Lunar surface take-off return transportation system and method
By using a two-stage solid fuel vector engine and reaction control system in the lunar take-off and return transport system, the problem of complex and low flexibility in the return transport technology of the moon returning to the earth is solved, and simplified flight operation process and improved flexibility are achieved.
Patent Information
- Application Number
- CN202510270062.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-07
- Publication Date
- 2025-06-27
AI Technical Summary
The return transportation technology of returning to the earth from the moon has problems of complex flight operation processes and low flexibility.
A lunar take-off return transport system is adopted, which includes a sequentially connected return chamber, a service chamber, a first stage interstage, a second stage solid fuel vector engine, a second stage interstage and a first stage solid fuel vector engine. Through the use of a series connection and reaction control system of two-stage solid fuel vector engines, multiple attitude adjustments and speed increments of the aircraft are realized, simplifying the flight operation process and improving flexibility.
The flight operation process of the moon surface take-off and return transportation system has been simplified, and flexibility has been improved, so that the system is not limited by the moon surface take-off position and take-off time, which has improved the flexibility and efficiency of flight transportation.
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Figure CN120207612A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of aircraft, and particularly to a lunar takeoff and return transportation system and method. Background Art
[0002] The lunar exploration mission is an important part of human deep space exploration. Among them, in the return transportation application scenario from the moon to the earth, the lunar orbit rendezvous scheme and the direct lunar takeoff and return to the earth scheme have been widely used.
[0003] Specifically, in the direct lunar takeoff and return to the earth scheme, the aircraft usually has a single-stage rocket configuration, with low launch efficiency. In addition, the single-stage rocket configuration has more constraints on the launch position and launch window time. Both the Apollo mission and the Chang'e mission adopted the lunar orbit rendezvous scheme, which requires complex orbital rendezvous operations and reduces the flexibility of the mission.
[0004] It can be seen that the return transportation technology from the moon to the earth has problems such as complex flight operation processes and low flexibility. Summary of the Invention
[0005] The technical problem to be solved by the present invention is that the return transportation system from the moon to the earth has problems such as complex flight operation processes and low flexibility.
[0006] To solve the above technical problems, the present invention provides a lunar takeoff and return transportation system and method, and specifically adopts the following technical solutions:
[0007] In a first aspect, the present invention provides a lunar takeoff and return transportation system, including: a return capsule, a service module, a first interstage section, a second-stage solid fuel vector engine, a second interstage section, and a first-stage solid fuel vector engine connected in sequence. Among them, a reaction control system is provided in the service module. The return capsule is used to load the transportation target. The first-stage solid fuel vector engine is used to propel the return capsule into the lunar sub-orbit and make the return capsule glide in the lunar sub-orbit. The second-stage solid fuel vector engine is used to start at the first ignition moment to propel the return capsule from the lunar sub-orbit into the earth-moon transfer orbit and make the return capsule glide in the earth-moon transfer orbit. The first ignition moment is determined according to the position, speed, and attitude information of the return capsule gliding in the lunar sub-orbit. The reaction control system is used to control the return capsule to enter the reentry point from the earth-moon transfer orbit, so that the return capsule returns to the earth's surface from the reentry point. The second interstage section is used to connect the first-stage solid fuel vector engine and the second-stage solid fuel vector engine, and separate from the second-stage solid fuel vector engine before the second-stage solid fuel vector engine starts. The first interstage section is used to connect the service module and the second-stage solid fuel vector engine, and separate from the service module after the second-stage solid fuel vector engine shuts down.
[0008] In this system, the two-stage solid fuel vector engines (i.e., the first-stage solid fuel vector engine and the second-stage solid fuel vector engine) can be connected in series through the first intermediate section and the second intermediate section, thereby improving the carrying capacity of the lunar takeoff and return transportation system. Moreover, the two ignitions of the two-stage solid fuel vector engines can provide two velocity increments, combined with the "first propulsion stage - first glide stage - second propulsion stage - second glide stage" flight method adopted by the lunar takeoff and return transportation system. In this way, the flight operation process of the lunar takeoff and return transportation system can be simplified, and the flexibility can be improved. In addition, the lunar takeoff and return transportation system can be unrestricted in terms of the takeoff position and takeoff time on the lunar surface to further enhance the flexibility of flight transportation.
[0009] Combined with the first aspect, in an alternative implementation, the reaction control system is further configured to: perform a first attitude adjustment on the return capsule to enable the return capsule to enter the lunar sub-orbit. And / or, perform a second attitude adjustment on the return capsule to enable the return capsule to glide in the lunar sub-orbit. And / or, perform a third attitude adjustment on the return capsule to enable the return capsule to enter the Earth-moon transfer orbit. And / or, perform a fourth attitude adjustment on the return capsule to enable the return capsule to glide in the Earth-moon transfer orbit.
[0010] Combined with the first aspect, in an alternative implementation, during the process of the return capsule gliding in the Earth-moon transfer orbit, the reaction control system is further configured to: perform a slow rotation attitude towards the sun at 0.5° / s - 2° / s to achieve passive temperature control of the return capsule.
[0011] Combined with the first aspect, in an alternative implementation, during the process of the return capsule gliding in the Earth-moon transfer orbit, the reaction control system is further configured to: spin at an angular velocity of 10 r / min - 15 r / min to control the spin stability of the return capsule during reentry.
[0012] Combined with the first aspect, in an alternative implementation, after the return capsule enters the reentry point from the Earth-moon transfer orbit, the service module separates from the return capsule.
[0013] Combined with the first aspect, in an alternative implementation, after the return capsule enters the reentry point from the Earth-moon transfer orbit, the return capsule reenters the atmosphere in a ballistic manner and returns to the Earth.
[0014] Combined with the first aspect, in an alternative implementation, the service module is also provided with an energy system. The energy system is used to collect solar energy, convert solar energy into electrical energy, and provide electrical energy for the lunar takeoff and return transportation system.
[0015] In combination with the first aspect, in an alternative implementation, the service module is also provided with an integrated electronics system and a thermal control system. Among them, the integrated electronics system is used to provide control management for spacecraft management, attitude control, TT&C communication, and payload tasks. The thermal control system is used to control the temperature of the lunar takeoff and return transportation system within a preset safe operating temperature range.
[0016] In combination with the first aspect, in an alternative implementation, the second interstage section is an open semi-monocoque structure.
[0017] In a second aspect, the present invention provides a lunar takeoff and return transportation method, which can be applied to a lunar takeoff and return transportation system. The system includes: a return capsule, a service module, a first interstage section, a second-stage solid fuel vector engine, a second interstage section, and a first-stage solid fuel vector engine connected in sequence. Among them, a reaction control system is provided in the service module. Specifically, the method includes: First, start the first-stage solid fuel vector engine, and perform a first attitude adjustment on the return capsule through the reaction control system to make the return capsule enter the lunar suborbital; the return capsule is used to load the transportation target. Then, after the return capsule enters the lunar suborbital, turn off the first-stage solid fuel vector engine, and perform a second attitude adjustment on the return capsule through the reaction control system to make the return capsule glide in the lunar suborbital. Next, before the first ignition moment, control the separation of the second interstage section from the second-stage solid fuel vector engine; the first ignition moment is determined according to the position, speed, and attitude information of the return capsule gliding in the lunar suborbital. Then, at the first ignition moment, start the second-stage solid fuel vector engine, and perform a third attitude adjustment on the return capsule through the reaction control system to make the return capsule enter the Earth-moon transfer orbit from the lunar suborbital. Further, after the return capsule enters the Earth-moon transfer orbit, turn off the second-stage solid fuel vector engine, and perform a fourth attitude adjustment on the return capsule through the reaction control system to make the return capsule glide in the Earth-moon transfer orbit. Next, after turning off the second-stage solid fuel vector engine, control the separation of the first interstage section from the service module. Finally, control the return capsule to enter the reentry point from the Earth-moon transfer orbit through the reaction control system, so that the return capsule returns to the Earth's surface from the reentry point.
[0018] In a third aspect, an electronic device is provided, including: a memory, one or more processors; the memory is coupled to the processor; among them, computer program code is stored in the memory, and the computer program code includes computer instructions. When the computer instructions are executed by the processor, the electronic device is caused to execute the method provided in the second aspect as described above.
