CN113212808A - Carrier rocket based on extrusion engine - Google Patents
Carrier rocket based on extrusion engine Download PDFInfo
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- CN113212808A CN113212808A CN202110488214.8A CN202110488214A CN113212808A CN 113212808 A CN113212808 A CN 113212808A CN 202110488214 A CN202110488214 A CN 202110488214A CN 113212808 A CN113212808 A CN 113212808A
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- 238000001125 extrusion Methods 0.000 title claims abstract description 18
- 239000007788 liquid Substances 0.000 claims abstract description 13
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 11
- 239000000446 fuel Substances 0.000 claims description 11
- 238000011084 recovery Methods 0.000 claims description 6
- 238000005192 partition Methods 0.000 claims description 5
- 235000015842 Hesperis Nutrition 0.000 claims description 4
- 235000012633 Iberis amara Nutrition 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 claims description 4
- 238000000926 separation method Methods 0.000 claims description 4
- IBSREHMXUMOFBB-JFUDTMANSA-N 5u8924t11h Chemical compound O1[C@@H](C)[C@H](O)[C@@H](OC)C[C@@H]1O[C@@H]1[C@@H](OC)C[C@H](O[C@@H]2C(=C/C[C@@H]3C[C@@H](C[C@@]4(O3)C=C[C@H](C)[C@@H](C(C)C)O4)OC(=O)[C@@H]3C=C(C)[C@@H](O)[C@H]4OC\C([C@@]34O)=C/C=C/[C@@H]2C)/C)O[C@H]1C.C1=C[C@H](C)[C@@H]([C@@H](C)CC)O[C@]11O[C@H](C\C=C(C)\[C@@H](O[C@@H]2O[C@@H](C)[C@H](O[C@@H]3O[C@@H](C)[C@H](O)[C@@H](OC)C3)[C@@H](OC)C2)[C@@H](C)\C=C\C=C/2[C@]3([C@H](C(=O)O4)C=C(C)[C@@H](O)[C@H]3OC\2)O)C[C@H]4C1 IBSREHMXUMOFBB-JFUDTMANSA-N 0.000 claims 1
- 238000005452 bending Methods 0.000 claims 1
- 238000006243 chemical reaction Methods 0.000 claims 1
- 238000007599 discharging Methods 0.000 claims 1
- 239000007800 oxidant agent Substances 0.000 claims 1
- 230000001590 oxidative effect Effects 0.000 claims 1
- 230000002787 reinforcement Effects 0.000 claims 1
- 238000010008 shearing Methods 0.000 claims 1
- 239000007921 spray Substances 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 239000000463 material Substances 0.000 abstract description 2
- 230000007547 defect Effects 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Natural products C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 239000002699 waste material Substances 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/401—Liquid propellant rocket engines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a multistage liquid carrier rocket adopting an extrusion type liquid rocket engine. The rocket adopts a low-cost extrusion type liquid engine, each sublevel engine is fixed below a spherical shell of a storage tank in an annular parallel mode, a high-pressure-resistant intersecting spherical shell common-bottom storage tank structure made of high-strength materials is adopted, the rocket realizes that a payload is sent into a space orbit through multi-stage ignition, each sublevel of the rocket is connected and separated through a small-diameter sublevel section connected with the spherical shell of the storage tank, a first sublevel structure, a second sublevel structure and a fairing of the rocket are all recovered through ballistic falling water, and the first sublevel and the second sublevel rely on high-pressure gas discharged and ignited in the storage tank to realize recoil deceleration when approaching the falling water, so that the falling water impact is reduced. Based on the comprehensive measures, the structural weight can be greatly reduced, the number of parts is reduced, the manufacturing cost is reduced, and the low-cost reusable rocket design is realized.
Description
Technical Field
The invention relates to the field of launching of space rockets, in particular to a design scheme of a low-cost reusable rocket.
Background
The current carrier rocket comprises two types of solid fuel and liquid fuel, wherein the solid fuel rocket has the defects of high cost and low carrying capacity, and the liquid rocket mostly needs to use a complex turbine pump to pressurize the fuel, so that the liquid rocket has the defects of complex structure, low reliability and high cost. Extrusion formula engine has with low costs, the reliable advantage of simple structure, but because need carry out whole pressure boost to liquid fuel storage tank, requires the storage tank structure to bear very high internal pressure, and this will reduce rocket carrying capacity in three aspects: firstly, the thickness and the weight of the storage box structure are increased; secondly, the pressure of the combustion chamber of the engine is obviously lower than that of the scheme adopting a turbine pump, so that the specific impulse of the engine is greatly reduced; and thirdly, the weight demand of the gas for pressurization in the storage tank is far greater than that of the pumping-type engine, so that the flying waste weight is increased. The above disadvantages result in extrusion engines that are not the mainstream solution for current rocket designs, and are currently used only for the last stage of a few rockets (the last stage operates in a vacuum environment, and has low requirements on boost pressure).
In the aspect of recovery technology, the most successful scheme in the world at present is an expanding landing leg buffer recovery scheme of the American SpaceX company, the scheme has very high requirements on multiple engine starting, thrust control, navigation guidance control and buffer landing technologies, and has the defects of large landing device weight and large requirement on landing reverse thrust deceleration fuel, so that the carrying capacity is influenced.
Aiming at the problems, on the premise of fully playing the advantages of simple structure and low cost of the extrusion engine, the structure weight and the recovery difficulty are reduced as much as possible by optimally designing the rocket structure, and the scheme of designing and realizing the reusable carrier rocket based on the extrusion engine is an important direction for reducing the launching cost of the carrier rocket.
Disclosure of Invention
The invention mainly solves the technical problem of providing a reusable low-cost multistage carrier rocket scheme using an extrusion type liquid engine and an intersecting spherical shell common-bottom storage tank, which can reduce the structural weight of the rocket, reduce the manufacturing cost of the rocket, and facilitate the reliable recovery of most structures except the final stage, thereby greatly reducing the launching cost of the rocket.
The invention has the beneficial effects that: on the premise of reducing the carrying efficiency (the ratio of the mass of the effective load launched into orbit by the rocket to the mass of takeoff) within a small acceptable range, the carrier rocket is manufactured at low cost and can be recycled, the reliability of the carrier rocket is improved, and the cost of launching the effective load per unit mass into space is greatly reduced.
Drawings
FIG. 1 is a schematic diagram of a preferred embodiment of the present invention;
FIG. 2 is a schematic representation of the interstage separation of a preferred embodiment of the rocket of the present invention;
the parts in the drawings are numbered as follows:
one-stage engine(s);
a first-level common-bottom storage tank;
the first-level storage tank is provided with a bottom-sharing partition plate;
fourthly, a secondary interstage fairing;
a second-level period;
sixthly, a secondary engine;
seventhly, a secondary storage tank;
eighthly, a second-stage storage tank is provided with a bottom partition plate;
ninthly, three sub-stages (including annular intersected spherical shell storage tanks and engines);
an r fairing.
Detailed Description
The following detailed description of the preferred embodiments of the present invention with reference to fig. 1 and 2 is provided to enable those skilled in the art to more easily understand the advantages and features of the present invention, so as to clearly and clearly define the protection scope of the present invention.
Referring to fig. 1 and 2, a reusable launch vehicle based on an extrusion engine according to an embodiment of the present invention includes:
1) the rocket is a three-stage rocket, and three substages all adopt extrusion type liquid oxygen methane rocket engines;
2) the pressurizing pressure of each sub-stage is not less than 1.0MPa, and the pressure of one sub-stage is higher;
3) the first sub-stage and the second sub-stage are serially connected intersecting spherical shell common-bottom storage tanks, and the third sub-stage is an annular intersecting spherical shell storage tank;
4) the rocket storage tanks are made of high-strength alloy steel, and the yield strength of the material in the use environment is not lower than 1000 MPa;
5) the diameter of the first-level storage tank is 5.0 meters, the distance between the centers of the intersected spherical shells is 2.5 meters, and the thicknesses of the spherical shells and the partition plates are equal;
6) in order to avoid fuel waste, the common bottom clapboard is in a convex shape, and the thickness of the common bottom clapboard is slightly higher than that of other non-common bottom clapboards;
7) the diameter of the secondary stage is 5.0 meters, and the structural form is similar to that of the primary stage;
8) each spherical shell of the three-sub-stage storage box has the diameter of 2.0 m, and the three-sub-stage storage box and the instrument cabin are integrally designed and are integrally enveloped by the fairing;
9) the diameter of the first secondary stage section is 2.0 meters, the height is 0.5 meters, the first secondary stage section is a bearing structure, and the interstage separation is realized;
10) the diameter of the secondary interstage fairing is 5.0 meters, the height of the secondary interstage fairing is 5.0 meters, the secondary interstage fairing is of a pneumatic dimensional structure and does not bear flight loads. A secondary interstage fairing can be eliminated on the premise of meeting pneumatic safety;
11) the third sub-stage is connected with the second sub-stage through a plurality of explosive bolts and realizes separation;
12) the first sub-stage adopts 12 extrusion engines with sea level thrust of 800kN and total takeoff thrust of 9600kN, and the second sub-stage adopts 4 extrusion engines with vacuum thrust of 1000 kN; the three-level adopts 4 extrusion engines with vacuum thrust of 100 kN;
13) the secondary engine and the rocket axis are arranged at an angle of 30 degrees;
14) each sub-stage oxygen box and each combustion box adopt a self-generation pressurization mode;
15) before the first sublevel and the second sublevel fall into water, high-pressure oxygen and methane in the storage tank are pressed into a plurality of engine combustion chambers, so that reverse thrust braking is realized, and the falling water speed is reduced to a structure bearable range;
the above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes performed by the present specification and drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (5)
1. A low cost reusable launch vehicle based on an extrusion engine; it is characterized by comprising: firstly, a low-cost extrusion type liquid rocket engine is used; secondly, the rocket is generally a multi-stage carrier rocket, the launching of a satellite into orbit can be realized by three stages or four stages, and the sub-orbit flight can be realized by a single-stage rocket; thirdly, a plurality of engines are connected in parallel in the boosting stages of the first sub-stage, the second sub-stage and the like, and the parallel engines are circumferentially and symmetrically distributed at the bottom of the storage tank; fourthly, using an intersecting spherical shell common-bottom storage box; connecting the top of the first sub-stage of the rocket and the spherical shell at the tail end of the second sub-stage of the rocket through a small-diameter and small-height stage section, and designing an interstage separation device in the stage section; sixthly, the secondary engine can be inclined to the axis of the rocket when being installed, and the secondary engine can rotate to be parallel to the axis of the rocket after being separated; seventhly, except for the final stage, all booster stages and all fairing of the rocket are recovered through splashing water; and before each recovery sublevel falls into water, high-pressure gas in the storage tank is sent to the engine and ignited to realize reverse thrust deceleration and reduce the falling speed.
2. The extrusion engine-based liquid launch vehicle of claim 1, wherein: firstly, each boosting sub-stage adopts an extrusion type liquid engine, and fuel and oxidant are pushed into an engine combustion chamber by the internal pressure of a storage tank; secondly, the type of the engine fuel is not limited, and in order to reduce the volume of the fuel, high-density specific impulse liquid fuel is firstly used; and thirdly, each sub-stage adopts a plurality of small-thrust engines which are connected in parallel to meet the requirement of total thrust, and the sub-stage engines are distributed around the axis of the rocket in parallel at the periphery of the ball bottom at the lower end of the sub-stage storage box.
3. The multi-stage launch vehicle of claim 1, wherein: firstly, if the payload is to be sent into orbit around the earth, at least 2-stage rockets, generally 3-stage or 4-stage rockets are used; the sub-orbital flight can be a single-stage rocket; taking a 3-stage rocket as an example, the structure of the typical rocket is shown in the attached figure 1 and comprises a plurality of sections of a first-stage engine, a first-stage common-bottom storage tank, a second-stage section, a second-stage fairing, a plurality of second-stage engines, a second-stage common-bottom storage tank, a third-stage engine, a third-stage storage tank, a fairing (wrapping a third-stage engine and a payload) and the like; the second-level section is positioned between the spherical shells of the first-level and second-level storage tanks, the diameter of the second-level section is obviously smaller than that of the storage tanks, the height of the second-level section is preferably suitable for satisfying the annular distribution of the second-level engine, and compared with the conventional rocket-level section, the height and the diameter of the second-level section are greatly reduced; connecting and separating a secondary stage and a secondary stage through a stage section, and transferring the rocket flying load through the stage section, wherein the rocket flying load comprises axial force, bending moment and shearing force; the interstage fairing mainly plays a role in maintaining the aerodynamic appearance, almost does not bear the flight load, and can be cancelled under the condition of meeting the aerodynamic safety requirement; and seventhly, the secondary engine is obliquely arranged on the axis of the rocket to adapt to a large-size spray pipe if necessary, and the secondary engine returns to a normal state parallel to the axis of the rocket after the primary engine and the secondary engine are separated, as shown in the attached figure 2.
4. An intersecting spherical-shell bottomless tank structure according to claim 1, wherein: the storage tank is formed by intersecting a plurality of ideal spherical shells, and the ideal spherical shells are intersected in series except for the final stage, and the final stage is annularly intersected for reducing the height; secondly, a partition plate is arranged at the position of the intersecting surface of each spherical shell, and the partition plate is used as a common bottom structure or an anti-shaking plate structure among different fuels; thirdly, under equal pressure, the main bodies of the spherical shell and the clapboard are respectively of equal-thickness structures (the thicknesses of the spherical shell and the clapboard are possibly different); fourthly, arranging connecting through holes among the spherical shell clapboards of the same fuel, and considering local reinforcement; the pressurizing mode of the storage tank can adopt various modes such as compressed gas, autogenous pressurizing, chemical reaction pressurizing and the like.
5. A reusable liquid rocket as claimed in claim 1 wherein: except for the final stage, other booster sub-stages and a fairing are recovered by water surface splashing; secondly, each recovery body falls into water in a ballistic free falling mode, and if necessary, a parachute, a parafoil and a reverse thrust engine are adopted to control the landing posture or buffer and decelerate; the reverse thrust can be realized by discharging the high-pressure gas in the storage tank into the engine and igniting; fourthly, the recovered sublevels float on the water surface after falling into the water, and an air bag is used to increase the buoyancy when necessary.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110488214.8A CN113212808A (en) | 2021-05-08 | 2021-05-08 | Carrier rocket based on extrusion engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110488214.8A CN113212808A (en) | 2021-05-08 | 2021-05-08 | Carrier rocket based on extrusion engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113212808A true CN113212808A (en) | 2021-08-06 |
Family
ID=77090906
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110488214.8A Pending CN113212808A (en) | 2021-05-08 | 2021-05-08 | Carrier rocket based on extrusion engine |
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| Country | Link |
|---|---|
| CN (1) | CN113212808A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151232A (en) * | 2021-11-01 | 2022-03-08 | 北京宇航系统工程研究所 | Storage tank anti-shaking structure suitable for reusable rocket |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6293503B1 (en) * | 1998-01-30 | 2001-09-25 | D. Andy Beal | Space Launch system with pressure reduction devices between stages |
| CN1487186A (en) * | 2003-06-05 | 2004-04-07 | 王雪松 | Commercial carrier rocket with oxyhydrogen rocket enjine |
| RU2464208C1 (en) * | 2011-06-10 | 2012-10-20 | Николай Борисович Болотин | Multistage carrier rocket, liquid-propellant rocket engine, turbo pump unit and bank nozzle unit |
| WO2017018903A1 (en) * | 2015-07-28 | 2017-02-02 | Общество С Ограниченной Ответственностью "Космокурс" Ооо "Космокурс" | Method for placing a payload into orbit using a carrier rocket |
| CN106628269A (en) * | 2016-12-05 | 2017-05-10 | 中国运载火箭技术研究院 | First-child-stage parachuting-recovery carrier rocket |
| CN109018439A (en) * | 2018-08-02 | 2018-12-18 | 中国人民解放军国防科技大学 | Rocket-powered mars transporter |
| CN111322173A (en) * | 2020-02-25 | 2020-06-23 | 北京航空航天大学 | Solid-liquid rocket engine with annular column-shaped storage tank |
-
2021
- 2021-05-08 CN CN202110488214.8A patent/CN113212808A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6293503B1 (en) * | 1998-01-30 | 2001-09-25 | D. Andy Beal | Space Launch system with pressure reduction devices between stages |
| CN1487186A (en) * | 2003-06-05 | 2004-04-07 | 王雪松 | Commercial carrier rocket with oxyhydrogen rocket enjine |
| RU2464208C1 (en) * | 2011-06-10 | 2012-10-20 | Николай Борисович Болотин | Multistage carrier rocket, liquid-propellant rocket engine, turbo pump unit and bank nozzle unit |
| WO2017018903A1 (en) * | 2015-07-28 | 2017-02-02 | Общество С Ограниченной Ответственностью "Космокурс" Ооо "Космокурс" | Method for placing a payload into orbit using a carrier rocket |
| CN106628269A (en) * | 2016-12-05 | 2017-05-10 | 中国运载火箭技术研究院 | First-child-stage parachuting-recovery carrier rocket |
| CN109018439A (en) * | 2018-08-02 | 2018-12-18 | 中国人民解放军国防科技大学 | Rocket-powered mars transporter |
| CN111322173A (en) * | 2020-02-25 | 2020-06-23 | 北京航空航天大学 | Solid-liquid rocket engine with annular column-shaped storage tank |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151232A (en) * | 2021-11-01 | 2022-03-08 | 北京宇航系统工程研究所 | Storage tank anti-shaking structure suitable for reusable rocket |
| CN114151232B (en) * | 2021-11-01 | 2022-12-27 | 北京宇航系统工程研究所 | Storage tank anti-shaking structure suitable for reusable rocket |
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Effective date of registration: 20220406 Address after: 215000 factory building 11, No. 103, chenmenjing Road, Chengxiang Town, Taicang City, Suzhou City, Jiangsu Province Applicant after: Lightyear exploration (Jiangsu) Space Technology Co.,Ltd. Address before: 100086 no.1502, Hengrun international building, No.32, North Third Ring Road West, Haidian District, Beijing Applicant before: Beijing greid Technology Co.,Ltd. |