch (ten thousand yuan), number of times it can be reused;

[0035] Selection principles: Reusable rockets are preferred for low Earth orbit missions, and high-thrust orbital transfer vehicles are preferred for Earth-Moon transfer missions.

[0036] 1.2 Elements for setting up a refueling station:

[0037] Candidate nodes: Low Earth Orbit (LEO), Earth-Moon Lagrange points L1 and L2 (EML1, EML2);

[0038] Key parameters: service radius (number of transport links covered), cost per refueling (ten thousand yuan), refueling cycle (days);

[0039] Setting principles: EML2 refueling stations must be set up for Earth-Moon transportation, and LEO refueling stations should be set up as needed for near-Earth transportation.

[0040] 1.3 Launch scheduling elements:

[0041] Constraints: Maximum number of launches per month at the launch site (e.g., 8 launches per month at the Wenchang Launch Center in Hainan), mission time window (e.g., 2 optimal launch windows per month for Earth-Moon transfer);

[0042] Objective: Avoid launch conflicts and ensure missions are executed within their designated time windows.

[0043] 1.4 Transfer orbit selection factors:

[0044] Types: Earth-Moon transfer orbit (fast transfer / Hohmann transfer), interplanetary Hohmann transfer orbit;

[0045] Key parameters: orbital period (days), fuel consumption (kg);

[0046] Selection principles: Select high-speed rail for personnel transportation (cycle ≤ 5 days), and select energy-saving rail for freight transportation.

[0047] 1.5 Core Constraints:

[0048] Efficiency: Single task cycle ≤ 15 days;

[0049] Cost: Unit weight transportation cost ≤ US$2000 / kg;

[0050] Reliability: Task completion rate ≥ 98%.

[0051] Step Two: Build a collaborative model around the four key stages to avoid fragmentation, as detailed below:

[0052] 2.1 Launch Vehicle-Torch Matching Model:

[0053] Method: Establish a "carrying capacity-orbit fuel requirement" matching table. For example, if the Earth-Moon rapid transfer orbit requires 1200kg of fuel, priority should be given to orbital transfer vehicles with a carrying capacity of ≥2000kg.

[0054] Output: Match score (1-10 points), with a score ≥8 points being the best match (e.g., Long March 10 rocket + Earth-Moon Hohmann transfer orbit gets 9 points).

[0055] 2.2 Refueling Station-Transportation Link Collaborative Model:

[0056] Method: The cost-effectiveness ratio was calculated based on "number of coverage links / construction cost". The EML2 refueling station covers two links, "LEO-Moon" and "Earth-Mars", with a cost-effectiveness ratio of 0.6 (number of links / cost). The LEO refueling station covers one link, with a cost-effectiveness ratio of 0.4.

[0057] Output: Optimal refueling station combination (e.g., for Earth-Moon missions, select the "LEO+EML2" combination).

[0058] 2.3 Launch Scheduling-Orbit Window Coordination Model:

[0059] Method: Sort by "task window priority", with personnel transportation window priority (10 points) > cargo transportation (7 points). Prioritize the arrangement of high-priority tasks to avoid conflicts;

[0060] Output: Monthly launch schedule (e.g., personnel transportation is arranged from the 1st to the 5th of each month, and cargo transportation is arranged from the 15th to the 20th).

[0061] 2.4 Cost-Efficiency Synergistic Model:

[0062] Method: Calculate the "efficiency-cost ratio" (task cycle / unit cost). A ratio ≤ 0.0075 (day·kg / yuan) is considered satisfactory (e.g., if the task cycle is 10 days and the unit cost is 1300 yuan / kg, the ratio is 0.0077, which is close to the standard).

[0063] Output: Cost efficiency meets target.

[0064] Step 3: Optimize the model to address key uncertainties related to the launch vehicle, refueling station, and track, as detailed below:

[0065] 3.1 Uncertainty Identification:

[0066] Launch vehicle uncertainty: The actual number of reuses of a reusable rocket deviates by ±1 time (e.g., designed for 5 reuses, but actually used 4-6 times);

[0067] Uncertainties at refueling stations: Supply cycle delay of ±2 days (e.g., designed for 15 days, but actually 13-17 days);

[0068] Track uncertainty: fuel consumption deviation ±5% (e.g., designed 1200kg, actual 1140-1260kg).

[0069] 3.2 Optimization Methods:

[0070] Launch vehicle optimization: Reserve one reuse redundancy (e.g., plan according to the design reuse count - 1, arrange 4 reuses if designed for 5 reuses);

[0071] Refueling station optimization: The refueling cycle will be brought forward by 2 days (e.g., if designed for 15 days, refueling will start on 13 days).

[0072] Track optimization: Fuel reserves are set at the design value + 5% (e.g., design value 1200kg, reserve value 1260kg);

[0073] Optimization objective: Ensure a task completion rate of ≥98% and a cost increase of ≤8%.

[0074] Step 4: Simplify the evaluation process by focusing on the three main objectives of efficiency, cost, and reliability, as follows:

[0075] 4.1 Evaluation indicators: See Table 1 for details.

[0076] Table 1

[0077] Target Key Indicators Standards efficiency Single task cycle ≤15 days cost Unit weight transportation cost ≤30,000 yuan / kg reliability Task completion rate 98％

[0078] 4.2 Weight Determination:

[0079] Method: Weights were assigned based on task type: personnel transportation (reliability 40%, efficiency 35%, cost 25%), and freight transportation (cost 40%, efficiency 35%, reliability 25%).

[0080] Basis: Safety and speed are prioritized in personnel transportation, while cost control is prioritized in freight transportation.

[0081] 4.3 Comprehensive Evaluation (Simplified Calculation):

[0082] Step 1: Score each indicator according to the standard (100 points for meeting the standard, and points are deducted for not meeting the standard, such as 10 points deducted for a 16-day cycle, resulting in 90 points).

[0083] Step 2: Calculate the overall score according to the weights (e.g., personnel transportation: reliability 98 points × 40% + efficiency 90 points × 35% + cost 95 points × 25% = 94.45 points);

[0084] Standard: A score of ≥90 is the optimal solution, 80-89 is a feasible solution, and <80 is a solution that needs optimization.

[0085] Taking the Earth-Moon cargo transportation mission as an example:

[0086] 1. Task Requirements

[0087] Goods weight: 1500kg, task cycle ≤ 15 days, unit cost ≤ 12000 yuan / kg, task completion rate ≥ 98%.

[0088] 2. Modeling process

[0089] 2.1 Launch Vehicle-Orbit Matching: Select "Long March 10 (carrying capacity 2700kg) + Earth-Moon Energy-Saving Orbit (fuel 1100kg)", matching score 9 points;

[0090] 2.2 Refueling Station Setup: Select "EML2 Refueling Station" (covers 1 Earth-Moon link, cost-effectiveness 0.5);

[0091] 2.3 Launch scheduling: Arranged for the 15th-20th of each month (cargo transport window, priority 7 points);

[0092] 2.4 Cost efficiency: The cycle is 12 days, the unit cost is US$1,800 / kg, and the efficiency-cost ratio is 0.0067 (meets the standard).

[0093] 3. Uncertainty Optimization

[0094] Launch vehicle: designed for 4 reuses (5 reuses, with 1 redundancy reserved);

[0095] Refueling station: Replenishment cycle 13 days (designed 15 days, 2 days ahead);

[0096] Track: Fuel reserves 1155kg (design 1100kg, +5%);

[0097] After optimization: Task completion rate 99%, cost increased by 6%.

[0098] 4. Overall Evaluation

[0099] Weighting: Cost 40%, Efficiency 35%, Reliability 25%;

[0100] Scores: Cost 90 points ($1800 / kg), Efficiency 95 points (12 days), Reliability 99 points;

[0101] Overall score: 90×40%+95×35%+99×25%=93.75 points (optimal solution).

[0102] This embodiment retains only key elements such as vehicle selection, refueling station setup, and track selection, avoiding redundancy and simplifying operation. This embodiment constructs a collaborative model of "vehicle-track-refueling station-scheduling" to solve existing fragmentation problems. This embodiment assigns weights according to task type, aligning with actual needs, and the comprehensive score is intuitive and easy to understand. After optimization, this embodiment increases costs by ≤8%, achieves a task completion rate of ≥98%, and balances efficiency and reliability.

