DEVICE FOR NEUTRALIZING AN ARTIFICIAL SATELLITE AND ASSOCIATED METHOD

Abstract

ARTIFICIAL SATELLITE NEUTRALIZATION DEVICE AND ASSOCIATED METHOD The invention relates to a neutralization device (100) for a target satellite (200) having a nominal operating mode said neutralization device comprising: a collision mechanism (300) configured to be able to mechanically connect said neutralization device (100) and said target satellite (200); a controllable effector (400) configured to have a passive state in which it does not alter the nominal operating mode of said target satellite (200), and an active state in which it alters the nominal operating mode of said target satellite (200); an operational information acquisition unit (500);a processing unit (600) comprising an effector control module (610) configured to be able to switch said controllable effector from said passive state to said active state and vice versa, once said docking mechanism (300) is mechanically linked to said target satellite (200), according to said operating information. Figure for the abbreviation: Figure 1;

Description

Title of the invention: DEVICE FOR NEUTRALIZING AN ARTIFICIAL SATELLITE AND ASSOCIATED METHOD Technical field of the invention

[0001] The invention relates to a device for neutralizing an artificial satellite. More particularly, the invention relates to a neutralization device intended to be carried on a space vehicle and configured to neutralize, on command, an artificial satellite, referred to as the target satellite, via a controllable effector. Technological background

[0002] The neutralization of artificial satellites is a complex field involving technological, strategic and legal considerations.

[0003] Artificial satellites have a limited lifespan due to wear and tear on their components or the depletion of their fuel supply, which is necessary to maintain their orbit. When this occurs, it is necessary to deorbit them to prevent them from becoming hazardous debris.

[0004] In the context of space conflicts or defense strategies, some countries may also seek to neutralize enemy satellites used for communication, espionage or navigation.

[0005] In the broader context of space congestion, several methods have been developed to neutralize an artificial satellite. Among these is controlled deorbiting, which involves bringing a satellite back down to Earth or transferring it to a graveyard orbit, particularly for geostationary satellites. Satellites are often equipped with propulsion systems to adjust their orbit. At the end of their life, satellites can activate a survival mode, and these systems can be used to deorbit the satellite in a controlled manner, by bringing it back into the atmosphere where it will disintegrate. The major drawback of this solution remains the inexorable production of space debris and waste.

[0006] Another approach relies on the use of space tugs. This developing technology consists of sending a satellite or spacecraft to capture a failing satellite and redirect it to a lower orbit or to a graveyard orbit.

[0007] In a military or space defense context, there are various methods for neutralizing an enemy or obsolete satellite. Among these methods is neutralization via weapon systems based on the use of anti-satellite missiles (ASATs). These missiles are launched from Earth or from a space platform to destroy a targeted satellite. This method remains controversial because it can create a large amount of dangerous space debris and contribute to the theory The Kessler syndrome states that a cloud of debris generated by each destruction pollutes several orbits. Therefore, if orbits become cluttered with too much debris, the remaining intact satellites within them will in turn be destroyed, further exacerbating orbital pollution. This can lead to an uncontrollable chain reaction.

[0008] Directed energy systems such as lasers or high-energy microwaves are also used to disrupt or disable the electronic components of a satellite without necessarily destroying it physically. Although this method of neutralization is cleaner, it remains quite experimental and energy-intensive.

[0009] In the field of neutralization, the prior art primarily provides for space debris capture systems for inactive or already defunct satellites that need to be deorbited or neutralized. These capture means are physical means based on the use of harpoons or nets for the purpose of clearing space debris. Furthermore, these means do not include controllable effectors for neutralizing or disrupting an "active" target satellite, particularly one with a military purpose.

[0010] The inventors therefore wish to propose a solution aimed at remedying the disadvantages of the prior art. Objectives of the invention

[0011] The invention aims to provide, in at least one embodiment, a neutralization device capable of identifying and attaching itself to an active target satellite and exhibiting a nominal operating mode.

[0012] The invention also aims to provide, in at least one embodiment, a device enabling the temporary or permanent alteration of the nominal operation of a target satellite.

[0013] The invention also aims to provide, in at least one embodiment, a device for temporarily or permanently reducing the performance of a target satellite.

[0014] The invention also aims to provide, in at least one embodiment, a device capable of neutralizing a target on command.

[0015] The invention also aims to provide, in at least one embodiment, a device capable of reversibly neutralizing a target.

[0016] The invention also aims to provide, in at least one embodiment, a device capable of neutralizing a target satellite, by limiting the production of space debris.

[0017] The invention also aims to provide a method for neutralizing a target satellite, said method being implemented by a neutralization device intended to be carried on a space vehicle. Description of the invention

[0018] To this end, the invention relates to a device for neutralizing an artificial satellite, referred to as the target satellite, said target satellite having at least one operating mode, referred to as the nominal mode, characterized in that said neutralization device comprises: - a boarding mechanism configured to be able to mechanically link said neutralization device and said target satellite; - a controllable effector configured to exhibit a state, called the passive state, in which it does not alter the nominal operating mode of said target satellite, and a state, called the active state, in which it alters said nominal operating mode of said target satellite; - a unit for acquiring information representative of said target satellite and the environment of said neutralization device, referred to as operational information; - a processing unit configured to process said acquired operational information, and comprising a control module, called effector control module, configured to be able to switch said controllable effector from said passive state or said active state and vice versa, once said docking mechanism is mechanically linked to said target satellite, according to said operational information.

[0019] Throughout the following text, and unless otherwise indicated, the term "nominal operating mode" refers to the normal operation of a satellite, that is, an operating mode in which the onboard avionics, the various navigation and / or computing systems function normally, in an undisturbed state. This "nominal" operating mode can also be defined in contrast to a "disturbed" or "altered" operating mode, which are equivalent terms in this application and define an operating mode in which the satellite, in particular the target satellite, is no longer able to function normally, either temporarily and / or permanently. A satellite's survival mode can therefore be considered an altered or disturbed operating mode of the satellite.

[0020] Throughout the following text, the terms "target satellite" or "target" are defined as equivalent unless otherwise indicated.

[0021] Throughout the following text, the neutralization device is an artificial satellite, preferably a CubeSat-type cubic unit (U) nanosatellite. The neutralization device according to the invention may also be a nanosatellite constructed using units of dimensions other than the cubic units (U) of CubeSat. Preferably, the neutralization device according to the invention comprises one or more cubic units (U), preferably three cubic units (3U). It is understood that said neutralization device may include one or more platforms carrying a payload, the neutralization device being capable of carrying a payload proportional to the number of cubic units (U) forming the nanosatellite.

[0022] For the purposes of this invention, the payload is defined as corresponding to all the necessary means and equipment carried on said neutralization device to accomplish a task of neutralizing and / or boarding an artificial satellite, called the target satellite.

[0023] It is understood, for the purposes of the present invention, that said neutralization device is an artificial satellite, preferably a nanosatellite, compatible with a low Earth orbit (LEO) environment and a geostationary orbit (GEO) environment.

[0024] The neutralization device according to the invention is intended to be carried on a spacecraft for release in space. Furthermore, said device can be placed into orbit using a mothership, a rocket-type launcher, or a spacecraft known to those skilled in the art and suitable for placing artificial satellites, in particular nanosatellites, into orbit.

[0025] The engagement mechanism of said neutralization device may be selected from a harpoon, staples, or a clamp, and may be driven by a source of mechanical energy such as a motor or a spring, for example, or any other means enabling the engagement mechanism to move. It may also be a reversible engagement mechanism, capable of detaching itself from the target after engagement.

[0026] According to the invention, the neutralization device advantageously makes it possible to obtain a reliable mechanical link between said device and said target satellite during the collision.

[0027] The neutralization device allows a controllable effector to be activated on command once the neutralization device is linked to the target satellite. Advantageously, the invention allows for physical tracking of the target while limiting the production of space debris during the docking.

[0028] The invention also enables the device to collect information on said target satellite and to activate it accordingly and if necessary to disrupt or alter its nominal operation, temporarily and / or permanently.

[0029] Unlike remotely usable armed means, the effector according to the invention is preferably a contact effector, requiring a boarding mechanism to establish a mechanical link between said neutralization device and said target satellite.

[0030] The effector is controllable via a control module of the processing unit.

[0031] Advantageously and according to the invention, said device further comprises a plurality of sensors, including at least one distance measurement means, configured to acquire distance data between said device and said target satellite.

[0032] Thus and according to the invention, said device makes it possible to obtain a real-time update of the measurement of the relative position between the latter and said target satellite.

[0033] It is understood that said neutralization device may include a plurality of sensors associated with guidance and / or image acquisition means to ensure its orientation in space. In this respect, and without limitation, said device may include an image acquisition camera in the visible or infrared spectrum, such as a thermal camera, radar, or a laser remote sensing system better known by the acronym LIDAR.

[0034] Advantageously and according to the invention, the operating information is information from the ground, the space vehicle, or the sensors of said neutralization device.

[0035] By information from the ground, we mean information emitted from a ground base.

[0036] Thus and according to the invention, the neutralization device includes means of communication and can be guided by several operators or operate autonomously according to the operational information captured by sensors of said neutralization device.

[0037] Advantageously and according to the invention, said processing unit further comprises an identification module, configured to identify said target satellite from said operational information.

[0038] Thus and according to the invention, the neutralization device can identify the body of the target satellite and in particular the orientation of the faces of the latter in order to identify a point of contact.

[0039] Advantageously and according to the invention, said processing unit further comprises a collision control module, configured to control the mechanical link by said collision mechanism between said neutralization device and said target satellite.

[0040] By collision control module, we mean a module designed to evaluate the status of the mechanical link between said neutralization device and said target satellite. The main role of this module is to verify several aspects, including the presence of such a mechanical link, the quality of said link, and possibly its continuous monitoring.

[0041] Regarding the presence of the mechanical link, said boarding module detects whether the link is made or not.

[0042] Regarding the quality of said connection, said boarding module evaluates whether the connection is properly executed in compliance with the required technical or safety criteria such as alignment, tightening, locking, absence of play, etc.

[0043] Regarding continuous monitoring, said boarding module may include mechanical sensors such as force or position sensors, non-destructive testing means such as ultrasound, x-rays, or vision systems known to a person skilled in the art.

[0044] Thus and according to the invention, the neutralization device benefits from a safety ensuring the reliability of the mechanical link and that the controllable effector can be used.

[0045] Advantageously and according to the invention, the docking mechanism further comprises a fastening means configured to ensure a permanent link between said neutralization device and said target satellite.

[0046] Thus and according to the invention, the neutralization device makes it possible to act as a tracer or a contact beacon, and makes it possible to operate later in time while tracking the target.

[0047] Advantageously and according to the invention, the fastening means ensuring the connection between said neutralization device and said satellite is chosen from a self-drilling anchor, an adhesive, an expanding foam, a lasso, a permanent magnet, a staple, a motorized clamp or a weld.

[0048] The adhesive may be composed of a mixture of several chemical elements, the contact of which with the target satellite by the docking mechanism accelerates the fixation time. It may also be heated or cooled by a means integrated into the docking mechanism, such as a heating element or a cryostat, upon contact between the docking mechanism and the target satellite.

[0049] The lasso can be a cable forming a loop whose diameter can be varied by a bidirectional motor to wind or unwind said cable. The attachment of the docking mechanism to the target is ensured after placing the lasso around said target satellite and winding the cable until contact is made between the neutralization device and the target satellite.

[0050] The permanent magnet can be used by the neutralization device on a ferromagnetic surface of the target satellite. This magnet can be an electromagnet enabling contact between the device and a ferromagnetic surface of said target satellite when it is powered by an electric current.

[0051] Advantageously and according to the invention, the controllable effector is chosen from a torque or vibration generator, an electrical discharge generator, an electromagnetic wave generator, a heat or cold generator, or an aerosol generator.

[0052] The controllable effector is preferably an inertia wheel equipped with an unbalanced weight, generating vibrations to disrupt the target satellite. According to this preferred embodiment, the inertia wheel can also be used by the neutralization device to orient itself before the engagement of the collision mechanism.

[0053] In another embodiment, the controllable effector makes it possible to generate electromagnetic disturbances or degradations on the communication and electromagnetic localization means of the target, in particular with an electromagnetic pulse (EMP) type means.

[0054] In another embodiment, the controllable effector includes an electrical discharge generator configured to generate electrical discharges intended to disrupt the apparatus and / or equipment of said target satellite.

[0055] In another embodiment, the effector includes an aerosol generator, in particular by spraying a substance on said target satellite in order to reduce the capacity of the solar cells possibly equipping the latter, or to obfuscate the optics and / or the means of communication of the latter.

[0056] Advantageously and according to the invention, the boarding mechanism is a harpoon.

[0057] The harpoon may include a head made of titanium, reinforced steel, or any other material known to a person skilled in the art capable of penetrating the surface of a space object. The harpoon also includes a flexible or rigid shaft connecting the head to the boarding mechanism. Furthermore, the harpoon may include a tether, rope, or connecting cable linking the harpoon to its launching system. It is understood that such a launching system is known to a person skilled in the art and that it can be arranged on a platform of the neutralization device.

[0058] Said harpoon may include an integrated retraction system to bring said neutralization device and said target satellite closer together, or to maintain tension on said harpoon to prevent loss of contact with said target satellite. Said harpoon may further include a retractable anchoring means or an expanding mechanism allowing for a better grip on the surface of said target satellite.

[0059] In a particular embodiment, said harpoon may include an injector configured to inject an expanding substance into the target and solidify the hook of said harpoon in order to prevent any retraction of said harpoon.

[0060] In another particular embodiment, the controllable effector is an electrical discharge generator integrated into said harpoon.

[0061] Advantageously and according to the invention, said device further comprises a propulsion system.

[0062] Said propulsion system may include one or more nozzles for controlling said neutralization device. Said system may also include a set of reaction wheels for directing the thrust. The propulsion system may further include a propellant engine of the rocket engine type known to those skilled in the art.

[0063] Thus and according to the invention, the neutralization device includes a propulsion system enabling it to approach as closely as possible to its target, at a distance conducive to boarding.

[0064] Advantageously and according to the invention, said device further comprises an energy production and storage system.

[0065] The energy production and storage systems that can be used in the invention can be chosen from energy storage batteries, fuel cells, solar cells, radioisotope thermoelectric generators, or thermoelectric conversion systems known to a person skilled in the art.

[0066] The invention also relates to a neutralization device characterized in whole or in part by the characteristics mentioned above and / or below.

[0067] The invention also relates to a method for neutralizing an artificial satellite, referred to as a target satellite, said target satellite having at least one nominal operating mode, said method being implemented by a neutralization device intended to be carried on board a space vehicle, said method being characterized in that it comprises the following steps: - a step El of acquiring information representative of said target satellite and of the environment of said neutralization device, called operational information; - a step E2 of processing said operational information; - an E3 stage of approaching said target satellite; - a neutralization step E4 of said target satellite, according to said operational information.

[0068] Thus and according to the invention, it is possible to provide for a control cycle of the effector between its active state and its passive state until the end of life of the neutralization device and / or said target satellite.

[0069] The E3 boarding step can be carried out by a boarding mechanism of a neutralizing device.

[0070] The neutralization step E4 can be performed on command by means of a controllable effector, between a passive state, in which it does not modify the nominal operating mode of said target satellite, and an active state in which said effector commandable alters the nominal operating mode of said target satellite, said commandable effector switching on command from said passive state to said active state and vice versa, once said docking mechanism is mechanically linked to said target satellite, according to said operating information.

[0071] Advantageously and according to the invention, the method further comprises a step El.l of identifying said target satellite.

[0072] Advantageously and according to the invention, the method further comprises a collision control step E3.1.

[0073] Thus and according to the invention, this step makes it possible to control a mechanical link that can be made by the approaching mechanism of a neutralization device.

[0074] Advantageously and according to the invention, the E4 step of commanding a controllable effector is further carried out according to the identification of said target satellite and the control of the collision.

[0075] Thus, and according to the invention, the control of the controllable effector between its active and passive state can be managed autonomously depending on the approach, and in particular the positioning of the approach mechanism on said target satellite and the securing of the mechanical link. List of figures

[0076] Other objects, features and advantages of the invention will become apparent from the following description, given by way of non-limiting example only, and which refers to the accompanying figures in which: • [Fig.1] schematically represents a neutralization device according to one embodiment of the invention. • [Fig.2] schematically represents a boarding step according to the mode of realization of [Fig.1]. • [Fig.3] schematically represents the interactions of said device neutralization and its environment according to an embodiment of the invention. • [Fig.4] schematically represents the steps of the neutralization process according to one embodiment of the invention.

[0077] Detailed description of an embodiment of the invention

[0078] In the figures, the scales and proportions are not strictly respected, for the purposes of illustration and clarity.

[0079] In the entire detailed description that follows with reference to the figures, unless otherwise indicated, each element of the neutralization device according to the invention is described as it is arranged during its use.

[0080] Identical, similar or analogous elements are designated by the same references in all figures.

[0081] With reference to [Fig. 1], [Fig. 2], and [Fig. 3], the neutralization device 100 described is a device intended to be carried on board a space vehicle 90 of the shuttle or spacecraft type, which may or may not be launched from a ground-based rocket launcher. The device 100 is a nanosatellite comprising at least one cubic unit (U), preferably three cubic units 101, 102, and 103 (3U). The unit 103 may include avionics similar or different from those and equipment similar or different from those of the other cubic units (U). In the described embodiment, the various elements of the neutralization device 100 will be those carried on board the cubic unit 103. The cubic unit 101 includes a pair of solar panels 910.

[0082] Said neutralization device 100 is placed in orbit attached to a space vehicle 90. Said space vehicle 90 places itself on a trajectory close to that of an artificial satellite, called target satellite 200 and estimates, by means of its avionics, and operational information from a ground base 80, the orbit of the target 200.

[0083] The neutralization device 100 is then separated from the space vehicle 90 and can implement its propulsion system 800 to approach the target 200 if necessary.

[0084] The device 100 includes communication means and sensors 700, including at least one rangefinder and a lidar, for measuring the target's position. Communication can be achieved using a low-power, omnidirectional radio frequency transceiver capable of transmitting and receiving operational information related to the environment of the neutralization device 100, including information relating to the target satellite 200, the spacecraft 90, or a ground base 80, as shown in Figure [Fig. 3]. More specifically, the device can receive operational information relating to the target satellite from the spacecraft, the ground base, or both.

[0085] In addition, the neutralization device includes an acquisition unit 500 configured to receive said operational information from the sensors 700 and the collision data 340. In the described embodiment, the operational information includes data from the sensors 700, data representative of the environment of said device 100, data representative of said target satellite 200 and data 340 relating to the collision mechanism.

[0086] The neutralization device 100 includes a processing unit 600 configured to process the operating information acquired by said acquisition unit 500.

[0087] The processing unit 600 includes, for example, a computing device which should be understood in a broad sense (computer, plurality of computers, virtual server on the internet, virtual server on the Cloud, virtual server on a platform, virtual server on a local infrastructure, server networks, etc.). This computing device typically includes one or more computers 640 and optionally one or more memories containing instructions for software routines used by the processing unit.

[0088] The 640 calculator is an electronic circuit designed to manipulate and / or transform data represented by electronic or physical quantities in registers of the 640 calculator and / or memories into other similar data corresponding to physical data in register memories or other types of display devices, transmission devices or storage devices.

[0089] As specific examples, the computer 640 includes hardware such as a single-core or multi-core processor (such as a central processing unit (CPU), a graphics processing unit (GPU)) and modules. The computer 102 of the described embodiment is a space computer designed and adapted to meet space standards.

[0090] The neutralization device 100 includes a collision mechanism 300 configured to mechanically link said device 100 with the target satellite 200.

[0091] The docking mechanism 300 includes a harpoon 330 configured to anchor itself to the target satellite 200. Furthermore, the docking mechanism 300 includes a fastening means 320, such as a self-drilling pin, and a control element 310 configured to trigger the docking mechanism. This control element 310 can be configured to be controlled by the processing unit 600 or by external control means for the neutralization device 100.

[0092] The docking mechanism 300 may include one or more motors used respectively for the harpoon 300 or the attachment means 320. Furthermore, the initial impact of the harpoon 330 on the target 200 allows the neutralizing device 100 to establish initial contact, while the action of the self-drilling pin of the attachment means 320 ensures the connection and fixation of the docking mechanism. Advantageously, the use of a self-drilling pin in this embodiment limits the production of space debris and secures the docking.

[0093] To ensure optimal positioning and location for the docking, the processing unit 600 also includes an identification module 620 configured to identify the target satellite 200. This module can compile and combine data from operational information and / or databases relating to to satellites and various onboard equipment and systems. Advantageously, the 620 identification module complements the 300 docking mechanism and the various 700 sensors to ensure the best docking position on the target 200.

[0094] Once the approach has been made, the processing unit can receive and process the information 340 representative of the approach mechanism 300 in order to allow the neutralization device 100 to check the proper execution of the approach and the anchoring of the attachment means 320 to the target satellite 200.

[0095] The approach carried out by the device 100 of the described embodiment is illustrated schematically in [Fig.3].

[0096] In this figure, the device 100 performs an approach and has identified the target satellite 200 according to the means described above. The processing unit 600 calculates a trajectory enabling the engagement mechanism 300 to trigger the firing of the harpoon 330 based on various parameters such as the position and speed of the target 200. Once the harpoon 330 has penetrated the target 200, a drive motor for the self-drilling pin tightens and solidifies the mechanical connection obtained between the neutralization device 100 and the target 200.

[0097] The neutralization device 100 now positioned on the target 200 can receive and communicate operational information relating to the target to a space vehicle 90, a ground base 80 or store and process said information in order to assess the success of the engagement.

[0098] The device 100 further includes a controllable effector 400 configured to have a state, called the passive state, in which it does not alter the nominal operating mode of said target satellite 200, and a state, called the active state, in which it alters said nominal operating mode of said target satellite 200. In the embodiment described and without limitation, the controllable effector 400 may be an inertia wheel including an unbalance.

[0099] The control of said controllable effector 400 is carried out by an effector control module 610 configured to be able to switch said controllable effector 400 from said passive state to said active state and vice versa, once said docking mechanism 300 is mechanically connected to said target satellite 200, according to said operating information and / or the state of said target satellite 200.

[0100] In this way, the neutralization device 100 can, on command, activate the controllable effector 400.

[0101] In addition, the device 100 can send operational information, including its telemetry, to report on an evaluation of the controllable effector 400 on the target satellite.

[0102] The device 100 can therefore alternate phases between the active state and the passive state of said controllable effector.

[0103] Fig. 4 schematically represents the steps of the neutralization process implemented by the neutralization device according to one embodiment of the invention.

[0104] The sequence of steps is represented by solid arrows. However, each of the steps E3, E3.1 and E4 can loop back with a step E2 for processing operational information so that the target device can continuously monitor the different operations performed.

Claims

Demands

1. A device (100) for neutralizing an artificial satellite, referred to as the target satellite (200), said target satellite having at least one operating mode, referred to as the nominal mode, characterized in that said neutralization device (100) comprises: • a collision mechanism (300) configured to be able to mechanically connect said neutralization device (100) and said target satellite (200); • a controllable effector (400) configured to have a state, referred to as the passive state in which it does not alter the nominal operating mode of said target satellite, and a state, referred to as the active state in which it alters said nominal operating mode of said target satellite; • an acquisition unit (500) for information representative of said target satellite and the environment of said neutralization device, referred to as operating information;• a processing unit (600) configured to process said acquired operating information, and comprising a control module, called effector control module (610), configured to be able to switch said controllable effector (400) from said passive state to said active state and vice versa, once said docking mechanism (300) is mechanically linked to said target satellite (200), according to said operating information.;

2. A device according to claim 1, characterized in that it further comprises a plurality of sensors (700), including at least one distance-measuring means, configured to acquire distance data between said device and said target satellite

3. Device according to claim 2, characterized in that the operating information is information from the ground, from a space vehicle, or from the sensors of said neutralization device (100).

4. Device according to any one of the preceding claims, characterized in that said processing unit further comprises an identification module (620), configured to identify said target satellite (200) from said operating information.

5. Device according to any one of the preceding claims characterized in that said processing unit further comprises a collision control module (630), configured to control the mechanical link made by said collision mechanism (300) between said neutralization device (100) and said target satellite (200).

6. Device according to any one of the preceding claims characterized in that the docking mechanism further comprises a fastening means (320) configured to ensure a permanent link between said neutralization device (100) and said target satellite (200).

7. Device according to claim 6, characterized in that the fastening means (320) ensuring the connection between said neutralization device (100) and said target satellite (200) is selected from a self-drilling anchor, an adhesive, an expanding foam, a lasso cable, a permanent magnet, a staple, a motorized clamp or a weld.

8. Device according to any one of the preceding claims characterized in that the controllable effector (400) is selected from a torque or vibration generator, an electrical discharge generator, an electromagnetic wave generator, a heat or cold generator, or an aerosol generator.

9. Device according to any one of the preceding claims, characterized in that the boarding mechanism (300) is a harpoon.

10. Device according to any one of the preceding claims, characterized in that it further comprises a propulsion system (800).

11. Device according to any one of the preceding claims characterized in that it further comprises a system (900) for the production and storage of energy.

12. A method for neutralizing an artificial satellite, referred to as the target satellite (200), said target satellite (200) having at least one nominal operating mode, said method being characterized in that it comprises the following steps: • a step E1 of acquiring information representative of said target satellite (200) and of the environment of said neutralization device (100), referred to as operating information; • a step E2 of processing said operating information;

13.

14.

15. • an E3 approach step of said target satellite (200); • a neutralization step E4 of said target satellite (200) in based on said operational information. Method according to claim 12, characterized in that it further comprises a step El.l of identification of said target satellite (200). Method according to claim 13, characterized in that it further comprises a 3.1 collision control step. Method according to claims 13 to 14, characterized in that the step E4 of commanding a controllable effector (400) is further carried out according to the identification of said target satellite (200) and the control of the collision.

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