CN109911247A - Rocket and its propellant tank - Google Patents
Rocket and its propellant tank Download PDFInfo
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- CN109911247A CN109911247A CN201910189651.2A CN201910189651A CN109911247A CN 109911247 A CN109911247 A CN 109911247A CN 201910189651 A CN201910189651 A CN 201910189651A CN 109911247 A CN109911247 A CN 109911247A
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- tank
- section
- propellant
- propellant tank
- rocket
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- 239000003380 propellant Substances 0.000 title claims abstract description 55
- 238000010276 construction Methods 0.000 claims abstract description 6
- 239000003795 chemical substances by application Substances 0.000 claims description 15
- 239000007800 oxidant agent Substances 0.000 claims description 15
- 230000001590 oxidative effect Effects 0.000 claims description 13
- 238000009413 insulation Methods 0.000 claims description 7
- 238000003672 processing method Methods 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 5
- 239000002360 explosive Substances 0.000 claims description 4
- 238000009987 spinning Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 8
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 12
- 238000003466 welding Methods 0.000 description 9
- 230000002787 reinforcement Effects 0.000 description 7
- 238000009835 boiling Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 6
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000003860 storage Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- 238000007493 shaping process Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 239000002937 thermal insulation foam Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
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- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The present invention provides a kind of rocket and its propellant tank, including the first tank, the second tank and cab signal box bottom, the first tank and the second tank are connected by cab signal box bottom, and cab signal box bottom forms enclosed construction with the junction of the first tank and the second tank respectively.Rocket and its propellant tank provided by the invention, eliminate the cascaded structure of inter-tank section, can effectively shorten rocket body height, reduce the slenderness ratio of carrier rocket, are conducive to the stability for increasing rocket, and rocket weight is most light, space utilization rate highest, and carrying capacity is maximum.And cost can significantly be reduced using standardized structure, shorten the manufacturing cycle, improve the reliability of product.
Description
Technical field
The present invention relates to the technical fields of carrier rocket processing, and in particular to a kind of rocket and its propellant tank.
Background technique
The tank of traditional carrier rocket is generally cascaded structure, as shown in Figures 1 and 2, tank include oxidant tank 1,
Incendiary agent tank 2 and inter-tank section 3, oxidant tank 1 and incendiary agent tank 2 are attached by inter-tank section 3.Oxidant tank 1
Function with incendiary agent tank 2 is storage propellant, while transmitting the load of rocket, and inter-tank section 3 mainly connects oxidant storage
Case 1 and incendiary agent tank 2.Tank is closed structure, and the connection between all parts generallys use the mode of welding, inter-tank section 3
It is the open cylindrical section in left and right, the connection between oxidant tank 1, incendiary agent tank 2 and inter-tank section 3, which uses, connects connecting bolt
It connects.This structure has the disadvantage that
(1) concatenated tank structure increases the height and slenderness ratio of rocket, that is, increase rocket total high and diameter it
Than being unfavorable for the stability of rocket body flight.
(2) traditional tank structure mostly uses welding or splicing form, number of parts to be up to over one hundred item, and process is many and diverse, system
Make that the period is long, and overall expenses is high, weld seam is more once in a while；
(3) since product category is more, generalization degree is low, and each moulds of industrial equipment for customizing component assembly are flexible poor, adapts to knot
The range of structure parameter is very narrow, is difficult to meet the requirement that business space flight low cost fast manufactures.
Summary of the invention
The purpose of the present invention is to provide a kind of rocket and its propellant tanks, to solve tank structure in the prior art
, generalization degree big with assembly difficulty be not high and height and the larger technical problem of slenderness ratio.
To achieve the above object, the technical solution adopted by the present invention is that: a kind of propellant tank is provided, comprising: first storage
Case, the second tank and cab signal box bottom, first tank are connected with second tank；The cab signal box bottom is fixed on described
Between first tank and second tank, and the cab signal box bottom company with first tank and second tank respectively
The place of connecing forms enclosed construction.
Further, first tank includes first section, the first bottom and the second bottom, first bottom and institute
It states the second bottom and is located at first section opposite end；Second tank includes second section and third bottom, and described the
Two bottoms and the third bottom are located at the opposite end of second section, and second bottom is the cab signal box
Bottom.
Further, first bottom and second bottom are fixedly connected with first section respectively, and described
Two bottoms are fixedly connected with the third bottom respectively at second section.
Further, first bottom, second bottom and the third bottom are all made of standard container base accessory, described
Standard container base accessory includes annulus and the top cover that is fixed on the annulus, offers several connecting holes on the top cover.
Further, the annulus is made of the processing method of single plate body spinning, liquid-filling shaping or explosive forming.
Further, the opposite end of the annulus is respectively first end and the second end, the first end it is straight
Diameter is less than the diameter of the second end, and the top cover is fixed on the first end.
Further, the first end is equipped with blind hole, and first through hole is offered on the top cover, and fixing piece passes through described
First through hole and the blind hole are simultaneously fixedly connected.
Further, the junction of the top cover and institute's first end is additionally provided with sealing ring.
Further, first section and second section are formed by single plate body is coiling welded.
Further, the both ends of first section are mutually welded with first bottom and second bottom respectively, institute
The one end and the third bottom for stating second section are mutually welded.
Further, the outside of second bottom is equipped with fixed station, and second section is mutually welded with the fixed station.
It further, further include delivery pipe, one end of the delivery pipe is fixed on second bottom and with described
One tank is connected, and the delivery pipe passes through second section and the third bottom and is connected to outside.
Further, the delivery pipe include tube body, the tunneltron being placed on the outside of the tube body and be set to the tunnel
Insulation between pipe and the tube body.
Further, the opposite end of the delivery pipe is additionally provided with abutted flange, and the abutted flange is respectively at described
Two bottoms are connected with the third bottom.
Further, it is convex distracted to be equipped with several reinforcements for the outer surface of the tunneltron.
It further, further include short cylinder part, the short cylinder part is set between second section and the third bottom.
Further, the short cylinder part is formed by single plate body is coiling welded.
The present invention also provides a kind of rockets, including the propellant tank as described in above-mentioned any bar, first storage
Case is for accommodating oxidant, and second tank is for accommodating incendiary agent.
The beneficial effect of rocket and its propellant tank provided by the invention is: compared with prior art, present invention fire
Arrow and its propellant tank eliminate the cascaded structure of inter-tank section, directly pass through cab signal box bottom for the first tank and the second tank
It is connected, can effectively shortens rocket body height, reduce the slenderness ratio of carrier rocket, is conducive to the stability for increasing rocket, and energy
Enough in the case where guaranteeing that repropellenting amount is the same, rocket weight is most light, space utilization rate highest, and carrying capacity is maximum.And
And cost can significantly be reduced using standardized cylinder segment structure and base, shorten the manufacturing cycle, that improves product can
By property.
Detailed description of the invention
It, below will be to specific in order to illustrate more clearly of the specific embodiment of the invention or technical solution in the prior art
Embodiment or attached drawing needed to be used in the description of the prior art be briefly described, it should be apparent that, it is described below
Attached drawing is some embodiments of the present invention,
Fig. 1 is the structural schematic diagram of the tank of traditional carrier rocket in the prior art；
Fig. 2 is the side structure schematic view of the tank of traditional carrier rocket in the prior art；
Fig. 3 is the schematic perspective view of propellant tank provided in an embodiment of the present invention；
Fig. 4 is the half section structure diagram of propellant tank shown in Fig. 3；
Fig. 5 is the structural schematic diagram of propellant tank provided in an embodiment of the present invention；
Fig. 6 is the schematic view of the front view of standard container base accessory used by the embodiment of the present invention；
Fig. 7 is the overlooking structure diagram of standard container base accessory shown in fig. 6；
Fig. 8 is the local half section structure diagram of the annulus of standard container base accessory shown in fig. 6；
Fig. 9 be propellant tank provided in an embodiment of the present invention the second bottom respectively with first section and second section
Welding structure schematic diagram；
Figure 10 is the schematic perspective view of frame reinforcement structure in purlin used by the embodiment of the present invention；
Figure 11 is the schematic perspective view of delivery pipe used by the embodiment of the present invention.
Description of symbols:
1- oxidant tank；2- incendiary agent tank；3- inter-tank section；The first tank of 4-；The second tank of 5-；6- delivery pipe；7-
Standard container base accessory；The short cylinder part of 8-；The purlin 9- frame reinforcement structure；First section of 41-；The first bottom of 42-；The second bottom of 43-；431-
Fixed station；Second section of 51-；52- third bottom；61- tube body；62- tunneltron；63- insulation；64- abutted flange；621-
Reinforce convex distracted；71- annulus；72- top cover；73- connecting hole；711- first end；712- the second end；713- blind hole；91- light
Barrel structure；The longitudinally reinforced frame of 92-；The horizontal frame of 93-.
Specific embodiment
Technical solution of the present invention is clearly and completely described below in conjunction with attached drawing, it is clear that described implementation
Example is a part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill
Personnel's every other embodiment obtained without making creative work, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for description the present invention and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.In addition, term " first ", " second ",
" third " is used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.
As long as in addition, the non-structure each other of technical characteristic involved in invention described below different embodiments
It can be combined with each other at conflict.
Also referring to Fig. 3 to Fig. 5, now propellant tank provided by the invention is illustrated.The propellant tank,
Including the first tank 4, the second tank 5 and cab signal box bottom, first tank 4 is connected with second tank 5；It is described to share
Bottom is fixed on first tank 4 and second tank) between, and the cab signal box bottom respectively with first tank 4
Enclosed construction is formed with the junction of the second tank 5.
Propellant tank provided by the invention eliminates the cascaded structure of inter-tank section 3 compared with prior art, directly logical
It crosses cab signal box bottom and the first tank 4 is connected with the second tank 5, can effectively shorten rocket body height, the length for reducing carrier rocket is thin
Than being conducive to the stability for increasing rocket, and can be in the case where guaranteeing that repropellenting amount is the same, rocket weight is most
Gently, space utilization rate highest, carrying capacity are maximum.And it can significantly be dropped using standardized cylinder segment structure and base
Low cost shortens the manufacturing cycle, improves the reliability of product.
Further, a kind of specific implementation also referring to Fig. 5 to Fig. 7, as propellant tank provided by the invention
Mode, first tank 4 include first section 41, the first bottom 42 and the second bottom 43, first bottom 42 and described
Second bottom 43 is located in first section, 41 opposite end；Second tank 5 includes second section 51 and third bottom
52, second bottom 43 and the third bottom 52 are located at the opposite end of second section 51, second case
Bottom 43 is the cab signal box bottom.Specifically, first section 41 is consistent with the structure of second section 51, the first bottom 42, second
The structure of bottom 43 and third bottom 52 is almost the same, as standardized cylinder segment structure and base.For liquid embarkation
For rocket, oxidant liquid oxygen and the comparable advantage of incendiary agent methane cryogenic propellant warm area, the wherein boiling of methane are made full use of
Point is -161.4 DEG C, and the boiling point of liquid oxygen is -183 DEG C, and liquid oxygen is than only low 21.6 DEG C of methane.The cascaded structure of inter-tank section 3 is eliminated,
Merge oxidizer tank and fuel tank, propellant tank specific gravity occupy entire 60% or more rocket body structure, it can using total bottom tank
It effectively shortens rocket body height, reduces the slenderness ratio of carrier rocket, be conducive to the stability for increasing rocket.
Further, a kind of specific implementation also referring to Fig. 5 to Fig. 7, as propellant tank provided by the invention
Mode, first bottom 42 and second bottom 43 are fixedly connected with first section 41 respectively, second bottom
43 are fixedly connected with the third bottom 52 respectively at second section 51.Specifically, first section 41 and the first bottom 42
It is directly fixedly connected with the second bottom 43, the mode being fixedly connected can be the modes such as threaded connection, bonding or welding；Second
For cylinder section 51 with third bottom 52 also to be directly fixedly connected, the mode being fixedly connected may be threaded connection, bonding or weldering
It the modes such as connects, first section 41 and the first bottom 42 and the second bottom 43 is separated, second section 51 and third bottom 52 are divided
It opens, is more advantageous to the standardized structure of building, and standardized structure is smaller, be more favorable for assembling and transport.Certainly, according to
Actual conditions and specific requirements, in other embodiments of the invention, first section 41 and the first bottom 42 and the second bottom 43
It can also directly be integrally formed, second section 51 and third bottom 52 do not limit uniquely herein also to be directly integrally formed.
Further, a kind of specific implementation also referring to Fig. 5 to Fig. 7, as propellant tank provided by the invention
Mode, first bottom 42, second bottom 43 and the third bottom 52 are all made of standard container base accessory 7, the standard
Bottom part 7 includes annulus 71 and the top cover 72 being fixed on the annulus 71, offers several connecting holes on the top cover 72
73.Specifically, forming the first bottom 42, the second bottom 43 and third bottom 52 using standard container base accessory 7, three casees can be taken into account
The function at bottom eliminates weld seam using the universal architecture of 71 part of annulus, the connecting holes such as all apertures, flange 73 is set to
Big top cover 72, top cover 72 are fixedly connected with annulus 71, can significantly be reduced cost using standardized composite structure, be shortened system
The period is made, the reliability of product is improved.Wherein, connecting hole 73 may include delivery port, boost port, exhaust outlet, pressure tap and people
Any one or more in hole.
Further, Fig. 5 to Fig. 7 is please referred to, as a kind of specific embodiment of propellant tank provided by the invention,
The annulus 71 is formed by the processing method of single plate body spinning, liquid-filling shaping or explosive forming.Specifically, integrally formed circle
Ring 71 uses the processing method of spinning, liquid-filling shaping or explosive forming, wherein the middle part of annulus 71 is uniform thickness, thickness
It is determined by the inner pressuring load and temperature environment that are born.Wherein, the inner mold face of annulus 71 can be spherical, elliposoidal or dish
Deng not limiting uniquely herein.
Further, refering to Fig. 6, as a kind of specific embodiment of propellant tank provided by the invention, the circle
The opposite end of ring 71 is respectively first end 711 and the second end 712, and the diameter of the first end 711 is less than described the
The diameter of two ends 712, the top cover 72 are fixed on the first end 711.Specifically, the cross-sectional shape of the annulus 71 is
Taper, elliposoidal or dish etc., and first end 711 and the second end 712 are located at the opposite end of the annulus 71, and should
Annulus 71 is hollow structure, the structure convex under being of the second bottom 43 at this time, using lower male structure relative to the second tank 5
Total bottom be easily achieved propellant in the first tank 4 i.e. oxidizer tank it is normal go out stream and in-flight sink to the bottom function.
Further, Fig. 6 to Fig. 8 is please referred to, as a kind of specific embodiment of propellant tank provided by the invention,
The first end 711 is equipped with blind hole 713, and first through hole is offered on the top cover 72, and fixing piece passes through the first through hole
With the blind hole 713 and be fixedly connected.Specifically, the first end 711 of annulus 71 is evenly distributed with several tapped blind holes 713, top cover 72
On corresponding position setting first through hole docking, first through hole and blind hole 713 are sequentially passed through using fixing piece and realize top cover 72
Being fixedly connected between annulus 71, connection tightness is more preferable, and top cover 72 can be replaced, convenient to realize standard container bear building-up
Structure, and 71 end of annulus is blind hole 713, and gas leak also can be effectively avoided.Wherein, fixing piece can be bolt, screw
Or the fixed structures such as fixed card buckle.
Further, as a kind of specific embodiment of propellant tank provided by the invention, the top cover 72 and institute
The junction of first end 711 is additionally provided with sealing ring (not shown).Specifically, first end 711 is provided with lug, top cover 72
Lower surface be provided with the groove for accommodating the lug, the junction in lug and groove can be set in sealing ring, close
Seal can also be arranged at the abutting of first end 711 and top cover 72.Wherein, sealing ring can be rubber or other can be real
The material now sealed.
Further, refering to Fig. 3 to Fig. 5, as a kind of specific embodiment of propellant tank provided by the invention, institute
First section 41 and second section 51 is stated to be formed by single plate body is coiling welded.Specifically, conventional cartridge segment structure is light cylinder knot
Structure 91 or inside grid reinforced structure, cylinder segment structure by 90 ° to 120 ° of arc plate of length within muti-piece 2m welding.The application
In first section 41 and second section 51 using domestic advanced wide plate rolling technique, 360 ° of cylinders of length about 4m are carried out
Coiling welded, entire cylinder section only has a longitudinal seam, wherein welding manner generally uses agitating friction to weld mode, more compared to tradition
Arc plate splicing construction, loss of weight while, improve the reliability of product, and production process also greatly simplifies, and the manufacturing cycle shortens at least
50%, wherein the inner surface of first section 41 and second section 51 can be light barrel structure 91 or inside grid reinforced structure.
Preferably, refering to fig. 10, purlin frame reinforcement structure 9, purlin frame can be set in first section 41 and second section 51
Reinforcement structure 9 includes light cylinder, longitudinally reinforced frame 92 and horizontal frame 93, and the light cylinder is hollow cylinder；The longitudinally reinforced frame 92
Length direction it is consistent with the radial direction of the light cylinder, and several longitudinally reinforced frames 92 are fixed on the interior of the light cylinder
Portion, several longitudinally reinforced frames 92 are evenly arranged along the internal circumferential of the light cylinder；And the horizontal frame 93 is around the light
The circumferential setting of cylinder, and the horizontal frame 93 is fixed on side of the longitudinally reinforced frame 92 far from the light cylinder.
Compared with the inner surface of first section 41 and second section 51 is light barrel structure 91 or inside grid reinforced structure, with vertical
It reinforces to 93 pairs of light cylinders of reinforcing frame 92 and horizontal frame, is reinforced by the radial bearing capacity of 92 pairs of light cylinders of longitudinally reinforced frame,
Reinforced by the lateral bearing capacity of horizontal 93 pairs of light cylinders of frame, and longitudinally reinforced frame 92 and horizontal frame 93 can construct Universal Die
Block, it includes independent component can adapt to wide in range load working condition, and each part is adopted according to mission requirements flexible combination
It is supplied and is produced with standard specification, production cost is lower.Light cylinder, longitudinally reinforced frame 92 and horizontal frame 93 in tank all can be one
Bodyization design, compared to the siding of tradition machinery milling, structure partial change is smaller, can flexibly handle in design and producing,
Technology category can effectively be simplified, reduce the turnover process between equipment investment and process.Purlin frame reinforcement structure 9 its with light cylinder
The advantages of being simple to manufacture also has the advantages that increase the light-weighted of the ribbed lattice structure of longitudinally reinforced frame 92 and horizontal frame 93, together
When improve the limitation of conventional mesh reinforced structure.
Further, Fig. 3, Fig. 5 and Fig. 9 are please referred to, a kind of specific implementation as propellant tank provided by the invention
Mode, the both ends of first section 41 are welded with first bottom 42 and 43 phase of the second bottom respectively, and described second
It is welded with 52 phase of third bottom one end of cylinder section 51.Specifically, first section 41 and the first bottom 42 and the second bottom 43
Directly to weld, second section 51 and third bottom 52 are also directly to weld, and wherein welding manner is that direct splicing is welded, i.e., and the
The bottom surface of a tin section 41 or second section 51 and the bottom surface of the second end 712 abut against simultaneously rotating welding, using agitating friction
The technologies such as weldering, monolithic molding are higher to initial deformation defect degree of containing, and the load-carrying properties of product are promoted, and can repeatedly use.
Further, Fig. 3, Fig. 5 and Fig. 9 are please referred to, a kind of specific implementation as propellant tank provided by the invention
The outside of mode, second bottom 43 is equipped with fixed station 431, and second section 51 is welded with 431 phase of fixed station.Tool
Body, fixed station 431 is located at the outside of the second bottom 43, and fixed station 431 is located at the second bottom 43 close to the second end 712
Side, fixed station 431 protrude from the second bottom 43 and are arranged and form the platform that can be connect with the contacted inner surfaces of second section 51
Face, and fixed station 431 and the realization of the inner surface of second section 51 are welded and fixed, fixed structure is more stable, and cost is relatively low.
Further, Fig. 4, Fig. 5 and Figure 11 are please referred to, a kind of specific implementation as propellant tank provided by the invention
Mode, one end of the delivery pipe 6 are fixed on second bottom 43 and are connected with first tank 4, the delivery pipe 6
Across second section 51 and the third bottom 52 and it is connected to outside.
Further, Fig. 4, Fig. 5 and Figure 11 are please referred to, a kind of specific implementation as propellant tank provided by the invention
Mode, the delivery pipe 6 include tube body 61, the tunneltron 62 for being placed on 61 outside of tube body and are set to 62 and of tunneltron
Insulation 63 between the tube body 61.Specifically, tunneltron 62 is located at the outside of delivery pipe 6, tube body 61 is light wall construction,
The outside setting tunneltron 62 of tube body 61 can play the role of spacer medium and temperature field, and tunneltron 62 can carry internal pressure
Load, tube body 61 are able to bear outer compressive load, and tube body 61 is avoided to damage under the collective effect of inner pressuring load and outer compressive load
It is bad, insulation 63 is set between tunneltron 62 and tube body 61, heat preservation and insulation can be played the role of.Wherein, insulation 63
Heat insulation foam is generally used, heat insulation foam is pasted between tube body 61 and tunneltron 62.
Further, Figure 11 is please referred to, it is described as a kind of specific embodiment of propellant tank provided by the invention
The opposite end of delivery pipe 6 is additionally provided with abutted flange 64, and institute's abutted flange 64 is respectively at second bottom 43 and the third
Bottom 52 is connected.Specifically, the both ends of delivery pipe 6 are connected with the second bottom 43 with third bottom 52 respectively, act on
In the substance in the first tank 4 is sent to the outside of entire propellant tank, and make in the first tank 4 and the second tank 5
Substance be unlikely to mix too early.It is provided with and is used for and the corresponding flange of delivery pipe 6 in second bottom 43 and third bottom 52
Hole, and flange hole is opened on top cover 72, is conducive to the second bottom 43 and third bottom 52 forms standardized structure.
