CN113656940B - Manned moon exploration task track design system - Google Patents
Manned moon exploration task track design system Download PDFInfo
- Publication number
- CN113656940B CN113656940B CN202110774269.5A CN202110774269A CN113656940B CN 113656940 B CN113656940 B CN 113656940B CN 202110774269 A CN202110774269 A CN 202110774269A CN 113656940 B CN113656940 B CN 113656940B
- Authority
- CN
- China
- Prior art keywords
- orbit
- lunar
- calculation
- transfer
- subsystem
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/12—Geometric CAD characterised by design entry means specially adapted for CAD, e.g. graphical user interfaces [GUI] specially adapted for CAD
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/04—Constraint-based CAD
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Computer Hardware Design (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Human Computer Interaction (AREA)
- Computational Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The invention relates to a manned lunar exploration task track design system which comprises a lunar landing window calculation subsystem, a lunar orbit deployment subsystem, an unmanned lunar orbiting subsystem, a manned lunar orbiting subsystem and a manned lunar landing subsystem. Each subsystem is formed by combining a window calculation module, a general transfer orbit calculation module, a free return orbit design module, a monthly return transfer orbit design module, a three-pulse transfer orbit design module and the like. When different tasks are designed, the system can consider the constraint coupling among the tasks; a moon-landing window can be calculated, and a feasible moon-landing window is provided on the premise of not designing a specific track; design initial values do not need to be provided, and only the ranges of design parameters, constraint parameters and traversal time are given, so that the method is convenient for users to use; and respectively displaying the initial value and the high-precision result, and performing high-precision calculation on the basis of a reasonable initial value to improve the design efficiency.
Description
Technical Field
The invention belongs to the technical field of manned lunar exploration task track design, and particularly relates to a manned lunar exploration task track design system.
Background
The manned lunar exploration orbit design is important content of the demonstration of manned lunar exploration tasks, and the manned lunar exploration task orbit design method relates to the earth-moon transfer tasks of manned aircrafts and unmanned aircrafts, and specifically comprises a general transfer orbit, a free return orbit and a fixed point return orbit. The general transfer track and the free return track need to be matched with the launching task in track, and the free return track and the fixed point return track need to be subjected to different-surface orbital transfer so as to respectively realize full lunar arrival and fixed point return at any time. Generally, the transfer orbit, the free return orbit and the fixed point return orbit can adopt a conic section splicing method to divide the transfer orbit into a geocentric two-body orbit and a lunar two-body orbit and obtain an orbit initial value through splicing, or adopt a multi-cone analytic method utilizing a pseudo state theory, consider the earth, the moon and the solar gravitation in the whole process, and obtain higher result precision with less calculation amount.
At present, the only manned lunar-landing task is the American 'Apollo' lunar-landing plan, manned lunar-landing is realized for the first time in 7 months in 1969, 7 lunar-landing airships are launched successively in 12 months in 1972, except Apollo-13, the rest is successful, 12 astronauts are sent to the moon in total, the lunar-landing mode is a direct lunar-landing of a launching task, and the task orbit design can be carried out by adopting the method. However, the lunar exploration task based on the lunar space station also comprises a plurality of launching tasks, a plurality of intersection butt joints are required to be carried out on the lunar orbit, and all tasks are coupled through the orbit parameters of the lunar space station.
It is obvious from the previous research that certain difference exists between the track design and the mission track design, the single track design can not meet the complex mission track design requirement, and a powerful mission design platform is required to realize the manned lunar exploration mission consisting of a plurality of sequence missions. In short, manned lunar exploration tasks become more complex in the future, and a track design tool aiming at a specific track and a specific launching task cannot meet all engineering requirements. Therefore, a task track design platform capable of flexibly setting track parameters and constraint parameters is required to be designed.
At present, a relatively mature track design analysis simulation platform is an STK (Satellite Tool Kit), and an Astrogator plug-in the track design analysis simulation platform can set different constraint and iteration targets through combination of different modules, so that design of a single task flow is realized. The plug-in does not present an efficient design module for free return tracks, general transfer tracks, fixed point return tracks. A user needs to have a more accurate initial value solution at the beginning of design, so that rapid iterative design can be realized by using the Astrogator on the STK, and the platform is more suitable for simulation verification. The STK is only limited to single task design, coupling constraint among multiple tasks cannot be considered, the track design is too general, and the task design efficiency cannot be improved. For a manned lunar landing task in a specific lunar orbit intersection, the task mode is fixed, and a more efficient design platform is often needed.
Disclosure of Invention
The invention aims to provide a manned moon exploration task track design system which is provided with design modules aiming at different tracks, does not need prior information of a user, and can realize display from a primary design result to a final design result after constraint and design indexes are given. In addition, other design factors such as illumination, the residence time of the moon surface, the condition of returning to a landing field and the like can be considered, a task window is directly provided, and the appropriate moon-climbing opportunity can be found on the premise of not developing specific track design.
The invention provides a manned moon exploration task track design system which comprises a moon landing window subsystem, an unmanned moon winding subsystem, a lunar orbit deployment subsystem, a manned moon surrounding subsystem and a manned moon landing subsystem, wherein the moon landing window subsystem comprises a moon landing window subsystem, a moon landing subsystem and a moon landing subsystem;
the lunar landing window subsystem is used for re-track deployment and existing track deployment; the re-orbit deployment comprises the steps of calculating a lunar landing window meeting the illumination condition according to the illumination constraint and the longitude and latitude of the landing point, enabling a user to check the lunar landing window meeting the condition in a calculation result list, obtaining a window with a feasible returning condition through the deployment orbit calculation, enabling the user to select a target lunar orbit at a certain lunar landing moment from the calculation result, and calculating a rising window aiming at the lunar orbit; the existing orbit deployment comprises the steps of calculating orbit satellite-to-satellite point information according to an existing lunar orbit, determining a lunar falling moment according to user selection, and calculating a rising window;
the lunar orbit deployment subsystem is used for designing a general transfer orbit according to time design parameters, geocentric segment constraint parameters of lunar transfer and target lunar orbit parameters selected and set by a user, calculating an initial value and high precision, and calculating position and speed information of the whole process according to the transfer orbit;
the unmanned lunar orbit subsystem is used for designing a lunar orbit working condition of the manned spacecraft, and comprises the steps of directly calculating feasible free return orbit initial values according to user setting parameters, displaying all feasible orbit initial value results in a rocket coplanar launching window, carrying out high-precision calculation on the selected results, and carrying out overall process orbit data calculation on the orbits selected by a user through orbit calculation;
the manned lunar sub-system is used for respectively carrying out initial value calculation of a free return orbit and three-pulse transfer, high-precision calculation of the free return orbit, high-precision calculation of the three-pulse transfer and the calculation of the whole earth-moon transfer process according to the sequence of parameter configuration, emission window calculation and transfer orbit calculation; according to the sequence of parameter configuration, emission window calculation and transfer orbit calculation, respectively carrying out initial value calculation of monthly ground return orbit and three-pulse transfer, high-precision calculation of monthly ground return orbit, high-precision calculation of three-pulse transfer and whole monthly ground transfer process calculation;
the manned lunar landing subsystem is used for respectively designing a lander and a manned spacecraft to obtain initial values of transfer orbits through configuration parameters, a user selects and calculates results of the initial values of a certain row to perform high-precision calculation, and high-precision three-pulse transfer calculation and calculation of results of the whole process of the transfer orbits are performed on a transfer orbit calculation interface.
Further, the platform architecture adopts a three-level organization architecture, and the first level is a task level and comprises the following steps: determining a window, winding a moon without a person, carrying a person around the moon, and carrying a person to land the moon; the second level is an object level comprising: manned spacecraft, lander, space station, return section; the third stage is a functional stage comprising: parameter configuration, rocket coplanar launching window, transfer orbit calculation, lunar landing window, lunar orbit deployment and ascending window; the task level is composed of different object level members, the different object level members comprise different function level members, and different manned lunar series tasks are formed through different combinations.
