CN103587730A - Two-stage launching and unfolding method of spatial flying net - Google Patents
Two-stage launching and unfolding method of spatial flying net Download PDFInfo
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- CN103587730A CN103587730A CN201310504653.9A CN201310504653A CN103587730A CN 103587730 A CN103587730 A CN 103587730A CN 201310504653 A CN201310504653 A CN 201310504653A CN 103587730 A CN103587730 A CN 103587730A
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Abstract
The invention discloses a two-stage launching and unfolding method of a spatial flying net. A secondary launcher pushes four auxiliary pistons through a main piston, in the initial stage, the main piston pushes the auxiliary pistons to cut off a shearing pin through mechanical contact, the main piston continues to move to allow a seal ring to lose sealing effect, high-pressure fuel gas directly acts on the auxiliary pistons, each auxiliary piston pushes the corresponding connecting rod and the mass block fixedly connected with the connecting rod, so that launching of multiple mass blocks is achieved, launching synchronism of the mass blocks is achieved, launching speed is increased by utilizing the high-pressure fuel gas, and high safety is achieved. A buffer device is disposed at the bottom of the secondary launcher to lower the large recoil generated during launching of the secondary launcher. By the method, the flying net can be drawn out regularly and orderly until the net is pulled straight, the flying net can be unfolded smoothly during spatial tasks, the problem that the flying net is prone to winding, penetration and knotting during launching and unfolding is solved, and safety and reliability are increased.
Description
Technical field
The present invention relates to a kind of space and fly net unfolding method, relate in particular to a kind of space and fly net secondary transmitting method of deploying, belong to space technology field.
Background technology
Along with the development of space technology, the noncooperative targets such as space debris, discarded satellite are implemented to arrest in-orbit to become more and more important.Wherein, flying net capture technique is to study in the world more popular a kind of space technology, be mainly to utilize to fly net unfolding mechanism to a large net being compiled into by cord of target acquisition direction transmitting, after wrapping passive space vehicle, passive space vehicle regained or controlled.Utilization flies netting gear larger footprint, is beneficial to the feature that covers capture target, and flying net capture technique becomes the capturing system with certain fault-tolerant ability, has improved the safety and reliability that extraterrestrial target is arrested.Due to the expensive and high risk of space tasks, fly net capture technique and need to carry out lot of experiments checking.Owing to flying the particularity (area is large, quality is little, mesh is large etc.) of web frame, flying net is easily wound around, penetrates in expansion process and the phenomenon such as knotting in transmitting, cause to fly net and cannot launch smoothly, so need to design specific unwind so that fly Wondertek to developed area requirement.At present abroad relevantly fly net capturing system to study disclosed data few, generally also in the starting stage, but relevant support technology (if space rope is dynam, material and release control technology) has passed through space flight experiment examination.
Summary of the invention
The technical matters that the present invention solves is: overcome the deficiencies in the prior art, provide a kind of space to fly net secondary transmitting method of deploying, the method can make to fly network planning, pull out in order, guaranteeing to fly net in space tasks can launch smoothly, avoid being wound around, the problem such as knotting, improved safe reliability.
Technical scheme of the present invention is: a kind of space flies net secondary transmitting method of deploying, and step is as follows:
(1) set up space and fly net secondary transmitting expanding unit;
(2) when satellite is found after objective body, satellite Autonomous is controlled the one-level projector work in secondary transmitting expanding unit, one-level projector launches away et hold lid from et hold outlet, net bag is along with et hold lid ejects from et hold, fly net under the drive of et hold lid from net bag successively inverted order pull out, along with flying net, be drawn out, fly net and mooring line is straightened gradually;
(3) flying net and mooring line stretching moment, the secondary projector that satellite Autonomous is controlled in secondary transmitting expanding unit is started working, firing unit igniting in secondary projector, secondary projector promotes four masses according to default emission rate and the motion of transmitting subtended angle, mass is flown net and is launched from back to front and reach the state being filled by the closing in traction of restricting, and finally realizes catching objective body.
Space flies net secondary transmitting expanding unit by one-level projector, secondary projector, four masses, net bag, et hold, et hold lid, fly net, shock absorber, mooring line and the rope that closes up form, flying net is contained in net bag, net is packaged in et hold, net bag is connected with et hold lid, one-level projector is arranged on the bottom of et hold, between one-level projector and et hold lid, adopting elasticity to be connected makes et hold cap seal be contained in the outlet of et hold, net bag is connected with shock absorber by mooring line, secondary projector is arranged on shock absorber, shock absorber is fixed on satellite structure, between one-level projector and secondary projector, be fixedly connected with, four masses are arranged on secondary projector, four masses are connected with the edge that flies net by the rope that closes up respectively.
One-level projector comprises mount pad, firer's cutter, compressor arm, spring spool and release spring, mount pad is arranged on the bottom of et hold, firer's cutter is arranged between mount pad and et hold, spring spool is positioned at et hold inside center position and is connected with the bottom of et hold, release spring is arranged in spring spool, compressor arm one end is connected with mount pad through et hold lid, spring spool, firer's cutter, and the other end of compressor arm is pressed on et hold lid on et hold by nut fastener.
Secondary projector comprises firing unit, firing device, main piston, guide finger, seal ring, four minutes piston sleeves, four minutes pistons, shear pin, main piston guiding sleeve, pipe link and base, firing unit and firing device are arranged in the base of synchronized transmissions device, before the work of synchronized transmissions device, the part that master piston area is larger is arranged in base and is positioned on firing device, the part that master piston area is less is arranged in main piston guiding sleeve, between the less part of the part that master piston area is larger and area, adopt the transition of taper shoulder, guide finger is arranged on main piston guiding sleeve for carrying out spacing to the motion of main piston, the bottom of main piston is provided with four through holes for being communicated with four minutes pistons to upper when master piston motion in limited time, within four minutes, piston sleeve is distributed on the transition phase between base and main piston guiding sleeve, within four minutes, piston is arranged in four minutes piston sleeves, the bottom of four minutes pistons is all positioned on the taper shoulder of main piston, pipe link is installed at the top of four minutes pistons, pipe link is connected with a minute piston sleeve by shear pin, between main piston and base, dividing between piston and minute piston sleeve all adopts seal ring to seal.Each angle that divides between piston sleeve axis and main piston guiding sleeve axis is 20 °～55 °.
Shock absorber comprises receiver, auricle, buffering honeycomb, pressing plate, extension spring, piston and connecting panel, circular buffering honeycomb and the face of cylinder, lower end of piston are all positioned at receiver, the face of cylinder, lower end of piston and receiver are axis hole free-running fit, the upper end of pressing plate and receiver is connected and piston lower end cylinder table exponent part is pressed on buffering honeycomb, piston upper end is connected with the base of secondary projector, connecting panel is arranged on the upper end of piston, auricle is arranged on the lateral surface of receiver, and the two ends of extension spring are hung on auricle and connecting panel.
Mooring line and the rope that closes up adopt lamination coating to work out.
The present invention compared with prior art beneficial effect is:
(1) the present invention has adopted two-stage transmitting, one-level transmitting can make to fly network planning and pull out, in order until stretching, guaranteeing to fly net in space tasks can launch smoothly, has overcome in transmitting and has easily been wound around, penetrates in expansion process and the phenomenon such as knotting, has improved safe reliability;
(2) secondary transmitting of the present invention realizes the transmitting of a plurality of masses, realized the transmitting synchronism of different quality piece, realization flies to net stretching rear dictyosome and launches, secondary launching technique will fly net and pull out with expansion process and be divided into two processes, well avoid pulling out the phase mutual interference with expansion process, improved the reliability that flies net unfolding
Accompanying drawing explanation
Fig. 1 is the composition constructional drawing that space flies net secondary transmitting expanding unit;
Fig. 2 is the composition constructional drawing of one-level projector;
Fig. 3 is the profile schematic diagram of secondary projector;
Fig. 4 is the composition constructional drawing of secondary projector;
Fig. 5 is the view of secondary projector while cutting off shear pin;
Fig. 6 is the view that secondary projector master piston motion puts in place;
Fig. 7 is the composition constructional drawing of shock absorber;
Fig. 8 is that the present invention flies to net stretching process schematic diagram;
Fig. 9 is that the present invention flies net unfolding process schematic diagram.
The specific embodiment
For clearer understanding the present invention, below the present invention will be further described in detail:
As shown in Figure 1, realization of the present invention is completed by secondary transmitting expanding unit, secondary transmitting expanding unit is by one-level projector 1, secondary projector 2, four masses 3, net bag 4, et hold 5, et hold lid 6, fly net 7, shock absorber 8, mooring line 9 and the rope 10 that closes up form, flying net 7 is contained in net bag 4, net bag 4 is contained in et hold 5, net bag 4 is connected with et hold lid 6, one-level projector 1 is arranged on the bottom of et hold 5, between one-level projector 1 and et hold lid 6, adopt elasticity to be connected to make et hold to cover 6 outlets that are encapsulated in et hold 5, net bag 4 is connected with shock absorber 8 by mooring line 9, secondary projector 2 is arranged on shock absorber 8, shock absorber 8 is fixed on satellite structure, , between one-level projector 1 and secondary projector 2, be fixedly connected with, four masses 3 are arranged on secondary projector 2, four masses 3 are connected with the edge that flies net 7 by the rope 10 that closes up respectively.
The structure of one-level projector as shown in Figure 2, one-level projector 1 comprises mount pad 101, firer's cutter 102, compressor arm 103, spring spool 104 and release spring 105, mount pad 101 is arranged on the bottom of et hold 5, firer's cutter 102 is arranged between mount pad 101 and et hold 5, spring spool 104 is positioned at et hold 5 inside center positions and is connected with the bottom of et hold 5, release spring 105 is arranged in spring spool 104, compressor arm 103 one end are through et hold lid 6, spring spool 104, firer's cutter 102 is connected with mount pad 101, the other end of compressor arm 103 is pressed on et hold lid 6 on et hold 5 by nut fastener.During the work of one-level projector, firer's cutter 102 detonates and cuts off compressor arm 103, and release spring 105 discharges et hold lid 6 and compressor arm 103 are ejected, and et hold lid 6 obtains initial velocity net bag is pulled out, and realizes one-level emission function.
The structure of secondary projector is as Fig. 3, shown in 4, comprise firing unit 201, firing device 202, main piston 203, guide finger 204, seal ring 205, within four minutes, piston sleeve 206, within four minutes, piston 207, shear pin 208, main piston guiding sleeve 209, pipe link 210 and base 211, firing unit 201 and firing device 202 are arranged in the base 211 of synchronized transmissions device, before the work of synchronized transmissions device, the part that main piston 203 areas are larger is arranged in base 211 and is positioned on firing device 202, the part that main piston 203 areas are less is arranged in main piston guiding sleeve 209, between the less part of the part that main piston 203 areas are larger and area, adopt the transition of taper shoulder, guide finger 204 is arranged on main piston guiding sleeve 209 for carrying out spacing to the motion of main piston 203, the bottom of main piston 203 is provided with four through holes for moving in limited time and be communicated with four minutes pistons 207 when main piston 203, within four minutes, piston sleeve 206 is distributed on the transition phase between base 211 and main piston guiding sleeve 209, within four minutes, piston 207 is arranged in four minutes piston sleeves 206, the bottom of four minutes pistons 207 is all positioned on the taper shoulder of main piston 203, pipe link 210 is installed at the top of four minutes pistons 207, pipe link 210 is connected with a minute piston sleeve 206 by shear pin 208, between main piston 203 and base 211, dividing between piston 207 and minute piston sleeve 206 all adopts seal ring 205 to seal.Each angle that divides between piston sleeve 206 axis and main piston guiding sleeve 209 axis is 20 °～55 °, in practical application, within each minute, piston sleeve 206 axis can be adjusted according to the different of engagement range requirement from the emission angle between main piston guiding sleeve 209 axis within the scope of this.The mount pad 101 of one-level projector is installed on main piston guiding sleeve 209.
When space flies to net stretching moment, firing unit 201(implements in parallel triggering according to flying to net stretching distance and deployment time) igniting, firing device 202 produces high-pressure gas after getting angry, promote main piston 203 at base 211 and the interior upward movement of main piston guide sleeve 209,204 minutes pistons 207 of the synchronous promotion of taper shoulder of main piston 203 are at minute interior upward movement of piston sleeve 206, as shown in Figure 5, divide piston 207 upward movements to cut off shear pin 208; Main piston 203 continues motion makes seal ring 205 depart from sealing surface, high-pressure gas acts directly on minute piston 207 by four through holes of main piston 203 bottoms, as shown in Figure 6, high-pressure gas promotes minute piston 207 and hightails minute piston sleeve 206 with certain speed promotion pipe link 210, and the mass being arranged on pipe link 210 is launched away.The present invention divides the stroke of piston and the explosive load of firing device can realize different mass emission rates by appropriate design, by appropriate design emission angle, can adapt to the demand that certain size space flies the different engagement ranges of net.
The structure of shock absorber as shown in Figure 7, comprises receiver 801, auricle 802, buffering honeycomb 803, pressing plate 804, extension spring 805, piston 806, connecting panel 807.Circular buffering honeycomb 803 and piston 806 faces of cylinder, lower end are all in receiver 801, piston 806 faces of cylinder, lower end and receiver 801 are axis hole free-running fit, pressing plate 804 is connected with receiver 801, and piston 806 lower end cylinder table exponent parts are pressed on buffering honeycomb 803, piston 806 upper ends are connected with projector base 211 by tapped bore, connecting panel 807 is in piston 806 upper ends, auricle 802 is arranged on receiver 801 lateral surfaces, extension spring 805 is hung on auricle 802 and connecting panel 807, and extension spring 805 is 4 to 6 of receiver 801 circumferential directions.After the work of secondary projector, secondary projector base 211 can produce larger recoil, recoil is passed to buffering honeycomb 803 by piston 806, to cushion honeycomb 803 conquassation, buffering honeycomb 803 Collapse of Concretes can absorb energy and reduce recoil to the impact of mounting structure and application force, and the size of buffering honeycomb 803 can be determined according to the design of mounting structure load-carrying capacity size.
Mooring line 9 and rope 10 employings of closing up have lamination coating works out, and mooring line 9 is after flying net 7 target acquisition aircraft, for target aircraft is implemented to drag operation.The rope 10 that closes up is connected on mass 3, by mechanism's rolling of mass 3 inside, is closed up and is restricted 10, realizes and flies tightening up of net 7 network interfaces.
The space that the present invention proposes flies net secondary and pulls out method of deploying and comprise: the first step: fly net encapsulation hatchcover by launching, to fly net pulls out gradually from net bag, space flies net one-level expansion process as shown in Figure 8, when satellite is found after objective body, satellite Autonomous is controlled 1 work of one-level projector, one-level projector 1 launches away et hold lid 6 from et hold 5 outlets, net bag 4 is along with et hold lid 6 ejects from et hold 5, fly net under the drive of et hold lid 6 from net bag 4 successively inverted order pull out, along with flying net 7, be drawn out, fly net 7 and mooring line 9 is straightened gradually; Et hold lid 6 obtains υ under the effect of one-level projector
t, realize separatedly with launching of et hold 5, net bag 4 is along with the ejections of et hold lid 6, fly net 7 under the drive of et hold lid from net bag 4 successively inverted order pull out, in this process, fly net 7 peripheries and be fixed on all the time on et hold wall with the rope 9 that closes up.Second step, when fly to net stretching after, by four traction masses, to fly net launches gradually from bottom, space flies net secondary expansion process as shown in Figure 9, is flying net 7 and mooring line 9 stretching moment, and satellite Autonomous is controlled secondary projector 2 and started working, be placed in firing unit (according to flying to net stretching distance and the deployment time enforcement triggering in parallel) igniting in secondary projector, secondary projector 2 promotes four masses 3 according to default emission rate υ
0, transmitting subtended angle α motion, mass 3 restrict and 10 is driven and fly net 7 and launch from back to front and reach the state being filled, finally realization catching objective body by closings in.
The unspecified part of the present invention belongs to general knowledge as well known to those skilled in the art.
Claims (8)
1. space flies a net secondary transmitting method of deploying, it is characterized in that step is as follows:
(1) set up space and fly net secondary transmitting expanding unit;
(2) when satellite is found after objective body, satellite Autonomous is controlled the one-level projector work in secondary transmitting expanding unit, one-level projector launches away et hold lid from et hold outlet, net bag is along with et hold lid ejects from et hold, fly net under the drive of et hold lid from net bag successively inverted order pull out, along with flying net, be drawn out, fly net and mooring line is straightened gradually;
(3) flying net and mooring line stretching moment, the secondary projector that satellite Autonomous is controlled in secondary transmitting expanding unit is started working, firing unit igniting in secondary projector, secondary projector promotes four masses according to default emission rate and the motion of transmitting subtended angle, mass is flown net and is launched from back to front and reach the state being filled by the closing in traction of restricting, and finally realizes catching objective body.
2. a kind of space according to claim 1 flies net secondary transmitting method of deploying, it is characterized in that: described secondary transmitting expanding unit is by one-level projector (1), secondary projector (2), four masses (3), net bag (4), et hold (5), et hold lid (6), fly net (7), shock absorber (8), mooring line (9) and the rope (10) that closes up form, flying net (7) is contained in net bag (4), net bag (4) is contained in et hold (5), net bag (4) is connected with et hold lid (6), one-level projector (1) is arranged on the bottom of et hold (5), between one-level projector (1) and et hold lid (6), adopt elasticity to be connected and make et hold cover the outlet that (6) are encapsulated in et hold (5), net bag (4) is connected with shock absorber (8) by mooring line (9), secondary projector (2) is arranged on shock absorber (8), shock absorber (8) is fixed on satellite structure, between one-level projector (1) and secondary projector (2), be fixedly connected with, four masses (3) are arranged on secondary projector (2), four masses (3) are connected with the edge that flies net (7) by the rope (10) that closes up respectively.
3. a kind of space according to claim 2 flies net secondary transmitting method of deploying, it is characterized in that: described one-level projector (1) comprises mount pad (101), firer's cutter (102), compressor arm (103), spring spool (104) and release spring (105), mount pad (101) is arranged on the bottom of et hold (5), firer's cutter (102) is arranged between mount pad (101) and et hold (5), spring spool (104) is positioned at et hold (5) inside center position and is connected with the bottom of et hold (5), release spring (105) is arranged in spring spool (104), compressor arm (103) one end is through et hold lid (6), spring spool (104), firer's cutter (102) is connected with mount pad (101), the other end of compressor arm (103) is pressed on et hold lid (6) on et hold (5) by nut fastener.
4. a kind of space according to claim 2 flies net secondary transmitting method of deploying, it is characterized in that: described secondary projector (2) comprises firing unit (201), firing device (202), main piston (203), guide finger (204), seal ring (205), four minutes piston sleeves (206), four minutes pistons (207), shear pin (208), main piston guiding sleeve (209), pipe link (210) and base (211), firing unit (201) and firing device (202) are arranged in base (211), before the work of transmitting expanding unit, the larger part of main piston (203) area is arranged in base (211) and is positioned on firing device (202), the less part of main piston (203) area is arranged in main piston guiding sleeve (209), between the less part of the part that main piston (203) area is larger and area, adopt the transition of taper shoulder, it is upper for carrying out spacing to the motion of main piston (203) that guide finger (204) is arranged on main piston guiding sleeve (209), the bottom of main piston (203) be provided with four through holes for when main piston (203), move to prescribe a time limit with four minutes piston (207) be communicated with, four minutes piston sleeve (206) be distributed on the transition phase between base (211) and main piston guiding sleeve (209), four minutes piston (207) be arranged in four minutes piston sleeve (206), four minutes piston (207) bottom be all positioned on the taper shoulder of main piston (203), four minutes piston (207) top pipe link (210) is installed, pipe link (210) is connected with a minute piston sleeve (206) by shear pin (208), between main piston (203) and base (211), dividing between piston (207) and minute piston sleeve (206) all adopts seal ring (205) to seal.
5. a kind of space according to claim 4 flies net secondary transmitting method of deploying, it is characterized in that: the angle between described each minute piston sleeve (206) axis and main piston guiding sleeve (209) axis is 20 °～55 °.
6. a kind of space according to claim 4 flies net secondary transmitting method of deploying, it is characterized in that: the launching technique of described secondary projector is: when space flies to net stretching moment, firing unit (201) igniting, firing device (202) produces high-pressure gas after getting angry, promote main piston (203) upward movement in base (211) and main piston guide sleeve (209), synchronous (204) individual minute piston (207) upward movement in minute piston sleeve (206) that promotes of taper shoulder of main piston (203), divide piston (207) upward movement to cut off shear pin (208), main piston (203) continues motion makes seal ring (205) depart from sealing surface, high-pressure gas acts directly on a minute piston (207) by four through holes of main piston (203) bottom, high-pressure gas promotes minute piston (207) and hightails a minute piston sleeve (206) with certain speed promotion pipe link (210), the mass (3) that makes to be arranged on pipe link (210) launches away.
7. a kind of space according to claim 2 flies net secondary transmitting method of deploying, it is characterized in that: described shock absorber (8) comprises receiver (801), auricle (802), buffering honeycomb (803), pressing plate (804), extension spring (805), piston (806) and connecting panel (807), circular buffering honeycomb (803) and the face of cylinder, lower end of piston (806) are all positioned at receiver (801), the face of cylinder, lower end of piston (806) and receiver (801) are axis hole free-running fit, pressing plate (804) is connected and piston (806) lower end cylinder table exponent part is pressed on buffering honeycomb (803) with the upper end of receiver (801), piston (806) upper end is connected with the base of secondary projector, connecting panel (807) is arranged on the upper end of piston (806), auricle (802) is arranged on the lateral surface of receiver (801), the two ends of extension spring (805) are hung on auricle (802) and connecting panel (807).
8. a kind of space according to claim 1 and 2 flies net secondary transmitting method of deploying, it is characterized in that: described mooring line (9) and the rope (10) that closes up adopt lamination coating to work out.
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| CN201310504653.9A CN103587730B (en) | 2013-10-23 | 2013-10-23 | A kind of space flies net secondary and launches method of deploying |
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| CN201310504653.9A CN103587730B (en) | 2013-10-23 | 2013-10-23 | A kind of space flies net secondary and launches method of deploying |
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| CN104807664A (en) * | 2015-05-15 | 2015-07-29 | 中国人民解放军国防科学技术大学 | Ground test device for space web projecting deployment |
| CN105667842A (en) * | 2016-01-29 | 2016-06-15 | 中国人民解放军国防科学技术大学 | Concentric circle type net folding device |
| CN106394940A (en) * | 2016-10-25 | 2017-02-15 | 杭州电子科技大学 | Space rope net capturing system based on recombining rope system formation flying |
| CN108363837A (en) * | 2018-01-18 | 2018-08-03 | 西北工业大学 | A kind of rope is the computational methods of flying mesh system impact force |
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| CN104807664A (en) * | 2015-05-15 | 2015-07-29 | 中国人民解放军国防科学技术大学 | Ground test device for space web projecting deployment |
| CN106275518B (en) * | 2015-06-01 | 2018-08-07 | 北京空间飞行器总体设计部 | Gas-filled unfolded space junk capturing system and extraterrestrial target catching method |
| CN105667842A (en) * | 2016-01-29 | 2016-06-15 | 中国人民解放军国防科学技术大学 | Concentric circle type net folding device |
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| CN108363837A (en) * | 2018-01-18 | 2018-08-03 | 西北工业大学 | A kind of rope is the computational methods of flying mesh system impact force |
| CN109592080B (en) * | 2018-11-28 | 2020-07-31 | 中国人民解放军国防科技大学 | Tether-electromagnetic cooperative control micro-nano satellite flexible recovery method and device |
| CN109592080A (en) * | 2018-11-28 | 2019-04-09 | 中国人民解放军国防科技大学 | Tether-electromagnetic cooperative control micro-nano satellite flexible recovery method and device |
| CN109549314A (en) * | 2018-12-07 | 2019-04-02 | 上海宇航系统工程研究所 | A kind of space capture collecting bag and netting accommodation method of netting |
| CN109677643A (en) * | 2019-02-02 | 2019-04-26 | 中国人民解放军国防科技大学 | Net flying claw device assembly |
| CN109677643B (en) * | 2019-02-02 | 2020-06-19 | 中国人民解放军国防科技大学 | Net flying claw device assembly |
| CN109850190A (en) * | 2019-02-02 | 2019-06-07 | 中国人民解放军国防科技大学 | Space shape following capture net |
| CN109850190B (en) * | 2019-02-02 | 2020-09-18 | 中国人民解放军国防科技大学 | Space shape following capturing device |
| CN113277129A (en) * | 2021-05-31 | 2021-08-20 | 北京理工大学 | Net shooting device flies of adjustable launch angle |
| CN113277129B (en) * | 2021-05-31 | 2022-07-05 | 北京理工大学 | Net shooting device flies of adjustable launch angle |
| CN115071995A (en) * | 2022-07-06 | 2022-09-20 | 南京理工大学 | Differential-time out-of-phase rope net launching mechanism for balanced launching |
| CN115779288A (en) * | 2022-11-18 | 2023-03-14 | 南京理工大学 | But receipts mouth is from dynamic rope net voluntarily suitable for space non-cooperative target is caught |
| CN115779288B (en) * | 2022-11-18 | 2023-09-26 | 南京理工大学 | Independently motor rope net of can binding off suitable for space non-cooperative target is caught |
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| CN103587730B (en) | 2015-11-25 |
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