Further, Figure 11 is please referred to, it is described as a kind of specific embodiment of propellant tank provided by the invention
The outer surface of tunneltron 62 is equipped with several reinforcements convex distracted 621.Rise specifically, tunneltron 62 is generally after aluminum alloy plate materials are welded
Shape reinforces convex stupefied height and is generally 10 to 15mm, thickness 2 to 3mm.Reinforce convex distracted 621 to set around the outer surface of tunneltron 62
It sets, can uniformly reinforce the intensity of entire tunneltron 62, so that the tube body 61 inside tunneltron 62 is supported and be protected.
Further, Fig. 3 to Fig. 5 is please referred to, as a kind of specific embodiment of propellant tank provided by the invention,
It further includes short cylinder part 8, and the short cylinder part 8 is set between second section 51 and the third bottom 52.Specifically, short cylinder
The both ends of part 8 are mutually welded with second section 51 with the second end 712 of third bottom 52 respectively, and weld seam is around short cylinder part 8, at this time
Weld seam is less, substantially reduces the quantity of weld seam, and welding thickened area reduces accordingly, and structure is useless to be mitigated again.And it is possible to according to reality
The length of the second tank 5 is adjusted in border situation, and short cylinder part 8 or standardized structural, and product versatility degree is high,
High reliablity, cost reduce
Further, as a kind of specific embodiment of propellant tank provided by the invention, the short cylinder part 8 is by list
One plate body is coiling welded to be formed.Specifically, the structure of the structure and processing method and first section 41 of short cylinder part 8 and second section 51 and
Processing method is almost the same, cancels the splicing of multi wall plate to short cylinder part 8, is directly welded into the agitating friction of 360 degree of arc plate
Long cylinder, process-cycle substantially reduce than traditional structure, using the weldering of advanced agitating friction, monolithic molding technology to initial deformation
Defect degree of containing is higher, and the load-carrying properties of product are promoted, and can repeatedly use.
Fig. 3 to Figure 11 is please referred to, the present invention also provides a kind of rocket, the rocket includes the propulsion as above stated in any bar
Agent tank, first tank 4 is for accommodating oxidant, and second tank 5 is for accommodating incendiary agent.
Rocket provided by the invention eliminates the cascaded structure of inter-tank section 3, merges the first tank 4 and the second tank 5, can
It effectively shortens rocket body height, reduces the slenderness ratio of carrier rocket, be conducive to the stability for increasing rocket, and can guarantee push away
Into agent adding amount it is the same in the case where, rocket weight is most light, space utilization rate highest, and carrying capacity is maximum.And the standard of using
The cylinder segment structure and base of change can significantly reduce cost, shorten the manufacturing cycle, improve the reliability of product.
Specifically, the first tank 4 accommodates oxidant, i.e. the first tank 4 is equivalent to the oxidant tank 1 in traditional technology,
Oxidant is generally liquid oxygen, and boiling point is -183 DEG C；Second tank 5 accommodates incendiary agent, i.e. the second tank 5 is equivalent to incendiary agent storage
Case 2, incendiary agent generally use methane, and the boiling point of methane is -161.4 DEG C, and the boiling point of liquid oxygen is than only low 21.6 DEG C of the boiling point of methane.
Obviously, the above embodiments are merely examples for clarifying the description, and does not limit the embodiments.It is right
For those of ordinary skill in the art, can also make on the basis of the above description it is other it is various forms of variation or
It changes.There is no necessity and possibility to exhaust all the enbodiments.And it is extended from this it is obvious variation or
It changes still within the protection scope of the invention.
Claims (18)
1. propellant tank, it is characterised in that: including
First tank (4) and the second tank (5), first tank (4) are connected with second tank (5)；
Cab signal box bottom, the bottom is fixed between first tank (4) and second tank (5), and the cab signal box
Bottom forms enclosed construction with the junction of first tank (4) and second tank (5) respectively.
2. bottom structure altogether as described in claim 1, it is characterised in that: first tank (4) includes first section (41), the
One bottom (42) and the second bottom (43), first bottom (42) and second bottom (43) are located in described first
Cylinder section (41) opposite end；
Second tank (5) includes second section (51) and third bottom (52), second bottom (43) and the third bottom
(52) it is located at the opposite end of second section (51), second bottom (43) is the cab signal box bottom.
