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WO2018154603A1 - Fils ultra-minces en tant que système d'amélioration de traînée pour engin spatial et procédé de déploiement - Google Patents

Fils ultra-minces en tant que système d'amélioration de traînée pour engin spatial et procédé de déploiement Download PDF

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Publication number
WO2018154603A1
WO2018154603A1 PCT/IN2018/050094 IN2018050094W WO2018154603A1 WO 2018154603 A1 WO2018154603 A1 WO 2018154603A1 IN 2018050094 W IN2018050094 W IN 2018050094W WO 2018154603 A1 WO2018154603 A1 WO 2018154603A1
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WIPO (PCT)
Prior art keywords
wires
tuft
drag
spacecraft
spool
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/IN2018/050094
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English (en)
Inventor
Sharanabasaweshwara ASUNDI
Aishwarya MANJUNATH
Vinod RAVI
Chaithra KRISHNARAJ
Navyata GATTU
Yashwanth AMARA
Vinod Kumar Agrawal
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PES University
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PES University
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Publication date
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Publication of WO2018154603A1 publication Critical patent/WO2018154603A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • 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
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/244—Spacecraft control systems
    • 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
    • B64G1/2229—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 deployment actuating mechanism
    • 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
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/32—Guiding or controlling apparatus, e.g. for attitude control using earth's magnetic field
    • 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
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D17/00—Parachutes
    • B64D17/62—Deployment

Definitions

  • the present subject matter relates, in general, to techniques for de-orbiting spacecraft.
  • Space debris is junk/waste fragments which orbit around the earth and has been accumulated due to human space activity. Space debris consists of fragments due to deterioration of spacecraft surfaces, used non- reusable stages of rockets, non-functional satellites, or the like.
  • spacecraft such as satellites launched in an orbit around Earth to conducts dedicated operations, such as research, data collection, surveillance, or the like have a predetermined life for which the spacecraft remains in the orbit. Once the operation has concluded, the satellite remains in their orbit thereby acting as a trash in space. In other cases, satellite may suffer malfunction or failure rendering the satellite as trash in space. In yet another case, the satellite may break down into smaller fragments resulting in accumulation of debris in space.
  • FIG. 1 illustrates a drag enhancement apparatus for a spacecraft, in accordance with an implementation of the present subject matter.
  • FIG. 2a illustrates an undeployed drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • FIG. 2b illustrates a deployed drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • FIG. 3a illustrates a schematic of the drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • FIG. 3b illustrates a spool of the drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • Fig. 3c illustrates a tuff of wires of the drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • Fig. 3d illustrates a control of the drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • Fig. 3e illustrates an electrostatic charge generator of the drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • Fig. 4 illustrates another implement of drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • Fig. 5(a)-(d) illustrates another design of the spool, in accordance with an implementation of the present subject matter.
  • FIG. 6(a)-(f) illustrates another implement of the drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • FIG. 7 illustrates yet another implement of the drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • FIG. 8(a)-(d) illustrates another type of drag enhancement apparatus installed within the spacecraft, in accordance with an implementation of the present subject matter.
  • FIG. 9(a)-(e) illustrates different designs of a drag device, in accordance with an implementation of the present subject matter.
  • Fig. 10 illustrates a method of deploying the drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • Fig. 1 1 illustrates a method of operating a lid 204 release mechanism of the drag enhancement apparatus, in accordance with an implementation of the present subject matter.
  • De-orbiting is a technique of bringing down the spacecraft from its orbit at a rate faster than a rate at which the spacecraft drops from the orbit naturally and causing the spacecraft to drop altitude. De-orbiting culminates with re-entry of the spacecraft in Earth's atmosphere causing the spacecraft to either disintegrate and burn mid-air due to atmospheric resistance or causing the spacecraft to crash into sea or ocean to prevent damages on Earth or both.
  • One technique of de-orbiting is the use of small rockets called thrusters in the spacecraft that adjusts the trajectory of the spacecraft towards Earth.
  • drag sail are not effective in de-orbiting the spacecraft orbiting in MEO since air present at those altitudes is very thin to create drag needed to de-orbit the spacecraft.
  • deployment of drag sails requires complex mechanical mechanisms that are prone to failure.
  • electrodynamic tether device that includes a long current carrying conductor extending from the spacecraft. Further, the current carrying conductor extending from the spacecraft experience forces by Earth Magnetic field thereby causing the spacecraft to change trajectory.
  • Use of electrodynamic tether requires high electric current in order to generate forces needed to change the trajectory.
  • use of electrodynamic tether does not work properly since Earth Magnetic field is not constant and vary from time to time and region to region. As a result, electrodynamic tether is less effective in de-orbiting the spacecraft.
  • the present subject matter relates to the concept of providing effective de-orbiting that provides effective deorbiting to a spacecraft in both MEO and LEO without causing substantial increase in payload of the spacecraft.
  • the concept of present subject matter makes use of a combination of aerodynamic drag and Coulomb drag to de-orbit the spacecraft.
  • the apparatus for enhancing drag for the spacecraft includes a spool and tuft of wires wound around the spool and deployable to form a drag device of predefined drag to create aerodynamic drag for the spacecraft.
  • the tuft of ultra-thin wires offers more cross sectional area for experiencing drag than that of a drag sail of equivalent mass and size. As a result, the tuft of wires achieves better aerodynamic drag than the conventional drag sail and at the same time lighter thereby adding less to the payload.
  • the apparatus also includes a control module that deploys the tuft of wires to form the drag device.
  • the control module in one example, polarizes the tuft of wires and the spool causing a mutual repulsion thereby causing the tuft of wires to deploy away from the spool. In other words, the control module induces a charge of predetermined polarity to the spool 106 and the tuft of wires. Further, the control module allows the deployment of the tuft of wires resulting from the electrostatic repulsion to form the drag device that creates aerodynamic and Coulomb drag. Since, the deployment of the tuft of wires dues to electrostatic repulsion, a need of complex deployment systems is avoided.
  • polarized drag device interacts with the plasma/ ions present in high altitudes thereby creating additional drag, commonly called as Coulomb drag.
  • Coulomb drag Such drag is effective in MEO where the concentration of plasma/ions is comparatively more than in LEO.
  • a synergistic effect of aerodynamic drag and Coulomb drag provides effective drag for the spacecraft.
  • Fig. 1 illustrates an apparatus 100 for enhancing drag for a spacecraft 102, in accordance with one implementation of the present subject matter.
  • the apparatus 100 includes a housing 104 attached to the host spacecraft 102.
  • the apparatus 100 further includes a spool 106 and a tuft of wires 108 shown in Fig. 1 in deployed state.
  • the tuft of wires includes a proximal end 108-1 which is near to the spool and a distal end opposite to the proximal end 108-2.
  • the proximal end 108-1 is connected to the spool by an anchor wire 1 10.
  • the tuft of wires 108 once deployed forms a drag device 1 12 of a predetermined shape that creates a combination of aerodynamic drag and Coulomb drag for the spacecraft 102.
  • the apparatus 100 can be employed for deorbiting spacecraft with their orbits entirely (both perigee & apogee) within 6000 km altitude range or those on elliptical/highly-eccentric orbits with their perigee lower than 6000 km altitude.
  • the apparatus 100 is deployed when the spacecraft approaches the perigee. Further, deployment of the apparatus 100 of the spacecraft 102 to descend in successive revolutions around Earth resulting in orbital decay.
  • a tail-like extension of wire can be present and also embedded within a simple flap/tag like structure as with the anchor wire 1 10.
  • the extension When in stowed state, the extension is held taut between the top flange of the spool 106 and curved plate 204-1 on the lid 204.
  • This distal flap can serve 2 purposes - (1 ) avoid slippage of drag wire windings by holding them taut and securely in position to prevent the knotting or damage of tuft of wires 108 during launch.
  • the flap gets released free and unwinding of wire tuft can happen; (2) Due to its large flat area, the tag like structure can experience better mutual repulsion force with the underlying windings around the spool barrel for a greater radially outward push. This facilitates easy initiation of unwinding and deployment of tuft of wires 108.
  • the apparatus 100 can be implemented in two ways.
  • One of the way is a 'plug-and-play' deorbiting system, shown in Fig. 1 , that can be easily integrated to the spacecraft before launch, in particular for pico-, nano- and micro-satellites, for space debris mitigation to deorbit the spacecraft 102 either after their end of operational life (EOL) as a post-mission life disposal (PMLD) system or when the spacecraft becomes defunct due to on-board systems malfunction and is achieved by deploying the tuft of wires 108.
  • EOL operational life
  • PMLD post-mission life disposal
  • the apparatus 100 module can be integrated with the spacecraft either externally or internally.
  • Another implementation is by acting as a primary payload on- board a spacecraft that has micro-propulsion capabilities like electric- propulsion, etc.
  • the dedicated spacecraft can manoeuvre on orbit while in space and can reach hazardous space debris like spent-upper-stages of rockets, defunct satellites, etc., that is already present on orbit. Further, the dedicated spacecraft is provided with a grappling mechanism to grab on to these space debris objects using its arms/claws and then deploy the apparatus 100, thereby facilitating the rapid orbit-decay of the debris.
  • the apparatus 100 for enhancing drag provides Coulomb drag when the spacecraft 102 is orbiting in lower MEOs.
  • MEOs is a region that extends from an altitude of 2000 km and above. In such regions, density of air is very less and hence, aerodynamic drag is negligible.
  • MEO is a region of plasma and highly charged particles called ions.
  • MEO also has a region called Inner Van Allen Radiation Belt (IVARB) that includes ions.
  • IVARB Inner Van Allen Radiation Belt
  • the polarized tuft of wires 108 when deployed interact with the ions.
  • the tuft of wire is polarized with a charge same as the charge of ions present in MEO.
  • the tuft of wires 108 repels with the like- charged particles of space plasma and ions in IVARB. Moreover, due to high speed of the tuft of the wires 108 travelling through the ions and the space plasma, there is a considerable amount of momentum loss of the tuft of wire thereby decelerating the spacecraft 102. As may be understood, greater density of space plasma and ion results in greater momentum loss of the tuft of wires, and in turn, of the spacecraft 102. Thus, the electrostatic resistance offered by the tuft of wire reduces the velocity of the spacecraft 102 that is travelling at orbital velocity. As the velocity drops, the spacecraft 102 starts descending from its orbit.
  • the apparatus 100 for enhancing drag provides Coulomb drag in addition to aerodynamic drag when the spacecraft 102 is orbiting in LEOs.
  • LEOs is a region that extends at an altitude of up to 2000 km from Earth surface.
  • the tuft of ultra-thin wires 108 experience drag from density of air gets thicker thereby providing aerodynamic drag to the tuft of wires 108.
  • the tuft of thin wires moves through the air, molecules in the air ram into the wires of the tuft thereby causing nanoscopic collision resulting in loss of momentum.
  • the loss of momentum further exerts a tugging (pulling) force on the spacecraft in a direction opposite to motion of the spacecraft 102. Since the tuft of wires is anchored to the spacecraft 102, the tuft of wires forces the spacecraft to decelerate gradually resulting in deorbiting of the spacecraft 102. In addition to aerodynamic drag, the ions present in LEO also provide Coulomb drag further slowing the spacecraft 102.
  • the tuft of wires 108 makes use of both aerodynamic drag and Coulomb drag to de-orbit the spacecraft. Since the tuft of wires are electrostatically charged to a high potential, the tuft of wires 108 generates Coulomb drag force by ramming into ions present in space plasma in LEOs & MEOs, which accounts to plasma braking effect. This drag is incremented by addition of aerodynamic drag produced by their cross sectional / projected area perpendicular to the spacecraft direction of motion while in orbit.
  • both the aerodynamic drag & Coulomb drag act simultaneously as a 'hybrid drag' force to deorbit the spacecraft.
  • a magnitude of both the aerodynamic drag and Coulomb drag varies with changing altitude & inclination.
  • aerodynamic drag & Coulomb drag can together cause greater orbit decay of the spacecraft in a given time than what each of them could accomplish individually & hence, results in the 'synergistic drag' effect.
  • a combination of the aerodynamic drag and Coulomb drag provides a synergistic effect for rapid de-orbiting of the spacecraft 102 thus mitigating the issue of space debris.
  • Fig 2 (a) and (b) illustrates the apparatus 100, in accordance with one implementation of the present subject matter.
  • Fig. 2 (a) illustrates the apparatus 100 in undeployed state while
  • Fig. 2(b) illustrates the apparatus 100 in a partial deployed state.
  • the apparatus includes a housing 104 that houses the spool 106 and the tuft of the wires 108.
  • the housing 104 may include a trunk 202 and a lid 204.
  • the lid 204 can be hinged to the trunk 202 with a set of torsion spring to facilitate the opening of the lid 204.
  • the apparatus also includes a lid 204 release mechanism (not shown) that allows the opening of the lid 204.
  • the lid 204 release mechanism may include, but not limited to, heat destructible wires that holds the lid 204 closed until heated by a heating device of the lid 204 release mechanism.
  • a base 206 of the trunk 202 can be attached to a chassis of the spacecraft 102 (not shown) by various means, such as, but not limited to bolts, rivets, welds, or the like.
  • the housing 104 has a cuboidal structure, the structure of the housing can be of different geometric shapes, such as cubicle, trapezoid, cylindrical, hemispherical, polygonal and can be of different sizes according to a requirement of the spacecraft 102 on to which the apparatus 100 will be mounted.
  • the housing is cylindrical, the housing can be attached by the base portion.
  • the base portion 206 also allows for electronic interfaces, such as buses and cables between the spacecraft 102 and the apparatus 100.
  • the spool 106 is connected to the base of the housing 104 by one or more compressed springs 208-1 , 208-2, 208-3, commonly referred to as 208 hereinafter.
  • the springs 208 can be helical spring.
  • the springs 208 pushes the spool 106 and the tuft of wires 108 out from the housing 104 as shown in Fig. 2(b) so that the housing 104 does not obstruct the unwinding of the tuft of wires 108.
  • the tuft of wires 108 is wound around the spool in such a manner that the tuft of wires 108 can easily unwound from the spool 106 when deployed.
  • a spring loaded telescopic boom or a shape memory alloy based boom can also be to push the spool 106 and the tuft of wires 108 out from the housing 104.
  • the apparatus 100 also includes a control module 302 (not shown in Fig) that regulates all the operations of the apparatus 100.
  • the apparatus 100 also includes an electrostatic charge generator (ECG) that, when activated, polarizes the spool 106 and the tuft of wires 108.
  • ECG electrostatic charge generator
  • the apparatus 100 includes a power system to power all the components of the apparatus.
  • the power system and the ECG can be a part of the control module 302. The structural and operational details of the control module 302 and various other details will be explained in detail with respect to Fig. 3.
  • the apparatus 100 may not include the control module 302 for polarizing the tuft of wires 108.
  • passive charging there is no dedicated ECG for electrostatic charging and the deployment happens entirely on a passive basis on the interaction of the apparatus 100 with space plasma in LEOs & MEOs, in particular, the inner Van-Allen radiation belt (IVARB).
  • IVARB inner Van-Allen radiation belt
  • the initial activation of UWDES is based on the lid-release command from either the spacecraft or the RTC on-board. Placement of solar panels in this passive UWDES variant is optional.
  • Fig. 3 a-e illustrates various components of the apparatus 100, in accordance with one implementation of the present subject matter.
  • Fig. 3(a) illustrates a schematic of the apparatus 100, in accordance with one implementation of the present subject matter.
  • the apparatus 100 broadly includes a control module 302 and the tuft of wires 108.
  • the control module 302 may also include a power system 304 that further includes power sources, such as batteries 306 and solar panels 308.
  • the solar panels 308 may be mounted on lid 204 and housing or on the spacecraft 102 or both.
  • the apparatus 100 preferably coupled to one face of the spacecraft 102 towards one corner of it to facilitate greater exposure to the Sun and to avoid any obstruction to lid 204 opening.
  • the power system 304 may also include a power regulator and distributer 310 that regulates the power from the power sources to the control module 302 and the spacecraft 102.
  • the apparatus 100 includes a timer 312 coupled to the power sources that triggers the activation of a lid 204 release mechanism 314.
  • the timer 312 is a module that operates independent from the controller 326 to facilitate the deployment of the tuft of wires 108, in case the controller 326 fails to deploy the tuft of wires 108.
  • the apparatus 100 may also include component, such as angle sensor/ gyro sensor 316 that measure an orientation of the lid 204 to monitor the opening of the lid 204.
  • control module 302 may be hermetically sealed. All the subsystems of the control module 302 can be co-located on the same board or the ECG 318 may be on a separate board to protect the other two components from charges leaked out from the ECG 318.
  • the power system 304 draws power from the solar panels 308 and supplies it to the host satellite during its mission and to the apparatus 100 after the end of life of the host satellite. In the apparatus 100, it powers the sensors and the control module 302.
  • the controller 326 receives data from all the sensors onboard the payload module and processes it and uses it for housekeeping and health monitoring purposes. Main function of controller 326 is to activate the ECG 318 based on the data from the sensors.
  • the apparatus 100 can act autonomously i.e. having self- sufficiency and can sustain by itself and operate independent of the spacecraft. Additional to the ECG 318 module, it houses a dedicated OBC board and APS (auxiliary power subsystem) card. It acts like a stand-alone plug-and-play module and does not depend on the spacecraft for power or operating commands. Further, the controller 326 along with the timer 312, can be used to activate & deploy tuft of wires 108 when there is a failure of the controller 326 of apparatus 100. The controller 326 of control module 302 can also be used to process the data received from various sensors present in the apparatus 100. The advantage of autonomous ability is that even if the spacecraft suffers with multiple subsystem failure, the apparatus 100 can still operate & perform its duty of reliably deorbiting the spacecraft 102.
  • OBC board and APS auxiliary power subsystem
  • Fig. 3(b) illustrates the spool 106 of the apparatus 100, in accordance with one implementation of the present subject matter.
  • the spool 106 is the central body of the apparatus and performs two functions. First, the spool 106 acts as a support structure 320 and hold the tuft of wires 108 securely in a wound position till the tuft of wires 108 is deployed. Second, the spool 106 facilitates the deployment of the tuft of wires 108 by acting as a gaussian surface to accumulate static charge when the spool 106 is polarized.
  • the spool 106 creates a strong electric field causing repulsion to the like-charged tuft of wires 108 thereby unwinding the tuft of wires 108.
  • the spool 106 includes a support structure 320 having an external surface -1 to support the tuft of wires 108.
  • the support structure 320 can be a hollow or solid structure.
