CN107933974A - The catapult technique of satellite return capsule and its main parachute - Google Patents
The catapult technique of satellite return capsule and its main parachute Download PDFInfo
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- CN107933974A CN107933974A CN201711396591.9A CN201711396591A CN107933974A CN 107933974 A CN107933974 A CN 107933974A CN 201711396591 A CN201711396591 A CN 201711396591A CN 107933974 A CN107933974 A CN 107933974A
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- lock
- return capsule
- main parachute
- locking mechanism
- nacelle
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- 239000002775 capsule Substances 0.000 title claims abstract description 127
- 238000000034 method Methods 0.000 title claims abstract description 13
- 230000007246 mechanism Effects 0.000 claims abstract description 64
- 230000005540 biological transmission Effects 0.000 claims description 23
- 230000033001 locomotion Effects 0.000 claims description 13
- 238000001179 sorption measurement Methods 0.000 description 9
- 230000000694 effects Effects 0.000 description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 6
- 238000005422 blasting Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 229910052742 iron Inorganic materials 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000005191 phase separation Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000004064 recycling Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 241000252254 Catostomidae Species 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 210000000988 bone and bone Anatomy 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/62—Deployment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/62—Deployment
- B64D17/70—Deployment by springs
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Lock And Its Accessories (AREA)
- Toys (AREA)
Abstract
The present invention provides a kind of satellite return capsule, including：Return capsule nacelle, the top of the return capsule nacelle set top flange；Main parachute bucket, is arranged in the return capsule nacelle, has main parachute in the main parachute bucket；And ejection structure, including locking mechanism and lock, the locking mechanism and the lock be respectively arranged at the top flange with the main parachute bucket；The locking mechanism is contacted with the lock, and the main parachute bucket is locked in the return capsule nacelle；During ejection, the locking mechanism departs from the lock, and to unlock the return capsule nacelle and the main parachute bucket, the main parachute bucket is ejected from the return capsule nacelle.It can be ejected safely from return capsule nacelle under the pulling force of main parachute and main parachute bucket in parachute.The present invention also provides a kind of catapult technique of main parachute in satellite return capsule.
Description
Technical field
The present invention relates to satellite launch technical field, more particularly to the ejection of a kind of satellite return capsule and its main parachute
Method.
Background technology
At present, the separation of main parachute bucket and satellite return capsule often uses the ejection mode of blasting bolt.This separation
Technology application it is more mature, the advantages of blasting bolt is large carrying capacity, simple in structure, reliable operation, easy to use, deficiency
Part is to generally require multiple bolts, and it is difficult larger to ensure that whole bolts simultaneously switch off.In addition also to ensure residual when bolt disconnects
The bones of the body do not injure the structure and equipment of surrounding, therefore should correspondingly set protection structure if necessary.Satellite return capsule can so be increased
Volume and weight, increase the degree of difficulty of its return.
The content of the invention
Based on this, it is necessary to for caused by being simultaneously switched off by multiple blasting bolts realize the ejection of main parachute bucket at present
Difficult big problem, there is provided a kind of satellite return capsule of main parachute ejection, while main landing in a kind of satellite return capsule is also provided
The catapult technique of umbrella.
Above-mentioned purpose is achieved through the following technical solutions：
A kind of satellite return capsule, including：
Return capsule nacelle, the top of the return capsule nacelle set top flange；
Main parachute bucket, is arranged in the return capsule nacelle, has main parachute in the main parachute bucket；And
Ejection structure, including locking mechanism and lock, the locking mechanism are respectively arranged at the top with the lock
On flange and the main parachute bucket；The locking mechanism is contacted with the lock, and the main parachute bucket is locked in described return
In reboard nacelle；During ejection, the locking mechanism departs from the lock, to unlock the return capsule nacelle and the main parachute
Bucket, the main parachute bucket are ejected from the return capsule nacelle.
In one of the embodiments, the locking mechanism includes electromagnet, magnet sucking disc and connects with the magnet sucking disc
The connecting rod connect, the electromagnet can adsorb the magnet sucking disc, one end of the connecting rod and the magnetic when powering off
Iron sucker connects；
The lock has lock slots, and the connecting rod, which can block, sets or depart from the lock slots；The electromagnet
After energization, the magnet sucking disc makes the connecting rod depart from the lock slots away from the electromagnet.
In one of the embodiments, the locking mechanism further includes elastic component, the elastic component and the magnet sucking disc
Connection, the elastic component are in extended state；
After the electromagnet is powered, the elastic component drives the magnet sucking disc away from the electromagnet, and described in drive
Connecting rod departs from the lock slots.