3. propellant tank as claimed in claim 2, it is characterised in that: first bottom (42) and second bottom
(43) it is fixedly connected respectively with first section (41), second bottom (43) and the third bottom (52) are respectively at institute
Second section (51) is stated to be fixedly connected.
4. propellant tank as claimed in claim 3, it is characterised in that: first bottom (42), second bottom
(43) it is all made of standard container base accessory (7) with the third bottom (52), the standard container base accessory (7) includes annulus (71) and fixes
In offering several connecting holes (73) on the top cover (72) on the annulus (71), the top cover (72).
5. propellant tank as claimed in claim 4, it is characterised in that: the annulus (71) is by single plate body spinning, filling liquid
The processing method of forming or explosive forming is made.
6. propellant tank as claimed in claim 4, it is characterised in that: the opposite end of the annulus (71) is respectively first
End (711) and the second end (712), the diameter of the first end (711) are less than the diameter of the second end (712),
The top cover (72) is fixed on the first end (711).
7. propellant tank as claimed in claim 6, it is characterised in that: the first end (711) is equipped with blind hole (713),
Offer first through hole on the top cover (72), fixing piece passes through the first through hole and the blind hole (713) and is fixedly connected.
8. propellant tank as claimed in claim 6, it is characterised in that: the top cover (72) and institute's first end (711)
Junction is additionally provided with sealing ring.
9. propellant tank as claimed in claim 2, it is characterised in that: first section (41) and second section
(51) it is formed by single plate body is coiling welded.
10. propellant tank as claimed in claim 3, it is characterised in that: the both ends of first section (41) respectively with institute
It states the first bottom (42) mutually to weld with second bottom (43), one end of second section (51) and the third bottom
(52) it mutually welds.
11. propellant tank as claimed in claim 10, it is characterised in that: the outside of second bottom (43), which is equipped with, to be fixed
Platform (431), second section (51) are mutually welded with the fixed station (431).
12. propellant tank as claimed in claim 2, it is characterised in that: it further includes delivery pipe (6), the delivery pipe (6)
One end be fixed on second bottom (43) and be connected with first tank (4), the delivery pipe (6) passes through described the
Two sections (51) and the third bottom (52) are simultaneously connected to outside.
13. propellant tank as claimed in claim 12, it is characterised in that: the delivery pipe (6) includes tube body (61), is placed on
Tunneltron (62) on the outside of the tube body (61) and the insulation being set between the tunneltron (62) and the tube body (61)
(63)。
14. propellant tank as claimed in claim 12, it is characterised in that: the opposite end of the delivery pipe (6) is additionally provided with
Abutted flange (64), the abutted flange (64) are connected respectively at second bottom (43) with the third bottom (52).
15. propellant tank as claimed in claim 13, it is characterised in that: the outer surface of the tunneltron (62) is equipped with several
Reinforce convex distracted (621).
16. such as the described in any item propellant tanks of claim 1 to 15, it is characterised in that: it further includes short cylinder part (8), institute
Short cylinder part (8) are stated to be set between second section (51) and the third bottom (52).
17. propellant tank as claimed in claim 16, it is characterised in that: the short cylinder part (8) is welded shape by single plate body
At.
