Commercial spaceflight electromagnetic emission combined test verification platform

Abstract

The invention, which relates to the technical field of spaceflight electromagnetic emission, discloses a commercial spaceflight electromagnetic emission combined test verification platform comprising an emission track area and a storage and transformation center. The launching track area comprises a launching track subsystem, an electromagnetic propulsion subsystem and a comprehensive guarantee subsystem; the storage and transformation center comprises a superconducting zero-level booster subsystem and a control center. Aiming at the low-cost, high-frequency and customized launching requirements of a large-scale near-earth orbit constellation, the method fully considers the existing technical levels of a spaceflight electromagnetic launching system and a carrier rocket, and aims at improving the carrying capacity, shortening the launching period, reducing the launching cost and the like.

Description

Technical Field

[0001] This invention relates to the field of aerospace electromagnetic launch technology, and more specifically to the field of a commercial aerospace electromagnetic launch joint test and verification platform technology. Background Technology

[0002] Commercial electromagnetic launch is a novel launch method that can be viewed as a reusable "stage-zero booster" for space launch vehicles. It utilizes magnetic levitation technology to eliminate friction and vibration by decoupling from the orbit, and electromagnetic propulsion technology to provide powerful acceleration capabilities. This allows various space launch vehicles to be safely and efficiently accelerated to supersonic speeds or higher on the ground. It boasts significant advantages such as low cost, reusability, and environmental friendliness. It is a disruptive technology for rapidly improving launch capabilities, reducing launch costs, and achieving low-cost, "flight-like" space transportation, representing a crucial development direction for next-generation space launch technology.

[0003] Commercial reusable electromagnetic launch systems are characterized by large booster mass (tens to hundreds of tons), high booster speed (sonic), limited booster distance, and complex booster environment. This involves the coupling of multiple disciplines, including overall design, electromagnetics, mechanics, aerodynamics, structure, and dynamics, resulting in high system development complexity. To address the core technical challenges arising from these characteristics, such as near-ground supersonic speeds, high thrust, and high power, dedicated research and development of key technologies is required.

[0004] The United States has made electromagnetic launch technology its development goal for the next generation of space launch systems and has carried out a great deal of research, forming a solid technological foundation. Domestic research is still in its infancy. Although relevant demonstrations have been carried out, breakthroughs are urgently needed in various core technologies. Summary of the Invention

[0005] The purpose of this invention is to address the technical challenges of achieving high precision, high power, and high energy density in existing aerospace electromagnetic launch technologies by providing a joint test and verification platform for commercial aerospace electromagnetic launch.

[0006] To achieve the above objectives, the present invention specifically adopts the following technical solution: This invention provides a joint test and verification platform for commercial aerospace electromagnetic launch, including a launch orbit area and a power storage and transformation center; the launch orbit area includes a launch orbit subsystem, an electromagnetic propulsion subsystem, and a comprehensive support subsystem; the power storage and transformation center includes a superconducting zero-stage booster subsystem and a control center. The launch orbit subsystem is the launch basis for the physical components of the joint test and verification platform; The electromagnetic propulsion subsystem is the core power subsystem of the joint test and verification platform. It is used to provide controllable acceleration of the superconducting zero-stage booster subsystem and test load, as well as safe braking of the system. The superconducting zero-stage booster subsystem is the main force-transmitting component in the electromagnetic propulsion process and serves as the moving carrier of the physical part of the joint test and verification platform. The control center is the system hub that combines the physical and digital components of the joint test and verification platform. It uses different software to control and demonstrate the physical and digital components of the entire joint test and verification platform.

[0007] In one embodiment, the launch track subsystem includes a track beam, a lower foundation disposed at the bottom of the track beam, a slide rail disposed on the track beam, and a precast slab; the track beam is used to provide mounting and fixing for equipment within the track and the slide rail, and the slide rail is used to support the superconducting zero-stage booster body and constrain dynamic flight tests.

[0008] In one embodiment, a groove is provided in the middle of the upper surface of the track beam along the track pushing direction, and two slide rails are symmetrically arranged on the upper surface of the track beam along the track pushing direction, with the groove located in the middle of the two slide rails; a receiving device for the positioning and speed measuring device is installed on the top of the track beam.

[0009] Specifically, the track beam is a high-precision reinforced concrete structure with a channel in the middle of the top.

[0010] In one embodiment, the superconducting zero-stage booster subsystem includes a superconducting zero-stage booster body and a mobile data acquisition device disposed on the superconducting zero-stage booster body. An installation assembly for placing the test load is disposed above the superconducting zero-stage booster body. The bottom of the superconducting zero-stage booster body is equipped with two guide sliders that correspond to and cooperate with two slide rails respectively. The two sides of the superconducting zero-stage booster body are respectively equipped with mounting brackets located outside the track beam, and each mounting bracket is equipped with a levitation magnet at the bottom. The superconducting zero-stage booster is equipped with a light source board that works in conjunction with the receiving device to provide position and velocity information for the system's flight tests.

[0011] Specifically, a slide rail is typically installed on the top of the track beam to support and guide the superconducting zero-stage booster body throughout the propulsion and braking process, thereby achieving the target speed, such as... Figure 4 , Figure 5 As shown.

[0012] In one embodiment, the electromagnetic propulsion subsystem mainly includes a superconducting magnet, a ground propulsion module, an eddy current braking module, a converter, an energy storage device, a switching device, an electromagnetic propulsion control system, and a power cable network. From the perspective of energy transfer, both the ground propulsion module and the superconducting magnet are located in the channel. The energy storage device and the converter provide the ground propulsion module with alternating current of variable frequency and amplitude. The energy storage device and the superconducting magnet interact to provide propulsion for the system.

[0013] Specifically, from the perspective of the working principle of electromagnetic propulsion: the joint test and verification platform adopts the same overall electromagnetic propulsion technology scheme as the target scheme, which is "distributed flywheel energy storage + H-bridge converter + matrix switching power supply + double-sided superconducting linear motor". Its working principle is shown in Figure 6: Upon receiving the system's transmission command and control instructions, the electromagnetic propulsion system generates a variable voltage and variable frequency drive control signal based on the current position information of the superconducting zero-stage booster. The signal is then transmitted to the propulsion module via the energy storage subsystem and the converter subsystem through a switching switch, thereby forming a traveling wave magnetic field in space. This traveling wave magnetic field interacts with the DC magnetic field of the mover superconducting magnet. When the traveling wave magnetic field leads the DC magnetic field of the superconducting magnet, propulsion force is generated.

[0014] In one embodiment, the slide rail includes an acceleration section, a coasting section, and an eddy current braking section arranged sequentially. In the acceleration section, the superconducting zero-stage booster body accelerates to the target speed, and in the coasting section, the superconducting zero-stage booster body separates from the test load. After separation, the superconducting zero-stage booster body completes braking in the eddy current braking section, and the separated test load flies to the terminal protection facility.

[0015] In one embodiment, an auxiliary braking section is also provided at the end of the eddy current braking section.

[0016] Specifically, from the perspective of the launch process: the main body of the slide rail is divided into three sections: the acceleration section, the coasting section, and the eddy current braking section, such as... Figure 3 As shown. During the acceleration phase, the system accelerates the superconducting zero-stage booster body to the target velocity, and during the coasting phase, the superconducting zero-stage booster body separates from the test load. After separation, the superconducting zero-stage booster body completes braking in the eddy current braking phase, and the separated test load flies to the terminal protection facility. In special cases, if the eddy current braking phase does not completely brake the superconducting zero-stage booster body, the superconducting zero-stage booster can be braked through an auxiliary eddy current braking phase.

[0017] In one implementation, the integrated support subsystem is a subsystem that provides support for all physical components of the joint test and verification platform. The integrated support subsystem includes the superconducting zero-stage booster body support system, the superconducting magnet support system, and the auxiliary safety braking and protection system.