In one of the embodiments, electromagnet, the magnet sucking disc and the axis described in each locking mechanism
The quantity for holding connecting rod is two, and two magnet sucking discs are oppositely arranged, and the elastic component connects two magnet and inhales
Disk；
After there are the lock two lock slots, the electromagnet to be powered, the magnet sucking disc is in the elastic component
Effect is lower away from the corresponding electromagnet, and drives the corresponding connecting rod to depart from the corresponding lock slots.
In one of the embodiments, the connecting rod has supporting part, and the connecting rod passes through the supporting part
It is rotatably fixed in the top flange；
The supporting part connecting rod is separated into the first segment that is connected with the magnet sucking disc and with the lock
The second segment of cooperation, the length of the first segment are 0.2 times~1 times of the length of the second segment.
In one of the embodiments, the locking mechanism includes electromagnetism lock box and is arranged in the electromagnetism lock box
Electromagnetic lock and locking bearing, the electromagnetism lock box are arranged in the return capsule nacelle, and the lock has lock slots, and sets
In on the main parachute bucket；
The locking bearing, which can block, sets or departs from the lock slots, to lock or unlock the return capsule nacelle and institute
State；The electromagnetic lock can discharge the locking bearing after being powered, and the locking bearing is departed from the lock slots.
In one of the embodiments, the locking mechanism includes lock out motor, transmission component and latch assembly, the biography
Dynamic component and the output shaft of the lock out motor are sequentially connected, and the latch assembly is arranged on the transmission component；
There are lock slots, the lock out motor drives the transmission component movement, and drives the locking on the lock
Component movement makes the latch assembly card set or depart from the lock slots.
In one of the embodiments, the transmission component include driving gear and be meshed with the driving gear from
Moving gear, the driving gear are installed on the output shaft of the lock out motor；
The locked component includes two lock shafts and two locking bearings, and two lock shafts are respectively arranged in the active
On gear and the driven gear, two locking bearings are respectively arranged on the lock shaft；
The lock out motor drives the driving gear to rotate, and drives the driven gear to rotate, while the lock shaft
The corresponding locking bearing movable is driven respectively so that the locking bearing card sets or depart from the lock slots.
In one of the embodiments, the quantity of the locking mechanism is multiple that multiple locking mechanisms are uniformly distributed
In in the top flange；
The quantity of the lock is equal to the quantity of the locking mechanism, the position latched on the main parachute bucket
It is corresponding with the locking mechanism.
A kind of catapult technique of the main parachute of satellite return capsule, is returned applied to the satellite as described in any of the above-described technical characteristic
Reboard, the catapult technique include：
The return capsule nacelle sends main parachute ejection instruction；
Locking mechanism is powered, and departs from lock；
The main parachute and main parachute bucket are ejected from the return capsule nacelle.
After adopting the above technical scheme, beneficial effects of the present invention are：
The satellite return capsule of the present invention and its catapult technique of main parachute, are realized by locking mechanism and snap fit and led
Parachute bucket and the locking and unlock of return capsule nacelle, specifically：Locking mechanism is in contact with the lock, main parachute bucket quilt
Ejection structure is locked in return capsule nacelle；During ejection, locking mechanism departs from lock, and main parachute bucket is hit by a bullet from return capsule nacelle
Go out；Effectively solve the problems, such as to simultaneously switch off by multiple blasting bolts at present and realize that main parachute bucket is difficult big caused by launching,
Main parachute bucket is facilitated to launch, can be from return capsule nacelle so under the pulling force of main parachute and main parachute bucket in parachute
Middle safety pop-up；It is additionally, since the locking mechanism of ejection structure and lock is respectively arranged at return capsule nacelle and main parachute bucket
On, locking mechanism is directly separated with lock during ejection, without being recycled to each parts of ejection structure, that is, saves recycling
Structure, can so reduce the volume and weight of satellite return capsule, improve the security of return.
Brief description of the drawings
Fig. 1 is the main structure diagram of the satellite return capsule of one embodiment of the invention；
Fig. 2 is the overlooking the structure diagram of the satellite return capsule shown in Fig. 1；
Fig. 3 is structure diagram when structure latches are launched in the satellite return capsule shown in Fig. 1；
Structure diagram when Fig. 4 is the ejection structure unlock shown in Fig. 3；
Wherein：
100- satellite return capsules；
110- return capsule nacelles；
111- top flanges；
The main parachute buckets of 120-；
130- ejection structures；
131- locking mechanisms；
1311- electromagnet；
1312- magnet sucking discs；
1313- connecting rods；13131- supporting parts；
1314- elastic components；
132- is latched；
1321- lock slots.
Embodiment
In order to make the purpose , technical scheme and advantage of the present invention be clearer, by the following examples, and combine attached
Figure, the catapult technique of satellite return capsule and its main parachute to the present invention are further elaborated.It should be appreciated that herein
Described specific embodiment only to explain the present invention, is not intended to limit the present invention.
