CN105156231A - Gas self-pressurization hybrid rocket engine - Google Patents
Gas self-pressurization hybrid rocket engine Download PDFInfo
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- CN105156231A CN105156231A CN201510574948.2A CN201510574948A CN105156231A CN 105156231 A CN105156231 A CN 105156231A CN 201510574948 A CN201510574948 A CN 201510574948A CN 105156231 A CN105156231 A CN 105156231A
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Abstract
The invention provides a gas self-pressurization hybrid rocket engine which comprises an oxidizing agent storage box, an oxidizing agent control valve, a check valve, an oxidizing agent injector, a spray pipe, a flow regulating valve, a poor-oxygen gas generator, a filter and a pressure reducer. A sealing piston is arranged in the oxidizing agent storage box. The sealing piston divides an inner cavity of the oxidizing agent storage box into two sealed cavities, an oxidizing agent is placed in one sealed cavity, one end of the poor-oxygen gas generator is a sealed end, the other end of the poor-oxygen gas generator is provided with the spray pipe, a grain is poured at the position of the sealed end, and the flow regulating valve is arranged in a cavity of the poor-oxygen gas generator in which a grain is not poured. The flow regulating valve divides the cavity in which a grain is not poured into two cavities, and the cavity close to the spray pipe is a secondary combustion chamber. According to the gas self-pressurization hybrid rocket engine, self-pressurization can be achieved, and the complexity of an oxidizing agent supply system can be simplified greatly.
Description
Technical field
The invention belongs to engine design field, particularly relate to a kind of combustion gas auto-pressurizing hybrid rocket engine.
Background technique
At present, hybrid rocket engine generally adopts liquid oxidizer and solid-fuelled compound mode, is made up of parts such as liquid oxidizer tank, liquid line transporting system, gas cylinder or turbine pump, oxygenant ejector filler, solid fuel ignition room and jet pipes.The working procedure of hybrid rocket engine is: oxygenant gas cylinder extruding or turbine pump driving effect under, precombustion chamber or the gasification room of main fuel upstream is entered by ejector filler atomization, the oxidant gas formed carries out diffusive combustion with fuel thermal decomposition gas in fuel channel, finally generates high-temperature fuel gas and discharges generation thrust by jet pipe.
Traditional hybrid rocket engine adopts the hydrocarbons such as HTPB, PE as fuel, and add and add metallic dust on a small quantity or not, fuel density is low; In the process of diffusive combustion, the flow parameter of combustion face diverse location is not identical with local mixture ratio, can cause the difference of fuel regression rate, cause combustion efficiency lower, be difficult to give full play to than punching performance; In thrust adjustment process, because oxygen combustion is than changing greatly, engine performance change also greatly; In addition, by the restriction of solid fuel fuel regression rate, traditional hybrid rocket engine, in order to the thrust of acquiring demand, adopts the charge constitution form of porous, multistage usually, and charge constitution is complicated, and volumetric loading fraction is low and easily produce more residual medicine.。
Summary of the invention
For solving the problem, the invention provides a kind of combustion gas auto-pressurizing hybrid rocket engine, the fuel-rich combustion gas utilizing the primary combustion of oxygen-depleted combustion gases generator to produce and liquid oxidizer carry out secondary blending in a combustion chamber and burn and release energy; Meanwhile, utilize this characteristic that gas generator pressure ratio chamber pressure is high, a part of combustion gas produced by gas generator introduces oxygenant tank as the extruding gas of oxygenant, realizes from supercharging, significantly can simplify the complexity of oxygenant supply system.
The invention provides a kind of combustion gas auto-pressurizing hybrid rocket engine, it comprises: oxygenant tank, oxidizer control valve, one-way valve, oxygenant ejector filler, jet pipe, flow control valve, oxygen-depleted combustion gases generator, filter, decompressor;
Wherein: in oxygenant tank, establish packed-piston, the inner chamber of oxygenant tank is separated into two sealed cavities by sealing piston, and one of them sealed cavity is built with oxygenant; Oxygen-depleted combustion gases generator one end is sealed end, the other end is provided with jet pipe, and built powder column at sealed end place, flow control valve is provided with in the cavity that powder column do not built by oxygen-depleted combustion gases generator, the cavity that this is not built powder column by flow control valve is separated into two cavitys, and is secondary-burning chamber near the cavity of jet pipe;
Annexation is: the sealed cavity that oxygenant is housed of oxygenant tank is connected with oxygenant ejector filler by the first pipeline, this first pipeline is provided with oxidizer control valve and one-way valve successively from the sealed cavity that oxygenant is housed, and the secondary combustion that pipeline oxidization agent ejector filler is installed on oxygen-depleted combustion gases generator is indoor; And be connected with oxygenant tank by second pipe near the cavity of oxygen-depleted combustion gases generator sealed end, and this second pipe is provided with filter and decompressor successively from the cavity near oxygen-depleted combustion gases generator sealed end.
Further, powder column is being provided with igniter pad on flow control valve one end.
Beneficial effect:
The combustion gas of the present invention's design is from supercharging hybrid rocket engine, utilize the characteristic that oxygen-depleted combustion gases generator pressure ratio chamber pressure is high, because the Some gases produced by gas generator introduces oxygenant tank as extruding gas, realize combustion gas from supercharging, realize combustion gas from supercharging, do not need gas cylinder or turbine pump, significantly simplify architecture quality and the complexity of oxygenant supply system, reduce the passive quality of power system.
Accompanying drawing explanation
Fig. 1 is combustion gas auto-pressurizing hybrid rocket engine schematic diagram of the present invention.
Its reference character is: 1-oxygenant tank; 2-oxidizer control valve; 3-one-way valve; 4-oxygenant ejector filler; 5-jet pipe; 6-flow control valve; 7-oxygen-depleted combustion gases generator; 8-filter; 9-decompressor.
Embodiment
Testing apparatus structure of the present invention as shown in Figure 1, comprising: oxygenant tank 1, oxidizer control valve 2, one-way valve 3, oxygenant ejector filler 4, jet pipe 5, flow control valve 6, oxygen-depleted combustion gases generator 7, filter 8, decompressor 9.
Establish packed-piston in oxygenant tank 1, oxygenant tank 1 is divided into the first tank and the second tank by sealing piston; Second tank is built with oxygenant; Powder column has been built in the inner one end of oxygen-depleted combustion gases generator 7, and the other end leaves cavity, is provided with flow control valve 6 in cavity, and cavity is divided into the first cavity and secondary-burning chamber by flow control valve 6;
Second tank of oxygenant tank 1 is connected with oxygenant ejector filler 4 by the first pipeline, and this first pipeline is provided with oxidizer control valve 2, one-way valve 3 successively from the second tank; The secondary combustion that pipeline oxidization agent ejector filler 4 is installed on oxygen-depleted combustion gases generator 7 is indoor; First cavity of oxygen-depleted combustion gases generator 7 is connected with oxygenant tank 1 by second pipe, and this second pipe is provided with filter 8 and decompressor 9 successively from the first cavity; The secondary-burning chamber of oxygen-depleted combustion gases generator 7 is connected with jet pipe 5.
Wherein, powder column is being provided with igniter pad on flow control valve 6 one end.
The combustion gas that the present invention proposes is as follows from the working procedure of supercharging hybrid rocket engine: be first light igniter pad, oxygen-depleted combustion gases generator 7 is lighted a fire and is produced the once fuel-rich combustion gas of high temperature, high pressure, combustion gas sub-fraction once fuel-rich combustion gas enters the first tank of oxygenant tank 1 after reducing pressure through filter 8 impurity screening, decompressor 9, once fuel-rich combustion gas crush seal piston, the oxygenant that packed-piston promotes in the second tank enters oxidizer control valve 2 and one-way valve 3 from the second tank, after oxygenant ejector filler 4 is atomized, enter secondary-burning chamber; In addition, major part once fuel-rich combustion gas enters in secondary-burning chamber through flow control valve 6, carries out secondary combustion with the oxygenant after oxygenant ejector filler 4 is atomized, and the high-temperature fuel gas of generation is discharged at a high speed by jet pipe 5 and produced thrust.
Combustion gas, in supercharging hybrid rocket engine working procedure, according to trajectory demand, by the pressure regulating the flow control valve 6 in oxygen-depleted combustion gases generator 7 to change oxygen-depleted combustion gases generator 7, can realize the adjustment to a gas flow and oxidizer flow rate simultaneously.
Combustion gas selects from supercharging hybrid rocket engine the fuel rich propellant that metallic dust content is higher, has higher energy and density relative to hydrocarbon; Adopt the cigarette burning charge structure of full filling, filling mark is high, and rule is retired simply in combustion face, and combustion speed is easy to regulate; By designing the pressure index of fuel rich propellant, oxygen combustion in thrust adjustment process can be kept to occur significantly to change than not, and engine operation is near design point, and performance is higher.
Certainly; the present invention also can have other various embodiments; when not deviating from the present invention's spirit and essence thereof; those of ordinary skill in the art are when making various corresponding change and distortion according to the present invention, but these change accordingly and are out of shape the protection domain that all should belong to the claim appended by the present invention.
Claims (2)
1. a combustion gas auto-pressurizing hybrid rocket engine, it is characterized in that, comprising: oxygenant tank (1), oxidizer control valve (2), one-way valve (3), oxygenant ejector filler (4), jet pipe (5), flow control valve (6), oxygen-depleted combustion gases generator (7), filter (8), decompressor (9);
Wherein: oxygenant tank establishes packed-piston in (1), the inner chamber of oxygenant tank (1) is separated into two sealed cavities by sealing piston, and one of them sealed cavity is built with oxygenant; Oxygen-depleted combustion gases generator (7) one end is sealed end, the other end is provided with jet pipe (5), and built powder column at sealed end place, flow control valve (6) is provided with in the cavity that powder column do not built by oxygen-depleted combustion gases generator (7), the cavity that this is not built powder column by flow control valve (6) is separated into two cavitys, and is secondary-burning chamber near the cavity of jet pipe (5);
Annexation is: the sealed cavity that oxygenant is housed of oxygenant tank (1) is connected with oxygenant ejector filler (4) by the first pipeline, this first pipeline is provided with oxidizer control valve (2) and one-way valve (3) successively from the sealed cavity that oxygenant is housed, and the secondary combustion that pipeline oxidization agent ejector filler (4) is installed on oxygen-depleted combustion gases generator (7) is indoor; And be connected with oxygenant tank (1) by second pipe near the cavity of oxygen-depleted combustion gases generator (7) sealed end, and this second pipe is provided with filter (8) and decompressor (9) successively from the cavity near oxygen-depleted combustion gases generator (7) sealed end.
2. combustion gas auto-pressurizing hybrid rocket engine as claimed in claim 1, is characterized in that, powder column is being provided with igniter pad on flow control valve (6) one end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510574948.2A CN105156231A (en) | 2015-09-10 | 2015-09-10 | Gas self-pressurization hybrid rocket engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510574948.2A CN105156231A (en) | 2015-09-10 | 2015-09-10 | Gas self-pressurization hybrid rocket engine |
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| CN105156231A true CN105156231A (en) | 2015-12-16 |
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| CN201510574948.2A Pending CN105156231A (en) | 2015-09-10 | 2015-09-10 | Gas self-pressurization hybrid rocket engine |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106194500A (en) * | 2016-08-26 | 2016-12-07 | 北京宇航系统工程研究所 | A kind of tridyne pressure charging system being applied to liquid rocket |
| CN106917699A (en) * | 2017-01-19 | 2017-07-04 | 北京航空航天大学 | Hydrogen peroxide solid-liquid rocket is from pressurizing transmission system |
| CN107829842A (en) * | 2017-09-28 | 2018-03-23 | 北京航空航天大学 | Nitrous oxide temperature control pressure charging system |
| CN108380416A (en) * | 2018-05-15 | 2018-08-10 | 中国空间技术研究院 | It is a kind of can multi-injection detachable jet device and jetting method |
| CN109695514A (en) * | 2018-12-06 | 2019-04-30 | 北京宇航系统工程研究所 | A kind of interior quick pressurization system that burns of tank |
| CN111521072A (en) * | 2020-04-29 | 2020-08-11 | 西北工业大学 | Fire extinguishing rocket projectile based on gas-solid hybrid rocket engine |
| GB2581150A (en) * | 2019-02-05 | 2020-08-12 | Desmond Lewis Stephen | Increased safety general purpose hybrid rocket engine cycle |
| CN111622866A (en) * | 2020-05-15 | 2020-09-04 | 大连理工大学 | Constant force spring type storage tank for liquid propellant |
| CN114109654A (en) * | 2021-11-25 | 2022-03-01 | 宁波天擎航天科技有限公司 | Solid-liquid mixed engine and aircraft |
| CN114514371A (en) * | 2019-10-08 | 2022-05-17 | 法国国家太空研究中心 | Propulsion assembly for rocket |
| CN114941967A (en) * | 2022-06-01 | 2022-08-26 | 西北工业大学 | Controllable target aircraft based on solid-liquid hybrid rocket engine |
-
2015
- 2015-09-10 CN CN201510574948.2A patent/CN105156231A/en active Pending
Non-Patent Citations (1)
| Title |
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| 王永寿: "燃气混合火箭发动机的燃烧特性", 《飞航导弹》 * |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106194500A (en) * | 2016-08-26 | 2016-12-07 | 北京宇航系统工程研究所 | A kind of tridyne pressure charging system being applied to liquid rocket |
| CN106194500B (en) * | 2016-08-26 | 2018-01-05 | 北京宇航系统工程研究所 | A kind of tridyne pressure charging system applied to liquid rocket |
| CN106917699A (en) * | 2017-01-19 | 2017-07-04 | 北京航空航天大学 | Hydrogen peroxide solid-liquid rocket is from pressurizing transmission system |
| CN107829842A (en) * | 2017-09-28 | 2018-03-23 | 北京航空航天大学 | Nitrous oxide temperature control pressure charging system |
| CN108380416A (en) * | 2018-05-15 | 2018-08-10 | 中国空间技术研究院 | It is a kind of can multi-injection detachable jet device and jetting method |
| CN109695514A (en) * | 2018-12-06 | 2019-04-30 | 北京宇航系统工程研究所 | A kind of interior quick pressurization system that burns of tank |
| CN109695514B (en) * | 2018-12-06 | 2020-08-07 | 北京宇航系统工程研究所 | Quick supercharging system of storage tank internal combustion |
| GB2581150A (en) * | 2019-02-05 | 2020-08-12 | Desmond Lewis Stephen | Increased safety general purpose hybrid rocket engine cycle |
| GB2581150B (en) * | 2019-02-05 | 2021-05-12 | Desmond Lewis Stephen | Increased safety general purpose hybrid rocket engine |
| CN114514371A (en) * | 2019-10-08 | 2022-05-17 | 法国国家太空研究中心 | Propulsion assembly for rocket |
| CN111521072A (en) * | 2020-04-29 | 2020-08-11 | 西北工业大学 | Fire extinguishing rocket projectile based on gas-solid hybrid rocket engine |
| CN111521072B (en) * | 2020-04-29 | 2022-08-16 | 西北工业大学 | Fire extinguishing rocket projectile based on gas-solid hybrid rocket engine |
| CN111622866A (en) * | 2020-05-15 | 2020-09-04 | 大连理工大学 | Constant force spring type storage tank for liquid propellant |
| CN111622866B (en) * | 2020-05-15 | 2021-09-24 | 大连理工大学 | Constant force spring type storage tank for liquid propellant |
| CN114109654A (en) * | 2021-11-25 | 2022-03-01 | 宁波天擎航天科技有限公司 | Solid-liquid mixed engine and aircraft |
| CN114941967A (en) * | 2022-06-01 | 2022-08-26 | 西北工业大学 | Controllable target aircraft based on solid-liquid hybrid rocket engine |
| CN114941967B (en) * | 2022-06-01 | 2023-07-25 | 西北工业大学 | Controllable target aircraft based on solid-liquid hybrid rocket engine |
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Application publication date: 20151216 |