CN107284692A - A kind of pyrolysis coupling expandable truss system suitable for space plate aerial - Google Patents
A kind of pyrolysis coupling expandable truss system suitable for space plate aerial Download PDFInfo
- Publication number
- CN107284692A CN107284692A CN201710405393.8A CN201710405393A CN107284692A CN 107284692 A CN107284692 A CN 107284692A CN 201710405393 A CN201710405393 A CN 201710405393A CN 107284692 A CN107284692 A CN 107284692A
- Authority
- CN
- China
- Prior art keywords
- truss
- joint
- freedom
- disc spring
- tabletting
- 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.)
- Granted
Links
- 230000008878 coupling Effects 0.000 title claims abstract description 20
- 238000010168 coupling process Methods 0.000 title claims abstract description 20
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 20
- 238000000197 pyrolysis Methods 0.000 title claims abstract description 17
- 238000009434 installation Methods 0.000 claims abstract description 15
- 210000004907 gland Anatomy 0.000 claims description 23
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 125000000852 azido group Chemical group *N=[N+]=[N-] 0.000 claims 1
- 238000010276 construction Methods 0.000 abstract description 3
- 230000007812 deficiency Effects 0.000 abstract description 3
- 230000008646 thermal stress Effects 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000035882 stress Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000036316 preload Effects 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
Classifications
-
- 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
-
- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Support Of Aerials (AREA)
Abstract
A kind of pyrolysis coupling expandable truss system suitable for space plate aerial, including rectangular frame and expandable truss with hot decoupling ability；The pyrolysis coupling function of under(-)chassis joint can be used for the release plate aerial face internal degree of freedom, maintain the installation foundation of expandable truss not changed under high/low temperature condition, it is ensured that in-orbit reliable expansion is as stable girders support system.Expandable truss is drawn in launching phase, bears the load of launching phase；It can reliably deploy after entering the orbit, enough expansion rigidity and precision is provided for plate aerial.The present invention overcomes the existing Antenna support structure space severe temperatures irretentive technical deficiency of type face precision off field, can carry out pyrolysis coupling with antenna, discharge thermal stress, meet antenna to high accuracy, the demand of the deployable supporting construction of high rigidity.
Description
Technical field
The present invention relates to a kind of deployable sub-truss system.
Background technology
The large-scale load of spacecraft such as antenna, solar wing etc., need folding to be collapsed into less volume in transmitting, bear each
Plant the examination of mechanical environment condition；After entering the orbit, need to reach certain rigidity of structure after expansion locking, in vacuum high/low temperature ring
Need under border keep higher type face precision.
Launching phase, truss, which is folded, to be drawn at the antenna back side, is connected with aerial panel, is born the load of launching phase；Defend
After star is entered the orbit, truss expansion is locked into a spatial configuration, and the rigidity and precision for antenna are kept.Due to the in-orbit flight of antenna
When, the temperature field of whole system is severe and uneven, the deformation of antenna and truss, causes truss internal stress larger,
The deformation of aerial panel and truss is constrained each other, and precision is difficult to keep, it is impossible to meet the in-orbit high thermal stability of high-precision antenna
It is required that.If temperature environment furtherization is it is also possible to the structure of truss is destroyed caused by internal stress is excessive.
In ground large antenna product, also there is what is caused in installation interface by discharging the free degree come acclimatization change
Deformation.But this design one is that thermal adaptability requirement is relatively low, and two be that coupling stiffness requirement is relatively low, it is impossible to meets vehicle launch
When require and bear the requirement of launching phase load to the storage of large-scale planar array antenna, while adaptive capacity to environment is limited.
The content of the invention
The technical problem to be solved in the present invention is：Overcome the deficiencies in the prior art, the present invention provides a kind of suitable for space
The pyrolysis coupling expandable truss system of plate aerial, realizes that the Large Spacecraft antenna wing draws transmitting in and deploys to be locked into after entering the orbit
The function of stable support structure, overcomes the existing Antenna support structure space severe temperatures irretentive technology of type face precision off field
Deficiency, can carry out pyrolysis coupling with antenna, discharge thermal stress, meet need of the antenna to high accuracy, the deployable supporting construction of high rigidity
Ask.
The technical solution adopted in the present invention is：A kind of pyrolysis coupling expandable truss system suitable for space plate aerial
System, including expandable truss, rectangular frame；Rectangular frame includes the free joint of base connecting rod, single-degree-of-freedom, two-freedom and dissociated
Joint, anchor tip；Single-degree-of-freedom is dissociated, and joint, two-freedom are free to be connected between joint and anchor tip by base connecting rod
Connect；Rectangular frame is connected by anchor tip, the free joint of single-degree-of-freedom, the free joint of two-freedom with antenna structure plate；Its
In, anchor tip is connected with antenna structure plate, and the free joint of single-degree-of-freedom is released along antenna width direction, length direction respectively
Single-degree-of-freedom constraint, two-freedom dissociate joint release along antenna structure plate width and length direction two frees degree about
Beam；Expandable truss includes four bars, four bar one end by rotatable mechanism fixing device same position mounted externally,
The other end is connected with the free joint of single-degree-of-freedom, the free joint of two-freedom, anchor tip by tumbler respectively, deployable
Truss has unfolded function.
The free joint of the single-degree-of-freedom has two, is separately mounted on rectangular frame diagonal two-end-point；Anchor tip,
The free joint of two-freedom is separately mounted on another diagonal two-end-point of rectangular frame.
Two bars possess unfolded function in the expandable truss, and another two bars are not foldable；Not folding two
Root bar is fixed on external fixation device；Dissociate joint, two with a single-degree-of-freedom respectively for the end of not folding two bars
The free joint of the free degree is connected by tumbler；The end for possessing two connecting rods of unfolded function connects with fixation respectively
The free joint of head, another single-degree-of-freedom is connected by tumbler.
The anchor tip includes the first truss base, the first tabletting, the first fixing screws, the first gland, the first joint
Bearing and the first connecting shaft；First oscillating bearing outer ring is arranged in the first truss floor installation through hole and by installation through-hole
Ledge structure positioning；First gland is flange arrangement, in the first truss floor installation through hole, ring flange and the first purlin
Frame base is fixed, and flange arrangement barrel end compresses the first oscillating bearing outer ring；First connecting shaft one end is fixed on antenna structure
On plate, the other end inserts the first oscillating bearing inner ring, the first joint shaft from the side that the first truss base does not install the first gland
Inner ring is held to position by the shaft shoulder；The first connection axial end and the first oscillating bearing inner ring are pushed down in first tabletting；First fixing screws
In the first gland centre bore, through the through hole of the first tabletting, by being threadably mounted at through hole of first connecting shaft along axis
Interior, head compresses the first tabletting.
The single-degree-of-freedom joint that dissociates includes the second connecting shaft, the first end cap, the first disc spring tabletting, the second tabletting, the
Two glands, the second truss base, the second fixing screws, the first free sliding block, second joint bearing, the first disc spring；First disc spring,
First disc spring tabletting is arranged in truss base installing hole, and first disc spring one end is pushed down in the first disc spring tabletting；First end cap is installed
In the second truss base installing hole port, the first disc spring other end is compressed；First free sliding block is arranged on truss floor installation
In hole, compress in the first disc spring tabletting, the first free its center hole and second joint bearing, second joint bearing outer ring one are installed
Side is positioned by ledge structure in the first free its center hole；Second gland is arranged in the first free its center hole, and one
The tight second joint bearing outer ring opposite side of side pressure, the other end props up the second truss base installing hole top inner wall；Second connecting shaft
It is vertically fixed on antenna structure plate, through the first end cap central bore, the first disc spring, the first disc spring tabletting centre bore, end peace
In second joint bearing inner race, the second fixing screws are arranged on the second connection shaft end and compress second by the second tabletting
Oscillating bearing；A raised word structure is arranged on the word on the second truss base installing hole side wall on first free sliding block outer wall
In groove.
The two-freedom joint that dissociates includes the 3rd connecting shaft, the second end cap, the second disc spring tabletting, the 3rd tabletting, the
Three glands, the 3rd truss base, the 3rd fixing screws, the second free sliding block, three-knuckle bearing, the second disc spring；Second disc spring,
Second disc spring tabletting is arranged in truss base installing hole, and second disc spring one end is pushed down in the second disc spring tabletting；Second end cap is installed
In the 3rd truss base installing hole port, the second disc spring other end is compressed；Second free sliding block is arranged on truss floor installation
In hole, compress in the second disc spring tabletting, the second free its center hole and three-knuckle bearing, three-knuckle bearing outer ring one are installed
Side is positioned by ledge structure in the second free its center hole；3rd gland is arranged in the second free its center hole, and one
The tight three-knuckle bearing outer ring opposite side of side pressure, the other end props up the 3rd truss base installing hole top inner wall；3rd connecting shaft
It is vertically fixed on antenna structure plate, through the second end cap central bore, the second disc spring, the second disc spring tabletting centre bore, end peace
In three-knuckle bearing inner ring, the 3rd fixing screws are arranged on the 3rd connection shaft end and compress the 3rd by the 3rd tabletting
Oscillating bearing；Second free sliding block outer wall is the face of cylinder, and the second free sliding block occurs relatively in the 3rd truss base installing hole
Motion.
