Space debris deceleration system and method

Abstract

A system and method for decelerating space objects are provided. The system comprises at least one enclosure that is inflated by a medium, such as a gas, liquid, solid particles, or any mixture thereof. The enclosure can be transported to a predetermined orbital location in the path of the space object. Upon penetrating the enclosure membrane, the object passes through the medium and is thereby decelerated leading to decay of its orbit and / or disintegration thereof.

Description

PCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1SPACE DEBRIS DECELERATION SYSTEM AND METHODCROSS REFERENCE TO PRIOR APPLICATIONS

[0001] Not applicable.FIELD OF THE DESCRIPTION

[0002] The present description relates to systems and methods for removing space debris in orbit around a celestial body, in particular a planet or moon.BACKGROUND

[0003] The presence of space debris in the Earth's and other celestial bodies' orbits poses a significant danger to both manned spacecraft and unmanned satellites. Unwanted collisions with such debris, given their high relative velocities, can release an immense amount of kinetic energy, potentially causing severe damage to a space vehicle's structure and endangering the lives of crew members.

[0004] The sources of space debris include discarded boosters and their components, defunct satellites, lost instruments and parts, as well as fine particles like dust, solid rocket motor slug, and paint flakes. Additionally, numerous pieces of satellites intentionally destroyed during military exercises significantly contribute to the growing debris problem.

[0005] As the quantity of space debris continues to escalate, the likelihood of collisions among them increases, potentially triggering the phenomenon called Kessler Syndrome. This phenomenon entails a self-sustaining chain reaction where debris collisions generate more debris, leading to an exponential growth in their numbers.

[0006] To address these challenges and ensure the safety of future space flights, there is a need for a system capable of removing orbital debris and preventing the onset of Kessler Syndrome.

[0007] Several suggestions have been made to address the above-mentioned problem, such as described in US Patent Numbers, 4,936,528, 5,405,108, 8,800,933, 8,919,702, and 9,302,789. Each of these references is incorporated herein by reference in its entirety. In these examples of known method, deceleration of unwanted orbiting debris is achieved by providing a means of disrupting the trajectory of such debris such that they enter into Earth’sPCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1 orbit and allowed to disintegrate. In some of these cases, a cloud of debris is scattered in the path of the debris to cause deceleration and, thereby, orbital decay. US 9,302,789, for example, teaches the placement and maintenance of a hollow body in a geocentric orbit above the Earth, where the body is filled with a medium having a density that serves to decelerate debris passing there-through to cause orbital decay.

[0008] There still exists a need for an effective and ideally low-cost system and method capable of removing orbital debris as well as a need for a cost-effective transportation method to deliver the necessary equipment to high altitudes where the space debris can be intercepted and removed.SUMMARY OF THE DESCRIPTION

[0009] In one aspect, there is provided a system for decelerating at least one orbiting object, the system comprising:

[0010] an enclosure comprising an inflatable membrane having one or more layers;

[0011] a first medium to inflate and be contained within the enclosure, the medium providing a resistance to the travel of the orbiting object and for decelerating the object as it passes through the enclosure once inflated.

[0012] In another aspect, there is provided a method of decelerating a space object travelling in an orbital path, the method comprising:

[0013] - positioning a deceleration system in the path of the space object, the deceleration system comprising an inflatable enclosure and a means to inflate the enclosure with at least one medium;

[0014] - inflating the enclosure with the medium; and

[0015] - allowing the object to enter and pass through the enclosure, whereby the object is decelerated upon contact with the enclosure and / or the medium.BRIEF DESCRIPTION OF THE FIGURES

[0016] The features of certain embodiments will become more apparent in the following detailed description in which reference is made to the appended figures wherein:PCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1

[0017] FIG. 1 shows a method of decelerating a space object moving at high velocity using a volume with a liquid, solid, or gaseous substance, or mixture of thereof positioned on the trajectory of the object;

[0018] FIG. 2 shows a variety of shapes for a volume with a liquid, solid, or gaseous substance, or mixture of thereof used to decelerate high-velocity space objects;

[0019] FIG. 3 shows a variety of shapes for a volume with a liquid, solid, or gaseous substance, or mixture of thereof used to decelerate groups of objects moving close to each other or clouds of debris;

[0020] FIG. 4 shows a volume divided by walls or membranes into a plurality of volumes containing the same or different liquid, solid, or gaseous substances, or mixture of thereof;

[0021] FIG. 5 shows a volume with a liquid, solid, or gaseous substance, or mixture of thereof that is equipped with thrusters for position and orientation control;

[0022] FIG. 6 shows several volumes with liquid, solid, or gaseous substances, or mixture of thereof positioned sequentially on the trajectory of the moving object to perform multiple steps of deceleration of the object;

[0023] FIG. 7 shows the work sequence diagram for the orbital debris deceleration using a rocket-launched deceleration system.DETAILED DESCRIPTION

[0024] In the present description, the terms “wall” and “membrane” may be used together or in singular form. These terms will be understood to be synonymous and to be descriptive of a means of forming an enclosed volume. The walls or membranes described herein may be formed of one or more layers. In the case of multiple layers, the wall or membrane may comprise layers of different materials.

[0025] The term “launching means” may be used herein. This term will be understood to comprise any mechanism or device that is capable or adapted to transport or convey the deceleration system described herein to a predetermined altitude or orbit above the surface of a celestial body, such as the Earth.PCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1

[0026] The specific term “Earth” and the general term “celestial body” are used herein. These terms will be understood to be examples of bodies around which debris may be orbiting. While the deceleration system described herein is adapted to be used in connection with the Earth, it will be understood that such system may be used on any celestial body.

[0027] The terms “comprise”, “comprises”, “comprised” or “comprising” may be used in the present description. As used herein (including the specification and / or the claims), and unless stated otherwise, these terms are to be interpreted as open-ended terms and as specifying the presence of the stated features, integers, steps or components, but not as precluding the presence of one or more other feature, integer, step, component or a group thereof as would be apparent to persons having ordinary skill in the relevant art. Thus, the term "comprising" as used in this specification means "consisting at least in part of’. When interpreting statements in this specification that include that term, the features, prefaced by that term in each statement, all need to be present but other features can also be present. Related terms such as "comprise" and "comprised" are to be interpreted in the same manner.

[0028] The phrase “consisting essentially of’ or “consists essentially of’ will be understood as generally closed terms, with the exception of allowing inclusion of additional items, materials, components, steps, or elements, that do not materially affect the basic and novel characteristics or function of the item(s) used in connection therewith. For example, trace elements present in a composition, but not affecting the composition's nature or characteristics would be permissible if present under the “consisting essentially of’ language, even though not expressly recited in a list of items following such terminology. When using an open-ended term, such as “comprising” or “including”, it will be understood that direct support should be afforded also to “consisting essentially of’ language as well as “consisting of’ language as if stated explicitly and vice versa. In essence, use of one of these terms in the specification provides support for all of the others.

[0029] For the purposes of the present description and / or claims, and unless otherwise indicated, all numbers expressing quantities, percentages or proportions, and other numerical values used in the specification and claims, are to be understood as being modified in all instances by the term “about.” Accordingly, unless indicated to the contrary, the numerical parameters set forth herein are approximations that may vary depending upon the desired properties sought to be obtained by the present invention, inclusive of the statedPCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1 value and has the meaning including the degree of error associated with measurement of the particular quantity. The term “about” generally refers to a range of numbers that one of ordinary skill in the art would consider as a reasonable amount of deviation to the recited numeric values (i.e., having the equivalent function or result). For example, this term “about” can be construed as including a deviation of ±10 percent of the given numeric value provided such a deviation does not alter the end function or result of the value. Therefore, a value of about 1% can be construed to be a range from 0.9% to 1.1%.

[0030] The term "and / or" can mean "and" or "or".

[0031] Unless stated otherwise herein, the articles “a” and “the”, when used to identify an element, are not intended to constitute a limitation of just one and will, instead, be understood to mean “at least one” or “one or more”.

[0032] To address the need of altering the trajectory of space debris or unwanted high- velocity objects at various altitudes above Earth’s and other celestial bodies' surfaces, a system and method for deceleration are described herein. This approach aims to reduce the velocity of the space object, enabling it to change its trajectory. As a result, the object will enter a decaying orbit and subsequently either disintegrate in the atmosphere (if present) or collide with the surface of the celestial body following a ballistic or near-ballistic trajectory. Alternatively, the decelerated object may enter a lower orbit or adopt an alternative trajectory to evade potential collisions or unwanted interactions with other space objects.

[0033] According to one embodiment, the deceleration of a high-velocity object is achieved by providing a deceleration system comprised of at least one enclosure formed by a wall or membrane capable of being penetrated by the moving object. The enclosure contains a medium, which may comprise liquid, solid, or gaseous substances, or any mixtures thereof. It will be understood that the terms wall and membrane, as used in the present context, are synonymous and are intended to mean a physical barrier that serves to create the enclosure, namely a contained space comprising the medium. As discussed further herein, the membrane preferably comprises a flexible material capable of being provided in a collapsed or folded form and capable of being unfolded or deployed by inflation or by other methods upon introduction of the medium.

[0034] As noted above, the walls or membranes described herein may comprise one or more layers of the same or different materials. In one embodiment, the wall of the enclosurePCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1 may be formed of two or more layers, wherein the outer layer may comprise a harder material that offers greater physical resistance to the debris. In one embodiment, the harder, outer layer may be formed with a tile or scale material to provide the required physical strength. In this way, the outer layer of the enclosure may serve to initiate disintegration of the debris prior to entering into the medium, which would serve as a second means of disintegration. Similarly, the walls forming the sub-enclosures and / or compartments and subcompartments may also be formed of two or more layer to achieve the same purpose. It will be appreciated that with such structure, disintegration of the debris may be conducted in a series of steps.

[0035] When the system is in use, the enclosure is positioned in the trajectory or path of the moving object that is deemed to be debris and chosen for removal from orbit. Upon penetrating the walls or membranes of the enclosure, the object enters the enclosed volume containing the medium. As would be understood by persons skilled in the art, when the object moves through the medium, it experiences dynamic forces that effectively reduce its velocity. Additionally, the object may experience heating due to the drag and compression resulting from the object passing through the medium. The heating can lead to melting, burning, and / or evaporation of material from the object. The mechanical stresses resulting from dynamic forces may also lead to the disintegration of the object as it passes through the medium.

[0036] The velocity loss experienced by the object depends on both the duration and magnitude of the dynamic forces it encounters. These parameters are discussed, for example, in some of the references discussed above. For example, the duration of the object's movement through the medium depends on the object's speed and the distance it travels therethrough. As would be understood, longer distances travelled through the medium would result in greater speed reductions. The magnitude of the dynamic forces also depends on the object’s speed and the density of the medium, where higher density and higher speed lead to increased decelerating forces. Therefore, the parameters of the medium, including its composition, pressure, temperature, and density, together with the object’s velocity, shape, mass, and path within the volume, collectively determine the overall velocity reduction. Based on these parameters and using knowledge in the field of hydrodynamics, thermodynamics, and chemistry, it is possible for a person skilled in the art to accurately calculate or predict the magnitude of velocity loss. Put another way, once the energy of a moving debris object is known, it would be possible for the skilled person toPCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1 determine the size and / or composition of the enclosure that would be used to decelerate such object. As would be understood, the debris described herein would be travelling in space and, therefore, its travel would not be impeded by any atmospheric resistance. In contrast, any medium contained in the enclosure would therefore provide at least some degree of resistance to the travel of the debris, regardless of the composition of the medium, at least as a result of frictional resistance offered by the medium.

[0037] During the process of deceleration, the shock waves in the medium caused by the moving object may disintegrate the walls or membranes of the enclosure in a manner resembling an explosion. However, the acquired velocity of the resulting fragments of the enclosure, or the material forming the medium, will not be sufficient to maintain an orbit. Therefore, such fragments will descend to the celestial body shortly after the disintegration.

[0038] Using the presently described method, the moving object can be decelerated either to a velocity below orbital speed, resulting in a subsequent deorbiting, or to a predetermined velocity that enables a required trajectory change without immediate deorbiting. Such adjustment in trajectory may be needed in cases where the path of the object needs to be adjusted to avoid a collision with other objects in space or for other reasons.

[0039] In another embodiment, the present description also provides various launch means and methods for delivering the deceleration system to the required location on the trajectory of the moving space object. In one example, a ground-based, a sea-based, or an airborne launch platform equipped with an accelerator, such as a chemical gun, an electromagnetic coil gun, or a superconducting quench gun (each of which are known in the art) can be used. These means and methods can ensure that the necessary altitude above the surface of the Earth or a celestial body is reached and with sufficient accuracy so as to position the system in the path of the object's trajectory.

[0040] In an alternative approach, launching of the deceleration system may use a rocket-based system. In this instance, the system may be launched from on board a rocket that carries the system from the ground, from an offshore platform, a ship, a submarine, or an airborne platform, including an airplane, helicopter, airship, or balloon.

[0041] The deceleration system's launch can be performed either vertically or at an angle, ensuring that the tangential component of the system’s velocity remains below thePCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1 orbital speed. In this embodiment, the launch profile effectively prevents the risk of generating additional space debris from the system’s components.

[0042] Launching or deploying the deceleration system can also be done from a spacecraft. However, if the system is designed to move with an orbital velocity or higher, it should be equipped with a control means preventing it from becoming uncontrolled, and thereby itself becoming orbital debris or an undesired space object. Such control means may include but not limited to collision avoidance equipment, active propulsion system, and deorbiting mechanisms, as would be known in the art.

[0043] In one embodiment, the presently described deceleration system can be equipped with rocket engines, gas thrusters, reaction wheels, and other passive or active means to adjust its positioning in space along the object's trajectory, control speed, and maintain proper orientation before, during, and after interaction with the moving debris object(s).

[0044] During launch and positioning of the deceleration system, the aforementioned medium can be initially stored as a payload in a small package. The medium can be in a folded, compressed, liquefied, or solidified form. The medium may also be formed by a chemical reaction. In this instance, the reagents for the reaction may be initially deployed with the system in separated form. Thereafter, to form the medium, the reagents may be combined thus causing them to react and thereby generate the necessary amount of the medium to fill the enclosure to achieve deceleration of the object.

[0045] In one embodiment, to achieve and keep the properties of the medium for use at the time of interaction with the moving object, the medium, or precursor thereof, the enclosure may be formed with compartments that are formed with additional, internal walls or membranes provide within the enclosure. The internal walls or membranes of the enclosure may be constructed from materials of sufficient strength so as to be capable of containing the medium, or precursors thereof, at the required conditions until the interaction with the intended object occurs. It will be understood that the material from which the enclosure is made, and which are used for forming the optional internal walls or membranes, are designed to be strong enough to maintain the required volume(s), while allowing penetration of the object without causing the object to explosively disintegrate or ricochet off the enclosure.PCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1

[0046] Initially, before and during the launch of the deceleration system, the walls or membranes of the enclosure can be stored in a small package. At the required time, the enclosure can be deployed, unfolded, stretched, and / or expanded and filled with the medium to prepare for object deceleration.

[0047] The deployed enclosure of the deceleration system can have a simple spherical shape or an elongated shape such as a cylinder, blimp, or cigar. In one embodiment, then in an elongated shape, the enclosure can be oriented so as to position the long dimension in the moving object’s path, thereby increase the length and duration of the object's path through the medium. In another embodiment, such as when used to decelerate a group of closely spaced moving objects or a cloud of space debris, the enclosure can be designed as a flat disk-shaped structure, or a polygonal prism of the required thickness. In such cases, the enclosure would be preferably oriented so that its face is perpendicular to the trajectory of the moving objects.

[0048] As mentioned above, the enclosure of the deceleration system may in one embodiment be divided into two or more compartments, with adjacent compartments being separated by internal walls or membranes. Such compartments may or may not be in communication with each other. Additionally, in another embodiment, one or more of such compartment may be further divided into two or more sub-compartments. The internal volumes of the compartments and / or sub-compartments may be filled with the same or different medium under the same or different conditions to improve the efficiency of the system. Further, in another embodiment, the enclosure may comprise one or more mediumcontaining sub-enclosures that may be filled with the same or different media as the primary enclosure or as other sub-enclosures. These features are discussed further in the present description.

[0049] For example, the enclosure of the system may comprise multiple medium-filled compartments or sub-compartments, with each being arranged sequentially along the object's trajectory and containing the same or different medium, which may be under the same or different conditions, such as pressure and temperature. In this way, the sequential exposure of the moving object to more than one wall or membrane and / or different media, allows for a step-wise deceleration that enhances the overall efficiency of the system by improving the interaction between the moving object and the medium within each volume.PCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1

[0050] The volumes of the media in the compartments and / or sub-compartments of the enclosure of the deceleration system can be arranged freely or connected to each other in various ways to form the overall geometric configuration of the enclosure. The means for connecting include but are not limited to, various tethers, cables, spacers, struts, membranes, electric and magnetic fields, as well as surrounding shells and films.

[0051] An example of the method of deploying and using the present deceleration system for removal of space debris from the Earth’s orbit is provided below.

[0052] In a preferred embodiment, the deceleration system is provided in a compact form to facilitate transport of the system to a desired location. Once at such location, the system may be deployed to its final form. For this purpose, the enclosure of the system may be initially in the form of a folded balloon that is capable of being inflated with the medium when the desired orbital position. The medium may also be provided in a compact manner such as in the case of pressurized tanks, for gaseous media. For example, the medium may comprise a liquid nitrogen tank, a hydrogen peroxide tank, etc. The medium may also be formed by combining a gas generation material with a suitable catalyst. The system may further include one or more of a control system, a guidance system, a navigation system, a communications system, a telemetry system, a propulsion system, a parachute system, and a system for attitude and position control.

[0053] In one embodiment, the launch of the deceleration system is carried out from a sea-based launch platform, which is positioned on a body of water. The system, particularly when in the compact form as described above, may be launched as a payload aboard the first stage of a reusable commercial rocket system. The launch follows a ballistic trajectory, similar to sounding rockets, to prevent the payload from becoming space debris both in case of a successful debris interception or in case of a miss.

[0054] The first stage accelerates the payload and delivers it to a predetermined altitude. Preferably, the first stage then returns to the launch platform for a soft landing so as to be reused and not itself becoming space debris. The deceleration system continues to follow the ballistic trajectory and starts generating the medium for inflating the enclosure. In one example, the medium may be formed by catalytically generating steam and oxygen by decomposing hydrogen peroxide. The generated hot gas boils liquid nitrogen that is also provided with the system, which inflates the enclosure in its balloon form. The enclosure is deployed as required or shortly before the system reaches the predetermined point of debrisPCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1 interception, preferably at or close to the apogee of the ballistic trajectory. At the point of debris interception, the ballistic trajectory intersects the trajectory of the space debris object. An onboard guidance system provide with the deceleration system ensures that the inflated enclosure reaches the debris trajectory at the correct time for successful debris interception. It will be understood that method of placement of the deceleration system would be known to persons skilled in the art. The present description is not limited to any specific deployment means or method.

[0055] Upon penetrating membrane, the debris moves through the medium (in the present example, a gas) inside the enclosure at hypersonic speed, experiencing significant aerodynamic forces that slow down its flight. The object is also heated during travel through the medium, and may, preferably, break apart and / or fully or partly burn. After exiting the enclosure, the remnants of the space debris, now decelerated to a velocity below orbital, enter Earth’s atmosphere along a ballistic trajectory, and either completely burn up or fall to a predetermined surface location.

[0056] In one embodiment, upon penetration by the debris, the enclosure membrane may rupture due to the generation of gas shock waves, and the medium thus escapes into space and subsequently falling to Earth separately from enclosure. The deflated enclosure and the rest of the deceleration system continue to follow the ballistic trajectory entering the Earth’s atmosphere. In a preferred embodiment, the parachute system mentioned above is deployed to allow such components of the deceleration system to have a soft-landing, thereby allowing such components to be reused and preventing same from becoming itself space debris.

[0057] The system and method described herein effectively reduces the velocity of the moving object, causing it to deorbit and descend to a designated area on Earth or on the celestial body. Alternatively, the object can be put into a lower orbit, allowing for potential subsequent deceleration steps or other manipulations. The method also offers flexibility in altering the object's trajectory to achieve various objectives that do not require deorbiting, such as altitude control and collision avoidance.

[0058] The versatility of the presently described method enables its application to a wide range of objects, including multiple space debris objects moving on different trajectories with different velocities, and which are moving in tumbling and non-tumbling manner. The trajectories encompass orbits ranging from low to high altitude and beyond. The size of thePCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1 space object that can be intercepted and decelerated is determined by the capacity of the enclosure. For larger and heavier objects, multiple deceleration systems can be used by sequentially deploying them along the object's trajectory.

[0059] A further description will now be provided with reference to the accompanying figures.

[0060] FIG. 1 shows the overall concept of the high-velocity space object deceleration method according to one embodiment. The deceleration system is comprised of an enclosure 112 that, as described above, is filled with a medium, which may comprise a liquid, solid, or gaseous substance, or any mixture thereof. In use, the enclosure 112 is positioned on the trajectory path of a space object 116 above the surface 100 of the Earth or another celestial body. The enclosure 112 is strategically positioned on the trajectory of the targeted moving object 116 and at a predetermined time such that the object penetrates the wall or membrane of the enclosure 112 on one side, thus creating an entry opening 114. As the object passes through the medium within the enclosure 112, it experiences a reduction in velocity, accompanied by other effects caused by passing through the medium, such as melting, burning, and / or disintegration. Finally, the object 116, now decelerated and possibly in the early stages of disintegration, emerges from the opposite side of the enclosure 112, creating an exit opening 110 in the enclosure wall. The remaining pieces 104 and 108 of the initial object 116, having partially lost their speed, follow trajectories 102 and 106 that are different from the initial trajectory 118 due to the gravitational field of the Earth or a celestial body.

[0061] FIG. 2 shows a variety of shapes (200, 202, 204, 206) that the enclosure can have, once deployed and filled with a medium. In each case, enclosure is capable of decelerating a high-velocity space object, shown generally at 208. As can be seen, enclosure 200 features a simple spherical shape. Enclosure 202 has an elliptical blimp-like shape, aligned along the trajectory of moving object 208. Enclosure 204 exhibits a cylindrical shape and is also oriented along the trajectory of moving object 208. Enclosure 206 has an elongated cigar-like shape and is oriented along the trajectory of moving object 208 as well. As discussed above, by aligning the elongated shaped enclosures with the object's trajectory, the path through the medium is increased, resulting in enhanced velocity loss for the same amount of substance.PCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1

[0062] FIG. 3 shows other shapes (300, 304) of enclosures that can be used to decelerate a group of objects, such as shown at 302 and 306, moving closely together in space. The broken line arrows depict the trajectories of the objects before and after passing through the enclosure. Enclosure 300 features a polygonal prism having a least one flat face 301 that is positioned perpendicular to the trajectory of the group of space objects 302. Enclosure 304 on the other hand has the form of a cylinder or a disk having at least one flat face 305 that is likewise oriented perpendicular to the trajectory of the group of moving objects 306. As discussed above, and as would be appreciated by persons skilled in the art, such perpendicular orientation allows the deceleration system to act upon a group of spaced apart but grouped objects or a “cloud” of space debris.

[0063] FIG. 4 illustrates an enclosure 400 according to an embodiment of the deceleration system, wherein the enclosure 400 is filled with a first medium and further encloses a sub-enclosure 408 therewithin, which is defined by a membrane or wall 402 and which contains a second medium. The second medium contained within sub-enclosure 408 can be the same or different from the first medium that fills the enclosure 400. In one embodiment, and as illustrated in FIG. 4, the enclosure 400 may be further divided by internal walls or membranes 404 and 406 into one or more compartments such as shown at 410, 412, 414, and 416. Each of the compartments may be filled with the same or different medium. Consequently, in the embodiment illustrated in FIG. 4, as a space object 418 moves along its trajectory 420, it will encounter varying deceleration and destructive forces while traversing the compartments and / or sub-enclosures contained within the enclosure 400. As mentioned above, this sequential application of destructive forces can be further enhanced with the use of wall formed with multiple layers, wherein, in one embodiment, each layer may have different strength characteristics.

[0064] It will be understood that although FIG. 4 illustrates, for convenience, a combination of a number of embodiments, in particular one where the enclosure includes a sub-enclosure and one where the enclosure includes four sub-compartments, the description is not limited to such specific combination. It will therefore be understood that the illustrated embodiments are mutually exclusive. In other words, in some embodiments an enclosure may only be provided with one or more sub-enclosures and in other embodiments an enclosure may only be provided with one or more compartments and / or sub-compartments.PCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1

[0065] FIG. 5 shows a deceleration system comprising an enclosure 500 filled with a medium and to which is provided a motion control apparatus 502 that may comprise one or more thrusters (as illustrated), reaction wheels, or other means to control the position and / or orientation of the enclosure 500 and thereby improve its effectiveness of intercepting a space object 504 as it moves along trajectory 506. In case of a failed object interception, the motion control apparatus 502 can be used to relocate the system to the trajectory of another moving object, ensuring adaptability and continued functionality.

[0066] FIG. 6 shows a deceleration system that comprises multiple enclosures that are arranged in series. As shown, enclosures 600, 602, and 604 are arranged sequentially along the trajectory 608 of a space object 606. The enclosures can contain the same or different media, which may be under similar or different conditions, such as pressure and temperature. As discussed above, the sequential positioning of the enclosures allows for a stepwise deceleration of object 606 as it interacts with the medium contained within each enclosure as it passes there-through.

[0067] FIG. 7 shows the work sequence diagram for the orbital deceleration of space debris using a rocket-launched deceleration system. The deceleration system 730 is launched as a payload onboard a rocket booster 732 from Earth's surface 740, utilizing a ground or sea-based launch platform 734. The rocket booster 732 can be the first stage of a reusable commercial rocket system. The launch follows a ballistic trajectory similar to commonly known sounding rockets. At a predetermined time, rocket booster 724 and the payload 720, containing the decelerating system, separate. Subsequently, and according to one embodiment, rocket booster 726 initiates a boost-back burn and returns to the landing platform 738, performing a soft landing as illustrated. Upon landing the booster may be reconfigured for later use, which is depicted as booster 736.

[0068] Meanwhile, the deceleration system 720 continues along its ballistic trajectory, driven by inertia, and initiates an inflation of the enclosure as shown at 708. As described above, such inflation may be performed in a variety of ways, such as by using onboard compressed gas tanks, or by generating a gas using a chemical reaction (not illustrated). At or close to the apogee, when the vertical velocity reduces or reaches zero, the inflated enclosure 708 intersects with trajectory 714 of space debris 712. The onboard guidance system (not illustrated) of the deceleration system ensures that the enclosure 708 reaches debris trajectory 714 at the precise time for successful debris interception.PCT ApplicationCPST Ref: 42168 / 00004CPST Doc: 1387-0821 -1727.1

[0069] It will be understood that, in one embodiment, the deceleration system 720 may be placed in a given orbit and retained in a non-inflated state until needed. In other words, the system 720 will be placed in a “standby” mode in preparation for an encounter with a selected debris article or articles. In such case, inflation of the enclosure would be initiated either remotely by an operator or in an automated manner based on anticipated collision with the debris. In this embodiment, the system, in the “standby” mode, would preferably be retained with an orbital velocity, whereby it is maintained in a desired or predetermined orbit until needed for deployment. When deployment to intercept a selected debris is needed, the system may be decelerated to a suborbital velocity to ensure that its orbit decays, whereby the system, as with the decelerated debris fragments, is returned to the surface.

[0070] As described above, as the debris 712 penetrates the membrane of enclosure 708, it moves through the medium contained therein at hypersonic speed, thus experiencing substantial dynamic forces that decelerate its flight and preferably disintegrate its structure. After exiting the enclosure 708, the disintegrated parts 702 and 706 of the debris 712 travel at velocities below orbital speed and ultimately enter Earth's (or other celestial body’s) atmosphere along ballistic trajectories 700 and 704, respectively. They either completely burn up or fall into designated areas on the Earth’s surface. It will be understood that, in the case where the system is used in relation to a celestial body devoid of an atmosphere, the parts 702 and 706 would simply crash on the body’s surface.

[0071] As also illustrated in FIG. 7, the membrane of the enclosure, following penetration by the debris, ruptures due to shock waves into pieces, as shown at 718, which fall back to Earth. As discussed above, upon rupture of the enclosure membrane, the medium previously contained therein escapes into space and then fall back to Earth under gravity forces. The pieces 718 of the destroyed enclosure membrane and other components of the deceleration system 716 continue to follow their ballistic trajectory. In one embodiment, upon entering Earth's atmosphere, the deceleration system deploys a parachute 722 and the now tethered system, shown at 728, performs a soft landing on the ground or sea surface 740, thereby allowing it to be reused.

[0072] Although the above description includes reference to certain specific embodiments, various modifications thereof will be apparent to those skilled in the art. Any examples provided herein are included solely for the purpose of illustration and are not intended to be limiting in any way. Any drawings provided herein are solely for the purposePCT Application CPST Ref: 42168 / 00004 CPST Doc: 1387-0821 -1727.1 of illustrating various aspects of the description and are not intended to be drawn to scale or to be limiting in any way. The scope of the claims appended hereto should not be limited by the preferred embodiments set forth in the above description but should be given the broadest interpretation consistent with the present specification as a whole. The disclosures of all references in the present description herein are incorporated herein by reference in their entirety.

Claims

PCT Application CPST Ref: 42168 / 00004 CPST Doc: 1387-0821 -1727.1WE CLAIM:1 . A system for decelerating at least one orbiting object, the system comprising: an enclosure comprising an inflatable membrane having one or more layers; a first medium to inflate and be contained within the enclosure, the medium providing a resistance to the travel of the orbiting object and for decelerating the object as it passes through the enclosure once inflated.

2. The system of claim 1 further comprising at least one of a control system, a guidance system, a navigation system, a communications system, a telemetry system, a propulsion system, a parachute system, and a system for attitude and position control.

3. The system of claim 1 or 2, wherein the medium comprises at least one gas, at least one liquid, at least one solid, or any combination thereof.

4. The system of any one of claims 1 to 3, wherein, in its inflated form, the enclosure comprises a spherical shape, a polygonal prism-shaped, a disk shape, or an elongated shape, wherein the elongated shape comprises a cylindrical, blimp-like, or cigar-shaped form.

5. The system of any one of claims 1 to 4, wherein the enclosure comprises one or more sub-enclosures, each of the sub-enclosures comprising one or more second media, each of the second media being the same or different from each other and from the first medium.

6. The system of any one of claims 1 to 5, wherein the enclosure comprises one or more compartments, each of the compartments comprising one or more third media, each of the third media being the same or different from each other and from the first medium.

7. The system of any one of claims 1 to 6, wherein the system is adapted to be conveyed to a predetermined orbital location by a launching means.

8. A method of decelerating a space object travelling in an orbital path, the method comprising:PCT Application CPST Ref: 42168 / 00004 CPST Doc: 1387-0821 -1727.1- positioning a deceleration system in the path of the space object, the deceleration system comprising an inflatable enclosure and a means to inflate the enclosure with at least one medium;- inflating the enclosure with the medium; and- allowing the object to enter and pass through the enclosure, whereby the object is decelerated upon contact with the enclosure and / or the medium.

9. The method of claim 8, wherein deceleration of the object further comprises decaying the orbital path of the object.

10. The method of claim 8 or 9, wherein the enclosure comprises one or more subenclosures and / or one or more compartments, wherein each of the sub-enclosures and compartments comprise the same or different media.11 . The method of any one of claims 8 to 10, comprising the positioning of a further inflated enclosure in the path of the space object, to cause a sequential deceleration of the object.

12. The method of any one of claims 8 to 11 , wherein the deceleration system is launched from a surface of a celestial body by a launching means and wherein the system comprises the payload of the vehicle.

13. The method of claim 12, wherein the launching means comprises a rocket or a gun.

14. The method of claim 12 or 13, wherein the launching means deploys the deceleration system upon reaching a predetermined altitude.

15. The method of claim 14, wherein the deceleration system inflates the enclosure with the medium when the deceleration system reaches a predetermined orbital position or when the deceleration system is in a position to intercept the space object.

16. The method of claim 15, wherein the system is maneuvered into the predetermined orbital position or into the position to intercept the space object with a propulsion system.PCT Application CPST Ref: 42168 / 00004 CPST Doc: 1387-0821 -1727.

117. The method of claim 15 or 16, wherein the deceleration system is maintained with an orbital velocity and at a predetermined altitude and / or position until prior to intercepting the space object and is decelerated to a suborbital velocity after intercepting the space object.

18. The method of any one of claims 15 to 17, wherein, following collision with the space object, remaining portions of the deceleration system are returned to the surface of the celestial body.

19. The method of claim 18, wherein the return of the remaining portions of the deceleration system comprises deployment of a parachute.

20. The method of any one of claims 8 to 19, comprising placement of a plurality of deceleration systems in the path of the space object to cause sequential deceleration of the object.

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