CN105836162A - Braking-sail deorbiting device for micro/nano satellite - Google Patents
Braking-sail deorbiting device for micro/nano satellite Download PDFInfo
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- CN105836162A CN105836162A CN201610353504.0A CN201610353504A CN105836162A CN 105836162 A CN105836162 A CN 105836162A CN 201610353504 A CN201610353504 A CN 201610353504A CN 105836162 A CN105836162 A CN 105836162A
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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
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
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Abstract
The invention discloses a deorbiting device for a micro/nano satellite. The deorbiting device for the micro/nano satellite comprises a sail storing device, a sail unfolding device and an unlocking device, wherein the sail unfolding device is of a centrosymmetric structure, and comprises an upper end cover, a lower end cover, a clack-shaped central shaft, two ring flanges, two strip elastic masts, four supporting prisms, four pairs of pilot sleeves, four hold-down mechanisms and four leaf springs. After a ground command is received, the unlocking device releases the clack-shaped central shaft of the sail unfolding device; the strip elastic masts wound on the clack-shaped central shaft drive a thin-film sail, which is stored in a sail storing chamber, to unfold through releasing elastic potential energy stored by the strip elastic masts. According to the deorbiting device for the micro/nano satellite, the normal sectional area, in which a satellite moves, is increased by utilizing the unfolding of the thin-film sail, the effect of atmospheric drag perturbation on the micro/nano satellite is enhanced, and thus, the passive deorbiting of the micro/nano satellite is prompted.
Description
Technical field
The invention belongs to spacecraft leave the right or normal track field, be specifically related to a kind of micro-nano satellite braking sail and leave the right or normal track device.
Background technology
Since the mankind launch its first man made earth satellite so far, space technology obtains great achievement and develops rapidly, but
Meanwhile also result in the substantial amounts of space junk of longer-term persistence in the range of terrestrial space, and the sky that these quantity increase day by day
Between fragment had influence on the proper space activity of the mankind.The mankind have carried out more than 5000 Spacecraft Launchs work altogether up to now
Dynamic, there is more than 200 spacecraft or rocket carrier blast/crash in-orbit altogether, also create substantial amounts of space junk simultaneously.
The most obvious example is the space that the former Soviet Union occurred for 2009 discards satellite Kosmos-2251 and American satellite Iridium-33
Collision accident.
The safety of spacecraft in-orbit in the existence serious threat of space junk, constrains the development of mankind's space technology.As
What slows down the growth of space junk has become as the problem needing solution both at home and abroad badly.For current technology condition, reduce sky
Between the only effective method of number of tiles be to make it reenter earth dense atmosphere to burn the technology that i.e. leaves the right or normal track.Inter-agency space is broken
The sheet coordination committee (IADC) if also indicating that satellite can not become rail to graveyard track, just should after completing its task in 25 years or
Can leave the right or normal track voluntarily in launching latter 30 years, enter dense atmosphere and burn.Therefore, the research spacecraft technology of leaving the right or normal track has very important
Meaning.
Along with development and the demand of new and high technology, micro-nano satellite is little with its volume, low in energy consumption, the construction cycle is short, can form into columns
Networking, completes the advantage of a lot of complicated space tasks, increasingly by domestic and international associated mechanisms and colleges and universities with lower cost
Attention.Along with micro-nano satellite launches the increasing of quantity, the impact on spatial environments is the most more and more significant, if none of can
The technology that leaves the right or normal track leaned on, the transmitting of following micro-nano satellite will be by certain restriction.Abroad in Recent Years many colleges and universities and institute
The most actively throw oneself into micro-nano satellite to leave the right or normal track the research of technology, the most several modes of leaving the right or normal track include inflatable ball, electric power tether with
And braking sail etc..
The braking sail technology of leaving the right or normal track is to form variously-shaped sail by stent thin film on satellite, thus increases satellite
The normal section of the direction of motion is amassed, and improves atmospheric drag suffered in satellite flight course in-orbit, force satellite ahead of time from
Rail enters dense atmosphere and burns.The braking sail that can vary in size according to satellite different quality development, general sail area is several squares
Rice is to tens square metres.This device light weight, simple in construction, low cost, be particularly well-suited to quickly to respond, duty cycle short
Low orbit micro-nano satellite.