The base connecting rod is carbon fibre pipe fitting.
Connected between the first truss base, the second truss base, the 3rd truss base by base connecting rod.
The advantage of the present invention compared with prior art is：
(1) expandable truss of the invention is a spatial four-bar mechanism, and the expansion to slab construction can be achieved and draws function in,
And draw in when can it is parallel with celestial body press close to, store small volume；Spaceborne large-scale load is met to compare high rigidity, high accuracy, big store
The demand of deployable supporting mechanism, the bearing capacity for possessing launching phase, while meeting in-orbit high accuracy and high thermal stability
It is required that.
(2) rectangular frame of the invention is swum by 1 group of anchor tip, the free joint of 2 groups of single-degree-of-freedoms, 1 group of two-freedom
It is connected from joint with antenna structure plate.Wherein, anchor tip is connected with antenna structure plate, the free joint difference of 2 groups of single-degree-of-freedoms
The single-degree-of-freedom constraint along antenna length and width is released, the free joint of two-freedom releases wide along antenna structure plate
Two frees degree of degree and length direction are constrained；Under expansion lock-out state, expandable truss may make up one with rectangular frame
Stable quadrangular truss structure, configuration is simple, but with higher structural support rigidity.
(3) rectangular frame of the invention is connected by 4 groups of free joints with antenna structure plate, and passes through disc spring in junction
Group pretension realizes larger coupling stiffness, while ensure that the connection precision along antenna structure plate normal direction.
(4) present invention is applied to need the large-scale flat plane antenna in space of in-orbit expansion on spacecraft, and height can be provided after expansion
Rigidity, high-precision structural support, and good plane can be kept in severe temperature alternating environment.
Brief description of the drawings
The schematic diagram that Fig. 1 discharges for the medium-sized face degree free degree of the invention
Fig. 2 is mechanism deploying view of the present invention；
Fig. 3 is mechanism rounding state schematic diagram of the present invention；
Fig. 4 is the structure chart of anchor tip of the present invention；
Fig. 5 is the structure chart of the free joint of single-degree-of-freedom of the present invention；
Fig. 6 is the truss understructure figure of the free joint of single-degree-of-freedom of the present invention；
Fig. 7 is that the free joint of single-degree-of-freedom of the present invention removes the structure chart after truss base；
Fig. 8 is the truss understructure figure of the free joint of two-freedom of the present invention；
Fig. 9 is the structure chart of the free joint of two-freedom of the present invention.
Embodiment
As shown in figure 1, being expandable truss deployed condition, as shown in Fig. 2 being expandable truss rounding state.
A kind of pyrolysis coupling expandable truss system suitable for space plate aerial, including expandable truss 3, rectangular frame
5；Rectangular frame 5 includes base connecting rod, single-degree-of-freedom and dissociated joint 2,7, and two-freedom dissociates joint 4, anchor tip 1；First
Single-degree-of-freedom joint 2, the second single-degree-of-freedom dissociate joint 4 and the anchor tip 1 of joint 7, two-freedom that dissociate that dissociate passes through base
Connecting rod is connected, and is separately mounted on four angle points of rectangular frame 5.Connecting shaft in four joints is connected with antenna structure plate 6,
Truss base 11,26,46 in four joints is linked into an integrated entity by base connecting rod, rectangular frame 5 is constituted, as deployable
The installation foundation of truss.Base connecting rod is carbon fibre pipe fitting.
Rectangular frame 5 passes through anchor tip 1, the free joint 2 of the first single-degree-of-freedom, the free joint 7, two of the second single-degree-of-freedom
The free degree joint 4 that dissociates is connected with antenna structure plate 6, and realizes in junction larger coupling stiffness by disc spring pretension,
It ensure that the connection precision along the normal direction of antenna structure plate 6.Wherein, anchor tip 1 is connected with antenna structure plate 6, and first is single
The free joint 2 of the free degree releases the single-degree-of-freedom constraint along antenna width direction, and the free joint 7 of the second single-degree-of-freedom is released
Constrained along the single-degree-of-freedom of the length direction of antenna structure plate 6, the free joint 4 of two-freedom is released along the width of antenna structure plate 6
Constrained with two frees degree of length direction, as shown in Figure 3.
Expandable truss 3 is a spatial four-bar mechanism.One end of four bars is concatenated by articulated manner in expandable truss 3
Together；There are two bars to possess unfolded function, another two bars are not foldable；Not folding two bars are fixed on outside solid
Determine on device (celestial body)；Dissociate respectively with the free joint 7 of the second single-degree-of-freedom, two-freedom the end of not folding two bars
Joint 4 is connected through the hinge；The end for possessing two connecting rods of unfolded function is single freely with anchor tip 1, first respectively
The free joint 2 of degree is connected through the hinge.
Under expansion lock-out state, expandable truss 3 may make up a stable rectangular pyramid truss knot with rectangular frame 5
Structure, with higher structural support rigidity.In transmit state, two bars for possessing unfolded function are folded, by two certainly
Antenna structure plate 6 is pulled for axle by the free free hinge between joint 7 and celestial body of the single-degree-of-freedom of joint 4 and second of degree, can
Expanded truss 3 draws in together with antenna structure plate 6 and is pressed on external fixation device (celestial body), bears the load of launching phase；
Expansion locking constitutes a stable rectangular pyramid truss structure after entering the orbit, it is ensured that the expansion rigidity of antenna structure plate 6.
Anchor tip 1 is as shown in Figure 4.Anchor tip 1 includes the first truss base 11, the first tabletting 12, first and fixes spiral shell
Follow closely the 13, first gland 14, the first oscillating bearing 15 and the first connecting shaft 16；The outer ring of first oscillating bearing 15 is arranged on the first truss
Positioned in the installation through-hole of base 11 and by the ledge structure in installation through-hole, the first gland 14 is flange arrangement, installed in the
In the installation through-hole of one truss base 11, ring flange is fixed by screw with the first truss base 11, flange arrangement barrel end pressure
The tight outer ring of first oscillating bearing 15；The one end of first connecting shaft 16 is fixed on antenna structure plate 6, and the other end is from the first truss base
11 do not install the side insertion inner ring of the first oscillating bearing 15 of the first gland 14, and the inner ring of the first oscillating bearing 15 is fixed by the shaft shoulder
Position；The end face of the first connecting shaft 16 and the inner ring of the first oscillating bearing 15 are pushed down in first tabletting 12；First fixing screws 13 are located at first
In the centre bore of gland 14, through the through hole of the first tabletting 12, by being threadably mounted at the first connecting shaft 16 along along the through hole of axis,
Head compresses the first tabletting 12；To adapt to, the form variations of antenna structure plate 6 and antenna structure plate 6 are relative with rectangular frame 5 to be missed
Difference, has used the first oscillating bearing 15, to ensure the one preferable mounting plane of formation of rectangular frame 5.
As shown in figure 5, single-degree-of-freedom is dissociated, joint 2,7 includes the second connecting shaft 21, the first end cap 22, the first disc spring tabletting
23rd, the second tabletting 24, the second gland 25, as shown in Figure 6, the free sliding block of the second fixing screws 27, first of the second truss base 26
28th, second joint bearing 29, the first disc spring 210.Connect as shown in fig. 7, being that single-degree-of-freedom after truss base 26 is removed is free
First 2,7 structure chart.
First disc spring 210, the first disc spring tabletting 23 are arranged in the mounting hole of truss base 26, and the first disc spring tabletting 23 is pushed down
The one end of first disc spring 210；First end cap 22 is arranged on the mounting hole port of the second truss base 26, compresses the first disc spring 210 another
One end；First free sliding block 28 is arranged in the mounting hole of truss base 26, compresses and the is installed in the first disc spring tabletting 23, centre bore
Two oscillating bearings 29, the outer ring side of second joint bearing 29 is positioned by ledge structure in the first free centre bore of sliding block 28, separately
Side is compressed by the second gland 25 on the first free centre bore of sliding block 28；Second gland 25 is cylindrical structure, is led to
Being threadably mounted in the first free centre bore of sliding block 28 on the wall of side is crossed, end plane props up the mounting hole top of the second truss base 26
Portion's inwall；Second connecting shaft 21 is vertically fixed on antenna structure plate 6, through the centre bore of the first end cap 22, the first disc spring 210,
The centre bore of first disc spring tabletting 23, end is arranged in the inner ring of second joint bearing 29, and the second fixing screws 27 are arranged on second
The end of connecting shaft 21 simultaneously compresses second joint bearing 29 by the second tabletting 24；
Second connecting shaft 21 and the inner ring of second joint bearing 29, the second tabletting 24, the one of the second fixing screws 27, with second
It can be relatively rotated between the outer ring of oscillating bearing 29, the first free end cap 25 of sliding block 28 and second, to adapt to antenna plate shape
The relative error of shape deviation and antenna plate and framework.When the extraneous load because of transmitting, thermal environment formation is less than the first disc spring 210
During preload, the second truss base 26 and the second connecting shaft 21 and the relative position of antenna structure plate 6 are fixed.Work as the external world
When load is more than the preload of the first disc spring 210, between the second truss base 26 and the second connecting shaft 21 and antenna structure plate 6
Generation Relative sliding, release the internal stress in truss rod, it is ensured that the base shape of truss installa-tion.