[0018] In one implementation, the control center includes a launch control system for controlling the physical test process, a data analysis module for processing and analyzing test data, and a supersonic hardware-in-the-loop simulation system based on a hardware-in-the-loop simulation platform.

[0019] In one implementation, the launch control system, the data analysis module, and the supersonic hardware-in-the-loop simulation system share a single hardware device.

[0020] The beneficial effects of this invention are as follows: This invention addresses the low-cost, high-frequency, and customized launch requirements of large-scale near-Earth orbit constellations. It fully considers the existing technological levels of aerospace electromagnetic launch systems and launch vehicles, and focuses on improving launch capacity, shortening launch cycles, and reducing launch costs to form a complete and closed-loop overall scheme for a commercial aerospace electromagnetic launch system. Based on this, it tackles five core key technologies: high-precision, low-magnetic-resistance, high-load-bearing track beam design and development; high-thrust, high-speed, high-efficiency superconducting linear motor design and development; high-power, high-current converter system design at its limits and high-robustness, high-reliability control technology; cluster energy storage unit array construction and energy management technology; and high-reliability / fast-response control technology. It completes the corresponding prototype development and testing, and builds an integrated system to complete full-system verification testing. Attached Figure Description

[0021] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the architecture of a commercial aerospace electromagnetic launch joint test and verification platform according to the present invention; Figure 2 This is a layout diagram of a commercial aerospace electromagnetic launch joint test and verification platform according to the present invention; Figure 3 This is a schematic diagram of the launch trajectory; Figure 4 This is a schematic diagram of the end of the launch trajectory subsystem; Figure 5 This is a schematic diagram of the transmission and reception of the positioning and speed measuring device; Figure 6 This is a schematic diagram of the electromagnetic propulsion subsystem; Attached reference numerals: 1. Launch trajectory subsystem; 2. Superconducting zero-stage booster subsystem; 3. Electromagnetic propulsion subsystem; 4. Control center; 5. Integrated support subsystem; 6. Test load; 11. Track beam; 12. Slide rail; 21. Superconducting zero-stage booster body; 22. Suspension magnet; 31. Ground propulsion module; 32. Superconducting magnet. Detailed Implementation

[0023] To make the technical problems, technical solutions, and technical effects of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0024] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0025] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0026] In the description of the embodiments of the present invention, it should be noted that the terms "inner", "outer", "upper", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the present invention.

[0027] Example 1 like Figures 1 to 6 As shown, this embodiment provides a commercial aerospace electromagnetic launch joint test and verification platform, including a launch orbit area and a power storage and transformation center; the launch orbit area includes a launch orbit subsystem 1, an electromagnetic propulsion subsystem 3, and an integrated support subsystem 5; the power storage and transformation center includes a superconducting zero-stage booster subsystem 2 and a control center 4; Launch orbit subsystem 1 is the launch basis for the physical part of the joint test and verification platform; The electromagnetic propulsion subsystem 3 is the core power subsystem of the joint test and verification platform, which is used to provide controllable acceleration process and safe braking of the superconducting zero-stage booster subsystem 2 and test load 6. Superconducting zero-stage booster subsystem 2 is the main force-transmitting component in the electromagnetic propulsion process and is the moving carrier of the physical part of the joint test and verification platform. Control Center 4 is the system center that combines the physical and digital parts of the joint test and verification platform. It uses different software to control and demonstrate the physical and digital parts of the entire joint test and verification platform.

[0028] Example 2 like Figures 1 to 6 As shown, this embodiment provides a commercial aerospace electromagnetic launch joint test and verification platform, including a launch orbit area and a power storage and transformation center; the launch orbit area includes a launch orbit subsystem 1, an electromagnetic propulsion subsystem 3, and an integrated support subsystem 5; the power storage and transformation center includes a superconducting zero-stage booster subsystem 2 and a control center 4; Launch orbit subsystem 1 is the launch basis for the physical part of the joint test and verification platform; The electromagnetic propulsion subsystem 3 is the core power subsystem of the joint test and verification platform, which is used to provide controllable acceleration process and safe braking of the superconducting zero-stage booster subsystem 2 and test load 6. Superconducting zero-stage booster subsystem 2 is the main force-transmitting component in the electromagnetic propulsion process and is the moving carrier of the physical part of the joint test and verification platform. Control Center 4 is the system center that combines the physical and digital parts of the joint test and verification platform. It uses different software to control and demonstrate the physical and digital parts of the entire joint test and verification platform.

[0029] The launch track subsystem 1 includes a track beam 11, a lower foundation located at the bottom of the track beam 11, a slide rail 12 located on the track beam 11, and a precast slab. The track beam 11 is used to provide mounting and fixing for the equipment inside the track and the slide rail 12. The slide rail 12 is used to support the superconducting zero-stage booster body 21 and to constrain the dynamic flight test.

[0030] A groove is provided in the middle of the upper surface of the track beam 11 along the direction of track pushing. There are two slide rails 12, which are symmetrically arranged on the upper surface of the track beam 11 along the direction of track pushing. The groove is located in the middle of the two slide rails 12. A receiving device for the positioning and speed measuring device is installed on the top of the track beam 11.

[0031] Specifically, the track beam 11 is a high-precision reinforced concrete solid with a channel in the middle of the top.

[0032] The superconducting zero-stage booster subsystem 2 includes a superconducting zero-stage booster body 21 and a mobile data acquisition device installed on the superconducting zero-stage booster body 21. An installation assembly for placing the test load 6 is installed on top of the superconducting zero-stage booster body 21. The bottom of the superconducting zero-stage booster body 21 is provided with two guide sliders that correspond to and cooperate with the two slide rails 12 respectively. The two sides of the superconducting zero-stage booster body 21 are respectively provided with mounting brackets located outside the track beam 11, and each mounting bracket is provided with a levitation magnet 22 at the bottom. The superconducting zero-stage booster body 21 is equipped with a light source board that works together with the receiving device to provide position and velocity information for the system's flight test.

[0033] Specifically, a slide rail 12 is typically mounted on the top of the track beam 11 to support and guide the superconducting zero-stage booster body throughout the propulsion and braking process, thereby achieving the target speed, such as... Figure 4 , Figure 5 As shown.

[0034] Example 3 This embodiment is a further optimization based on embodiment 2, specifically: The electromagnetic propulsion subsystem 3 mainly includes a superconducting magnet 32, a ground propulsion module 31, an eddy current braking module, a converter, an energy storage device, a switching device, an electromagnetic propulsion control system, and a power cable network. From the perspective of energy transfer, both the ground propulsion module 31 and the superconducting magnet 32 ​​are located in the channel. The energy storage device and the converter provide the ground propulsion module 31 with a variable frequency and amplitude alternating current. The energy storage device and the superconducting magnet 32 ​​interact to provide propulsion for the system.

[0035] Specifically, from the perspective of the working principle of electromagnetic propulsion: the joint test and verification platform adopts the same overall electromagnetic propulsion technology scheme as the target scheme, which is "distributed flywheel energy storage + H-bridge converter + matrix switching power supply + double-sided superconducting linear motor". Its working principle is shown in Figure 6: upon receiving the system's transmission command and control instructions, the electromagnetic propulsion system generates a variable voltage and variable frequency drive control signal based on the current position information of the superconducting zero-stage booster. This signal is then transmitted to the propulsion module via the energy storage subsystem and the converter subsystem through a switching switch, thereby forming a traveling wave magnetic field in space. This traveling wave magnetic field interacts with the DC magnetic field of the mover superconducting magnet 32. When the traveling wave magnetic field leads the DC magnetic field of the superconducting magnet 32, propulsion is generated.

[0036] Example 4 This embodiment is a further optimization based on embodiment 3, specifically: The slide rail 12 includes an acceleration section, a coasting section, and an eddy current braking section arranged in sequence. In the acceleration section, the superconducting zero-stage booster body 21 accelerates to the target speed, and in the coasting section, the superconducting zero-stage booster body 21 separates from the test load 6. After separation, the superconducting zero-stage booster body 21 completes braking in the eddy current braking section, and the separated test load 6 flies to the terminal protection facility.

[0037] It also includes an auxiliary braking section located at the end of the eddy current braking section.

[0038] Specifically, from the perspective of the launch process: the main body of the slide rail 12 is divided into three sections: the acceleration section, the coasting section, and the eddy current braking section, as follows: Figure 3 As shown. During the acceleration phase, the system accelerates the superconducting zero-stage booster body to the target speed, and during the coasting phase, the superconducting zero-stage booster body separates from the test load 6. After separation, the superconducting zero-stage booster body completes braking in the eddy current braking phase, and the separated test load 6 flies to the terminal protection facility. In special circumstances, if the eddy current braking phase does not completely brake the superconducting zero-stage booster body, the superconducting zero-stage booster can be braked through an auxiliary eddy current braking phase.

[0039] Example 5 This embodiment is a further optimization based on embodiment 3, specifically: The integrated support subsystem 5 is a subsystem that provides support for all physical components of the joint test and verification platform. The integrated support subsystem 5 includes the superconducting zero-stage booster body 21 support system, the superconducting magnet 32 ​​support system, and the auxiliary safety braking and protection system.

[0040] Control center 4 includes a control system for controlling the physical test process, a data analysis module for processing and analyzing test data, and a supersonic hardware-in-the-loop simulation system based on a hardware-in-the-loop simulation platform.

[0041] The launch control system, data analysis module, and supersonic hardware simulation system share a single hardware device.

[0042] The joint test and verification platform's tests revolved around the launch of the superconducting zero-stage booster and test payload from the launch orbit. A single flight test procedure consisted of six major steps: "transfer," "polar alignment," "acceleration," "separation," "braking," and "reset." The specific procedure is as follows: S1. Transfer: After the superconducting zero-stage booster completes the excitation closed loop, it marks the start of the single flight test process; the superconducting zero-stage booster is transferred to the initial end of the launch orbit by the propulsion of the transfer vehicle along the technical preparation area track, and is ready for pole alignment. S2. Pole alignment: Using a laser reflection scheme, a laser emitting device is installed on the track in the technical preparation area, and a reflecting device is installed on the I-shaped main beam at the tail of the superconducting zero-stage booster. This determines the precise position of the transport vehicle during pole alignment and feeds the precise position information back to the electromagnetic propulsion control system to adjust the initial power angle and meet the launch conditions. The positioning and speed measuring receiver on the track is activated, and the energy storage-converter unit and switching switch are ready for testing. S3, Acceleration: According to the operation instructions issued by the control center's generator control subsystem, power is supplied to the ground module of the superconducting linear motor, and the superconducting zero-stage booster accelerates under the action of electromagnetic thrust until the end of the acceleration phase; S4. Separation: When the superconducting zero-stage booster reaches the coasting phase, the separation unlocking device on the superconducting zero-stage booster unlocks from the test load, the superconducting zero-stage booster enters the braking phase to decelerate, while the test load travels along the track under the action of inertia. S5. Braking: After the superconducting zero-stage booster enters the braking phase, the superconducting magnet and the eddy current braking module interact to generate braking force on the system, and the superconducting zero-stage booster gradually decelerates. Until the end of the launch track, the speed of the eddy current braking module that has not been fully braked is braked by the auxiliary braking arresting cable until it comes to a complete stop. S6. Reset: After the superconducting zero-stage booster completes braking, the power supply is switched off on the launch track; the superconducting zero-stage booster is recovered, and the transport vehicle enters the launch track from the technical preparation area track, docks with the superconducting zero-stage booster, and then pulls the superconducting zero-stage booster to the technical preparation area track.

Claims

1. A commercial spaceflight electromagnetic launch joint test and verification platform, characterized in that, The system comprises a launching track area and a storage and transformation center; the launching track area comprises a launching track subsystem, an electromagnetic propulsion subsystem and a comprehensive guarantee subsystem; the storage and transformation center comprises a superconducting zero-stage booster subsystem and a control center; the electromagnetic propulsion subsystem is used for providing controllable acceleration process of the superconducting zero-stage booster subsystem and test load and safe braking of the system; the superconducting zero-stage booster subsystem is a main force transmission component in the electromagnetic propulsion process; the control center is a system center combined with the entity part and the digital part of the joint test and verification platform, and controls and demonstrates and verifies the entity part and the digital part of the joint test and verification platform through different software.

2. The commercial space electromagnetic launch joint test and verification platform according to claim 1, characterized in that, The launching track subsystem comprises a track beam, a lower foundation arranged at a lower part of the track beam, a slide rail arranged on the track beam and a prefabricated plate; the track beam body is used for providing installation and fixation of equipment in the track and the slide rail, and the slide rail is used for bearing of the superconducting zero-stage booster subsystem and constraint of dynamic navigation test.

3. The commercial space electromagnetic launch joint test and verification platform according to claim 2, characterized in that, A groove is arranged in a middle part of an upper surface of the track beam along a track pushing direction, two slide rails are symmetrically arranged on the upper surface of the track beam along the track pushing direction, and the groove is located in the middle part of the two slide rails; a receiving device of a speed measuring device is arranged on a top part of the track beam.

4. The commercial space electromagnetic launch joint test and verification platform according to claim 3, characterized in that, The superconducting zero-stage booster subsystem comprises a superconducting zero-stage booster body and a mobile data acquisition device arranged on the superconducting zero-stage booster body; an installation assembly for placing a test load is arranged above the superconducting zero-stage booster body. Two guide sliding blocks corresponding to the two slide rails are arranged at a bottom part of the superconducting zero-stage booster body; installation frames are arranged at two side edges of the superconducting zero-stage booster body and located outside the track beam; and a suspension magnet is arranged at a bottom part of each installation frame. An optical source plate is arranged on the superconducting zero-stage booster body and cooperates with the receiving device to provide position and speed information for system navigation test.

5. The commercial space electromagnetic launch joint test and verification platform according to claim 4, characterized in that, The electromagnetic propulsion subsystem mainly comprises a superconducting magnet, a ground propulsion module, an eddy current braking module, a converter, an energy storage device, a switching switch, an electromagnetic propulsion control and a power cable network. The ground propulsion module and the superconducting magnet are arranged in the groove; the energy storage device and the converter provide variable frequency and amplitude alternating current for the ground propulsion module; and the energy storage device interacts with the superconducting magnet to provide propulsion force for the system.

6. The commercial space electromagnetic launch joint test and verification platform according to claim 3, characterized in that, The slide rail comprises an acceleration section, an idling section and an eddy current braking section arranged in sequence; the superconducting zero-stage booster body is accelerated to a target speed on the acceleration section, and the superconducting zero-stage booster body and the test load are separated on the idling section; after separation, the superconducting zero-stage booster body is braked on the eddy current braking section, and the separated test load flies to an end protection facility.

7. The commercial space electromagnetic launch joint test and verification platform according to claim 6, characterized in that, An auxiliary braking section is arranged at an end of the eddy current braking section.

8. The commercial space electromagnetic launch joint test and verification platform according to claim 4, characterized in that, The comprehensive guarantee subsystem comprises a superconducting zero-stage booster body guarantee system, a superconducting magnet guarantee system and an auxiliary safe braking and protection system.

9. The commercial space electromagnetic launch joint test and verification platform according to claim 5, characterized in that, The control center comprises a control system for conducting physical test process control, a data analysis module for conducting test data processing and analysis, and an ultrasonic semi-physical simulation system based on a semi-physical simulation platform.

10. The commercial space electromagnetic launch joint test verification platform according to claim 9, wherein, The control system, the data analysis module and the ultrasonic semi-physical simulation system share a set of hardware devices.

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