CN108033033A - Microsatellite ejector and its catapult technique - Google Patents
Microsatellite ejector and its catapult technique Download PDFInfo
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- CN108033033A CN108033033A CN201711394727.2A CN201711394727A CN108033033A CN 108033033 A CN108033033 A CN 108033033A CN 201711394727 A CN201711394727 A CN 201711394727A CN 108033033 A CN108033033 A CN 108033033A
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- microsatellite
- nacelle
- hatchcover
- ejection
- supporting plate
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- 108091092878 Microsatellite Proteins 0.000 title claims abstract description 159
- 238000000034 method Methods 0.000 title claims abstract description 15
- 230000007246 mechanism Effects 0.000 claims description 21
- 230000006835 compression Effects 0.000 claims description 6
- 238000007906 compression Methods 0.000 claims description 6
- 230000002159 abnormal effect Effects 0.000 claims description 2
- 238000000926 separation method Methods 0.000 abstract description 9
- 230000037452 priming Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000004880 explosion Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 239000013013 elastic material Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 230000000116 mitigating effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Launching or towing gear
- B64F1/06—Launching or towing gear using catapults
Abstract
The present invention provides a kind of microsatellite ejector, including：Shell structure, including nacelle and the hatchcover that the nacelle can be opened or closed；Ejection structure, in the nacelle；The ejection structure includes helical spring and ejection supporting plate, and the bottom of the nacelle is fixed in one end of the helical spring, and the other end of the helical spring fixes the ejection supporting plate, and the ejection supporting plate is used to carry microsatellite；And the cross sectional shape of the helical spring is in polygon；And latch-up structure, it is arranged in the shell structure, for locking or unlocking the hatchcover and the nacelle.During ejection, latch-up structure unlocks nacelle and hatchcover, and helical spring stretches under its own resilient force and drives ejection supporting plate movement so that the microsatellite on ejection supporting plate is ejected from nacelle, it can realize the separation of microsatellite safety, ensure that microsatellite safe ejection goes out cabin.The present invention also provides a kind of catapult technique of microsatellite ejector.
Description
Technical field
The present invention relates to satellite launch technical field, more particularly to a kind of microsatellite ejector and its catapult technique.
Background technology
At present, the separation of satellite and carrier rocket often coordinates priming system to realize whole microsatellite using cage construction
Separation.But be the damage that possible bring to microsatellite in itself using the problem of priming system, particularly equipped with highly sensitive
The microsatellite of sensor；In addition, the explosion of priming system is there may be certain impact force, and these impact forces are to the shadow of satellite
Sound is huge, and the ejection of whole project may be caused to fail.
The content of the invention
Based on this, it is necessary to realize that the separation of microsatellite causes microsatellite to damage for the explosion at present using priming system
Wound even launches the problem of failure, there is provided a kind of separation for realizing microsatellite safety, avoid producing microsatellite in itself damage
The microsatellite ejector of wound, while a kind of catapult technique applied to above-mentioned microsatellite ejector is also provided.
Above-mentioned purpose is achieved through the following technical solutions：
A kind of microsatellite ejector, including：
Shell structure, including nacelle and the hatchcover that the nacelle can be opened or closed；
Ejection structure, in the nacelle；The ejection structure includes helical spring and ejection supporting plate, the spiral bullet
The bottom of the nacelle is fixed in one end of spring, and the other end of the helical spring fixes the ejection supporting plate, the ejection support
Plate is used to carry microsatellite；And the cross sectional shape of the helical spring is in polygon；And
Latch-up structure, is arranged in the shell structure, for locking or unlocking the hatchcover and the nacelle.
In one of the embodiments, the sectional dimension of the helical spring from away from it is described ejection supporting plate one end to by
One end of the nearly ejection supporting plate gradually increases；
And after the helical spring compression, the helical spring is in same plane.
In one of the embodiments, the helical spring is rectangular coil spring.