Fig. 5 is the free joint of single-degree-of-freedom, the first free sliding block 28, as shown in fig. 7, a word structure quilt raised on outer wall
Flat recess constraint on the mounting hole side wall of second truss base 26, as shown in fig. 6, the free sliding block 28 of limitation can only occur along a word
Left and right displacement occurs for groove direction.
As shown in figure 9, two-freedom dissociates, joint 4 includes the 3rd connecting shaft 41, the second end cap 42, the second disc spring tabletting
43rd, the 3rd tabletting 44, the 3rd gland 45, the 3rd truss base 46, the free sliding block the 48, the 3rd of the 3rd fixing screws 47, second are closed
Bearings 49, the second disc spring 410；Second disc spring 410, the second disc spring tabletting 43 are arranged in the mounting hole of truss base 46, and second
The one end of the second disc spring 410 is pushed down in disc spring tabletting 43；Second end cap 42 is arranged on the mounting hole port of the 3rd truss base 46, compresses
The other end of second disc spring 410；Second free sliding block 48 is arranged in the mounting hole of truss base 46, compresses the second disc spring tabletting 43,
Three-knuckle bearing 49 is installed, the outer ring side of three-knuckle bearing 49 passes through the second free cunning in the second free centre bore of sliding block 48
Ledge structure is positioned in the centre bore of block 48；3rd gland 45 is arranged in the second free centre bore of sliding block 48, and one end compresses the 3rd
The outer ring opposite side of oscillating bearing 49, the other end props up the mounting hole top inner wall of the 3rd truss base 46；3rd connecting shaft 41 is vertical
It is fixed on antenna structure plate 6, through the centre bore of the second end cap 42, the second disc spring 410, the centre bore of the second disc spring tabletting 43, end
Portion is arranged in the inner ring of three-knuckle bearing 49, and the 3rd fixing screws 47 are arranged on the end of the 3rd connecting shaft 41 and by the 3rd pressure
Piece 44 compresses three-knuckle bearing 49；The second free outer wall of sliding block 48 is the face of cylinder, the second free truss bottom of sliding block 48 and the 3rd
There is gap between 46 mounting holes of seat, the second free sliding block 48 is arranged in the mounting hole of the 3rd truss base 46, occurs relative fortune
It is dynamic.
Two-freedom dissociates, and joint 4 is consistent with the structure of the free joint 2,7 of single-degree-of-freedom, and difference is：Two-freedom is swum
Dissociate from second that the free joint 4 of circular hole, two-freedom is only installed on the 3rd truss base 46 (as shown in Figure 8) of joint 4
Sliding block 48 is cylindrical shape, and the second free sliding block 48 is arranged in the mounting hole of the 3rd truss base 46 so that two-freedom joint 4
In the mounting hole of the 3rd truss base 46 in-plane moving occurs for the second free sliding block 48.
Space solid lubrication is employed on the relative part interface slided., can be with by the rigidity Design of disc spring 210,410
Skid force effectively between the relative moving parts of control two.
When the in-orbit experience of system is severe and during complicated thermal environment or during antenna itself operational heat, antenna structure plate 6 will not
Occur with can avoiding to stretch or dilatancy in face, antenna structure plate 6 is with expandable truss mechanism because heterogeneity phantom inequality will
The unmatched thermal deformation of generation, now system should by the sliding release heat in the direction discharged by 4 free joints along the free degree
Power, it is ensured that antenna structure plate 6 does not occur due to distortion caused by thermal stress or even destroyed with expandable truss 3, maintains truss
The type face of mechanism is so as to maintain the pointing accuracy of antenna array.
Unspecified part of the present invention belongs to technology as well known to those skilled in the art.
Claims (8)
1. a kind of pyrolysis coupling expandable truss system suitable for space plate aerial, it is characterised in that including expandable truss
(3), rectangular frame (5)；Rectangular frame (5) includes the free joint (2,7) of base connecting rod, single-degree-of-freedom, two-freedom and dissociates and connect
Head (4), anchor tip (1)；Dissociate joint (2,7), two-freedom of single-degree-of-freedom is free between joint (4) and anchor tip (1)
Connected by base connecting rod；Rectangular frame (5) is swum by anchor tip (1), the free joint (2,7) of single-degree-of-freedom, two-freedom
It is connected from joint (4) with antenna structure plate (6)；Wherein, anchor tip (1) is connected with antenna structure plate (6), and single-degree-of-freedom is dissociated
Joint (2,7) releases the single-degree-of-freedom constraint along antenna width direction, length direction respectively, and two-freedom dissociates joint (4)
Release two frees degree constraint along antenna structure plate (6) width and length direction；Expandable truss (3) includes four bars,
Four bar one end are by rotatable mechanism fixing device same position mounted externally, and the other end is free with single-degree-of-freedom respectively
Dissociate joint (4), anchor tip (1) of joint (2,7), two-freedom is connected by tumbler, and expandable truss (3) has exhibition
Unfold azido functional.
2. a kind of pyrolysis coupling expandable truss system suitable for space plate aerial according to claim 1, its feature
It is：The single-degree-of-freedom joint (2,7) that dissociates has two, is separately mounted on rectangular frame (5) diagonal two-end-point；It is fixed
The free joint (4) of joint (1), two-freedom is separately mounted on another diagonal two-end-point of rectangular frame (5).
3. a kind of pyrolysis coupling expandable truss system suitable for space plate aerial according to claim 1 or 2, it is special
Levy and be：Two bars possess unfolded function in the expandable truss (3), and another two bars are not foldable；It is not folding
Two bars are fixed on external fixation device；Dissociate joint with a single-degree-of-freedom respectively for the end of not folding two bars
The free joint (4) of (2,7), two-freedom is connected by tumbler；Possesses the end part of two connecting rods of unfolded function
The joint (2,7) that do not dissociate with anchor tip (1), another single-degree-of-freedom is connected by tumbler.
4. a kind of pyrolysis coupling expandable truss system suitable for space plate aerial according to claim 1 or 2, it is special
Levy and be：The anchor tip (1) includes the first truss base (11), the first tabletting (12), the first fixing screws (13), first
Gland (14), the first oscillating bearing (15) and the first connecting shaft (16)；First oscillating bearing (15) outer ring is arranged on the first truss
Positioned in base (11) installation through-hole and by the ledge structure in installation through-hole；First gland (14) is flange arrangement, is installed
In first truss base (11) installation through-hole, ring flange and the first truss base (11) are fixed, flange arrangement barrel end pressure
Tight first oscillating bearing (15) outer ring；First connecting shaft (16) one end is fixed on antenna structure plate (6), and the other end is from the first purlin
Frame base (11) is not installed in side insertion the first oscillating bearing (15) inner ring of the first gland (14), the first oscillating bearing (15)
Circle is positioned by the shaft shoulder；The first connecting shaft (16) end face and the first oscillating bearing (15) inner ring are pushed down in first tabletting (12)；First
Fixing screws (13) are located in the first gland (14) centre bore, through the through hole of the first tabletting (12), by being threadably mounted at the
One connecting shaft (16) is along along the through hole of axis, and head compresses the first tabletting (12).
5. a kind of pyrolysis coupling expandable truss system suitable for space plate aerial according to claim 4, its feature
It is：The single-degree-of-freedom dissociates joint (2,7) including the second connecting shaft (21), the first end cap (22), the first disc spring tabletting
(23), the second tabletting (24), the second gland (25), the second truss base (26), the second fixing screws (27), the first free sliding block
(28), second joint bearing (29), the first disc spring (210)；First disc spring (210), the first disc spring tabletting (23) are arranged on truss
In base (26) mounting hole, the first disc spring (210) one end is pushed down in the first disc spring tabletting (23)；First end cap (22) is arranged on second
Truss base (26) mounting hole port, compresses the first disc spring (210) other end；First free sliding block (28) is arranged on truss bottom
In seat (26) mounting hole, compress in the first disc spring tabletting (23), first free sliding block (28) centre bore and second joint bearing is installed
(29), second joint bearing (29) outer ring side is positioned by ledge structure in first free sliding block (28) centre bore；Second pressure
Cover (25) to be arranged in first free sliding block (28) centre bore, one end compresses second joint bearing (29) outer ring opposite side, another
End props up second truss base (26) mounting hole top inner wall；Second connecting shaft (21) is vertically fixed on antenna structure plate (6),
Through the first end cap (22) centre bore, the first disc spring (210), first disc spring tabletting (23) centre bore, end is arranged on second and closed
In bearings (29) inner ring, the second fixing screws (27) are arranged on the second connecting shaft (21) end and pressed by the second tabletting (24)
Tight second joint bearing (29)；A raised word structure is arranged on the second truss base (26) on first free sliding block (28) outer wall
In flat recess on the wall of mounting hole side.
6. a kind of pyrolysis coupling expandable truss system suitable for space plate aerial according to claim 5, its feature
It is：The two-freedom dissociate joint (4) including the 3rd connecting shaft (41), the second end cap (42), the second disc spring tabletting (43),
3rd tabletting (44), the 3rd gland (45), the 3rd truss base (46), the 3rd fixing screws (47), the second free sliding block (48),
Three-knuckle bearing (49), the second disc spring (410)；Second disc spring (410), the second disc spring tabletting (43) are arranged on truss base
(46) in mounting hole, the second disc spring (410) one end is pushed down in the second disc spring tabletting (43)；Second end cap (42) is arranged on the 3rd truss
Base (46) mounting hole port, compresses the second disc spring (410) other end；Second free sliding block (48) is arranged on truss base
(46) in mounting hole, compress in the second disc spring tabletting (43), second free sliding block (48) centre bore and three-knuckle bearing is installed
(49), three-knuckle bearing (49) outer ring side is positioned by ledge structure in second free sliding block (48) centre bore；3rd pressure
Cover (45) to be arranged in second free sliding block (48) centre bore, one end compresses three-knuckle bearing (49) outer ring opposite side, another
End props up the 3rd truss base (46) mounting hole top inner wall；3rd connecting shaft (41) is vertically fixed on antenna structure plate (6),
Through the second end cap (42) centre bore, the second disc spring (410), second disc spring tabletting (43) centre bore, end is arranged on the 3rd and closed
In bearings (49) inner ring, the 3rd fixing screws (47) are arranged on the 3rd connecting shaft (41) end and pressed by the 3rd tabletting (44)
Tight three-knuckle bearing (49)；Second free sliding block (48) outer wall is the face of cylinder, and the second free sliding block (48) is at the 3rd truss bottom
Occurs relative motion in seat (46) mounting hole.
7. a kind of pyrolysis coupling expandable truss system suitable for space plate aerial according to claim 1 or 2, it is special
Levy and be：The base connecting rod is carbon fibre pipe fitting.
8. a kind of pyrolysis coupling expandable truss system suitable for space plate aerial according to claim 5 or 6, it is special
Levy and be：Pass through base connecting rod between the first truss base (11), the second truss base (26), the 3rd truss base (46)
Connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710405393.8A CN107284692B (en) | 2017-05-31 | 2017-05-31 | A kind of pyrolysis coupling expandable truss system suitable for space plate aerial |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710405393.8A CN107284692B (en) | 2017-05-31 | 2017-05-31 | A kind of pyrolysis coupling expandable truss system suitable for space plate aerial |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107284692A true CN107284692A (en) | 2017-10-24 |
| CN107284692B CN107284692B (en) | 2019-09-06 |
Family
ID=60094709
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710405393.8A Active CN107284692B (en) | 2017-05-31 | 2017-05-31 | A kind of pyrolysis coupling expandable truss system suitable for space plate aerial |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107284692B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110112533A (en) * | 2019-06-05 | 2019-08-09 | 哈尔滨工业大学 | A kind of gas-filled unfolded Z-fold array antenna of rigid flexible system support |
| CN111409862A (en) * | 2020-03-10 | 2020-07-14 | 上海卫星工程研究所 | Structure and method for mounting load and star sensor of satellite |
| CN112429275A (en) * | 2020-12-10 | 2021-03-02 | 北京空间机电研究所 | Spacing formula space rotation locking and releasing mechanism |
| CN113734467A (en) * | 2021-11-05 | 2021-12-03 | 北京微焓科技有限公司 | Satellite solar wing |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070044415A1 (en) * | 2005-08-29 | 2007-03-01 | Donald Merrifield | Deployable triangular truss beam with orthogonally-hinged folding diagonals |
| CN102167165A (en) * | 2011-04-11 | 2011-08-31 | 哈尔滨工业大学 | Seven-revolute pair extensible unit and space extensible mechanism using same |
| CN102358435A (en) * | 2011-08-18 | 2012-02-22 | 哈尔滨工业大学 | Truss unit capable of being foldable to launch and being convenient to assemble on orbit |
| CN105799950A (en) * | 2016-03-18 | 2016-07-27 | 燕山大学 | Single-degree-of-freedom overconstrained shear-type deployable unit and space deployable mechanisms composed of same |
| CN105923170A (en) * | 2016-04-26 | 2016-09-07 | 北京空间飞行器总体设计部 | Repeatable folding and unfolding truss structure and cell element thereof |
-
2017
- 2017-05-31 CN CN201710405393.8A patent/CN107284692B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070044415A1 (en) * | 2005-08-29 | 2007-03-01 | Donald Merrifield | Deployable triangular truss beam with orthogonally-hinged folding diagonals |
| CN102167165A (en) * | 2011-04-11 | 2011-08-31 | 哈尔滨工业大学 | Seven-revolute pair extensible unit and space extensible mechanism using same |
| CN102358435A (en) * | 2011-08-18 | 2012-02-22 | 哈尔滨工业大学 | Truss unit capable of being foldable to launch and being convenient to assemble on orbit |
| CN105799950A (en) * | 2016-03-18 | 2016-07-27 | 燕山大学 | Single-degree-of-freedom overconstrained shear-type deployable unit and space deployable mechanisms composed of same |
| CN105923170A (en) * | 2016-04-26 | 2016-09-07 | 北京空间飞行器总体设计部 | Repeatable folding and unfolding truss structure and cell element thereof |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110112533A (en) * | 2019-06-05 | 2019-08-09 | 哈尔滨工业大学 | A kind of gas-filled unfolded Z-fold array antenna of rigid flexible system support |
| CN111409862A (en) * | 2020-03-10 | 2020-07-14 | 上海卫星工程研究所 | Structure and method for mounting load and star sensor of satellite |
| CN112429275A (en) * | 2020-12-10 | 2021-03-02 | 北京空间机电研究所 | Spacing formula space rotation locking and releasing mechanism |
| CN113734467A (en) * | 2021-11-05 | 2021-12-03 | 北京微焓科技有限公司 | Satellite solar wing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107284692B (en) | 2019-09-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107284692A (en) | A kind of pyrolysis coupling expandable truss system suitable for space plate aerial | |
| EP3290344B1 (en) | Toroidal support structures | |
| CN102167165B (en) | Seven-revolute pair extensible unit and space extensible mechanism using same | |
| CN107685880B (en) | Expandable combined unit and large-scale space expandable mechanism composed of same | |
| CN102593571B (en) | Scissors-based quadrilateral unit planar array developable mechanism | |
| CN104009278A (en) | Modularized space parabolic cylinder antenna folding and unfolding mechanism | |
| CN202508286U (en) | Foldable landing buffering mechanism | |
| CN106450649B (en) | A kind of H configuration satellite antenna development agency | |
| US6229501B1 (en) | Reflector and reflector element for antennas for use in outer space and a method for deploying the reflectors | |
| JP2016507419A (en) | Tank holding device in aircraft | |
| CN104698509A (en) | Geostationary orbit meteorological satellite | |
| CN110450983B (en) | Agile satellite configuration | |
| CN109659701B (en) | Truss type synchronous deployable antenna | |
| CN107449581B (en) | Free degree release device for wind tunnel free flight experiment | |
| Shore et al. | A new generation of deployable optics for Earth observation using small satellites | |
| CN104816841B (en) | Satellite unlocks separator | |
| CN202503095U (en) | Scissor-based quadrangle element planar array extendable mechanism | |
| CN112736403B (en) | Deployable double-layer hybrid spatial planar antenna | |
| US4805368A (en) | Expandable pallet for space station interface attachments | |
| CN106229601B (en) | A kind of synchronous deployable trusses of spacecraft flat plane antenna and Method of Adjustment | |
| CN106025488A (en) | Two-dimensional planar antenna unfolding apparatus | |
| CN113258249B (en) | On-orbit ultra-large deployable space structure system | |
| CN112817196B (en) | Large-scale high rigidity lens hood of accomodating that can expand | |
| CN110492220B (en) | Extensible space large-scale telescopic truss unfolding mechanism | |
| RU2349517C1 (en) | Passive docking assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |