CN104590591B - One is novel arrests and retaining mechanism in-orbit - Google Patents
One is novel arrests and retaining mechanism in-orbit Download PDFInfo
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- CN104590591B CN104590591B CN201510007463.5A CN201510007463A CN104590591B CN 104590591 B CN104590591 B CN 104590591B CN 201510007463 A CN201510007463 A CN 201510007463A CN 104590591 B CN104590591 B CN 104590591B
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Abstract
The present invention provides a kind of and novel arrests in-orbit and retaining mechanism, this mechanism is by the stage of arresting, axis rotation correction stage, locking stage and release separation phase, effectively extraterrestrial target can be arrested and lock, especially solve the angle allowance that spacecraft rotates about the axis, finally ensure to be arrested rapidly by extraterrestrial target aircraft and lock, thus be conducive to improving the level of China's service technology in-orbit.
Description
Technical field
The invention belongs to extraterrestrial target and arrest field in-orbit, relate to the design to target aircraft arresting agency in-orbit, special
Not being the control when target aircraft is arrested in-orbit and furthered around axis direction rotation tolerance situation, mechanism is permissible
Effectively give and solution, finally realize target aircraft being arrested and locking.
Background technology
Spacecraft plays an important role in the national economy and defence and military of China, is that China obtains spatial information
One of Main Means.Along with the fast development of Chinese Space science and technology, Some Key Technologies has reached or close to external
Advanced level.Aircraft service technology in-orbit has extremely strong military background, can provide quick, high for following space militarization
The logistics support of effect, and can directly implement target to arrest, attack, thus increase substantially the anti-war ability in space.
At present, in China's aircraft service technology system in-orbit, extraterrestrial target aircraft is arrested in-orbit the process of technology
Not being the most perfect, the angle allowance rotated about the axis in capture process can not well control, in the mistake arrested and locked
Cheng Buneng processes fast and effectively, thus affects function and the efficiency of the arresting agency in-orbit of extraterrestrial target, it is impossible to ensure flight
The function of device.
Summary of the invention
It is an object of the invention to provide a set of novel arresting in-orbit and retaining mechanism, solve spacecraft and revolve around axis
The angle allowance problem turned.
The present invention uses following methods to be attained in that
One is novel arrests and retaining mechanism, in-orbit including pedestal one main support 1, flexible axle 2, electric rotating machine assembly 3, pedestal
One 4, transmission component 1, sleeve assembly 6, runner assembly 1, pedestal 28, automatic aligning bar 9, preload detent assembly 10,
Spring loads probe assembly 11, runner assembly 2 12, screw arbor assembly 13, transmission component 2 14, locking motor assembly 15, locking electricity
Machine support 16, leading screw 17, pedestal one auxiliary stand 18, mair motor 19, transmission system 20, lead screw shaft bearing 21, connect seat 22, auxiliary
Help axle 23, actuator beairng 24, actuator beairng seat 25, actuator base 26, correcting motor 27, electric rotating machine shaft coupling
Device 28, electric rotating machine connecting shaft 29, gear 1, gear 2 31, turnbarrel 32, turnbarrel bearing 33, turnbarrel axle
Bearing 34, firm docking probe 35, spring 36, end cap 37, preloading detent 38, preloading detent pedestal 39, locking motor
40, locking motor shaft coupling 41, locking motor connecting shaft 42, gear 3 43, gear 4 44, locking sleeve assembly 45, locking silk
Thick stick 46, tie down screw 47, locking sleeve bearing 48, locking sleeve bearing block 49；On the basis of entering pedestal one main support 1, successively
Transmission system 20, mair motor 19, lead screw shaft bearing 21, actuator beairng 24, leading screw 17, asessory shaft 23 are installed, connect seat 22
With flexible axle 2；On the basis of pedestal 28, automatic aligning bar 9, spring loading probe assembly 11 are installed successively, preload detent
10, locking motor support 16, locking motor assembly 15, transmission component 2 14, screw arbor assembly 13 and runner assembly 2 12；Wherein base
Seat one main support 1, leading screw 17 and pedestal 1 match, for the position of fixed pedestal one and the smooth transmission of guarantee power；Soft
Axle 2 and pedestal 1 match, for arresting space in-orbit；Electric rotating machine assembly 3, runner assembly 1, sleeve assembly
6, pedestal 28, automatic aligning bar 9, preloading detent assembly 10 and spring loading probe assembly 11 match, for by space
Target aircraft carries out the correction of attitude；Pedestal 28, runner assembly 2 12, screw arbor assembly 13, transmission component 2 14, locking electricity
Thermomechanical components 15 and locking motor support 16 match, for being locked by extraterrestrial target aircraft；
Described electric rotating machine assembly 3 is mainly made up of correcting motor 27, rotating machine coupling 28 and corresponding key,
Under the rotation of correcting motor 27, by rotating machine coupling 28, the rotary motion of motion motor is transferred to transmission component；
Described transmission system 20 includes gear, axle, flat key and installing plate；
Described transmission component 1, transmission component 2 14 are main by rotating machine coupling 28 and corresponding key and rotation
Rotating motor connecting shaft 29, locking motor connecting shaft 43 form, and mainly the rotary motion of motor are transferred to gear 1 and tooth
Take turns on 3 43；
Described runner assembly 1, runner assembly 2 12 are main by gear 1 and gear 2 31 or gear 3 43 and
Gear 4 44 and corresponding key and rotating machine coupling 28, preloading detent 38 form, in runner assembly 1 and rotation
Under the effect of assembly 2 12, gear 1 and gear 2 31 or gear 3 43 and gear 4 44 is driven to be meshed, for correction appearance
State or lock ready；
Described sleeve assembly 6 is mainly made up of turnbarrel bearing block 34, turnbarrel 32 and turnbarrel bearing 33,
When target aircraft is carried out attitude updating, act primarily as the intermediate axle beam effect of transmission power；
Described latch assembly is mainly by locking motor support 16, locking motor 40, locking motor shaft coupling 41, locking electricity
Machine connecting shaft 42, gear 3 43, gear 4 44, locking screw 46, tie down screw 47 and locking sleeve bearing 48 and lock sleeve
Cylinder bearing block 49 forms, and locking motor 40 rotates, and drives locking motor shaft coupling 41, locking motor connecting shaft 42 and gear 3 43
Rotate together, be meshed by gear 3 43 and gear 4 44, and then drive locking sleeve to rotate, in tie down screw 47 and locking
Under the cooperation of sleeve and locking screw 46, screw rod screws out slowly the most at last；
Described spring loads probe assembly 11 mainly by firm docking probe 35, spring 36, hollow multidiameter and corresponding
End cap 37 forms, and spring loads in probe and is provided with spring, is with outward end cap 37 and fixes, by process close for target aircraft
In, target's center's cone contacts with firm docking probe 35, on the one hand reduces the impact between aircraft and eliminates gap, on the other hand
Spring pressurized, stores energy, separates for later release and prepares；
Described preloading detent assembly 10 is mainly by preloading detent 38, preloading detent pedestal 39 and corresponding
Torsion spring composition；Described spring loads probe assembly 11 mainly by firm docking probe 35, spring 36 and corresponding end cap 37 groups
Becoming, spring loads the centre of probe and is provided with spring, is with outward end cap 37 and fixes；Preload detent pedestal 39 to install and fix
On pedestal 28, preload detent 38 be arranged on preloading detent pedestal 39 on, firm docking probe 35 by impact to
Rear motion, now, firm docking probe 35 contacts with preloading detent 38 and makes the torsion spring stress in preloading detent 38, from
And reduce the impact of two aircraft；
When target aircraft is within the scope of arresting, mair motor 19 starts, through transmission system 20 by the rotation of motor
Motion is transferred on leading screw 17, by leading screw 17 and the cooperation being connected seat 22, by the convert rotational motion of leading screw 17 for connecting seat
The linear motion of 22；Connect seat 22 and flexible axle 2 and is connected seat 22 with under the cooperation of asessory shaft 23, finally realization connection seat 22 and
Flexible axle 2 moves along a straight line together；When flexible axle 2 slowly stretches to the locked position of target's center's cone and after completing to be flexible coupling, main
Motor 19 inverts, and is retracted by flexible axle 2 together with target aircraft；If automatic aligning bar 9 is not within the scope of anti-roll cover, correction
Motor 27 starts to start, and through transmission component 5, the rotary motion of correcting motor 27 is transferred to runner assembly 1 and sleeve assembly
On 6, final sleeve assembly band moving base 28 rotates together with the assembly above it so that automatic aligning bar 9 is at the model of anti-roll cover
Within enclosing；Along with target aircraft continues to further, automatic aligning bar 9 contacts with anti-roll cover, and target aircraft is carried out attitude
Correction；Meanwhile, spring loads probe assembly 11 and alleviates impact the pressurized storage capacity of two aircraft contacts, eliminates gap；When
After automatic aligning bar 9 enters to automatic aligning socket, locking motor assembly 15 starts, through transmission component 2 14, rotating group
Part 2 12, locking sleeve assembly 45 and locking motor assembly 15 and the cooperation of screw arbor assembly 13, the most at last screw rod screw out and with
Automatic aligning socket locks；When target aircraft needs release to separate, locking motor assembly 15 inverts, by screw rod from certainly
Dynamic alignment socket screws out, under the effect of the spring restoring force in spring loads probe assembly, is bored by target's center and bullet
Spring loads the contact of probe assembly 11 and two aircraft releases is separated.
Further, flexible axle 2 be connected seat 22, connect seat and asessory shaft 23 and leading screw 17 coordinate formed complete stretching
Mechanism；Under the work of mair motor 19, the rotary motion of motor is transferred to leading screw 17, through leading screw 17 be connected seat 22, even
Joint chair 22 and flexible axle 2 and be connected coordinating of seat 22 and asessory shaft 23, the convert rotational motion of mair motor 19 is flexible axle 2 the most at last
Linear motion, during this, the pitch of leading screw 17 be designed as 2mm, a length of 1800mm, connect seat 22 thickness be 20mm and
Asessory shaft 23 centre-to-centre spacing flexible axle 2 center 45mm, selects away from the position that leading screw 17 is 60mm.
Further, start at correcting motor 27, after selection campaign is transferred to pedestal 28 by transmission component 1, pedestal
The end angular velocity of rotation of 28 should be not more thanRad/s, thus ensure can there be enough time after correcting in the range of 360 °
Lock.
Further, after locking motor 40 starts, after locking motor 40 rotary motion is transferred to tie down screw 47, locking screw
The pace of bar 47 is not less than 2mm/s, it is ensured that have enough time to lock；The speed regained, not less than 4mm/s, is used for protecting
Card can quick release release.
Further, if automatic aligning bar 9 is not within the scope of anti-roll cover, correcting motor 27 starts to start, through transmission
The rotary motion of correcting motor 27 is transferred to runner assembly 1 by assembly 5, by gear 1 and the engagement of gear 2 31, rotation
Transhipment is dynamic to be further transferred on sleeve assembly 6, and final sleeve assembly band moving base 28 rotates together with the assembly above it,
Make automatic aligning bar 9 within the scope of anti-roll cover.
Extraterrestrial target, by this novel arresting in-orbit and retaining mechanism, effectively can be arrested and lock by the present invention
Tightly, especially solving the angle allowance that spacecraft rotates about the axis, extraterrestrial target aircraft is grabbed by final guarantee rapidly
Catch and lock, thus be conducive to improving the level of China's service technology in-orbit.
Accompanying drawing explanation
Fig. 1 is that the present invention assembles structural representation；
Fig. 2 is position relationship schematic diagram between mair motor, transmission device, flexible axle and mounting bracket；
Fig. 3 is automatic aligning bar, spring loading probe, position relationship signal between electric rotating machine assembly and correction assembly
Figure；
Fig. 4 is Standard schematic diagram between latch assembly, transmission component, runner assembly and screw rod；
Fig. 5, Fig. 6 are that target is arrested and the process schematic of active correction attitude by flexible axle；
Fig. 7, Fig. 8 are the locking to target aircraft and release isolating construction schematic diagram.
Detailed description of the invention
Below by way of the concrete application implementation structure arrested with retaining mechanism novel to the present invention and function, capture process,
Locking process and release separation process are described in detail.
1, the novel assembly relation arrested with retaining mechanism critical piece and function (Fig. 1)
One is novel arrests and retaining mechanism, in-orbit including pedestal one main support 1, flexible axle 2, electric rotating machine assembly 3, pedestal
One 4, transmission component 1, sleeve assembly 6, runner assembly 1, pedestal 28, automatic aligning bar 9, preload detent assembly 10,
Spring loads probe assembly 11, runner assembly 2 12, screw arbor assembly 13, transmission component 2 14, locking motor assembly 15, locking electricity
Machine support 16, leading screw 17, pedestal one auxiliary stand 18, mair motor 19, transmission system 20, lead screw shaft bearing 21, connect seat 22, auxiliary
Help axle 23, actuator beairng 24, actuator beairng seat 25, actuator base 26, correcting motor 27, electric rotating machine shaft coupling
Device 28, electric rotating machine connecting shaft 29, gear 1, gear 2 31, turnbarrel 32, turnbarrel bearing 33, turnbarrel axle
Bearing 34, firm docking probe 35, spring 36, end cap 37, preloading detent 38, preloading detent pedestal 39, locking motor
40, locking motor shaft coupling 41, locking motor connecting shaft 42, gear 3 43, gear 4 44, locking sleeve assembly 45, locking silk
Thick stick 46, tie down screw 47, locking sleeve bearing 48, locking sleeve bearing block 49；On the basis of entering pedestal one main support 1, successively
Transmission system 20, mair motor 19, lead screw shaft bearing 21, actuator beairng 24, leading screw 17, asessory shaft 23 are installed, connect seat 22
With flexible axle 2；On the basis of pedestal 28, automatic aligning bar 9, spring loading probe assembly 11 are installed successively, preload detent
10, locking motor support 16, locking motor assembly 15, transmission component 2 14, screw arbor assembly 13 and runner assembly 2 12；Wherein base
Seat one main support 1, leading screw 17 and pedestal 1 match, for the position of fixed pedestal one and the smooth transmission of guarantee power；Soft
Axle 2 and pedestal 1 match, for arresting space in-orbit；Electric rotating machine assembly 3, runner assembly 1, sleeve assembly
6, pedestal 28, automatic aligning bar 9, preloading detent assembly 10 and spring loading probe assembly 11 match, for by space
Target aircraft carries out the correction of attitude；Pedestal 28, runner assembly 2 12, screw arbor assembly 13, transmission component 2 14, locking electricity
Thermomechanical components 15 and locking motor support 16 match, for being locked by extraterrestrial target aircraft；
Electric rotating machine assembly 3 is mainly made up of correcting motor 27, rotating machine coupling 28 and corresponding key, at correction electricity
Under the rotation of machine 27, by rotating machine coupling 28, the rotary motion of motion motor is transferred to transmission component；
Transmission system 20 includes gear, axle, flat key and installing plate；
Transmission component 1, transmission component 2 14 are mainly by rotating machine coupling 28 and corresponding key and electric rotating machine
Connecting shaft 29, locking motor connecting shaft 43 form, and the rotary motion of motor is mainly transferred to gear 1 and gear 3 43
On；
Runner assembly 1, runner assembly 2 12 are main by gear 1 and gear 2 31 or gear 3 43 and gear four
44 and corresponding key and rotating machine coupling 28, preload detent 38 and form, at runner assembly 1 and runner assembly two
Under the effect of 12, gear 1 and gear 2 31 or gear 3 43 and gear 4 44 is driven to be meshed, for correction attitude or lock
The most ready；
Sleeve assembly 6 is mainly made up of turnbarrel bearing block 34, turnbarrel 32 and turnbarrel bearing 33, to mesh
When mark aircraft carries out attitude updating, act primarily as the intermediate axle beam effect of transmission power；
Latch assembly is mainly connected by locking motor support 16, locking motor 40, locking motor shaft coupling 41, locking motor
Axle 42, gear 3 43, gear 4 44, locking screw 46, tie down screw 47 and locking sleeve bearing 48 and locking sleeve bearing
Seat 49 composition, locking motor 40 rotates, and drives locking motor shaft coupling 41, locking motor connecting shaft 42 to revolve together with gear 3 43
Turn, be meshed by gear 3 43 and gear 4 44, and then drive locking sleeve to rotate, at tie down screw 47 and locking sleeve and
Under the cooperation of locking screw 46, screw rod screws out slowly the most at last；
Spring loads probe assembly 11 mainly by firm docking probe 35, spring 36, hollow multidiameter and corresponding end cap 37
Composition, spring loads in probe and is provided with spring, is with outward end cap 37 and fixes, during target aircraft is close,
Target's center's cone contacts with firm docking probe 35, on the one hand reduces the impact between aircraft and eliminates gap, on the other hand bullet
Spring pressurized, stores energy, separates for later release and prepares；
Preload detent assembly 10 mainly by preloading detent 38, preloading detent pedestal 39 and corresponding torsion spring
Composition；Described spring loads probe assembly 11 and is mainly made up of firm docking probe 35, spring 36 and corresponding end cap 37, spring
The centre loading probe is provided with spring, is with outward end cap 37 and fixes；Preload detent pedestal 39 and be mounted and fixed on pedestal
On 28, preload detent 38 and be arranged on preloading detent pedestal 39, transported backward by impact at firm docking probe 35
Dynamic, now, firm docking probe 35 contacts with preloading detent 38 and makes the torsion spring stress in preloading detent 38, thus subtracts
The impact of little two aircraft.
2, novel arrest and retaining mechanism capture process explanation
In capture process, two stages can be divided into: detection-phase and arrest the stage.
1) detection-phase
Under the detection of detection device, if target aircraft is not within arresting, servicing aircraft keeps and carries out
The adjustment of attitude, until making target aircraft within the scope of arresting；If target aircraft is within the scope of arresting, drive main
Motor 19 prepares to start working.
2) arrest the stage
Mair motor 19 starts, and the rotary motion of motor is transferred on leading screw 17 through transmission system 20, leading screw 17 two ends
There are actuator beairng 24 and actuator beairng seat 25 that leading screw is positioned respectively；By leading screw 17 and joining of being connected seat 22
Close, be the linear motion connecting seat 22 by the convert rotational motion of leading screw 17；Connect seat 22 and flexible axle 2 and be connected seat 22 with auxiliary
Help under the cooperation of axle 23, finally realize asessory shaft 23 and provide track for the linear motion connecting seat 22, connect seat 22 and flexible axle 2 one
Rise and move along a straight line.When flexible axle 2 slowly stretches to the locked position of target's center's cone and after completing to be flexible coupling, and mair motor 19 is anti-
Turn, flexible axle 2 is retracted together with target aircraft.
3, novel arresting locks procedure declaration with retaining mechanism
During locking, two stages can be divided into: axis rotation correction stage and locking stage.
1) the axis rotation correction stage
After target aircraft is furthered, under the detection of detection device, it is judged that whether automatic aligning bar 9 flies in target
Within the anti-roll cover scope of row device.
If within scope, then without carrying out rotation correction；If automatic aligning bar 9 is not within the scope of anti-roll cover, school
Positive motor 27 starts to start, and through transmission component 1, the rotary motion of correcting motor 27 is transferred to runner assembly 1, passes through
Gear 1 and the engagement of gear 2 31, rotary motion is further transferred on sleeve assembly 6, final sleeve assembly band moving base
28 rotate together with the assembly above it so that automatic aligning bar 9 is within the scope of anti-roll cover.
2) the locking stage
Along with target aircraft continues to further, automatic aligning bar 9 contacts with anti-roll cover, and target aircraft is carried out attitude
Correction；Meanwhile, target's center's cone loads probe assembly 11 with spring and contacts, on the one hand the impact of buffering two aircraft contact, separately
On the one hand spring 36 pressurized during spring loads probe assembly storage capacity, eliminate gap, and prepare for separating release.
After automatic aligning bar 9 enters to automatic aligning socket, locking motor 40 starts, through transmission component 2 14,
Runner assembly 2 12 and the cooperation of locking sleeve assembly 45, finally tie down screw 47 is screwed out also by the effect at locking motor 40
Lock with automatic aligning socket.
4, novel arresting discharges separation process explanation with retaining mechanism
When target aircraft needs release to separate, locking motor 40 inverts, by tie down screw 47 from automatic aligning socket
Middle back-out, under the restoring force of the spring 36 in spring loads probe assembly, loads probe group by target's center's cone with spring
Two aircraft releases are separated by the contact of part 11.
Claims (5)
1. novel arrest in-orbit and retaining mechanism for one kind, it is characterised in that: include pedestal one main support (1), flexible axle (2), rotate
Electric machine assembly (3), pedestal one (4), transmission component one (5), sleeve assembly (6), runner assembly one (7), pedestal two (8), automatically
Alignment rod (9), preloading detent assembly (10), spring load probe assembly (11), runner assembly two (12), screw arbor assembly
(13), transmission component two (14), locking motor assembly (15), locking motor support (16), leading screw (17), pedestal one auxiliary stand
(18), mair motor (19), transmission system (20), lead screw shaft bearing (21), connection seat (22), asessory shaft (23), transmission device axle
Hold (24), actuator beairng seat (25), actuator base (26), correcting motor (27), rotating machine coupling (28), rotation
Rotating motor connecting shaft (29), gear one (30), gear two (31), turnbarrel (32), turnbarrel bearing (33), turnbarrel
Bearing block (34), firm docking probe (35), spring (36), end cap (37), preloading detent (38), preloading detent pedestal
(39), locking motor (40), locking motor shaft coupling (41), locking motor connecting shaft (42), gear three (43), gear four
(44), locking sleeve assembly (45), locking screw (46), tie down screw (47), locking sleeve bearing (48), locking sleeve bearing
Seat (49)；On the basis of pedestal one main support (1), transmission system (20), mair motor (19), lead screw shaft bearing are installed successively
(21), actuator beairng (24), leading screw (17), asessory shaft (23), connection seat (22) and flexible axle (2)；With pedestal two (8) as base
Standard, installation automatic aligning bar (9) successively, spring loading probe assembly (11), preloading detent assembly (10), locking motor prop up
Frame (16), locking motor assembly (15), transmission component two (14), screw arbor assembly (13) and runner assembly two (12)；Wherein pedestal
One main support (1), leading screw (17) and pedestal one (4) match, for the position of fixed pedestal one and the smooth biography of guarantee power
Pass；Flexible axle (2) and pedestal one (4) match, for arresting space in-orbit；Electric rotating machine assembly (3), runner assembly one
(7), sleeve assembly (6), pedestal two (8), automatic aligning bar (9), preloading detent assembly (10) and spring load probe group
Part (11) matches, for extraterrestrial target aircraft carries out the correction of attitude；Pedestal two (8), runner assembly two (12), screw rod
Assembly (13), transmission component two (14), locking motor assembly (15) and locking motor support (16) match, for by space mesh
Mark aircraft locking；
Described electric rotating machine assembly (3) is mainly made up of correcting motor (27), rotating machine coupling (28) and corresponding key,
Under the rotation of correcting motor (27), by rotating machine coupling (28), the rotary motion of motion motor is transferred to transmission group
Part；
Described transmission system (20) includes gear, axle, flat key and installing plate；Described transmission component one (5), transmission component two
(14) main by rotating machine coupling (28) and corresponding key and electric rotating machine connecting shaft (29), locking motor connecting shaft
(42) composition, is mainly transferred to the rotary motion of motor on gear one (30) and gear three (43)；
Described runner assembly one (7), runner assembly two (12) are main by gear one (30) and gear two (31) or gear three
(43) and gear four (44) and corresponding key and rotating machine coupling (28), preload detent (38) composition, rotating
Under the effect of assembly one (7) and runner assembly two (12), drive gear one (30) and gear two (31) or gear three (43) and
Gear four (44) is meshed, for correcting attitude or locking ready；
Described sleeve assembly (6) is main by turnbarrel bearing block (34), turnbarrel (32) and turnbarrel bearing (33) group
Become, when target aircraft is carried out attitude updating, act primarily as the intermediate axle beam effect of transmission power；
Described locking motor support (16), locking motor (40), locking motor shaft coupling (41), locking motor connecting shaft
(42), gear three (43), gear four (44), locking screw (46), tie down screw (47) and locking sleeve bearing (48) and lock
Tight sleeve bearing seat (49) composition latch assembly, locking motor (40) rotates, and drives locking motor shaft coupling (41), locking motor
Connecting shaft (42) rotates together with gear three (43), is meshed by gear three (43) and gear four (44), and then drives locking
Sleeve rotating, at tie down screw (47) with under the cooperation of locking sleeve and locking screw (46), screw rod screws out slowly the most at last；
Described spring loads probe assembly (11) mainly by firm docking probe (35), spring (36), hollow multidiameter and corresponding
End cap (37) composition, spring load probe in spring is installed, be with outward end cap (37) fix, target aircraft is close
During, target's center's cone contacts with firm docking probe (35), on the one hand reduces the impact between aircraft and eliminates gap,
On the other hand spring pressurized, stores energy, separates for later release and prepares；
Described preloading detent assembly (10) is mainly by preloading detent (38), preloading detent pedestal (39) and phase
The torsion spring composition answered；Described spring loads probe assembly (11) mainly by firm docking probe (35), spring (36) and accordingly
End cap (37) forms, and spring loads the centre of probe and is provided with spring, is with outward end cap (37) and fixes；Preload detent pedestal
(39) it is mounted and fixed on pedestal two (8), preloads detent (38) and be arranged in preloading detent pedestal (39), firmly
Docking probe (35) is by impact rearward movement, and now, firm docking probe (35) contacts with preloading detent (38) and makes pre-
Load the torsion spring stress in detent (38), thus reduce the impact of two aircraft；
When target aircraft is within the scope of arresting, mair motor (19) starts, through transmission system (20) by the rotation of motor
Motion is transferred on leading screw (17), by leading screw (17) and the cooperation being connected seat (22), by the convert rotational motion of leading screw (17)
For connecting the linear motion of seat (22)；Connect seat (22) with flexible axle (2) and be connected seat (22) with under the cooperation of asessory shaft (23),
Final realization connects seat (22) and moves along a straight line together with flexible axle (2)；When flexible axle (2) slowly stretches to the locking of target's center's cone
Position after completing to be flexible coupling, mair motor (19) inverts, and is retracted by flexible axle (2) together with target aircraft；If automatic aligning
Bar (9) is not within the scope of anti-roll cover, and correcting motor (27) starts to start, through transmission component one (5) by correcting motor
(27) rotary motion is transferred on runner assembly one (7) and sleeve assembly (6), final sleeve assembly band moving base two (8) and
Assembly above it rotates together so that automatic aligning bar (9) is within the scope of anti-roll cover；Along with target aircraft continues
Furthering, automatic aligning bar (9) contacts with anti-roll cover, and target aircraft is carried out attitude updating；Meanwhile, spring loads probe assembly
(11) alleviate impact the pressurized storage capacity of two aircraft contacts, eliminate gap；When automatic aligning bar (9) enter to the most right
After neat socket, locking motor assembly (15) starts, through transmission component two (14), runner assembly two (12), locking sleeve group
Part (45) and locking motor assembly (15) and the cooperation of screw arbor assembly (13), the most at last screw rod screw out and with automatic aligning socket
Lock；When target aircraft needs release to separate, locking motor assembly (15) inverts, by screw rod from automatic aligning socket
Middle back-out, under the effect of the spring restoring force in spring loads probe assembly, loads probe by target's center's cone with spring
Two aircraft releases are separated by the contact of assembly (11).
One the most according to claim 1 is novel arrests and retaining mechanism in-orbit, it is characterised in that: flexible axle (2) be connected
Seat (22), connect seat and asessory shaft (23) and leading screw (17) coordinate formed complete telescoping mechanism；At mair motor (19)
Under work, the rotary motion of motor is transferred to leading screw (17), through leading screw (17) be connected seat (22), connect seat (22) with soft
Axle (2) and connect seat (22) and the coordinating of asessory shaft (23), the convert rotational motion of mair motor (19) is flexible axle (2) the most at last
Linear motion, during this, the pitch of leading screw (17) be designed as 2mm, a length of 1800mm, connect seat (22) thickness be
20mm and asessory shaft (23) centre-to-centre spacing flexible axle (2) center 45mm, the position away from leading screw (17) 60mm selects.
One the most according to claim 1 is novel arrests and retaining mechanism in-orbit, it is characterised in that: in correcting motor (27)
Starting, after selection campaign is transferred to pedestal two (8) by transmission component one (5), the end angular velocity of rotation of pedestal two (8) should
It is not more thanRad/s, thus ensure enough time can be had to lock after correcting in the range of 360 °.
One the most according to claim 1 is novel arrests and retaining mechanism in-orbit, it is characterised in that: locking motor (40) opens
After Dong, after locking motor (40) rotary motion is transferred to tie down screw (47), the pace of tie down screw (47) is not less than
2mm/s, it is ensured that have enough time to lock；The speed regained, not less than 4mm/s, is used for guaranteeing quick release release.
One the most according to claim 1 is novel arrests and retaining mechanism in-orbit, it is characterised in that: if automatic aligning bar
(9) not within the scope of anti-roll cover, correcting motor (27) starts to start, through transmission component one (5) by correcting motor (27)
Rotary motion be transferred to runner assembly one (7), by gear one (30) and the engagement of gear two (31), rotary motion enters one
Step is transferred on sleeve assembly (6), and final sleeve assembly band moving base two (8) rotates together with the assembly above it so that from
Dynamic alignment rod (9) is within the scope of anti-roll cover.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510007463.5A CN104590591B (en) | 2015-01-08 | 2015-01-08 | One is novel arrests and retaining mechanism in-orbit |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510007463.5A CN104590591B (en) | 2015-01-08 | 2015-01-08 | One is novel arrests and retaining mechanism in-orbit |
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| Publication Number | Publication Date |
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| CN104590591A CN104590591A (en) | 2015-05-06 |
| CN104590591B true CN104590591B (en) | 2016-09-07 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105000199B (en) * | 2015-07-17 | 2016-11-30 | 兰州空间技术物理研究所 | A kind of space is with small-sized butt-joint locking device |
| CN105035369B (en) * | 2015-08-14 | 2017-07-28 | 西北工业大学 | A kind of allosteric type module leading screw self-locking plane connecting equipment |
| CN110104226A (en) * | 2019-04-25 | 2019-08-09 | 北京控制工程研究所 | A kind of satellites coupling is berthed and make-up system |
| CN113998153A (en) * | 2021-11-17 | 2022-02-01 | 南京理工大学 | Universal butt joint device for cubic satellite |
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| CN203806151U (en) * | 2014-03-20 | 2014-09-03 | 西北工业大学 | Modularized jointing and serving unit for miniaturized spacecraft |
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| EP0349333A2 (en) * | 1988-07-01 | 1990-01-03 | General Electric Company | Coupling arrangements |
| WO1991006473A1 (en) * | 1989-10-31 | 1991-05-16 | Space Industries, Inc. | Capture/berthing system for spacecraft |
| US6969030B1 (en) * | 2004-07-14 | 2005-11-29 | Macdonald Dettwiler Space And Associates Inc. | Spacecraft docking mechanism |
| CN101327850A (en) * | 2008-07-30 | 2008-12-24 | 哈尔滨工业大学 | Under-actuated three-arm non-cooperative target docking capture apparatus |
| CN101722510A (en) * | 2009-11-30 | 2010-06-09 | 哈尔滨工业大学 | High-tolerance flexibility capture mechanism for space environment |
| CN102294690A (en) * | 2011-05-12 | 2011-12-28 | 哈尔滨工业大学 | Large-tolerance docking acquisition device focused on space large mechanical arm and rendezvous and docking |
| CN203806151U (en) * | 2014-03-20 | 2014-09-03 | 西北工业大学 | Modularized jointing and serving unit for miniaturized spacecraft |
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| CN104590591A (en) | 2015-05-06 |
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