By means of the scheme, the manned moon exploration task track design system has the following technical effects:
1) The system may consider constrained coupling between tasks when designing different tasks.
2) The invention can calculate the moon landing window and provide a feasible moon landing window on the premise of not designing a specific track.
3) Design initial values do not need to be provided, and only the ranges of design parameters, constraint parameters and traversal time are given, so that the method is convenient for users to use;
4) And respectively displaying the initial value and the high-precision result, and performing high-precision calculation on the basis of a reasonable initial value to improve the design efficiency.
Drawings
FIG. 1 is a block diagram of a design system for a manned lunar exploration mission orbit according to the present invention;
FIG. 2 is a diagram of the architecture of the manned lunar exploration mission trajectory design system of the present invention;
FIG. 3 is an internal flow chart of the manned lunar landing subsystem according to the present invention;
FIG. 4 is a simulation verification result of the manned lunar-circle task of the present invention;
FIG. 5 shows simulation verification results of the space station deployment trajectory according to the present invention.
Detailed Description
The following detailed description of embodiments of the present invention is provided in connection with the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.
The manned lunar exploration task orbit design system (platform) provided by the embodiment mainly designs a multi-level platform architecture and realizes specific functions under the multi-level architecture. In order to realize manned lunar exploration tasks, task window design needs to be considered, and track design of different tasks is carried out on the basis. The functions of each subsystem comprise parameter configuration, calculation analysis and result display: the parameter configuration is realized by manually modifying the configuration parameters in the interface by a user or loading the configuration parameters by a file; the calculation analysis mainly comprises the selection and the screening of a moon landing window, and the design of a general transfer orbit, a free return orbit, a fixed point return orbit and a three-pulse transfer orbit; the results are presented in the interface in a graph mode and can be stored as data files. Unmanned flying vehicles are designed to freely return to the orbit around the lunar subsystem; a lunar station deployment subsystem designs a general transfer orbit and a near-lunar braking orbit of a space station; the manned lunar sub-system mainly designs a free return track, a three-pulse transfer-in track, a three-pulse transfer-out track and a fixed point return track of the manned spacecraft; the manned lunar landing subsystem mainly designs a general transfer orbit of a lander, and the manned spacecraft designs a free return orbit, a three-pulse transfer-in orbit, a three-pulse transfer-out orbit and a fixed-point return orbit.
The present invention will be described in detail below.
The lunar landing window subsystem determines a proper lunar landing time through the conditions of a lunar landing point, illumination constraint, lunar residence time, returning to a landing field and the like, and provides a corresponding target lunar orbit. On the basis, different subsystems such as unmanned lunar circling, space station deployment, manned lunar circling, manned lunar boarding and the like are arranged, the combination of different spacecraft objects such as manned spacecrafts, lunar circling space stations, lunar landers and the like is arranged according to different tasks, the function modules under the different spacecraft objects realize the parameter configuration function, the different types of track design functions such as a general transfer track, a free return track, a three-pulse transfer track, a fixed point return track and the like are realized, and the functions of displaying and storing the parameter information at the key stages such as the transfer track, the process maneuver, the reentry return and the like are realized.
The embodiment relates to a manned lunar exploration task orbit design, which mainly comprises a lunar landing window calculation subsystem, a lunar orbit deployment subsystem, an unmanned lunar orbiting subsystem, a manned lunar orbiting subsystem and a manned lunar landing subsystem. Each subsystem is formed by combining a window calculation module, a general transfer orbit calculation module, a free return orbit design module, a monthly return transfer orbit design module, a three-pulse transfer orbit design module and the like. The whole composition structure is shown in figure 1.
The platform architecture corresponding to the functional modules is a three-level organization architecture, and the subsystems are integrated into a track design platform through the three-level architecture, as shown in fig. 2. The platform three-level organization architecture, the first level is a task level comprising: determining a task design window, an unmanned moon winding task, a manned moon circling task and a manned moon logging task; the second level is an aircraft object level comprising: manned spacecrafts, landers, space stations and re-entry cabins; the third stage comprises for the platform functional stage: parameter configuration, rocket coplanar launching window, transfer orbit calculation, lunar landing window, lunar orbit deployment and ascending window. The task level is made up of different object level members, which in turn include different function level members. Different manned lunar-landing series tasks are formed through different combinations.
And the lunar landing window calculation subsystem comprises re-orbit deployment and existing orbit deployment. For tasks without a lunar orbit, the target lunar orbit needs to be designed before the transfer orbit is designed. And calculating the lunar landing windows meeting the illumination conditions according to the illumination constraints and the latitude and longitude of the landing points, wherein the user can check the lunar landing windows meeting the conditions in a calculation result list, the deployment track calculation can further calculate the windows with feasible returning conditions according to the previous results, the user selects a target lunar orbit at a certain moon landing moment from the calculation results, and the lifting window calculation is carried out aiming at the lunar orbit. And the existing deployment can calculate the information such as orbit satellite points and the like according to the existing lunar orbit, still determines the lunar falling time according to the selection of a user, and then calculates the ascending window. The subsystem comprises an interface parameter setting module, a monthly payment calculation module, a deployment track calculation module, an existing track calculation module and an ascending window calculation module.
And the interface parameter setting module comprises input of illumination constraint, track deployment, return conditions and the like. The user can save the parameters through the save configuration function. And the lunar orbit deployment can calculate a corresponding target lunar orbit according to the window, and the existing orbits can be extrapolated when the lunar orbit deployment is performed. And the platform stores the falling month time and the corresponding track number into a memory according to the selection of the user. The calculation of the ascending window is to calculate the ascending at different time, the deviation phase difference between the falling point and the orbit surface and whether the earth can return to the designated landing field. The calculation results are displayed in a list and can also be saved in a file form.
An unmanned moon-winding subsystem mainly designs the working condition of a manned spacecraft around the moon, i.e. directly back to earth without a near-moon braking after approaching the moon. The subsystem mainly comprises an interface parameter setting module, a free return track design module and a track calculation module. And directly calculating a feasible free return orbit according to parameters set by a user, and calculating the orbit data of the whole process aiming at the orbit selected by the user by the orbit calculation.
And after the track calculation, a free return track initial value calculation module is called to give an initial result, and the high-precision calculation of the selected row of the user can be carried out by adopting single-row calculation, and the calculation of all traversal results can also be carried out by adopting batch calculation.
And according to the result selected by the user, calculating the free return orbit of the whole process, displaying the position components under the coordinate systems of the moon center and the geocentric in the interface, and directly storing the calculation result in a file form.
Designing a general transfer orbit according to a time design parameter, a moon transfer geocentric segment constraint parameter and a target lunar orbit parameter which are selected and set by a user, calculating an initial value and high precision, and finally calculating the position and speed information of the whole process according to the transfer orbit. A
The interface configuration result can be stored in a file by storing the configuration, and the configuration is directly imported when the interface configuration result is started. In addition, the calculation result of the transfer track may be stored in a file form.
The manned ring lunar subsystem comprises a parameter setting module, a free return orbit calculation module, a three-pulse transfer calculation module and a lunar return orbit calculation module. And the three track calculation modules comprise track preliminary calculation and track high-precision calculation. The import key of the interface can directly import the parameters of the target lunar orbit, and the orbit design is developed on the basis of the parameters.
The manned lunar cycle subsystem designs a lunar transfer orbit by a manned spacecraft page, and respectively calls initial value calculation of a free return orbit and a three-pulse transfer, high-precision calculation of the free return orbit, high-precision calculation of the three-pulse transfer and the calculation of the whole lunar transfer process according to the sequence of parameter configuration, emission window calculation and transfer orbit calculation. And (3) designing a monthly ground transfer orbit by a monthly ground return page, and calling initial value calculation of the monthly ground return orbit and the three-pulse transfer, high-precision calculation of the monthly ground return orbit, high-precision calculation of the three-pulse transfer and the whole monthly ground transfer process calculation respectively according to the sequence of parameter configuration, emission window calculation and transfer orbit calculation.
The manned lunar landing subsystem comprises a general transfer orbit design part of a previous lunar orbit deployment subsystem, a free return orbit design part of the manned lunar landing subsystem and a lunar transfer orbit design part, and the functions of the parts are consistent with the functions in the previous subsystem. Through parameter configuration, the lander and the manned spacecraft are respectively designed to obtain initial values of the transfer orbit, a user selects and calculates the initial value result of a certain row to perform high-precision calculation, and high-precision three-pulse transfer calculation and calculation of the whole process result of the transfer orbit are performed on a transfer orbit calculation interface.
Fig. 3 shows the internal workflow of the manned lunar landing subsystem. Firstly, a user opens software, a platform loads a configuration file and other database files, and a result is displayed on an interface; the user modifies the configuration through the interface and updates the data; the user selects to calculate the free return/monthly return initial value calculation and the general transfer initial value calculation of the manned spacecraft page or the lander, and simultaneously performs the initial value calculation of the three-pulse transfer, and the result is displayed in an interface list; the user clicks a certain line of data to carry out high-precision calculation, and the lander or manned spacecraft respectively calls the high-precision calculation of the general transfer orbit and the free return orbit/monthly ground return and returns the calculation to the interface; selecting calculation by a user in a track calculation module, calling three-pulse transfer high-precision calculation and transfer whole-process calculation, and displaying a calculation result in a chart mode; the user selects to save the configuration, the platform directly takes the information of the parameter configuration as an XML file, and the user loads the configuration file by default when opening the software next time.
Description of user operation:
each functional level interface mainly consists of three parts: parameter configuration, result analysis and result display. Parameter configuration is used for configuring parameters required by a task track design; the result analysis is to perform further design calculation according to the display of the preliminary result; and the result is displayed by displaying key data and graphs of the final result. Parameter setting and moon landing windows in the platform belong to a parameter configuration interface, rocket coplanar launching, lunar orbit deployment and ascending windows belong to a result analysis interface, and transfer orbit calculation belongs to a result display interface.
The first step is as follows: the design platform is started.
The second step is that: the platform loads the configuration. And the data in each parameter configuration page is stored in an independent XML file, and the platform calls an import function to display the configuration file data to the interface after the platform is started.
The third step: the user modifies the configuration parameters, clicks 'save configuration', and can save the configuration result into an XML file; and directly clicking 'calculation', directly importing interface configuration parameters into data, calling a corresponding calculation function by the platform, calculating and analyzing a design result, and displaying the result on a result analysis interface.
The fourth step: the user clicks a certain row of results in the result analysis list, and clicks 'single-row calculation' to obtain a high-precision calculation result of the row of tracks; and clicking batch calculation to obtain high-precision results of all initial values of the list.
The fifth step: and switching a selection result display interface, clicking 'track calculation' by a user, analyzing the whole process transfer result of the track in the selected row on the page by using the calculation result, and drawing a curve graph.
And a sixth step: after the result is finished, the user clicks the result saving mode, and the calculation result can be saved in a data file for subsequent viewing.
The seventh step: and (5) exiting the platform.
The invention has the following technical effects:
1) The system may consider constrained coupling between tasks when designing different tasks.
2) The method can calculate the moon landing window and provide a feasible moon landing window on the premise of not designing a specific track.
3) Design initial values do not need to be provided, and only the ranges of design parameters, constraint parameters and traversal time are given, so that the method is convenient for users to use;
4) And respectively displaying the initial value and the high-precision result, and performing high-precision calculation on the basis of a reasonable initial value to improve the design efficiency.
Simulation verification is performed by using an example of manned cyclic month and space station cabin segment transfer, wherein the track epoch of manned cyclic month is 2025 months and 30 days, the track epoch of space station cabin segment transfer is 2024 years, 3 months and 27 days, and the design results are shown in table 1 and table 2. The result of the design is verified by simulation with STK software, as shown in fig. 4 and 5. Wherein, EJ2000 coordinate system is geocentric J2000 coordinate system, MJ2000 is lunar center J2000 coordinate system.