[0103] This embodiment focuses on four core aspects: launch vehicle selection, refueling station setup, launch scheduling, and orbit selection. It also presents a modeling and evaluation method that balances efficiency, cost, and reliability. For different mission scenarios such as constellation deployment, deep space exploration, Earth-Moon round trips, and high-orbit missions, it can analyze and optimize performance values ​​based on various parameters of the transportation system, solving the problems of fragmentation and one-sided evaluation in existing technologies, and supporting the design of efficient transportation systems.

[0104] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A method for modeling a spatial transportation system, characterized in that... include: To obtain the key components and constraints of space transportation; Construct a collaborative model based on the key components and constraints of spatial transportation; Optimize the collaborative model.

2. The spatial transportation system modeling method according to claim 1, characterized in that... Also includes: Multi-objective evaluation is carried out based on the optimized collaborative model.

3. The spatial transportation system modeling method according to claim 1, characterized in that: Key components of space transportation include vehicle selection, refueling station setup, launch scheduling, and transfer orbit selection.

4. The spatial transportation system modeling method according to claim 3, characterized in that: The factors for selecting a launch vehicle include launch vehicle type, key launch vehicle parameters, and launch vehicle selection principles; among them, The types of launch vehicles include launch vehicles and orbital transfer vehicles, wherein orbital transfer vehicles include chemically propelled orbital transfer vehicles, electrically propelled orbital transfer vehicles, and nuclear-powered orbital transfer vehicles; The key parameters of the launch vehicle include carrying capacity, cost per launch, and number of times it can be reused. The principles for selecting launch vehicles include: prioritizing launch vehicles for low Earth orbit missions and prioritizing orbital transfer vehicles for Earth-Moon transfers.

5. The spatial transportation system modeling method according to claim 3, characterized in that: The elements for setting up a refueling station include candidate nodes, key parameters, and principles for setting up the station; among them, Candidate nodes for refueling stations include low Earth orbit, Earth-Moon Lagrange point L1, and Earth-Moon Lagrange point L2; Key parameters for refueling stations include service radius, cost per refueling, and refueling cycle; The principles for setting up refueling stations include: a refueling station at the Earth-Moon Lagrange L2 point is mandatory for Earth-Moon transportation, while a low Earth orbit refueling station is set up as needed for near-Earth transportation.

6. The spatial transportation system modeling method according to claim 3, characterized in that: Launch scheduling elements include launch constraints and launch targets; among them, Launch constraints include the maximum number of launches per month at the launch site and the mission time window; The launch objectives include ensuring the mission is executed within the time window.

7. The spatial transportation system modeling method according to claim 3, characterized in that: The factors for transferring orbit selection include the type of transfer orbit, key parameters of the transfer orbit, and principles for selecting the transfer orbit; among them, Transfer orbit types include Earth-Moon transfer orbits and interplanetary Hohmann transfer orbits; Key parameters for the transfer orbit include orbital period and fuel consumption; The principles for selecting transfer tracks include: selecting high-speed tracks for personnel transportation and energy-saving tracks for freight transportation.

8. The spatial transportation system modeling method according to claim 1, characterized in that: Constraints on space transportation include efficiency, cost, and reliability; among them, The efficiency is that the cycle time for a single task is ≤15 days; The cost is ≤2000 USD / kg for transportation per unit mass; Reliability is defined as a task completion rate of ≥98%.

9. The spatial transportation system modeling method according to claim 1, characterized in that: The collaborative models include the launch vehicle-orbit matching model, the refueling station-transportation link collaborative model, the launch scheduling-orbit window collaborative model, and the cost-efficiency collaborative model; among them, The vehicle-track matching model is used to establish a matching table between carrying capacity and track fuel requirements; The refueling station-transportation link collaboration model determines the cost-effectiveness based on the number of covered links and construction costs. The launch scheduling-orbit window coordination model prioritizes mission windows, with personnel transport windows having higher priority than cargo transport windows, and high-priority missions are scheduled first. The cost-efficiency synergy model calculates the efficiency-cost ratio based on the task cycle and unit cost.

10. The spatial transportation system modeling method according to claim 1, characterized in that: Optimization of the collaborative model includes: vehicle optimization, refueling station optimization, trajectory optimization, and objective optimization; among which, The launch vehicle is optimized to reserve one reuse redundancy; The refueling station has been optimized to shorten the refueling cycle by 2 days; The track is optimized to have fuel reserves at the design value plus 5%; The target is optimized to a task completion rate of ≥98% and a cost increase of ≤8%.

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