CN107165739B - Solid-liquid rocket circular seam type plug nozzle - Google Patents
Solid-liquid rocket circular seam type plug nozzle Download PDFInfo
- Publication number
- CN107165739B CN107165739B CN201710616678.6A CN201710616678A CN107165739B CN 107165739 B CN107165739 B CN 107165739B CN 201710616678 A CN201710616678 A CN 201710616678A CN 107165739 B CN107165739 B CN 107165739B
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- China
- Prior art keywords
- jet pipe
- solid
- ring
- laryngeal mask
- liquid rocket
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The invention discloses a kind of solid-liquid rocket circular seam type plug nozzles, including ring laryngeal mask, jet pipe pressing plate, jet pipe shell, plug cone and heat-insulating shield；The ring laryngeal mask is mounted on the outlet end of the jet pipe shell by the jet pipe pressing plate；Boss is equipped with by floor in the jet pipe shell；The plug cone is suspended in the throat of the ring laryngeal mask and connect with the boss；The outer peripheral surface of the plug cone and the throat of the ring laryngeal mask cooperatively form converging portion and expansion segment；The heat-insulating shield is mounted on the arrival end of the jet pipe shell, and the heat-insulating shield and the floor are equipped with the through slot to connect.High-temperature high-pressure fuel gas in solid-liquid rocket engine combustor enters via the arrival end of jet pipe shell, and combustion gas is ramped up in converging portion, flows into expansion segment after the throat of ring laryngeal mask reaches velocity of sound and continues to accelerate to supersonic speed.Solid-liquid rocket suitable for different operating height.
Description
Technical field
The present invention relates to rocket engine field, in particular to a kind of solid-liquid rocket circular seam type plug nozzle.
Background technique
Component part of the jet pipe as rocket engine is a key factor for influencing engine performance.
The jet pipe of rocket engine is generally La Faer jet pipe, the high-temperature high-pressure fuel gas for the Indoor Combustion generation that will burn
Conversion of heat into kinetic energy.Acceleration is constantly expanded when high-temperature high-pressure fuel gas flows through jet pipe, is finally arranged with high speed from nozzle exit plane
Out, thrust is generated.The jet pipe of existing solid or liquid-propellant rocket engine is mostly bell nozzle.
Traditional bell nozzle, since its divergence ratio does not adapt to the variation of environmental pressure, in the distribution process of rocket,
It will appear expansion or deficient expansion issues, and reduced the efficiency of jet pipe.Compared with traditional bell nozzle, plug nozzle has certainly
Dynamic height compensation characteristic can keep higher nozzle efficiency in biggish working height range, high suitable for bigger work
Spend range.By reasonably designing and optimizing, compared with traditional bell nozzle, the more compact structure of plug nozzle, size is more
Small, weight is lighter.The structure and form of existing plug nozzle do not account for all just for solid or liquid-propellant rocket engine
Applicable cases on solid-liquid rocket, are not suitable for solid-liquid rocket.
Summary of the invention
The purpose of the present invention is to provide a kind of solid-liquid rocket circular seam type plug nozzles, to solve in the prior art
The structure and form of existing existing plug nozzle do not account for all just for solid or liquid-propellant rocket engine in solid-liquid
Applicable cases on rocket engine, the technical issues of not being suitable for solid-liquid rocket.
Solid-liquid rocket circular seam type plug nozzle provided by the invention, including ring laryngeal mask, jet pipe pressing plate, jet pipe shell
Body, plug cone and heat-insulating shield；
The ring laryngeal mask is mounted on the outlet end of the jet pipe shell by the jet pipe pressing plate；
Boss is equipped with by floor in the jet pipe shell；
The plug cone is suspended in the throat of the ring laryngeal mask and connect with the boss；
The outer peripheral surface of the plug cone and the throat of the ring laryngeal mask cooperatively form converging portion and expansion segment；
The heat-insulating shield is mounted on the arrival end of the jet pipe shell, and the heat-insulating shield is equipped with the floor and connects
Through slot.
Further, the throat of the ring laryngeal mask includes sequentially connected hemispherical-shaped aperture and equal diameter through-hole, the plug cone
Including sequentially connected arc section and conical section, the end face of the arc section is connect with the boss, the periphery of the arc section
Face matches to form converging portion with the hemispherical-shaped aperture, and the conical section stretches out the equal diameter through-hole of the ring laryngeal mask, the cone
The outer peripheral surface of shape section matches to form expansion segment with the equal diameter through-hole.
Further, the end face of the arc section of the plug cone is equipped with groove, and the end face of the arc section of the plug cone passes through
The groove is set on the boss and is connected as one by bolt and the boss.
Further, it is equipped with bolt hole in the boss, threaded hole is equipped in the groove, the bolt passes through described
Bolt hole is connect with the threaded hole.
Further, the heat-insulating shield is to be detachably connected with the jet pipe shell.
Further, the jet pipe pressing plate is to be detachably connected with the jet pipe shell.
Further, the plug cone of stating is made of high temperature ablation resistant material.
Further, the ring laryngeal mask is made of high temperature ablation resistant material.
Further, sealing ring is installed between the ring laryngeal mask and the outlet end of the jet pipe shell.
Further, the floor is structure as a whole with the boss.
Solid-liquid rocket circular seam type plug nozzle provided by the invention, has the advantages that
High-temperature high-pressure fuel gas in solid-liquid rocket engine combustor enters via the arrival end of jet pipe shell, and combustion gas is being received
It holds back section to ramp up, flow into expansion segment after the throat of ring laryngeal mask reaches velocity of sound and continues to accelerate to supersonic speed.
1, the solid-liquid rocket suitable for different operating height.
2, compact-sized, size is smaller, the ground experiment suitable for solid-liquid rocket.
3, compared with traditional bell nozzle, there is automatic height compensation characteristic, it can be in very big working height range
Higher nozzle efficiency is kept, the solid-liquid rocket wider especially suitable for working height range.
4, nozzle entry plane can play the role of flow-disturbing, be conducive to the blending of combustion gas, improve solid-liquid rocket
Efficiency of combustion improves engine performance.
5, the practical divergence ratio of jet pipe can change with the variation of engine chamber pressure, suitable for the solid-liquid with change propulsive characteristic
Rocket engine.
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, for those of ordinary skill in the art, before not making the creative labor
It puts, is also possible to obtain other drawings based on these drawings.
Fig. 1 is the structural schematic diagram for the solid-liquid rocket circular seam type plug nozzle that the embodiment of the present invention one provides；
Fig. 2 is the A-A cross-sectional view of Fig. 1；
Fig. 3 is the structural schematic diagram for the jet pipe shell that the present embodiment one provides；
Fig. 4 is the B-B cross-sectional view of Fig. 3；
Fig. 5 is the structural schematic diagram for the ring laryngeal mask that the present embodiment one provides；
Fig. 6 is the structural schematic diagram for the plug cone that the present embodiment one provides；
Fig. 7 is the structural schematic diagram for the jet pipe pressing plate that the present embodiment one provides；
Fig. 8 is the C-C cross-sectional view of Fig. 7；
Fig. 9 is the structural schematic diagram for the heat-insulating shield that the present embodiment one provides；
Figure 10 is the D-D cross-sectional view of Fig. 9.
Appended drawing reference: 1- ring laryngeal mask；2- jet pipe pressing plate；3- jet pipe shell；4- plug cone；5- heat-insulating shield；6- floor；7- is convex
Platform；8- converging portion；9- expansion segment；10- through slot；11- hemispherical-shaped aperture；12- equal diameter through-hole；41- arc section；42- conical section；
The end face 411-；412- groove；13- bolt；31- step one；51- counter sink；413- threaded hole；14- sunk screw；21- unthreaded hole；
32- step two；33- step three；15- sealing ring；71- bolt hole；16- groove.
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 as the case may be
Concrete meaning in the present invention.