The results of the nominal mission trajectory design for a manned spacecraft in the manned cyclic-lunar mission are shown in table 1.
TABLE 1 nominal mission trajectory for manned spacecraft
The mission trajectory results for the space station service bay duration are shown in table 2.
TABLE 2 nominal task track for service bay of space station
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and it should be noted that, for those skilled in the art, many modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (2)
1. A manned moon exploration task track design system is characterized by comprising a moon landing window subsystem, an unmanned moon winding subsystem, a lunar orbit deployment subsystem, a manned moon surrounding subsystem and a manned moon landing subsystem;
the lunar landing window subsystem is used for re-track deployment and existing track deployment; the re-orbit deployment comprises the steps of calculating a lunar landing window meeting the illumination condition according to the illumination constraint and the longitude and latitude of the landing point, enabling a user to check the lunar landing window meeting the condition in a calculation result list, obtaining a window with a feasible return condition through the deployment orbit calculation, enabling the user to select a target lunar orbit at a certain lunar landing moment from the calculation result, and calculating a rising window aiming at the lunar orbit; the existing orbit deployment comprises the steps of calculating orbit satellite-to-satellite point information according to an existing lunar orbit, determining a lunar falling moment according to user selection, and calculating a rising window;
the lunar orbit deployment subsystem is used for designing a general transfer orbit according to time design parameters, geocentric segment constraint parameters of lunar transfer and target lunar orbit parameters selected and set by a user, calculating an initial value and high precision, and calculating position and speed information of the whole process according to the transfer orbit;
the unmanned lunar-orbiting subsystem is used for designing lunar-orbiting working conditions of the manned spacecraft, and comprises the steps of directly calculating feasible initial values of the free return orbit according to user setting parameters, displaying all feasible initial value results of the orbit in a rocket coplanar launching window, carrying out high-precision calculation on the selected results, and carrying out overall-process orbit data calculation on the orbit selected by a user through orbit calculation;
the manned lunar sub-system is used for respectively carrying out initial value calculation of a free return orbit and three-pulse transfer, high-precision calculation of the free return orbit, high-precision calculation of the three-pulse transfer and the calculation of the whole earth-moon transfer process according to the sequence of parameter configuration, emission window calculation and transfer orbit calculation; according to the sequence of parameter configuration, emission window calculation and transfer orbit calculation, respectively carrying out initial value calculation of monthly return orbit and three-pulse transfer, high-precision calculation of monthly return orbit, high-precision calculation of three-pulse transfer and whole monthly transfer process calculation;
the manned lunar landing subsystem is used for respectively designing a lander and a manned spacecraft to obtain initial values of transfer orbits through configuration parameters, a user selects and calculates results of the initial values of a certain row to perform high-precision calculation, and high-precision three-pulse transfer calculation and calculation of results of the whole process of the transfer orbits are performed on a transfer orbit calculation interface.