In one of the embodiments, the microsatellite ejector further includes small described in the nacelle for compressing
The compressing structure of satellite；
The compressing structure includes compressed part, and the compressed part protrusion is arranged at a table of the hatchcover towards the nacelle
On face；The hatchcover is covered in the nacelle, and the compressed part is abutted with the microsatellite；
The compressing structure further includes elastic component, and the elastic component is arranged at a surface of the hatchcover towards the nacelle
On；The hatchcover is covered in the nacelle, and the elastic component is abutted with the top of the microsatellite and/or the nacelle.
In one of the embodiments, the microsatellite ejector further includes self-locking structure, the self-locking structure connection
The nacelle and the hatchcover, are opened to the hatchcover of predetermined angle for assisting the hatchcover to open and locking.
In one of the embodiments, the self-locking structure include special-shaped wheel, STATEMENT OF FEDERALLY SPONSORED, delivery arm and with the delivery arm
The limiting section of connection, the special-shaped wheel connect the hatchcover and the nacelle, the STATEMENT OF FEDERALLY SPONSORED connection special-shaped wheel with it is described
Delivery arm, the limiting section can limit the ejection supporting plate；
The hatchcover is opened and drives the special-shaped wheel movement, and the hatchcover is opened to predetermined angle, the STATEMENT OF FEDERALLY SPONSORED
It is arranged on the special-shaped wheel, and drives the delivery arm and the limiting section to discharge the ejection supporting plate.
In one of the embodiments, the latch-up structure includes electromagnetic mechanism and electromagnetism and latches, the electromagnetic mechanism with
The electromagnetic lock button is respectively arranged on the nacelle and the hatchcover；The electromagnetic mechanism has locking bearing, the electromagnetism
Lock has a sticking department, and the locking bearing, which can block, sets or depart from the sticking department, with lock or unlock the hatchcover and
The nacelle.
In one of the embodiments, the microsatellite ejector has power supply interface, the power supply interface and delivery
Rocket is electrically connected, and is powered to the electromagnetic mechanism.
In one of the embodiments, the ejection structure further includes fixing piece, and one end of the helical spring passes through institute
The bottom that fixing piece is fixed on the nacelle is stated, the other end of the helical spring passes through the fixing piece and the ejection supporting plate
It is fixedly connected.
A kind of catapult technique of microsatellite ejector, applied to the microsatellite bullet as described in any of the above-described technical characteristic
Emitter, the catapult technique include the following steps：
After microsatellite enters planned orbit, carrier rocket is powered to microsatellite ejector；
Hatchcover and nacelle are unlocked, after opening the hatchcover to predetermined angle, locks the hatchcover；
Coil spring urges ejection supporting plate skids off the nacelle, and the microsatellite is ejected the nacelle.
After adopting the above technical scheme, beneficial effects of the present invention are：
The microsatellite ejector and its catapult technique of the present invention, microsatellite are positioned on ejection supporting plate and compress spiral
Spring, hatchcover is covered in nacelle, and is locked by latch-up structure and hatchcover is locked in nacelle；During ejection, latch-up structure
Unlock nacelle causes hatchcover to open nacelle with hatchcover, and helical spring stretches under its own resilient force and drives ejection supporting plate
Movement so that the microsatellite on ejection supporting plate is ejected from nacelle；The microsatellite ejector of the present invention uses cross sectional shape
The power source launched for the helical spring of polygon as microsatellite, has larger lateral stability；It is effective to solve mesh
The problem of separation of microsatellite causes microsatellite damage or even ejection failure, is realized in the preceding explosion using priming system, to realize
The separation of microsatellite safety, avoids producing microsatellite in itself damage, while is also avoided that impact force produces microsatellite
Raw influence, ensures that microsatellite safe ejection goes out cabin.
Brief description of the drawings
Fig. 1 is the structure diagram after the hatchcover of the microsatellite ejector of one embodiment of the invention is opened；
Fig. 2 be Fig. 1 shown in microsatellite ejector in helical spring overlooking the structure diagram；
Fig. 3 is the main structure diagram of the helical spring shown in Fig. 2；
Structure diagram when Fig. 4 unlocks for latch-up structure in the microsatellite ejector shown in Fig. 1；
Structure diagram when Fig. 5 is the latch-up structure locking shown in Fig. 4；
Fig. 6 is the backsight structural representation when hatchcover of the microsatellite ejector shown in Fig. 1 is closed；
Fig. 7 be Fig. 6 shown in microsatellite ejector in self-locking structure right view；
Wherein：
100- microsatellite ejectors；
110- shell structures；
111- nacelles；1111- ejector rails；
112- hatchcovers；
120- ejection structures；
121- helical springs；
122- launches supporting plate；
123- fixinig plates；
124- screw elements；
130- latch-up structures；
131- electromagnetic mechanisms；1311- locks bearing；
132- electromagnetism latches；1321- sticking departments；
140- compressing structures；
141- compressed parts；
142- elastic components；
150- self-locking structures；
160- power supply interfaces.
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, is further elaborated the microsatellite ejector and its catapult technique of the present invention.It is it should be appreciated that described herein
Specific embodiment only to explain the present invention, be not intended to limit the present invention.
Referring to Fig. 1, the present invention provides a kind of microsatellite ejector 100, which is used to launch
Microsatellite so that microsatellite ejects cabin, to realize that communication, remote sensing of the earth, interplanetary exploration, scientific research, technology are tried
The application of each side such as test.When microsatellite enters outer space planned orbit, carrier rocket can will be micro- according to mission program
Moonlet launches, also, microsatellite ejector 100 using the present invention ejection microsatellite, can realize that microsatellite is pacified
Full separation, avoids producing microsatellite in itself damage, while is also avoided that the influence that impact force produces microsatellite, protects
Card microsatellite safe ejection goes out cabin.
In the present invention, microsatellite ejector 100 includes shell structure 110, ejection structure 120 and latch-up structure 130.
Shell structure 110 plays storage, and the most of structure and microsatellite of microsatellite ejector 100 are respectively positioned on shell structure
In 110, in order to which microsatellite is carried in the outer space.Latch-up structure 130 is arranged in shell structure 110, for locking
Or open shell structure 110.It is understood that microsatellite ejector 100 is equal before outer space planned orbit is entered
Closed state need to be in, to avoid microsatellite occur not in orbit the problem of and ejection failure the problem of, only into
Prepare just to open during ejection after entering outer space planned orbit, to ensure that microsatellite can be ejected from shell structure 110.Bullet
Penetrate structure 120 to be arranged in shell structure 110, for launching microsatellite.Microsatellite is located in shell structure 110 and places
In on ejection structure 120, ejection structure 120 provides thrust to microsatellite, which is the ejection force of microsatellite so that micro-
Moonlet ejects safely, effectively avoids passing through the separation that microsatellite is realized in priming system explosion, can avoid to microsatellite
Itself produces damage, while is also avoided that the influence that impact force produces microsatellite, ensures that microsatellite safe ejection goes out cabin.
Specifically, shell structure 110 includes nacelle 111 and can open or close the hatchcover 112 of nacelle 111.Hatchcover 112
After closing nacelle 111, shell structure 110 is in closed state；After hatchcover 112 opens nacelle 111, ejection structure 120 can incite somebody to action
Microsatellite is ejected from nacelle 111.Latch-up structure 130 is used to locking or unlocking hatchcover 112 and nacelle 111, to ensure hatchcover
112 are reliably covered in nacelle 111.In carry process, latch-up structure 130 all the time locks hatchcover 112 and nacelle 111, makes
Obtain hatchcover 112 to be covered in nacelle 111, avoid microsatellite from going out cabin；During ejection, latch-up structure 130 unlocks hatchcover 112 and nacelle
111 so that hatchcover 112 is opened relative to nacelle 111, and at this time, microsatellite can be hit by a bullet by ejection structure 120 from nacelle 111
Go out, realize the ejection of microsatellite.Exemplary, nacelle 111 is set in hollow cuboid, and its one end has opening, ejection knot
Structure 120 is arranged in hollow cuboid, and hatchcover 112 is covered on opening, to close the nacelle 111 in cuboid.Certainly, exist
In the other embodiment of the present invention, the shapes such as nacelle 111 can be also in the form of a column are set.Alternatively, hatchcover 112 and nacelle 111 it
Between connected by folding, facilitate opening and the closing of hatchcover 112, certainly, the present invention other embodiment in, hatchcover 112
It can be also connected with nacelle 111 by shaft.
Referring to Fig. 1 to Fig. 3, ejection structure 120 includes helical spring 121 and launches supporting plate 122, and the one of helical spring 121
The bottom of nacelle 111 is fixed at end, and the other end of helical spring 121 fixes ejection supporting plate 122, and ejection supporting plate 122 is used to carry
Microsatellite.The compressible setting in nacelle 111 of helical spring 121, when microsatellite loads, ejection is positioned over by microsatellite
On supporting plate 122, and apply active force to microsatellite, with compression helical spring 121, hatchcover 112 is then covered on nacelle 111
On, and hatchcover 112 and nacelle 111 are locked by latch-up structure 130.When microsatellite enters outer space planned orbit, delivery
Rocket installation desired guiding trajectory control latch-up structure 130 unlocks hatchcover 112 and nacelle 111, and then hatchcover 112 opens nacelle 111, spiral shell
Rotation spring 121 can stretch under the effect of natural resiliency power, and drive plastic trays gradually to stretch out so that spring planet will be small
Satellite releases nacelle 111, realizes that microsatellite safe ejection goes out cabin.
Also, the cross sectional shape of helical spring 121 is in polygon.So the elastic force of helical spring 121 is as microsatellite
Thrust so that microsatellite can be ejected smoothly from nacelle 111, moreover, helical spring 121 has larger transverse direction
Power, ensures the stability in microsatellite ejection process, and then ensures the reliability of microsatellite ejection so that microsatellite is accurate
On the planned orbit of true ejection.The shape of ejection supporting plate 122 is adapted with the cross sectional shape of nacelle 111, to ensure spiral bullet
Spring 121 drives ejection supporting plate 122 to stretch out or retract in nacelle 111.Alternatively, launching on supporting plate 122 has multiple lightening holes,
The lightening hole is used for the weight for mitigating ejection supporting plate 122, so that the thrust of helical spring 121 largely acts on small defend
On star, reduce energy loss.
In addition, ejection structure 120 further includes fixing piece, nacelle 111 is fixed in one end of helical spring 121 by fixing piece
Bottom, the other end of helical spring 121 is fixedly connected by fixing piece with ejection supporting plate 122.Spiral bullet can so be avoided
Spring 121 departs from and influences the ejection of microsatellite so that the thrust that helical spring 121 produces can accurately act on small defend
On star, ensure the accuracy of microsatellite ejection.Exemplary, fixing piece includes screw element 124 and/or fixinig plate 123, spiral bullet
Spring 121 is fixed in nacelle 111 by screw element 124 and/or fixinig plate 123 or launched on supporting plate 122, ensures helical spring
121 is reliable fixed.In the present embodiment, one end of helical spring 121 is fixed on the bottom of nacelle 111, spiral shell by fixinig plate 123
The other end for revolving spring 121 is fixedly connected by screw element 124 with ejection supporting plate 122.
Certainly, in the other embodiment of the present invention, helical spring 121 can also be fixed by structures such as pillar, grooves
Or fixed by adhesive means.
Further, the sectional dimension of helical spring 121 is from one end away from ejection supporting plate 122 to close to ejection supporting plate
122 one end gradually increases.After helical spring 121 compresses, helical spring 121 is in same plane.That is, helical spring
It is in the structure similar to taper after 121 stretching, extensions, after helical spring 121 compresses, each ring layer layer of helical spring 121 is arranged and is located at
In same plane.After helical spring 121 is set using the above structure, be conducive to save space, also, there is stronger carrying energy
Power, then ensures to produce larger thrust, to eject microsatellite from nacelle 111 when ensureing and launching.It is exemplary, spiral bullet
Spring 121 is rectangular coil spring 121.I.e. rectangular coil spring 121 compress after be a rectangle frame, 121 energy of rectangular coil spring
Enough there is larger lateral stability.
Alternatively, there is ejector rail 1111, ejector rail 1111 is engaged with ejection supporting plate 122, will in nacelle 111
Ejection supporting plate 122 is limited in nacelle 111.During ejection, ejection supporting plate 122 can be slided along ejector rail 1111.So can
Ensure the running orbit of ejection supporting plate 122, avoid ejection supporting plate 122 from occurring in nacelle 111 to the outside of ejector rail 1111
Offset, and then ensure that ejection supporting plate 122 launches the accuracy of microsatellite so that microsatellite can be exactly into pre- orbit determination
Road.Exemplary, the quantity of ejector rail 1,111 four, four ejector rails 1111 are respectively positioned at four edge ejections of nacelle 111
At the seamed edge in direction, four corners of ejection supporting plate 122 are engaged with four ejector rails 1111 respectively, during ejection, latch bracket
Plate can be slided along ejector rail 1111；During loading, microsatellite enables to ejection supporting plate 122 along bullet under external force
Guide rail 1111 is penetrated to move, and compression helical spring 121.It is preferred that the L-shaped setting of the cross sectional shape of ejector rail 1111, ejection
The corner of supporting plate 122 is abutted with the inner surface of L-type ejector rail 1111, to ensure the movement locus of ejection supporting plate 122.
As a kind of embodiment, microsatellite ejector 100 is further included for compressing microsatellite in nacelle 111
Compressing structure 140.Compressing structure 140 can compress microsatellite, avoid microsatellite from being rocked in nacelle 111, ensure micro-
The reliability of moonlet delivery, avoids the performance of wobble effects microsatellite.Compressing structure 140 includes compressed part 141, pressure
The tight protrusion of portion 141 is arranged at hatchcover 112 towards on a surface of nacelle 111；Hatchcover 112 is covered in nacelle 111, compressed part
141 abut with microsatellite.That is, after hatchcover 112 is covered on nacelle 111, microsatellite is compressed by compressed part 141
In nacelle 111, microsatellite is avoided to be rocked in nacelle 111.Exemplary, compressed part 141 is the pressure that cross sectional shape is rectangle
Tight ring, can so increase the contact area of compressed part 141 and microsatellite, while also ensure that microsatellite is equal with compression ring
Even contact, ensures microsatellite uniform force, avoids the microsatellite caused by unbalance stress from being tilted in nacelle 111, to protect
Posture of the microsatellite in nacelle 111 is demonstrate,proved, then ensures the accuracy of microsatellite ejection.Certainly, the present invention other
In embodiment, compressed part 141 can also be multiple pillars, and multiple pillars are evenly distributed on a table of the hatchcover 112 towards nacelle 111
On face.Alternatively, the altitude range that compressed part 141 is protruded is 1mm~100mm.
Further, compressing structure 140 further includes elastic component 142, and elastic component 142 is arranged at hatchcover 112 towards nacelle 111
A surface on；Hatchcover 112 is covered in nacelle 111, and elastic component 142 is abutted with the top of microsatellite and/or nacelle 111.
Elastic component 142 can also play the role of compressing microsatellite.Exemplary, microsatellite passes through elastic component 142 and compressed part 141
Mating reaction by being pressed in nacelle 111 tightly.Also, after latch-up structure 130 unlocks hatchcover 112 and nacelle 111, hatchcover
112 automatically open up under the resilient force of elastic component 142, and after hatchcover 112 opens predetermined angle, helical spring 121 drives
Ejection supporting plate 122 skids off nacelle 111, and makes ejection supporting plate 122 that microsatellite thereon is ejected nacelle 111.Alternatively, it is elastic
Part 142 is spring or the elastic made of elastic material.Certainly, in the other embodiment of the present invention, compressed part 141 can
It is structure as a whole with elastic component 142, at this time, compressed part 141 is made of elastic material.
Referring to Fig. 6 and Fig. 7, as a kind of embodiment, microsatellite ejector 100 further includes self-locking structure 150, from
Lock construction 150 connects nacelle 111 and hatchcover 112, is opened for assisting hatchcover 112 to open and locking to the hatchcover of predetermined angle
112.After hatchcover 112 is opened, hatchcover 112 is locked by self-locking structure 150, avoids the position of hatchcover 112 that play occurs, ensures micro-
The reliability of moonlet ejection so that microsatellite accurately enters planned orbit；Also it is avoided that hatchcover 112 occurs with microsatellite
Colliding with causes microsatellite to damage, and realizes that microsatellite goes out safely cabin.Also, after hatchcover 112 opens predetermined angle, ejection knot
Structure 120 just launches microsatellite, avoids microsatellite from colliding with hatchcover 112.Alternatively, predetermined angle refers to hatchcover 112
Relative to the movement angle of nacelle 111, which needs >=110 °.In the present embodiment, predetermined angle >=130 °, that is,
Say, after hatchcover 112 is opened more than 130 °, ejection structure 120 just launches microsatellite.
Further, self-locking structure 150 includes special-shaped wheel, STATEMENT OF FEDERALLY SPONSORED, delivery arm and the limiting section being connected with delivery arm, different
Type wheel connects hatchcover 112 and nacelle 111, and the special-shaped wheel of STATEMENT OF FEDERALLY SPONSORED connection and delivery arm, limiting section can limit ejection supporting plate 122；
Hatchcover 112 is opened and drives special-shaped wheel movement, and hatchcover 112 is opened to predetermined angle, and STATEMENT OF FEDERALLY SPONSORED is arranged on special-shaped wheel, and band
Dynamic delivery arm and the limiting section release ejection supporting plate 122.Alternatively, the outer contour of special-shaped wheel is by the different circular arc of multistage radius
Enclose to set and form.It is used to block the card slot for setting fixed STATEMENT OF FEDERALLY SPONSORED moreover, on special-shaped wheel having.In the present embodiment, the foreign steamer of special-shaped wheel
Exterior feature is spliced by the circular arc of at least three sections different-diameters, and forms card slot on abnormal shape wheel.Alternatively, set at the top of STATEMENT OF FEDERALLY SPONSORED
Bearing is put, facilitates the movement between STATEMENT OF FEDERALLY SPONSORED and special-shaped wheel.After hatchcover 112 is opened to predetermined angle, the axis at the top of STATEMENT OF FEDERALLY SPONSORED
Hold and be arranged in card slot, realize the locking of hatchcover 112；Meanwhile special-shaped wheel drives STATEMENT OF FEDERALLY SPONSORED to move downward, and drive delivery arm to
Lower movement, in this way, limiting section can drive ejection 122 reverse compression helical spring 121 of supporting plate to move and discharge ejection supporting plate
122 so that microsatellite is ejected cabin by ejection structure 120.Exemplary, limiting section is angle steel piece device, ejector rail 1111
Upper have an opening, and angle steel piece device can retract or stretch out opening.Limiting section stretching can limit ejection supporting plate 122 and launch；Limit
Position portion retracts, and ejection supporting plate 122 can be slided along ejector rail 1111, and microsatellite is ejected.
Referring to Fig. 4 and Fig. 5, as a kind of embodiment, latch-up structure 130 includes electromagnetic mechanism 131 and electromagnetism latches
132, electromagnetic mechanism 131 is respectively arranged on nacelle 111 and hatchcover 112 with electromagnetism lock 132.Electromagnetic mechanism 131 has locking
Bearing 1311, electromagnetism lock 132 have sticking department 1321, and locking bearing 1311, which can block, sets or depart from sticking department 1321, with
Locking or unlock hatchcover 112 and nacelle 111.It is understood that electromagnetic mechanism 131 coordinates locking hatchcover with electromagnetism lock 132
112 with nacelle 111 when, closed between hatchcover 112 and nacelle 111, can realize the delivery of microsatellite at this time；Work as microsatellite
Into after outer space planned orbit, after microsatellite ejector 100 receives ejection signal, electromagnetic mechanism 131 and electromagnetism lock 132
Coordinate unlock hatchcover 112 and nacelle 111, at this time, hatchcover 112 opens nacelle 111, also, when hatchcover 112 opens predetermined angle
Afterwards, 112 self-locking structure 150 of hatchcover locking hatchcover 112, and make guide rail locking structure retract by spring pull rod, with rear screw bullet
Spring 121 drives ejection supporting plate 122 to be slided along ejector rail 1111, and is ejected microsatellite thereon by launching supporting plate 122
Nacelle 111.Exemplary, electromagnetism lock 132 has two sticking departments 1321, correspondingly, locking bearing 1311 is also two, loads
After the completion of, hatchcover 112 is covered, locking bearing 1311 blocks respectively to be set in corresponding sticking department 1321, to realize hatchcover 112 and cabin
Locking between body 111.After microsatellite runs to planned orbit, carrier rocket can be according to mission program by ejection signal
It is sent to microsatellite ejector 100, after microsatellite ejector 100 receives ejection signal, electromagnetic mechanism 131 is powered simultaneously
Release locking bearing 1311 so that locking bearing 1311 departs from the sticking department 1321 of electromagnetism lock 132, realizes hatchcover 112 and cabin
The unlock of body 111.In the present embodiment, sticking department 1321 is lock slots.
In addition, microsatellite ejector 100 has power supply interface 160, power supply interface 160 is electrically connected with carrier rocket, and
Power to electromagnetic mechanism 131.Microsatellite ejector 100 establishes carrier rocket and electromagnetic mechanism 131 by power supply interface 160
It is electrically connected, to control electromagnetic mechanism 131 to unlock, realizes unlock hatchcover 112 and nacelle 111.Exemplary, power supply interface 160 is two
A, corresponding latch-up structure 130 is also two, to ensure that locking is reliable；Two power supply interfaces 160 are respectively to electromagnetic mechanism 131
Power supply.
The present invention also provides a kind of catapult technique of microsatellite ejector 100, applied to small in above-described embodiment
Satellite ejector 100, catapult technique includes the following steps：
After microsatellite enters planned orbit, carrier rocket is powered to microsatellite ejector 100；
Hatchcover 112 and nacelle 111 are unlocked, after opening hatchcover 112 to predetermined angle, locks hatchcover 112；
Helical spring 121 promotes ejection supporting plate 122 to skid off nacelle 111, and microsatellite is ejected nacelle 111.
When microsatellite enters outer space planned orbit, carrier rocket can be connect according to mission program by two power supplies
Mouth 160 is powered to the electromagnetic mechanism 131 of microsatellite ejector 100, and then electromagnetic mechanism 131 can discharge lock shaft after being powered
Hold 1311 so that locking bearing 1311 departs from the sticking department 1321 of electromagnetism lock 132, realizes the solution of hatchcover 112 and nacelle 111
Lock.Then, hatchcover 112 causes hatchcover 112 certainly under the micro-elasticity power of elastic component 142 and the collective effect of self-locking structure 150
It is dynamic to open.After hatchcover 112 is opened to such as 130 ° of predetermined angle, self-locking structure 150 locks hatchcover 112, ejection structure 120
Helical spring 121 stretches under its own resilient force, and drives ejection supporting plate 122 to be slided along ejector rail 1111, will be micro-
Moonlet ejects cabin, realizes that microsatellite safe ejection goes out cabin.
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. microsatellite ejector, it is characterised in that including：Shell structure, including nacelle and the hatchcover that the nacelle can be opened or closed；Ejection structure, in the nacelle；The ejection structure includes helical spring and ejection supporting plate, the helical spring The bottom of the nacelle is fixed in one end, and the other end of the helical spring fixes the ejection supporting plate, and the ejection supporting plate is used In carrying microsatellite；And the cross sectional shape of the helical spring is in polygon；AndLatch-up structure, is arranged in the shell structure, for locking or unlocking the hatchcover and the nacelle.
- 2. microsatellite ejector according to claim 1, it is characterised in that the sectional dimension of the helical spring is from remote One end from the ejection supporting plate gradually increases to close to one end of the ejection supporting plate；And after the helical spring compression, the helical spring is in same plane.
- 3. microsatellite ejector according to claim 1, it is characterised in that the helical spring is rectangular coil bullet Spring.
- 4. microsatellite ejector according to any one of claims 1 to 3, it is characterised in that the microsatellite ejection Device further includes the compressing structure for compressing microsatellite described in the nacelle；The compressing structure includes compressed part, and the compressed part protrusion is arranged at a surface of the hatchcover towards the nacelle On；The hatchcover is covered in the nacelle, and the compressed part is abutted with the microsatellite；The compressing structure further includes elastic component, and the elastic component is arranged at the hatchcover towards on a surface of the nacelle； The hatchcover is covered in the nacelle, and the elastic component is abutted with the top of the microsatellite and/or the nacelle.
- 5. microsatellite ejector according to any one of claims 1 to 3, it is characterised in that the microsatellite ejection Device further includes self-locking structure, and the self-locking structure connects the nacelle and the hatchcover, for assisting the hatchcover to open and locking It is fixed to open to the hatchcover of predetermined angle.
- 6. microsatellite ejector according to claim 5, it is characterised in that the self-locking structure includes special-shaped wheel, connection Moving part, delivery arm and the limiting section being connected with the delivery arm, the special-shaped wheel connects the hatchcover and the nacelle, described The moving part connection special-shaped wheel can limit the ejection supporting plate with the delivery arm, the limiting section；The hatchcover is opened and drives the special-shaped wheel movement, and the hatchcover is opened to predetermined angle, and the STATEMENT OF FEDERALLY SPONSORED card is set Taken turns in the abnormal shape, and drive the delivery arm and the limiting section to discharge the ejection supporting plate.
- 7. microsatellite ejector according to any one of claims 1 to 3, it is characterised in that the latch-up structure includes Electromagnetic mechanism and electromagnetism lock, the electromagnetic mechanism are respectively arranged in the nacelle and the hatchcover with the electromagnetic lock button； The electromagnetic mechanism has locking bearing, and the electromagnetic lock fastener has sticking department, and the locking bearing, which can block, to be set or depart from The sticking department, to lock or unlock the hatchcover and the nacelle.
- 8. microsatellite ejector according to claim 7, it is characterised in that the microsatellite ejector has power supply Interface, the power supply interface are electrically connected with carrier rocket, and are powered to the electromagnetic mechanism.
- 9. microsatellite ejector according to any one of claims 1 to 3, it is characterised in that the ejection structure also wraps Fixing piece is included, one end of the helical spring is fixed on the bottom of the nacelle by the fixing piece, the helical spring The other end is fixedly connected by the fixing piece with the ejection supporting plate.
- A kind of 10. catapult technique of microsatellite ejector, applied to such as claim 1 to 9 any one of them microsatellite Ejector, it is characterised in that the catapult technique includes the following steps：After microsatellite enters planned orbit, carrier rocket is powered to microsatellite ejector；Hatchcover and nacelle are unlocked, after opening the hatchcover to predetermined angle, locks the hatchcover；Coil spring urges ejection supporting plate skids off the nacelle, and the microsatellite is ejected the nacelle.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711394727.2A CN108033033B (en) | 2017-12-21 | 2017-12-21 | Microsatellite catapult and catapulting method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711394727.2A CN108033033B (en) | 2017-12-21 | 2017-12-21 | Microsatellite catapult and catapulting method thereof |
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| CN108033033A true CN108033033A (en) | 2018-05-15 |
| CN108033033B CN108033033B (en) | 2024-03-22 |
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| CN112304547A (en) * | 2020-08-31 | 2021-02-02 | 中国空间技术研究院 | Free collision adsorption test device |
| CN112722339A (en) * | 2021-03-30 | 2021-04-30 | 北京星际荣耀空间科技股份有限公司 | Locking piece, connector and low-temperature rocket system |
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| CN112722339A (en) * | 2021-03-30 | 2021-04-30 | 北京星际荣耀空间科技股份有限公司 | Locking piece, connector and low-temperature rocket system |
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| Publication number | Publication date |
|---|---|
| CN108033033B (en) | 2024-03-22 |
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