An aerostat-based space decoy system and method of deploying the same

Abstract

The application discloses a space false target system based on an inflatable structure and a deployment method thereof, and relates to the technical field of spacecraft protection.The system comprises a load cabin and a storage cabin, a camouflage module is arranged in the storage cabin, an inflation module for inflating the camouflage module, a power supply module for power supply and an attitude control module for controlling attitude are arranged in the load cabin, the storage cabin is composed of multiple folding plates, the folding plates can be automatically unfolded to release the camouflage module in the storage cabin, the deployment method is realized through satellite release, and subsequent attitude adjustment and inflation are performed, the folding storage cabin and a torsional spring hinge are combined to realize quick unfolding, the inflation module and the attitude control module are combined to realize quick deployment and stable control, the problems of complex deployment, low unfolding efficiency and insufficient attitude adjustment of a traditional system are solved, and the system has the advantages of quick deployment, compact structure, stable and reliable attitude and suitability for a dynamic space environment.

Description

Technical Field

[0001] This invention relates to the field of spacecraft protection technology, and in particular to a space decoy system based on an inflatable structure and its deployment method. Background Technology

[0002] With increasingly frequent space activities, spacecraft on-orbit safety faces growing surveillance and identification threats, making space situational awareness and strategic defense a key area of ​​focus for all countries. Space decoy systems, as an effective means of satellite deception and protection, can significantly improve satellite survivability, thereby protecting critical space assets. However, traditional space decoy systems typically rely on rigid structures or complex mechanical devices, resulting in high launch costs, heavy weight, and complex deployment processes. These drawbacks severely limit their effectiveness in dynamic and resource-constrained space environments.

[0003] While inflatable structures offer advantages such as lightweight design, compact storage, and rapid deployment, and have been applied in aerospace fields like deployable antennas and space station expansion modules, their application in space decoy systems remains significantly limited. The inflation, deployment, and shape maintenance processes are overly complex, often requiring mechanical supports to maintain shape, resulting in lengthy deployment times that fail to meet the stringent rapid deployment requirements of time-sensitive missions. Furthermore, existing inflatable structures generally lack rapid and effective on-orbit attitude stabilization mechanisms after deployment, hindering rapid attitude adjustment for space decoy systems. This severely restricts their application value in critical missions such as emergency threat response and electronic countermeasures deception. Summary of the Invention

[0004] The purpose of this application is to provide a space dummy target system based on an inflatable structure and its deployment method, which has the advantages of rapid deployment, compact structure, stable and reliable attitude and suitability for dynamic space environments.

[0005] Firstly, this application provides a space decoy system based on an inflatable structure, employing the following technical solution:

[0006] A space decoy system based on an inflatable structure includes a payload compartment and a storage compartment. The storage compartment contains a camouflage module, and the payload compartment contains an inflatable module for inflating the camouflage module, a power supply module for supplying power, and an attitude control module for controlling attitude.

[0007] The storage compartment is composed of multi-faceted folding panels; the side walls of the load compartment are all hinged with folding panels, and end panels are also hinged to the folding panels; the multi-faceted folding panels fold inward to form the side walls of the storage compartment, and the multi-faceted end panels fold inward and overlap and splice. The outermost top surface of the storage compartment is composed of two opposite end panels spliced ​​together and connected by explosive bolts; torsion springs are provided at the hinge points between the load compartment and the folding panels, as well as at the hinge points between the folding panels and the end panels; when the torsion springs are in their natural state, the storage compartment is in the unfolded state and the camouflage module is exposed.

[0008] Optionally, the camouflage module includes a bottom skin, an outer skin, and a support ring, all of which can be folded and stored in a storage compartment; the bottom skin is mounted on the load compartment via a connecting module; the support ring is a hollow ring that is fixed to the edge of the bottom skin; and the edge of the outer skin is fixed to the support ring.

[0009] Optionally, the connection assembly includes two flanges, one of which is fixedly connected to the load chamber, and the other flange is fixedly connected to the bottom skin. The two flanges cooperate to fix the bottom skin to the load chamber.

[0010] Optionally, the inflation module includes a gas cylinder, a pressure regulating valve, and a gas passage pipeline; the gas cylinder is fixedly installed in the load chamber; the gas passage pipeline connects the cavity of the support ring to the gas cylinder, and the pressure regulating valve is installed on the gas passage pipeline.

[0011] Optionally, the power supply module includes a lithium battery pack and a power controller, both of which are fixed in the payload compartment.

[0012] Optionally, the attitude control module includes a strong magnetometer, a magnetic torque generator, and a jet nozzle. The strong magnetometer and the magnetic torque generator are both installed in the payload compartment. The jet nozzle is located on the side wall and bottom of the payload compartment. The gas cylinder is connected to the jet nozzle through a gas passage pipe. The gas cylinder is sequentially connected to a main shut-off valve, a diversion valve, a pressure regulating valve, and a gas passage pipe.

[0013] Optionally, the jet holes on the sides of the payload compartment are located in the middle, and the jet holes on any two opposite sides are located one near the upper middle side and the other near the lower middle side; the jet holes on the bottom of the payload compartment are located at two opposite corners, the jet holes on the sides are used to control the pitch and roll of the payload compartment, and the jet holes on the bottom are used for propulsion.

[0014] Secondly, this application also provides a deployment method for a space decoy system based on an inflatable structure, employing the following technical solution:

[0015] A method for deploying a space decoy system based on an inflatable structure includes the following steps:

[0016] S1: During the ground preparation phase, the space decoy module is vacuumed and folded, and then fixedly connected to the storage compartment via a clamping flange; the storage compartment is folded into a closed state and secured with explosive bolts.

[0017] S2: In space orbit, when a satellite encounters an emergency or needs to perform a camouflage mission, it will eject its onboard space decoy system to achieve rapid separation from the satellite platform;

[0018] S3: After separation, the space decoy system activates the attitude adjustment module to perform three-axis attitude stabilization and orientation adjustment on the space decoy system, suppress the tumbling motion caused by the separation process, and ensure the attitude stability of the subsequent deployment stage;

[0019] S4: After the attitude stabilizes, the explosive bolts are unlocked, and the cabin panel rotates and opens around the pivot under the drive of the elastic potential energy preloaded by the torsion spring hinge, so that the internally folded space decoy module is completely exposed to the external space;

[0020] S5: Activate the inflation module, the elastic support ring inflates and unfolds, and the skin connected to it unfolds synchronously, gradually transforming from a folded configuration into a complete decoy with a predetermined shape, thus beginning the camouflage mission;

[0021] S6: After inflation is complete, activate the attitude adjustment jets. When the space decoy system needs to perform rapid response tasks, it generates a large torque response through pulsed gas injection to achieve rapid attitude correction and orbital fine-tuning, ensuring that the outer skin is always aligned with the enemy target. Simultaneously, the magnetic torque generator continues to operate, maintaining long-term attitude stability.

[0022] In summary, this application includes the following beneficial technical effects:

[0023] This application achieves rapid deployment through a foldable storage compartment and a torsion spring hinge, and combines an inflation module and an attitude control module to achieve rapid deployment and stable control. It solves the problems of complex deployment, low deployment efficiency and insufficient attitude adjustment of traditional systems, and has the advantages of rapid deployment, compact structure, stable and reliable attitude and suitability for dynamic space environments. Attached Figure Description

[0024] Figure 1 This is an overall structural diagram of the application when its structure is in a closed state;

[0025] Figure 2 This is an overall structural diagram of the application when its structure is in the open state;

[0026] Figure 3 This is a perspective view of the payload compartment in this application;

[0027] Figure 4 This is a schematic diagram showing the status of this application during its operation;

[0028] Figure 5 This is an overall structural diagram of the inflation module of this application;

[0029] Figure 6 This is a flowchart illustrating the scheme in this application.

[0030] Explanation of reference numerals in the attached figures:

[0031] 1. Storage compartment; 11. Explosion bolts; 12. End panel A; 13. End panel B; 14. Folding plate; 15. Torsion spring; 2. Load compartment; 3. Camouflage module; 31. Support ring; 32. External skin; 33. Bottom skin; 34. Inflation port; 41. Flange A; 42. Flange B; 51. Gas passage pipeline; 52. Pressure regulating valve; 53. Diverter valve; 54. Main shut-off valve; 55. High-pressure gas cylinder; 61. Lithium battery pack; 62. Power controller; 7. Magnetometer; 8. Magnetic torque generator; 9. Jet nozzle. Detailed Implementation

[0032] The following is in conjunction with the appendix Figure 1-6 This application will be described in further detail.

[0033] This application discloses a space decoy system based on an inflatable structure. This system can be carried by a satellite for easy deployment into outer space. It mainly includes a payload compartment 2 and a storage compartment 1. The storage compartment 1 houses a camouflage module 3, while the payload compartment 2 houses an inflation module, a power supply module, and an attitude control module. The storage compartment 1 is composed of multi-faceted folding panels 14. The side walls of the payload compartment 2 are hinged to the folding panels 14, and the folding panels 14 are hinged to end panels. The multi-faceted folding panels 14 fold inward to form the side walls of the storage compartment 1. The end panels fold inward and overlap, then are connected to the top surface via expansion bolts 11. It should be noted that when the entire system is in a folded state... Figure 2 One of the end panels A12 and B13 is pressed down by the other; while the external end panels are connected by explosion bolts 11. Torsion springs 15 are installed at the hinges between the load compartment 2 and the folding plate 14, and between the folding plate 14 and the end panels. In its natural state, the torsion springs 15 allow the storage compartment 1 to unfold and expose the camouflage module 3.

[0034] Upon receiving the separation command, the explosive bolt 11 disengages from the top surface, and the torsion spring 15 releases its stored elastic potential energy, driving the folding plate 14 to rotate and unfold around the hinge. During the unfolding process, the folding plate 14 causes the end panel to move synchronously, ultimately exposing the camouflage module 3 completely to the external space. The side walls of the unfolded storage compartment 1 are formed by the fully extended folding plate 14, and the top surface, separated from the end panel, forms an open structure. The inflation module then injects gas into the camouflage module 3, inflating it to the predetermined shape. Simultaneously, the attitude control module adjusts the system's attitude magnetically to suppress rotational motion generated during unfolding.

[0035] Through the above technical solution, this application achieves rapid autonomous deployment of a space decoy system. The cabin unfolds within 0.5 seconds after the explosive bolt 11 is unlocked, and enters the inflation phase within 3 seconds, reducing preparation time by 60% compared to traditional mechanical deployment methods. The torsion spring 15 drive mechanism avoids motor power consumption, enabling the system to complete deployment even without external power supply. The coordinated operation of the attitude control module and the inflation system ensures that the decoy has stable ground orientation capability when fully deployed, meeting the immediate response requirements in sudden threat scenarios.

[0036] This application further proposes a camouflage module 3 including a bottom skin 33, an outer skin 32, and a support ring 31, all of which can be folded and stored in the storage compartment 1; the bottom skin 33 is set on the load compartment 2 through a connecting module; the support ring 31 is a hollow ring body and is fixed to the edge of the bottom skin 33; the edge of the outer skin 32 is fixed to the support ring 31, and the support ring 31 is also provided with an inflation port 34 for connecting to the inflation module.

[0037] The bottom skin 33 refers to a planar foldable material layer connected to the payload compartment 2, which can be made of polyimide film or aramid fiber composite material, and forms a deployment reference surface through edge fixing. The outer skin 33 refers to a foldable flexible skin covering the outside of the support ring 31, which can be made of multi-layer aluminized polyester film, and forms a continuous surface with the support ring 31 through edge stitching or bonding; it can also be coated with an optical reflective layer and a radar scattering layer to simulate the reflection characteristics of a real satellite in the visible, infrared, and microwave bands. The support ring 31 is an inflatable structure with an annular cavity, which can be made of polyimide film, forming a rigid annular support frame after inflation. The connection module is the fixing interface between the bottom skin 33 and the payload compartment 2, which can be implemented using a flange and bolt combination structure to ensure the positioning accuracy of the skin during deployment.

[0038] The bottom skin 33 is fixedly connected to the load chamber 2 via a flange and compresses along with the chamber in the folded state. The support ring 31 remains flexibly folded when not inflated, and its annular cavity is connected to the inflation system. The bottom skin 33 is evenly distributed circumferentially along the support ring 31 and folds synchronously with it during inflation. During inflation, gas is first injected into the cavity of the support ring 31 to unfold it, causing the bottom skin 33 to unfold and form a reference plane. Simultaneously, the gas pulls the bottom skin 33 to extend circumferentially along the ring, forming a complete closed surface. After unfolding, the support ring 31 maintains its annular shape through internal air pressure, providing a continuous support boundary for the skin and preventing skin deformation due to the thermal environment of space.

[0039] Through the above technical solution, this application achieves efficient folding and storage of the camouflage module 3. After the support ring 31 is inflated and unfolded, it forms a self-sustaining frame, ensuring the stability of the unfolded skin shape. The fixed connection between the bottom skin 33 and the load chamber 2 provides an unfolding reference for the entire camouflage module 3, avoiding positional deviations when multiple components are unfolded. The fixing method between the bottom skin 33 and the support ring 31 eliminates the risk of skin wrinkling or displacement after unfolding, ensuring the integrity of the camouflage shape.

[0040] This application further proposes a connection assembly including two flanges, one flange being fixedly connected to the load chamber 2, and the other flange being fixedly connected to the bottom skin 33. The two flanges cooperate to fix the bottom skin 33 to the load chamber 2.

[0041] Through the above technical solution, this application achieves rapid and reliable fixing of the bottom skin 33 and the load chamber 2. The planar contact of the flange and the bolt fastening method ensure that the connection surface is evenly stressed, avoiding skin tearing caused by local stress during the inflation process.

[0042] This application further proposes an inflation module including a gas cylinder, a pressure regulating valve 52, and a gas passage pipeline 51. The gas cylinder is fixedly installed in the load chamber 2, and the gas passage pipeline connects the cavity of the support ring 31 to the gas cylinder. The pressure regulating valve 52 is installed on the gas passage pipeline.

[0043] The inflation module stores compressed gas in a gas cylinder, and the gas channel pipeline 51 connects the gas cylinder and the support ring 31 to form a gas transmission path. During the inflation phase, the pressure regulating valve 52 adjusts the gas flow rate according to a preset pressure threshold, causing the internal pressure of the support ring 31 cavity to gradually rise to the target value, pushing the support ring 31 to inflate from a folded state to a predetermined shape. During inflation, the pressure regulating valve 52 monitors the pipeline pressure in real time. When the pressure exceeds the threshold, it automatically reduces the flow rate to prevent the skin from rupturing due to overpressure; when the pressure is below the threshold, it increases the flow rate to ensure inflation efficiency. After inflation is complete, the support ring 31 maintains a constant pressure, providing stable support for the bottom skin 33.

[0044] Through the above technical solution, this application resolves the contradiction between low deployment efficiency and difficulty in maintaining shape in traditional inflatable systems, achieving efficient inflation and structural stability of the support ring 31. Simultaneously, dynamic pressure adjustment avoids the risk of skin rupture. The stable air source output from the inflation module further provides pressure assurance for the jet control of the attitude adjustment module, ensuring the response speed and control accuracy of subsequent attitude adjustments.

[0045] This application further proposes a power supply module including a lithium battery pack 61 and a power controller 62, both of which are fixed in the payload compartment 2.

[0046] This application further proposes an attitude control module including a strong magnetometer 7, a magnetic torque generator 8, and a jet nozzle 9. The strong magnetometer 7 and the magnetic torque generator 8 are both installed in the load chamber 2. The jet nozzle 9 is opened on the side wall and bottom surface of the load chamber 2. The gas cylinder is connected to the jet nozzle 9 through a gas passage pipe. The gas cylinder is sequentially connected to a main shut-off valve 54, a diversion valve 53, a pressure regulating valve 52, and a gas passage pipe.

[0047] Among them, the strong magnetometer 7 refers to the attitude sensing unit used for real-time monitoring of the spatial orientation of the space decoy system. Specifically, it can be implemented using a three-axis magnetoresistive sensor array, determining the system attitude angle by measuring the geomagnetic field vector. The magnetic torque generator 8 refers to the actuator that generates a continuous and stable torque through the action of a magnetic field. Specifically, it can be implemented using an orthogonally arranged magnetic coil group, generating a control torque that interacts with the geomagnetic field through current regulation. The main shut-off valve 54 is a safety device used to control the on / off of the gas cylinder's main gas path. Specifically, it can be implemented using a dual-redundant solenoid valve structure to prevent gas leakage during non-operating states. The diversion valve 53 is a control component used to distribute gas flow. Specifically, it can be implemented using a multi-channel proportional valve structure, adjusting the flow ratio of each nozzle according to control commands. The pressure regulating valve 52 is an actuator used to precisely control the gas injection pressure. Specifically, it can be implemented using a piezoelectric ceramic-driven precision pressure regulating valve structure to achieve graded control of the injection pressure.

[0048] Specifically, the strong magnetometer 7 collects the three-axis attitude data of the space decoy system in real time, and the magnetic torque generator 8 generates a stabilizing torque coupled with the geomagnetic field according to control commands, forming a basic attitude stabilization mechanism. Two pairs of jet nozzles 9 are symmetrically arranged in the middle of the sidewall of the payload compartment 2, near the upper and lower middle areas respectively, with two jet nozzles 9 arranged diagonally on the bottom surface. The sidewall jet nozzles 9 generate pitch and roll control torques through differential injection, while the bottom jet nozzles 9 generate propulsion torques through symmetrical injection. The main shut-off valve 54 acts as the main gas circuit switch, remaining closed in the non-operating state to ensure safety; the diversion valve 53 distributes gas to different nozzles according to control requirements; the pressure regulating valve 52 precisely controls the outlet pressure of each nozzle, enabling the gas injection to generate large thrust pulses for rapid attitude correction, and also output fine-tuning pressure to maintain precise control. The main shut-off valve 54, diversion valve 53, and pressure regulating valve 52 form a series pressure control system, achieving precise adjustment of gas injection parameters through graded control.

[0049] Through the above technical solutions, this application solves the problem of weak attitude control after the deployment of the inflatable space decoy system. The cooperation between the strong magnetometer 7 and the magnetic torque device 8 achieves basic attitude stability and suppresses attitude drift caused by space environment disturbances; the specially arranged jet nozzle system 9, through graded pressure regulation, can both generate large thrust pulses to quickly correct sudden attitude deviations and perform fine adjustments to maintain precise pointing; the parallel air circuit control system achieves independent and precise control of the flow and pressure of multiple nozzles while ensuring safe sealing. This composite control system enables the space decoy to quickly respond to sudden threats and perform attitude maneuvers after inflation and deployment, and to maintain a stable pointing state for a long time to perform continuous camouflage missions.

[0050] This application further proposes that the jet holes 9 on the sides of the payload compartment 2 are located in the middle position, and the jet holes 9 on any two opposite sides are located one near the upper middle side and the other near the lower middle side; the jet holes 9 on the bottom surface of the payload compartment 2 are located at two opposite corners, the jet holes 9 on the sides are used to control the pitch and roll of the payload compartment 2, and the jet holes 9 on the bottom surface are used for propulsion.

[0051] Specifically, when pitch adjustment is needed, the jet nozzle 9 near the upper center generates downward thrust by spraying gas, while the jet nozzle 9 near the lower center generates upward thrust; the combined force of these two forces creates a pitch moment. When roll suppression is needed, the difference in spray intensity between the two jet nozzles 9 creates a reverse torque. The two diagonally opposite jet nozzles 9 on the bottom surface generate thrust in different directions through alternating sprays; for example, the left front and right rear jet nozzles 9 working together can achieve rightward translational propulsion. The functional decoupling of the side jet nozzles 9 and the bottom jet nozzles 9 allows attitude control and trajectory adjustment to be performed in parallel. For example, during emergency maneuvers, the side jet nozzles 9 rapidly correct attitude deviations through high-frequency pulse sprays, while the bottom jet nozzles 9 continuously spray to achieve trajectory maneuvering.

[0052] Through the above technical solution, this application achieves independent control and rapid orbit adjustment of the three-axis attitude of the inflatable space decoy after deployment, enabling simultaneous attitude stabilization and position maneuvering when encountering sudden threats. For example, in electronic countermeasures deception scenarios, the system eliminates the 20-degree roll angle deviation caused by separation within 0.5 seconds through the side jet nozzles 9, while the bottom jet nozzles 9 generate continuous thrust to keep the decoy synchronized with the real satellite. This solution solves the camouflage failure problem caused by control lag in traditional inflatable structures, meeting the requirements of time-sensitive missions for millisecond-level response and centimeter-level positioning accuracy.

[0053] This application further proposes a deployment method for a space decoy system based on an inflatable structure, including the following steps: S1: In the ground preparation stage, the space decoy camouflage module 3 is evacuated and folded, and fixedly connected to the storage compartment 1 by a clamping flange; the storage compartment 1 is folded to a closed state and locked in place by an explosion bolt 11.

[0054] S2: In space orbit, when a satellite encounters an emergency or needs to perform a camouflage mission, it will eject its onboard space decoy system to achieve rapid separation from the satellite platform;

[0055] S3: After separation, the space decoy system activates the attitude adjustment module to perform three-axis attitude stabilization and orientation adjustment on the space decoy system, suppress the tumbling motion caused by the separation process, and ensure the attitude stability of the subsequent deployment stage;

[0056] S4: After the attitude stabilizes, the explosive bolt 11 is unlocked, and the cabin panel rotates and opens around the pivot under the elastic potential energy preloaded by the torsion spring 15 hinge, so that the internally folded space decoy module is completely exposed to the external space;

[0057] S5: Activate the inflation module, the elastic support ring inflates and unfolds, and the skin connected to it unfolds synchronously, gradually transforming from a folded configuration into a complete decoy with a predetermined shape, thus beginning the camouflage mission;

[0058] S6: After inflation is complete, activate the attitude adjustment jet port 9. When the space decoy system needs to perform a rapid response mission, it generates a large torque response through pulsed gas injection to achieve rapid attitude correction and orbital fine-tuning, ensuring that the bottom skin 33 is always aligned with the enemy target. At the same time, the magnetic torque generator 8 continues to operate to maintain long-term attitude stability.

[0059] In some specific embodiments, the jet nozzle 9 may employ a conical diffuser structure to reduce the impact of airflow disturbances on the skin, for example, by providing a porous damping layer at the nozzle. The magnetic torquer 8 coil may be embedded in the side wall interlayer of the load chamber 2, for example, by printing the coil on the surface of the carbon fiber composite material using a flexible circuit board process.

[0060] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. An aerostat-based space decoy system, characterized by: The load cabin and the storage cabin are provided with a camouflage module, the load cabin is provided with an inflation module for inflating the camouflage module, a power supply module for power supply and an attitude control module for controlling attitude; The storage cabin is composed of multi-faceted folding plates; the side walls of the load cabin are hingedly provided with folding plates, and end plates are further hingedly provided on the folding plates; the multi-faceted folding plates are folded inward to form the side walls of the storage cabin, the multi-faceted end plates are folded inward and then overlapped and spliced, the top surface of the outermost side of the storage cabin is formed by two opposite end plates and then connected by explosion bolts; torsional springs are arranged at the hinges of the load cabin and the folding plates and the hinges of the folding plates and the end plates; when the torsional springs are in a natural state, the storage cabin is in an unfolded state and the camouflage module is exposed.

2. A space decoy system based on inflatable structures according to claim 1, characterized in that: The camouflage module includes a bottom skin, an outer skin and a support ring, which can be folded and stored in the storage cabin; The bottom skin is arranged on the load cabin through a connecting assembly; the support ring is a hollow ring body fixed with the edge of the bottom skin; the edge of the outer skin is fixed with the support ring.

3. An inflatable structure based space decoy system according to claim 2, characterized in that: The connecting assembly includes two flanges, one of which is fixedly connected to the load cabin, and the other is fixedly connected with the bottom skin, and the two flanges are cooperatively fixed to fix the bottom skin on the load cabin.

4. A space decoy system based on inflatable structures according to claim 3, characterized in that: The inflation module includes a gas cylinder, a pressure regulating valve and a gas passage pipeline; the gas cylinder is fixedly arranged in the load cabin; the gas passage pipeline communicates the cavity of the support ring with the gas cylinder, and the pressure regulating valve is arranged on the gas passage pipeline.

5. An inflatable structure based space decoy system according to claim 4, characterized in that: The power supply module includes a lithium battery pack and a power supply controller, both of which are fixed in the load cabin.

6. An inflatable structure based space decoy system according to claim 5, characterized in that: The attitude control module includes a strong magnetometer, a magnetic torque device and a jet hole, both of which are installed in the load cabin; the jet hole is arranged on the side wall and the bottom surface of the load cabin; the gas cylinder is connected to the jet hole through the gas passage pipeline; the gas cylinder is sequentially connected with a main stop valve, a shunt valve, a pressure regulating valve and a gas passage pipeline.

7. An inflatable structure based space decoy system according to claim 6, characterized in that: The jet holes on the side of the load cabin are located at the middle position, and the jet holes on any two opposite sides are located close to the upper middle position and the lower middle position; the jet holes on the bottom surface of the load cabin are located at two opposite corners; the jet holes on the side are used to control the pitch and roll of the load cabin, and the jet holes on the bottom surface are used for propulsion.

8. A deployment method of an aerostat-based space decoy system for deploying the space decoy system of claim 7 into outer space, characterized in that: The method comprises the following steps: S1: in the ground preparation stage, the space decoy camouflage module is vacuumized and folded, and is fixedly connected with the storage cabin through clamping flanges; the storage cabin is folded to a closed state, and explosion bolts are installed for locking and fixing; S2: on the space orbit, when the satellite encounters an emergency or needs to perform a camouflage task, the space decoy system is thrown out to realize rapid separation from the satellite platform; S3: after separation, the space decoy system starts the attitude adjustment module to stabilize and adjust the three-axis attitude of the space decoy system, suppresses the rolling motion caused by the separation process, and ensures the attitude stability in the subsequent unfolding stage; S4: after the attitude is stabilized, the explosion bolts are unlocked, the cabin body panels are rotated and opened around the rotating shaft under the driving of the elastic potential energy of the torsional spring hinge preload, and the internally folded space decoy module is completely exposed to the outside space. S5: start the inflation module, the elastic support ring is inflated and unfolded, which drives the skin connected therewith to be unfolded synchronously, and gradually changes from the folded configuration to the complete decoy having the predetermined shape, and starts the camouflage task; S6: after the inflation is completed, the attitude adjustment jet orifice is enabled; when the space decoy system needs to perform a rapid response task, a large torque response is generated through pulse gas injection to realize rapid attitude correction and orbit fine adjustment, and ensure that the external skin is always aligned with the hostile target; at the same time, the magnetic moment device continues to work to maintain long-term attitude stability.

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