CN201090319Y - Improved apparatus capable of enhancing rocket thrust force - Google Patents
Improved apparatus capable of enhancing rocket thrust force Download PDFInfo
- Publication number
- CN201090319Y CN201090319Y CNU2007200459501U CN200720045950U CN201090319Y CN 201090319 Y CN201090319 Y CN 201090319Y CN U2007200459501 U CNU2007200459501 U CN U2007200459501U CN 200720045950 U CN200720045950 U CN 200720045950U CN 201090319 Y CN201090319 Y CN 201090319Y
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- CN
- China
- Prior art keywords
- rocket
- outlet pipe
- thrust
- utility
- model
- 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.)
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Abstract
The utility model relates to an improved device that can improve the thrust of rocket, which is characterized in that: above three exhaust tubes are arranged on the exhaust wall of the combustion chamber of rocket that is composed of a rocket body and a combustion chamber. The axial line of each exhaust tube form an angle of 45 degrees with the exhaust wall, therefore in the case of no adding fuel, the thrust of rocket can be enhanced by 50 percent. The utility model is in particular suitable for binding type rocket and also suitable for jet plane.
Description
Technical field
The utility model design satellite-launching facility specifically, is the modifying device that can improve rocket thrust.
Technical background
The rocket of launching an artificial satellite is that the gas that is given off by the firing chamber promotes the outer air of rocket afterbody, gives rocket body reaction force by the outer air of rocket afterbody again and promotes that the rocket body advances.Existing rocket from the gas of firing chamber discharging, all is to be discharged by an axis outlet pipe (being commonly called as trunnion) vertical with the firing chamber cross section.Like this, the surface of contact of the air that the gas of discharge and rocket body afterbody are outer is big, thereby the pressure that produces is just little, and then the reaction that air produced outside the rocket body afterbody is also little, thereby, also little to the thrust of rocket body.
Goal of the invention
The purpose of this utility model is a kind of modifying device of design, under the identical situation of fuel, improves thrust.
Technological scheme
The utility model is to realize purpose of design like this.At the outlet pipe of installing on the discharging wall of firing chamber more than three, the center that outlet pipe is evenly distributed in outlet pipe is on the same circumference in the center of circle, and makes the axis of outlet pipe and discharging wall cross section be miter angle.
The utility model can make the gas of discharging from each outlet pipe form " focus point " in a distance at rocket body afterbody center, locate at " focus point ", gas from each outlet pipe discharge, through interacting, form and make a concerted effort, the air outer to rocket body afterbody produces bigger pressure, thereby makes the rocket body obtain bigger thrust.
The utility model only need improve a little to existing rocket, just can obtain bigger thrust under the condition that does not increase fuel.
Description of drawings
Fig. 1 is a schematic representation of the present utility model.
Embodiment
Embodiment
Below in conjunction with accompanying drawing, a non-limiting examples is illustrated.
Three outlet pipes 3 have been installed on the discharging wall 4 of the rocket of being made up of rocket body 1, firing chamber 2, it is 120 degree positions of the same diameter circumference in the center of circle that each outlet pipe 3 is installed in respectively with discharging wall 4 centers, guaranteeing even distribution, and make the axis of each outlet pipe 3 and discharging wall cross section be 45 degree angles.The cross-section area of three outlet pipes and former outlet pipe section area equate.
The utility model can improve rocket thrust 50% under the situation that does not increase fuel.Be particularly suitable for cluster carrier rocket, also be suitable for jet airplane.
Claims (1)
1. can improve the modifying device of rocket thrust, form, it is characterized in that by rocket body (1), firing chamber (2):
Outlet pipe (3) more than three is 1. arranged on the discharging wall (4) of firing chamber (2);
2. to be evenly distributed in discharging wall (4) center be on the same circumference in the center of circle to outlet pipe (3);
3. angles are spent in the cross section 45 of the axis of outlet pipe (3) and discharging wall (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200459501U CN201090319Y (en) | 2007-09-07 | 2007-09-07 | Improved apparatus capable of enhancing rocket thrust force |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200459501U CN201090319Y (en) | 2007-09-07 | 2007-09-07 | Improved apparatus capable of enhancing rocket thrust force |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201090319Y true CN201090319Y (en) | 2008-07-23 |
Family
ID=39862079
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007200459501U Expired - Fee Related CN201090319Y (en) | 2007-09-07 | 2007-09-07 | Improved apparatus capable of enhancing rocket thrust force |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201090319Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103455646A (en) * | 2012-05-31 | 2013-12-18 | 北京宇航系统工程研究所 | Main binding connection structure dynamic simulation method |
| CN106150755A (en) * | 2015-03-09 | 2016-11-23 | 谭佑军 | Aero-jet engine |
| CN112211747A (en) * | 2020-10-13 | 2021-01-12 | 西北工业大学 | Internal structure of rotary acceleration type solid rocket engine |
-
2007
- 2007-09-07 CN CNU2007200459501U patent/CN201090319Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103455646A (en) * | 2012-05-31 | 2013-12-18 | 北京宇航系统工程研究所 | Main binding connection structure dynamic simulation method |
| CN106150755A (en) * | 2015-03-09 | 2016-11-23 | 谭佑军 | Aero-jet engine |
| CN112211747A (en) * | 2020-10-13 | 2021-01-12 | 西北工业大学 | Internal structure of rotary acceleration type solid rocket engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080723 Termination date: 20120907 |