Referring to Fig. 1 and Fig. 2, the present invention provides a kind of satellite return capsule 100, which includes return capsule
Nacelle 110, main parachute bucket 120 and ejection structure 130.Satellite return capsule 100 from the outer space return ground when, it is necessary to main landing
Umbrella slows down return capsule nacelle 110, reduces difficulty and risk when return capsule nacelle 110 is landed, to ensure that satellite returns
Cabin 100 is maked a return voyage safe and accurate landing.When satellite return capsule 100 is in certain altitude in return course, return capsule nacelle
110 send main parachute ejection instruction, and at this time, ejection structure 130 can launch main parachute bucket 120 so that main parachute bucket
120 eject from return capsule nacelle 110；It is effective to solve to simultaneously switch off by multiple blasting bolts at present to realize main parachute bucket
Difficult big problem, facilitates main parachute bucket 120 to launch, is so being dropped in main parachute and main parachute bucket 120 caused by ejection
Falling can eject safely under the pulling force of umbrella from return capsule nacelle 110；Moreover, the satellite return capsule 100 of the present invention is after ejection
After main parachute bucket 120, without being recycled to each parts of ejection structure 130, that is, recovery structure is saved, so can
Reduce the volume and weight of satellite return capsule 100, improve the security of return.
In the present invention, the top of return capsule nacelle 110 sets top flange 111.Top connecting flange plays connection function,
For connecting ejection structure 130.Certainly, in the other embodiment of the present invention, also connection can be realized by other
Structure such as connecting plate etc. realizes the installation of ejection structure 130.Main parachute bucket 120 is arranged in return capsule nacelle 110.Main landing
There is main parachute in umbrella bucket 120.Satellite launch and its in orbit during, main parachute bucket 120 is housed in always to be returned
In reboard nacelle 110, when cabin nacelle 110 to be returned returns, and relatively face has certain altitude, main drop to return capsule nacelle 110
Fall 120 ability of umbrella bucket to eject from return capsule nacelle 110, reduce the speed of return capsule nacelle 110 so that return capsule nacelle 110 is pacified
It is complete to land, improve the security that satellite return capsule 100 returns.
Moreover, ejection structure 130 connects the top flange 111 of return capsule nacelle 110 and main parachute bucket 120, ejection knot
When structure 130 launches, main parachute bucket 120 is enabled to depart from return capsule nacelle 110, main parachute bucket 120 and main drop therein
Fall umbrella to eject and be unfolded under a stretching force, to reduce the speed of return capsule nacelle 110.Specifically, ejection structure 130 includes lock
Determine mechanism 131 and lock 132, locking mechanism 131 is respectively arranged at top flange 111 and main parachute bucket 120 with lock 132
On；Locking mechanism 131 is contacted with lock 132, and main parachute bucket 120 is locked in return capsule nacelle 110；During ejection, machine is locked
Structure 131 departs from lock 132, and to unlock return capsule nacelle 110 and main parachute bucket 120, main parachute bucket 120 is from return capsule nacelle
Ejected in 110.It is understood that when ejection structure 130 locks, locking mechanism 131 is in contact with lock 132 so that locking
The fixed lock 132 of mechanism 131 tightly, and then realize the locking of return capsule nacelle 110 and main parachute bucket 120, at this time, main drop
Falling umbrella bucket 120 cannot separate from return capsule nacelle 110；When ejection structure 130 launches, latch-up structure departs from lock 132 so that
Latch-up structure and the phase separation of lock 132, and then realize the unlock of return capsule nacelle 110 and main parachute bucket 120, at this time, main drop
Falling umbrella bucket 120 can eject from return capsule nacelle 110.Exemplary, locking mechanism 131 is arranged at the top of 110 volume of return capsule nacelle
On flange 111, lock 132 is arranged on main parachute bucket 120, after so main parachute bucket 120 launches, main parachute bucket 120
The pop-up return capsule of lock 132 nacelle 110 is driven, the weight of main parachute bucket 120 can be mitigated, facilitate main parachute bucket 120
Ejection.Certainly, in the other embodiment of the present invention, locking mechanism 131 and the position of lock 132 are also interchangeable.