Embodiment one:
Fig. 1 is the structural schematic diagram for the solid-liquid rocket circular seam type plug nozzle that the embodiment of the present invention one provides；Fig. 2
For the A-A cross-sectional view of Fig. 1；Fig. 3 is the structural schematic diagram for the jet pipe shell that the present embodiment one provides；Fig. 4 is the B-B section view of Fig. 3
Figure；Fig. 5 is the structural schematic diagram for the ring laryngeal mask that the present embodiment one provides；Fig. 6 is that the structure for the plug cone that the present embodiment one provides is shown
It is intended to；Fig. 7 is the structural schematic diagram for the jet pipe pressing plate that the present embodiment one provides；Fig. 8 is the C-C cross-sectional view of Fig. 7；Fig. 9 is this reality
The structural schematic diagram of the heat-insulating shield of the offer of example one is provided；Figure 10 is the D-D cross-sectional view of Fig. 9；As shown in Fig. 1-Figure 10, the present invention is provided
Solid-liquid rocket circular seam type plug nozzle, including ring laryngeal mask 1, jet pipe pressing plate 2, jet pipe shell 3, plug cone 4 and heat-insulating shield
5；
The ring laryngeal mask 1 is mounted on the outlet end of the jet pipe shell 3 by the jet pipe pressing plate 2；
Boss 7 is equipped with by floor 6 in the jet pipe shell 3；
The plug cone 4 is suspended in the throat of the ring laryngeal mask 1 and connect with the boss 7；
The outer peripheral surface of the plug cone 4 and the throat of the ring laryngeal mask 1 cooperatively form converging portion 8 and expansion segment 9；
The heat-insulating shield 5 is mounted on the arrival end of the jet pipe shell 3, and the heat-insulating shield 5 is equipped with phase with the floor 6
The through slot 10 of perforation.
Preferably, the throat of the ring laryngeal mask 1 includes sequentially connected hemispherical-shaped aperture 11 and equal diameter through-hole 12, the plug
Cone 4 includes sequentially connected arc section 41 and conical section 42, and the end face 411 of the arc section 41 is connect with the boss 7, described
The outer peripheral surface of arc section 41 matches to form converging portion 8 with the hemispherical-shaped aperture 11, and the conical section 42 stretches out the equal diameter
Through-hole 12, the outer peripheral surface of the conical section 42 match to form expansion segment 9 with the equal diameter through-hole 12.
Preferably, the end face 411 of the arc section 41 of the plug cone 4 is equipped with groove 412, the arc section 41 of the plug cone 4
End face 411 be set on the boss 7 by the groove 412 and be connected as one with the boss 7 by bolt 13.
Groove 412 and boss 7 are clearance fit, and groove 412, which is located on plug cone 4, can play reduction plug 4 material requesteds of cone, section
The effect of cost-saving.
Preferably, it is equipped with bolt hole 71 in the boss 7, is equipped with threaded hole 413, the bolt in the groove 412
13 pass through the bolt hole 71 connect with the threaded hole 413 in the groove 412.
Preferably, the heat-insulating shield 5 is to be detachably connected with the jet pipe shell 3, and the arrival end of jet pipe shell 3, which is equipped with, to be used
In the step 1 for installing the heat-insulating shield 5.
Heat-insulating shield 5 is equipped with counter sink 51, and jet pipe shell 3 is equipped with the threaded hole 413 being correspondingly arranged with counter sink 51, sinks
The counter sink 51 that head screw 14 passes through on heat-insulating shield 5 is threadedly coupled with the threaded hole 413 on jet pipe shell 3.
Counter sink 51 on heat-insulating shield 5 is four, and the threaded hole 413 on jet pipe shell 3 is four.
Four counter sinks 51 on heat-insulating shield 5 are located on heat-insulating shield 5 by center of circle ring of the axis of heat-insulating shield 5.
