CN106134369B - A kind of spacecraft propulsion system propellant is concentrated carrying implementation method - Google Patents
A kind of spacecraft propulsion system propellant is concentrated carrying implementation methodInfo
- Publication number
- CN106134369B CN106134369B CN201218001926.4A CN201218001926A CN106134369B CN 106134369 B CN106134369 B CN 106134369B CN 201218001926 A CN201218001926 A CN 201218001926A CN 106134369 B CN106134369 B CN 106134369B
- Authority
- CN
- China
- Prior art keywords
- conical shell
- carbon fibre
- fibre composite
- propellant
- bogey
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Abstract
The present invention relates to the propellant bogey in aerospace engineering aircraft propulsion. Technical problem to be solved is to provide a kind of spacecraft propulsion system propellant and concentrates carrying implementation method, and the propellant that can effectively solve manned astro-engineering target aircraft propulsion subsystem is concentrated carrying problem. It is characterized in that: the bogey that adopts frustum form; Top is the top panel (3) of slab construction, offers some installing holes for propellant receptacle box container is installed on it; Described bogey bottom is carbon fibre of composite material conical shell (1), and is installed on the body of cabin by lower end mounting flange (5). The present invention has adopted honeycomb slab construction to add the form of composite conical shell structure, and be aided with the structural strengthening mode of various ways, rood beam as I-shaped in large scale, hat reinforcement, triangle aluminium alloy angle brace and the design of Varying-thickness step-wise transition etc., structural stability is good, and has the advantages such as structure efficiency is high, lightweight.
Description
Technical field
The present invention relates to aerospace engineering aircraft, relate generally to pushing away in aerospace engineering aircraft propulsionEnter agent bearing structure device.
Technical background
The present invention concentrates carrying problem for manned astro-engineering model propulsion subsystem solves propellantDesign, the manned spacecraft propulsion system propellant amount of carrying of China was relatively less in the past, and propellant receptacleThe installation site of box container comparatively disperses, and does not encounter the problem that needs to concentrate carrying, so in the pastThe flat sheet of metal material formula structure adopting or the bogey of composite structure can not be suitable for this system,There is no at present the propellant bogey of the large opening state of high capacity and load concentration.
And this system is having in comparatively harsh cabin in envelope limited case, propellant carries matterAmount increases again more to some extent, what therefore the installation site of the tank container of propellant can only be at bogeyNear centralized arrangement center, and need on bogey, carry out large opening and be formed for holding propellingThe large opening shape installation position of agent tank. In sum, for solve propellant more and carrying relatively collectionIn problem, can only newly grind the bogey of the dull and stereotyped large opening structure of a kind of high capacity large scale.
Summary of the invention
Technical problem to be solved by this invention is to provide a kind of spacecraft propulsion system propellant and concentrates carryingImplementation method, the propellant that can effectively solve manned astro-engineering target aircraft propulsion subsystem is concentratedCarrying problem.
For solving the problems of the technologies described above, technical solution of the present invention is:
A kind of spacecraft propulsion system propellant is concentrated carrying implementation method, it is characterized in that: adopt frustumThe bogey of form; The top panel 3 that described bogey top is slab construction, on described top panel 3Offer some installing holes for propellant receptacle box container is installed; Described bogey bottom is compositeCarbon fiber conical shell 1, and be installed on the body of cabin by lower end mounting flange 5; Described mounting flange 5 be forThe ring shape abutted flange that bogey is connected with cabin body; Described top panel 3 adopts splicing, titanium to closeGold screw connecting mode is fixedly connected on the bottom conical shell 1 of bogey, and adopt plate 3 belows in the aboveCarry out reinforcement with the rood beam 2 of I-shaped cross-section; Described mounting flange 5 passes through composite with conical shell 1The laying processing of carbon fiber is one-body molded; The junction of conical shell 1 bottom and mounting flange 5 adopts Varying-thicknessReinforcement is carried out in step-wise transition design;
The panel intermediate layer of described top panel 3 is aluminium honeycomb core layer 7, and its upper epidermis 8 and lower top layer 9 areCarbon fibre composite covering layer; Adopt 4 reinforcement of annular Al-alloy metal reinforcing frame at installing hole place,And the mode of passing through affixed metal connecting piece between adjacent metal reinforcing frame 4 is by each annular aluminium alloyMetal reinforcing frame 4 connects into an entirety for improving integral rigidity; Described aluminium honeycomb core layer 7 first andPre-buried metal reinforcing frame 4 connects by cementing form, afterwards integral form and carbon fibre compositeUpper and lower covering layer 8,9 glueds joint, and becomes plank frame, then by glueing joint and Titanium Alloy Screw connection sideFormula is connected with rood beam 2;
Described top panel 3 adopts the design of Varying-thickness step-wise transition to carry out reinforcement with the junction of conical shell 1,Described junction is also evenly provided with several triangle aluminium alloy angle braces 10 along top panel 3 marginating compartments;On the outer surface of described conical shell 1, be provided with evenly spaced some hat reinforcements 6; Described hat reinforcement6 are connected with carbon fibre composite conical shell 1 with riveting method by splicing, afterwards conical shell 1 again by glued joint,The mode that Titanium Alloy Screw connects is connected with top panel 3 and rood beam 2, then closes by splicing, titaniumGold screw connecting mode is installed aluminium alloy angle brace 10.
Preferably, the inclination angle of described conical shell 1 is designed to 45 °.
Preferably, described triangle aluminium alloy angle brace 10 is 28.
Preferably, totally 16 of the hat reinforcements 6 of described conical shell 1 outer surface, for being often separated by 22.5 ° allEven setting.
Preferably, the material of described conical shell 1 is T700 carbon fibre composite.
Preferably, the upper epidermis 8 of described top panel 3 and lower top layer 9 all adopt M40 carbon fiber compositeMaterial.
The present invention can bring following beneficial effect:
The present invention has adopted good structural configuration, and honeycomb slab construction adds composite conical shell structureForm, and be aided with the structural strengthening mode of various ways, rood beam as I-shaped in large scale, hat are strengthenedMuscle, triangle aluminium alloy angle brace and the design of Varying-thickness step-wise transition etc., the fine place module that solvedPropellant loads is comparatively concentrated the carrying problem of (installed and caused by envelope restriction by propellant tank), knotStructure has good stability. In addition, common structural member is as the situation that exists high capacity comparatively to concentrate, for guaranteeing canRow, the weight cost of sacrifice is larger, needs but still fully take into account loss of weight in design process of the present inventionAsk, not only adopted T700 carbon fibre composite as main structure conical shell material, top panel main structure moreTo have adopted M40 carbon fibre material covering to add aluminium honeycomb inner core material composition, than traditional metal materialIn weight, there is very significantly advantage. Bogey of the present invention self accounts for place module gross weight ratioExample, less than 3.6%, has the advantages such as structure efficiency is high, lightweight.
The present invention, in having solved the concentrated carrying problem of propellant, has also rationally dodged place flightThe longitudinal fundamental frequency of the whole device of device, has eliminated the hidden danger of high capacity module product in low-frequency range and the resonance of whole device.
Brief description of the drawings
Fig. 1 (a): the structure composition schematic diagram of a preferred embodiment of the present invention
Fig. 1 (b): the top view of a preferred embodiment of the present invention
Fig. 2: the top surface plate structure composition schematic diagram of a preferred embodiment of the present invention
Fig. 3: 4 aluminum alloy round ring position views of a preferred embodiment of the present invention
Fig. 4: the conical shell 1 of a preferred embodiment of the present invention and the Varying-thickness staged mistake of the junction of top panel 3Cross structural representation
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described in further detail.
In the present embodiment, in satisfied comparatively harsh cabin, under envelope limited case, need 4 propellings of carryingAgent tank, all concentrates near bogey center as the 1400kg propellant of Main Load part, andThe container installation form that loads propellant also needs to carry out the installation of large opening form, and therefore design difficulty is larger.