[0019] In a fourth aspect, a computer-readable storage medium is provided, including computer instructions. When the computer instructions run on an electronic device, the electronic device is caused to execute the method provided in the second aspect as described above.
[0020] Understandably, for the beneficial effects that can be achieved by the lunar takeoff and return transportation method provided in the second aspect above, the electronic device in the third aspect, and the computer-readable storage medium in the fourth aspect, reference can be made to the beneficial effects in the first aspect and any of its possible design manners, which will not be elaborated here. BRIEF DESCRIPTION OF THE DRAWINGS
[0021] Figure 1 FIG. is a schematic structural diagram of a lunar takeoff and return transportation system provided by an embodiment of the present application;
[0022] Figure 2 FIG. is a schematic structural diagram of the separated lunar takeoff and return transportation system provided by an embodiment of the present application Figure 1 ;
[0023] Figure 3 FIG. is a schematic structural diagram of the separated lunar takeoff and return transportation system provided by an embodiment of the present application Figure 2 ;
[0024] Figure 4 FIG. is a schematic flowchart of a lunar takeoff and return transportation method provided by an embodiment of the present application;
[0025] Figure 5 FIG. is a flight schematic diagram of a lunar takeoff and return transportation method provided by an embodiment of the present application. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0026] The embodiments will be described in detail below, and the examples are shown in the drawings. When the following description refers to the drawings, unless otherwise indicated, the same numbers in different drawings represent the same or similar elements. The embodiments described in the following examples do not represent all embodiments consistent with the present application. They are merely examples of systems and methods consistent with some aspects of the present application detailed in the claims.
[0027] The lunar exploration mission is an important part of human deep space exploration. Among them, in the application scenario of returning from the moon to the earth, the lunar orbit rendezvous scheme and the lunar takeoff and direct return to the earth scheme have been widely used.
[0028] Specifically, in the lunar takeoff and direct return to the earth scheme, the aircraft is usually configured as a single-stage rocket, with low launch efficiency. In addition, the single-stage rocket configuration has more constraints on the launch position and launch window time. Both the Apollo mission and the Chang'e mission adopted the lunar orbit rendezvous scheme, which requires complex orbit rendezvous operations and reduces the flexibility of the mission.
[0029] It can be seen that the related technologies for returning from the moon to the earth have problems such as complex flight operation processes and low flexibility.
[0030] To solve the above problems, an embodiment of the present application provides a lunar takeoff and return transportation system and method. Among them, the lunar takeoff and return transportation system is a lightweight transportation system. By connecting two inter-stage sections in series with two-stage solid fuel vector engines, the carrying capacity of the lunar takeoff and return transportation system can be improved. Two speed increments can be provided by the two-stage solid fuel vector engines starting twice by ignition, and a flight method of "the first propulsion stage - the first glide stage - the second propulsion stage - the second glide stage" is adopted. In this way, the flight operation process of the lunar takeoff and return transportation system is simple and highly flexible. Moreover, the takeoff position and takeoff time on the lunar surface can be not limited.
[0031] The following introduces the solution provided by the embodiment of the present application in conjunction with the accompanying drawings.
[0032] Specifically, Figure 1 is a schematic structural diagram of the lunar takeoff and return transportation system provided by the embodiment of the present application. As Figure 1 shown, the lunar takeoff and return transportation system 100 provided by the embodiment of the present application includes: a return capsule 110, a service module 120, a first inter-stage section 130, a two-stage solid fuel vector engine 140, a second inter-stage section 150, and a one-stage solid fuel vector engine 160, which are connected in sequence.
[0033] In the embodiment of the present application, the return capsule 110 is the capsule section that the lunar takeoff and return transportation system needs to transport back to the Earth. The return capsule 110 can be used to load the transportation target. Exemplarily, the transportation target can be lunar soil samples collected from the Moon.
