An autonomous system for space debris removal in low earth orbit and beyond

Abstract

The present invention discloses an autonomous system (100) for the removal of sub-10-centimeter orbital debris in Low Earth Orbit (LEO) and beyond. The system comprises an air tank module (102), a collector module (104), a deployable connector tunnel (112) forming a hermetically sealed debris transfer path, a laser alignment system (106) for axial coordination, an electromagnetic levitation system (108) for module separation and reattachment, ion propulsion systems (110) integrated on both modules for orbital maneuvering and positional control, and a centralized Al -based control unit (114) integrating an infrared imaging engine (114a) and a trajectory computation module (114b). The system also features a closed-loop gas recovery and re-pressurisation subsystem for sustainable multi-cycle operations. The system detects untracked debris, separating the modules to align on opposite sides of the debris, guiding, and propelling the debris centrally through the tunnel, capturing and compacting it internally, and reconnecting the modules to reset for the next cycle.

Description

[0001] FORM 2

[0002] THE PATENTS ACT, 1970 (as amended) (39 of 1970)

[0003] &

[0004] The Patent Rules, 2003 COMPLETE SPECIFICATION (See Section 10 rule 13)

[0005] 1. TITLE OF THE INVENTION

[0006] “AN AUTONOMOUS SYSTEM FOR SPACE DEBRIS REMOVAE IN EOW EARTH ORBIT

[0007] AND BEYOND”

[0008] 2. APPLICANT (S) a) Name MUJAWAR ZAARA MUSKAAN b) Nationality INDIAN c) Address PLOT# A54, RUKMINIPURI, OPP A.S. RAO

[0009] NAGAR, HYDERABAD - 500062, TELANGANA, INDIA. a) Name RASHIDA BANU MUJAWAR b) Nationality INDIAN c) Address : PLOT# A54, RUKMINIPURI, OPP A.S. RAO

[0010] NAGAR, HYDERABAD - 500062, TELANGANA, INDIA.

[0011] 3. PREAMBLE TO THE DESCRIPTION

[0012] COMPLETE

[0013] The following specification particularly describes the invention and the manner in which it is to be performed. 4. DESCRIPTION

[0014] Technical Field of the Invention

[0015] The present invention relates to the field of autonomous space systems, particularly in the domain of orbital debris detection, capture, and remediation. More specifically, the invention pertains to a modular robotic platform engineered for the detection, targeting, acquisition, and in-situ processing of sub- 10- centimeter space debris across all orbital regimes, including Low Earth Orbit (LEO), Medium Earth Orbit (MEO), Geostationary Orbit (GEO), and other relevant trajectories.

[0016] Background of the Invention

[0017] The exponential growth in the deployment of satellites, particularly in Low Earth Orbit (LEO), has led to an alarming accumulation of orbital debris, including a substantial number of fragments smaller than 10 centimeters. These sub-10 cm particles, while individually small, travel at extremely high velocities and pose a severe threat to operational spacecraft, satellites, and astronauts. Despite their size, such debris can cause catastrophic damage due to the high kinetic energy involved in orbital collisions. As the global space industry moves toward mega-constellation deployments and commercial space activities, the proliferation of untracked micro-debris has emerged as one of the most pressing challenges in space safety and sustainability.

[0018] Traditional debris removal strategies have largely focused on larger fragments and defunct satellites using techniques such as net capture, harpoons, robotic arms, tethered systems, or ground-commanded missions. While these methods may be effective for objects over 10 cm, they are inherently unsuitable for autonomous tracking and retrieval of smaller, fast-moving fragments. Moreover, many such systems require human intervention, pre-mission object cataloging, and extensive maneuvering, which make them inefficient or infeasible for smaller debris clusters that lack precise orbital data. Additionally, passive shielding or collision avoidance methods employed by operational spacecraft are reactive in nature and do not eliminate debris from orbit, thus offering no long-term remediation.

[0019] Prior art systems attempting autonomous debris mitigation typically rely on bulky multi-arm robotic mechanisms or electromagnetic tethers, which introduce complexity in mechanical design, consume significant onboard energy, and suffer from limited responsiveness in dynamic debris fields. These systems also struggle to maintain stability during free-flying module operations, especially when attempting precision capture in microgravity. Moreover, many lack integration of real-time trajectory computation, image-based target classification, and modular redundancy, all of which are vital for high- frequency autonomous operations in cluttered orbital environments. A critical technological gap exists in the development of compact, modular, and fully autonomous systems capable of detecting, targeting, and neutralizing sub- 10 cm debris without reliance on ground- based instructions or manual alignment. There is also a lack of effective systems that can maintain precise spatial coordination between multiple mobile modules in orbit while executing gas-based debris transfer and secure post-capture processing. Furthermore, existing systems often fail to integrate adaptive Al that can compute orbital maneuvers, align modules using optical feedback, and manage complex post-capture transitions such as re-docking, logging, and diagnostic updates.

[0020] In view of the above challenges, there is a dire need for an improved and technically advanced autonomous system that addresses the drawbacks of prior art. The present invention proposes a modular robotic system specifically designed for autonomous in-orbit capture and neutralization of sub- 10 cm debris.

[0021] Objects of the Invention

[0022] The primary object of the present invention is to provide an autonomous space system for the detection, interception, containment, and processing of orbital debris, with a focus on debris smaller than 10 centimetres. The invention utilizes a modular, reconfigurable architecture capable of dynamic, adaptive engagement across all orbital environments, including Low Earth Orbit (LEO), Medium Earth Orbit (MEO), Geostationary Orbit (GEO), and other relevant trajectories.

[0023] Another object of the invention is to incorporate an electromagnetic levitation -based modular design, wherein an air tank module and a collector module can separate and reattach without the use of mechanical hinges or docking mechanisms. This configuration enables the non-intrusive deployment and retrieval of a sealed transfer tunnel in a vacuum environment, facilitating the redirection of sub- 10- centimeter orbital debris using controlled bursts of compressed gas. The system ensures precise alignment and containment while minimizing mechanical complexity and physical wear in space operations.

[0024] It is a further object of the present invention to provide a hybrid debris detection system comprising, at minimum, infrared sensors configured for thermal signature identification of orbital debris. The system may further include, but is not limited to, optical imaging devices, LiDAR (Light Detection and Ranging) units, radar systems, and hyperspectral sensors, collectively enabling real-time detection, trajectory computation, and cross-spectral data validation. Such a configuration enhances detection accuracy, system redundancy, and operational reliability across varying orbital altitudes and environmental conditions. Yet another object of the invention is to provide an Al-based control system capable of multi-modal sensor fusion, dynamic decision-making, orbital manoeuvring, and coordination of subsystem functions, including gas burst activation, tunnel pressurization, inter-module alignment, and postprocessing logging.

[0025] A further object of the present invention is to provide a tunnel deployment assembly configured to extend, fold, or inflate between modular units of the system, while maintaining airtight integrity within a vacuum environment. This tunnel structure is designed to facilitate the safe, controlled transfer of captured orbital debris from the collection interface to the internal processing chamber, without compromising environmental isolation or operational reliability.

[0026] Still another object of the present invention is to provide a debris handling system integrated within the collector module, wherein captured orbital debris is subjected to mechanical reduction through one or more processing mechanisms, such as shredders, crushers, or pulverisers. The system may further include automated sorting and segregation subsystems configured to categorize and route the processed material for either in-situ recycling, repurposing, or secure long-term containment, depending on the material composition and mission objectives.

[0027] It is also an object of the present invention to promote energy -efficient and autonomous operation of the overall system through the integration of onboard solar power generation units, a closed-loop gas recovery and compression mechanism for repeated use of propellant gases, and an Al -governed control logic. The Al system is further configured to initiate operational cycles based on real-time threat assessment and prioritization algorithms, ensuring optimal allocation of resources toward high-risk debris targets while minimizing energy consumption and mission latency.

[0028] An additional object of the invention is to enable secure telemetry of mission logs, capture metadata, and health diagnostics to Earth stations using encrypted communication protocols.

[0029] Finally, the invention seeks to be adaptable to varying mission contexts, allowing the same system architecture to be redeployed for satellite servicing, sample return missions, or swarm-based coordinated debris mitigation in orbital environments around Earth, the Moon, Mars, or other celestial bodies.

[0030] An additional object of the invention is to provide an orbital maneuvering system utilizing ion propulsion for precision control, while not being limited to it. The system may also employ electric propulsion, Hall-effect thrusters, electrospray engines, nuclear thermal or electric propulsion, solar sails, chemical thrusters, or cold gas systems, enabling modular adaptation to mission requirements, energy constraints, and orbital environments with Al -optimized trajectory and fuel efficiency.

[0031] Brief Summary of the Invention

[0032] Aspects of the present invention relate to an autonomous system designed to detect, intercept, and process small orbital debris in low Earth orbit (LEO), as well as in medium Earth orbit (MEO), geostationary orbit (GEO), and other relevant space environments. The invention provides a modular spacecraft platform comprising an air tank module and a collector module, which are detachably connected via an electromagnetic levitation interface. This configuration enables precise and controlled separation and reattachment of the modules without the need for physical hinges or mechanical joints, thereby allowing flexible spatial orientation and stability during debris acquisition, containment, and transfer operations.

[0033] Another aspect of the invention involves the deployment of a sealed and pressure -tolerant tunnel between the separated modules, enabling safe transfer of captured debris in a vacuum environment. The tunnel may be extended, inflated, or deployed in an accordion-folded configuration, ensuring structural integrity and adaptability to spatial constraints during deployment and retraction cycles.

[0034] The invention further encompasses an advanced multi-modal sensor suite incorporating infrared sensors and cameras as primary detection elements. The system is not limited to these and may additionally include optical imaging devices, LiDAR (Light Detection and Ranging) units, radar systems, and hyperspectral sensors. This sensor array enables real-time detection, localization, and classification of orbital debris based on parameters such as size, material composition, reflectivity, and trajectory. Sensor outputs are processed and fused in real-time by an Al -driven control system, which governs all mission- critical operations including orbital manoeuvring, inter-module alignment, tunnel deployment and pressurization, debris trajectory tracking, classification, capture initiation, and post-processing analysis. The Al system is further configured for adaptive decision-making, optimizing performance under varying environmental and mission-specific conditions.

[0035] A further aspect of the present invention includes an air tank module, which is equipped with a ventilation-based gas delivery system comprising variable-pressure gas burst outlets. This system is configured to generate directional impulses for guiding sub-10-centimeter orbital debris into the collector module through a deployed interconnecting tunnel. The pressure, angle, and duration of gas bursts are dynamically modulated based on the mass, shape, and velocity of the incoming debris, as calculated by the onboard Al engine. The Al governs only the debris manipulation process, ensuring precision targeting and minimal off-axis dispersion. The collector module is designed to receive debris transferred through the tunnel originating from the air tank module. It contains a debris processing unit comprising shredders, crushers, or compactors to reduce debris volume for secure containment. The module may include internal compartments for material segregation and identification via embedded sensor arrays. A gas recovery system is integrated within both modules to reclaim residual gas after each propulsion event, enhancing energy efficiency and environmental safety.

[0036] Both the air tank module and the collector module are equipped with ion thrusters, enabling independent fine-tuned orbital manoeuvring, including station-keeping, approach alignment, and spatial reorientation. These thrusters are managed by a dedicated Al subroutine responsible for real-time trajectory calculation, energy optimization, and system stabilization. The modules may further include components such as pressure regulators, heat dissipation systems, structural health sensors, and onboard telemetry units to ensure autonomous navigation and operational integrity throughout the mission cycle.

[0037] Overall, the invention presents a highly integrated and adaptive debris removal system that can be operated individually or in coordinated swarms. It is scalable and configurable for use in Earth, lunar, Martian, or interplanetary orbital operations and may be repurposed for other aerospace functions such as satellite servicing, in-orbit construction, or sample retrieval missions.

[0038] Brief Description of the Drawings

[0039] The invention will be further understood from the following detailed description of exemplary embodiments, taken in conjunction with the accompanying drawings, in which:

[0040] Fig. la illustrates an isometric schematic view of the autonomous space debris removal system (100), showing the air tank module (102), collector module (104), electromagnetic levitation interface (108), deployable connector tunnel (112), and sensor arrays (102d, 104d) mounted on both modules in a fully operational configuration.

[0041] Fig. lb shows the separated configuration of the air tank module (102) and the collector module (104), with the electromagnetic levitation system (108) engaged and the connector tunnel (112) deployed, forming a sealed transfer pathway for debris.

[0042] Fig. 1c depicts the internal structural arrangement within the modules (102, 104), including the compressed gas storage chamber (102a), ventilation and release system (102b), debris intake chamber (104a), airtight shutter mechanism (104b), and mechanical crusher (104c). Fig. 2a presents a flowchart outlining the autonomous operational sequence of the system (100), including initialization, debris detection, target tracking, orbital maneuvering, tunnel deployment, debris propulsion, capture, processing, and system reset.

[0043] Fig. 2b illustrates Stage 1 of operation, depicting post-launch initialization, debris scanning by multimodal sensors (102d, 104d), and initial orbital corrections by the ion propulsion system (110).

[0044] Fig. 2c illustrates Stage 2, showing electromagnetic levitation -based module separation, tunnel deployment (112), laser-guided alignment (106), and propulsion of debris via controlled gas burst (102b).

[0045] Fig. 2d illustrates Stage 3, showing debris capture within the collector module (104), activation of the airtight shutter mechanism (104b), debris compaction using the mechanical crusher (104c), and retraction of the connector tunnel ( 112), preparing the system for the next operational cycle.

[0046] Fig. 3 illustrates sequential schematic views representing various operational phases of the autonomous space debris removal system (100).

[0047] Fig. 4 presents the internal architecture of the Al -based control unit (114), including the infrared image processing engine (114a), trajectory computation module (114b), and system coordination module.

[0048] Fig. 5 illustrates the ion propulsion system (110) in detail, showing the compressed gas storage, feed system, control modules, and Hall-effect or gridded ion thrusters used for orbital corrections and velocity matching.

[0049] Fig. 6 shows the stage-wise operational deployment sequence of the system (100), encompassing six phases: standby initialization, debris detection, orbital alignment, debris propulsion and capture, compaction and storage, and reconfiguration for subsequent cycles.

[0050] Fig. 7 illustrates the operational flow of the autonomous space debris removal system (100).

[0051] The figures are provided solely for illustrative purposes and are not intended to limit the scope of the invention, which is defined by the appended claims. Detailed Description of the Invention

[0052] According to an exemplary embodiment of the present invention, an autonomous modular system is provided for the detection, targeting, capture, and in-situ processing of orbital debris, particularly sub- 10-centimeter particles, across all orbital regimes, including Low Earth Orbit (LEO), Medium Earth Orbit (MEO), and Geostationary Orbit (GEO). The system is configured to operate with minimal or no human intervention and incorporates Al-driven control logic, multi-modal sensor fusion, modular electromagnetic separation, and closed-loop resource management to provide an efficient, scalable solution for long-duration space debris remediation.

[0053] The invention comprises a dual-module architecture consisting of an air tank module and a collector module, which operate in coordination. These modules are designed to temporarily decouple during debris capture operations and reattach via an electromagnetic levitation interface that maintains precise alignment without mechanical hinges or physical contact, enabling reconfiguration in microgravity environments.

[0054] The air tank module houses a ventilation -based debris propulsion system comprising high-pressure inert gas storage. This system is configured to emit controlled gas bursts to redirect sub-10-centimeter orbital debris into the collector module through a deployed tunnel. Burst parameters, pressure, angle, and duration, are modulated based on real-time estimations of debris mass, shape, and velocity by the onboard AL To conserve resources, the module includes reverse-flow suction inlets for reclaiming unused or residual gas.

[0055] Furthermore, the invention includes a closed-loop gas recovery and re-pressurisation subsystem within the air tank module. This system reclaims expelled gases post debris capture and stores them for reuse, enhancing mission sustainability and minimizing resource consumption.

[0056] The collector module is configured to receive and process redirected debris. It includes a debris handling system comprising shredders, crushers, or compactors that reduce volume for optimized storage. Internally, compartmentalized zones may be used to segregate debris by type (e.g., metallic, composite, or ceramic), supported by real-time classification from onboard sensors. A gas recovery subsystem, integrated within both the tunnel and the collector module, filters and recycles gas used during capture, maintaining environmental safety and operational efficiency.

[0057] A sealed, deployable tunnel constructed from radiation-resistant, flexible materials extends from the air tank module to the collector module. This tunnel establishes an airtight path for debris transfer, with embedded isolation elements to preserve vacuum integrity and enable efficient gas recovery postcapture. The tunnel retracts upon completion of the debris transfer and processing cycle.

[0058] Ion thrusters are integrated into both the air tank module and the collector module to provide fine-tuned orbital maneuvering capabilities. These thrusters are used for station -keeping, spatial alignment, approach vectoring, and orbital repositioning. Each module’s thrusters are independently governed by an Al-based trajectory and stabilization system that ensures precise, energy-efficient movement and coordinated formation control. Additional subsystems in both modules may include pressure regulators, heat dissipation surfaces, structural health monitors, and internal telemetry sensors.

[0059] The system utilizes a hybrid sensor suite with an emphasis on infrared sensors for thermal detection of non-reflective debris, supplemented by optical cameras, LiDAR units, radar systems, and hyperspectral imaging sensors. These are distributed across both modules to provide 360-degree awareness, real-time tracking, and classification of debris targets. Sensor data is processed via Al -based sensor fusion algorithms, enabling adaptive threat prioritization and autonomous mission planning.

[0060] An onboard Al control unit governs all major functions, including detection, propulsion modulation, tunnel deployment, module alignment, and debris processing. It also handles telemetry logging, fault detection, and continuous learning from mission outcomes. This Al allows the system to operate in either a fully autonomous mode or under limited ground supervision.

[0061] The system supports secure telemetry transmission of operational data, diagnostics, and mission logs to Earth-based control stations using encrypted communication channels. All core functions, capture initiation, processing, navigation, and recovery, can be executed autonomously based on real-time Al analysis of threat vectors and mission urgency.

[0062] Designed to function as either a standalone unit or part of a swarm, the system is scalable for wider orbital coverage. Its modular structure allows for mission-specific upgrades and adaptation to related aerospace tasks such as satellite servicing, orbital construction, and extraterrestrial sample retrieval.

[0063] By integrating intelligent sensing, Al-guided propulsion, electromagnetic modular separation, internal material processing, and regenerative gas management, the invention offers a technically advanced, sustainable solution for mitigating sub-10-centimeter orbital debris across a broad range of orbital environments. The Al-based control unit described herein may employ any suitable combination of rule-based systems, reinforcement learning, supervised learning, or hybrid models to achieve autonomous operational functionality, and is not restricted to any particular algorithm or software architecture.

[0064] Detailed Description of the Invention Referring to Drawings

[0065] Referring to Fig. 1, the system (100) is an autonomous modular platform designed for the capture, redirection, and processing of sub-10-centimeter space debris across various orbital regimes, including Low Earth Orbit (LEO), Medium Earth Orbit (MEO), and Geostationary Orbit (GEO). The system comprises a first module identified as the air tank module (102), a second module termed the collector module (104), and a set of intermediate mechanical and Al -coordinated subsystems. Operations are orchestrated primarily by an onboard Al -based control unit (114), with optional semi-autonomous overrides or ground-based monitoring.

[0066] The air tank module ( 102) contains a compressed gas storage chamber ( 102a) for inert propulsion gases such as nitrogen, xenon, krypton, argon, or carbon dioxide. A ventilation and release system (102b) governs directional gas bursts used for debris redirection via electronically actuated valves and pressure regulators. The system also incorporates reverse suction inlets to reclaim unused gas, forming a regenerative cycle. The module features an electromagnetic levitation stabilizer system (102c) to maintain a controlled non-contact spatial offset from the adjacent collector module (104), enabling precise tunnel-based debris transfer.

[0067] The air tank module (102) further incorporates a reverse suction inlet and re -pressurisation mechanism that captures residual propulsion gas from the tunnel and collector module post debris transfer. This recovered gas is filtered, compressed, and stored back into the gas storage chamber (102a), forming a closed-loop system that conserves resources and extends operational life.

[0068] In one embodiment, the reverse suction inlet incorporates filtration and molecular sieving elements to remove particulates before gas is re-pressurised and stored back in the compressed gas chamber (102a).

[0069] To achieve robust object tracking, the air tank module is equipped with a hybrid detection suite, including infrared (IR) sensors for thermal profiling, along with optical cameras, LiDAR units, radar modules, and hyperspectral sensors. This allows for adaptive sensor fusion and cross-validation of orbital debris parameters such as size, trajectory, material type, and thermal signature. A laser-based alignment unit (102e) provides target-locking and debris engagement accuracy.

[0070] The collector module (104) includes a debris intake chamber (104a) and an airtight shutter mechanism (104b), which activates during capture to maintain vacuum integrity and prevent fragment ejection. Incoming debris is processed through a mechanical crusher (104c), which compacts the material for optimized long-term storage. A dedicated IR sensor (104d) confirms successful capture before processing initiates. Like the air tank module, the collector module integrates electromagnetic levitation stabilizers and similar detection sensors for modular alignment and situational awareness.

[0071] In one embodiment, the tunnel (112) is constructed from materials such as polyimide films, aramid- reinforced laminates, or metalized polymer composites, selected for their radiation resistance, mechanical flexibility, and vacuum durability.

[0072] To maintain accurate orientation and positioning, a laser guidance and alignment system (106) is employed, comprising optical sensors (106a) and laser emitters (106b). These components work in conjunction with a electromagnetic levitation interface (108) that enables smooth decoupling and reattachment of the modules before and after each collection cycle.

[0073] As illustrated in Fig. 5 (500), both the air tank module (102) and the collector module (104) are equipped with ion thruster systems (110), such as Hall-effect or gridded ion engines. These propulsion units enable low-thrust, high-efficiency orbital maneuvers for realignment, velocity matching, or repositioning. Each set of thrusters operates under a dedicated Al -guided trajectory and stabilization subsystem that adjusts course based on mission parameters and debris distribution.

[0074] The core of the invention is the Al-based control unit (114), depicted in Fig. 4 (400). It includes:

[0075] • An infrared image processing engine (114a) for real-time debris classification

[0076] • A trajectory computation module (114b) to determine orbital parameters and delta-V requirements

[0077] • A system coordination module for managing tunnel deployment, propulsion control, debris capture sequencing, sensor feedback, and inter-module synchronization

[0078] The Al can operate in fully autonomous mode or with semi -autonomous override capabilities via ground-based telemetry. The system continually logs performance data, self-corrects for drift or system inefficiencies, and adapts using machine learning from mission feedback.

[0079] Fig. 2a provides a phase-wise flowchart of system (100) operations. The autonomous sequence includes:

[0080] 1. Initialization

[0081] 2. Pursuit and tracking

[0082] 3. Tunnel deployment

[0083] 4. Collection and internal debris processing 5. System reset and repositioning

[0084] Each step is executed without human input unless override is initiated, ensuring scalability and responsiveness in increasingly congested orbital environments.

[0085] Phase I: Post-Deployment Initialization

[0086] (201) Post-Launch System Initialization:

[0087] Upon reaching the designated orbital altitude, the autonomous / semi -autonomous system (100) activates. Key subsystems, including the Al control unit (114), ion propulsion system (110), multimodal imaging suite, and alignment modules, are initialized for mission readiness.

[0088] (202) Infrared-Based Debris Detection:

[0089] The air tank module and collector module (102) scans its surrounding orbital region using a sensor suite comprising infrared sensors and cameras, as well as optical imagers, LiDAR, radar, and hyperspectral units. This enables high-accuracy detection of untracked orbital debris under 10 centimeters in size.

[0090] (203) AI-Guided Target Lock and Tracking:

[0091] The Al control unit (114) autonomously processes sensor data to track debris in real time, calculating parameters such as orbital path, relative velocity, and spin orientation. Once locked, the system prepares for interception.

[0092] (204) Guided Orbital Approach:

[0093] The ion propulsion system (110), located on both the air tank and collector modules, performs fine orbital corrections and alignment maneuvers to synchronize the platform’s trajectory with that of the target debris.

[0094] Phase II: Orbital Pursuit and Engagement Setup

[0095] (205) Electromagnetic Levitation Separation and Debris-Centric Alignment:

[0096] Upon achieving optimal orientation, the electromagnetic levitation system (108) enables precise spatial separation of the air tank module (102) and the collector module (104), without requiring mechanical hinges or contact. Following this separation, both modules autonomously reposition themselves on either side of the identified debris, with the debris centered along the system’s shared axis. This strategic alignment establishes the baseline for tunnel deployment and ensures direct, uninterrupted debris transfer through the central corridor.

[0097] (206) Real-Time Positional Adjustment:

[0098] Dynamic micro -adjustments are executed using sensor feedback and the alignment system, maintaining tight orientation tolerances between both modules throughout debris transit. Phase III: Tunnel Deployment and Containment

[0099] (207) Sealed Tunnel Engagement:

[0100] The connector tunnel (112) remains hermetically sealed during the operation to maintain internal pressure integrity and prevent gas leakage into the vacuum environment.

[0101] (208) Laser-Based Axial Tracking:

[0102] Throughout the transfer, the laser alignment system (106) ensures continuous axial congruence between both modules. This guarantees accurate debris redirection into the collector intake.

[0103] (209) Controlled Gas Burst Activation:

[0104] Using the ventilation system (102b), the air tank module (102) releases a calibrated burst of inert gas (e.g., nitrogen or CO2). This airburst redirects debris into the connector tunnel (112), based on AI- estimated mass, shape, and speed of the target object.

[0105] (210) Synchronized Collector Gate Activation:

[0106] The collector module (104) autonomously actuates its airtight shutter mechanism (104b), preparing to receive redirected debris. This process is coordinated by the Al to align with the debris arrival window.

[0107] Phase IV: Debris Collection and Processing

[0108] (211) Debris Confirmation via Internal Sensors:

[0109] Internal sensors, especially infrared detectors and optical units, verify successful debris capture inside the collector module (104). The shutter (104b) closes immediately to secure containment.

[0110] (212) Mechanical Processing of Captured Debris:

[0111] Captured debris is passed into a crushing or shredding unit (104c) to reduce volume. This enables secure storage and facilitates long-term mission sustainability.

[0112] (213) Air Recovery and Depressurization:

[0113] Any residual gas within the tunnel and collector module is reclaimed using reverse suction into the air tank module (102), enhancing propulsion resource efficiency. The collector is depressurized to a neutral state post-transfer.

[0114] (214) Tunnel Retraction and Magnetic Reattachment:

[0115] The connector tunnel (112) retracts into its stowed configuration. The modules (102, 104) are reconnected magnetically using the electromagnetic levitation system (108) in preparation for the next operation. Phase V: Cycle Reset and Autonomous Logging

[0116] (215) Telemetry and Reinitialization:

[0117] The Al control unit (114) logs operational metrics, sensor performance, system diagnostics, and debris classification. It then autonomously or semi -autonomously reinitiates the system’s detection phase, returning to block (202).

[0118] Figure 2b illustrates Stage 1 (220) of the autonomous space debris removal system (100), capturing the critical initial phase of operation: deployment, system initialization, and debris targeting. In this stage, the system, comprising the air tank module (102) and the collector module (104), is shown in a electromagnetically docked configuration after being deployed into its designated orbital path in Low Earth Orbit (LEO) or other applicable orbits. The outer surface of each module features a geodesic frame embedded with infrared (IR) sensors and cameras (102d, 104d), optical cameras, LiDAR units, radar modules, and hyperspectral detectors, enabling 360-degree surveillance of the surrounding orbital environment. Once deployed, the electromagnetic levitation system (108) enters standby mode while internal subsystems perform calibration routines, Al model initialization, and sensor diagnostics.

[0119] Following successful initialization, the system enters the debris detection and targeting phase, where IR sensors and cameras (102d, 104d) and other onboard instruments scan for sub-10-centimeter, non- cooperative debris. Detected debris is then classified by the Al -based navigation and control unit (114) to verify it is inactive and suitable for neutralization. Using inputs from onboard sensors, the Al computes orbital parameters including right ascension, declination, relative velocity (AV), and angular displacement, referencing known tagged objects for accuracy. An optimal low-AV trajectory is calculated, after which the ion propulsion systems (110), located on both the air tank and collector modules, execute coordinated adjustments to match velocity and position with the debris.

[0120] Figure 2c illustrates Stage 2 (230), encompassing the critical operational phases of capture, transfer, and onboard processing. At this point, the air tank module (102) and collector module (104) undergo electromagnetic levitation-based separation. Following this controlled detachment, both modules autonomously reposition themselves on opposite sides of the target debris, aligning symmetrically with the debris cantered between them. The connector tunnel (112) is then deployed, creating a sealed and telescopically or inflatable channel for debris transit. The laser alignment system (106), consisting of multiple sensors (106a) and guidance beams (106b), actively maintains axial alignment, shown as “laser center align” in the diagram.

[0121] Figure 2d illustrates Capture and Transfer, where a precisely modulated air burst is generated by the ventilation system (102b) in the air tank module. Compressed gas (such as nitrogen or other inert gases) propels the debris through the tunnel (112) toward the collector intake chamber (104a). As the debris enters, the airtight shutter gates (104b) seal automatically, preventing backflow. The debris is then processed by the onboard crushing mechanism (104c) into compressed, storable fragments. Meanwhile, the system activates reverse-flow air recovery, drawing the displaced gas from the tunnel and collector back into the air tank’s gas storage chamber (102a) to enhance efficiency and sustainability.

[0122] Once the debris is securely stored and pressure conditions normalized, the connector tunnel (112) retracts, and the modules reconnect using the (electromagnetic) levitation system (108), restoring their default docked configuration. This visual sequence demonstrates the precision, control, and closed-loop sustainability of the autonomous debris removal cycle.

[0123] Figure 2d illustrates Stage 3 (240), representing cycle reset and next-cycle initialization. Here, the air tank module (102) and collector module (104) are reattached, with the connector tunnel (112) fully stowed. Their symmetric alignment indicates completion of the previous cycle and readiness for the next debris engagement.

[0124] The Al-based control system (114) performs a mission log update, cataloguing the captured object as “neutralized.” All telemetry, sensor readings, and diagnostic outputs are stored for performance tracking and adaptive optimization. The sensor grid (102d, 104d) is reactivated, and the system resumes autonomous scanning for new debris targets, marking the start of another closed-loop capture cycle.

[0125] Figure 3 illustrates sequential schematic views representing various operational phases of the autonomous space debris removal system (100). Each sub-figure depicts the relative positioning and configuration of the air tank module (102) and collector module (104) during different mission stages:

[0126] Post-Deployment Initialization (300): Shows the modules in a docked configuration, with all subsystems active and sensors initialized for debris detection.

[0127] Orbital Pursuit (302): The system begins active scanning of the orbital environment. Upon identifying target debris, it initiates orbital maneuvers using the ion propulsion system (110). The modules remain docked during this low- AV pursuit phase, guided by real-time Al trajectory predictions from the navigation and control system (114).

[0128] Engagement Setup (304): In preparation for capture, the system activates the electromagnetic levitation system (108) to separate the modules. The laser alignment system (106) begins calibration, while the deployable connector tunnel (112) begins extending between the modules. The system locks onto the debris using laser guidance (106b) and positional feedback from alignment sensors (106a). Debris Collection and Processing (Capture) (306): Once the connector tunnel (112) is fully deployed, the air ventilation system (102b) triggers a compressed gas burst from the air storage chamber (102a), transferring the debris into the collector chamber (104a). The airtight shutter (104b) then seals the debris inside.

[0129] Debris Collection and Processing (Crushing) (308): The metal crusher (104c) is activated to reduce the debris into compacted fragments for efficient storage. Simultaneously, the displaced air is recovered and compressed back into the air tank module (102) using a reverse-pressure mechanism, contributing to system sustainability.

[0130] Cycle Reset and System Logging (310): After processing, the connector tunnel (112) retracts, and the modules reattach electromagnetically into their original docked configuration. The Al system (114) updates the mission logs with telemetry and classification data, marking the debris as “neutralized.” The system is now ready to repeat the detection and capture cycle autonomously.

[0131] Figure 6 (600) outlines the six-stage operational deployment of the system, from initialization to debris capture and reset.

[0132] • Stage 1: System in standby with modules docked, tunnel (112) retracted, and sensors active.

[0133] • Stage 2: Upon debris detection, ion thrusters (110) on both modules are activated to perform orbital alignment.

[0134] • Stage 3: Modules separate using electromagnetic levitation, then autonomously align with debris positioned in the center. Tunnel (112) is deployed and laser alignment (106) is initiated.

[0135] • Stage 4: An air burst from air tank module (102) propels debris through the tunnel to the collector (104).

[0136] • Stage 5: Debris is sealed, crushed, and stored; gas is reclaimed; tunnel retracts.

[0137] • Stage 6: Modules reconnect; mission data is logged by Al (114); the system resets for the next operation.

[0138] Fig. 6 (600) illustrates a progressive, stage-wise deployment sequence of the autonomous system (100) designed for the capture and neutralization of sub- 10 centimeter orbital debris in Low Earth Orbit (LEO). The depiction encompasses six critical operational stages that span from initial activation to successful debris containment and system reset, representing the full cycle of an autonomous engagement.

[0139] In Stage 1, the system begins in its stowed or standby configuration. Both the air tank module (102) and the collector module (104) are structurally connected, with the deployable connector tunnel (112) retracted and locked. Infrared sensors and cameras (102d, 104d), optical sensors, LiDAR units, radar modules, and hyperspectral detectors are passively scanning for thermal anomalies indicative of debris. The Al-based control unit (114) remains in low-power observation mode, periodically logging environmental telemetry.

[0140] In Stage 2, upon successful detection of orbital debris, the Al-based control unit (114) activates the ion propulsion system (110) to perform fine-tuned orbital corrections. Using parameters computed by the trajectory computation module (114b), the system aligns itself with the target object’s trajectory and velocity. The onboard sensors confirm positional convergence, and the laser alignment system (106), with multiple beam emitters (106a) and detectors (106b), pre-aligns axial orientation between the modules.

[0141] Stage 3 the electromagnetic levitation system (108) disengages the air tank module (102) from the collector module (104), inducing a controlled and measurable spatial separation initiates the physical deployment of the connector tunnel (112). The tunnel (112), now fully extended, forms a sealed conduit that guides debris from the air tank’s output toward the collector’s intake. The alignment is continuously refined by the laser guidance subsystem (106b) to ensure axial locking precision.

[0142] In Stage 4, the ventilation and release system ( 102b) within the air tank module ( 102) emits a directional gas burst. This controlled propulsion, leveraging any gas as the working fluid, transfers the orbital debris, now aligned with the system’s axis, through the tunnel (112) and into the intake chamber (104a) of the collector module (104). The laser alignment system ensures accurate focus and vector trajectory during the propulsion event.

[0143] Stage 5 involves immediate sealing of the intake using the airtight shutter mechanism (104b), thereby isolating the debris in the collector module (104). The mechanical crusher (104c) is subsequently activated to compact the debris, converting bulk objects into high -density, storable fragments. Compression ratios are maintained between 4: 1 and 5: 1, optimizing the post-compaction volume and enabling higher object throughput per mission cycle. The IR sensor (104d) confirms successful containment.

[0144] In Stage 6, the system performs depressurizing of the collector module for air tank module to receive the air for reuse and tunnel retraction and reattachment of the air tank and collector modules using the electromagnetic levitation system (108). The onboard Al-based control unit (114) logs the entire cycle, including debris mass estimation, energy consumption, component health checks, and trajectory deltas. The system resets to standby configuration, ready to repeat the detection-to-collection sequence for the next debris object. The modular architecture disclosed is adaptable and may be reconfigured for other applications including but not limited to satellite servicing, orbital construction, sample retrieval, or planetary exploration, without departing from the core inventive concept.

[0145] It is to be understood that the embodiments described herein are exemplary and non -limiting. Variations, modifications, and adaptations may be made by those skilled in the art without departing from the scope and spirit of the present invention, which is defined by the appended claims.

[0146] Figure 7 (700) (Part A) presents the first sequence in the operational flow of the autonomous space debris removal system (100), initiating from the system’s deployment into low Earth orbit (LEO). The process begins with system initialization, followed by a comprehensive health check to ensure all subsystems, including sensors, propulsion, and Al modules, are functioning correctly. After initialization, the system accesses real-time orbital data such as satellite locations, known debris fields, and asteroid paths from ground stations, combining this with onboard infrared (IR) sensors and cameras to detect and track debris smaller than 10 cm in diameter.

[0147] Once a potential debris object is detected, the system locks onto the target, verifying it falls within the sub-10-centimeter range. If confirmed, the system proceeds to calculate the approximate coordinates and relative velocity of the debris. Subsequently, the onboard Al activates the ion propulsion system (110), which initiates a controlled maneuver to approach the debris. While en route, the Al performs real-time trajectory adjustments, applying delta velocity (AV) corrections to ensure precision targeting. Upon reaching the proximity of the target object’s orbit, the system matches its velocity vector to achieve orbital synchronization. The process concludes with the activation of both the air tank module (102) and the collector module (104), setting the stage for debris engagement in the next part of the flow.

[0148] Figure 7 (Part B) illustrates the mid-phase operations of the autonomous space debris removal system, focusing on module activation, electromagnetic separation, alignment, and capture setup. The process begins by confirming that both the air tank module ( 102) and the collector module (104) are successfully activated. Once both modules are functional, the system proceeds to initiate the electromagnetic levitation system (108), which, upon activation, creates a controlled electromagnetic separation between the two modules. This spatial separation is crucial for establishing the proper geometry and clearance for debris engagement.

[0149] Using the ion propulsion system (110), the identified debris is maneuvered precisely into the space between the modules. The system then engages the laser alignment system (106) to ensure accurate axial alignment between the air tank’s ventilation port, the collector chamber, and the connector tunnel (112). After alignment is confirmed, the connector tunnel is deployed to interlock both modules, creating an airtight path around the target debris. Sensors verify the presence of the debris inside the tunnel. Upon successful confirmation, the air tank module’s ventilation system (102b) releases a calculated burst of compressed air, pushing the debris securely through the tunnel and into the collector chamber (104a). This entire sequence ensures a non-contact, vacuum -compatible debris capture process, enabling the safe containment of high-speed micro-debris.

[0150] Figure 7 (Part C) illustrates the concluding operational stage of the autonomous debris removal cycle, focusing on processing the captured debris, internal air recycling, and preparing the system for its next mission. After the debris is securely enclosed within the collector chamber (104a), the system triggers the airtight shutter mechanism (104b) to fully isolate the internal environment. Subsequently, the metal crusher (104c) inside the collector is activated to break down the debris into compact fragments, enhancing volume efficiency for onboard storage. A confirmation check ensures that the debris has been properly crushed.

[0151] Following this, the ventilation system in the air tank module (102b) is activated in reverse mode to draw displaced air from the tunnel and the collector back into the compressed air chamber (102a). Simultaneously, the collector module returns to vacuum conditions, achieving a net-zero pressure balance. Once the system verifies successful air suction, it proceeds to retract and isolate the connector tunnel (112), confirming airtight separation between modules.

[0152] A secondary confirmation ensures complete retraction and tunnel deflation. With the tunnel sealed and debris fully contained, the Al-driven system (114) logs the captured object into the onboard database, updating the mission records. The electromagnetic levitation system (108) is then gradually shut down, and both modules, now electromagnetically reattached return to their default standby configuration. This stage concludes with the system fully reset, enabling the infrared sensor grid to resume orbital scanning and initiate the next debris targeting sequence, ensuring uninterrupted, autonomous space debris removal.

[0153] Applications

[0154] The autonomous system (100) for orbital debris removal is primarily intended for active remediation of sub-10-centimetre debris in Low Earth Orbit (LEO) and beyond, where such particles pose significant risks to operational spacecraft, satellite constellations, and human missions. Designed as a modular and deployable solution, the system integrates a sensor module including infrared imagers, optical cameras, LiD AR units, radar modules, and hyperspectral sensors to scan orbital zones for untracked debris ( 102d, 104d). Upon identifying a target, the Al-based control unit (114) processes data from these sensors using onboard neural network models and trajectory computation modules (114b), enabling the system to autonomously calculate interception vectors and execute debris acquisition without ground intervention.

[0155] The spacecraft comprises two structurally separate modules: an air tank module (102) and a collector module (104), operable to maintain spacing via an electromagnetic levitation system (108). In deployment, the modules disengage and orient themselves based on real-time drift analysis of the debris. The air tank module ( 102) features a gas burst propulsion system ( 102b) used to redirect debris along a computed trajectory. A deployable connector tunnel (112), formed via inflatable or telescopic mechanisms, extends between the modules to create a sealed debris transfer channel. During capture, the Al system initiates pressurization control, assisted by an airtight shutter (104b), directing debris into the intake chamber (104a). Confirmation of ingress is obtained through internal sensors ( 104d), after which the debris is processed using an internal crushing mechanism ( 104c) or other processing methods such as pulverization or folding.

[0156] The system can be configured to accompany retired satellites to support post-mission disposal by capturing detached structural components, or deployed during constellation launches to remove inactive payloads and deployment artifacts. In such missions, the ion propulsion system (110) adjusts orbital altitude and velocity, guided by real-time data fusion from multi-spectral sensors. The gas recovery subsystem reclaims spent gases after each capture cycle, and the control logic engine in the Al unit autonomously initiates new debris removal cycles based on mission readiness and environmental conditions.

[0157] For larger-scale operations, multiple systems (100) may be deployed as a coordinated swarm, each operating independently while relaying telemetry to a central command station via encrypted uplink protocols. The system’s modular storage design within the collector module (104) allows for categorization of recovered debris, facilitating potential research or recycling post-retrieval. This multimission capability, ranging from scheduled debris clearance, emergency capture of high-risk fragments, to orbital traffic deconfliction, positions the invention as a versatile platform for sustainable orbital environment management in current and future satellite ecosystems.

[0158] Performance Parameters and Operational Estimates

[0159] The autonomous space debris removal system (100) is designed to deliver high-precision operations over long mission durations in and beyond Low Earth Orbit (LEO). At the core of its propulsion mechanism lies a high -efficiency ion propulsion system (110), which generates thrust in the range of approximately 100 to 300 millinewtons. This level of output is characteristic of microsatellite -class ion thrusters and is powered by deployable solar panels that provide a continuous power supply of about 1 to 1.5 kilowatts. The system uses gases, such as xenon or krypton, as the primary propellants, which are stored in pressurized tanks with a capacity of approximately 60 to 80 kilograms. These storage tanks support a AV budget in the range of 500 to 800 meters per second per mission, enabling a significant number of orbital manoeuvres. The ion propulsion system (110) is rated for a lifespan of 3 to 5 years, accommodating up to 10,000 start-stop cycles, ensuring longevity and operational resilience.

[0160] Table 1: Propulsion & Power Parameters

[0161] Table 2: Debris Capture & Mission Performance Estimates

[0162] In terms of debris capture and mission throughput, the system (100) is optimized to target space debris in the range of 2 to 10 centimetres in diameter, with an estimated mass of 50 to 300 grams per object, depending on the material composition. The collector module (104) is configured with an internal debris intake chamber (104a) that features a post-compaction volume capacity of approximately 2 cubic meters. The integrated mechanical crusher (104c) achieves a compression ratio between 4: 1 and 5: 1, allowing the system to accommodate a shredded debris mass of about 1,200 to 1,800 kilograms per mission. Based on an average object mass of 250 grams, the system can collect and store approximately 4,000 to 7,000 individual debris fragments over a single mission. The projected operational duration for each deployed unit of the system (100) is approximately 4.5 years. During this period, the Al-based control unit (114) orchestrates autonomous operations to complete an estimated 5,000 to 8,000 rendezvous and debris capture cycles. Depending on orbital traffic and environmental conditions, the system is capable of conducting 3 to 5 full debris engagement manoeuvres per day. Each individual engagement, comprising infrared detection via sensors and cameras (102d, 104d), trajectory computation by module (114b), realignment through the laser alignment system (106), and pressurized transfer via the ventilation and release system (102b) to enables the system to maintain a consistent and efficient pace of operations.

[0163] Under optimal conditions in high-density debris zones, the system can achieve a daily removal throughput of up to 50 objects, significantly enhancing the effectiveness of space remediation missions. The air tank module (102) includes an advanced reverse -pressure air recovery mechanism that enables approximately 500 to 700 transfer cycles per full tank. This mechanism recaptures and re -pressurizes displaced air after each debris ejection cycle, enhancing the reusability and sustainability of the system's propulsion capabilities.

[0164] Collectively, these performance parameters reflect a highly scalable and autonomous solution for longterm debris mitigation. The coordinated integration of modular components, including propulsion, alignment, compression, and Al -driven decision-making, ensures the system’s ability to function without manual intervention, even in congested and dynamic orbital environments. These estimates provide a detailed operational roadmap for deployment planning, capacity scaling, and mission cost optimization.

Claims

5. CLAIMSWe Claim1. An autonomous system (100) for the removal of sub-10-centimetre orbital debris in and beyond Low Earth Orbit (LEO), comprising: an air tank module (102) comprising: a compressed gas storage chamber (102a) adapted to store a propulsion gas; a ventilation and release system (102b) configured to control directional gas bursts; a plurality of infrared (IR) sensors and cameras (102c) configured to detect and track orbital debris in real-time; a laser-based alignment sensor (102e) configured to assist in target locking; and an electromagnetic levitation stabilizer (102d) configured to enable controlled separation from a collector module (104); the collector module (104) comprising: a debris intake chamber (104a) configured to receive debris; an airtight shutter mechanism (104b) configured to seal the chamber post-transfer; a mechanical crusher (104c) configured to compact the debris into storable fragments; and at least one IR sensor (104d) for debris capture verification; a deployable connector tunnel (112) mechanically linking the air tank module (102) and the collector module (104), the tunnel (112) being an airtight conduit for guided debris transfer via the gas burst; a laser alignment system (106) comprising a plurality of sensors (106a) and a laser guidance mechanism (106b) configured to maintain axial alignment among the air tank module (102), the connector tunnel (112), and the collector module (104); an electromagnetic levitation system (108) configured to perform module separation and controlled reattachment during debris transfer; an ion propulsion system (110) configured to perform orbital manoeuvres and match the system's velocity with target debris using inert propellants; an onboard Al-based control unit (114) comprising: an infrared image processing engine (114a) configured to classify debris based on thermal signature; a trajectory computation module (114b) configured to calculate orbital parameters including delta velocity (AV), right ascension, and declination; and a system coordination module configured to manage module separation, tunnel deployment, debris transfer, reattachment, and logging of neutralized debris.. The system (100) as claimed in claim 1, wherein the propulsion gas stored in the compressed gas storage chamber (102a) comprises an inert gas selected from nitrogen, xenon, krypton, argon, or carbon dioxide.

3. The system ( 100) as claimed in claim 1 , wherein the ventilation and release system ( 102b) comprise electronically actuated valves and pressure regulators for controlled air burst generation.

4. The system (100) as claimed in claim 1, wherein the air tank module (102) comprises a reverse - flow suction inlet and re-pressurisation mechanism configured to recover residual propulsion gas post debris capture and store it in the compressed gas storage chamber (102a) for reuse.

5. The system (100) as claimed in claim 1, wherein the reverse-flow suction inlet of the air tank module (102) includes integrated filtration and molecular sieving elements configured to remove particulates before re-pressurisation and storage in the compressed gas storage chamber (102a).

6. The system (100) as claimed in claim 1, wherein the electromagnetic levitation stabilizer (102d) maintains spatial separation of 100 to 150 cm between the air tank module (102) and the collector module (104) during debris transfer.

7. The system (100) as claimed in claim 1, wherein the airtight shutter mechanism which houses multi filter system (104b) in the collector module (104) is mechanically actuated to prevent backscatter of debris post-transfer.

8. The system (100) as claimed in claim 1, wherein the mechanical crusher (104c) is configured to achieve a debris compression ratio between 4: 1 and 5: 1 to optimize storage volume within the collector module (104).

9. The system (100) as claimed in claim 1, wherein the collector module (104) comprises multiple storage compartments configured to segregate captured debris by material type for optimized postmission processing, recycling, or secure containment.

10. The system (100) as claimed in claim 1, wherein the ion propulsion system (110) comprises a Halleffect or gridded ion thruster using xenon or krypton as the propellant.

11. The system (100) as claimed in claim 1, wherein the power source comprises deployable solar panels configured to deliver continuous power output in the range of 1 to 1.5 kilowatts for propulsion, sensing, and processing subsystems.

12. The system (100) as claimed in claim 1, wherein the deployable connector tunnel (112) includes a pressure isolation valve to prevent unintended decompression during standby operations.

13. The system (100) as claimed in claim 1, wherein the deployable connector tunnel (112) is constructed from radiation-resistant, flexible materials selected from polyimide films, aramid- reinforced laminates, or metalized polymer composites, enabling airtight integrity and mechanical durability in vacuum environments.

14. The system (100) as claimed in claim 1, wherein the deployable connector tunnel (112) is configured for accordion-folded, telescopic, or inflatable deployment modes to adapt to spatial constraints during operations.

15. The system (100) as claimed in claim 1, wherein the deployable connector tunnel (112) includes a pressure isolation valve configured to maintain vacuum integrity during standby, deployment, and retraction phases.

16. The system (100) as claimed in claim 1, wherein the Al -based control unit (114) is configured to synchronize time-tagged positional data with onboard telemetry and diagnostics.

17. The system (100) as claimed in claim 1, wherein the Al -based control unit (114) employs real-time multi-modal sensor fusion algorithms integrating data from infrared sensors, optical cameras, LiDAR units, radar modules, and hyperspectral sensors for enhanced debris detection and classification accuracy.

18. The system (100) as claimed in claim 1, wherein the reverse-flow suction inlet of the air tank module (102) includes integrated filtration and molecular sieving elements configured to remove particulates before re-pressurisation and storage in the compressed gas storage chamber (102a).

19. The system (100) as claimed in claim 1, wherein the laser alignment system (106) comprises multiple beam sources and detectors arranged circumferentially to ensure concentric axis locking across modules.

20. The system (100) as claimed in claim 1, wherein a plurality of such systems (100) are operable in a coordinated swarm configuration to enhance orbital debris removal coverage and operational efficiency.

21. A method of autonomously removing sub-10-centimeter orbital debris in Low Earth Orbit using the system (100) as claimed in claim 1, the method comprising: scanning the orbital environment using IR sensors and cameras (102c, 104d) to detect debris; computing real-time orbital parameters of the debris using the trajectory computation module (H4b); performing trajectory correction using the ion propulsion system (110) to approach the debris; deploying the connector tunnel (112) and activating the electromagnetic levitation system (108) to separate modules; aligning the modules (102, 104) and target debris using the laser alignment system (106); releasing a controlled gas burst from the ventilation system (102b) to propel debris into the collector module (104) through the tunnel (112) sealing the collector chamber (104a) using the shutter mechanism (104b) and activating the crusher (104c); retracting the tunnel (112) and reattaching the modules (102, 104); and logging the debris capture event and preparing for the next collection cycle using the control unit (114).

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