In conjunction with referring to Fig. 1 (a), Fig. 1 (b), in figure, 1 is conical shell, and 2 is I-shaped cross-section crossBeam, 3 is top panel, and 4 is 28 aluminium alloy angle braces, and 5 is mounting flange, and 6 is that 16 hats are strengthenedMuscle, 7 is aluminium honeycomb core layer, 8 is covering on M40 carbon fibre composite, 9 for M40 carbon fiber multipleCovering under condensation material, 10 is 4 aluminium alloy reinforcing rings. The version of the present embodiment is taper type structure,The top panel 3 of slab construction, installs needs design for adapting to container; Bottom conical shell 1, adapts to height dimensionNeed design; Lower end mounting flange 5 is the circle loop method docking for bogey is connected with cabin bodyFlange, one-body molded by the laying processing of carbon fibre of composite material with conical shell 1. This bogey entiretyVersion is the splicing construction of the connected modes such as composite material by adopting is gluedd joint, is spirally connected, riveted joint.
Top panel 3 basic composition is (in conjunction with referring to Fig. 2): aluminium honeycomb core layer 7, M40 carbon fiber are compound9,4 annular Al-alloy metal reinforcing frames of covering under covering 8, M40 carbon fibre composite on material
10。
The structural design of top panel 3:
In the present embodiment, bogey top is external diameter Φ 1900mm, the slab construction face of thickness 30mmPlate in order to solve the problem of high capacity and load concentration, has first been selected the aluminium that thickness is thicker on materialHoneycomb sandwich layer 7 thereon lower surface adopt M40 carbon fibre composite covering, and aluminium honeycomb adds composite woodThe effect on the integral rigidity that improves structure of material stressed-skin construction is comparatively obvious, simultaneously in order to prevent local stressThe excessive problem that causes aluminium honeycomb unstability, adopts annular aluminium to close at the installing hole place of 4 propellant tanksGold metal reinforcing frame 10 carries out reinforcement (specifically seeing shown in accompanying drawing 2), and adopts metal connecting piece by 4Between annular aluminium alloy reinforcing frame 10, be connected to form between two entirety (seeing accompanying drawing 3), this form is to improvingIntegral rigidity also has certain effect.
Conical shell 1 top need to the coupling part of top panel 3 and aluminium alloy heel brace 4, for preventing stress mistakeCross and can cause structure to be destroyed, need to increase conical shell 1 wall thickness of junction, therefore adopted Varying-thickness rankStepwise transition design, three ladders that are 71mm by overall length increase the 2mm thin-walled of conical shell 1 graduallyThick in 6.8mm, between each ladder and ladder, employing seamlessly transits mode and (seamlessly transits region long simultaneously8mm) realize the local reinforcement (specifically as shown in Figure 4) of stress raiser, conical shell 1 bottom and peaceLocal reinforcement design and conical shell 1 top of dress flange 5 are basically identical, are also to adopt Varying-thickness ladderFormula Transition Design is realized local reinforcement for increasing conical shell 1 wall thickness (already described) of junction above.
In addition, consider that himself longitudinal fundamental frequency of top panel 3 of slab construction form is on the low side, therefore also existTop panel 3 belows have adopted rood beam 2 to carry out reinforcement, because 4 large openings on top panel 3 exist,Therefore in the selection of the section form of rood beam 2, selected size relatively little and improve longitudinal rigidityAct on larger I-shaped cross-section. Rood beam 2 is 45 ° with large opening, and in order to adapt on conical shell 1,The Varying-thickness step-wise transition form at two ends, bottom, rood beam 2 at position corresponding thereto also as rankLadder transition face, to realize and the complete laminating of conical shell 1, does not produce fit-up gap.
The structural design of conical shell 1:
Conical shell 1, as the latter half of taper type bogey, is also an extremely important part, and it is negativeThe power of top panel 3 is passed to mounting flange 5 places by duty, and be diffused into bogey place with flange 5On the body of cabin. In the time of design, adopt T700 carbon fibre composite as conical shell 1, greatly to alleviate structureThe weight of part self. In addition, consider that top panel 3 is lower to the height of cabin body interface, by conical shell 1Inclination angle be designed to 45 ° to improve the structure efficiency of himself, avoid the intrinsic frequency of conical shell 1 itself inclined to one sideLow. Connecting portion at conical shell 1 with lower end mounting flange 5, is also one of stress position of concentrating the most,Adopted the design of Varying-thickness step-wise transition to carry out local reinforcement, configuration signal is shown in shown in accompanying drawing 4. RightThe position of concentrating the most in another place's stress is the junction of top panel 3 and conical shell 1, is spirally connected except adoptingAdd outside cementing mode, be provided with 28 triangle aluminium alloy angle braces 4 and extra uniform, and at conical shellOn take Varying-thickness step-wise transition design to carry out again reinforcement, reach top panel 3 and composite conical shell 1Good connection.