Patrick is open reports a kind of braking sail device AEOLDOS being applicable to low orbit cube satellite
(Advances in Space Research 54 (2014) 82 91), this device relies on the mechanical energy that system self is stored
Driving intermediate rotary shaft rotates, thus is launched by braking sail.Braking sail area designed by this device is less, thus can lead to
Crossing a rotating shaft to be launched by four masts, 4 Ge Fan locker rooms are separately positioned between four masts.System structure is simple, volume
Little, light weight, it is adaptable to leaving the right or normal track of low orbit cube satellite.Improve constantly however as cube satellite orbital altitude, star
Weight constantly increases, and the application of this device has some limitations.
Summary of the invention
It is an object of the invention to provide a kind of micro-nano satellite braking sail to leave the right or normal track device, can make orbit altitude be 800km,
The micro-nano satellite of quality 70kg left the right or normal track in 25 years, solves micro-nano satellite and cannot leave the right or normal track at the appointed time after completing task
Thus become the problem that space junk affects the normal operation of other satellites.
The technical solution realizing the object of the invention is: a kind of micro-nano satellite braking sail leaves the right or normal track device, and its size takiesSpace, including from up to down set gradually sail storage device, sail expanding unit and unlock dress
Put.
Described sail storage device includes sail locker room, thin film sail and journal stirrup, and sail locker room is rectangular structure, four sides
Four dovetail grooves are opened respectively for memory films sail in face, and the most each trench bottom is equipped with two through holes, by one of thin film sail
Angle is fixed in described through hole；Four sidewall bottom of sail locker room are equipped with downward journal stirrup, are used for and sail expanding unit
Side is connected.
Described sail expanding unit is centrosymmetric structure, including upper end cover, bottom end cover, flap central shaft, two ring flanges,
Two strip-like resilient masts, four support prisms, four pairs of pilot sleeves, four hold-down mechanisms and four spring leafs.
Four pairs of pilot sleeves are arranged on four angles of bottom end cover, and four support rib column symmetry are distributed in four of bottom end cover
On side, two ends are connected with upper end cover and bottom end cover respectively, and next-door neighbour's pilot sleeve, support upper end cover and bottom end cover, upper end cover
Bottom centre is provided with a ring flange；Bottom end cover top center is provided with another ring flange；Flap central shaft is arranged on ring flange
Center, two ends are connected with two ring flanges respectively；Hold-down mechanism is arranged between adjacent two couple pilot sleeve, respectively with upper end
Lid and bottom end cover are hinged；Spring leaf one end is fixed on support prism, and the other end is fixed on hold-down mechanism；Two strip-like resilient
Mast is wrapped on flap central shaft.
Described bottom end cover center is sequentially provided with bearing groove, ring flange central shaft through hole and flange surface groove；Bearing groove in order to
Assembling rolling bearing make upper and lower end cap be connected with ring flange respectively, ring flange central shaft through hole in order to make ring flange pass, flange
Card groove is in order to assembly flange dish, and upper end cover is identical with bottom end cover structure.
Described flap central shaft includes four cylinders arranged in petal-shaped, and leaves gap between cylinder, two
Strip-like resilient mast passes and two cylinders of envelope from above-mentioned gap respectively, and said two cylinder is positioned at same diagonal
On, then four free ends of strip-like resilient mast are wrapped on flap central shaft, cylinder top and bottom respectively with up and down
Two ring flanges are connected, and cylindrical sides centre position has groove and screwed hole, is worn between cylinder by screw in compression
The strip-like resilient mast crossed.
Described strip-like resilient mast is formed by stacking by two tape springs, and two tape spring cambered surfaces are relative, cross section radian
It is 70 ° 90 °, free end has aperture, be connected with the thin film sail in sail locker room by nylon rope.
Described ring flange includes card, disk center's axle and four flaky strong magnets, and disk center's axle is positioned at card top center, dish
Face is distributed uniformly and circumferentially four flaky strong magnets, and disk center's axle is respectively connected with by bearing and upper and lower end cap, and its end face
Stretch out bottom end cover to be connected with tripper.
Described bottom end cover has sensor through hole at flaky strong magnet correspondence position, and sensor through hole is used for assembling hall sensing
Device.
Described hold-down mechanism includes that cylinder, gripper shoe and support shaft, gripper shoe side have cylinder mounting groove, and opposite side is opened
Support shaft mounting groove, the support shaft mounting groove degree of depth is had to exceed the center of gripper shoe；Cylinder is arranged in cylinder mounting groove, support shaft
It is arranged in support shaft mounting groove, and is positioned at the end of gripper shoe；The cental axial position of gripper shoe has upper and lower two through holes, uses
In hinged with upper end cover, bottom end cover；Gripper shoe outer wall is curved, outwardly, and cylinder compresses and is wrapped on flap central shaft
Strip-like resilient mast, spring card is in support shaft.
Every pair of pilot sleeve is made up of two single pilot sleeves, leaves space, strip-like resilient between two single pilot sleeves
Four free ends of mast, are each passed through the space of above-mentioned pilot sleeve.
Compared with prior art, its remarkable advantage is the present invention:
(1) volume is little, light weight, complies fully with micro-nano satellite miniaturization, lightweight requirements, reduces other system quality and sky
Between restriction, improve micro-nano satellite functional density.
(2) applied widely, when satellite orbital altitude is 800km, the present invention can be to quality owning within 70kg
Satellite effectively leaves the right or normal track；When orbit altitude is less than 800km, present invention may also apply to the quality micro-nano satellite more than 70kg.
(3 without outside energy supply, only relies on the elastic strain energy self stored and launches braking sail, reduces ground and control difficulty,
Reduce micro-nano satellite manufacturing cost.
(4) present invention is a set of single system, and function modoularization, will not increase the life requirements of other system,
Also will not be affected the most normally by other system, while not disturbing other system, also ensure the reliability of the system that leaves the right or normal track.
(5) ' () ' type elasticity mast that elastic mast utilizes the tape spring of two monolayer opening column shell structures to be combined into
Bar, when it can utilize gathering, the elastic strain energy of accumulation realizes Automatic-expanding without other power set；After deployment,
Stiffness by itself can be relied on again to provide and to support the self-lock force needed for thin film sail and the ability of external force resistance interference, without additionally adding
Locking device.
(6) hold-down mechanism compresses the not deployed part of residue during the expansion of mast, can effectively prevent mast not
Deploying portion is lost a part of mechanical energy and blocks the situation appearance died from sail expanding unit because of expansion because of expansion.
(7) thin film sail uses the Kapton aluminized, and its thickness is thin, and mechanical property is good and is easy to fold pressure
Contracting, the elemental oxygen being simultaneously highly resistant in spatial environments corrosion and solar radiation.
(8) simple in construction, good reliability, processing cost is low, practical, is highly suitable for quickly responding, duty cycle
Short cube satellite.
Accompanying drawing explanation
Fig. 1 is that micro-nano satellite of the present invention braking sail leaves the right or normal track the strip-like resilient mast structure schematic diagram of device.
Fig. 2 be micro-nano satellite of the present invention braking sail leave the right or normal track device strip-like resilient mast draw in structural representation.
Fig. 3 is that micro-nano satellite of the present invention braking sail leaves the right or normal track the partial schematic diagram of strip-like resilient mast of device.
Fig. 4 is that micro-nano satellite of the present invention braking sail leaves the right or normal track the structural representation of upper lower flange of device.
Fig. 5 is that micro-nano satellite of the present invention braking sail leaves the right or normal track the structural representation of hold-down mechanism of device.
Fig. 6 is that micro-nano satellite of the present invention braking sail leaves the right or normal track the bottom end cover structural representation of device.
Fig. 7 is that micro-nano satellite of the present invention braking sail leaves the right or normal track the internal structure schematic diagram of sail expanding unit of device.
Fig. 8 is that micro-nano satellite of the present invention braking sail leaves the right or normal track the external structure schematic diagram of sail expanding unit of device.
Fig. 9 is that micro-nano satellite of the present invention braking sail leaves the right or normal track the structural representation of sail locker room of device.
Figure 10 is that micro-nano satellite of the present invention braking sail leaves the right or normal track the overall structure schematic diagram of device.
Figure 11 be micro-nano satellite of the present invention braking sail leave the right or normal track device sail launch after structural representation.
Detailed description of the invention
Below in conjunction with the accompanying drawings the present invention is described in further detail.
In conjunction with Figure 10, a kind of micro-nano satellite braking sail leaves the right or normal track device, and its size takiesSky
Between, it is possible to apply to cube satellite, take a cube space of star 1.5U.Including the sail storage dress from up to down set gradually
Put, sail expanding unit 32 and tripper 33.
In conjunction with Fig. 9 and Figure 11, described sail storage device is used for storing thin film sail, including sail locker room 29, thin film sail 34 and
Journal stirrup 31, sail locker room 29 is rectangular structure, opens four dovetail grooves 30 respectively four sides for memory films sail 34, with
Time each trench bottom be equipped with two through holes, an angle of thin film sail 34 is fixed in described through hole；The four of sail locker room 29
Individual sidewall bottom is equipped with downward journal stirrup 31, is connected for the side with upper end cover 28.
In conjunction with Fig. 7 and Fig. 8, sail expanding unit 32 is centrosymmetric structure, including in upper end cover 28, bottom end cover 24, flap
2, four support prisms of 3, two strip-like resilient masts of 6, two ring flanges of mandrel, 26, four compacting machines of 25, four pairs of pilot sleeves
Structure 16 and four spring leafs 27.
Four pairs of pilot sleeves 26 are arranged on four angles of bottom end cover 24, and four support prisms 25 are symmetrically distributed in bottom end cover
On four sides of 24, two ends are connected with upper end cover 28 and bottom end cover 24 respectively, and next-door neighbour's pilot sleeve 26, support upper end cover 28
With bottom end cover 24, upper end cover 28 bottom centre is provided with a ring flange 3；Bottom end cover 24 top center is provided with another ring flange 3.
Flap central shaft 6 is arranged on ring flange 3 center, and two ends are connected with two ring flanges 3 respectively.Hold-down mechanism 16 is arranged on adjacent
Between two pairs of pilot sleeves 26, hinged with upper end cover 28 and bottom end cover 24 respectively.Spring leaf 27 one end is fixed on support prism 25
On, the other end is fixed on hold-down mechanism 16.Two strip-like resilient masts 2 are wrapped on flap central shaft 6.
In conjunction with Fig. 1 and Fig. 2, flap central shaft 6 includes four cylinders 1 arranged in petal-shaped, simultaneously between cylinder 1
Leaving gap, two strip-like resilient masts 2 pass and two cylinders 1 of envelope from above-mentioned gap respectively, said two cylinder 1
It is positioned on same diagonal, then four free ends of strip-like resilient mast 2 is wrapped on flap central shaft 6, cylinder 1 top
Having screwed hole 4 with bottom to be connected with upper and lower two ring flanges 3, cylindrical sides centre position has groove and screwed hole
5, the strip-like resilient mast 2 passed between cylinder 1 by screw in compression.
In conjunction with Fig. 4, ring flange 3 includes card 9,12, four flaky strong magnets 13 of disk center's axle, and disk center's axle 12 is positioned at card
9 top center, card 9 is distributed uniformly and circumferentially four flaky strong magnets 13, and disk center's axle 12 top is hexagon, disk center
Axle 12 is connected with upper and lower end cap by bearing, hexagon end face external part lid.It is positioned at six limits of the ring flange central shaft 12 of bottom
Shape end face is connected with tripper 33.
Every pair of pilot sleeve 26 is made up of two single pilot sleeves, leaves space, banding bullet between two single pilot sleeves
Four free ends of property mast 2, are each passed through the space of above-mentioned pilot sleeve 26.Pilot sleeve 26 is used for guiding strip-like resilient mast
Bar 2 outwards launches, and limits its expansion direction.
In conjunction with Fig. 3, strip-like resilient mast 2 is formed by stacking by two tape springs 7, and two tape spring 7 cambered surfaces are relative, its
Middle tape spring 7 is to be processed by the beallon band of wide 19mm thickness 0.1mm, and cross section radian is 70 ° 90 °, on free end
Have aperture 8, be connected with the thin film sail in sail locker room 29 by nylon rope.
In conjunction with Fig. 5, hold-down mechanism 16 is used for compressing the not deployed part of strip-like resilient mast 2, prevents it during launching
Expanding, card is died from sail expanding unit 32, and including cylinder 14, gripper shoe 15 and support shaft 17, gripper shoe 15 side has cylinder
Mounting groove, opposite side has support shaft mounting groove, and the support shaft mounting groove degree of depth exceedes the center of gripper shoe 15.Cylinder 14 is arranged on
In cylinder mounting groove, support shaft 17 is arranged in support shaft mounting groove, and is positioned at the end of gripper shoe 15.The center of gripper shoe 15
Shaft position has upper and lower two through holes 10, for hinged with upper end cover 28, bottom end cover 24.Gripper shoe 15 outer wall is curved, outwards
Protruding, cylinder 14 compresses the strip-like resilient mast 2 being wrapped on flap central shaft 6, and spring leaf 27 is stuck in support shaft 17.
In conjunction with Fig. 6, described bottom end cover 24 center is sequentially provided with bearing groove 20, ring flange central shaft through hole 19 and flange surface
Groove 23, bottom end cover 24 side is uniformly distributed four support prism grooves 21；Bearing groove 20 makes upper and lower end cap in order to assemble rolling bearing
Being connected with ring flange 3 respectively, ring flange central shaft through hole 19 is in order to make ring flange pass, and flange surface groove 23 is in order to assembly flange
Dish 3, supports prism groove 21 in order to assemble support prism 25；Upper end cover 28 is identical with bottom end cover 24 structure.
Bottom end cover 24 has sensor through hole 18 at flaky strong magnet 13 correspondence position, and sensor through hole is used for installing Hall and passes
Sensor.
Tripper 33 is positioned at micro-nano satellite and leaves the right or normal track bottom of device, and the tripper of the present invention uses the space flight of American TI NI public
Frangibolt(http: //www.tiniaerospace.com/products.html of department) disk center's axle 12 is locked
Fixed.
After receiving expansion signal, tripper 33 energising discharges disk center's axle 12, and strip-like resilient mast 2 is by self
The elastic strain energy of storage drives thin film sail 34 to launch from sail locker room 29, and during launching, hold down gag compresses banding
Elastic mast 2 remains furlling part, in case strip-like resilient mast 2 is died from sail expanding unit 32 to circumferencial direction expansion card.
Job description
A kind of micro-nano satellite braking sail leaves the right or normal track device, is fixed on the bottom of micro-nano satellite heading, before satellite launch, and two bands
Shape elasticity mast 2 draws in sail expanding unit 32, and the end of strip-like resilient mast 2 hitches the thin film being stored in sail locker room 29
One jiao of sail 34, tripper 33 is by locked for disk center's axle 12 of sail expanding unit 32 simultaneously.The task in-orbit of micro-nano satellite is complete
Cheng Hou, receive launch braking sail leave the right or normal track device instruction after, tripper 33 discharges disk center's axle 12 of sail expanding unit 32,
The elastic strain stretchy of strip-like resilient mast 2 release storage is stored in four thin film sails 34 of sail locker room 29 respectively to four
Direction is launched, and during extension satellite flight, the sectional area on velocity attitude, increases the air drag suffered by micro-nano satellite, make
Satellite is rapidly separated track.
Embodiment: as a example by three unit cube stars
In conjunction with Fig. 1 ~ Figure 11, a kind of micro-nano satellite braking sail leaves the right or normal track device, for leaving the right or normal track, after preventing it from completing task of cube star
Become space junk.This micro-nano satellite braking sail device that leaves the right or normal track is installed on bottom cube star, takies a cube space of star 1.5U.Bag
Include sail storage device, sail expanding unit 32 and the tripper 33 from up to down set gradually.
Described sail storage device includes that sail locker room 29, thin film sail 34 and journal stirrup 31, sail locker room 29 are rectangular structure,
Opening four dovetail grooves 30 respectively four sides for memory films sail 34, the most each trench bottom is equipped with two through holes, will
One angle of thin film sail 34 is fixed in described through hole；Four sidewall bottom of sail locker room 29 are equipped with downward journal stirrup 31,
It is connected for the side with upper end cover 28.
Sail expanding unit 32 is centrosymmetric structure, including upper end cover 28, bottom end cover 24,6, two flanges of flap central shaft
2, four support prisms of 3, two strip-like resilient masts of dish, 26, four hold-down mechanisms 16 of 25, four pairs of pilot sleeves and four springs
Sheet 27.
Four pairs of pilot sleeves 26 are arranged on four angles of bottom end cover 24, and four support prisms 25 are symmetrically distributed in bottom end cover
On four sides of 24, two ends are connected with upper end cover 28 and bottom end cover 24 respectively, and next-door neighbour's pilot sleeve 26, support upper end cover 28
With bottom end cover 24, upper end cover 28 bottom centre is provided with a ring flange 3；Bottom end cover 24 top center is provided with another ring flange 3.
Flap central shaft 6 is arranged on ring flange 3 center, and two ends are connected with two ring flanges 3 respectively.Hold-down mechanism 16 is arranged on adjacent
Between two pairs of pilot sleeves 26, hinged with upper end cover 28 and bottom end cover 24 respectively.Spring leaf 27 one end is fixed on support prism 25
On, the other end is fixed on hold-down mechanism 16.Two strip-like resilient masts 2 are wrapped on flap central shaft 6.
Flap central shaft 6 includes four cylinders 1 arranged in petal-shaped, leaves gap between cylinder 1 simultaneously, two
Strip-like resilient mast 2 passes and two cylinders 1 of envelope from above-mentioned gap respectively, and said two cylinder 1 is positioned at same pair of horns
On line, then being wrapped on flap central shaft 6 by four free ends of strip-like resilient mast 2, cylinder 1 top and bottom are opened respectively
Having screwed hole 4 to be connected with upper and lower two ring flanges 3, cylindrical sides centre position has groove and screwed hole 5, by screw pressure
The tight strip-like resilient mast 2 passed between cylinder 1.
Ring flange 3 includes card 9,12, four flaky strong magnets 13 of disk center's axle, and disk center's axle 12 is positioned in card 9 top
The heart, card 9 is distributed uniformly and circumferentially four flaky strong magnets 13, and disk center's axle 12 top is hexagon, and disk center's axle 12 leads to
Cross bearing to be connected with upper and lower end cap, top hexagon end face external part lid.It is positioned at the hexagon of the ring flange central shaft 12 of bottom
End face is connected with tripper 33.
Every pair of pilot sleeve 26 is made up of two single pilot sleeves, leaves space, banding bullet between two single pilot sleeves
Four free ends of property mast 2, are each passed through the space of above-mentioned pilot sleeve 26.
Strip-like resilient mast 2 is formed by stacking by two tape springs 7, and two tape spring 7 cambered surfaces are relative, wherein banding bullet
Spring 7 is to be processed by the beallon band of wide 19mm thickness 0.1mm, and cross section radian is 90 °, free end has aperture 8, passes through
Nylon rope is connected with the thin film sail in sail locker room 29.
Hold-down mechanism 16 includes that cylinder 14, gripper shoe 15 and support shaft 17, gripper shoe 15 side have cylinder mounting groove, separately
Side has support shaft mounting groove, and the support shaft mounting groove degree of depth exceedes the center of gripper shoe 15.Cylinder 14 is arranged on cylinder and installs
In groove, support shaft 17 is arranged in support shaft mounting groove, and is positioned at the end of gripper shoe 15.The cental axial position of gripper shoe 15 is opened
There are upper and lower two through holes 10, for hinged with upper end cover 28, bottom end cover 24.Gripper shoe 15 outer wall is curved, outwardly, cylinder
14 compress the strip-like resilient mast 2 being wrapped on flap central shaft 6, and spring leaf 27 is stuck in support shaft 17.
Described bottom end cover 24 center is sequentially provided with bearing groove 20, ring flange central shaft through hole 19 and flange surface groove 23, under
End cap 24 side is uniformly distributed four support prism grooves 21；Bearing groove 20 in order to assemble rolling bearing make upper and lower end cap respectively with method
Blue dish 3 is connected, and ring flange central shaft through hole 19 is in order to make ring flange pass, and flange surface groove 23, in order to assembly flange dish 3, supports
Prism groove 21 is in order to assemble support prism 25；Upper end cover 28 is identical with bottom end cover 24 structure.
Bottom end cover 24 has sensor through hole 18 at flaky strong magnet 13 correspondence position, and sensor through hole is used for installing Hall and passes
Sensor.
Tripper 33 is positioned at micro-nano satellite and leaves the right or normal track bottom of device, and the tripper of the present invention uses the space flight of American TI NI public
Frangibolt(http: //www.tiniaerospace.com/products.html of department) disk center's axle 12 is locked
Fixed.
In sum, the micro-nano satellite of the present invention braking sail device volume that leaves the right or normal track is little, and light weight complies fully with micro-nano satellite
To the equipment miniaturization that leaves the right or normal track, lightweight requirements, its modularity, independent does not interferes with the running of other system yet, and does not has
The life-span of other subsystems is proposed requirements at the higher level.The micro-nano satellite braking sail of the present invention apparatus structure that leaves the right or normal track is simple, is processed into
This is the lowest, and integrity is good, and reliability is high, and the micro-nano satellite braking sail of the present invention device developed area that leaves the right or normal track is big simultaneously, the scope of application
Extensively, to the micro-nano satellite being in Low Earth Orbit being applicable to low cost, the lead time is short, functional density is big.
Claims (9)
1. micro-nano satellite braking sail leaves the right or normal track device, it is characterised in that: its size takiesSky
Between, including the sail storage device, sail expanding unit (32) and the tripper (33) that from up to down set gradually；
Described sail storage device includes sail locker room (29), thin film sail (34) and journal stirrup (31), and sail locker room (29) are cuboid
Structure, opens four dovetail grooves (30) respectively and is used for memory films sail (34) four sides, and the most each trench bottom is equipped with two
Individual through hole, is fixed on an angle of thin film sail (34) in described through hole；Four sidewall bottom of sail locker room (29) are equipped with
Downward journal stirrup (31), is connected for the side with sail expanding unit (32).
Micro-nano satellite the most according to claim 1 braking sail leaves the right or normal track device, it is characterised in that: described sail expanding unit (32)
It is centrosymmetric structure, including upper end cover (28), bottom end cover (24), flap central shaft (6), two ring flanges (3), two bandings
Elastic mast (2), four support prisms (25), four pairs of pilot sleeves (26), four hold-down mechanisms (16) and four spring leafs
(27)；
Four pairs of pilot sleeves (26) are arranged on four angles of bottom end cover (24), and four support prisms (25) are symmetrically distributed in lower end
On four sides of lid (24), two ends are connected with upper end cover (28) and bottom end cover (24) respectively, and next-door neighbour's pilot sleeve (26),
Support upper end cover (28) and bottom end cover (24), upper end cover (28) bottom centre is provided with a ring flange (3)；In bottom end cover (24) top
The heart is provided with another ring flange (3)；Flap central shaft (6) is arranged on ring flange (3) center, two ends respectively with two ring flanges
(3) connect；Hold-down mechanism (16) is arranged between adjacent two couple pilot sleeve (26), respectively with upper end cover (28) and bottom end cover
(24) hinged；Spring leaf (27) one end is fixed in support prism (25), and the other end is fixed on hold-down mechanism (16)；Two bands
Shape elasticity mast (2) is wrapped on flap central shaft (6).
Micro-nano satellite the most according to claim 2 braking sail leaves the right or normal track device, it is characterised in that: described bottom end cover (24) center
It is sequentially provided with bearing groove (20), ring flange central shaft through hole (19) and flange surface groove (23)；Bearing groove 20 is in order to assemble rolling
Bearing makes upper and lower end cap be connected with ring flange 3 respectively, ring flange central shaft through hole 19 in order to make ring flange pass, flange surface groove
23 in order to assembly flange dish 3；Upper end cover (28) is identical with bottom end cover (24) structure.
Micro-nano satellite the most according to claim 2 braking sail leaves the right or normal track device, it is characterised in that: described flap central shaft (6)
Including four cylinders (1) arranged in petal-shaped, and leave gap between cylinder (1), two strip-like resilient masts (2) point
Not from above-mentioned gap through also two cylinders (1) of envelope, said two cylinder (1) is positioned on same diagonal, then will band
Four free ends of shape elasticity mast (2) are wrapped on flap central shaft (6), cylinder (1) top and bottom respectively with up and down
Two ring flanges (3) are connected, and cylindrical sides centre position has groove and screwed hole (5), by screw in compression from cylinder
(1) the strip-like resilient mast (2) passed between.
Micro-nano satellite the most according to claim 4 braking sail leaves the right or normal track device, it is characterised in that: described strip-like resilient mast
(2) being formed by stacking by two tape springs (7), two tape spring (7) cambered surfaces are relative, and cross section radian is 70 ° 90 °, freely
Have aperture (8) on end, be connected with the thin film sail (34) in sail locker room (29) by nylon rope.
Micro-nano satellite the most according to claim 2 braking sail leaves the right or normal track device, it is characterised in that: described ring flange (3) includes
Card (9), disk center's axle (12) and four flaky strong magnets (13), disk center's axle (12) is positioned at card (9) top center, card
(9) being distributed uniformly and circumferentially four flaky strong magnets (13), disk center's axle (12) is respectively connected with by bearing and upper and lower end cap,
And its end face stretches out bottom end cover (24) and is connected with tripper (33).
Micro-nano satellite the most according to claim 6 braking sail leaves the right or normal track device, it is characterised in that: described bottom end cover (24) is at sheet
Shape strong magnetic (13) correspondence position has sensor through hole (18), and sensor through hole (18) is used for assembling Hall element.
Micro-nano satellite the most according to claim 2 braking sail leaves the right or normal track device, it is characterised in that: described hold-down mechanism (16) wraps
Including cylinder (14), gripper shoe (15) and support shaft (17), gripper shoe (15) side has cylinder mounting groove, and opposite side has support
Axle mounting groove, the support shaft mounting groove degree of depth exceedes the center of gripper shoe (15)；Cylinder (14) is arranged in cylinder mounting groove, supports
Axle (17) is arranged in support shaft mounting groove, and is positioned at the end of gripper shoe (15)；The cental axial position of gripper shoe (15) has
Upper and lower two through holes (10), for hinged with upper end cover (28), bottom end cover (24)；Gripper shoe (15) outer wall is curved, convex
Going out, cylinder (14) compresses the strip-like resilient mast (2) being wrapped on flap central shaft (6), and spring leaf (27) is stuck in support shaft
(17) on.
Micro-nano satellite the most according to claim 2 braking sail leaves the right or normal track device, it is characterised in that: the every pair of pilot sleeve (26) by
Two single pilot sleeves are constituted, and leave space between two single pilot sleeves, four free ends of strip-like resilient mast (2), point
Chuan Guo the space of above-mentioned pilot sleeve (26).
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| CN201610353504.0A CN105836162B (en) | 2016-05-25 | 2016-05-25 | A kind of micro-nano satellite braking sail leaves the right or normal track device |
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| CN110525687A (en) * | 2019-07-12 | 2019-12-03 | 长沙天仪空间科技研究院有限公司 | One kind leaves the right or normal track sail method of deploying and its device |
| CN110723314A (en) * | 2019-10-12 | 2020-01-24 | 上海宇航系统工程研究所 | Space film structure unfolding mechanism |
| CN110901959A (en) * | 2019-12-04 | 2020-03-24 | 成都星时代宇航科技有限公司 | Passive satellite derailment device, remote sensing satellite and satellite |
| CN111591471A (en) * | 2020-04-30 | 2020-08-28 | 南京理工大学 | Braking sail derailing device applied to standing satellite |
| CN112591143A (en) * | 2020-12-14 | 2021-04-02 | 兰州空间技术物理研究所 | Transition plate for accommodating flexible spacecraft |
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| CN113525724A (en) * | 2021-07-05 | 2021-10-22 | 陕西智星空间科技有限公司 | Micro-nano satellite braking sail device |
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| CN114132528A (en) * | 2021-11-30 | 2022-03-04 | 北京卫星制造厂有限公司 | Flexible sail unfolding device |
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| CN110010324B (en) * | 2019-04-02 | 2023-08-22 | 南京理工大学 | Double-electromagnet parallel locking device and working method thereof |
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| CN110525687A (en) * | 2019-07-12 | 2019-12-03 | 长沙天仪空间科技研究院有限公司 | One kind leaves the right or normal track sail method of deploying and its device |
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| CN110901959A (en) * | 2019-12-04 | 2020-03-24 | 成都星时代宇航科技有限公司 | Passive satellite derailment device, remote sensing satellite and satellite |
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| CN113525724A (en) * | 2021-07-05 | 2021-10-22 | 陕西智星空间科技有限公司 | Micro-nano satellite braking sail device |
| CN113650813A (en) * | 2021-08-09 | 2021-11-16 | 南京理工大学 | Active driving type large-scale film unfolding sail device |
| CN114132528A (en) * | 2021-11-30 | 2022-03-04 | 北京卫星制造厂有限公司 | Flexible sail unfolding device |
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| CN117022685A (en) * | 2023-08-04 | 2023-11-10 | 南京理工大学 | Space debris passive driving resistance-increasing off-track device |
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