CN117048850A - Integrated ultra-low orbit constellation carrying platform - Google Patents

Abstract

The integrated ultra-low orbit constellation carrying platform comprises an air inlet cabin section, a middle cabin section and a tail cabin section, wherein the air inlet cabin section comprises an air inlet channel, the middle cabin section comprises a radio frequency ionization chamber, an electric control solid thruster storage cabin and a satellite storage cabin, the tail cabin section comprises a magnetic spraying accelerating tube, a propellant supplementing mechanism and an electric control solid rocket upper stage, and the air inlet channel, the radio frequency ionization chamber and the magnetic spraying accelerating tube are communicated to form an air suction type electric propulsion system of the carrying platform. The satellites are connected with the upper stage of the corresponding electric control solid rocket in the launching channel. In the satellite conveying and orbit networking stage, the upper stage of the electric control solid rocket carrying the satellite is taken out of the cabin, the upper stage of the electric control solid rocket adopts electric control solid propellant as a propelling working medium, the electric control solid rocket can be repeatedly ignited and started, after reaching a target orbit, the satellite is separated from the upper stage of the electric control solid rocket and automatically expands and networking, and the upper stage of the electric control solid rocket returns to a carrying platform for fuel replenishment by means of residual fuel to prepare for starting the next satellite conveying task.

Description

Integrated ultra-low orbit constellation carrying platform

Technical Field

The application mainly relates to the technical field of constellation carrying platform design, in particular to an integrated ultra-low orbit constellation carrying platform.

Background

With the continuous development of the aerospace technology and the increasing expansion of the aerospace industry scale, satellite internet construction is brought into a new infrastructure range, and low orbit satellite constellation construction enters a rapid development stage. The low orbit satellite constellation needs thousands of satellite networking to provide stable high-speed space-based communication service, the launching cost of satellites usually occupies more than half of the cost, and the traditional satellite launching mode is difficult to meet the low-cost operation requirement of commercial aerospace, so the constellation construction is urgent to develop novel low-cost aerospace launching technology, and the main technical routes comprise rocket recycling multiplexing technology and one-rocket multi-satellite technology.

The existing satellite launching and orbit entering modes depend on a carrier rocket to lift off from the ground to directly send the satellite into a preset working orbit, and the one-rocket multi-satellite technology is difficult to realize larger breakthrough due to limited carrying capacity of the rocket, and the preparation period of a rocket launching task is too long, so that the goal of quickly launching and orbit entering thousands of satellites is difficult to be met.

Disclosure of Invention

The present satellite transmitting technology has a large gap from the targets with low cost, high density and short period, and the application provides an integrated ultra-low orbit constellation carrying platform aiming at the current situation.

In order to achieve the above purpose, the technical scheme adopted by the application is as follows:

the integrated ultra-low orbit constellation carrying 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 channel, and the air inlet channel is used for taking in external ultra-low orbit lean atmosphere;

the middle cabin section comprises a radio frequency ionization chamber, an electric control solid propeller storage cabin and a satellite storage cabin, wherein the radio frequency ionization chamber is positioned on the central axis of the middle cabin section, and the air inlet channel provides a gas source for the radio frequency ionization chamber; the periphery of the radio frequency ionization chamber is provided with a plurality of electric control solid propellant storage tanks, each electric control solid propellant storage tank is internally provided with a supply mechanism, and the supply mechanism is used for pushing electric control solid propellants in the electric control solid propellant storage tank to the outlet end of the electric control solid propellant storage tank; the plurality of satellite storage cabins are arranged at the outermost periphery in the middle cabin section, and the plurality of satellites are filled in the satellite storage cabins;

the tail cabin section comprises a magnetic spraying accelerating tube, a propellant supplementing mechanism and an electric control solid rocket upper stage, wherein an outlet of the radio frequency ionization chamber is communicated with an inlet of the magnetic spraying accelerating tube, a plurality of electric control solid rocket upper stages are annularly distributed on the periphery of the magnetic spraying accelerating tube, and the satellite storage cabins are in one-to-one correspondence with the electric control solid rocket upper stages; an electric control solid propellant supplementing window is arranged at the upper stage of the electric control solid rocket; the outlet end of the electric control solid propellant storage cabin is arranged in the tail cabin section, and corresponds to the propellant supplementing mechanism.

Further, the air inlet cabin section, the middle cabin section and the tail cabin section are sequentially butted to form a carrying platform with a polygonal column-shaped structure.

Furthermore, solar panels are distributed on the surface of the shell of the carrying platform, and streamline spoilers are arranged on the side edges of the carrying platform.

Further, the outlet end of the air inlet channel is connected with a gas storage and flow distribution device, and the gas from the air inlet channel is supplied to the radio frequency ionization chamber through the gas storage and flow distribution device for maintaining the track of the platform; if gas from the inlet channel remains on the premise of ensuring that the platform track is kept normal, the remaining gas is stored in a gas chamber in the gas storage and flow distribution device for providing additional impulse required during track lifting.

Further, the air inlet of the air inlet channel is positioned at the front end of the air inlet cabin section, and external air enters the air inlet channel through the air inlet.

Further, a series of air inlets in the air inlet are arranged in a honeycomb shape; the air inlet is of a parabolic cross-section tapered structure, and the inner wall of the air inlet is coated with aluminized reflecting materials.

Further, the space between the outer side of the air inlet channel and the outer shell of the air inlet cabin section is used as the installation space of a power supply system, a control system or/and various satellite-borne sensors of the carrying platform.

Furthermore, each satellite storage cabin is of an expandable structure, and under the condition of filling satellites, the satellite storage cabin can be expanded outwards, and a plurality of satellites are filled in the satellite storage section in a stacked storage mode.

Furthermore, each satellite is provided with the solar cell panel with the expandable structure, and after the satellite is launched into orbit, the solar cell panel folded on the outer side surface of the satellite body can be rotated and expanded to provide electric energy for the satellite body.

Further, the upper stage of the electric control solid rocket comprises a fuel cabin, an electrode, a combustion chamber and a tail nozzle, wherein electric control solid propellant is arranged in the fuel cabin, a propellant pushing mechanism is arranged at the bottom of the fuel cabin, the front end face of the electric control solid propellant is sent to the position where the electrode is positioned for combustion through the propellant pushing mechanism, the combustion chamber is arranged at the other side of the electrode structure, and an outlet of the combustion chamber is communicated with the shrinkage nozzle;

the electrodes in the upper stage of the electric control solid rocket adopt a fixed electrode type staggered electrode structure, the electrodes comprise a first electrode and a second electrode, the first electrode is provided with a series of positive electrodes which are arranged in parallel and equidistantly, the second electrode is provided with negative electrodes which are the same as the positive electrodes in number and are arranged in parallel and equidistantly, the first electrode and the second electrode are oppositely arranged on the same plane, the positive electrodes of the first electrode and the negative electrodes of the second electrode are staggered and alternately distributed, and the interval between the adjacent electrodes is fixed;

an openable electric control solid propellant supplementing window is arranged on one side of the fuel cabin, after the electric control solid propellant in the upper stage of the electric control solid rocket is consumed, the electric control solid propellant supplementing window is opened, and the propellant supplementing mechanism can push the electric control solid propellant at the outlet end of the electric control solid propellant storage cabin into the fuel cabin of the upper stage of the electric control solid rocket through the electric control solid propellant supplementing window, so that the electric control solid propellant in the upper stage of the electric control solid rocket is supplemented.

The application has the beneficial technical effects that:

(1) The satellite transmitting cost is low. The ultra-low working orbit of the carrying platform can greatly reduce the load pressure and technical difficulty of satellite transportation, thereby reducing the overall emission cost; the suction type propulsion system can obtain ultra-low orbit rarefied atmosphere as working medium for thrust compensation and orbit lifting, and the carrier rocket of the upper stage adopts a solid propulsion system with simple structure and low cost.

(2) The satellite emission density is high. The carrier platform can be used for loading a large number of satellites at a time, and the carrier rocket of the upper stage can be used for conveying a plurality of satellites into a preset orbit at a time.

(3) The satellite transmission period is short. After the satellite in the carrying platform is launched, the satellite can quickly return to the ultra-low orbit loading orbit for satellite loading, and after the upper-level carrier rocket finishes the task, the satellite can also quickly return to the platform for supplementing the propellant.

The application designs a constellation carrying platform working on the ultra-low orbit of the earth, and the space carrier only needs to carry the satellites to the carrying platform, so that more satellites can be carried at one time due to the extremely low orbit height, and simultaneously, the next carrying task can be conveniently and rapidly started. The carrying platform can realize on-orbit thrust compensation and certain orbit lifting by means of the self-inspiration type electric propulsion system, and finally the upper stage of the carried electric control solid rocket carries satellites to the working orbit of the constellation in batches, so that the goals of low cost, high density and short period of constellation networking can be realized.

Drawings

In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of the overall appearance structure of a view angle of an embodiment;

FIG. 2 is a schematic view of the overall appearance of the embodiment of FIG. 1 from another perspective;

FIG. 3 is a side view of the embodiment shown in FIG. 1;

FIG. 4 is a cross-sectional view of FIG. 3;

FIG. 5 is a schematic diagram of an exemplary satellite pod after deployment;

FIG. 6 is a side view of FIG. 5;

FIG. 7 is a schematic diagram of the structure of the upper stage of the electronically controlled solid rocket in one embodiment;

FIG. 8 is a schematic view of the upper stage structure of the electronically controlled solid rocket of FIG. 7 (with electronically controlled solid propellant replenishment windows open);

FIG. 9 is a schematic view of a satellite architecture according to an embodiment;

FIG. 10 is a schematic diagram of the satellite deployment process of FIG. 9, wherein (a) is a satellite original state diagram; (b) a satellite initial deployment state diagram; (c) a satellite redeployment state diagram; (d) is a satellite fully extended state diagram;

FIG. 11 is a schematic diagram of the operation of an embodiment;

reference numerals in the drawings:

1. an air intake compartment section; 1-1, an air inlet channel; 1-2, an air inlet; 1-3, an air inlet hole;

2. a middle cabin section; 2-1, an electric control solid propeller storage cabin; 2-2, satellite storage tanks;

3. a tail cabin section; 4. a solar cell panel; 5. a spoiler; 6. a gas storage and flow distribution device; 7. a radio frequency ionization chamber; 8. a supply mechanism; 9. electronically controlled solid propellant; 10. a satellite; 11. a magnetic spraying accelerating tube; 12. a propellant replenishing mechanism;

13. electrically controlling the upper stage of the solid rocket; 13-1, an electronically controlled solid propellant replenishment window; 13-2, a fuel tank; 13-3, electrodes; 13-4, a combustion chamber; 13-5, a tail nozzle; 13-6, a propellant pushing mechanism; 13-7, a first electrode; 13-8, a second electrode.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the spirit of the present disclosure will be clearly described in the following drawings and detailed description, and any person skilled in the art, after having appreciated the embodiments of the present disclosure, may make alterations and modifications by the techniques taught by the present disclosure without departing from the spirit and scope of the present disclosure. The exemplary embodiments of the present application and the descriptions thereof are intended to illustrate the present application, but not to limit the present application.

Referring to fig. 1, 2, 3 and 4, in one embodiment, a reusable integrated ultra-low orbit constellation carrying platform is provided, which can effectively increase the number of disposable transport satellites and shorten the transmission period.

The integrated ultra-low orbit constellation carrying platform comprises an air inlet cabin section 1, a middle cabin section 2 and a tail cabin section 3; the air inlet cabin section 1, the middle cabin section 2 and the tail cabin section 3 are sequentially butted to form a carrying platform with a polygonal column-shaped structure. Solar panels 4 are distributed on the surface of the outer shell of the carrying platform, and streamline spoilers 5 are arranged on the side edges of the carrying platform. The spoiler 4 can reduce pneumatic resistance, and can also control the attitude by changing the inclination angle of the plate body.

The air inlet cabin section 1 comprises an air inlet channel 1-1, and the air inlet channel 1-1 is used for taking in external ultra-low orbit lean atmosphere. The air inlet 1-2 of the air inlet channel 1-1 is positioned at the front end of the air inlet cabin section 1, and external air enters the air inlet channel 1-1 through the air inlet 1-2. A series of air inlets 1-3 in the air inlet 1-2 are arranged in a honeycomb shape. The air inlet channel 1-1 is of a parabolic cross-section tapered structure, and the inner wall of the air inlet channel 1-1 is coated with aluminized reflecting materials.

Because the air inlet channel 1-1 is of a parabolic cross-section tapered structure, the outer side wall of the air inlet channel is provided with an annular space between the shells of the air inlet cabin section, and the annular space can be used as a mounting space of a power supply system, a control system and various satellite-borne sensors of the carrying platform. Namely, a power supply system, a control system and various satellite-borne sensors of the carrying platform are distributed around the outer side of the air inlet channel, and the air inlet cabin section 1 is a respiratory system and a control center of the carrying platform.

The outlet end of the air inlet channel 1-1 is connected with a gas storage and flow distribution device 6, and the gas storage and flow distribution device 6 supplies part of external gas captured by the air inlet channel to the radio frequency ionization chamber 7 at the rear end to be accelerated for maintaining the track of the carrying platform, if the external gas captured by the air inlet channel remains after being supplied to the radio frequency ionization chamber, the remaining gas is stored in a gas chamber in the gas storage and flow distribution device, and the gas in the gas chamber can be used as a supplementary gas source of the radio frequency ionization chamber under special conditions, such as an extra impulse required for providing track lifting.

The whole carrying platform is of an axisymmetric structure. The gas storage and flow distribution device 6 comprises a series of pipes, valves and gas chambers, and the gas from the inlet channel 1-1 is supplied via the gas storage and flow distribution device 6 to the rf ionization chamber 7 for track maintenance of the carrier platform. A flow valve is arranged on the gas supply pipeline between the gas storage and flow distribution device 6 and the radio frequency ionization chamber 7, and is used for controlling the flow rate of the gas supplied to the radio frequency ionization chamber 7. The gas storage and flow distribution device 6 comprises a plurality of gas chambers, the gas chambers are arranged around the central axis of the carrying platform, flow valves for controlling the flow of gas entering the gas chambers are arranged on gas pipelines between the gas chambers and the air inlet channel 1-1, and flow valves for controlling the flow of gas flowing out of the gas chambers are arranged on gas supply pipelines between the radio frequency ionization chambers 7.

The middle cabin section 2 comprises a radio frequency ionization chamber 7, an electric control solid propeller storage cabin 2-1 and a satellite storage cabin 2-2, the radio frequency ionization chamber 7 is positioned on the central axis of the middle cabin section 2, and the air inlet channel 1-1 provides a gas source for the radio frequency ionization chamber 7. The periphery of the radio frequency ionization chamber 7 is distributed with a plurality of electric control solid propellant storage tanks 2-1, a supply mechanism 8 is arranged in each electric control solid propellant storage tank 2-1, and the supply mechanism is used for pushing electric control solid propellant 9 in the electric control solid propellant storage tank 2-1 to the outlet end of the electric control solid propellant storage tank 2-1; a plurality of satellite storage tanks 2-2 are arranged at the outermost periphery in the middle tank section 2, and a plurality of satellites 10 are stacked and packed in the satellite storage tanks 2-2, so that the tank space can be maximally utilized. The structure of the supply mechanism 8 is not limited, for example, a spring structure is adopted, the supply mechanism 8 shown in fig. 4 is a spring, and the deformation of the spring is utilized to push the electrically-controlled solid propellant 9 in the electrically-controlled solid propellant storage bin 2-1.

The tail cabin section 3 comprises a magnetic spraying accelerating tube 11, a propellant supplementing mechanism 12 and an electric control solid rocket upper stage 13, an outlet of the radio frequency ionization chamber 7 is communicated with an inlet of the magnetic spraying accelerating tube 11, a plurality of electric control solid rocket upper stages 13 are annularly distributed on the periphery of the magnetic spraying accelerating tube 11, the satellite storage cabins 2-2 are in one-to-one correspondence with the electric control solid rocket upper stages 13, and the electric control solid rocket upper stages 13 are used for conveying satellites 10 to a specified working orbit. The upper stage 13 of the electric control solid rocket is provided with an electric control solid propellant supplementing window 13-1; the outlet end of the electric control solid propellant storage cabin 2-1 is arranged in the tail cabin section 3, and the outlet end of the electric control solid propellant storage cabin 2-1 corresponds to the propellant supplementing mechanism 12. After the upper stage 13 of the electric control solid rocket finishes a satellite conveying task and returns to the tail cabin section 3, after the electric control solid propellant 9 in the upper stage 13 of the electric control solid rocket is exhausted, the electric control solid propellant supplementing window 13-1 is opened, the electric control solid propellant 9 in the electric control solid propellant storage cabin 2-1 is pushed to the outlet end of the electric control solid propellant storage cabin 2-1 by the supply mechanism, the electric control solid propellant 9 at the outlet end of the electric control solid propellant storage cabin 2-1 is pushed to the upper stage 13 of the electric control solid rocket by the propellant supplementing mechanism 12 through the electric control solid propellant supplementing window 13-1, and the supplementation of the electric control solid propellant in the upper stage 13 of the electric control solid rocket is realized, so that the carrying platform can work on orbit for a long time, and the design concept of the carrying platform in satellite emission aspect with low cost, high density and short period is fully embodied.

Wherein: the air inlet channel 1-1, the air storage and flow distribution device 6, the radio frequency ionization chamber 7 and the magnetic spraying accelerating tube 11 form an air suction type electric propulsion system of the constellation carrying platform. The radio frequency ionization chamber 7 adopts the electrodeless inductive discharge technology to realize high-efficiency ionization of gas molecules, and the magnetic spraying accelerating tube 11 utilizes the induction magnetic field of an electrified coil to converge and accelerate plasma plumes.

Referring to fig. 5 and 6, in an embodiment, the satellite storage tanks are designed to be in a deployable structure, the middle tank section 2 is designed with 6 satellite storage tanks 2-2 in total, when the satellite is filled, the satellite storage tanks 2-2 are deployed outwards, and the satellites in the satellite storage tanks 2-2 adopt a stacked storage mode, so that the space of the tank body can be maximally utilized.

Referring to fig. 9 and 10, in one embodiment the satellite is designed to be in a deployable configuration, i.e., the satellite 10 itself may be deployed, and after the satellite is launched into orbit, the solar panels folded on the sides of the satellite will be rotated to deploy to provide power thereto.

In a preferred embodiment, the upper stage 13 of the electric control solid rocket adopts HAN-based electric control solid propellant, electrodes adopt a fixed electrode type staggered electrode structure, two electrodes are distributed on the end face of the propellant in a staggered mode, and the electrode spacing is fixed. An openable window is arranged on the side face of the upper stage, and when the propellant is exhausted, the propellant in the carrying platform can press the electric control solid propellant into the fuel cabin through the window under the action of the motor.

Referring to fig. 7 and 8, an embodiment provides an electrically controlled solid rocket upper stage 13, where the electrically controlled solid rocket upper stage 13 includes a fuel tank 13-2, an electrode 13-3, a combustion chamber 13-4 and a tail nozzle 13-5, an electrically controlled solid propellant 9 is disposed in the fuel tank 13-2, a propellant pushing mechanism 13-6 is disposed at the bottom of the fuel tank 13-2, the front end surface of the electrically controlled solid propellant is sent to the position where the electrode 13-3 is located by the propellant pushing mechanism 13-6 to be burned, the combustion chamber 13-4 is disposed at the other side of the electrode 13-3, an outlet of the combustion chamber 13-4 is communicated with the tail nozzle 13-5, and the tail nozzle 13-5 is a shrinkage nozzle.

The electrodes 13-3 in the upper stage 13 of the electric control solid rocket adopt a fixed electrode type staggered electrode structure, the electrodes 13-3 comprise a first electrode 13-7 and a second electrode 13-8, the first electrode 13-7 is provided with a series of positive electrodes which are arranged in parallel and equidistantly, the second electrode 13-8 is provided with negative electrodes which are the same in number as the positive electrodes and are arranged in parallel and equidistantly, the first electrode 13-7 and the second electrode 13-8 are oppositely arranged on the same plane, the positive electrodes of the first electrode 13-7 and the negative electrodes of the second electrode 13-8 are staggered and distributed with each other, and the interval between the adjacent electrodes is fixed. The fixed electrode structure is adopted, two electrodes are distributed on the end face of the propellant in a staggered way, and the electric control solid propellant can be supplied by using power such as a motor in the propellant pushing mechanism 13-6. Because the electrode spacing is fixed, the device has the advantage of stable and reliable operation.

An openable electric control solid propellant supplementing window 13-1 is arranged on one side of the fuel tank 13-2, after the electric control solid propellant in the upper stage 13 of the electric control solid rocket is consumed, the electric control solid propellant supplementing window 13-1 is opened, and the propellant supplementing mechanism 12 can push the electric control solid propellant at the outlet end of the electric control solid propellant storage tank 2-1 into the fuel tank 13-2 of the upper stage 13 of the electric control solid rocket through the electric control solid propellant supplementing window 13-1, so that the electric control solid propellant in the upper stage 13 of the electric control solid rocket is supplemented.

Referring to fig. 11, the operation of the present application can be divided into three stages:

(1) Networking satellite loading stage:

in the stage, the integrated ultra-low orbit constellation carrying platform is moored in an ultra-low orbit with the height of about 200km, the self-orbit thrust compensation is finished by means of an air suction type electric propulsion system, after the space vehicle filled with satellites enters orbit, each satellite storage cabin of the middle cabin section of the carrying platform is unfolded, and after the satellite storage cabins are filled, the satellite storage cabins are closed.

(2) And (3) a carrying platform track lifting stage:

in this stage, the control system of the integrated ultra-low orbit constellation carrying platform allocates the satellite transmitting channels according to the target orbit parameters of the networking satellites and the number of satellites in the same orbit. The channel between the satellite storage cabin 2-2 and the upper stage 13 of the electric control solid rocket is a satellite launching channel, a docking driving mechanism (power is generally a motor) for pushing the satellite to dock with the upper stage 13 of the electric control solid rocket is arranged in the satellite storage cabin 2-2, and the docking driving mechanism pushes the satellite from the satellite storage cabin to the satellite launching channel, so that the satellite is connected with the corresponding upper stage of the electric control solid rocket in the launching channel.

In this phase, the gas-absorbing electric propulsion system of the carrying platform supplies the gas stored in the gas chamber to the rf ionization chamber, providing the additional impulse required for orbit lifting, lifting the orbit of the platform to a height of about 250km, and simultaneously selecting the appropriate phase angle of the transfer orbit for the in-orbit transfer of the satellite.

(3) Satellite transport in-orbit networking phase:

the upper stage of the electric control solid rocket carrying the satellite is taken out of the cabin from the tail end of the tail cabin section 3. After the electric control solid rocket is taken out of the cabin, the upper stage of the electric control solid rocket adopts electric control solid propellant as a propelling working medium, the electric control solid propellant can be repeatedly ignited and started, after reaching a target orbit, the satellite is separated from the upper stage of the electric control solid rocket and automatically expands and forms a network, and the upper stage of the electric control solid rocket returns to the carrying platform by means of residual fuel to supplement the fuel, so that the next satellite carrying task is ready to start.

Each satellite storage cabin is of an expandable structure, the satellite storage cabin can be expanded outwards under the condition of filling the satellites, and a plurality of satellites are filled in the satellite storage section in a stacked storage mode to maximize the utilization space.

Each satellite adopts an expandable structure, and is provided with a solar cell panel with the expandable structure, and is folded into a cylinder in the storage cabin. After the satellite is launched into orbit, the solar cell panel folded on the outer side surface of the satellite body can be rotated and unfolded to provide electric energy for the satellite body.

The upper stage of the electric control solid rocket is utilized to transport a plurality of satellites to the working orbit at one time, and has the advantages of repeatable starting, simple structure and low cost.

After the satellite is transported, the satellite can return to the carrying platform for propellant supplementation, an openable electric control solid propellant supplementing window is arranged on the side surface of the fuel cabin of the upper stage of the electric control solid rocket, and the electric control solid propellant in the carrying platform can be pressed into the fuel cabin of the electric control solid propellant through the electric control solid propellant supplementing window under the action of a propellant supplementing mechanism (the power of the electric control solid propellant supplementing mechanism is generally a motor).

The application is not a matter of the known technology.

The technical features of the above embodiments may be arbitrarily combined, and all possible combinations of the technical features in the above embodiments are not described for brevity of description, however, as long as there is no contradiction between the combinations of the technical features, they should be considered as the scope of the description.

The above examples illustrate only a few embodiments of the application, which are described in detail and are not to be construed as limiting the scope of the application. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the application, which are all within the scope of the application. Accordingly, the scope of protection of the present application is to be determined by the appended claims.

Claims (10)

1. The integrated ultra-low orbit constellation carrying platform is characterized by comprising an air inlet cabin section, a middle cabin section and a tail cabin section;

the air inlet cabin section comprises an air inlet channel, and the air inlet channel is used for taking in external ultra-low orbit lean atmosphere;

the middle cabin section comprises a radio frequency ionization chamber, an electric control solid propeller storage cabin and a satellite storage cabin, wherein the radio frequency ionization chamber is positioned on the central axis of the middle cabin section, and the air inlet channel provides a gas source for the radio frequency ionization chamber; the periphery of the radio frequency ionization chamber is provided with a plurality of electric control solid propellant storage tanks, each electric control solid propellant storage tank is internally provided with a supply mechanism, and the supply mechanism is used for pushing electric control solid propellants in the electric control solid propellant storage tank to the outlet end of the electric control solid propellant storage tank; the plurality of satellite storage cabins are arranged at the outermost periphery in the middle cabin section, and the plurality of satellites are filled in the satellite storage cabins;

the tail cabin section comprises a magnetic spraying accelerating tube, a propellant supplementing mechanism and an electric control solid rocket upper stage, wherein an outlet of the radio frequency ionization chamber is communicated with an inlet of the magnetic spraying accelerating tube, a plurality of electric control solid rocket upper stages are annularly distributed on the periphery of the magnetic spraying accelerating tube, and the satellite storage cabins are in one-to-one correspondence with the electric control solid rocket upper stages; an electric control solid propellant supplementing window is arranged at the upper stage of the electric control solid rocket; the outlet end of the electric control solid propellant storage cabin is arranged in the tail cabin section, and corresponds to the propellant supplementing mechanism.

2. The integrated ultra-low track constellation delivery platform of claim 1 wherein said inlet, middle and tail pod segments are sequentially docked into a polygonal column structured delivery platform.

3. The integrated ultra-low track constellation carrying platform of claim 2 wherein solar panels are distributed on the surface of the housing of the carrying platform and streamline spoilers are provided on the sides of the carrying platform.

4. An integrated ultra-low track constellation carrying platform according to claim 1, 2 or 3, wherein the outlet end of the air inlet channel is connected with a gas storage and flow distribution device, through which gas from the air inlet channel is supplied to a radio frequency ionization chamber for track maintenance of the platform; if gas from the inlet channel remains on the premise of ensuring that the platform track is kept normal, the remaining gas is stored in a gas chamber in the gas storage and flow distribution device for providing additional impulse required during track lifting.

5. The integrated ultra-low track constellation delivery platform of claim 4 wherein said inlet port is located at a front end of said inlet section and ambient air enters the inlet port through the inlet port.

6. The integrated ultra-low track constellation delivery platform of claim 5 wherein a series of air intake holes in said air intake are arranged in a honeycomb pattern; the air inlet is of a parabolic cross-section tapered structure, and the inner wall of the air inlet is coated with aluminized reflecting materials.

7. The integrated ultra-low track constellation delivery platform according to claim 1 or 2 or 4 or 5 or 6, wherein the space between the outside of the air inlet channel and the air inlet section housing is used as the installation space for the power supply system, control system or/and various kinds of satellite-borne sensors of the delivery platform.

8. The integrated ultra-low orbit constellation carrying platform according to claim 7, wherein each satellite storage compartment is of a deployable structure, and when the satellite storage compartment is filled with satellites, the satellite storage compartment is deployed outwards, and a plurality of satellites are filled in the satellite storage section in a stacked storage manner.

9. The integrated ultra-low orbit constellation carrying platform according to claim 8, wherein each satellite is provided with a solar panel with an expandable structure, and the solar panel folded on the outer side of the satellite body will be rotated and expanded to provide power for the satellite body after the satellite is launched into orbit.

10. The integrated ultralow orbit constellation carrying platform according to claim 8, wherein the upper stage of the electric control solid rocket comprises a fuel cabin, an electrode, a combustion chamber and a tail nozzle, electric control solid propellant is arranged in the fuel cabin, a propellant pushing mechanism is arranged at the bottom of the fuel cabin, the front end face of the electric control solid propellant is sent to the position where the electrode is positioned for combustion through the propellant pushing mechanism, the combustion chamber is arranged at the other side of the electrode structure, and the outlet of the combustion chamber is communicated with the shrinkage nozzle;

the electrodes in the upper stage of the electric control solid rocket adopt a fixed electrode type staggered electrode structure, the electrodes comprise a first electrode and a second electrode, the first electrode is provided with a series of positive electrodes which are arranged in parallel and equidistantly, the second electrode is provided with negative electrodes which are the same as the positive electrodes in number and are arranged in parallel and equidistantly, the first electrode and the second electrode are oppositely arranged on the same plane, the positive electrodes of the first electrode and the negative electrodes of the second electrode are staggered and alternately distributed, and the interval between the adjacent electrodes is fixed;

an openable electric control solid propellant supplementing window is arranged on one side of the fuel cabin, after the electric control solid propellant in the upper stage of the electric control solid rocket is consumed, the electric control solid propellant supplementing window is opened, and the propellant supplementing mechanism can push the electric control solid propellant at the outlet end of the electric control solid propellant storage cabin into the fuel cabin of the upper stage of the electric control solid rocket through the electric control solid propellant supplementing window, so that the electric control solid propellant in the upper stage of the electric control solid rocket is supplemented.