For further improve overall structure stability, the 22.5 ° of settings of being also often separated by conical shell 1 outer surfaceHat reinforcement 6, i.e. totally 16 uniform reinforcements. And inclined to one side to some sizes that exist on conical shell 1Large perforate, strengthens with Al-alloy parts at its periphery, avoids local buckling.
The installation process of the present embodiment is as follows:
1) assembly process of top panel 3 is as follows:
A), after aluminium honeycomb core layer 7 machines, add by glue and 4 pre-buried annular Al-alloy metalsStrong frame 10 carries out bonding;
B) then will aluminium honeycomb core layer 7 together with annular Al-alloy metal reinforcing frame 10 with processThe upper and lower covering 8,9 of complete M40 carbon fibre composite solidifies jointly by splicing form, solidifiesThe top panel 3 that rear formation is complete.
2) assembly technology of conical shell 1 is:
A) 16 hat reinforcements 6 are passed through to splicing and riveting method successively at T700 carbon fiber compositeThe housing outer surface of material conical shell 1 is installed;
B) some sizes hole bigger than normal on the housing of T700 carbon fibre composite conical shell 1, at its peripheryGlued joint, rivet fixing with Al-alloy parts;
3) rood beam 2 assembles together with top panel 3 and conical shell 1, adopts to glued joint to be connected with Titanium Alloy ScrewMode connects, and forms an entirety after adhesive curing completes;
4) finally 28 aluminium alloy angle braces 4 are in place by splicing, Titanium Alloy Screw connected mode;After above step finishes, complete the installation of whole bogey.
Claims (6)
1. spacecraft propulsion system propellant is concentrated a carrying implementation method, it is characterized in that: adopt coneThe bogey of platform form; The top panel (3) that described bogey top is slab construction, described aboveOn plate (3), offer some installing holes for propellant receptacle box container is installed; Described bogey bottom isCarbon fibre composite conical shell (1), and be installed on the body of cabin by lower end mounting flange (5); DescribedMounting flange (5) is the ring shape abutted flange for bogey is connected with cabin body; Above describedThe bottom carbon fiber that plate (3) employing is gluedd joint, Titanium Alloy Screw connected mode is fixedly connected on bogey is multipleCondensation material conical shell (1) is upper, and plate (3) below adopts the rood beam (2) of I-shaped cross-section to enter in the aboveRow reinforcement; Described mounting flange (5) passes through carbon fiber composite with carbon fibre composite conical shell (1)The laying processing of material is one-body molded; Carbon fibre composite conical shell (1) bottom and mounting flange (5)Junction adopts the design of Varying-thickness step-wise transition to carry out reinforcement;
The panel intermediate layer of described top panel (3) is aluminium honeycomb core layer (7), on it covering layer (8) andLower covering layer (9) is carbon fibre composite covering layer; Adopt annular aluminium alloy gold at installing hole placeBelong to reinforcing frame (10) reinforcement, and by solid between adjacent annular Al-alloy metal reinforcing frame (10)Each annular Al-alloy metal reinforcing frame (10) is connected into an entirety by the mode that connects metal connecting pieceBe used for improving integral rigidity; Described aluminium honeycomb core layer (7) first with pre-buried annular Al-alloy metalReinforcing frame (10) connects by splicing form, afterwards the upper covering of integral form and carbon fibre compositeLayer (8), lower covering layer (9) glued joint, and become plank frame, then by glueing joint and titanium alloy spiral shellNail connected mode is connected with rood beam (2);
Described top panel (3) adopts Varying-thickness ladder with the junction of carbon fibre composite conical shell (1)Formula Transition Design carries out reinforcement, and described junction is also evenly provided with some along top panel (3) marginating compartmentIndividual triangle aluminium alloy angle brace (4); On the outer surface of described carbon fibre composite conical shell (1), arrangeEvenly spaced some hat reinforcements (6); Described hat reinforcement (6) is by glueing joint and rivetingMode is connected with carbon fibre composite conical shell (1), and carbon fibre composite conical shell (1) is logical more afterwardsThe mode of crossing splicing, Titanium Alloy Screw connection is connected with top panel (3) and rood beam (2), thenBy splicing, Titanium Alloy Screw connected mode, triangle aluminium alloy angle brace (4) is installed.
2. concentrate carrying implementation method according to a kind of spacecraft propulsion system propellant claimed in claim 1,It is characterized in that: the inclination angle of described carbon fibre composite conical shell (1) is designed to 45 °.
3. concentrate carrying implementation method according to a kind of spacecraft propulsion system propellant claimed in claim 1,It is characterized in that: described triangle aluminium alloy angle brace (4) is 28.
4. concentrate carrying implementation method according to a kind of spacecraft propulsion system propellant claimed in claim 1,It is characterized in that: the hat reinforcement (6) of the outer surface of described carbon fibre composite conical shell (1) altogether16, in order to be often separated by, 22.5 ° evenly arrange.
5. concentrate carrying implementation method according to a kind of spacecraft propulsion system propellant claimed in claim 1,It is characterized in that: the material of described carbon fibre composite conical shell (1) is T700 carbon fibre composite.
6. concentrate carrying implementation method according to a kind of spacecraft propulsion system propellant claimed in claim 1,It is characterized in that: upper covering layer (8) and the lower covering layer (9) of described top panel (3) all adopt M40Carbon fibre composite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201218001926.4A CN106134369B (en) | 2012-06-18 | 2012-06-18 | A kind of spacecraft propulsion system propellant is concentrated carrying implementation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201218001926.4A CN106134369B (en) | 2012-06-18 | 2012-06-18 | A kind of spacecraft propulsion system propellant is concentrated carrying implementation method |
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| CN106134369B true CN106134369B (en) | 2014-10-22 |
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| CN201218001926.4A Expired - Fee Related CN106134369B (en) | 2012-06-18 | 2012-06-18 | A kind of spacecraft propulsion system propellant is concentrated carrying implementation method |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628266A (en) * | 2017-01-13 | 2017-05-10 | 哈尔滨工业大学 | Suspension type composite storage box structure |
| CN107745829A (en) * | 2017-09-13 | 2018-03-02 | 北京空间飞行器总体设计部 | A kind of lightweight spacecraft main structure |
| CN107782196A (en) * | 2017-10-25 | 2018-03-09 | 北京航天发射技术研究所 | Composite launching tube metal frame Cutout reinforcement structure |
| CN110001085A (en) * | 2019-03-29 | 2019-07-12 | 江苏恒神股份有限公司 | A kind of multiple one mould of material radome fairing RTM technique, two chamber preparation method |
| CN113184223A (en) * | 2020-03-13 | 2021-07-30 | 北京星际荣耀空间科技股份有限公司 | Engine supporting device and carrier rocket |
-
2012
- 2012-06-18 CN CN201218001926.4A patent/CN106134369B/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628266A (en) * | 2017-01-13 | 2017-05-10 | 哈尔滨工业大学 | Suspension type composite storage box structure |
| CN106628266B (en) * | 2017-01-13 | 2019-08-02 | 哈尔滨工业大学 | Suspension type composite material tank structure |
| CN107745829A (en) * | 2017-09-13 | 2018-03-02 | 北京空间飞行器总体设计部 | A kind of lightweight spacecraft main structure |
| CN107782196A (en) * | 2017-10-25 | 2018-03-09 | 北京航天发射技术研究所 | Composite launching tube metal frame Cutout reinforcement structure |
| CN110001085A (en) * | 2019-03-29 | 2019-07-12 | 江苏恒神股份有限公司 | A kind of multiple one mould of material radome fairing RTM technique, two chamber preparation method |
| CN113184223A (en) * | 2020-03-13 | 2021-07-30 | 北京星际荣耀空间科技股份有限公司 | Engine supporting device and carrier rocket |
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Legal Events
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| GR03 | Grant of secret patent right | ||
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| DC01 | Secret patent status has been lifted | ||
| DCSP | Declassification of secret patent | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20141022 Termination date: 20200618 |
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| CF01 | Termination of patent right due to non-payment of annual fee |