CN1487186A - Commercial carrier rocket with oxyhydrogen rocket enjine - Google Patents
Commercial carrier rocket with oxyhydrogen rocket enjine Download PDFInfo
- Publication number
- CN1487186A CN1487186A CNA03140832XA CN03140832A CN1487186A CN 1487186 A CN1487186 A CN 1487186A CN A03140832X A CNA03140832X A CN A03140832XA CN 03140832 A CN03140832 A CN 03140832A CN 1487186 A CN1487186 A CN 1487186A
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- rocket
- hydrogen
- oxygen
- liquid
- propellant
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Abstract
The commercial carrier rocket with oxyhydrogen rocket engine is one kind of carrier rocket system with simple structure and high reliability. The structure consists of one mainly loading bay, high energy stage, one main oxyhydrogen rocket engine propeller stage, two separable propellent storages bundled on two sides of the main stage and two liquid rocket boosters. It is mainly used in launching scientific instrument and commercial load to geo-stationary orbit.
Description
A kind of hydrogen-oxygen rocket commercial launch vehicle of technical field is a kind of booster system that useful load is transmitted into stationary orbit.
Background technique up to the present, main in the world stationary orbit means of transportation mostly is disposable multistage booster, and each the level independently rocket motor propulsion system is all arranged separately, complex structure and cost are higher.
Summary of the invention the design's purpose is that a kind of structure of design is slightly single, reliable performance, hydrogen-oxygen rocket commercial launch vehicle with low cost.
The main structure of hydrogen-oxygen rocket commercial launch vehicle is by the load cabin, High Energy Upper Stage, the hydrogen-oxygen rocket base level, two separable propellant tanks that laterally are bundled on the base level are formed with two liquid rocket booster rockets that are connected in parallel on the base level.Rocket is adopting the structure that laterally bundlees two separable propellant tanks of liquid on the hydrogen-oxygen rocket base level on the total arrangement, reduced the motivation on the one-stage rocket with respect to modern multistage booster, and only adopt the propulsion system of a cover hydrogen-oxygen rocket system, and advance the propellant agent of tanks to be delivered to a shared cover liquid propellant rocket engine propulsion system rocket base level and horizontal two ones of bundling by inter-stage fuel adapting system as rocket base level and two propellant tanks.Use up when the propellant tank fuel of horizontal binding, will totally separate automatically, thereby the rocket general structure is simplified with hydrogen-oxygen rocket base level and rocket.Improve the reliability and the Economy of rocket.
The hydrogen-oxygen rocket commercial launch vehicle is divided into two large divisions up and down.The top of forming rocket by load cabin and High Energy Upper Stage.By the hydrogen-oxygen rocket base level, two liquid propellant rocket engine booster rockets, two propellant tanks that laterally are bundled in the base level both sides become the lower stage of rocket.
Laterally the propellant tank of binding can be stored cryogenic propellant, and adopting liquid hydrogen and liquid oxygen is the rocket motor propellant agent.Propellant receptacle is stored in the aluminum alloy tank, and liquid oxygen tank is last, and the liquid hydrogen tank is following, and the end separates altogether between the two-stage.Thermal-protective coating is arranged in the tank, guarantee that propellant agent is not evaporated and prevents the influence that pneumatic heating causes.Tank is equipped with the propellant agent switching device that connects with the hydrogen-oxygen rocket base level.
The hydrogen-oxygen rocket base level is by hydrogen-oxygen rocket, and propellant tank, propellant agent pipeline carry several parts of adapting system to form.Sustainer rocket engine adopts 4 liquid hydrogen-oxygen rockets, but the hydrogen-oxygen rocket of re-lighting comprises: the electronic and helium command control system of motor, control system vertically is coupled.Proportions of ingredients regulating system and tank pressurization system, the inter-stage propellant agent is carried adapting system.
Instrument room is by housing, and mini engine and flat board are formed.The instrument flat board is equipped with guidance remote measurement and posture control system, and control apparatus will be made up of two laser gyroscope platforms, and control system realizes aloft attitude control by handling sustainer rocket engine gimbaled nozzle and attitude control engine.
The load cabin comprises cowling, load support and load, and the cowling shell is the sandwich plate that cfrp covering and aluminum alloy honeycomb sandwich constitute.The piece-rate system of cowling is divided this vertical and horizontal piece-rate system, and vertically piece-rate system is used for the separation of cowling Vertical direction, and the lateral separation system is used for cowling and instrument room horizontal separation.
High Energy Upper Stage is by rocket motor and propellant tank, and servo posture control system is formed, and High Energy Upper Stage adopts a liquid high energy rocket motor, for rocket provides the power of entering the orbit.But re-lighting and high energy rocket motor comprise the electronic of motor and helium command control system, the control system that vertically is coupled, and proportions of ingredients regulating system and tank pressurization system are formed.
The liquid rocket booster rocket is by rocket motor, and propellant tank and piece-rate system are formed.Rocket booster adopts high-power liquid propellant rocket engine, and for the rocket assist section provides most of thrust, liquid propellant rocket engine comprises the electronic and helium command control system of motor, and the tank pressurization system is formed.
Description of drawings Fig. 1 is the load cabin of hydrogen-oxygen rocket commercial launch vehicle and the ssembly drawing of High Energy Upper Stage.
Its structure: 1 load, 2 cowlings, 3 segregating units, 4 segregating units, 5 instrument rooms, 6 inter-stage sections, 7 incendiary agent tank pressure pipings, 8 incendiary agent tanks, 9 oxygenant tank pressure pipings, 10 efficient rocket motor, 11 oxygenant delivery lines, 12 aluminum alloy rears, 13 incendiary agent delivery lines, 14 aluminum alloy stage casings, 15 steel structure stiffening rings, 16 structure stiffening rings, 17 load supports, 18 load supports.
Fig. 2 is the hydrogen-oxygen rocket base level, and its structure is: 1 viewing window, 2 inter-stage sections, 3 separation rockets, 4 cables, 5 liquid oxygen tank, 6 liquid hydrogen tanks, 7 structure stiffening rings, 8 liquid oxygen delivery lines, 9 hydrogen-oxygen rockets, 10 propellant agent pipeline adapting systems, 11 pipelines, 12 external cables, 13 pipelines, 14 liquid hydrogen tank pressure pipings, 15 liquid oxygen tank pressure pipings, 16 steel structure stiffening rings.
Fig. 3 is the left side propellant tank, 1 permanent joint, 2 tank pressure pipings, 3 liquid oxygen tank, 4 separation rockets, 5 liquid hydrogen tanks, 6 permanent joints, 7 pressure piping valves, 8 liquid oxygen pipe valves, 9 liquid hydrogen pipe valves, 10 liquid hydrogen delivery lines, 11 structure stiffening rings, 12 liquid oxygen delivery lines, 13 aluminum alloy stage casings, 15 structure stiffening rings, 16 aluminum alloy leading portions, 17 conical heads.
Fig. 4 is the right side propellant tank, its structure: 1 tank pressure piping, 2 liquid oxygen tank, 3 separation rockets, 4 liquid hydrogen tanks, 5 liquid hydrogen delivery lines, 6 liquid hydrogen pipe valves, 7 pressure piping valves, 8 liquid oxygen pipe valves, 9 liquid hydrogen delivery lines, 10 permanent joints, 11 structure stiffening rings, 12 aluminum alloy stage casings, 13 steel structure stiffening rings, 14 structure stiffening rings, 15 aluminum alloy leading portions, 16 permanent joints, 17 conical heads.
Fig. 5 is anterior liquid propellant rocket engine booster rocket, its structure: 1 aluminum alloy leading portion, 2 permanent joints, 3 incendiary agent tank pressure pipings, 4 incendiary agent tanks, 5 separation rockets, 6 oxygenant tanks, 7 oxygenant tank pressure pipings, 8 permanent joints, 9 liquid propellant rocket engines, 10 oxygenant delivery lines, 11 aluminum alloy rears, 12 steel structure stiffening rings, 13 oxygenant delivery lines, 14 aluminum alloy stage casings, 15 steel structure stiffening rings, 16 structures add structure stiffening ring, 17 steel structure stiffening rings, 18 conical heads
Fig. 6 is a rear fluid rocket motor booster rocket, its structure: 1 aluminum alloy leading portion, 2 incendiary agent tank pressure pipings, 3 incendiary agent tanks, 4 separation rockets, 5 oxygenant tanks, 6 oxidant plenum pipelines, 7 oxygenant delivery lines, 8 liquid propellant rocket engines, 9 aluminum alloy rears, 10 permanent joints, 11 steel structure stiffening rings, 12 incendiary agent delivery lines, 13 aluminum alloy stage casings, 14 steel structure stiffening rings, 15 structure stiffening rings, 16 steel structure stiffening rings, 17 permanent joints, 18 conical heads.
Fig. 7-8 is a hydrogen-oxygen rocket commercial launch vehicle overall pattern.1 load cabin, 2 inter-stage sections, 3 high energy higher levels, 4 inter-stage sections, 5 right side propellant tanks, 6 hydrogen-oxygen rocket base level, 7 liquid rocket booster rockets, 8 left side propellant tanks.
Fig. 9 is scaled down hydrogen-oxygen rocket commercial launch vehicle overall pattern, and overall pattern 1 load cabin, 2 inter-stage sections, 3 High Energy Upper Stages, 4 inter-stage sections, 5 right side propellant tanks, 6 hydrogen-oxygen rocket base level, 7 liquid rocket booster rockets, the 8 left side propellant tanks of Fig. 7-Fig. 8
Embodiment hydrogen-oxygen rocket commercial launch vehicle is according to moderate performance, safe and reliable and principle cheaply, and a lot of structures and system adopt mature technology and simple and reliable system.
The hydrogen-oxygen rocket commercial launch vehicle is a kind of, and is simple in structure, the booster system that reliability is high.Its main structure is by energy level, hydrogen-oxygen rocket base level, two divided mode propellant tanks that laterally are bundled in the base level both sides on load cabin, the high energy, and two liquid propellant rocket engine booster rockets are formed it and are mainly used in the scientific instrument of geostationary orbit and the emission of commercial load.
Claims (2)
1 one kinds of hydrogen-oxygen rocket commercial launch vehicles, it is characterized in that, the main structure of hydrogen-oxygen rocket commercial launch vehicle is by the load cabin, High Energy Upper Stage, the hydrogen-oxygen rocket base level, two separable propelling tanks that laterally are bundled in the base level both sides, two liquid rocket booster rockets are formed.
2 is according to claim 1, it is characterized in that laterally being bundled in separable two propellant tanks of base level both sides.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA03140832XA CN1487186A (en) | 2003-06-05 | 2003-06-05 | Commercial carrier rocket with oxyhydrogen rocket enjine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA03140832XA CN1487186A (en) | 2003-06-05 | 2003-06-05 | Commercial carrier rocket with oxyhydrogen rocket enjine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1487186A true CN1487186A (en) | 2004-04-07 |
Family
ID=34155276
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA03140832XA Pending CN1487186A (en) | 2003-06-05 | 2003-06-05 | Commercial carrier rocket with oxyhydrogen rocket enjine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1487186A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103047911A (en) * | 2012-12-12 | 2013-04-17 | 江汉大学 | Liquid recoil type two-stage booster rocket body |
| CN107063006A (en) * | 2017-04-03 | 2017-08-18 | 湖北航天技术研究院总体设计所 | A kind of reusable carrying space system and round method |
| CN108688829A (en) * | 2018-05-28 | 2018-10-23 | 北京航空航天大学 | Solid-liquid power sub-orbital booster |
| CN113212808A (en) * | 2021-05-08 | 2021-08-06 | 北京格锐德科技有限公司 | Carrier rocket based on extrusion engine |
| CN116733635A (en) * | 2023-08-11 | 2023-09-12 | 东方空间技术(山东)有限公司 | Rocket propellant supply system and rocket |
-
2003
- 2003-06-05 CN CNA03140832XA patent/CN1487186A/en active Pending
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103047911A (en) * | 2012-12-12 | 2013-04-17 | 江汉大学 | Liquid recoil type two-stage booster rocket body |
| CN103047911B (en) * | 2012-12-12 | 2014-10-29 | 江汉大学 | Liquid recoil type two-stage booster rocket body |
| CN107063006A (en) * | 2017-04-03 | 2017-08-18 | 湖北航天技术研究院总体设计所 | A kind of reusable carrying space system and round method |
| CN107063006B (en) * | 2017-04-03 | 2018-11-27 | 湖北航天技术研究院总体设计所 | A kind of reusable carrying space system and round-trip method |
| CN108688829A (en) * | 2018-05-28 | 2018-10-23 | 北京航空航天大学 | Solid-liquid power sub-orbital booster |
| CN113212808A (en) * | 2021-05-08 | 2021-08-06 | 北京格锐德科技有限公司 | Carrier rocket based on extrusion engine |
| CN116733635A (en) * | 2023-08-11 | 2023-09-12 | 东方空间技术(山东)有限公司 | Rocket propellant supply system and rocket |
| CN116733635B (en) * | 2023-08-11 | 2024-03-19 | 东方空间(江苏)航天动力有限公司 | Rocket propellant supply system and rocket |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |