CN109339979A - Attitude control engine module - Google Patents
Attitude control engine module Download PDFInfo
- Publication number
- CN109339979A CN109339979A CN201810969059.XA CN201810969059A CN109339979A CN 109339979 A CN109339979 A CN 109339979A CN 201810969059 A CN201810969059 A CN 201810969059A CN 109339979 A CN109339979 A CN 109339979A
- Authority
- CN
- China
- Prior art keywords
- fluid
- runner
- attitude control
- engine
- control engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000012530 fluid Substances 0.000 claims abstract description 37
- 239000000446 fuel Substances 0.000 claims abstract description 26
- 239000007800 oxidant agent Substances 0.000 claims abstract description 26
- 230000001590 oxidative effect Effects 0.000 claims abstract description 26
- 238000007789 sealing Methods 0.000 claims abstract description 7
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 210000004262 dental pulp cavity Anatomy 0.000 abstract description 3
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 208000002925 dental caries Diseases 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- ZNKMCMOJCDFGFT-UHFFFAOYSA-N gold titanium Chemical compound [Ti].[Au] ZNKMCMOJCDFGFT-UHFFFAOYSA-N 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 229910001258 titanium gold Inorganic materials 0.000 description 1
Classifications
-
- 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
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/58—Propellant feed valves
-
- 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
-
- 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
- F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
- F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
- F02K9/766—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants with liquid propellant
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The present invention provides a kind of attitude control engine modules, include module carrier and engine；The module carrier is internally provided with the first cavity, and first cavity forms fluid and supplies runner；The second cavity is provided on the engine, second cavity forms fluid and receives runner；Module carrier is fastenedly connected with transmitter, and the fluid supply runner and fluid made, which receives, to be interconnected between runner and fluid channel is collectively formed；Fluid supply runner and fluid receive runner junction and are provided with sealing structure.In practical applications, module carrier can form 4 oxidant flow channels and 4 fuel flow channels by internal punches to the present invention, and mature technology, mechanical property are good, reduce 8 root canal roads and 16 weld seams than traditional design, system complexity reduces.
Description
Technical field
The present invention relates to rail control dynamical systems, and in particular, to a kind of attitude control engine module, especially a kind of attitude control
Four engine blocks.
Background technique
According to traditional design concept, propellant is transmitted through pipeline realization, and every two-components Adhesive configures 2 and enters
Mouth pipe, four machine units need to configure 8 root canal roads, are related to 16 weld seams.Pipe-line system is complicated, and weld seam is more, and mechanical property is poor,
Reliability is lower.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of attitude control engine modules.
The attitude control engine module provided according to the present invention includes module carrier and engine；Inside the module carrier
It is provided with the first cavity, first cavity forms fluid and supplies runner；It is provided with the second cavity on the engine, described
Two cavitys form fluid and receive runner；
Module carrier is fastenedly connected with transmitter, and the fluid supply runner and fluid made receives to be interconnected simultaneously between runner
Fluid channel is collectively formed；Fluid supply runner and fluid receive runner junction and are provided with sealing structure.
Preferably, the module carrier includes oxidant inlet and fuel inlet, includes oxidation in multiple fluid channels
Agent channel and fuel channel.
Preferably, the engine includes solenoid valve and thrust chamber；The solenoid valve insertion is mounted on fluid and receives runner
In；
The fluid channel is connected to thrust chamber.
Preferably, the module carrier includes four machine supports, and four machine supports are connected with four engines of setting；
It is provided with four oxidant channels and four fuel channels；Four oxidant channels are connected to the same oxidant
Entrance, four fuel channels are connected to the same fuel channel.
Preferably, pass through the two kinds of fastener connections of following any or all between module carrier and engine:
-- cruciform slot screw；
-- hexagon-headed bolt.
It preferably, include the first high chamber pressure engine and the second high chamber pressure engine in multiple engines；First high room
The normal thrust of hydraulic motor is greater than the normal thrust of the second high chamber pressure engine.
Preferably, the second high chamber pressure engine arranged opposite to each other comprising two.
Preferably, sealing structure includes O-ring seal.
Preferably, module carrier and/or engine are made of titanium alloy.
Preferably, oxidant inlet length is greater than fuel inlet length.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, module carrier forms 4 oxidant flow channels and 4 fuel flow channels, mature technology, power by internal punches
It is good to learn performance, reduces 8 root canal roads and 16 weld seams than traditional design, system complexity reduces；
2, reliability is obviously improved, while alleviating module weight, reduces envelope size；
3, attitude control engine module only has 2 mechanical interfaces, convenient for disassembly and assembly, can one integral piece if four machine modules break down
Replacement, if it is engine failure, can also be individually replaced engine and O-ring seal and fastener, maintainability is good.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is attitude control engine module main view provided by the invention；
Fig. 2 is attitude control engine module top view provided by the invention；
Fig. 3 is attitude control engine module left view provided by the invention；
Fig. 4 is attitude control engine module right view provided by the invention；
Fig. 5 is electromagnetism valve position fragmentary detail view.
