CN204419396U - Adjustable Double pulse solid rocket motor nozzle test device - Google Patents
Adjustable Double pulse solid rocket motor nozzle test device Download PDFInfo
- Publication number
- CN204419396U CN204419396U CN201520066186.0U CN201520066186U CN204419396U CN 204419396 U CN204419396 U CN 204419396U CN 201520066186 U CN201520066186 U CN 201520066186U CN 204419396 U CN204419396 U CN 204419396U
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- China
- Prior art keywords
- nozzle block
- safety pin
- pin
- extending section
- section parts
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- Withdrawn - After Issue
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Testing Of Engines (AREA)
- Toys (AREA)
Abstract
The utility model discloses a kind of adjustable Double pulse solid rocket motor nozzle test device, comprise nozzle block, larynx backing member, extending section parts, safety pin, upper shearing sleeve and down cut sleeve, larynx backing member is arranged on the fuel gas inlet end in nozzle block, extending section parts are arranged on the gas outlet end in nozzle block, larynx backing member is by the annular table terrace location fit in its annular table terrace axially and nozzle block, safety pin stretches into the pin-and-hole on extending section parts through the pin-and-hole on nozzle block wall, shearing sleeve is provided with between safety pin and nozzle block, down cut sleeve is set between safety pin and extending section parts, safety pin and nozzle block pin-and-hole arrange the screw thread matched at corresponding position near one end of nozzle block outer wall, the utility model can improve experimental safe, save experimentation cost.
Description
Technical field
The utility model belongs to Solid Rocket Engine Test research field, particularly a kind of adjustable Double pulse solid rocket motor nozzle test device.
Background technique
Along with the development of military science and technology, in order to improve existence and the penetration ability of guided missile, emphasize stand-off firing, trajectory variability.Pulsed motor utilizes isolation mounting that firing chamber is divided into some parts, by repeatedly shutting down and lighting a fire, reasonable distribution thrust and each burst length, realizes the optimum management of trajectory optimal control and engine power.For Double pulse solid rocket motor, have compared with traditional single thrust or Design of Single-chamber motor that range is farther, mobility is stronger, precision is higher.
Ground performance experimental study is the important means in development process.Because double pulsing motor barrier technique awaits further raising, the second pulsed motor accidental ignition is unsuccessfully caused for preventing interlayer work in test, chamber pressure is uprushed, housing is caused to burst, usually relief hole is set at head of combustion chamber or housing side, when internal pressure of combustion chamber be greater than burning chamber shell can bear pressure maximum time, relief hole is started working, and avoids the danger of blasting.But the method has certain defect.When being arranged on the relief hole work of head or side, firing chamber, the high-temperature high-pressure fuel gas of ejection may damage thrust pickup and other the data signal line of head.In addition, when carrying out many group tests, when throat's ablation has not seriously reached design objective, usually need change overall nozzle component, this method is uneconomical.Therefore, need to design a kind of novel adjustable jet pipe.
Summary of the invention
The purpose of this utility model is to provide a kind of adjustable Double pulse solid rocket motor nozzle test device that can improve experimental safe, save experimentation cost.
The technical solution realizing the utility model object is:
A kind of adjustable Double pulse solid rocket motor nozzle test device, comprise nozzle block, larynx backing member, extending section parts, safety pin, upper shearing sleeve and down cut sleeve, larynx backing member is arranged on the fuel gas inlet end in nozzle block, extending section parts are arranged on the gas outlet end in nozzle block, larynx backing member is by the annular table terrace location fit in its annular table terrace axially and nozzle block, safety pin stretches into the pin-and-hole on extending section parts through the pin-and-hole on nozzle block wall, shearing sleeve is provided with between safety pin and nozzle block, down cut sleeve is set between safety pin and extending section parts, safety pin and nozzle block pin-and-hole arrange the screw thread matched at corresponding position near one end of nozzle block outer wall.
The utility model compared with prior art, its remarkable advantage:
(1) the utility model part is few, and structure is simple, easy to assembly.
(2) the utility model is for different design objectives, under the prerequisite ensureing nozzle block size constancy, by changing the size of larynx backing member and expansion segment, can adapt to the designing requirement such as different divergence ratios, convergence half-angle, there is certain versatility.
(3) safety pin of the present utility model and upper and lower shearing sleeve with the use of, diameter of safety pin and upper and lower shearing sleeve diameter can be regulated according to test demand, the convenient shear strength regulating safety pin.
(4) the utility model avoids the defect needing integral replacing nozzle component when profile ablation is serious in jet pipe, only needs larynx backing member serious for ablation to change, and nozzle block still can continue to use, and effectively can save experimentation cost.
Below in conjunction with accompanying drawing, the utility model is described in further detail.
Accompanying drawing explanation
Fig. 1 be the utility model adjustable Double pulse solid rocket motor nozzle test device partly cut open structural representation.
Fig. 2 is the axial sectional view of the utility model adjustable Double pulse solid rocket motor nozzle test device.
Fig. 3 is the contrast scheme of installation of the utility model adjustable Double pulse solid rocket motor nozzle test device different size safety pin; A () is that thicker safety pin coordinates thinner shearing sleeve, (b) is that thinner safety pin coordinates thicker shearing sleeve.
Embodiment
Composition graphs 1 ~ Fig. 3:
A kind of adjustable Double pulse solid rocket motor nozzle test device of the utility model, comprise nozzle block 1, larynx backing member 2, extending section parts 3, safety pin 4, upper shearing sleeve 5 and down cut sleeve 6, larynx backing member 2 is arranged on the fuel gas inlet end in nozzle block 1, extending section parts 3 are arranged on the gas outlet end in nozzle block 1, larynx backing member 2 is by the annular table terrace location fit in its annular table terrace axially and nozzle block 1, safety pin 4 stretches into the pin-and-hole on extending section parts 3 through the pin-and-hole on nozzle block 1 wall, shearing sleeve 5 is provided with between safety pin 4 and nozzle block 1, down cut sleeve 6 is set between safety pin 4 and extending section parts 3, safety pin 4 and nozzle block 1 pin-and-hole arrange the screw thread matched at corresponding position near one end of nozzle block 1 outer wall.
The internal diameter of larynx backing member 2 is less than the internal diameter of extending section parts 3, and seamlessly transits between the two.
Safety pin 4 is symmetricly set on the circumference of nozzle block 1.
Standard: according to design objective, loads nozzle block by the larynx backing member 2 meeting designing requirement successively with extending section parts 3, first puts into down cut sleeve 6, and then put into shearing sleeve 5 from the pin-and-hole of nozzle block 1, note precedence.Finally to screw on safety pin 4.After confirming that assembling is errorless, nozzle block 1 is screwed into firing chamber, screws, can test.
Working principle: under the prerequisite ensureing nozzle block 1 size constancy, by changing the size of larynx backing member 2 and extending section parts 3, can adapt to the designing requirement such as different divergence ratios, convergence half-angle; Regulate the internal diameter (as Fig. 3) of safety pin 4 diameter and upper shearing sleeve 5 and down cut sleeve 6 according to test demand, convenient adjustment safety pin 4 shear strength, makes design have certain versatility.
In test, if interlayer work failure under the first pulsed motor high-temperature high-pressure fuel gas effect, cause the second pulse accidental ignition, chamber pressure is caused sharply to increase, under high-pressure gas effect, safety pin 4 is sheared disconnected, larynx backing member 2 and extending section parts 3 are released from nozzle block 1, makes blast tube area become large, thus reach the effect of safety relief.
Claims (3)
1. an adjustable Double pulse solid rocket motor nozzle test device, it is characterized in that: comprise nozzle block (1), larynx backing member (2), extending section parts (3), safety pin (4), upper shearing sleeve (5) and down cut sleeve (6), larynx backing member (2) is arranged on the fuel gas inlet end in nozzle block (1), extending section parts (3) are arranged on the gas outlet end in nozzle block (1), larynx backing member (2) is by the annular table terrace location fit in its annular table terrace axially and nozzle block (1), safety pin (4) stretches into the pin-and-hole on extending section parts (3) through the pin-and-hole on nozzle block (1) wall, shearing sleeve (5) is provided with between safety pin (4) and nozzle block (1), down cut sleeve (6) is set between safety pin (4) and extending section parts (3), safety pin (4) and nozzle block (1) pin-and-hole arrange the screw thread matched at corresponding position near one end of nozzle block (1) outer wall.
2. adjustable Double pulse solid rocket motor nozzle test device according to claim 1, is characterized in that: the internal diameter of described larynx backing member (2) is less than the internal diameter of extending section parts (3), and seamlessly transits between the two.
3. adjustable Double pulse solid rocket motor nozzle test device according to claim 1 and 2, is characterized in that: described safety pin (4) is symmetricly set on the circumference of nozzle block (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520066186.0U CN204419396U (en) | 2015-01-29 | 2015-01-29 | Adjustable Double pulse solid rocket motor nozzle test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520066186.0U CN204419396U (en) | 2015-01-29 | 2015-01-29 | Adjustable Double pulse solid rocket motor nozzle test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204419396U true CN204419396U (en) | 2015-06-24 |
Family
ID=53469774
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520066186.0U Withdrawn - After Issue CN204419396U (en) | 2015-01-29 | 2015-01-29 | Adjustable Double pulse solid rocket motor nozzle test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204419396U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104612858A (en) * | 2015-01-29 | 2015-05-13 | 南京理工大学 | Adjustable double-pulse solid rocket engine jet pipe testing device |
| CN105201689A (en) * | 2015-09-09 | 2015-12-30 | 西北工业大学 | Variable-geometry RBCC (rocket based combined cycle) engine for ground experiment |
| CN106640893A (en) * | 2016-12-18 | 2017-05-10 | 内蒙古航天红峡化工有限公司 | Guide pin for assembling jet pipe of solid rocket engine |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
-
2015
- 2015-01-29 CN CN201520066186.0U patent/CN204419396U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104612858A (en) * | 2015-01-29 | 2015-05-13 | 南京理工大学 | Adjustable double-pulse solid rocket engine jet pipe testing device |
| CN105201689A (en) * | 2015-09-09 | 2015-12-30 | 西北工业大学 | Variable-geometry RBCC (rocket based combined cycle) engine for ground experiment |
| CN106640893A (en) * | 2016-12-18 | 2017-05-10 | 内蒙古航天红峡化工有限公司 | Guide pin for assembling jet pipe of solid rocket engine |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150624 Effective date of abandoning: 20160921 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |