CN106742065A - A kind of payload space cabin structure suitable for orbiter - Google Patents
A kind of payload space cabin structure suitable for orbiter Download PDFInfo
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- CN106742065A CN106742065A CN201611163100.1A CN201611163100A CN106742065A CN 106742065 A CN106742065 A CN 106742065A CN 201611163100 A CN201611163100 A CN 201611163100A CN 106742065 A CN106742065 A CN 106742065A
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- hatch door
- orbiter
- sealing
- door
- support beam
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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
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- Aviation & Aerospace Engineering (AREA)
- Seal Device For Vehicle (AREA)
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Abstract
The invention discloses a kind of payload space cabin structure suitable for orbiter, including nacelle and hatch door, hatch door is connected in nacelle, hatch door is realized opening and closed to nacelle, hatch door is the two symmetrical opposite opened structures of fan, often fan hatch door includes inside panel, exterior skin, main bearing beam, honeycomb core, reinforcement and thermal protection structure, honeycomb core is located inside panel, between exterior skin, guiding gutter is opened up on the contact position of honeycomb core and exterior skin, reinforcement is arranged between honeycomb core, reinforcement is connected to two main bearing beams, three cabin door locks are uniformly arranged on main bearing beam, two fan hatch doors realize locking mutually when closing；Thermal protection structure is arranged on exterior skin, using staggeredly layout, steam resorption amount≤0.15% under the natural environment of thermal protection structure surface.Make payload cabin door structure rigidity high, structure compatibility, good airproof performance, while meeting integration, lighting requirement.
Description
Technical field
It is more particularly to a kind of with big the present invention relates to a kind of payload space cabin structure suitable for orbiter
The space cabin structure of size payload hatch door, belongs to Aircraft structural design field.
Background technology
Orbiter be can in-orbit stop for a long time, empty day come and go, the weapon for possessing comprehensive fight capability of vehicle out-driving
Platform, payload bay is the equipment container that aircraft performs space tasks, is protection payload safety when launching and reclaiming
Critical component, it is necessary to adapt to aircraft enter the orbit, orbit maneuver and reenter return three phases different operating modes.Wherein effectively carry
Lotus freight space bay section in aircraft, realizes that repeating exhibition receives and locking by hatch door mechanism.Mission profile demand according to aircraft,
It is required that space bay door system also needs the features such as possessing pneumatic carrying, thermal protection, heat seal, shield structure.
Payload bay is the important installation carrier that the important systems such as payload, solar array and unit are installed,
It is mostly important part in Aircraft structural design.Aircraft is reentering return stage, the inside and outside differential pressure that hatch door is subject to
It is relatively large, and payload cabin door structure yardstick is larger, therefore payload cabin door structure high rigidity, integration, lighting
Design requirement be particularly important.In addition, payload hatch door is required to carry out repeatedly exhibition receipts in space, and can hold
By flight environment of vehicle when reentering return, therefore, the design of payload cabin door structure also needs to consider space requirement and surrounding structure machine
The compatible and harsh heat seal requirement of structure, is the optimization design problem under a typical multi-constraint condition, is not had
Effect, quick, feasible method for designing and technology, it is impossible to which the optimization design of implementation is carried with orbiter is met to effective
The use requirement of lotus bay door system.
For above-mentioned orbiter to the particular/special requirement of hatch door, it is necessary to optimize design to load hatch door.
The content of the invention
Technology solve problem of the invention：To overcome the deficiencies in the prior art, there is provided a kind of suitable for orbiter
Payload space cabin structure, makes payload cabin door structure rigidity high, structure compatibility, good airproof performance, while meeting whole
Body, lighting requirement.
Technical solution of the invention：
A kind of payload space cabin structure suitable for orbiter, including nacelle and hatch door, hatch door are connected to cabin
On body, hatch door is realized opening and closed to nacelle, and hatch door is the two symmetrical opposite opened structures of fan, and often fanning hatch door includes inside panel, outer
Covering, main bearing beam, honeycomb core, reinforcement and thermal protection structure,
Honeycomb core is located between inside panel, exterior skin, and water conservancy diversion is opened up on the contact position of honeycomb core and exterior skin
Groove, arranges reinforcement between honeycomb core, and reinforcement is connected to two main bearing beams, and three cabins are uniformly arranged on main bearing beam
Door lock, two fan hatch doors realize locking mutually when closing；
Thermal protection structure is arranged on exterior skin, and using being staggeredly laid out, steam is returned under the natural environment of thermal protection structure surface
Pipette≤0.15%,
Nacelle upper end is big opening structure, and big opening structure surrounding is respectively symmetrically setting hatch door support beam and hatch door bulkhead,
Three hinges that the main bearing beam of hatch door passes through to be uniformly arranged are connected with hatch door support beam, and hatch door Zhan Shou mechanisms are fixed on hatch door branch
On support beam and hatch door bulkhead, control hatch door is opened, closure；
Dual heat seal structure is set between hatch door and hatch door bulkhead, hatch door support beam, hatch door bulkhead, hatch door support beam with
The contact position of hatch door is respectively provided with first and reheats sealing；
In hatch door support beam and hatch door bulkhead, sealing support beam and sealing carriage are correspondingly arranged on, seal carriage
Set fluted with sealing support beam, for placing heat seal flexible member, constitute second and reheat sealing, by heating seal bullet
Property element resilience be further ensured that outside thermal current can not enter cabin in.
Water conservancy diversion well width is 1~2mm, and the depth of guiding gutter is 2~3mm.
Material volatility total mass loss≤0.5% of thermal protection structure.
Material volatile substances content≤0.1% of thermal protection structure.
Inside panel, exterior skin are carbon fibre reinforced composite, and honeycomb core is the paper honeycomb of array arrangement.
First reheats sealing using pyroceram fibre cloth, intercepts thermal current and enters in cabin.
Heat seal flexible member is formed by high temperature alloy weaving filaments, internal stuffed heat insulated cotton, outer wrap high temperature fiber
Cloth.
Hatch door be in closure state when, hatch door surrounding by seal carriage, sealing support beam and heat seal flexible member,
Realize the support to hatch door, sealing and buffer.
First reheat sealing outer edge it is concordant with hatch door outer edge.
After hypersonic environment stand under load, deformation≤2mm of the hatch door with respect to hatch door support beam.
The present invention has the advantages that compared with prior art：
(1) open and close function, locking scheme, seal request towards large scale payload hatch door of the invention etc. proposes empty
Between structure-integrated design, while considering that property indices meet situation and structure boundary in full mission profile load
Influence under effect, design is optimized to cabin door structure under integrated performance index constraints, is met seal clearance
It is required that, motion envelope requirement and lock point intensity and functional requirement optimizing design scheme, solve payload and space mechanism
Location problem, space mechanism exhibition receive and folding process in motor coordination problem, hatch door sealing problem, space mechanism compress
The fixed environmental protection totality side for coordinating sex chromosome mosaicism, overall stress and dynamics index optimization problem and space bay door system
The problems such as case, it is ensured that maximize the structure efficiency of load cabin in limited space, while the reliability of the system of raising, is empty
Between cabin door structure design provide reference frame and technical support；
(2) stretching in its interior exterior skin of the invention whole bending stiffnesses almost there is provided hatch door sandwich plate and face is firm
Degree, honeycomb core provides the transverse shear stiffness of interlayer, while also acting as exterior skin in stabilization, preventing the work of local buckling
With honeycomb core is scattered, and it is highly higher by several times than covering, and biquadratic increases the moment of inertia of section therewith, and covering has
Sandwich is supported to be difficult unstability, therefore it not only increases interlayer composite material covering integral rigidity, also improves stability, improves
The mechanical property of whole hatch door.
Brief description of the drawings
Fig. 1 is cabin door structure schematic layout pattern of the present invention；
Fig. 2 is cabin door structure open mode schematic diagram of the present invention；
Fig. 3 is cabin door structure closure state schematic diagram of the present invention；
Fig. 4 is cabin door structure composition schematic diagram of the present invention；
Fig. 5 is honeycomb core structural representation of the present invention；
Fig. 6 is honeycomb core guiding gutter schematic diagram of the present invention；
Fig. 7 is that cabin door structure of the present invention heats seal schematic diagram；
Fig. 8 is that hatch door of the present invention heats seal interface shape schematic diagram with hatch door bulkhead；
Fig. 9 is that hatch door of the present invention heats seal interface shape schematic diagram with hatch door support beam.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings.
A kind of payload space cabin structure suitable for orbiter, including nacelle 8 and hatch door 1, hatch door 1 are connected to
In nacelle 8, hatch door 1 is realized opening and closed to nacelle 8, and hatch door 1 is the two symmetrical opposite opened structures of fan, and often fanning hatch door includes Inner Mongol
Skin 13, exterior skin 14, main bearing beam 15, honeycomb core 16, reinforcement 17 and thermal protection structure 18, as shown in figs. 2 to 4,
Honeycomb core 16 is located between inside panel 13, exterior skin 14, and reinforcement 17 is arranged between honeycomb core 16, is strengthened
Muscle 17 is connected between two main bearing beams 15, and 3 cabin door locks 2, reality when two fan hatch doors are closed are uniformly arranged on main bearing beam 15
Now locking mutually, the layout after closure in aircraft is as shown in Figure 1；
Covering is carbon fibre reinforced composite, honeycomb core 16 be paper honeycomb, the form of honeycomb core 16 as shown in figure 5,
In order to ensure heat-insulated and deflation rate of the hatch door under space environment, guiding gutter is opened up on honeycomb core 16, as shown in fig. 6,
Water conservancy diversion well width is 1~2mm, and the depth of guiding gutter is 2~3mm.
Its interior exterior skin 13,14 almost there is provided hatch door sandwich plate whole bending stiffnesses and face in tensible rigidity, honeybee
Nest fuse 16 provides the transverse shear stiffness of interlayer, while also acting as exterior skin 13,14 in stabilization, prevents the work of local buckling
With.From amechanical angle analysis, it is much like with I-beam, and interior exterior skin 13,14, equivalent to the edge of a wing of I-beam, is main receiving
Power position, additionally, there is protective effect to honeycomb core 16；
Equivalent to the web of I-beam, its Main Function is subject to lateral shear to honeycomb core 16, two-layer covering 13,14
From a distance, when sandwich plate bears bending load, honeycomb core 16 can support surface layer, increase surface layer and support resistant to bending
Ability, so that integrally bending rigidity is improved.
Same material from honeycomb core unlike I-beam 16 and panel, honeycomb core 16 be it is scattered, without
It is to concentrate on web.Because the height ratio panels of light sandwich are higher by several times, biquadratic increases the moment of inertia of section therewith, and
Panel has sandwich to support to be difficult unstability, therefore it not only increases interlayer composite material plate integral rigidity, also improves stability,
Improve the mechanical property of whole hatch door.
Thermal protection structure 18 is laid out using interlocking, as shown in figure 3, preventing hot-fluid from leaking.The material of thermal protection structure 18 meets
Material volatility total mass loss≤0.5% and volatile substances content≤0.1%, and thermal protection structure surface possesses waterproof
Steam resorption amount≤0.15% is met under function, natural environment, the performance of thermal protection structure meets use requirement after water suction.
Nacelle upper end is big opening structure, and big opening structure surrounding is respectively symmetrically setting hatch door support beam 4 and hatch door bulkhead
3,3 hinges that the main bearing beam 15 of hatch door passes through to be uniformly arranged are connected with hatch door support beam 4, and hatch door Zhan Shou mechanisms are fixed on cabin
In door support beam 4 and hatch door bulkhead 3, control hatch door is opened, closure；
To prevent aircraft thermal current under space environment from entering in cabin by hatch door gap, dual heat is set at gap
Sealing structure, the contact position of hatch door bulkhead 3, hatch door support beam 4 and hatch door 1 is respectively provided with first and reheats sealing, first reheat it is close
Envelope makes to be pasted onto on hatch door and its peripheral structure using pyroceram fibre cloth, is entered in cabin with intercepting thermal current；Fig. 7 is have
Effect load hatch door heat seal structural representation, in hatch door support beam 4 and hatch door bulkhead 3, is correspondingly arranged on sealing support beam 41
With sealing carriage 31, set fluted in sealing carriage 31 and sealing support beam 41, for placing heat seal flexible member
7, constitute second and reheat sealing, by stuffed heat insulated cotton inside the flexible member of high temperature alloy weaving filaments, outer wrap is high
Warm fiber cloth is combined, and can in high temperature environments possess good elasticity and sealing function, by heating seal flexible member 7
Resilience be further ensured that outside thermal current can not enter cabin in.
When hatch door is in closure state, hatch door surrounding is realized to hatch door by sealing carriage 31 and sealing support beam 41
The support of structure, sealing and buffer.
Fig. 8 is that payload cabin door structure and hatch door bulkhead 3 heat seal interface shape schematic diagram, hatch door bulkhead 3 with it is effective
Heat-barrier material is pasted in load hatch door side, after the completion of heat seal bonding, hatch door and the preset clearance of hatch door bulkhead 3, first reheat it is close
Envelope outer edge is concordant with hatch door outer edge.
Fig. 9 is that payload cabin door structure heats seal interface shape schematic diagram with hatch door support beam 4, and hatch door is supported with hatch door
Along normal direction gapless, deformation≤2mm of the stand under load rear door relative to aircraft door support beam 4 between fuselage at beam 4.
Hatch door in open mode rotates in the presence of hatch door Zhan Shou mechanisms around hatch door hinge, when hatch door is closed,
Left and right hatch door is snapped on hatch door bulkhead 3, and hatch door Zhan Shou mechanisms are stopped.
When hatch door is in closure state, hatch door surrounding is realized to hatch door knot by sealing carriage 31 and sealing support beam 41
The support and sealing of structure.Wherein sealing carriage 31 is fixed on the web surface of hatch door bulkhead 3, and sealing support beam 41 is fixed on hatch door
In support beam 4.Sealing carriage 31 and sealing support beam 41 are circumferentially fluted with axial arranged respectively, for placing heat seal
Flexible member 7, sealing and cushioning effect are played to hatch door closure.
Hatch door main bearing beam 15 is main force support structure, built-in hatch door center latch, for two butt-joint lockings of hatch door.Hatch door
The two ends of main bearing beam 15 are locked by hatch door end face carries out axial locking with body, and aircraft can leave the right or normal track and return to ground.
The content not being described in detail in description of the invention belongs to the known technology of professional and technical personnel in the field.
Claims (10)
1. a kind of payload space cabin structure suitable for orbiter, it is characterised in that including nacelle (8) and hatch door
(1), hatch door (1) is connected in nacelle (8), and hatch door (1) is realized opening and closed to nacelle (8), and hatch door (1) is symmetrical right for two fans
Open architecture, often fanning hatch door includes inside panel (13), exterior skin (14), main bearing beam (15), honeycomb core (16), reinforcement
(17) and thermal protection structure (18),
Honeycomb core (16) between inside panel (13), exterior skin (14), in connecing for honeycomb core (16) and exterior skin (14)
Touch and open up guiding gutter on position, reinforcement (17) is arranged between honeycomb core (16), reinforcement (17) is connected to two masters and holds
Power beam (15), is uniformly arranged three cabin door locks (2) on main bearing beam (15), two fan hatch doors realize locking mutually when closing；
Thermal protection structure (18) is arranged on exterior skin (14), using staggeredly layout, thermal protection structure (18) surface natural environment
Lower steam resorption amount≤0.15%,
Nacelle (8) upper end is big opening structure, and big opening structure surrounding is respectively symmetrically setting hatch door support beam (4) and hatch door bulkhead
(3), the main bearing beam (15) of hatch door (1) is connected by three hinges being uniformly arranged with hatch door support beam (4), hatch door exhibition receipts machine
Structure is fixed in hatch door support beam (4) and hatch door bulkhead (3), and control hatch door (1) is opened, closure；
Dual heat seal structure, hatch door bulkhead (3), hatch door are set between hatch door (1) and hatch door bulkhead (3), hatch door support beam (4)
The contact position of support beam (4) and hatch door (1) is respectively provided with first and reheats sealing；
In hatch door support beam (4) and hatch door bulkhead (3), sealing support beam (41) and sealing carriage (31) are correspondingly arranged on,
Set fluted in sealing carriage (31) and sealing support beam (41), for placing heat seal flexible member (7), constitute second
Reheat sealing, be further ensured that outside thermal current can not enter in cabin by the resilience for heating seal flexible member (7).
2. a kind of payload space cabin structure suitable for orbiter as claimed in claim 1, it is characterised in that lead
Chute width is 1~2mm, and the depth of guiding gutter is 2~3mm.
3. a kind of payload space cabin structure suitable for orbiter as claimed in claim 1, it is characterised in that heat
Material volatility total mass loss≤0.5% of safeguard structure (18).
4. a kind of payload space cabin structure suitable for orbiter as claimed in claim 1, it is characterised in that heat
Material volatile substances content≤0.1% of safeguard structure (18).
5. a kind of payload space cabin structure suitable for orbiter as claimed in claim 1, it is characterised in that interior
Covering (13), exterior skin (14) are carbon fibre reinforced composite, the paper honeycomb that honeycomb core (16) is arranged for array.
6. a kind of payload space cabin structure suitable for orbiter as claimed in claim 1, it is characterised in that the
One reheats sealing using pyroceram fibre cloth, intercepts thermal current and enters in cabin.
7. a kind of payload space cabin structure suitable for orbiter as claimed in claim 1, it is characterised in that heat
Sealed elastic element (7) is formed by high temperature alloy weaving filaments, internal stuffed heat insulated cotton, outer wrap high temperature fiber cloth.
8. a kind of payload space cabin structure suitable for orbiter as claimed in claim 1, it is characterised in that cabin
When door (1) is in closure state, hatch door surrounding is by sealing carriage (31), sealing support beam (41) and heat seal flexible member
(7) support to hatch door (1), sealing, are realized and is buffered.
9. a kind of payload space cabin structure suitable for orbiter as claimed in claim 7, it is characterised in that the
One reheat sealing outer edge it is concordant with hatch door (1) outer edge.
10. a kind of payload space cabin structure suitable for orbiter as claimed in claim 1, it is characterised in that
After hypersonic environment stand under load, deformation≤2mm of the hatch door (1) with respect to hatch door support beam (4).
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| CN201611163100.1A CN106742065B (en) | 2016-12-15 | 2016-12-15 | A kind of payload space cabin structure suitable for orbiter |
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| CN201611163100.1A CN106742065B (en) | 2016-12-15 | 2016-12-15 | A kind of payload space cabin structure suitable for orbiter |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107525435A (en) * | 2017-08-28 | 2017-12-29 | 北京航天发射技术研究所 | A kind of composite hatchcover and preparation method thereof |
| CN107839899A (en) * | 2017-09-19 | 2018-03-27 | 上海卫星工程研究所 | Suitable for the installation top plate of remote sensing of the earth Satellite Payloads |
| CN108725844A (en) * | 2018-06-26 | 2018-11-02 | 北京蓝箭空间科技有限公司 | The control cabin structure of space launch vehicle |
| CN110001684A (en) * | 2019-04-18 | 2019-07-12 | 西北工业大学 | The double covering pressurized constructions of vacuum line magnetic suspension train |
| CN110027695A (en) * | 2019-04-30 | 2019-07-19 | 中国商用飞机有限责任公司 | Honeycomb skin structure for aircraft |
| CN115180172A (en) * | 2022-06-20 | 2022-10-14 | 成都飞机工业（集团）有限责任公司 | Method for producing a side wall panel in a load compartment, wall panel, arrangement, storage medium and installation |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107525435A (en) * | 2017-08-28 | 2017-12-29 | 北京航天发射技术研究所 | A kind of composite hatchcover and preparation method thereof |
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| CN107839899A (en) * | 2017-09-19 | 2018-03-27 | 上海卫星工程研究所 | Suitable for the installation top plate of remote sensing of the earth Satellite Payloads |
| CN107839899B (en) * | 2017-09-19 | 2021-05-11 | 上海卫星工程研究所 | Installation roof suitable for ground remote sensing satellite payload |
| CN108725844A (en) * | 2018-06-26 | 2018-11-02 | 北京蓝箭空间科技有限公司 | The control cabin structure of space launch vehicle |
| CN108725844B (en) * | 2018-06-26 | 2020-04-21 | 蓝箭航天空间科技股份有限公司 | Control cabin structure of space carrier |
| CN110001684A (en) * | 2019-04-18 | 2019-07-12 | 西北工业大学 | The double covering pressurized constructions of vacuum line magnetic suspension train |
| CN110027695A (en) * | 2019-04-30 | 2019-07-19 | 中国商用飞机有限责任公司 | Honeycomb skin structure for aircraft |
| CN115180172A (en) * | 2022-06-20 | 2022-10-14 | 成都飞机工业（集团）有限责任公司 | Method for producing a side wall panel in a load compartment, wall panel, arrangement, storage medium and installation |
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