[0034] The service module 120 can be used to perform the separation and release operation of the return capsule 110. Among them, a reaction control system 121 is provided in the service module 120. The reaction control system 121 can be used to ensure the attitude stability of the return capsule 110 during the propulsion stage, the correction during the glide stage, adjust the alignment of the combined body of the return capsule 110 and the service module 120 to the atmospheric re-entry attitude before the separation of the return capsule 110, and provide the spin angular velocity of the return capsule 110 before separation.
[0035] The one-stage solid fuel vector engine 160 can be used to propel the return capsule 110 (that is, the combined body of the return capsule 110, the service module 120, the first inter-stage section 130, the two-stage solid fuel vector engine 140, the second inter-stage section 150, and the one-stage solid fuel vector engine 160) into the lunar sub-orbit and make the return capsule 110 glide in the lunar sub-orbit.
[0036] In the embodiments of the present application, the first-stage solid fuel vector engine 160 is a vector engine using solid fuel. The thrust generated by the first-stage solid fuel vector engine 160 can propel the return capsule 110 into the lunar sub-orbit and cause the return capsule 110 to glide in the lunar sub-orbit. That is, the return capsule 110 enters the first propulsion stage and the first gliding stage.
[0037] Specifically, from startup (ignition) to shutdown, the first-stage solid fuel vector engine 160 can propel the return capsule 110 into the lunar sub-orbit, i.e., the first propulsion stage.
[0038] Furthermore, from the shutdown of the first-stage solid fuel vector engine 160 to the startup of the second-stage solid fuel vector engine 140, the return capsule 110 is in a gliding state in the lunar sub-orbit, i.e., the first gliding stage.
[0039] In some embodiments, during the first propulsion stage, the reaction control system 121 can be used to perform a first attitude adjustment on the return capsule 110 so that the return capsule 110 enters the lunar sub-orbit. Among them, the first attitude adjustment can include one or more attitude adjustments.
[0040] In some embodiments, during the first gliding stage, the reaction control system 121 can also be used to perform a second attitude adjustment and correction on the return capsule 110 so that the return capsule 110 glides stably in the lunar sub-orbit. Among them, the second attitude adjustment can include one or more attitude adjustments.
[0041] In the embodiments of the present application, the second interstage section 150 can be used to connect the first-stage solid fuel vector engine 160 and the second-stage solid fuel vector engine 140, and separate from the second-stage solid fuel vector engine 140 before the second-stage solid fuel vector engine 140 starts.
[0042] Specifically, Figure 2 is a schematic diagram of the structure after separation of the lunar takeoff and return transportation system provided by the embodiments of the present application Figure 1 , as Figure 2 shown, the second interstage section 150 separates from the second-stage solid fuel vector engine 140, that is, the second interstage section 150 and the first-stage solid fuel vector engine 160 separate from the lunar takeoff and return transportation system 100, and the combination of the return capsule 110, the service module 120, the first interstage section 130, and the second-stage solid fuel vector engine 140 is retained. After the second interstage section 150 and the first-stage solid fuel vector engine 160 separate, they can fall back to the lunar surface, so as to facilitate the ignition and startup of the second-stage solid fuel vector engine 140. And it can prevent the first-stage solid fuel vector engine 160 from staying in the lunar sub-orbit and affecting other tasks.
[0043] In some embodiments, the second-stage intermediate section 150 may be an open semi-rigid shell structure. In this way, the gas flow generated by the operation of the second-stage solid fuel vector engine 140 can be discharged outside the second-stage intermediate section 150, thereby realizing the stage separation between the second-stage solid fuel vector engine 140 and the first-stage solid fuel vector engine 160.
[0044] The second-stage solid fuel vector engine 140 can be used to start at the first ignition moment to propel the reentry capsule 110 (i.e., the combination of the reentry capsule 110, the service module 120, the first-stage intermediate section 130, and the second-stage solid fuel vector engine 140) from the lunar sub-orbit into the Earth-Moon transfer orbit, and make the reentry capsule 110 glide in the Earth-Moon transfer orbit.
[0045] In the embodiments of the present application, the second-stage solid fuel vector engine 140 is a vector engine using solid fuel. The second-stage solid fuel vector engine 140 generates thrust to provide a velocity increment to propel the reentry capsule 110 from the lunar sub-orbit into the Earth-Moon transfer orbit, and make the reentry capsule 110 glide in the Earth-Moon transfer orbit. Even if the reentry capsule 110 enters the second propulsion stage and the second gliding stage.
[0046] Specifically, from the start to the shutdown of the second-stage solid fuel vector engine 140, the reentry capsule 110 can be propelled into the Earth-Moon transfer orbit, that is, the second propulsion stage.
[0047] Among them, the first ignition moment can be determined according to the position, velocity, and attitude information of the reentry capsule 110 gliding in the lunar sub-orbit. In one implementation, the first ignition moment can be determined according to the position, velocity, and attitude information of the reentry capsule 110 gliding in the lunar sub-orbit, as well as the predicted position, velocity, and attitude information of the reentry capsule 110 after the shutdown of the second-stage solid fuel vector engine 140.
[0048] Furthermore, from the shutdown of the second-stage solid fuel vector engine 140 to reaching the reentry point, the reentry capsule 110 is in a gliding state in the Earth-Moon transfer orbit, that is, the second gliding stage.
[0049] In some embodiments, in the second propulsion stage, the reaction control system 121 can be used to perform a third attitude adjustment on the reentry capsule 110 to make the reentry capsule 110 enter the Earth-Moon transfer orbit. Among them, the third attitude adjustment can include one or more attitude adjustments.
[0050] In some embodiments, in the second gliding stage, the reaction control system 121 can also be used to perform a fourth attitude adjustment and correction on the reentry capsule 110 to make the reentry capsule 110 glide stably in the Earth-Moon transfer orbit. Among them, the fourth attitude adjustment can include one or more attitude adjustments.
[0051] The first interstage section 130 may be used to connect the service module 120 and the second-stage solid fuel vectoring engine 140 , and may be separated from the service module 120 after the second-stage solid fuel vectoring engine 140 is shut down.
[0052] Specifically, Figure 3 Schematic diagram of the structure of the lunar takeoff and return transportation system after separation provided in the embodiment of the present application Figure 2 ,like Figure 3 As shown, the first interstage 130 is separated from the service module 120, that is, the first interstage 130 and the second-stage solid fuel vector engine 140 are separated from the lunar surface take-off and return transportation system 100, and the combination of the return module 110 and the service module 120 is retained.
[0053] In the embodiment of the present application, the reaction control system 121 can also be used to control the return capsule 110 to enter the re-entry point from the lunar-earth transfer orbit, so that the return capsule 110 returns to the earth's surface from the re-entry point.
[0054] In some embodiments, after the return capsule 110 enters the re-entry point from the lunar-earth transfer orbit, the service module 120 separates from the return capsule 110 .
[0055] In some embodiments, after the return capsule 110 enters the re-entry point from the lunar-earth transfer orbit, the return capsule 110 re-enters the atmosphere from the re-entry point in a ballistic manner and returns to the Earth's surface.
[0056] In one implementation, the return capsule 110 may land on the ground via atmospheric drag and parachute deceleration.
[0057] In some embodiments, while the return capsule 110 is gliding in the lunar-earth transfer orbit, the reaction control system 121 is also used to achieve passive temperature control of the return capsule 110 with a slow rotation attitude toward the sun of 0.5° / s-2° / s. In this way, the lunar takeoff and return transportation system can make the exposure time of each structural surface relative to the sun more balanced, thereby avoiding one side from being exposed to strong light for a long time and having too high a temperature. At the same time, it also avoids the other side from being in the shadow for a long time and having too low a temperature. This uniform heating can effectively reduce thermal gradients and reduce damage to structures and electronic components caused by thermal stress.
[0058] In addition, the use of passive temperature control methods can reduce dependence on active heating or cooling equipment, thereby reducing the energy consumption and complexity of the lunar takeoff and return transportation system, and improving the overall reliability and long-term operation safety of the lunar takeoff and return transportation system.
[0059] In one implementation, the reaction control system 121 can achieve passive temperature control of the return capsule 110 at a slow rotation attitude of 1° / s. Since 1° / s is a relatively slow rotation rate, it can meet the thermal control requirements without causing significant centrifugal force or other dynamic disturbances, thereby ensuring that the lunar takeoff and return transportation system can operate stably under low load without affecting the overall flight trajectory and mission execution.