18. rocket, it is characterised in that: including the described in any item propellant tanks of such as claim 1 to 17, first tank
(4) for accommodating oxidant, second tank (5) is for accommodating incendiary agent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910189651.2A CN109911247A (en) | 2019-03-13 | 2019-03-13 | Rocket and its propellant tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910189651.2A CN109911247A (en) | 2019-03-13 | 2019-03-13 | Rocket and its propellant tank |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109911247A true CN109911247A (en) | 2019-06-21 |
Family
ID=66964633
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910189651.2A Pending CN109911247A (en) | 2019-03-13 | 2019-03-13 | Rocket and its propellant tank |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109911247A (en) |
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| CN110712005A (en) * | 2019-10-23 | 2020-01-21 | 北京深蓝航天科技有限公司 | Tank storage device based on hydraulic forming technology |
| CN110714857A (en) * | 2019-10-09 | 2020-01-21 | 北京星际荣耀空间科技有限公司 | Energy dissipation device |
| CN110961820A (en) * | 2019-12-28 | 2020-04-07 | 天津航天长征火箭制造有限公司 | Assembly welding process and turnover tool for storage box body with common-bottom structure |
| CN111173645A (en) * | 2019-11-27 | 2020-05-19 | 上海宇航系统工程研究所 | Liquid rocket storage tank binding structure |
| CN112012849B (en) * | 2020-10-15 | 2021-03-16 | 北京星际荣耀空间科技股份有限公司 | Vortex-proof collapse-proof structure and propellant storage tank with same |
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| CN112969640A (en) * | 2019-10-10 | 2021-06-15 | 株式会社新史航空 | Composite material inner frame multiple joint type barrel, shell integrated type emitter propellant storage tank comprising same and preparation method thereof |
| CN113323771A (en) * | 2021-07-06 | 2021-08-31 | 北京宇航推进科技有限公司 | Modular power system for spacecraft and power propulsion method |
| CN114183685A (en) * | 2021-10-25 | 2022-03-15 | 中国运载火箭技术研究院 | Bearing type heat insulation supporting structure of low-temperature storage tank |
| CN115628155A (en) * | 2022-12-01 | 2023-01-20 | 精易兴航(北京)科技创新有限公司 | Common-bottom storage tank and rocket structure thereof |
| CN115750142A (en) * | 2022-10-31 | 2023-03-07 | 北京九天行歌航天科技有限公司 | Rocket low-temperature storage tank common-bottom heat insulation structure and processing method thereof |
| CN116025841A (en) * | 2022-11-30 | 2023-04-28 | 上海空间推进研究所 | Preparation method of common-bottom composite material storage tank shell |
| CN117869113A (en) * | 2023-12-26 | 2024-04-12 | 北京天兵科技有限公司 | Low-temperature storage tank propellant conveying structure and carrier rocket |
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| US20220026022A1 (en) * | 2019-10-10 | 2022-01-27 | Anh Structure Co., Ltd. | Composite inner frame multi-bonded barrel, shell-integrated projectile propellant tank including same, and method for manufacturing those |
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| CN112969640A (en) * | 2019-10-10 | 2021-06-15 | 株式会社新史航空 | Composite material inner frame multiple joint type barrel, shell integrated type emitter propellant storage tank comprising same and preparation method thereof |
| CN110712005A (en) * | 2019-10-23 | 2020-01-21 | 北京深蓝航天科技有限公司 | Tank storage device based on hydraulic forming technology |
| CN111173645A (en) * | 2019-11-27 | 2020-05-19 | 上海宇航系统工程研究所 | Liquid rocket storage tank binding structure |
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| CN110961820A (en) * | 2019-12-28 | 2020-04-07 | 天津航天长征火箭制造有限公司 | Assembly welding process and turnover tool for storage box body with common-bottom structure |
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| CN112523897B (en) * | 2020-11-27 | 2022-06-03 | 北京宇航系统工程研究所 | Special-shaped storage box outflow device |
| CN112523897A (en) * | 2020-11-27 | 2021-03-19 | 北京宇航系统工程研究所 | Special-shaped storage box outflow device |
| CN113323771A (en) * | 2021-07-06 | 2021-08-31 | 北京宇航推进科技有限公司 | Modular power system for spacecraft and power propulsion method |
| CN114183685A (en) * | 2021-10-25 | 2022-03-15 | 中国运载火箭技术研究院 | Bearing type heat insulation supporting structure of low-temperature storage tank |
| CN114183685B (en) * | 2021-10-25 | 2023-12-12 | 中国运载火箭技术研究院 | Bearing type heat insulation supporting structure of low-temperature storage box |
| CN115750142A (en) * | 2022-10-31 | 2023-03-07 | 北京九天行歌航天科技有限公司 | Rocket low-temperature storage tank common-bottom heat insulation structure and processing method thereof |
| CN115750142B (en) * | 2022-10-31 | 2024-06-07 | 北京九天行歌航天科技有限公司 | Rocket low-temperature storage tank common-bottom heat insulation structure and processing method thereof |
| CN116025841A (en) * | 2022-11-30 | 2023-04-28 | 上海空间推进研究所 | Preparation method of common-bottom composite material storage tank shell |
| CN115628155A (en) * | 2022-12-01 | 2023-01-20 | 精易兴航(北京)科技创新有限公司 | Common-bottom storage tank and rocket structure thereof |
| CN117869113A (en) * | 2023-12-26 | 2024-04-12 | 北京天兵科技有限公司 | Low-temperature storage tank propellant conveying structure and carrier rocket |
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Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Applicant after: Beijing Star glory Space Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Applicant before: BEIJING I-SPACE TECHNOLOGY Co.,Ltd. |
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Application publication date: 20190621 |