It should be noted that the counter sink 51 on heat-insulating shield 5 is four, the position of counter sink 51 is corresponded on jet pipe shell 3
The threaded hole 413 being equipped with is four and is only intended to illustrate, corresponds to counter sink on the counter sink 51 and jet pipe shell 3 on heat-insulating shield 5
The threaded hole 413 that 51 position is equipped with can also be set as other quantity, just not repeat one by one herein.
Heat-insulating shield 5 prevents from causing structural damage for protecting floor 6 not by high-temperature fuel gas ablation.
Preferably, heat-insulating shield 5 with a thickness of 10mm, meet thermal protection requirement.
It should be noted that heat-insulating shield 5 be only intended to a thickness of 10mm for example, heat-insulating shield 5 also can be used it is other
Thickness does not just repeat one by one herein.
Preferably, heat-insulating shield 5 is made of high silicon oxygen.
Preferably, the jet pipe pressing plate 2 is to be detachably connected with the jet pipe shell 3.
Jet pipe pressing plate 2 is equipped with unthreaded hole 21, and 21 position of unthreaded hole corresponded on jet pipe pressing plate 2 on jet pipe shell 3 offers spiral shell
Pit 413, bolt 13 pass through the threaded hole 413 being correspondingly arranged on unthreaded hole 21 and jet pipe shell 3 on the jet pipe pressing plate 2 and connect
It connects.
Unthreaded hole 21 on jet pipe pressing plate 2 is eight, and the position that the unthreaded hole 21 on jet pipe pressing plate 2 is corresponded on jet pipe shell 3 is opened
Equipped with eight threaded holes 413.
Eight unthreaded holes 21 on jet pipe pressing plate 2 are arranged on jet pipe pressing plate 2 by center of circle annular of the axis of jet pipe pressing plate 2.
It should be noted that unthreaded hole 21 on jet pipe pressing plate 2 is eight, corresponded on jet pipe shell 3 on jet pipe pressing plate 2 eight
The position of a unthreaded hole 21 offers eight threaded holes 413 and is only intended to illustrate, unthreaded hole 21 and jet pipe shell 3 on jet pipe pressing plate 2
The threaded hole 413 that the position of upper corresponding unthreaded hole 21 opens up can also be set as other quantity, just not repeat one by one herein.
Preferably, the outlet end of the jet pipe shell 3 is equipped with the step 2 32 matched with the ring laryngeal mask 1, step two
32 with ring laryngeal mask 1 be clearance fit, and jet pipe pressing plate 2 is equipped with the step 3 33 that cooperate with ring laryngeal mask 1, step 3 33 and ring laryngeal mask
It is clearance fit at 1 cooperation, facilitates the positioning of jet pipe pressing plate 2.
Preferably, the through slot 10 to connect on the heat-insulating shield 5 and the floor 6 is set as four.
It should be noted that the through slot 10 to connect on heat-insulating shield 5 and floor 6 is set as four and is only intended to illustrate
Bright, the through slot 10 to connect on heat-insulating shield 5 and floor 6 may also be configured to other quantity, just not repeat one by one herein.
The plug cone 4 is made of high temperature ablation resistant material, reduces serious ablation of the high-temperature fuel gas to plug cone 4.
The ring laryngeal mask 1 is made of high temperature ablation resistant material, when guaranteeing work, will not be made due to the expanded by heating of material
Area between ring laryngeal mask 1 and plug cone 4 becomes larger, and then influences nozzle performance.
Preferably, sealing ring is installed between the step 2 32 of the outlet end of the ring laryngeal mask 1 and the jet pipe shell 3
15。
Sealing ring 15 for the sealing between ring laryngeal mask 1 and jet pipe shell 3, generally select resistant to high temperature by the material of sealing ring 15
Sealing material, such as the soft graphite or red copper of sealing.
Preferably, the jet pipe shell 3 is equipped with unthreaded hole 21, and jet pipe shell 3 passes through unthreaded hole 21 and engine after-burner
Shell connection.
The quantity of unthreaded hole 21 on jet pipe shell 3 is eight.
It is needing to illustrate but, the quantity of the unthreaded hole 21 on jet pipe shell 3 is eight and is only intended to for example, jet pipe shell
Unthreaded hole 21 on body 3 may also be configured to other quantity, just not repeat one by one herein.
Unthreaded hole 21 on jet pipe shell 3 is arranged on jet pipe shell 3 by center of circle annular of the axis of jet pipe shell 3.
Preferably, jet pipe shell 3 is equipped with groove 16, and the groove 16 is for the tongue pair with after-burner shell flange
It answers, for sealing.
Preferably, the floor 6 is structure as a whole with the boss 7.
Solid-liquid rocket circular seam type plug nozzle provided by the invention, has the advantages that
High-temperature high-pressure fuel gas in solid-liquid rocket engine combustor enters via the arrival end of jet pipe shell 3, and combustion gas exists
Converging portion 8 ramps up, and flows into expansion segment 9 after the throat of ring laryngeal mask 1 reaches velocity of sound and continues to accelerate to supersonic speed.
1, the solid-liquid rocket suitable for different operating height.
2, compact-sized, size is smaller, the ground experiment suitable for solid-liquid rocket.
3, compared with traditional bell nozzle, there is automatic height compensation characteristic, it can be in very big working height range
Higher nozzle efficiency is kept, the solid-liquid rocket wider especially suitable for working height range.
4, nozzle entry plane can play the role of flow-disturbing, be conducive to the blending of combustion gas, improve solid-liquid rocket
Efficiency of combustion improves engine performance.
5, the practical divergence ratio of jet pipe can change with the variation of engine chamber pressure, suitable for the solid-liquid with change propulsive characteristic
Rocket engine.
Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent
Pipe present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: its according to
So be possible to modify the technical solutions described in the foregoing embodiments, or to some or all of the technical features into
Row equivalent replacement；And these are modified or replaceed, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (10)
1. a kind of solid-liquid rocket circular seam type plug nozzle, which is characterized in that including ring laryngeal mask, jet pipe pressing plate, jet pipe shell
Body, plug cone and heat-insulating shield；
The ring laryngeal mask is mounted on the outlet end of the jet pipe shell by the jet pipe pressing plate；
Boss is equipped with by floor in the jet pipe shell；
The plug cone is suspended in the throat of the ring laryngeal mask and connect with the boss；
The outer peripheral surface of the plug cone and the throat of the ring laryngeal mask cooperatively form converging portion and expansion segment；
It is logical equipped with what is connected that the heat-insulating shield is mounted on the arrival end of the jet pipe shell, the heat-insulating shield and the floor
Slot.
2. solid-liquid rocket circular seam type plug nozzle according to claim 1, which is characterized in that the ring laryngeal mask
Throat includes sequentially connected hemispherical-shaped aperture and equal diameter through-hole, and the plug cone includes sequentially connected arc section and conical section,
The end face of the arc section is connect with the boss, and the outer peripheral surface of the arc section matches to form convergence with the hemispherical-shaped aperture
Section, the conical section stretch out the equal diameter through-hole of the ring laryngeal mask, the outer peripheral surface of the conical section and the equal diameter through-hole phase
Cooperatively form expansion segment.
3. solid-liquid rocket circular seam type plug nozzle according to claim 2, which is characterized in that the circle of the plug cone
The end face of segmental arc is equipped with groove, and the end face of the arc section of the plug cone is set on the boss and is passed through by the groove
Bolt is connected as one with the boss.
4. solid-liquid rocket circular seam type plug nozzle according to claim 3, which is characterized in that set in the boss
There is bolt hole, threaded hole is equipped in the groove, the bolt passes through the bolt hole and connect with the threaded hole.
5. solid-liquid rocket circular seam type plug nozzle according to claim 1, which is characterized in that the heat-insulating shield with
The jet pipe shell is to be detachably connected.
6. solid-liquid rocket circular seam type plug nozzle according to claim 1, which is characterized in that the jet pipe pressing plate
It is to be detachably connected with the jet pipe shell.
7. solid-liquid rocket circular seam type plug nozzle according to claim 1, which is characterized in that it is described state plug cone by
High temperature ablation resistant material is made.
8. solid-liquid rocket circular seam type plug nozzle according to claim 1, which is characterized in that the ring laryngeal mask by
High temperature ablation resistant material is made.
9. solid-liquid rocket circular seam type plug nozzle according to claim 1, which is characterized in that the ring laryngeal mask with
Sealing ring is installed between the outlet end of the jet pipe shell.
10. solid-liquid rocket circular seam type plug nozzle according to claim 1, which is characterized in that the floor with
The boss is structure as a whole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710616678.6A CN107165739B (en) | 2017-07-26 | 2017-07-26 | Solid-liquid rocket circular seam type plug nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710616678.6A CN107165739B (en) | 2017-07-26 | 2017-07-26 | Solid-liquid rocket circular seam type plug nozzle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107165739A CN107165739A (en) | 2017-09-15 |
| CN107165739B true CN107165739B (en) | 2019-03-22 |
Family
ID=59817511
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710616678.6A Active CN107165739B (en) | 2017-07-26 | 2017-07-26 | Solid-liquid rocket circular seam type plug nozzle |
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| CN (1) | CN107165739B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109139296B (en) * | 2018-09-11 | 2020-01-24 | 中国人民解放军国防科技大学 | Rocket-based combined cycle engine |
| RU2737821C1 (en) * | 2020-06-09 | 2020-12-04 | Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка" | Dropping together with part of pyro drive a nozzle plug of engine, located inside fuselage of unmanned aerial vehicle |
| CN114776481A (en) * | 2022-04-26 | 2022-07-22 | 北京理工大学 | Plug type spray pipe engine with secondary flow injection structure |
| CN117846815A (en) * | 2023-03-27 | 2024-04-09 | 海南太空科技有限公司 | Annular pneumatic plug type rocket engine thrust chamber |
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| US3144751A (en) * | 1961-05-10 | 1964-08-18 | United Aircraft Corp | Hybrid rocket |
| CN102828851A (en) * | 2012-08-16 | 2012-12-19 | 北京航空航天大学 | Cold flow test device for scaling linear plug type spray pipe carrier |
| CN102852669A (en) * | 2012-08-16 | 2013-01-02 | 北京航空航天大学 | Modularized reusable multiunit circle-to-square compression ratio plug nozzle testing device |
| CN105626307A (en) * | 2014-11-28 | 2016-06-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary plug thrust vectoring nozzle |
| CN106930866A (en) * | 2017-01-26 | 2017-07-07 | 北京航空航天大学 | A kind of solid-liquid rocket ground experiment jet pipe blocking cover structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1224779C (en) * | 2002-12-26 | 2005-10-26 | 北京航空航天大学 | Stopper type jet pipe |
| CN102635463B (en) * | 2012-04-05 | 2014-04-02 | 北京航空航天大学 | Cold-flow test device for one-unit linear plug spray pipe |
| JP2016520176A (en) * | 2013-05-31 | 2016-07-11 | ゼネラル・エレクトリック・カンパニイ | Dual mode plug nozzle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3144751A (en) * | 1961-05-10 | 1964-08-18 | United Aircraft Corp | Hybrid rocket |
| CN102828851A (en) * | 2012-08-16 | 2012-12-19 | 北京航空航天大学 | Cold flow test device for scaling linear plug type spray pipe carrier |
| CN102852669A (en) * | 2012-08-16 | 2013-01-02 | 北京航空航天大学 | Modularized reusable multiunit circle-to-square compression ratio plug nozzle testing device |
| CN105626307A (en) * | 2014-11-28 | 2016-06-01 | 中国航空工业集团公司沈阳发动机设计研究所 | Binary plug thrust vectoring nozzle |
| CN106930866A (en) * | 2017-01-26 | 2017-07-07 | 北京航空航天大学 | A kind of solid-liquid rocket ground experiment jet pipe blocking cover structure |
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| Publication number | Publication date |
|---|---|
| CN107165739A (en) | 2017-09-15 |
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