[0060] In some embodiments, while the return capsule 110 is gliding in the lunar-earth transfer orbit, the reaction control system 121 is also used to: spin at an angular velocity of 10 r / min-15 r / min to control the re-entry spin stability of the return capsule 110.
[0061] By using the lunar takeoff and return transportation system provided in the embodiment of the present application, the two-stage solid fuel vector engine (i.e., the first-stage solid fuel vector engine and the second-stage solid fuel vector engine) can be connected in series through the first interstage and the second interstage, thereby improving the carrying capacity of the lunar takeoff and return transportation system. In addition, two speed increments can be provided by igniting and starting the two-stage solid fuel vector engine twice, and combined with the "first propulsion stage-first glide stage-second propulsion stage-second glide stage" flight method adopted by the lunar takeoff and return transportation system. In this way, the flight operation process of the lunar takeoff and return transportation system can be simplified and its flexibility can be improved. In addition, the lunar takeoff and return transportation system can not limit the takeoff position and takeoff time on the lunar surface, so as to further improve the flexibility of flight transportation.
[0062] In some embodiments, the service module 120 is further provided with an energy system 122. The energy system 122 can be used to collect solar energy, convert the solar energy into electrical energy, and provide electrical energy for the lunar takeoff and return transportation system.
[0063] In some embodiments, the energy system 122 may include a plurality of solar panels, and the plurality of solar panels may be attached to the outer surface of the service module 120 to collect solar energy.
[0064] In some embodiments, the service module 120 is also provided with an integrated electronics system and a thermal control system. The integrated electronics system can exchange information with the lower computers of other cabin components through the bus and interface in the lunar takeoff and return transportation system to provide satellite management, attitude control, measurement and control communications, and control and management of payload tasks. The thermal control system can be used to control the temperature of the lunar takeoff and return transportation system within a preset safe operating temperature range. That is, the thermal control system can control each subsystem in the lunar takeoff and return transportation system to operate within its safe operating temperature range to ensure that each cabin component in the lunar takeoff and return transportation system operates normally.
[0065] The embodiment of the present application further provides a lunar takeoff and return transportation method, which can be applied to a lunar takeoff and return transportation system as shown in Figure 1 Specifically, Figure 4 FIG. Figure 4 is a schematic flowchart of the lunar takeoff and return transportation method provided by the embodiment of the present application. As shown in
[0066] S101. Turn on the first-stage solid fuel vector engine, and perform a first attitude adjustment on the return capsule through the reaction control system to enable the return capsule to enter the lunar sub-orbit.
[0067] Specifically, Figure 5 FIG. Figure 5 is a flight schematic diagram of the lunar takeoff and return transportation method provided by the embodiment of the present application. After the first-stage solid fuel vector engine is turned on, that is, from startup to shutdown of the first-stage solid fuel vector engine, it can propel the return capsule into the lunar sub-orbit, that is, the first propulsion stage (S1). Among them, the return capsule can be used to load transportation targets.
[0068] S102. After the return capsule enters the lunar sub-orbit, turn off the first-stage solid fuel vector engine, and perform a second attitude adjustment on the return capsule through the reaction control system to enable the return capsule to glide in the lunar sub-orbit.
[0069] Specifically, as shown in Figure 5 , from the shutdown of the first-stage solid fuel vector engine to the startup of the second-stage solid fuel vector engine, the return capsule is in a gliding state in the lunar sub-orbit, that is, the first gliding stage (S2).
[0070] S103. Before the first ignition moment, control the separation of the second interstage section and the second-stage solid fuel vector engine. The first ignition moment can be determined according to the position, speed, and attitude information of the return capsule gliding in the lunar sub-orbit.
[0071] S104. At the first ignition moment, turn on the second-stage solid fuel vector engine, and perform a third attitude adjustment on the return capsule through the reaction control system to enable the return capsule to enter the Earth-Moon transfer orbit from the lunar sub-orbit.