  • the spool 106 also includes a top plate 322 mounted on top of the support structure 320 to prevent unwanted unwinding of the tuft of wires 108.
  • the top plate 322 also accumulates static charge with the support structure 320.
  • the top plate 322 can have a bi-convex shape.
  • the spool 106 also includes a base plate 324 that mounts the support structure 320 to the housing 104 (not shown in Fig).
  • the base plate 324 can be convex-o-concave surface such that a concave surface of the base plate 324 attaches to the housing 104 and the convex part mounts the support structure 320 thereon.
  • the convex portion also acts as the gaussian surface for accumulating the charges. However, the concave portion remains uncharged.
  • the base plate 324 (flange) can be a bi-convex hollow disc structure with a large central hole on a bottom face of the base plate 324 for the springs to pass through the halo & connect to the concave interior of the base plate 324.
  • the bottom flange can be larger than the top flange and also it is curved enough such that the potential build up will be greater.
  • the support structure 320 can have different shapes, such as spindle shape, hourglass shape, round plane cylinder or a cylinder made of multiple rings placed one above the other.
  • the support structure 320 can have a convex contour to provide maximum surface for accumulation of charge.
  • the support structure 320 should be large enough to reduce/ if not prevent, shape memory acquired by the tuft of wire wound around the spool 106.
  • the spool 106 may just include the support structure 320 and the bottom plate without the presence of the top plate 322.
  • either the lid 204 or the curved plate 204-1 attached to the lid 204 may act as a temporary removable top cover, that securely holds the tuft wires in position until the lid 204 opens.
  • the convex portion of the base plate 324 and the top plate 322 acts as stops for securing the tuft of wires 108 thereby preventing a need of the support structure 320.
  • the spool 106 may just include the base plate 324 such that the tuft of wires 108 may be arranged in a donut shape and the curved plate 204-1 on the lid 204 secures the tuft of wire inside the housing 104.
  • the spool 106 can be made from a variety of material, such as, but not limited to, electrically conductive metal/alloy/composite or can be made of a polymer/composite/ shape- retaining material (metal, etc.,) with a thin outer layer/coat of an electrically conductive material (metal, etc.,) or with an electroplated coating on outside which acts as a hollow metallic structure and builds electrostatic potential on its planar/convex exterior surface when polarized.
  • electrically conductive metal/alloy/composite or can be made of a polymer/composite/ shape- retaining material (metal, etc.,) with a thin outer layer/coat of an electrically conductive material (metal, etc.,) or with an electroplated coating on outside which acts as a hollow metallic structure and builds electrostatic potential on its planar/convex exterior surface when polarized.
  • the tuft of wires 108 are made of multiple strands of ultra-thin wires attached together to form a web.
  • the tuft of wires includes multiple strands of thin wires such that one end of each wire is tied together to form the proximal end 108-1 (shown in Fig. 1 ) and other end of each wire is tied to form the distal end.
  • the tuft of wire includes a single long strand of wire folded/pleated to form the web structure by clamping ends alternate ends together, thereby creating two ends with each end node comprising a set of alternate ends tied/fused together. The portion of the tuft of wires running (stretching) between the two nodes is an inter-nodal region.
  • a length of the tuft of wire can range from about 0.5 meters to about 5000 meters depending upon an amount of aerodynamic drag to be generated.
  • the tuft of wires can be made from a variety of material, such as, but not limited to Carbon fibre (T300, T800H, T800S, T1000G, Toray's MJ and M series), unsized carbon fibre, precursor PAN fibre, partially-carbonized carbon fibre, carbonized carbon fibre, partially graphitized carbon fibre, Pitch type carbon fibre, Poly-acrylo nitrile (PAN) fibre, Acrylic fibre, Glass fibre (S-glass, R-glass, D-glass, E-CR-glass, A- glass, C-glass, T-glass), fibreglass, Aramid fibre, Para-aramid fibre ( Kevlar fibre, Technora, Twaron, Heracron), Meta-aramid fibre (Nomex, Teijinconex), Innegra S, Vectran Precision wires/fibres of metal/metal alloys (copper, Be- Cu alloy
  • Nanowires and nanotubes (carbon nanotubes and others), given their extremely low thickness and moderate density, when carried on-board even in minute quantities can provide enormous drag area on deployment contributed by their maximum cumulative cross-sectional area. This allows more drag area to be generated by a given mass of payload material to be carried for, thus allowing the spacecraft 102 to experience huge drag force and hence very rapid deorbiting of spacecraft in comparison to other drag-enhancing devices of similar mass and size (form- factor) characteristics. This also facilitates smaller spacecraft (pico, nano and micro-satellites) to carry on-board drag-enhancing payloads with sizeable drag area for effective deorbiting capability.
  • the tuft of wires provides better aerodynamic drag than the conventional drag sail as the tuft of wires provides more cross-sectional area than the conventional drag sail of equivalent mass.
  • a total surface area (TSA) and MPCA of the drag sail will be 2 m 2 & 1 m 2 respectively.
  • TSA total surface area
  • MPCA both rise up to 4.23 m 2 and 1.414 m 2 respectively for the wire from the initial 2 m 2 TSA & 1 m 2 MPCA for the drag sail. From above calculations, it is understood, the long ultra-thin wire has greater TSA (1 1 1.5% rise) and MPCA (27.32% rise) than the drag sail of same thickness and similar volume.
  • the ultra-thin round-wire has a significant 27.32% increment in MPCA when drawn from a square sheet of same thickness and mass.
  • thin wires when employed as tuft of wires for drag enhancement of a spacecraft and oriented with their length normal to direction of motion of the spacecraft contribute to greater drag area (EAED) and the resultant greater aerodynamic drag effect in comparison to drag sails/gossamers having membranes of same thickness & same mass as tuft of wires and are also oriented with their plane normal to the spacecraft's direction of motion (maximum drag-generating orientation).
  • Fig. 3(d) illustrates the control module 302, in accordance with one implementation of the present subject matter.
  • the control module 302 controls all the operation of the apparatus 100.
  • the control module 302 may include a controller 326 that triggers the deployment of the tuft of the wires 108.
  • the control module 302 includes the electrostatic charge generator (ECG 318) that provides electrostatic charge to polarize the spool 106 and the tuft of wires 108.
  • the control module 302 may include the power system 304 that provides power supply to all components of the apparatus including the controller 326 and the ECG 318.
  • the power system 304 may receive power from the solar panels 308 and redirects some of the power to the spacecraft 102 when the apparatus 100 is not deployed and the power system 304 can redirect all the power to the controller 326 and the ECG 318 to polarize the tuft of wires 108 and the spool 106.
  • the operational details of the control module 302 will be explained in subsequent embodiment.
  • Fig. 3(e) illustrates a schematic of the ECG 318, in accordance with one implementation of the present subject matter.
  • the ECG 318 includes a voltage source 328 that derives power from the power system 304 to the ECG 318.
  • the ECG 318 also include a high voltage generator 330 that is coupled to an emitter 332.
  • the high voltage generator 330 receives the voltage from the voltage source 328 and steps the voltage up to sufficient high voltage for the emitter 332.
  • the emitter 332 provides charges to a collector 334 by drawing charges from a reservoir, that can be, in one example, the spool 106 and the tuft of wires 108.
  • the ECG 318 along with its supporting electronics & circuitry can be housed within a hermetically-sealed electrically-insulated case designated as ECG 318 module.
  • the tuft of wires 108 are preferably charged positive for better performance of drag device 1 12 in LEOs & MEOs that have a dominant number of positive-charged particles/ions but, can also be charged negatively, if required.
  • An electron emission device (electron gun) can be mounted externally (body-mounted) on the payload module in case of the active charging module and operated to shoot off back into space any excess charges acquired from there by the charged tuft of wires and thus, maintain the spacecraft system neutral.
  • FIG. 2 and 3 illustrates the spool 106 being deployable from the housing 104
  • another implementation of an apparatus 400 has the spool fixedly attached to the chassis of the spacecraft 102 as shown in Fig. 4.
  • a lid 204 402 may be hinged to the spacecraft to cover the apparatus 400 a housing may not be needed.
  • the lid 204 402 may include side walls 404 that provide all round cover the apparatus 400.
  • the lid 204 release mechanism 314 releases the lid 204 402 such that the lid 204 402 does not provide any obstruction in the deployment of tuft of wires 108.
  • Fig. 5 (a)-(d) illustrates an implementation of another implementation of fixed spool 500, in accordance of the present subject matter.
  • the spool 500 may include a container 502 and a support structure 504.
  • the container 502 can have funnel like structure having multiple facets 506 forming an internal surface 508 of the container 502. Further, each facet 506 has a curved profile and merges with adjacent facet to the form the internal surface 508.
  • the facets 506 acts as the gaussian surface for accumulating the charges.
  • the support structure 504 has a frustum shape having a tapered surface from bottom of the support structure to the top of the support structure.
  • the support structure 504 can be placed at a centre of the container as shown in Fig. 5 (d). Further, the support structure 504 can be solid or hollow structure an external surface 510 of the support structure can also act as the gaussian surface for accumulating the charges. In one example, the support structure 504 may be installed inside the container 502, such that a space 512 is formed between an external surface of the support structure and the internal surface of the container 502. This space 512 is used to stow the tuft of wires 108. In addition, the combination of the external surface and the internal surface of the support structure 504 and the container 502 offers more gaussian surface than the gaussian surface of the spool 106 (shown in Fig.
  • the container 502 and the support structure 504 are designed such that the support structure 504 can be detached and removed out of the container 502 for winding the tuft of wires 108 around the support structure 504 and after winding the tuft of wires, the support structure 504 along with the wound tuft of wires 108 can be placed back into the container 502 and fixed (fastened) to the centre of the container 502. Further, to prevent the slippage of tuft of wires 108, the support structure 504 has a flange towards the widest end of the tapered structure and fixed permanently thereto. On the opposite side, i.e.
  • the lid 204 of payload module is initially attached to the core during winding of the tuft of wires 108 thus, acting as a flange temporarily.
  • the lid 204 can now be hinged (coupled) to the payload module and the link between it and the support structure 504 can be removed.
  • the lid 204 stays in place holding the wound tuft of wires 108 securely in position.
  • the controller 326 activates the ECG 318 to provide electrostatic charge to the tuft of wires and the spool 500 thereby deploying the tuft of wires 108.
  • both the curved multi-faceted walls of the container 502 as well as the tapered support structure 504 act as gaussian surfaces with their convexity facing towards the stowage space of the container 502, with the electrostatic charges accumulated on the surfaces they generate an electric field directed towards this residual/stowage space, thus charging as well as mutually repelling the tuft of wires 108 stowed therein. This facilitates the deployment of tuft of wires 108 by forcing them gently out of the container 502, due to mutual-repulsion.
  • the top most coils/windings of tuft of wires 108 repel mutually and move out of the container pulling along with the subsequent coils/windings, thus gradually unwinding, unfurling and deploying the whole length of tuft of wires 108 out of the container 502 and so completing the deployment phase.
  • FIG. 6 a-f illustrates another configuration of the apparatus, in accordance with one implementation of the present subject matter.
  • Fig. 6(a) illustrates the apparatus 600 in undeployed states whereas
  • Fig. 6(b) illustrates the apparatus 600 in a semi-deployed state.
  • the spool 602 of the apparatus 600 is similar to the spool 106 shown in Fig. 2 having a support structure, a top plate and a base plate.
  • the apparatus 600 includes a tape spring 604 wound around the flanges of the spool 602.
  • one end 604-1 of the tape spring 604 is attached to the base of the housing 606 while the other end 604-2 is attached to the top of the top plate by, but not limited to, fasteners.
  • the tape spring 604 can be a double/multi-element boom having a shape memory. The whole assembly of spool 602 with both the tuft of wires 108 and the tape spring 604 wound about it is placed under tension inside the module, using a compressed ejection helical-spring similar to the springs 208 positioned at the floor of the housing and the lid 204 is closed to hold the spool and its contents securely in position.
  • Fig 7 illustrates another implementation of an apparatus 700, in accordance with one implementation of the present subject matter.
  • the apparatus 700 is mostly similar to the apparatus 600 shown in Fig.
  • the spool 702 is an elongated structure (dumbbell shaped) and is positioned horizontally in a housing 704.
  • the flanges 706 of the spool 702 are metallic/metal coated and are spherical & equal sized.
  • the spool 702 is stowed under tension by having ejection helical springs compressed against the base plate & held in position with the lid 204 closed. This helps in unobstructed deployment/ejection of the spool on the opening of lid.
  • the metallic core/barrel is spindle/cylinder shaped about which the tuft of wires are wound.
  • the tape spring 708 is wound about the spool 702 over the flanges perpendicular to the tuft of wires 108 windings.
  • the horizontal positioning of the spool 702, its elongated structure and the broader mouth of the housing 704 together makes the deployment easier.
  • FIG. 8 a-d illustrates an apparatus 800, in accordance of an implementation of the present subject matter.
  • the apparatus 800 is formed inside the spacecraft 102.
  • a lid 204 802 is also built into the spacecraft 102 and allows release of the tuft of wires 108.
  • the apparatus 800 is in undeployed state and Fig. 8(b) illustrates a state of the apparatus 800 just at the time of deployment.
  • Fig. 8(c) illustrates the tuft of wires 108 deployed from the spacecraft 102 and Fig. 5(d) illustrates the formation of the drag device 1 12.
  • Fig. 10 illustrates the operation of the different types of apparatuses.
  • Fig. 9 a-e illustrates different forms of drag devices 1 12, in accordance with one implementation of the present subject matter.
  • the drag device 1 12 can attain different shapes (configurations) which is determined based on an amount of mutual-repulsion force (due to electrostatic charging) acting on the drag device 1 12 against counter-balancing forces acting on the wires i.e. drag effect or reaction of aerodynamic & Coulomb drag & gravity gradient effect.
  • Drag device 1 12 can form into the following shapes or configurations: 1. boat, 2. spindle or pear, 3. globe/orb, 4. flower/ biconvex disc/ hub-of-spokes, 5. bunch-of-balloons.
  • Fig. 9 (a) illustrates the boat configuration of the drag device 1 12. This will be acquired when the electrostatic mutual-repulsion force between the tuft of wires is just enough to prevent their contact, but allows them to freely move around, thus behaving as a flexible structure [Fig.6(A)]. With the drag force acting gently upon it, the drag device 1 12 structure settles down into an elongated-boat shape due to the bellowing-effect caused by the drag force.
  • Fig 9 (b) illustrates the spindle configuration of the drag device 1 12. If the tuft of wires is charged further than the boat configuration, they move further apart from each other while arranging into a spindle or pear configuration that behaves like a semi-rigid entity. Most of the wires in this arrangement try to settle down in the outermost region of the spindle or pear, making it essentially into a hollow-spindle or pear-shaped drag device. In the pear configuration, if it's (spindle or pear) long-axis is nearly perpendicular to the velocity-vector of spacecraft, the drag-area contributed by drag device 1 12 is roughly 80-95% of the cumulative MPCA of tuft of wires.
  • Fig 9 (d) illustrates the globe configuration of the drag device 1 12.
  • the drag-area contributed by drag device 1 12 is around 70-85% of the cumulative cross- sectional area of tuft of wires available.
  • the drag-area projected (presented) by it will be nearly constant for a given drag device.
  • Fig 9 (e) illustrates the flower configuration of the drag device 1 12.
  • the wires On charging the wire-web to a high potential, the wires finally settle down into this flower- configuration pushing the inter-nodal regions of the tuft of wires radially outwards as far apart as possible while pulling the two nodes of the wire-web nearer.
  • the mutual-repulsion between all the tuft of wires with their adjacent ones is balanced by the mutual-repulsion between proximal and distal halves of the drag device 1 12.
  • anchor-wire acts as 'stalk' of the flower-configuration through which it is towed by the spacecraft.
  • the drag device 1 12 in flower-configuration if it is mostly flat with minimal coning and if the plane/disc of the flower-shaped wire-web is normal to the velocity vector of spacecraft, presents a drag-area that is about 80-95% of the cumulative MPCA of tuft of wires.
  • the drag area (EAED) in this case also depends on how radially outward the tuft of wires spread/bend because the more they spread radially outwards pulling the two nodes of wire-web closer, the greater will be the projected length of (both halves of) each individual drag-wire strand normal to the velocity vector of spacecraft and hence, the higher cumulative EAED of the 3D flower-shaped wire-web.
  • tuft of wires can be deployed using either a single deployable tape spring or a single long anchor wire as shown in Fig. 8(d). All these drag device 1 12s are held together like a bunch-of-balloons by anchoring (fastening) all their individual anchor-wires to the spool or to a central anchor wire.
  • Main advantage of this configuration is that, if many ultra- thin drag wire strands have to be accommodated into the drag device 1 12, as they all can't be crowded into a single drag device 1 12 that may render them ineffective, they can be distributed and placed into multiple individual drag device 1 12s that spread around evenly and thereby increasing the effectiveness of the apparatus 100.
  • the microgravity exerted by earth on the drag device 1 12 causes it to tend towards earth similar to the working of a gravity-boom used by various spacecraft.
  • the drag device 1 12 orients itself such that the anchor wire's long axis aligns mostly with the local vertical (zenith- nadir axis) in orbit. If the resultant torque due to drag force acting upon it rises, the drag device 1 12 tilts (inclines) backwards (with respect to velocity vector) away from its local vertical.
  • the amount of drag force acting upon each individual drag wire strand depends solely on the orientation of its long axis with respect to the velocity vector of the spacecraft.
  • the EAED is directly proportional to its projected length normal to the velocity vector.
  • the drag force acting on the entire drag device 112 depends on the number of tuft of wires and their projected length in the plane normal to the velocity vector of spacecraft.
  • the drag device orients such that the disc/ plane in which tuft of wires are present aligns with the plane perpendicular to the direction of motion of the spacecraft and the anchor wire aligns opposite to the velocity vector as in passive aero stabilization. With this orientation, depending upon their radially outward spread caused by the mutual-repulsion, the tuft of wires have their EAED close to their MPCA and experience the corresponding drag.
  • the tuft of wires is positively charged electrostatically and so, when moving through space plasma while on orbit, these charged tuft of wires interact with the ionospheric plasma.
  • the tuft of wires is moving at orbital velocity in LEOs, due to their high relative velocities with respect to the particle/molecules/ions present there, on collision (interaction) with these particles there will be momentum transfer between both. If charged particles like ions and electrons collide with the charged tuft of wires, these polarized tuft of wires may either gain or lose charges based on the polarity (positive or negative) of charged particles, their energies (potential) and their masses.
  • the potential of the charged tuft of wires may need to be regulated by powering on the ECG 318.
  • the drag enhancing device 1 12 deployed in upper LEOs has relatively higher EAED which is almost equal to its MPCA. Therefore, the drag enhancing device 1 12 device (apparatus 100) can be used for deorbiting spacecraft in upper LEOs with appreciable performance unlike drag-sails that require active attitude-control of spacecraft in those orbits and so are not very effective. Apparatus 100 doesn't require passive aero stabilization for optimum drag generation but, can still make use of it. The time taken for a spacecraft (with or without drag-enhancing devices) is longer to deorbit, using drag force, from 1200 km to 1000 km than from 1000 km to km. This implies a drag-enhancing device like the tuft of wires web apparatus 100 can perform reasonably well in upper low-Earth orbits is extremely beneficial to bring down the total-time taken to deorbit the spacecraft orbiting at higher altitudes.
  • apparatus 100 when coupled with the Coulomb drag, allows the apparatus 100 to deorbit spacecraft from much higher altitudes of about 1000 km - 6000 km where conventional aero drag-enhancing devices are ineffective.
  • This synergistic effect helps in bringing down the total/cumulative time-period of deorbiting, while necessitating much less mass of drag- enhancing payload material to be carried on-board.
  • apparatus 100 acts as a hybrid deorbiting system with higher efficiency than conventional deorbiting that employ only a single kind of drag force.
  • Fig. 10 illustrates a method 100 for providing navigation, in accordance with one implementation of the present subject matter.
  • the method 400 can be implemented by the apparatuses described above.
  • the exemplary method may be described in the general context of computer executable instructions embodied on a computer-readable medium.
  • computer executable instructions can include routines, programs, objects, components, data structures, procedures, modules, functions, etc., which perform particular functions or implement particular abstract data types.
  • the method may also be practiced in a distributed computing environment where functions are performed by remote processing devices that are linked through a communications network.
  • computer executable instructions may be located in both local and remote computer storage media, including memory storage devices.
  • the process begins at block 1010 by receiving a signal from the control module 302 for deploying the tuft of wires 108.
  • the signal can be a signal for the lid 204 release mechanism 314 to release the lid 204 allowing the deployment of the tuft of wires 108.
  • the signal for deployment can sent either from the spacecraft 102, or a ground based controller 326, or an autonomous function that checks if the spacecraft 102 is operational, or from the timer 312. In either condition, the control module 302 activates the lid 204 release mechanism 314 and the ECG 318 to trigger the deployment of the tuft of wires 108. Once the actuation of the ECG 318 occurs, the operation moves to the next block.
  • the tuft of wires 108 is deployed.
  • the tuft of wires 108 is deployed when the lid 204 release mechanism 314 releases the lid 204 for easy and unobstructed deployment of the tuft of wires 108.
  • the spool 106 is ejected out of the module by ejection springs and is held firmly by them at a specified distance from the spacecraft 102.
  • the lid 204 opens exposing the spool entirely following which the ECG 318 is activated.
  • the curved plate 204-1 settles at the brim of the lid 204 with help of spring attached thereto. As the curved plate 204-1 is also charged by ECG 318, the curved plate 204-1 repels mutually the like-charged tuft of wires away from the lid, thus, preventing them from coming closer to the lid. The unwinding & deployment of tuft of wires takes place on being charged by ECG 318.
  • the charges generated by the ECG 318 are transferred to the spool 16 and the tuft of wires 108 via the springs and initiate deployment of tuft of wires through the unwinding based on their mutual repulsion with the spool & the windings beneath.
  • the controller 326 actuates the power system to actuate the ECG 318.
  • the electrostatic charges are transferred to the spool 106 via the springs.
  • the charges start accumulating both on the spool and the tuft of wires 108, the charges start settling on both the spool's exterior and the tuft of wires 108.
  • the outermost winding/coil of the wires directly repels with the layer of windings immediately beneath it.
  • the outermost layers of windings together act (temporarily) as a cylindrical core/barrel of the spool and are responsible for generating the electric field necessary for the mutual repulsion based unwinding of wires instead of the support structure present beneath the innermost layer of wire windings.
  • the support structure may not hold much significance with respect to unwinding of wire tuft till the innermost layers of tuft of wires 108 start undergoing the process of unwinding & deployment.
  • an electrical contact gets established between the outer of the housing 104 (that acts as the ground of module and also as a plasma collector 334 on interaction with space plasma while in orbit) and an interior of the housing. With this, there will be transfer of excess charges from the module's frame/chassis to the interior of payload container, thus electrostatically charging the tuft of wires stowed inside the container causing their deployment.
  • Fig. 1 1 illustrates a flowchart 1 100 representing following modes of operation of releasing the lid 204 mechanism and the activating the ECG 318.
  • the spacecraft 102 sends a signal to the controller 326 of the apparatus 100 on a regular-basis at pre-defined time intervals. That time interval can be daily or weekly or monthly indicating an operational condition of the spacecraft.
  • the operational condition can be the spacecraft's health and performance & to let the controller 326 know that the spacecraft 102 is still in control. Further, the controller 326 also verifies the receipt of the feedback signal. Once the spacecraft 102 shutdowns after its functional life time or EOL- End of Life or the spacecraft 102 fails unexpectedly before EOL, the feedback signal from the spacecraft 102 stops coming indicating a failure on-board the host spacecraft.
  • the controller 326 As soon as the controller 326 detects a failure, it records the event as no-feedback period and register the same. In one example, the controller 326 is programmed to starts the countdown 'n' corresponding to the number of no-feedback. In one example, the controller 326 waits for 3 to 5 no-feedback periods (No feedback count) to determine the either the EOL or failure of the spacecraft 102. This count provides sufficient time for the debugging in case the failure can be fixed to prevent accidental loss/de-orbiting of spacecraft. Once the no feedback count reduces to zero, the controller 326 actuates the power system to activate/trigger the lid-release mechanism & to execute follow-on deployment steps.
  • Ground command based activation Another mode of activation is by sending ground signals to the spacecraft 102 indicates the deployment of the tuft of wires 108. Despite the proper functioning of spacecraft 102 in orbit in the scenarios like collision avoidance, potential system failure etc., a command can be sent from the ground control station to the spacecraft 102 which in turn instructs the controller 326 to activate/trigger the lid 204 release mechanism 314 and deploy the tuft of wires 108 for immediate deorbiting.
  • Timer 312 based activation The above mentioned two methods are either dependent on feedback or ground based command which are prone to fail due to various reasons, such as failure in feedback system or failure in telecommunication system. Therefore, a third method maybe employed that acts as a failsafe system, in case either of the above to method fails.
  • the third method employs the timer 312 positioned near the lid- release device. Prior to the launch, the timer 312 is programmed to activate the lid 204 release mechanism 314 at a predetermined time (e.g. 5yrs exactly from the moment of launch of Satellite) after the launch of the spacecraft 102.
  • the timer 312 keeps running clocking until the predetermined time as arrived and once the predetermined time comes, the timer 312 activates or gives command to the lid-release mechanism 314.
  • the timer facilitates the power supply from the solar panel directly to the lid 204 release mechanism 314 bypassing all other systems like controller 326 or the power system.
  • the timer 312 is the primary fail-safe mechanism for apparatus 100 deployment based on lid-release followed by tuft of wires 108 deployment through passive charging.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
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  • Environmental & Geological Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Automation & Control Theory (AREA)
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Abstract

La présente invention concerne un appareil (100) qui utilise une touffe de nombreux fils en tant que système d'amélioration de traînée pour engins spatiaux (102). Lorsque ces fils ultra-minces sont utilisés en grand nombre et déployés à bord d'un engin spatial, ils augmentent de manière cumulative la zone efficace subissant une traînée pour l'engin spatial en formant un dispositif de traînée (112), augmentant ainsi la force de traînée subie par l'engin spatial. Le dispositif de traînée (112) crée à la fois une traînée aérodynamique et une traînée de Coulomb, dont l'effet synergique permet une désorbitation efficace de l'engin spatial (102).
PCT/IN2018/050094 2017-02-22 2018-02-22 Fils ultra-minces en tant que système d'amélioration de traînée pour engin spatial et procédé de déploiement Ceased WO2018154603A1 (fr)

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CN109573059A (zh) * 2019-01-15 2019-04-05 中南大学 一种无人机降落伞弹射器
CN110751886A (zh) * 2019-09-18 2020-02-04 上海航天控制技术研究所 一种绳系拖曳控制地面试验验证方法及系统
CN111241634A (zh) * 2019-11-19 2020-06-05 中国空气动力研究与发展中心超高速空气动力研究所 一种航天器再入陨落的分析预报方法
CN112224448A (zh) * 2020-09-14 2021-01-15 北京空间机电研究所 一种用于空间飞行器清除的可展开锥形薄膜结构
CN114132528A (zh) * 2021-11-30 2022-03-04 北京卫星制造厂有限公司 一种柔性帆展开装置
CN114777975A (zh) * 2022-03-26 2022-07-22 苏州大学 一种用于行星探测的降落伞系统的监测及修复方法
US11585020B2 (en) * 2017-11-13 2023-02-21 Japan Aerospace Exploration Agency Net, tether storing apparatus, and manufacturing method for a net
CN115959308A (zh) * 2023-01-31 2023-04-14 北京理工大学 一种低成本电驱动的电动力绳释放装置及离轨实验装置
WO2024257235A1 (fr) * 2023-06-13 2024-12-19 株式会社Bull Dispositif de séparation d'orbite et procédé de séparation d'orbite
CN119284204A (zh) * 2024-11-28 2025-01-10 苏州三垣航天科技有限公司 一种空间离轨阻尼器
WO2025134326A1 (fr) * 2023-12-21 2025-06-26 株式会社Bull Dispositif de désorbitation et système de traitement d'informations
CN120578859A (zh) * 2025-06-11 2025-09-02 中国人民解放军军事航天部队航天工程大学 一种基于碎片与主体残骸交会时刻统计的空间解体事件时刻重构方法

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US11585020B2 (en) * 2017-11-13 2023-02-21 Japan Aerospace Exploration Agency Net, tether storing apparatus, and manufacturing method for a net
CN109573059A (zh) * 2019-01-15 2019-04-05 中南大学 一种无人机降落伞弹射器
CN109573059B (zh) * 2019-01-15 2022-03-04 中南大学 一种无人机降落伞弹射器
CN110751886A (zh) * 2019-09-18 2020-02-04 上海航天控制技术研究所 一种绳系拖曳控制地面试验验证方法及系统
CN110751886B (zh) * 2019-09-18 2021-12-07 上海航天控制技术研究所 一种绳系拖曳控制地面试验验证方法及系统
CN111241634A (zh) * 2019-11-19 2020-06-05 中国空气动力研究与发展中心超高速空气动力研究所 一种航天器再入陨落的分析预报方法
CN111241634B (zh) * 2019-11-19 2022-04-08 中国空气动力研究与发展中心超高速空气动力研究所 一种航天器再入陨落的分析预报方法
CN112224448A (zh) * 2020-09-14 2021-01-15 北京空间机电研究所 一种用于空间飞行器清除的可展开锥形薄膜结构
CN112224448B (zh) * 2020-09-14 2022-06-03 北京空间机电研究所 一种用于空间飞行器清除的可展开锥形薄膜结构
CN114132528A (zh) * 2021-11-30 2022-03-04 北京卫星制造厂有限公司 一种柔性帆展开装置
CN114132528B (zh) * 2021-11-30 2023-12-19 北京卫星制造厂有限公司 一种柔性帆展开装置
CN114777975A (zh) * 2022-03-26 2022-07-22 苏州大学 一种用于行星探测的降落伞系统的监测及修复方法
CN114777975B (zh) * 2022-03-26 2023-10-24 苏州大学 一种用于行星探测的降落伞系统的监测及修复方法
CN115959308A (zh) * 2023-01-31 2023-04-14 北京理工大学 一种低成本电驱动的电动力绳释放装置及离轨实验装置
CN115959308B (zh) * 2023-01-31 2024-03-22 北京理工大学 一种低成本电驱动的电动力绳释放装置及离轨实验装置
WO2024257235A1 (fr) * 2023-06-13 2024-12-19 株式会社Bull Dispositif de séparation d'orbite et procédé de séparation d'orbite
WO2025134326A1 (fr) * 2023-12-21 2025-06-26 株式会社Bull Dispositif de désorbitation et système de traitement d'informations
CN119284204A (zh) * 2024-11-28 2025-01-10 苏州三垣航天科技有限公司 一种空间离轨阻尼器
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