CN205532924U - Yawing force engine jet pipe - Google Patents
Yawing force engine jet pipe Download PDFInfo
- Publication number
- CN205532924U CN205532924U CN201520877206.2U CN201520877206U CN205532924U CN 205532924 U CN205532924 U CN 205532924U CN 201520877206 U CN201520877206 U CN 201520877206U CN 205532924 U CN205532924 U CN 205532924U
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- CN
- China
- Prior art keywords
- aircraft
- diffuser
- jet pipe
- spray tube
- force engine
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- 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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- Jet Pumps And Other Pumps (AREA)
Abstract
The utility model relates to a yawing force engine jet pipe, this spray tube be mainly by the triplex, conical convergent portion, circular shape throat, enter the mouth into circular, export for the diffuser of big length -width ratio rectangle. The diffuser exports cross -sectional area from round inlet to the rectangle increase in succession, and the air current accelerates in succession, avoids appearing the shock wave. Because the diffuser shape of this novel spray tube can adapt to the appearance of aircraft well, the convergent portion of spray tube and throat can be arranged in aircraft to this novel spray tube when installing inside, the diffuser stretches out the surface of aircraft. This design can improve the air current height of spray tube export, reduces spray tube side direction sport and the external coupling who streams of aircraft, easily realizes the accurate control to the aircraft.
Description
Technical field
This utility model relates to a kind of solid rocket motor nozzle, especially relates to the jet pipe of directly laterally force engine.
Background technology
Straight gas multiplex control system uses the coupling control mode of direct force and aerodynamic force to be controlled aircraft, can be effectively improved the mobility of aircraft, strengthen its survival ability.Side force electromotor has the biggest impact as the dynamical system of side-jet control device in straight gas multiplex control system to the performance of whole straight gas multiplex control system.
Although directly laterally force engine can make up the shortcoming that the aircraft aerodynamic force when the region flight of transmitting initial stage or rarefaction of air controls deficiency, but the whole jet pipe due to side force electromotor is placed in the inside of aircraft, the outlet of jet pipe is positioned at the surface of aircraft, the lateral jet of nozzle exit and the external of spacecraft is so made to stream generation coupling, near nozzle exit, be equivalent to local change the profile of aircraft, aircraft is produced near region interference；The aerofoil of the airflow convection warp after coupling produces additional power or moment, produces far field interference, and these interference are unfavorable for the accurate control to aircraft.The diffuser of jet pipe can be arranged on the surface of aircraft by the novel jet pipe of design of the present utility model, improves the outlet height of lateral jet, the coupling streamed outside the lateral jet of reduction side force engine jet pipe and aircraft body.
Summary of the invention
The purpose of this utility model is to provide a kind of novel side force engine jet pipe, reduces the coupling streamed outside lateral jet and aircraft body, it is easy to accomplish more accurately control aircraft.
The technical scheme is that
The converging portion of jet pipe uses conical profile, diffuser is connected by circular nozzle throat with converging portion, the diffuser of jet pipe is to be transitioned into rectangular outlet by round entrance, the length-width ratio of rectangular outlet is more than 7, ensure that nozzle contour is smooth in transient process, and sectional area increases continuously, air-flow can accelerate continuously, reducing the flow losses of jet pipe, the converging portion of jet pipe and throat are placed in aircraft interior, and diffuser stretches out the outer surface of aircraft.
The beneficial effects of the utility model are, the profile of this novel jet pipe diffuser can well adapt to the configuration design of aircraft, therefore diffuser can be placed in the outer surface of aircraft, improve the outlet height of side force engine jet pipe lateral jet, reduce lateral jet and the external coupling streamed, it is easy to accomplish the accurate control to aircraft.
Accompanying drawing explanation
Fig. 1 is the front view of novel jet pipe, and wherein 1 is diffuser, and 2 is nozzle throat, and 3 is converging portion, and 4 is engine chamber.
Fig. 2 is the top view of novel jet pipe, and wherein 5 is round entrance, and 6 is rectangular outlet.
Detailed description of the invention
With reference to shown in Fig. 1, this novel jet pipe is mainly made up of three parts, diffuser 1, nozzle throat 2 and converging portion 3.The combustion gas produced in engine chamber 4 is accelerated by the converging portion 3 of jet pipe, reaches velocity of sound at nozzle throat 2, continues to expand and accelerate after entering the diffuser 1 of jet pipe, and the rectangular outlet 6 at jet pipe reaches supersonic speed.
With reference to shown in Fig. 2, the diffuser round entrance 5 of this novel jet pipe i.e. round exit of nozzle throat 2, the outlet of jet pipe is rectangle, the design of this jet pipe can realize converging portion 3 and the nozzle throat 2 of jet pipe are placed in aircraft interior, the diffuser 1 of jet pipe stretches out the surface of aircraft, thus improve the outlet height of jet flow, reduce the coupling streamed outside lateral jet and aircraft body, it is easy to accomplish the accurate control to aircraft.
Claims (4)
1. a side force engine jet pipe, including diffuser [1], nozzle throat [2] and converging portion [3], it is characterized in that, described diffuser [1] is connected by nozzle throat [2] with converging portion [3], and described diffuser [1] is transitioned into rectangular outlet [6] by round entrance [5].
A kind of side force engine jet pipe the most according to claim 1, it is characterised in that the length-width ratio of rectangular outlet [6] is more than 7.
A kind of side force engine jet pipe the most according to claim 1, it is characterised in that described converging portion [3] is conical profile, described nozzle throat [2] is circular.
A kind of side force engine jet pipe the most according to claim 1, it is characterised in that described converging portion [3] and nozzle throat [2] are placed in aircraft interior, and described diffuser [1] stretches out aircraft surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520877206.2U CN205532924U (en) | 2015-11-06 | 2015-11-06 | Yawing force engine jet pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520877206.2U CN205532924U (en) | 2015-11-06 | 2015-11-06 | Yawing force engine jet pipe |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205532924U true CN205532924U (en) | 2016-08-31 |
Family
ID=56761511
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520877206.2U Active CN205532924U (en) | 2015-11-06 | 2015-11-06 | Yawing force engine jet pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205532924U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112727634A (en) * | 2020-12-07 | 2021-04-30 | 西安航天动力研究所 | Rectangular cross-section spray pipe |
-
2015
- 2015-11-06 CN CN201520877206.2U patent/CN205532924U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112727634A (en) * | 2020-12-07 | 2021-04-30 | 西安航天动力研究所 | Rectangular cross-section spray pipe |
| CN112727634B (en) * | 2020-12-07 | 2022-08-16 | 西安航天动力研究所 | Rectangular cross-section spray pipe |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |