WO2024023971A1 - Engin spatial d'élimination de débris - Google Patents

Engin spatial d'élimination de débris Download PDF

Info

Publication number
WO2024023971A1
WO2024023971A1 PCT/JP2022/028928 JP2022028928W WO2024023971A1 WO 2024023971 A1 WO2024023971 A1 WO 2024023971A1 JP 2022028928 W JP2022028928 W JP 2022028928W WO 2024023971 A1 WO2024023971 A1 WO 2024023971A1
Authority
WO
WIPO (PCT)
Prior art keywords
debris
spacecraft
launched
removal
servicing
Prior art date
Application number
PCT/JP2022/028928
Other languages
English (en)
Inventor
Junichiro Kawaguchi
Original Assignee
Patchedconics, Llc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Patchedconics, Llc filed Critical Patchedconics, Llc
Priority to PCT/JP2022/028928 priority Critical patent/WO2024023971A1/fr
Publication of WO2024023971A1 publication Critical patent/WO2024023971A1/fr

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B64G1/1078—Maintenance satellites
    • B64G1/1081—Maintenance satellites for debris removal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
    • B64G1/623—Retarding devices, e.g. retrorockets
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/646—Docking or rendezvous systems
    • B64G1/6462—Docking or rendezvous systems characterised by the means for engaging other vehicles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
    • B64G1/2227—Inflating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
    • B64G1/648—Tethers

Definitions

  • This invention is related to the spacecrafts dealing with the debris removal from the orbit they are flying, to shorten the orbital life, the decay period of them for the safe use of the low earth orbit space.
  • the contents are characterized by the words of Contactless and Multiple Space Debris Removal by Micro to Nanno Satellites.
  • the space debris problems have emerged and threatened the use of low earth orbit space owing to the increasing large number of spacecrafts launched and left.
  • servicing spacecrafts In the debris removal, a number of researches and patents have been proposed and published so far. They assume servicing spacecrafts to be built for accessing the target debris objects.
  • the servicing spacecrafts should be enough sophisticated automatically to access the target debris objects articulating the attitude and the translation motion actively and precisely with respect to the target debris objects.
  • This invention presents the idea of using one or multiple torpedo-like third body (bodies), which can be unsophisticated and disposable, in addition to the first body of the servicing spacecraft and the second body of the target debris object.
  • the third body is launched from the first body, once the first body arrives at the target debris object, from a distance farer than the size of the second body.
  • This invention presents the method and the system, in which one or multiple third body (bodies) is (are) launched from the first body.
  • This invention requests that the third body carries both a capturing device of projection type and an inflatable or extendible atmospheric drag decelerator, at the same time. And this invention solves many technical problems in the debris removal.
  • This invention enables even a micro to nano satellite to perform contactless and multiple debris removal even via a single flight.
  • the debris removal has been comprehensive subjects these decades.
  • the threat of the orbiting debris objects shall be swept away as the international regulation stipulates. Presence of orbiting debris objects is literally a threat to sharing the low earth orbit space. Besides, anti-satellite weapons may produce extraordinary debris objects and prevent the peaceful use of the region. And the debris removal sounds an immediate activity to the society.
  • Fig. 1 shows the typical scenario using a net projected from the servicing spacecraft. It utilizes the propulsion system to decelerate and deorbit the target debris object. Typical conventional scenario draws the use of the propulsion system to deorbit the target debris object.
  • the debris removal via atmospheric drag deceleration is also well known and not new. It excludes the use of propulsion system. It is represented, for instance, by inflatable ballute devices, inflated balloons and extendible membranes, etc.
  • Fig. 2 schematically shows the strategy using a ballute.
  • the servicing spacecraft accesses to the target debris object, and equips the target debris object with the ballute via an attachment if necessary.
  • the Echo satellites of NASA were built and launched as ballutes, inflated balloons, by NASA in old days, in 1960s.
  • the novelty in this invention lies in the use of one or multiple third body (bodies) that can be unsophisticated and disposable, launched from the servicing spacecraft from a distance farer then the size of the target debris object. It provides the solutions to the technical problems this invention points out as to the debris removal in this description.
  • NPTL 1 describes some current situation about the debris removal.
  • the article is titled ‘Space Junk Removal Is Not Going Smoothly.’ During the article, there is the description of: ‘Despite promising technology demonstrations, there is no one-size-fits-all solution for the growing problem of taking out the orbital trash.’
  • PTL 1 presents the use of atmospheric drag deceleration device, such as a ballute, an inflatable device.
  • PTL 1 fails to combine the use of a net projected to capture the target debris object with it. Besides, it does not look at the use of third body, a disposal device equipped with the double capabilities at the same time, which this invention claims.
  • PTL 2 relates only to the restraint schemes. This deals only with the fastener mechanism, and nothing to do with the contactless-ness feature this invention claims. This does not state anything about the use of third body equipped with a capturing device of projection type and a drag deceleration device.
  • NPTL 2 is the research on the use of a gun. It does not deal with a net projected for capturing debris objects.
  • NPTL 3 is the research on the use of a tethered net. But this does not state ‘Untethered’ scheme this invention presents. ‘Untethered’ scheme represents the net is not projected from the servicing spacecraft, the first body, but from the third body launched from the first body, as this invention claims.
  • NPTL 4 and NPTL 5 study the scenarios up to the capture by nets projected, and fail to provide the deorbiting strategy for the target debris objects.
  • NPTL 6 deals with completely different removal scheme, electromagnetic approach, which increases the complexity more and is not practical.
  • the access with the un-cooperated targets is the subject of the research area, and may not be so realistic and practical in real flight applications except the most simplified configuration, geometry or the demonstration at the laboratories.
  • the small satellites may not seem able to exhibit such performance and capability, and they are conceived not suitable for the debris removal.
  • the most expensive part of the spacecraft system is in developing the bus system comprising the attitude and orbit control and the propulsion system.
  • Current methods have to consume the bus system one by one every time one debris object is removed. This makes the removal cost high. If the servicing spacecraft carries a lot of propellant onboard, one bus system may become capable for multiple removal. However, it in turn requires further increase of the cost for removal and makes the servicing spacecraft larger and larger. Corresponding bus system becomes expensive.
  • the solution is to use of one or multiple third body (bodies) carrying both one or multiple atmospheric drag deceleration device(s) and one or multiple capturing device(s) of projection type at the same time onboard the third body (bodies), which are jettisoned and launched from the first body, the servicing spacecraft.
  • Fig. 3 schematically shows the launch of the third body toward the target debris object from the servicing spacecraft, the first body.
  • This invention solves said four major problems and presents the debris removal spacecraft system and the method, which can exhibit low cost, smallness, contactless-ness and multiple removal capabilities at the same time.
  • the third body projects one or multiple net(s) toward the target debris object to capture it.
  • the third body next starts inflation of the ballute using the inflation gas carried by the third body as in Fig. 5.
  • the sequence does not require any highly sophisticated function nor capability. Being captured by the net projected and decelerated by the ballute, the orbit of the target debris object rapidly starts shortening its orbital life.
  • the third body can be built enough small not to increase the mass and the volume of the complex to be decelerated.
  • the complex comprises the target debris object and the third body.
  • the definition of First Body and Third Body defines the third body as the spacecraft or the body that is jettisoned or launched from the servicing spacecraft, the first body.
  • the servicing spacecraft is defined as the spacecraft that approaches actively to the target debris object, once it is on orbit, regardless of whether it carries propulsion capability or not. In some cases, the servicing spacecraft may utilize the atmospheric drag to be guided to the target debris object.
  • the spacecraft released from a dispenser that actively approaches to the target debris object is regarded as the third body this invention describes. But the spacecraft released from a dispenser that does not approach actively to the target debris object is out of the third body scope this invention refers to. This invention requests that the first body must exist.
  • the present invention does not claim anything as to the configuration without use of the third body (bodies), in which the servicing spacecraft itself projects a net with its one end of the tethers mated to the servicing spacecraft itself, and also in which the servicing spacecraft itself inflates a ballute onboard.
  • the servicing spacecraft itself projects a net with its one end of the tethers mated to the servicing spacecraft itself, and also in which the servicing spacecraft itself inflates a ballute onboard.
  • Such a configuration requires a huge ballute to decelerate the target debris object together with the servicing spacecraft. It is not efficient way and is out of scope this invention claims.
  • this invention claims refers to the third body carrying both the capturing device of projection type and the deployable drag decelerator at the same time onboard.
  • the third body carries only the capturing device of projection type and it does not carry the deployable drag decelerator, such a configuration is out of scope this invention claims.
  • the third body carries only the deployable drag decelerator and does not carry the capturing device of projection type, such a configuration is also out of scope this invention claims.
  • Contactless-ness does not mean any use of laser or radio. ‘Mechanical but contactless’ opens a door to another era of sustainability for low earth orbit space. Besides, the present invention does not create new debris objects at all. Capturing devices of the projection type on the third body that is launched from the servicing spacecraft, the first body, realize the contactless-ness capturing with respect to the first body. Such a capture does not require extraordinary attitude and translation accuracy. This alleviates the high attitude and translational articulation requirement and never requests the Sophisticated capability to be on the servicing spacecraft. Besides, the servicing spacecraft can avoid the Contact Reaction force and torque. And shortening the life of the debris object utilizing the drag deceleration device excludes the significant Propellant, Fuel Consumption.
  • the method invented here should be taken for active debris removal, there is no need to have a large propulsion system onboard, and the debris removal service is provided even by micro to nano satellites. Those satellites can carry multiple third bodies, multiple projectiles and can provide debris removal services to multiple target debris objects during a single flight. Without this invention, no current solution can provide this kind of merit. This significantly reduces the debris removal cost, and even startups can launch the debris removal service.
  • the important issue is in peaceful and sustainable use of low earth orbit space. Under some circumstances, shooting enemy satellites may be anticipated about the low earth orbit space availability. Once the method and the means invented are published, any country will be aware of them. The invention will prevent any country from performing shooting the satellites ballistically, mechanically or in a destructive manner. It contributes to the sustainable use of low earth orbit space. And the method invented alleviates and removes the increase of on-orbit debris objects.
  • the world-wide debris removal business may drastically change and the existing debris removal demonstrations will be replaced with this method. This is plus to the space developing countries.
  • the debris removal service has now come into small, micro to nano satellites domain with small investment, while it may obtain global interest.
  • the present invention describes.
  • 100 Debris removal servicing spacecraft, the first body 110 Propulsion system onboard the servicing spacecraft 120 Tether connecting the net with either the servicing spacecraft, the target debris object or the third body 130 Net projected to capture the target debris object, the second body The net may be projected from either the servicing spacecraft or the third body.
  • 131 Tip mass at the end of the net to extract the net and also to close the net 140
  • Atmospheric drag deceleration device a ballute This device may be inflated during while being mated with either the servicing spacecraft, the target debris object or the third body.
  • Attachment between the ballute and the target debris object, the second body The other end of the device may be mated with either the target debris object, the third body or the net.
  • 160 Fixture, handler on the servicing spacecraft working to equip the target debris object with the attachment mated with the ballute.
  • Third body a torpedo-like projectile launched from the servicing spacecraft, carrying both one or multiple net(s), capturing device(s) of projection type and one or multiple atmospheric drag deceleration device(s) at the same time.
  • 300 Target debris object, the second body to be captured and decelerated.
  • Echo satellites had flown about 8 years starting from 1000km altitude. Referring to the Echo’s parameters, here is given an estimate of the preliminary typical ballute size for deorbiting a 100kg dry mass class satellite debris object.
  • the sphere diameter is concluded as 5m (in terms of volume it is 65.5m 3 and the cross-section area is 20m 2 )
  • the aluminized Mylar film thickness is assumed as 5 microns and results in the sphere mass of 534grams, occupying 0.4 Litter ideally. If the same liquidized gas is assumed as Echo-1, the gas mass weighs 639g. (3.57mol) Both the sphere and liquidized gas is contained well within about a 1 Litter cube.
  • a 12U-class satellite can carry two or more sets of ballute devices in one flight.
  • Fuel consumption estimate here is assumed 300 sec for Specific Impulse (Isp), in case a 100kg servicing spacecraft is assumed to deorbit a100kg dry-mass class target debris object. In reality, the mass required for the servicing spacecraft may become much heavier.
  • Isp Specific Impulse
  • the orbital decay period corresponds to the orbital life.
  • the decay period In case the conventional satellites, with the ballistic coefficient of 100(kg/m 2 ) under the solar flux F10.7 of 150SFU, when starting from the altitude of 600km, the decay period is 15 years, and the propulsive removal consumes about 11 kg or more for deorbiting. Also, when starting from the altitude of 750km, the decay period is 100 years, and the propulsive removal consumes about 17 kg or more for deorbiting.
  • the aerodynamic decay may make the spacecraft stay longer around the International Space Station (ISS) altitude. And it may sound a risk. However, in reality it is not critical. Around the ISS altitude (400 km), in a 10 km corridor around the ISS altitude, while the natural debris object stays for 1 month with the ballistic coefficient of 100 (kg/m 2 ), it is shortened only to 1.5 days with a ballute, a drag deceleration device, which lowers the ballistic coefficient down to 5 (kg/m 2 ). This assures the safety management by monitoring the debris object crossing the ISS altitude.
  • ISS International Space Station
  • the servicing spacecraft uses its own propulsion unit to approach to the target satellite. Meeting the target satellite by the servicing spacecraft is a key in the debris removal flight.
  • Typical contemporary launch vehicle can accurately inject the debris removal spacecraft, the servicing spacecraft on the specified orbit.
  • the eccentricity in other words, the altitude management of 20km requires approximately 10m/s delta-V (velocity correction amount). Compensating the typical inclination dispersion, the out of plane dispersion, of 0.1deg requests approximately 10m/s delta-V for compensation.
  • the altitude alteration of 20km controls the longitude of the ascending node almost 0.01deg/day.
  • a target debris object weighs 100kg dry mass each.
  • a typical 12U, 12 Litter class debris removal servicing spacecraft It carries two sets of torpedo-like projectiles, third bodies that occupy approximately 4U (2x2U), about 4 Litter volumes.
  • Each weigh 1.7kg consisting of 0.55kg for a ballute and 0.65kg for inflation gas as well as associated 0.5kg for the mechanics.
  • the ballute size is governed by the cross-section area of the ballute. Here, it is 5m in diameter.
  • the servicing spacecraft carries the modest cold gas thruster whose propellant is a liquidized gas.
  • the Isp assumed here is very modest and is 30sec.
  • the total mass of the 12U servicing spacecraft is about 18.5kg. The size well fits for the startups and also for the universities.
  • the spacecraft carries two sets of the net projectors, each of which weighs 1.7kg and each is contained in 1U, 1 Litter volume.
  • the spacecraft carries 3.7kg cold gas liquid propellant with 1.5kg of the mechanics associated with it. It occupies 2U, 2 Litter cubes.
  • the total mass of the spacecraft weighs 18.5kg including 6U, 6 Litter class the satellite bus system that weighs 6kg.
  • the bus system portion of 6U, 6 Litter volume includes an atmospheric drag deceleration, a ballute module that occupies 1U, 1 Litter volume, for the disposal of the servicing satellite itself.
  • the first demonstration can be performed even by a smaller 3U, 3 Litter class satellite. Despite that small size, it can carry a 2U, 2 Litter class torpedo-like projectile that is also assumed onboard the said 12U, 12 Litter debris removal servicing spacecraft in Example 2.
  • the demonstration does not need to have an artificial target debris object separately.
  • the hub 1U, 1 Litter size module may play the double roles of the servicing spacecraft and the target debris object.
  • the demonstrator itself is decelerated by the ballute and deorbits by itself. As Fig. 6 shows, the 3U, 3 Litter demonstrator separates 2U, 2 Litter size third body leaving 1U, 1 Litter size cube hub portion on orbit. The hub portion has now changed to the target virtual debris object to be captured.
  • the third body projects a net toward the hub, a dummy debris object, and capture it. Then, the third body inflates the ballute onboard. It is a very simple and affordable demonstration even the universities can perform. The demonstration does not require any propulsion system nor any fuel.
  • the drag decelerator does not have to be ballutes but can be membranes, films and kites, etc. Any deployable, inflatable or extendible device is included in and fits for the invention. Especially in terms of the gas vaporized for inflation weighs some, to a certain extent.
  • the ballute does not have to be a simple, single layered balloon, but can be multilayered for the portion to be filled with the gas or extendible with inflatable ribs to save the mass of the gas. Double layered spherical shell filled with a gas with some inflatable ribs is an example.
  • the gas that hardens quickly is also a choice.
  • the gas may be made of the material that hardens with ultra-violet ray or with temperature rise owing to the sun light.
  • the material of the balloon can be self-hardening without the gas. Any kind of drag decelerator fits for the invention.
  • any choice of the capturing devices of projection type fits for the core part of the invention. It does not have to be a net projected. Any tethers with certain hooks at the ends of them also meet the invention. Adhesives, magnets, wraps and the like fit for this invention, as long as they are projected from the third body in contactless manner, since the process is contactless with respect to the servicing spacecraft, the first body.
  • micro to nano satellites can carry multiple projectiles, third bodies and can provide debris removal service to multiple target debris objects during a single flight.
  • This invention significantly reduces the debris removal cost. Even startups can launch the debris removal service.
  • the world-wide debris removal business may drastically change and the existing debris removal demonstrations will be replaced with this method invented. This is plus to the space developing countries.
  • the debris removal service has now come into small, micro to nano satellites domain with small investment, while it may obtain global interest.
  • NPTL 1 Space Junk Net Successfully Completes Capture Test (https://www.popularmechanics.com/space/satellites/a23335998/space-junk-net-successfully-completes-capture-test/)
  • NPTL 2 Shankar Bhattarai and Jie-Rou Shang, Space Debris Removal Mechanism Using CubeSat with Gun Shot Facilities, American Journal of Applied Sciences, 2018, 15 (9): 456.463, DOI: 10.3844/ajassp.2018.456.463
  • NPTL 3 Michele Lavagna, et.

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

La partie centrale de la présente invention est l'introduction du ou des troisième corps lancé à partir de l'engin spatial d'entretien. Le troisième corps, qui peut être un dispositif non sophistiqué et jetable, doit être équipé des doubles capacités de décélération et de capture en même temps. Le troisième corps est lancé depuis une distance plus proche que la taille de l'objet débris cible. Il ne s'agit pas d'une simple combinaison de deux capacités, et peut difficilement être inspirée de manière ordinaire. La combinaison directe existante de deux capacités ne résout jamais les problèmes techniques que la présente invention surmonte, et la présente invention réalise l'élimination de débris spatiaux sans contact et multiples par des micro ou nanosatellites, qui n'ont pas été conçus jusqu'à présent.
PCT/JP2022/028928 2022-07-27 2022-07-27 Engin spatial d'élimination de débris WO2024023971A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/JP2022/028928 WO2024023971A1 (fr) 2022-07-27 2022-07-27 Engin spatial d'élimination de débris

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2022/028928 WO2024023971A1 (fr) 2022-07-27 2022-07-27 Engin spatial d'élimination de débris

Publications (1)

Publication Number Publication Date
WO2024023971A1 true WO2024023971A1 (fr) 2024-02-01

Family

ID=89705844

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2022/028928 WO2024023971A1 (fr) 2022-07-27 2022-07-27 Engin spatial d'élimination de débris

Country Status (1)

Country Link
WO (1) WO2024023971A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN118145029A (zh) * 2024-04-16 2024-06-07 南京理工大学 一种基于末端阻尼的绳网捕获装置

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6655637B1 (en) * 2002-06-24 2003-12-02 The Aerospace Corporation Spacecraft for removal of space orbital debris
US20140367523A1 (en) * 2011-11-02 2014-12-18 Ihi Aerospace Co., Ltd. Space debris removing device and space debris removing method
US20170081051A1 (en) * 2014-03-18 2017-03-23 Astroscale Japan Inc. Space device, debris removal system, and method for removing debris
US20170113818A1 (en) * 2014-09-30 2017-04-27 Ihi Corporation Debris removal device and debris removal method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6655637B1 (en) * 2002-06-24 2003-12-02 The Aerospace Corporation Spacecraft for removal of space orbital debris
US20140367523A1 (en) * 2011-11-02 2014-12-18 Ihi Aerospace Co., Ltd. Space debris removing device and space debris removing method
US20170081051A1 (en) * 2014-03-18 2017-03-23 Astroscale Japan Inc. Space device, debris removal system, and method for removing debris
US20170113818A1 (en) * 2014-09-30 2017-04-27 Ihi Corporation Debris removal device and debris removal method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
SZONDY DAVID: "ESA's potential space garbage collector nets itself a drone", 10 June 2016 (2016-06-10), XP093134441, Retrieved from the Internet <URL:https://newatlas.com/esa-drone-net-capture/43777/> *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN118145029A (zh) * 2024-04-16 2024-06-07 南京理工大学 一种基于末端阻尼的绳网捕获装置

Similar Documents

Publication Publication Date Title
Block et al. Ultralight deployable booms for solar sails and other large gossamer structures in space
WO2024023971A1 (fr) Engin spatial d&#39;élimination de débris
Lücking et al. A passive de-orbiting strategy for high altitude CubeSat missions using a deployable reflective balloon
Grundmann et al. From Sail to Soil-Getting Sailcraft out of the Harbour on a Visit to One of Earth's Nearest Neighbours
McNab Electromagnetic space launch considerations
Underwood et al. The InflateSail CubeSat mission: The first European demonstration of drag-sail de-orbiting
Lichodziejewski et al. Bringing an effective solar sail design to trl 6
Herbeck et al. Solar sail hardware developments
Reichhardt Space technology: Setting sail for history.
Lucking et al. A passive high altitude deorbiting strategy
Long Development of a passively stable pyramid sail to deorbit small satellites
Davis et al. The deployment of large de-orbit sails utilizing high strain composite booms
Davis et al. Planning for End-Of-Life Satellite Disposal; The Story of a High Strain Composite Tip-Rolled De-Orbit Sail
Firth Deployment Mechanisms for Rollable Spacecraft Booms
Johnson A Traveler's Guide to the Stars
Schillo et al. Analysis of the performance characteristics of a gossamer sail for nanosatellite applications
Starinova et al. The project of the small frame-type solar sail spacecraft
Johnson Solar sail propulsion
Macdonald Analytical methodologies for solar sail trajectory design
Herbeck Review on present solar sail hardware developments
Dooling Aerospace and military [Technology 1998 analysis and forecast]
Denny et al. Poyekhali! To Space and Back
Seedhouse Orbital Missions
van Pelt et al. To the stars
Bhattacharjee et al. A Simplified Guide To Rocket Science and Beyond--Understanding The Technologies of The Future

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 22953066

Country of ref document: EP

Kind code of ref document: A1