It is shown in figure:
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, various modifications and improvements can be made.These belong to the present invention
Protection scope.
In the description of the present invention, it is to be understood that, term " on ", "lower", "front", "rear", "left", "right", " perpendicular
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, is merely for convenience of description of the present invention and simplification of the description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.
As shown in Figures 1 to 4, attitude control engine module provided by the invention includes module carrier 1 and engine；It is described
Module carrier 1 is internally provided with the first cavity, and first cavity forms fluid and supplies runner；Is provided on the engine
Two cavitys, second cavity form fluid and receive runner；Module carrier 1 is fastenedly connected with transmitter, the fluid supply stream made
Road and fluid, which receive, to be interconnected between runner and fluid channel is collectively formed；Fluid is supplied runner and is connect with fluid reception runner
Place is provided with sealing structure.The module carrier 1 includes oxidant inlet 8 and fuel inlet 9, includes in multiple fluid channels
Oxidant channel and fuel channel.Preferably, 8 length of oxidant inlet is greater than 9 length of fuel inlet, in order to supplement combustion simultaneously
Material and oxidant.As shown in figure 5, the engine includes solenoid valve 4 and thrust chamber；The insertion of solenoid valve 4 is mounted on fluid
It receives in runner；The fluid channel is connected to thrust chamber.Sealing structure includes O-ring seal 5.
In embodiment, the module carrier 1 includes four machine supports, and four machine supports are connected with four engines of setting；If
It is equipped with four oxidant channels and four fuel channels；Four oxidant channels are connected to the same oxidant inlet 8, and four
Fuel channel is connected to the same fuel channel.Pass through two kinds of following any or all between module carrier 1 and engine
Fastener connection: cruciform slot screw 6, hexagon-headed bolt 7 facilitate rapid location and installation by cruciform slot screw 6, in conjunction with hexagonal
Hook bolt 7 can effectively adjust axle power precision.It include that the first high chamber pressure engine 2 and the second high chamber pressure are sent out in multiple engines
Motivation 3；The normal thrust of first high chamber pressure engine 2 is greater than the normal thrust of the second high chamber pressure engine 3, includes in embodiment
Two the second high chamber pressure engines 3 arranged opposite to each other, due to different, described two opposite cloth with four machine supports installation interface position
The high chamber pressure engine 3 of second set respectively corresponds as A condition, B state.Preferably, module carrier 1 and/or engine are closed by titanium
Gold is made, and while keeping sufficient intensity, mitigates the weight of entire attitude control engine module.
Preferred embodiment:
Attitude control engine module is four machine module of attitude control, and four machine module of attitude control is mainly by 1 four machine support, 2 160N high
Chamber pressure engine, 1 20N high chamber pressure engine (A condition), 1 20N high chamber pressure engine (B state), O-ring seal 5 and
Fastener composition, envelope range are 191mm × 88mm × 76mm, and gross weight is no more than 800g.Four machine supports pass through internal punches shape
At 4 oxidant flow channels and 4 fuel flow channels.
Four machine supports are titanium alloy bracket, form 4 oxidant flow channels and 4 fuel flow channels, setting 1 by internal punches
A oxidant inlet 8 (" o ") and 1 fuel inlet 9 (" f ") are that 4 attitude control engines supply oxidant and fuel.
160N and 20N high chamber pressure constant engine chamber pressure 4MPa, normal thrust are respectively 160N and 20N, are double elements, light
Small-sized, fast-response engine is made of 2 plug-in type solenoid valves and 1 thrust chamber.2 solenoid valves control oxidant road respectively
With the switch on fuel road.After 2 solenoid valves are opened simultaneously, oxidant and fuel enter thrust chamber mixing combustion according to a certain percentage
It burns, the high-temperature fuel gas of generation sprays after jet pipe accelerates, and forms thrust.Due to different with four machine supports installation interface position,
20N high chamber pressure engine is divided into A and B two states.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. a kind of attitude control engine module, which is characterized in that include module carrier (1) and engine；In the module carrier (1)
Portion is provided with the first cavity, and first cavity forms fluid and supplies runner；The second cavity is provided on the engine, it is described
Second cavity forms fluid and receives runner；
Module carrier (1) is fastenedly connected with transmitter, and the fluid supply runner and fluid made receives to be interconnected simultaneously between runner
Fluid channel is collectively formed；Fluid supply runner and fluid receive runner junction and are provided with sealing structure.
2. attitude control engine module according to claim 1, which is characterized in that the module carrier (1) includes oxidant
Entrance (8) and fuel inlet (9) include oxidant channel and fuel channel in multiple fluid channels.
3. attitude control engine module according to claim 2, which is characterized in that the engine include solenoid valve (4) with
Thrust chamber；Solenoid valve (4) insertion is mounted on fluid and receives in runner；
The fluid channel is connected to thrust chamber.
4. attitude control engine module according to claim 3, which is characterized in that the module carrier (1) includes four machine branch
Frame, four machine supports are connected with four engines of setting；
It is provided with four oxidant channels and four fuel channels；Four oxidant channels are connected to the same oxidant inlet
(8), four fuel channels are connected to the same fuel channel.
5. attitude control engine module according to claim 1, which is characterized in that lead between module carrier (1) and engine
Cross the two kinds of fastener connections of following any or all:
-- cruciform slot screw (6)；
-- hexagon-headed bolt (7).
6. attitude control engine module according to claim 1, which is characterized in that include the first high room in multiple engines
Hydraulic motor (2) and the second high chamber pressure engine (3)；The normal thrust of first high chamber pressure engine (2) is greater than the second high chamber pressure
The normal thrust of engine (3).
7. attitude control engine module according to claim 6, which is characterized in that the second high room arranged opposite to each other comprising two
Hydraulic motor (3).
8. attitude control engine module according to claim 1, which is characterized in that sealing structure includes O-ring seal (5).
9. attitude control engine module according to claim 1, which is characterized in that module carrier (1) and/or engine are by titanium
Alloy is made.
10. attitude control engine module according to claim 2, which is characterized in that oxidant inlet (8) length is greater than fuel
Entrance (9) length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810969059.XA CN109339979B (en) | 2018-08-23 | 2018-08-23 | Attitude control engine module |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810969059.XA CN109339979B (en) | 2018-08-23 | 2018-08-23 | Attitude control engine module |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109339979A true CN109339979A (en) | 2019-02-15 |
| CN109339979B CN109339979B (en) | 2020-12-01 |
Family
ID=65296887
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810969059.XA Active CN109339979B (en) | 2018-08-23 | 2018-08-23 | Attitude control engine module |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109339979B (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111237088A (en) * | 2020-03-30 | 2020-06-05 | 北京宇航推进科技有限公司 | Double-component five-machine combined power system |
| CN112228250A (en) * | 2020-09-10 | 2021-01-15 | 沈阳航天新光集团有限公司 | Liquid attitude control engine integrated block |
| CN113090414A (en) * | 2020-01-08 | 2021-07-09 | 星河动力(北京)空间科技有限公司 | Attitude control engine |
| CN113431707A (en) * | 2021-07-27 | 2021-09-24 | 北京宇航推进科技有限公司 | Single-component attitude control engine module and combination thereof |
| CN114576041A (en) * | 2022-02-10 | 2022-06-03 | 宁波天擎航天科技有限公司 | A highly integrated valve and control system |
| CN115303510A (en) * | 2022-07-19 | 2022-11-08 | 沈阳航天新光集团有限公司 | Attitude control power combined module |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106134367B (en) * | 2010-02-09 | 2013-10-30 | 上海空间推进研究所 | Highly integrated spacecraft engine block |
| CN104405533A (en) * | 2014-10-28 | 2015-03-11 | 上海空间推进研究所 | Sealing structure of small light type liquid rocket attitude control engine |
| CN107842444A (en) * | 2016-09-21 | 2018-03-27 | 湖北航天技术研究院总体设计所 | A kind of liquid attitude control engine rocking equipment |
| CN107940106A (en) * | 2017-11-10 | 2018-04-20 | 贵州航天林泉电机有限公司 | A kind of attitude control engine pipeline support component |
-
2018
- 2018-08-23 CN CN201810969059.XA patent/CN109339979B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106134367B (en) * | 2010-02-09 | 2013-10-30 | 上海空间推进研究所 | Highly integrated spacecraft engine block |
| CN104405533A (en) * | 2014-10-28 | 2015-03-11 | 上海空间推进研究所 | Sealing structure of small light type liquid rocket attitude control engine |
| CN107842444A (en) * | 2016-09-21 | 2018-03-27 | 湖北航天技术研究院总体设计所 | A kind of liquid attitude control engine rocking equipment |
| CN107940106A (en) * | 2017-11-10 | 2018-04-20 | 贵州航天林泉电机有限公司 | A kind of attitude control engine pipeline support component |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113090414A (en) * | 2020-01-08 | 2021-07-09 | 星河动力(北京)空间科技有限公司 | Attitude control engine |
| CN111237088A (en) * | 2020-03-30 | 2020-06-05 | 北京宇航推进科技有限公司 | Double-component five-machine combined power system |
| CN112228250A (en) * | 2020-09-10 | 2021-01-15 | 沈阳航天新光集团有限公司 | Liquid attitude control engine integrated block |
| CN112228250B (en) * | 2020-09-10 | 2023-06-09 | 沈阳航天新光集团有限公司 | Liquid attitude control engine integrated block |
| CN113431707A (en) * | 2021-07-27 | 2021-09-24 | 北京宇航推进科技有限公司 | Single-component attitude control engine module and combination thereof |
| CN114576041A (en) * | 2022-02-10 | 2022-06-03 | 宁波天擎航天科技有限公司 | A highly integrated valve and control system |
| CN114576041B (en) * | 2022-02-10 | 2024-09-13 | 宁波天擎航天科技有限公司 | High-integration valve and control system |
| CN115303510A (en) * | 2022-07-19 | 2022-11-08 | 沈阳航天新光集团有限公司 | Attitude control power combined module |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109339979B (en) | 2020-12-01 |
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