Integrated ultra-low earth orbit constellation launch platform

Abstract

The integrated ultra-low orbit constellation carrier platform comprises an air inlet cabin section, a middle cabin section and a tail cabin section, the air inlet cabin section comprises an air inlet, the middle cabin section comprises a radio frequency ionization chamber, an electric control solid propeller storage cabin and a satellite storage cabin, the tail cabin section comprises a magnetic jet acceleration pipe, a propellant supplement mechanism and an electric control solid rocket upper stage, the air inlet, the radio frequency ionization chamber and the magnetic jet acceleration pipe are connected to form an air-breathing electric propulsion system of the carrier platform. The satellite is connected with the corresponding electric control solid rocket upper stage in a launch channel. In the satellite transportation into orbit networking stage, the electric control solid rocket upper stage carrying the satellite is ejected from the cabin, the electric control solid rocket upper stage uses electric control solid propellant as a propellant working medium and can be repeatedly ignited and started, after reaching a target orbit, the satellite is separated from the electric control solid rocket upper stage and is unfolded and networked by itself, and the electric control solid rocket upper stage returns to the carrier platform for fuel supplement by relying on the remaining fuel, and is ready to start the next satellite transportation task.

Description

Technical Field

[0001] This invention mainly relates to the field of constellation launch platform design technology, and in particular to an integrated ultra-low orbit constellation launch platform. Background Technology

[0002] With the continuous development of aerospace technology and the increasing scale of the aerospace industry, satellite internet construction has been included in the scope of new infrastructure, and the construction of low-Earth orbit (LEO) satellite constellations has entered a stage of rapid development. LEO satellite constellations require tens of thousands of satellites to provide stable and high-speed space-based communication services. Satellite launch costs typically account for more than half of the total cost. Traditional satellite launch methods are insufficient to meet the low-cost operational requirements of commercial spaceflight. Therefore, the construction of constellations urgently requires the development of new low-cost space launch technologies, with key technological routes including rocket recovery and reuse technology and multi-satellite launch technology.

[0003] Current methods for launching satellites into orbit rely on launch vehicles to lift them off the ground and send them directly into their designated orbits. However, due to the limited carrying capacity of rockets, it is difficult to achieve significant breakthroughs in multi-satellite launch technology. Furthermore, the preparation cycle for rocket launch missions is too long, making it difficult to meet the goal of rapidly launching tens of thousands of satellites into orbit. Summary of the Invention

[0004] Current satellite launch technology still falls far short of the goals of low cost, high density, and short cycle. In response to this situation, this invention proposes an integrated ultra-low orbit constellation launch platform.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0006] An integrated ultra-low orbit constellation launch platform, comprising an air intake section, an intermediate section, and a tail section;

[0007] The air intake section includes an air intake duct, which is used to draw in the thin atmosphere of the ultra-low orbit outside.

[0008] The intermediate section includes a radio frequency ionization chamber, an electrically controlled solid propellant tank, and a satellite tank. The radio frequency ionization chamber is located on the central axis of the intermediate section, and the air inlet provides gas to the radio frequency ionization chamber. Multiple electrically controlled solid propellant tanks are distributed around the radio frequency ionization chamber, and each electrically controlled solid propellant tank is equipped with a supply mechanism for pushing the electrically controlled solid propellant thrusters within the tank to the outlet end of the tank. Multiple satellite tanks are located on the outermost perimeter of the intermediate section, and multiple satellites are loaded into these satellite tanks.

[0009] The tail section includes a magnetic jet accelerator tube, a propellant replenishment mechanism, and an electronically controlled solid rocket upper stage. The outlet of the radio frequency ionization chamber is connected to the inlet of the magnetic jet accelerator tube. Multiple electronically controlled solid rocket upper stages are arranged around the magnetic jet accelerator tube, and each satellite storage tank corresponds to one of the electronically controlled solid rocket upper stages. The electronically controlled solid rocket upper stage is provided with an electronically controlled solid propellant replenishment window. The outlet end of the electronically controlled solid propellant storage tank is located in the tail section, and the outlet end of the electronically controlled solid propellant storage tank corresponds to the propellant replenishment mechanism.

[0010] Furthermore, the air intake section, intermediate section, and tail section of the present invention are sequentially connected to form a polygonal columnar structure of the transport platform.

[0011] Furthermore, the outer shell surface of the transport platform described in this invention is provided with solar panels, and the sides of the transport platform are provided with streamlined spoilers.

[0012] Furthermore, the outlet end of the air intake duct of the present invention is connected to a gas storage and flow distribution device. The gas from the air intake duct is supplied to the radio frequency ionization chamber through the gas storage and flow distribution device for the maintenance of the platform's track. If there is any gas remaining from the air intake duct after ensuring that the platform track is maintained normally, the remaining gas is stored in the gas chamber of the gas storage and flow distribution device to provide the additional impulse required for track lifting.

[0013] Furthermore, the air inlet of the air intake duct described in this invention is located at the front end of the air intake compartment section, and external gas enters the air intake duct through the air inlet.

[0014] Furthermore, the series of air intake holes in the air intake of the present invention are arranged in a honeycomb pattern; the air intake channel has a parabolic cross-section tapering structure, and the inner wall of the air intake channel is coated with an aluminum-plated reflective material.

[0015] Furthermore, the space between the outer side of the air intake duct and the outer shell of the air intake section is used as the installation space for the power system, control system and / or various spaceborne sensors of the launch platform.

[0016] Furthermore, each satellite storage compartment in this invention is a deployable structure. When a satellite is loaded into the storage compartment, the storage compartment will deploy outward, and multiple satellites are loaded into the satellite storage compartment in a stacked manner.

[0017] Furthermore, each satellite of the present invention is equipped with a deployable solar panel. After the satellite is launched into orbit, the solar panels folded on the outer side of the satellite body will rotate and unfold to provide power to the satellite body.

[0018] Furthermore, the upper stage of the electrically controlled solid rocket of the present invention includes a fuel tank, an electrode, a combustion chamber, and a tail nozzle. The electrically controlled solid propellant is placed in the fuel tank, and a propellant pushing mechanism is provided at the bottom of the fuel tank. The propellant pushing mechanism delivers the front end of the electrically controlled solid propellant to the position of the electrode for combustion. The other side of the electrode structure is the combustion chamber, and the outlet of the combustion chamber is connected to the converging nozzle.

[0019] The electrodes in the upper stage of the electronically controlled solid rocket adopt a fixed electrode staggered electrode structure. The electrodes include a first electrode and a second electrode. The first electrode has a series of parallel and equidistant positive electrodes, and the second electrode has the same number of negative electrodes as the positive electrodes, which are also parallel and equidistant from each other. The first electrode and the second electrode are arranged opposite each other on the same plane, and the positive electrodes of the first electrode and the negative electrodes of the second electrode are staggered and distributed alternately, and the spacing between adjacent electrodes remains fixed.

[0020] The fuel tank is provided with an openable electronically controlled solid propellant replenishment window on one side. When the electronically controlled solid propellant in the upper stage of the electronically controlled solid rocket is depleted, the electronically controlled solid propellant replenishment window is opened, and the propellant replenishment mechanism can push the electronically controlled solid propellant at the outlet end of the electronically controlled solid propellant storage tank into the fuel tank of the upper stage of the electronically controlled solid rocket through the electronically controlled solid propellant replenishment window, thereby replenishing the electronically controlled solid propellant in the upper stage of the electronically controlled solid rocket.

[0021] The beneficial technical effects of this invention are:

[0022] (1) Low satellite launch cost. The ultra-low working orbit of the launch platform can significantly reduce the load pressure and technical difficulty of satellite transportation, thereby reducing the overall launch cost; the air-breathing propulsion system can obtain the thin atmosphere of the ultra-low orbit as the working fluid for thrust compensation and orbit lifting, and the upper stage launch vehicle adopts a solid propulsion system with simple structure and low cost.

[0023] (2) High satellite launch density. The launch platform can carry a large number of satellites at once, and the upper-stage launch vehicle can send multiple satellites into the predetermined orbit at once.

[0024] (3) Short satellite launch cycle. After the satellite is launched from the launch platform, it can quickly return to the ultra-low orbit loading orbit for satellite loading. After the upper stage launch vehicle completes its mission, it can also quickly return to the platform to replenish propellant.

[0025] This invention designs a constellation launch platform operating in a very low Earth orbit. The space launch vehicle only needs to transport the satellites to this platform. Due to the extremely low orbital altitude, more satellites can be transported at once, facilitating the rapid commencement of the next launch mission. The launch platform in this invention can achieve on-orbit thrust compensation and a certain degree of orbital elevation through its own air-breathing electric propulsion system. Finally, the carried electronically controlled solid rocket upper stage transports the satellites in batches to the constellation's working orbit, achieving the goals of low-cost, high-density, and short-cycle constellation deployment. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0027] Figure 1 This is a schematic diagram of the overall appearance structure from one perspective of one embodiment;

[0028] Figure 2 yes Figure 1 The schematic diagram of the overall appearance structure of the embodiment shown is from another perspective;

[0029] Figure 3 yes Figure 1 A side view of the embodiment shown;

[0030] Figure 4 yes Figure 3 A sectional view;

[0031] Figure 5 This is a schematic diagram of the satellite storage compartment after deployment in one embodiment;

[0032] Figure 6 yes Figure 5 Side view;

[0033] Figure 7 This is a schematic diagram of the structure of the upper stage of an electronically controlled solid rocket in one embodiment;

[0034] Figure 8 yes Figure 7 The diagram shows the structure of the upper stage of an electronically controlled solid rocket (with the electronically controlled solid propellant replenishment window open).

[0035] Figure 9 This is a schematic diagram of a satellite structure according to one embodiment;

[0036] Figure 10 yes Figure 9The diagram shows the satellite deployment process, where (a) is the original satellite state; (b) is the initial deployment state; (c) is the re-deployment state; and (d) is the fully deployed state.

[0037] Figure 11 This is a schematic diagram of the working process of one embodiment;

[0038] Numbering on the map:

[0039] 1. Air intake section; 1-1. Air intake duct; 1-2. Air inlet; 1-3. Air intake port;

[0040] 2. Intermediate section; 2-1. Electrically controlled solid propulsion tank; 2-2. Satellite tank;

[0041] 3. Tail section; 4. Solar panels; 5. Spoilers; 6. Gas storage and flow distribution device; 7. Radio frequency ionization chamber; 8. Supply mechanism; 9. Electronically controlled solid propellant; 10. Satellite; 11. Magnetic jet accelerator tube; 12. Propellant replenishment mechanism;

[0042] 13. Upper stage of electronically controlled solid rocket; 13-1. Electronically controlled solid propellant replenishment window; 13-2. Fuel tank; 13-3. Electrode; 13-4. Combustion chamber; 13-5. Tail nozzle; 13-6. Propellant delivery mechanism; 13-7. First electrode; 13-8. Second electrode. Detailed Implementation

[0043] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the spirit of the disclosed content will be clearly explained below with reference to the accompanying drawings and detailed description. Any person skilled in the art, after understanding the embodiments of the present invention, can make changes and modifications based on the techniques taught in the present invention without departing from the spirit and scope of the present invention. The illustrative embodiments and descriptions of the present invention are used to explain the present invention, but are not intended to limit the present invention.

[0044] Reference Figure 1 , Figure 2 , Figure 3 and Figure 4 In one embodiment, a reusable integrated ultra-low orbit constellation launch platform is provided, which can effectively increase the number of satellites transported at one time and shorten the launch cycle.

[0045] The integrated ultra-low orbit constellation launch platform includes an air intake section 1, an intermediate section 2, and a tail section 3; these sections are sequentially connected to form a polygonal columnar launch platform. Solar panels 4 are distributed on the outer surface of the launch platform, and streamlined spoilers 5 are located on its sides. The spoilers 4 reduce aerodynamic drag and can also achieve attitude control by changing their tilt angle.

[0046] The air intake section 1 includes an air intake duct 1-1, which is used to draw in the thin atmosphere of ultra-low Earth orbit. The air inlet 1-2 of the air intake duct 1-1 is located at the front end of the air intake section 1, through which outside air enters the air intake duct 1-1. A series of air inlets 1-3 in the air inlet 1-2 are arranged in a honeycomb pattern. The air intake duct 1-1 has a parabolic cross-section with a tapering design, and its inner wall is coated with an aluminum-plated reflective material.

[0047] Because the air intake 1-1 has a parabolic cross-section with a tapering shape, there is an annular space between the outer wall of the air intake and the outer shell of the air intake section. This annular space can be used as the installation space for the power system, control system, and various spaceborne sensors of the launch platform. That is, the power system, control system, and various spaceborne sensors of the launch platform are distributed around the outer side of the air intake, and the air intake section 1 is the breathing system and control center of the launch platform.

[0048] The outlet end of the air intake 1-1 is connected to a gas storage and flow distribution device 6. The gas storage and flow distribution device 6 supplies part of the external gas captured by the air intake to the radio frequency ionization chamber 7 at the rear end for acceleration, which is used for track maintenance of the carrier platform. If there is still gas remaining after the external gas captured by the air intake is supplied to the radio frequency ionization chamber, the remaining gas is stored in the gas chamber of the gas storage and flow distribution device. The gas in the gas chamber can be used as a supplementary gas source for the radio frequency ionization chamber under special circumstances, such as to provide the additional impulse required for track lifting.

[0049] The entire transport platform has an axisymmetric structure. The gas storage and flow distribution device 6 includes a series of pipes, valves, and gas chambers. Gas from the air inlet 1-1 is supplied to the radio frequency ionization chamber 7 via the gas storage and flow distribution device 6 for track maintenance of the transport platform. A flow valve is installed on the gas supply pipe between the gas storage and flow distribution device 6 and the radio frequency ionization chamber 7 to control the gas flow rate supplied to the radio frequency ionization chamber 7. The gas storage and flow distribution device 6 includes multiple gas chambers arranged around the central axis of the transport platform. A flow valve is installed on the gas pipe between each gas chamber and the air inlet 1-1 to control the gas flow rate entering the gas chamber. A flow valve is installed on the gas supply pipe between the radio frequency ionization chambers 7 to control the gas flow rate exiting the gas chamber.

[0050] The intermediate section 2 includes a radio frequency ionization chamber 7, an electrically controlled solid propellant tank 2-1, and a satellite tank 2-2. The radio frequency ionization chamber 7 is located on the central axis of the intermediate section 2, and the air inlet 1-1 provides the gas source for the radio frequency ionization chamber 7. Multiple electrically controlled solid propellant tanks 2-1 are distributed around the radio frequency ionization chamber 7. Each electrically controlled solid propellant tank 2-1 is equipped with a supply mechanism 8, which pushes the electrically controlled solid propellant 9 from the electrically controlled solid propellant tank 2-1 to its outlet end. Multiple satellite tanks 2-2 are located on the outermost periphery of the intermediate section 2, and multiple satellites 10 are stacked and filled in the satellite tanks 2-2 to maximize the use of the cabin space. The structure of the supply mechanism 8 is not limited; for example, a spring structure can be used. Figure 4 The supply mechanism 8 shown is a spring, which uses the deformation of the spring to push the electrically controlled solid propellant 9 in the electrically controlled solid propellant tank 2-1.

[0051] The tail section 3 includes a magnetic jet accelerator tube 11, a propellant replenishment mechanism 12, and an electronically controlled solid rocket upper stage 13. The outlet of the radio frequency ionization chamber 7 is connected to the inlet of the magnetic jet accelerator tube 11. Multiple electronically controlled solid rocket upper stages 13 are arranged around the magnetic jet accelerator tube 11, and each satellite storage tank 2-2 corresponds to one of the electronically controlled solid rocket upper stages 13. The electronically controlled solid rocket upper stages 13 are used to transport the satellite 10 to its designated working orbit. The electronically controlled solid rocket upper stage 13 is provided with an electronically controlled solid propellant replenishment window 13-1; the outlet end of the electronically controlled solid propellant storage tank 2-1 is located within the tail section 3, and the outlet end of the electronically controlled solid propellant storage tank 2-1 corresponds to the propellant replenishment mechanism 12. After the upper stage 13 of the electrically controlled solid rocket completes a satellite delivery mission and returns to the tail section 3, once the electrically controlled solid propellant 9 in the upper stage 13 is depleted, the supply mechanism pushes the electrically controlled solid thrusters 9 in the electrically controlled solid propellant tank 2-1 to the outlet end of the electrically controlled solid propellant tank 2-1 by opening the electrically controlled solid propellant replenishment window 13-1. The propellant replenishment mechanism 12 then pushes the electrically controlled solid propellant 9 from the outlet end of the electrically controlled solid propellant tank 2-1 into the upper stage 13 of the electrically controlled solid rocket through the electrically controlled solid propellant replenishment window 13-1, thereby replenishing the electrically controlled solid propellant in the upper stage 13 of the electrically controlled solid rocket. This enables the launch platform to operate in orbit for extended periods, fully embodying the launch platform's design philosophy of low cost, high density, and short cycle in satellite launch.

[0052] The air intake 1-1, gas storage and flow distribution device 6, radio frequency ionization chamber 7, and magnetic jet accelerator tube 11 constitute the air-breathing electric propulsion system of the constellation launch platform. The radio frequency ionization chamber 7 uses electrodeless inductive discharge technology to achieve high-efficiency ionization of gas molecules, and the magnetic jet accelerator tube 11 uses the induced magnetic field of the energized coil to converge and accelerate the plasma plume.

[0053] Reference Figure 5 and Figure 6 In one embodiment, the satellite storage compartment is designed as a deployable structure. The intermediate compartment 2 has a total of 6 satellite storage compartments 2-2. When satellites are loaded, the satellite storage compartments 2-2 will unfold outward. The satellites in the satellite storage compartments 2-2 are stored in a stacked manner to maximize the use of the compartment space.

[0054] Reference Figure 9 and Figure 10 In one embodiment, the satellite is designed as a deployable structure, meaning that the satellite 10 itself can also be deployed. After the satellite is launched into orbit, the solar panels folded on the side of the satellite will rotate and unfold to provide it with power.

[0055] In a preferred embodiment, the upper stage 13 of the electrically controlled solid rocket uses HAN-based electrically controlled solid propellant. The electrodes adopt a fixed electrode staggered electrode structure, with two electrodes staggered on the propellant end face and the electrode spacing remaining constant. An openable window is provided on the side of the upper stage. When the propellant is exhausted, the propellant in the launch platform will be forced into its fuel tank through the window by the motor.

[0056] Reference Figure 7 and Figure 8 One embodiment provides an electronically controlled solid rocket upper stage 13, which includes a fuel tank 13-2, an electrode 13-3, a combustion chamber 13-4, and a tail nozzle 13-5. An electronically controlled solid propellant 9 is placed in the fuel tank 13-2. A propellant pushing mechanism 13-6 is provided at the bottom of the fuel tank 13-2, which delivers the front end of the electronically controlled solid propellant to the position of the electrode 13-3 for combustion. The other side of the electrode 13-3 is the combustion chamber 13-4, and the outlet of the combustion chamber 13-4 is connected to the tail nozzle 13-5, which is a converging nozzle.

[0057] The electrodes 13-3 in the upper stage 13 of the electrically controlled solid rocket adopt a fixed-electrode staggered electrode structure. Electrode 13-3 includes a first electrode 13-7 and a second electrode 13-8. The first electrode 13-7 has a series of parallel, equidistantly arranged positive electrodes, and the second electrode 13-8 has the same number of negative electrodes arranged parallel and equidistantly. The first electrode 13-7 and the second electrode 13-8 are positioned opposite each other on the same plane, with the positive electrodes of the first electrode 13-7 and the negative electrodes of the second electrode 13-8 staggered and alternating, and the spacing between adjacent electrodes remains constant. Using a fixed electrode structure, the two electrodes are staggered on the propellant end face, and the supply of electrically controlled solid propellant can be achieved using a propellant pushing mechanism 13-6, such as a motor. Because the electrode spacing is constant, the device has the advantage of stable and reliable operation.

[0058] A refillable electronically controlled solid propellant window 13-1 is provided on one side of the fuel tank 13-2. When the electronically controlled solid propellant in the upper stage 13 of the electronically controlled solid rocket is depleted, the refill window 13-1 is opened, and the propellant replenishment mechanism 12 can push the electronically controlled solid propellant at the outlet end of the electronically controlled solid propellant storage tank 2-1 through the refill window 13-1 to the fuel tank 13-2 of the upper stage 13 of the electronically controlled solid rocket, thereby replenishing the electronically controlled solid propellant in the upper stage 13 of the electronically controlled solid rocket.

[0059] Reference Figure 11 The working process of this invention can be divided into the following three stages:

[0060] (1) Satellite loading phase for network deployment:

[0061] During this phase, the integrated ultra-low orbit constellation launch platform is parked at an altitude of about 200km in ultra-low orbit. It relies on an air-breathing electric propulsion system to complete its on-orbit thrust compensation. After the space transport vehicle loaded with satellites enters orbit, the satellite storage compartments in the middle section of the launch platform are deployed. After each satellite storage compartment is filled, the satellite storage compartments are closed.

[0062] (2) Track lifting stage of the transport platform:

[0063] During this phase, the control system of the integrated ultra-low Earth orbit constellation launch platform allocates satellite launch channels based on the target orbit parameters of the networked satellites and the number of satellites in the same orbit. The channel between the satellite storage compartment 2-2 and the electronically controlled solid rocket upper stage 13 serves as the satellite launch channel. The satellite storage compartment 2-2 is equipped with a docking drive mechanism that propels the satellite to dock with the electronically controlled solid rocket upper stage 13. The docking drive mechanism (usually powered by an electric motor) pushes the satellite from the satellite storage compartment to the satellite launch channel, enabling the satellite to connect with the corresponding electronically controlled solid rocket upper stage within the launch channel.

[0064] During this phase, the launch platform's air-breathing electric propulsion system supplies gas stored in the gas chamber to the radio frequency ionization chamber, providing the additional impulse required for orbital lifting, raising the platform's orbit to an altitude of approximately 250 km, and simultaneously selecting an appropriate transfer orbit phase angle for satellite orbital transfer.

[0065] (3) Satellite delivery and orbit deployment phase:

[0066] The upper stage of the electrically controlled solid rocket carrying the satellite exits from the tail section 3. After exiting the capsule, the upper stage uses electrically controlled solid propellant as its propellant and can be repeatedly ignited. Once it reaches the target orbit, the satellite detaches from the upper stage and deploys itself to form a satellite constellation. The upper stage then returns to the launch platform with its remaining fuel for refueling, preparing for the next satellite delivery mission.

[0067] Each satellite storage compartment is a deployable structure. When a satellite is loaded into the compartment, the compartment will unfold outwards. Multiple satellites are stacked and stored in the compartment to maximize space utilization.

[0068] Each satellite employs a deployable structure, and each satellite is equipped with deployable solar panels that fold into a cylinder within the storage compartment. After the satellite is launched into orbit, the solar panels folded onto the outer surface of the satellite will rotate and unfold to provide power to the satellite.

[0069] Using an electronically controlled solid rocket upper stage, multiple satellites can be transported to their working orbits at once. The electronically controlled solid rocket upper stage has the advantages of being re-startable, having a simple structure, and being low in cost.

[0070] After the satellite delivery mission is completed, the rocket can return to the launch platform for propellant replenishment. An openable electronic solid propellant replenishment window is provided on the side of the fuel tank of the upper stage of the electronically controlled solid rocket. The electronic solid propellant in the launch platform will be pushed into its fuel tank through the electronic solid propellant replenishment window by the propellant replenishment mechanism (which is generally powered by an electric motor).

[0071] Matters not covered in this invention are common knowledge.

[0072] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0073] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. An integrated ultra-low orbit constellation launch platform, characterized in that: Including the air intake section, the middle section, and the stern section; The air intake section includes an air intake duct, which is used to draw in the thin atmosphere of the ultra-low orbit outside. The intermediate section includes a radio frequency ionization chamber, an electronically controlled solid propellant tank, and satellite tanks. The radio frequency ionization chamber is located on the central axis of the intermediate section, and the air inlet provides the gas source for the radio frequency ionization chamber. Multiple electronically controlled solid propellant tanks are distributed around the radio frequency ionization chamber, and each electronically controlled solid propellant tank is equipped with a supply mechanism for pushing the electronically controlled solid propellant from the tank to its outlet. Multiple satellite tanks are located on the outermost perimeter of the intermediate section, and multiple satellites are loaded into these satellite tanks. The tail section includes a magnetic jet accelerator tube, a propellant replenishment mechanism, and an electronically controlled solid rocket upper stage. The outlet of the radio frequency ionization chamber is connected to the inlet of the magnetic jet accelerator tube. Multiple electronically controlled solid rocket upper stages are arranged around the magnetic jet accelerator tube, and each satellite storage tank corresponds to one of the electronically controlled solid rocket upper stages. The electronically controlled solid rocket upper stage is provided with an electronically controlled solid propellant replenishment window. The outlet end of the electronically controlled solid propellant storage tank is located in the tail section, and the outlet end of the electronically controlled solid propellant storage tank corresponds to the propellant replenishment mechanism.

2. The integrated ultra-low orbit constellation launch platform according to claim 1, characterized in that, The air intake section, intermediate section, and tail section are sequentially connected to form a polygonal columnar transport platform.

3. The integrated ultra-low orbit constellation launch platform according to claim 2, characterized in that, The outer shell of the transport platform is covered with solar panels, and the sides of the transport platform are equipped with streamlined spoilers.

4. The integrated ultra-low orbit constellation launch platform according to claim 1, 2, or 3, characterized in that, The outlet end of the air intake is connected to a gas storage and flow distribution device. The gas from the air intake is supplied to the radio frequency ionization chamber through the gas storage and flow distribution device for the maintenance of the platform's track. If there is any gas remaining from the air intake after ensuring that the platform's track is maintained normally, the remaining gas is stored in the gas chamber of the gas storage and flow distribution device to provide the additional impulse required for track lifting.

5. The integrated ultra-low orbit constellation launch platform according to claim 4, characterized in that, The air inlet of the air intake duct is located at the front end of the air intake compartment section, and outside air enters the air intake duct through the air inlet.

6. The integrated ultra-low orbit constellation launch platform according to claim 5, characterized in that, The air inlet has a series of air holes arranged in a honeycomb pattern; the air intake channel has a parabolic cross-section with a tapering structure, and the inner wall of the air intake channel is coated with aluminum-plated reflective material.

7. The integrated ultra-low orbit constellation launch platform according to claim 1, 2, 4, 5, or 6, characterized in that, The space between the outer side of the air intake and the outer shell of the air intake section is used as the installation space for the power system, control system and / or various spaceborne sensors of the launch platform.

8. The integrated ultra-low orbit constellation launch platform according to claim 7, characterized in that, Each satellite storage compartment is a deployable structure. When a satellite is loaded into the compartment, the compartment will unfold outwards, and multiple satellites are stacked and stored in the compartment.

9. The integrated ultra-low orbit constellation launch platform according to claim 8, characterized in that, Each satellite is equipped with deployable solar panels. After the satellite is launched into orbit, the solar panels, which are folded on the outside of the satellite body, will rotate and unfold to provide power to the satellite body.

10. The integrated ultra-low orbit constellation launch platform according to claim 8, characterized in that, The upper stage of the electronically controlled solid rocket includes a fuel tank, electrodes, a combustion chamber, and a tail nozzle. The electronically controlled solid propellant is placed in the fuel tank, and a propellant pushing mechanism is provided at the bottom of the fuel tank. The propellant pushing mechanism delivers the front end of the electronically controlled solid propellant to the position of the electrodes for combustion. The other side of the electrode structure is the combustion chamber, and the outlet of the combustion chamber is connected to the converging nozzle. The electrodes in the upper stage of the electronically controlled solid rocket adopt a fixed electrode staggered electrode structure. The electrodes include a first electrode and a second electrode. The first electrode has a series of parallel and equidistant positive electrodes, and the second electrode has the same number of negative electrodes as the positive electrodes, which are also parallel and equidistant from each other. The first electrode and the second electrode are arranged opposite each other on the same plane, and the positive electrodes of the first electrode and the negative electrodes of the second electrode are staggered and distributed alternately, and the spacing between adjacent electrodes remains fixed. The fuel tank is provided with an openable electronically controlled solid propellant replenishment window on one side. When the electronically controlled solid propellant in the upper stage of the electronically controlled solid rocket is depleted, the electronically controlled solid propellant replenishment window is opened, and the propellant replenishment mechanism can push the electronically controlled solid propellant at the outlet end of the electronically controlled solid propellant storage tank into the fuel tank of the upper stage of the electronically controlled solid rocket through the electronically controlled solid propellant replenishment window, thereby replenishing the electronically controlled solid propellant in the upper stage of the electronically controlled solid rocket.

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