The satellite return capsule 100 of the present invention realizes return capsule nacelle 110 by locking mechanism 131 and the cooperation of lock 132
With the locking and unlock of main parachute bucket 120；During ejection, return capsule nacelle 110 sends ejection signal, and locking mechanism 131 can
It is separated with lock 132, to unlock return capsule nacelle 110 and main parachute bucket 120 so that main parachute bucket 120 is made in pulling force
With lower pop-up return capsule nacelle 110；It can avoid realizing the pop-up of main parachute using bolt explosion, it is effective to solve by more
A blasting bolt, which simultaneously switches off, realizes main parachute bucket difficult big problem caused by launching, and facilitates main parachute bucket 120 to launch.And
And unlock and the lock of return capsule nacelle 110 and main parachute bucket 120 are realized by cooperation of the locking mechanism 131 with latching 132
Fixed, locking mechanism 131 is directly separated with lock 132 during ejection, so can need not to each parts of ejection structure 130 into
Row recycling, that is, save recovery structure, can so reduce the volume and weight of satellite return capsule 100, improve the security of return.
Referring to Fig. 1 to Fig. 4, in one embodiment of this invention, locking mechanism 131 includes electromagnet 1311, magnet sucking disc
1312 and the connecting rod 1313 that is connected with magnet sucking disc 1312, when electromagnet 1311 powers off can adsorption magnet sucker 1312,
One end of connecting rod 1313 is connected with magnet sucking disc 1312.Lock 132 has lock slots 1321, and connecting rod 1313 can block
If or depart from lock slots 1321；After electromagnet 1311 is powered, magnet sucking disc 1312 makes connecting rod away from electromagnet 1311
1313 depart from lock slots 1321.When ejection structure 130 locks, electromagnet 1311 is in off-position, and electromagnet 1311 adsorbs magnetic
Iron sucker 1312, and drive connecting rod 1313 to move so that connecting rod 1313 blocks the lock slots 1321 for being set to lock 132
In；Moreover, during locking, electromagnet 1311 is constantly in off-position.Electromagnet 1311 when ejection structure 130 launches
Be powered, electromagnet 1311 no longer produces adsorption capacity to magnet sucking disc 1312, at this time, magnet sucking disc 1312 away from electromagnet 1311,
And the connecting rod 1313 for driving magnet sucking disc 1312 to connect moves so that connecting rod 1313 departs from lock slots 1321, realizes
Return capsule nacelle 110 and the unlock of lock 132.Exemplary, electromagnet 1311 is forever-electromagnet, can after forever-electromagnet power-off
Adsorption magnet sucker 1312, forever-electromagnet no longer produce adsorption capacity after being powered, i.e. no longer adsorption magnet sucker 1312.
Further, locking mechanism 131 further includes elastic component 1314, and elastic component 1314 is connected with magnet sucking disc 1312, bullet
Property part 1314 is in extended state.After electromagnet 1311 is powered, elastic component 1314 drives magnet sucking disc 1312 away from electromagnet
1311, and drive connecting rod 1313 to depart from lock slots 1321.It is understood that ejection structure 130 locking when, electromagnet
1311 adsorption magnet suckers 1312, and then 1312 draw springs 1314 of magnet sucking disc always so that elastic component 1314 is located always
In extended state；When ejection structure 130 unlocks, the no longer adsorption magnet sucker 1312 of electromagnet 1311, at this time, elastic component 1314 exists
Retract under the resilient force of its own, and then elastic component 1314 can drive magnet sucking disc 1312 to be directed away from electromagnet 1311
Direction movement, and then magnet sucking disc 1312 drive connecting rod 1313 depart from lock slots 1321, realize return capsule nacelle 110 with
The unlock of lock 132.Connecting rod 1313 is driven to depart from lock it should be noted that elastic component 1314 can be magnet sucking disc 1312
Button 132 provides power source, ensures that unlock is reliable, and then avoids the occurrence of the problem of main parachute bucket 120 can not eject, and realizes main drop
Fall the safety pop-up of umbrella bucket 120.Exemplary, elastic component 1314 is compression spring.
Exemplary, the quantity of electromagnet 1311, magnet sucking disc 1312 and connecting rod 1313 is equal in each locking mechanism 131
For two, and two magnet sucking discs 1312 are oppositely arranged, and elastic component 1314 connects two magnet sucking discs 1312.Lock 132 has
Two lock slots 1321, after electromagnet 1311 is powered, magnet sucking disc 1312 is under the effect of elastic component 1314 away from corresponding electromagnetism
Iron 1311, and drive corresponding shaft bearing connecting rod 1313 to depart from corresponding lock slots 1321.When ejection structure 130 locks, two electromagnet
The 1311 corresponding magnet sucking discs 1312 of absorption, and then to drive corresponding connecting rod 1313 to be arranged in corresponding for magnet sucking disc 1312
In lock slots 1321, return capsule nacelle 110 and the locking of lock 132 are realized；When ejection structure 130 launches, two electromagnet
1311 are powered, and electromagnet 1311 no longer adsorbs corresponding magnet sucking disc 1312, at this time, elastic force of the elastic component 1314 at its own
Effect is lower to retract, and then the direction that elastic component 1314 can drive magnet sucking disc 1312 to be directed away from corresponding electromagnet 1311 is transported
It is dynamic, and then magnet sucking disc 1312 drives corresponding connecting rod 1313 to depart from corresponding lock slots 1321, realizes return capsule nacelle
110 with lock 132 unlock.
Certainly, in the other embodiment of the present invention, electromagnet 1311, magnet sucking disc in each locking mechanism 131
1312 and the quantity of connecting rod 1313 be alternatively one, at this time, one end of elastic component 1314 is connected with magnet sucking disc 1312, bullet
The other end of property part 1314 is connected with top flange 111, to ensure elastic component 1314 in magnet sucking disc 1312 and top flange 111
Between keep extended state.After electromagnet 1311 is powered, elastic component 1314 can be shunk under its own resilient force, and then
Magnet sucking disc 1312 is driven away from electromagnet 1311, and then magnet sucking disc 1312 drives connecting rod 1313 to depart from lock slots
1321, it so can also realize the unlock and locking of return capsule nacelle 110.
As a kind of embodiment, in order to ensure that it is accurate, reliable that connecting rod 1313 moves, connecting rod 1313 has
Supporting part 13131, connecting rod 1313 are rotatably fixed in top flange 111 by supporting part 13131.That is,
Connecting rod 1313 passes through supporting part 13131 equivalent to the effect of lever, supporting part 13131 equivalent to fulcrum in the present invention
Effect so that the direction of motion at the both ends of connecting rod 1313 on the contrary, and then realizing the unlock and locking of return capsule nacelle 110.
Ejection structure 130 is in locking, 1311 adsorption magnet sucker 1312 of electromagnet so that magnet sucking disc 1312 drives connecting rod
1313 one end is moved towards close to the direction of electromagnet 1311, simultaneously because the effect of supporting part 13131, connecting rod 1313
The other end be directed away from electromagnet 1311 direction movement, i.e., towards close to lock 132 direction movement, at this time, bearing company
The other end of bar 1313, which can block, to be set in the lock slots 1321 of lock 132.When ejection structure 130 unlocks, electromagnet 1311 is not
Adsorption magnet sucker 1312 again, elastic component 1314 are retracted under the resilient force of its own, and cause 1312 band of magnet sucking disc
One end of dynamic bearing connecting rod 1313 is directed away from the direction movement of electromagnet 1311, simultaneously because the effect of supporting part 13131, axis
The other end for holding connecting rod 1313 is moved towards close to the direction of electromagnet 1311, i.e., connecting rod 1313 departs from the card of lock 132
Groove.
Further, supporting part 13131 connecting rod 1313 is separated into the first segment that is connected with magnet sucking disc 1312 and
The second segment coordinated with lock 132, the length of first segment are 0.2 times~1 times of the length of second segment.In this way, connecting rod
1313 when locking or departing from lock 132, and the elastic force of elastic component 1314 can be amplified by connecting rod 1313, so only
It is that connecting rod 1313 can be achieved to lock or depart from lock 132 to need less elastic force, in convenient unlock and lock slots 1321.
In another embodiment of the invention, locking mechanism includes electromagnetism lock box and the electromagnetism being arranged in electromagnetism lock box
Lock and locking bearing, electromagnetism lock box are arranged in return capsule nacelle 110, and lock has lock slots, and is arranged at main parachute bucket
On 120.Locking bearing can block and set or departs from lock slots, with lock or unlock return capsule nacelle 110 and；After electromagnetic lock is powered
Locking bearing can be discharged, locking bearing is departed from lock slots.Exemplary, lock has two lock slots, correspondingly, lock shaft
Hold also is two.Locking bearing blocks respectively during locking is set in corresponding lock slots, to realize return capsule nacelle 110 and main landing
Locking between umbrella bucket 120.After satellite return capsule 100 has certain altitude from the ground in return course middle-range, return capsule cabin
Body 110 sends ejection signal, and the electromagnetic lock in electromagnetism lock box is powered and discharges locking bearing so that locking bearing departs from lock
Lock slots, realize the unlock of return capsule nacelle 110 and main parachute bucket 120.
In one more embodiment of the present invention, locking mechanism includes lock out motor, transmission component and latch assembly, transmission group
Part and the output shaft of lock out motor are sequentially connected, and latch assembly is arranged on transmission component.There is lock slots, locking electricity on lock
Machine drives transmission component movement, and drives latch assembly movement latch assembly card is set or depart from lock slots.Transmission component energy
Enough movement outputs by lock out motor, to control latch assembly to be arranged in lock slots or depart from lock slots, realize return capsule cabin
The locking and unlock of body 110 and main parachute bucket 120.In the present invention, transmission component is arranged in lock slots or departs from locking
Groove is to drive transmission component movement to realize by lock out motor rotating.Specifically, when locking main parachute bucket 120, lock
Determine motor work, at this time, lock out motor rotates facing one direction, and drives transmission component to move so that transmission component drives
Locked component is moved and blocked and is set in the lock slots of lock；In this way, realize the lock of return capsule nacelle 110 and main parachute bucket 120
It is fixed, lock out motor power-off.After satellite return capsule 100 has certain altitude from the ground in return course middle-range, return capsule nacelle
110 send ejection signal and power to lock out motor, and lock out motor is moved towards another direction at this time, to drive transmission component
Locked component is driven to move and depart from the lock slots of lock, lock out motor power-off, realizes return capsule nacelle 110 and main parachute bucket
120 unlock, at this time, main parachute bucket 120 can be ejected from return capsule nacelle 110.In the present embodiment, motor is positive is powered
After rotate forward, can by transmission component drive locked component be locked in the lock slots of lock；Motor inverts after leading to reversely energization,
Locked component can be driven to depart from the lock slots of lock by transmission component.
Exemplary, transmission component includes driving gear and the driven gear being meshed with driving gear, driving gear installation
In on the output shaft of lock out motor.Locked component includes two lock shafts and two locking bearings, and two lock shafts are respectively arranged in master
On moving gear and driven gear, two locking bearings are respectively arranged on lock shaft.Lock out motor driving driving gear rotates, and band
Dynamic driven gear rotates, while lock shaft drives corresponding locking bearing movable respectively so that locking bearing card sets or depart from lock
Determine groove.When ejection structure 130 locks return capsule nacelle 110 with main parachute bucket 120, lock out motor driving driving gear, which rotates forward, is
Rotate clockwise, and drive driven gear to rotate counterclockwise, at this time, driving gear is moved toward one another with the lock shaft on driven gear,
And block and be set in the lock slots of lock；When ejection structure 130 unlocks return capsule nacelle 110 with main parachute bucket 120, lock out motor
Driving driving gear reversion rotates counterclockwise, and drives driven gear to rotate clockwise, at this time, driving gear and driven gear
On lock shaft move opposite to each other, and depart from the lock slots of lock.Certainly, in the other embodiment of the present invention, transmission component is also
Can be replaced link mechanism etc. or other can realize that driving lock shaft drives locking bearing card to be set to the structure in lock slots.
Alternatively, in the other embodiment of the present invention, the lock slots of locking bearing and lock also can be only driven by a lock shaft
Coordinate.
Alternatively, locked component further includes two turntables, and two turntables are individually fixed on driving gear and driven gear,
And locking bearing is fixed on turntable by lock shaft.Turntable can facilitate the dress between lock shaft and driving gear and driven gear
Match somebody with somebody.
As a kind of embodiment, the quantity of locking mechanism 131 is multiple, and multiple locking mechanisms 131 are uniformly distributed in
In top flange 111.The quantity of lock 132 is equal to the quantity of locking mechanism 131, latches 132 position on main parachute bucket 120
Put corresponding with locking mechanism 131.It can ensure that main parachute bucket 120 is reliably locked in by multiple ejection structures 130 to return
In reboard nacelle 110；Moreover, during ejection, locking mechanism 131 can deduct a percentage big bearing capacity, realize whole main parachute bucket 120
On multigroup locking mechanism 131 at the same time with it is corresponding lock 132 phase separation, uniformity is high, ensure ejection the probability of success.
The present invention also provides a kind of catapult technique of 100 main parachute of satellite return capsule, applied to any of the above-described embodiment
In satellite return capsule 100, catapult technique includes：
Return capsule nacelle 110 sends main parachute ejection instruction；
Locking mechanism 131 is powered, and departs from lock 132；
Main parachute and main parachute bucket 120 are ejected from return capsule nacelle 110.
In 100 return course of satellite return capsule, when satellite return capsule 100 apart from ground in certain altitude after, return capsule
Nacelle 110 sends main parachute ejection instruction, the locking mechanism being subsequently fitted in the top flange 111 of return capsule nacelle 110
Electromagnet 1311 in 131 is powered, and magnet sucking disc 1312 is discharged under the action of elastic component 1314, and then magnet sucking disc 1312
Connecting rod 1313 is driven to depart from the lock 132 that is fixed on main parachute bucket 120 under the leverage of supporting part 13131
Lock slots 1321, in this way, whole main parachute and main parachute bucket 120 under the pulling force of parachute from return capsule nacelle 110
Safety flicks, and realizes the safety pop-up of main parachute bucket 120.
Each technical characteristic of embodiment described above can be combined arbitrarily, to make description succinct, not to above-mentioned reality
Apply all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, the record scope of this specification is all considered to be.
Embodiment described above only expresses the several embodiments of the present invention, its description is more specific and detailed, but simultaneously
Therefore the limitation to the scope of the claims of the present invention cannot be interpreted as.It should be pointed out that for those of ordinary skill in the art
For, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to the guarantor of the present invention
Protect scope.Therefore, the protection domain of patent of the present invention should be determined by the appended claims.
Claims (10)
- A kind of 1. satellite return capsule, it is characterised in that including：Return capsule nacelle, the top of the return capsule nacelle set top flange；Main parachute bucket, is arranged in the return capsule nacelle, has main parachute in the main parachute bucket；AndEjection structure, including locking mechanism and lock, the locking mechanism are respectively arranged at the top flange with the lock With on the main parachute bucket；The locking mechanism is contacted with the lock, and the main parachute bucket is locked in the return capsule In nacelle；During ejection, the locking mechanism departs from the lock, to unlock the return capsule nacelle and the main parachute bucket, The main parachute bucket is ejected from the return capsule nacelle.
- 2. satellite return capsule according to claim 1, it is characterised in that the locking mechanism includes electromagnet, magnet is inhaled Disk and the connecting rod being connected with the magnet sucking disc, the electromagnet can adsorb the magnet sucking disc, the axis when powering off The one end for holding connecting rod is connected with the magnet sucking disc；The lock has lock slots, and the connecting rod, which can block, sets or depart from the lock slots；The electromagnet is powered Afterwards, the magnet sucking disc is away from the electromagnet, and the connecting rod is departed from the lock slots.
- 3. satellite return capsule according to claim 2, it is characterised in that the locking mechanism further includes elastic component, described Elastic component is connected with the magnet sucking disc, and the elastic component is in extended state；After the electromagnet is powered, the elastic component drives the magnet sucking disc away from the electromagnet, and drives the bearing Connecting rod departs from the lock slots.
- 4. satellite return capsule according to claim 3, it is characterised in that electromagnet described in each locking mechanism, The quantity of the magnet sucking disc and the connecting rod is two, and two magnet sucking discs are oppositely arranged, the elasticity Part connects two magnet sucking discs；After there are the lock two lock slots, the electromagnet to be powered, the magnet sucking disc is acted in the elastic component The lower remote corresponding electromagnet, and drive the corresponding connecting rod to depart from the corresponding lock slots.
- 5. according to claim 2 to 4 any one of them satellite return capsule, it is characterised in that the connecting rod has support Portion, the connecting rod are rotatably fixed in the top flange by the supporting part；The supporting part connecting rod is separated into the first segment that is connected with the magnet sucking disc and with the snap fit Second segment, the length of the first segment is 0.2 times~1 times of the length of the second segment.
- 6. satellite return capsule according to claim 1, it is characterised in that the locking mechanism includes electromagnetism lock box and sets The electromagnetic lock and locking bearing being placed in the electromagnetism lock box, the electromagnetism lock box is arranged in the return capsule nacelle, described Lock has lock slots, and is arranged on the main parachute bucket；The locking bearing can block and set or depart from the lock slots, with lock or unlock the return capsule nacelle with it is described； The electromagnetic lock can discharge the locking bearing after being powered, and the locking bearing is departed from the lock slots.
- 7. satellite return capsule according to claim 1, it is characterised in that the locking mechanism includes lock out motor, transmission Component and latch assembly, the transmission component and the output shaft of the lock out motor are sequentially connected, and the latch assembly is arranged at On the transmission component；There are lock slots, the lock out motor drives the transmission component movement, and drives the latch assembly on the lock Movement makes the latch assembly card set or depart from the lock slots.
- 8. satellite return capsule according to claim 7, it is characterised in that the transmission component include driving gear and with institute The driven gear that driving gear is meshed is stated, the driving gear is installed on the output shaft of the lock out motor；The locked component includes two lock shafts and two locking bearings, and two lock shafts are respectively arranged in the driving gear And on the driven gear, two locking bearings are respectively arranged on the lock shaft；The lock out motor drives the driving gear to rotate, and drives the driven gear to rotate, while the lock shaft is distinguished Drive the corresponding locking bearing movable so that the locking bearing card sets or depart from the lock slots.
- 9. satellite return capsule according to claim 1, it is characterised in that the quantity of the locking mechanism is multiple to be multiple The locking mechanism is uniformly distributed in the top flange；The quantity of the lock is equal to the quantity of the locking mechanism, the position latched on the main parachute bucket and institute It is corresponding to state locking mechanism.
- A kind of 10. catapult technique of the main parachute of satellite return capsule, applied to such as claim 1 to 9 any one of them satellite Return capsule, it is characterised in that the catapult technique includes：The return capsule nacelle sends main parachute ejection instruction；Locking mechanism is powered, and departs from lock；The main parachute and main parachute bucket are ejected from the return capsule nacelle.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711396591.9A CN107933974B (en) | 2017-12-21 | 2017-12-21 | Satellite return cabin and ejection method of main parachute thereof |
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| CN201711396591.9A CN107933974B (en) | 2017-12-21 | 2017-12-21 | Satellite return cabin and ejection method of main parachute thereof |
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| CN107933974B CN107933974B (en) | 2024-03-22 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606749A (en) * | 2018-11-23 | 2019-04-12 | 北京空间机电研究所 | A kind of achievable parachute two point hangs conversion and separated structure system from above |
| CN115339659A (en) * | 2022-08-05 | 2022-11-15 | 哈尔滨工业大学（威海） | Load storage cabin for separated type returning device |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1749125A1 (en) * | 1990-12-20 | 1992-07-23 | Конструкторское бюро "Салют" | Ballistically returnable capsule |
| US20090140101A1 (en) * | 2006-10-12 | 2009-06-04 | Robert Salkeld | Direct Flight Far Space Shuttle |
| CN202745525U (en) * | 2012-09-19 | 2013-02-20 | 慈溪市天行电器有限公司 | Electromagnetic lock of range hood |
| CN104554826A (en) * | 2014-12-01 | 2015-04-29 | 南京理工大学 | Separate-orbit CubeSat launching device |
| CN204840936U (en) * | 2015-06-16 | 2015-12-09 | 河北农业大学 | Model rocket device for delayed parachute opening of re-entry capsule |
| JP2016161123A (en) * | 2015-03-05 | 2016-09-05 | 三菱重工業株式会社 | Impact absorption material |
| CN205872484U (en) * | 2016-06-08 | 2017-01-11 | 天津市瑞傲特科技发展有限公司 | Simple and easy device that quick umbrella of unmanned aerial vehicle was thrown |
| CN106542116A (en) * | 2016-09-22 | 2017-03-29 | 北京空间飞行器总体设计部 | A kind of spin ballistic based on mass property reenters return capsule |
| FR3046988A1 (en) * | 2016-09-19 | 2017-07-28 | Airbot Systems | PARACHUTE EJECTION SYSTEM FOR AIRCRAFT |
| CN207809817U (en) * | 2017-12-21 | 2018-09-04 | 星际漫步（北京）航天科技有限公司 | Satellite return capsule |
-
2017
- 2017-12-21 CN CN201711396591.9A patent/CN107933974B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1749125A1 (en) * | 1990-12-20 | 1992-07-23 | Конструкторское бюро "Салют" | Ballistically returnable capsule |
| US20090140101A1 (en) * | 2006-10-12 | 2009-06-04 | Robert Salkeld | Direct Flight Far Space Shuttle |
| CN202745525U (en) * | 2012-09-19 | 2013-02-20 | 慈溪市天行电器有限公司 | Electromagnetic lock of range hood |
| CN104554826A (en) * | 2014-12-01 | 2015-04-29 | 南京理工大学 | Separate-orbit CubeSat launching device |
| JP2016161123A (en) * | 2015-03-05 | 2016-09-05 | 三菱重工業株式会社 | Impact absorption material |
| CN204840936U (en) * | 2015-06-16 | 2015-12-09 | 河北农业大学 | Model rocket device for delayed parachute opening of re-entry capsule |
| CN205872484U (en) * | 2016-06-08 | 2017-01-11 | 天津市瑞傲特科技发展有限公司 | Simple and easy device that quick umbrella of unmanned aerial vehicle was thrown |
| FR3046988A1 (en) * | 2016-09-19 | 2017-07-28 | Airbot Systems | PARACHUTE EJECTION SYSTEM FOR AIRCRAFT |
| CN106542116A (en) * | 2016-09-22 | 2017-03-29 | 北京空间飞行器总体设计部 | A kind of spin ballistic based on mass property reenters return capsule |
| CN207809817U (en) * | 2017-12-21 | 2018-09-04 | 星际漫步（北京）航天科技有限公司 | Satellite return capsule |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606749A (en) * | 2018-11-23 | 2019-04-12 | 北京空间机电研究所 | A kind of achievable parachute two point hangs conversion and separated structure system from above |
| CN115339659A (en) * | 2022-08-05 | 2022-11-15 | 哈尔滨工业大学（威海） | Load storage cabin for separated type returning device |
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|---|---|
| CN107933974B (en) | 2024-03-22 |
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