[0072] Specifically, as shown in Figure 5 , from the startup of the second-stage solid fuel vector engine at the first ignition moment to shutdown, it can propel the return capsule into the Earth-Moon transfer orbit, that is, the second propulsion stage (S3).
[0073] S105. After the return capsule enters the Earth-Moon transfer orbit, turn off the second-stage solid fuel vector engine, and perform a fourth attitude adjustment on the return capsule through the reaction control system to enable the return capsule to glide in the Earth-Moon transfer orbit.
[0074] Specifically, as Figure 5 shown, from the shutdown of the secondary solid fuel vector engine to the arrival at the reentry point, the return capsule is in a gliding state on the lunar-earth transfer orbit, that is, the second gliding stage (S4).
[0075] S106. After shutting down the secondary solid fuel vector engine, control the separation of the first stage section from the service module.
[0076] S107. Control the return capsule to enter the reentry point from the lunar-earth transfer orbit through the reaction control system, so that the return capsule returns to the earth's surface from the reentry point.
[0077] In some embodiments, before starting the primary solid fuel vector engine in S101, the lunar takeoff return transportation system can be erected so that the lunar takeoff return transportation system takes off in a vertical state.
[0078] In some embodiments, after the return capsule enters the reentry point from the lunar-earth transfer orbit in S107, the return capsule reenters the atmosphere in a ballistic manner and returns to the earth.
[0079] In one implementation, the return capsule can land on the ground through atmospheric drag and parachute deceleration.
[0080] By using the lunar takeoff return transportation method provided in the embodiments of the present application, two velocity increments can be provided through two ignitions of the two-stage solid fuel vector engine, and in combination with the "first propulsion stage - first gliding stage - second propulsion stage - second gliding stage" flight method adopted by the lunar takeoff return transportation system. In this way, the flight operation process of the lunar takeoff return transportation system can be simplified and the flexibility can be improved. Moreover, the lunar takeoff return transportation system can not be limited to the takeoff position and takeoff time on the lunar surface to further improve the flexibility of flight transportation.
[0081] The embodiments of the present invention also provide an electronic device, which may include: a display screen, a memory, and one or more processors. The display screen, the memory, and the processor are coupled. The memory is used to store computer program code, and the computer program code includes computer instructions. When the processor executes the computer instructions, the electronic device can execute each method or step executed in the above embodiments of the lunar takeoff return transportation method. Of course, the electronic device includes, but is not limited to, the above display screen, memory, and one or more processors.
[0082] The embodiments of the present invention also provide a computer-readable storage medium for storing computer instructions for running the above lunar takeoff return transportation method.
[0083] Through the description of the above embodiments, those skilled in the art can clearly understand that for the convenience and conciseness of description, only the division of the above functional modules is used as an example. In actual applications, the above functions can be assigned to different functional modules as needed, that is, the internal structure of the device is divided into different functional modules to complete all or part of the functions described above.
[0084] In the description of the present invention, it should be understood that the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise specifically defined.
[0085] In the present invention, unless otherwise clearly defined and limited, the terms "installed", "connected", "connected", "fixed", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.
[0086] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.
[0087] The similar parts between the embodiments provided in this application can be referred to each other. The specific embodiments provided above are only several examples under the general concept of this application and do not constitute a limitation on the protection scope of this application. For those skilled in the art, any other embodiments extended based on the solution of this application without creative work belong to the protection scope of this application.
Claims
1. A lunar takeoff and return transportation system, characterized in that: include: A return module, a service module, a first interstage, a second solid fuel vector engine, a second interstage and a first solid fuel vector engine connected in sequence; wherein a reaction control system is provided in the service module; The return capsule is used to load the transport target; The first-stage solid fuel vector engine is used to propel the return capsule into the lunar suborbital and enable the return capsule to glide in the lunar suborbital; The two-stage solid fuel vector engine is used to start at a first ignition time to propel the return capsule from the lunar suborbital into the lunar-earth transfer orbit, and to make the return capsule glide on the lunar-earth transfer orbit; the first ignition time is determined according to the position, speed and attitude information of the return capsule gliding on the lunar suborbital; The reaction control system is used to control the return capsule to enter the re-entry point from the lunar-earth transfer orbit, so that the return capsule returns to the earth's surface from the re-entry point; The second interstage section is used to connect the first-stage solid fuel vector engine and the second-stage solid fuel vector engine, and is separated from the second-stage solid fuel vector engine before the second-stage solid fuel vector engine is started; The first interstage section is used to connect the service module and the second-stage solid fuel vector engine, and is separated from the service module after the second-stage solid fuel vector engine is shut down.
2. The system according to claim 1, characterized in that The reaction control system is also used for: Performing a first attitude adjustment on the return capsule to enable the return capsule to enter the lunar suborbital; and / or, performing a second attitude adjustment on the return capsule so as to enable the return capsule to glide in the lunar suborbital; and / or, performing a third attitude adjustment on the return capsule to enable the return capsule to enter the lunar-to-earth transfer orbit; And / or, performing a fourth attitude adjustment on the return capsule so as to enable the return capsule to glide in the lunar-earth transfer orbit.
3. The system according to claim 1, characterized in that During the sliding of the return module in the lunar-earth transfer orbit, the reaction control system is further used to: Passive temperature control of the return capsule is achieved by slowly rotating the capsule toward the sun at a speed of 0.5° / s-2° / s.
4. The system according to claim 1, characterized in that During the sliding of the return module in the lunar-earth transfer orbit, the reaction control system is further used to: The reentry spin stability of the return capsule is controlled by spinning at an angular velocity of 10 r / min-15 r / min.
5. The system according to claim 1, characterized in that After the return capsule enters the re-entry point from the lunar-earth transfer orbit, the service module separates from the return capsule.
6. The system according to claim 1, characterized in that After the return capsule enters the re-entry point from the lunar-earth transfer orbit, the return capsule re-enters the atmosphere from the re-entry point in a ballistic manner and returns to the earth.
7. The system according to claim 1, characterized in that The service cabin is also provided with an energy system; The energy system is used to collect solar energy, convert the solar energy into electrical energy, and provide the electrical energy for the lunar takeoff and return transportation system.
8. The system according to claim 1, characterized in that The service module is also provided with an integrated electronics system and a thermal control system; The integrated electronics system is used to provide satellite management, attitude control, telemetry and communication, and control and management of payload missions; The thermal control system is used to control the temperature of the lunar takeoff and return transportation system to be within a preset safe operating temperature range.
9. The system according to claim 1, characterized in that The second stage section is an open semi-rigid shell structure.
10. A lunar takeoff and return transportation method, characterized in that: Applied to a lunar takeoff and return transportation system, the system comprises: a return module, a service module, a first interstage, a second-stage solid fuel vector engine, a second interstage and a first-stage solid fuel vector engine connected in sequence; wherein a reaction control system is provided in the service module; The method comprises: Starting the first-stage solid fuel vector engine, and performing a first attitude adjustment on the return capsule through the reaction control system, so that the return capsule enters the lunar suborbital; wherein the return capsule is used to load a transport target; After the return capsule enters the lunar suborbital, shutting down the first-stage solid fuel vector engine, and performing a second attitude adjustment on the return capsule through the reaction control system, so that the return capsule glides in the lunar suborbital; Before a first ignition time, the second interstage is controlled to separate from the second-stage solid fuel vector engine; wherein the first ignition time is determined according to the position, speed and attitude information of the return capsule gliding in the lunar suborbital; At the first ignition time, the second-stage solid fuel vector engine is started, and the return capsule is subjected to a third attitude adjustment through the reaction control system, so that the return capsule enters the lunar-earth transfer orbit from the lunar suborbital orbit; After the return capsule enters the lunar-earth transfer orbit, shutting down the second-stage solid fuel vector engine, and performing a fourth attitude adjustment on the return capsule through the reaction control system, so that the return capsule glides in the lunar-earth transfer orbit; After shutting down the second-stage solid fuel vector engine, controlling the first interstage segment to separate from the service module; The reaction control system controls the return capsule to enter a re-entry point from the lunar-to-earth transfer orbit, so that the return capsule returns to the earth's surface from the re-entry point.