2. The manned lunar exploration task trajectory design system according to claim 1, wherein a platform architecture thereof employs a three-level organizational architecture, a first level being a task level comprising: determining a window, winding a moon without a person, carrying a person around the moon, and carrying a person to land the moon; the second level is an object level comprising: manned spacecraft, lander, space station and return section; the third stage is a functional stage comprising: parameter configuration, rocket coplanar launching window, transfer orbit calculation, lunar landing window, lunar orbit deployment and ascending window; the task level is composed of different object level members, the different object level members comprise different function level members, and different manned lunar series tasks are formed through different combinations.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110774269.5A CN113656940B (en) | 2021-07-08 | 2021-07-08 | Manned moon exploration task track design system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110774269.5A CN113656940B (en) | 2021-07-08 | 2021-07-08 | Manned moon exploration task track design system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113656940A CN113656940A (en) | 2021-11-16 |
| CN113656940B true CN113656940B (en) | 2022-10-25 |
Family
ID=78489257
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110774269.5A Active CN113656940B (en) | 2021-07-08 | 2021-07-08 | Manned moon exploration task track design system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113656940B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730200A (en) * | 2011-04-06 | 2012-10-17 | 北京空间技术研制试验中心 | Manned space and lunar exploration spacecraft system based on lunar cycle revisiting orbit and exploration method |
| CN109774973A (en) * | 2019-02-02 | 2019-05-21 | 北京空间技术研制试验中心 | The rising Orbit of Rendezvous Parameters design of manned lunar surface's lander |
| CN110963079A (en) * | 2019-12-18 | 2020-04-07 | 南京航空航天大学 | Overhead crane type manned lunar landing aircraft, lunar landing method and application thereof |
-
2021
- 2021-07-08 CN CN202110774269.5A patent/CN113656940B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730200A (en) * | 2011-04-06 | 2012-10-17 | 北京空间技术研制试验中心 | Manned space and lunar exploration spacecraft system based on lunar cycle revisiting orbit and exploration method |
| CN109774973A (en) * | 2019-02-02 | 2019-05-21 | 北京空间技术研制试验中心 | The rising Orbit of Rendezvous Parameters design of manned lunar surface's lander |
| CN110963079A (en) * | 2019-12-18 | 2020-04-07 | 南京航空航天大学 | Overhead crane type manned lunar landing aircraft, lunar landing method and application thereof |
Non-Patent Citations (1)
| Title |
|---|
| 环月轨道交会的载人登月任务轨道与窗口规划;贺波勇等;《深空探测学报》;20171015(第05期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113656940A (en) | 2021-11-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Batcha et al. | Artemis I trajectory design and optimization | |
| Reynolds et al. | NTP robustness for Mars conjunction and opposition class missions | |
| Young | The twenty-first century commercial space imperative | |
| Gutkowski et al. | Evolution of Orion mission design for exploration mission 1 and 2 | |
| CN113656940B (en) | Manned moon exploration task track design system | |
| Napoli et al. | BioSentinel: Mission Summary and Lessons Learned From the First Deep Space Biology CubeSat Mission | |
| Finger et al. | Public-private spaceport development | |
| CN113656939A (en) | Manned lunar landing orbit design method based on lunar orbit | |
| Goodliff et al. | HEOMD Strategic Campaign Operations Plan for Exploration | |
| Finger et al. | Economic Factors Driving Commercial Ventures Away From the National Ranges | |
| Finger et al. | State Spaceports-If You Build it, Will They Come? | |
| Stern et al. | Pluto orbiter–Kuiper belt explorer: Mission design for the gold standard | |
| Watson-Morgan et al. | NASA’s Human Landing System: A Sustaining Presence on the Moon | |
| Rana et al. | Parametric sizing Boeing X-20 DynaSoar to gain program architectural understanding of Sierra Nevada Corporation’s Dream Chaser | |
| Gangale | Time Maps of Human Spaceflight: 1965-1967 | |
| Studer | Spacecraft trajectory optimisation for asteroid mining | |
| Gutkowski et al. | Trajectory Design Analysis over the Lunar Nodal Cycle for the Multi-Purpose Crew Vehicle (MPCV) Exploration Mission 2 (EM-2) | |
| CN118153348A (en) | Integrated design system, design method and electronic equipment for manned lunar-entering task track | |
| Badikov et al. | Economic model of costs required to create and operate the Starlink fast internet system | |
| Burke et al. | A Selective History of the Jet Propulsion Laboratory | |
| Genova et al. | Transfers from TLI to Lunar Frozen Orbits with Applications to NASA's CLPS & ARTEMIS Programs | |
| Haws et al. | SLS with Kick Stages for Outer Planet Science Missions | |
| Konstantinov et al. | Ballistic design of a solar probe into a heliocentric orbit with a large inclination to the solar equator | |
| Zhou et al. | Research on Integrated Mission Planning and Design Method for China’s Manned Lunar Exploration | |
| Gangale et al. | Time Maps of Human Spaceflight: 1962-1964 |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |