WO2007007213A1 - A nozzle-vane system for a 122-mm diameter rocket - Google Patents
A nozzle-vane system for a 122-mm diameter rocket Download PDFInfo
- Publication number
- WO2007007213A1 WO2007007213A1 PCT/IB2006/050950 IB2006050950W WO2007007213A1 WO 2007007213 A1 WO2007007213 A1 WO 2007007213A1 IB 2006050950 W IB2006050950 W IB 2006050950W WO 2007007213 A1 WO2007007213 A1 WO 2007007213A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- nozzle
- vane
- vanes
- rockets
- hole
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
- F42B10/16—Wrap-around fins
Definitions
- This invention relates to a vane system which was built for 122-mm rockets and can be opened with a nozzle and a spring drive attached thereto.
- vanes used in the 122-mm rockets are fixed on the nozzle in an unmovable manner. Due to the projections formed by fixed vanes which are used in this way and located on the rear side of the rocket having a large diameter such as 122-mm, the rocket launcher barrel has to be built according to this structure, thus causing barrel to have a complex geometry. Considering the fact that success of the rocket particularly in reaching to the target in the nearest way is achieved through a narrow tolerance between the barrel and the rocket, it is difficult, for said barrel- rocket tolerance relationship, to achieve sensitivity in the target with a 122-mm rocket having a fixed vane configuration and a complex structured barrel pursuant thereto.
- vanes which are kept in a closed position during the launch and then opened by a spring pressure thereafter, and a nozzle system onto which these vanes are fitted are the fundamental point of this invention.
- recession-shaped guiding elements for the vanes in the circular sectioned inner surface of the barrel Owing to the vane structure which is used in a 122-mm rocket and has an ability to open in the air, there is no need for recession-shaped guiding elements for the vanes in the circular sectioned inner surface of the barrel.
- an economic rocket launcher system with increasable target hit ratio can be obtained.
- aerodynamic properties of the rocket are also improved with the angles formed in the vanes.
- the aim of this invention is to provide vanes which are kept in a closed position during the launch and then opened by a spring pressure thereafter, and a nozzle system onto which these vanes are fitted in a 122-mm rocket in order to increase the target hit ratio thereof.
- Fig. 1 is an assembled perspective view of the nozzle-vane system.
- Fig. 2 is a perspective view of the nozzle.
- Fig. 3 is side and sectional views of the nozzle.
- Fig. 4 is a perspective view of the vane.
- Fig. 5 is side and bottom views of the vane.
- Fig. 6 is a perspective view of the spring which enables vane to open in the air.
- Fig. 7 is a perspective view of the pin which is used in the connection of vane to the nozzle.
- Nozzle-vane system (1 ) Nozzle (10) Body (1 1 ) Inlet flange (12)
- a nozzle-vane system (1 ) for inventive 122-mm rockets of which assembled perspective view is shown as fig. 1 comprises a nozzle (10), and four vanes (40) which are fitted around the nozzle (10) with springs (60) and pins (70), which are in a closed position such that they surround the outer surface of the nozzle (10) during the rocket launch, and which can be opened by the pressure of spring (60) thereafter.
- FIG.3 comprises a body (1 1 ) in a hollow cylindrical form, of which both ends are open, an inlet flange (12) and an outlet flange (13) which are located on both ends of this body (1 1 ) and project from edge to outside, four lugs (17) which project in the middle of the body (1 1 ) outwards and have an equal angle among themselves, an inner conic surface (14) which advances towards the middle of the body (1 1 ) by narrowing with an angle of 13.2 ° from a large diameter towards the inside of the body (1 1 ) from where the inlet flange (12) is located, an inner middle surface (15) which starts with a sharp diameter expansion from the interface (21 ) where the inner conic surface (14) is ended and advances towards the outlet flange (13) without any conicity, an inner outlet surface (16) which also starts with a sharp diameter expansion from the interface (22) where the inner middle surface (15) is ended and expands towards the outside at the lower side of the outlet flange (13) without any
- a vane (40) of which perspective view is shown in fig. 4 and side and bottom views are shown in fig.5 comprises a vane body (41 ) which is at a thickness of a thin meat, in a parabolic form or circularly arched, vane rear angles (42, 42') of 7° which are on the lower and upper surface at the rear side of this body (41 ), vane side angles (43, 43') of 5,5 ° which are on the lower and upper surface at the side of said body (41 ), two pin seating slots (44, 44') which are located on the other side and in the front and rear side of the said body (41 ) and formed as in circular section with the expansion of the body (41 ) section, a pin hole (45) which passes through these slots, vane channels (46, 46') on the front side of the slots (44, 44'), of which inside is rounded and both sides are open, and into which vane front and rear guides (19, 20) on the nozzle (10) can seat and a spring seating channel (4
- a spring (60) which is a part of the nozzle-vane system (1 ) is a standard torsion spring and is shown in fig. 6 and a circular cross sectioned pin (70) which is yet another part of this system (1 ) is shown in fig. 7.
- vanes (40) are fitted on the nozzle (10) such that pin holes (45) are coaxial with the hole groups (18, 18', 18"), and vane front guides (19) confront with the vane channel (46) and vane rear guides (20) with the vane channel (46').
- Springs (60) are located between the lugs (17) and the pin seating slots (44'), and free one ends of the springs (60) are connected to the spring seating channel (47) and the other ends thereof rest against the lugs (17).
- pins (70) are fitted into the hole groups (18, 18', 18") and one ends of the pins (70) rest against inside the holes (18") and other free ends thereof remain within the holes (18).
- a nozzle-vane system (1 ) for above preferred 122-mm rocket is not intended to limit the protection scope of the invention. According to the information described with the invention, modifications to be performed on this preferred nozzle-vane system (1 ) for a 122-mm rocket should be evaluated within the protection scope of the invention.
Abstract
In order to increase the target hit ratio of a 122-mm rocket, vanes which are kept in a closed position during the launch and then opened by a spring pressure thereafter, and the nozzle onto which these vanes are fitted in a 122-mm rocket are the subject- matter of this invention. A nozzle-vane system (1 ) for 122-mm rockets described with the invention comprises a nozzle (10) and four vanes (40) which are fitted around the nozzle (10) with springs (60) and pins (70), which are in a closed position such that they surround the outer surface of the nozzle (10) during the rocket launch and which can be opened by the pressure of spring (60) thereafter.
Description
DESCRIPTION
A NOZZLE-VANE SYSTEM FOR A 122-MM DIAMETER ROCKET
Techn ical Field
This invention relates to a vane system which was built for 122-mm rockets and can be opened with a nozzle and a spring drive attached thereto.
Prior Art
It is known in the art that fundamental elements required to ignite and launch the rockets from their batteries and to advance them in the air are a nozzle which is used to discharge the rocket fuel located in the rear side of the rocket by burning and vanes which lie on the nozzle. A wide range of nozzle-vane system is employed upon the need in the nozzle and the vanes attached thereto, which are used in the rockets in different diameters and sizes. Particularly, success of rockets in traveling within the required range and reaching to the target is closely related with the structure of the nozzle-vane system and the rocket launcher barrel from which the rocket that bears this system is launched.
In the art, vanes used in the 122-mm rockets are fixed on the nozzle in an unmovable manner. Due to the projections formed by fixed vanes which are used in this way and located on the rear side of the rocket having a large diameter such as 122-mm, the rocket launcher barrel has to be built according to this structure, thus causing barrel to have a complex geometry. Considering the fact that success of the rocket particularly in reaching to the target in the nearest way is achieved through a narrow tolerance between the barrel and the rocket, it is difficult, for said barrel- rocket tolerance relationship, to achieve sensitivity in the target with a 122-mm rocket having a fixed vane configuration and a complex structured barrel pursuant thereto.
In a 122-mm rocket, vanes which are kept in a closed position during the launch and then opened by a spring pressure thereafter, and a nozzle system onto which these vanes are fitted are the fundamental point of this invention. Owing to the vane
structure which is used in a 122-mm rocket and has an ability to open in the air, there is no need for recession-shaped guiding elements for the vanes in the circular sectioned inner surface of the barrel. Thus, it is easier to achieve narrow tolerances between the barrel and the rocket and also, with a simpler barrel structure, an economic rocket launcher system with increasable target hit ratio can be obtained. Furthermore, aerodynamic properties of the rocket are also improved with the angles formed in the vanes.
Aim of the Invention
The aim of this invention is to provide vanes which are kept in a closed position during the launch and then opened by a spring pressure thereafter, and a nozzle system onto which these vanes are fitted in a 122-mm rocket in order to increase the target hit ratio thereof.
Description of Figures
A nozzle-vane system for invention of 122-mm rocket is shown in the attached drawings, wherein:
Fig. 1 is an assembled perspective view of the nozzle-vane system.
Fig. 2 is a perspective view of the nozzle.
Fig. 3 is side and sectional views of the nozzle.
Fig. 4 is a perspective view of the vane.
Fig. 5 is side and bottom views of the vane.
Fig. 6 is a perspective view of the spring which enables vane to open in the air.
Fig. 7 is a perspective view of the pin which is used in the connection of vane to the nozzle.
The parts in the figures are numbered one by one and the corresponding terms of these numbers are given below.
Nozzle-vane system (1 ) Nozzle (10) Body (1 1 )
Inlet flange (12)
Outlet flange (13)
Inner conic surface (14)
Inner middle surface (15)
Inner outlet surface (16)
Lug (17)
Holes (18, 18', 18")
Vane front guides (19)
Vane rear guides (20)
Interface (21 )
Interface (22)
Long axis (23)
Hole axis (24)
Channels (25)
Vane (40)
Vane body (41 )
Vane rear angles (42, 42')
Vane side angles (43, 43')
Pin seating slots (44, 44')
Pin hole (45)
Vane channels (46, 46')
Spring seating channel (47)
Spring (60)
Pin (70)
Description of Invention
A nozzle-vane system (1 ) for inventive 122-mm rockets, of which assembled perspective view is shown as fig. 1 comprises a nozzle (10), and four vanes (40) which are fitted around the nozzle (10) with springs (60) and pins (70), which are in a closed position such that they surround the outer surface of the nozzle (10) during the rocket launch, and which can be opened by the pressure of spring (60) thereafter.
A nozzle (10) of which perspective view is shown in fig. 2, and side and sectional views are shown in fig.3 comprises a body (1 1 ) in a hollow cylindrical form, of which both ends are open, an inlet flange (12) and an outlet flange (13) which are located on both ends of this body (1 1 ) and project from edge to outside, four lugs (17) which project in the middle of the body (1 1 ) outwards and have an equal angle among themselves, an inner conic surface (14) which advances towards the middle of the body (1 1 ) by narrowing with an angle of 13.2 ° from a large diameter towards the inside of the body (1 1 ) from where the inlet flange (12) is located, an inner middle surface (15) which starts with a sharp diameter expansion from the interface (21 ) where the inner conic surface (14) is ended and advances towards the outlet flange (13) without any conicity, an inner outlet surface (16) which also starts with a sharp diameter expansion from the interface (22) where the inner middle surface (15) is ended and expands towards the outside at the lower side of the outlet flange (13) without any conicity, a longitudinal hole (18) on the inlet flange (12), of which axes cross with hole axis (24) that forms an angle of 0,8° with the longitudinal axis (23) of the nozzle (10), a longitudinal hole (18') which is located on the lug (17), and a blind hole (18") which is located on the outlet flange (13) and totally a group of four holes (18, 18', 18") in which each of this group of holes (18, 18', 18") stands with an equal angle to one another, vane front guides (19) which are each located where the hole (18) on the inlet flange (12) lies, and extend as a projection towards the outlet such that they are in parallel with the longitudinal axis (23), and of which ends are rounded, vane rear guides (20) which have the similar structure as the vane front guides (19), extend towards the outlet and are located on the lug (17), channels (25) which are located around the outlet flange (13) and into which vane holding clamps (not show in the figures) are placed.
A vane (40) of which perspective view is shown in fig. 4 and side and bottom views are shown in fig.5 comprises a vane body (41 ) which is at a thickness of a thin meat, in a parabolic form or circularly arched, vane rear angles (42, 42') of 7° which are on the lower and upper surface at the rear side of this body (41 ), vane side angles (43, 43') of 5,5 ° which are on the lower and upper surface at the side of said body (41 ), two pin seating slots (44, 44') which are located on the other side and in the front and rear side of the said body (41 ) and formed as in circular section with the expansion of the body (41 ) section, a pin hole (45) which passes through these slots, vane channels (46, 46') on the front side of the slots (44, 44'), of which inside is
rounded and both sides are open, and into which vane front and rear guides (19, 20) on the nozzle (10) can seat and a spring seating channel (47) which is just at the back of the pin seating slot (44') on the vane body (41 ) and recesses inwards.
A spring (60) which is a part of the nozzle-vane system (1 ) is a standard torsion spring and is shown in fig. 6 and a circular cross sectioned pin (70) which is yet another part of this system (1 ) is shown in fig. 7.
In a nozzle-vane system (1 ) of which assembled view is given in fig. 1 , vanes (40) are fitted on the nozzle (10) such that pin holes (45) are coaxial with the hole groups (18, 18', 18"), and vane front guides (19) confront with the vane channel (46) and vane rear guides (20) with the vane channel (46'). Springs (60) are located between the lugs (17) and the pin seating slots (44'), and free one ends of the springs (60) are connected to the spring seating channel (47) and the other ends thereof rest against the lugs (17). In this position, pins (70) are fitted into the hole groups (18, 18', 18") and one ends of the pins (70) rest against inside the holes (18") and other free ends thereof remain within the holes (18).
Before a 122-mm rocket which includes inventive nozzle-vane system (1 ) is placed in its barrel, concave shaped lower surfaces of the vanes (40) are closed onto the nozzle (10), and vane holding clamps, which are placed into the channels (25) and used to hold the vanes (40) in this position in order not to be re-opened by the pressure of the springs (60), are used. These clamps are removed after rocket is placed in the barrel. Vanes (40) are opened by the pressure of the springs (60) after it is launched and vane channels (46, 46') are re-placed onto vane front and rear guides (19, 20).
A nozzle-vane system (1 ) for above preferred 122-mm rocket is not intended to limit the protection scope of the invention. According to the information described with the invention, modifications to be performed on this preferred nozzle-vane system (1 ) for a 122-mm rocket should be evaluated within the protection scope of the invention.
Claims
1 . A nozzle-vane system (1 ) for 122-mm rockets comprising a nozzle (10) including a body (1 1 ) in a hollow cylindrical form, of which both ends are open, and four vanes (40) in a parabolic form or circularly arched which are fitted around this nozzle (10) with springs (60) in the form of torsion spring and circular sectioned pins (70), which are in a closed position such that they surround the outer surface of the nozzle (10) during the rocket launch, and which can be opened by the pressure of spring (60) thereafter, characterized in that in order to increase the target hit ratio of a 122-mm rocket and open the vanes which are closed on the nozzle (10) prior to launch by the pressure of spring (60) after launching, there are four lugs (17) which project in the middle of the body (1 1 ) outwards and have an equal angle among themselves; vanes (40) are fitted on the nozzle (10) such that pin holes (45) thereon is coaxial with the hole groups (18,18', 18") on the nozzle (10); vane front guides (19) and vane rear guides (20) on the nozzle (10) are fitted such that they confront with the vane channels (46, 46'); springs (60) in the form of torsion springs are located between the lugs (17) on the nozzle (10) and the pin seating slots (44') on the vanes (40); free one ends of the springs (60) are connected to the spring seating channel (47) on the vanes (40) and the other ends thereof rest against the lugs (17); circular cross sectioned pins (70) are fitted into the hole groups (18,18'18") and one ends thereof rest against inside the holes (18") and other free ends thereof remain within the holes (18).
2. A nozzle-vane system (1 ) for 122-mm rockets according to the claim 1 , wherein the nozzle (10) comprises an inlet flange (12) and an outlet flange (13) which are located on both ends of its body (1 1 ) and project from edge to outside, an inner conic surface (14) which advances towards the middle of the body (11 ) by narrowing with an angle of 13.2° from a large diameter towards the inside of the body (11 ) from where the inlet flange (12) is located, an inner middle surface (15) which starts with a sharp diameter expansion from the interface (21 ) where the inner conic surface (14) is ended and advances towards the outlet flange (13) without any conicity, an inner outlet surface (16) which also starts with a sharp diameter expansion from the interface (22) where the inner middle surface (15) is ended and expands towards the outside at the lower side of the outlet flange (13) without any conicity.
3. A nozzle-vane system (1 ) for 122-mm rockets according to the claim 1 , wherein hole group (18,18', 18") comprises a longitudinal hole (18) on the inlet flange (12), of which axes cross with hole axis (24) that forms an angle of 0,8°with the longitudinal axis (23) of the nozzle (10), a longitudinal hole (18') which is located on the lug (17), and a blind hole (18") which is located on the outlet flange (13).
4. A hole group (18, 18', 18") according to the claim 3, wherein it is composed of four holes wherein each stands with an equal angle to one another on the body (11 ) of nozzle (10).
5. A nozzle-vane system (1 ) for 122-mm rockets according to the claim 1 , wherein vane front guides (19) are each located where the hole (18) on the inlet flange (12) lies, and structured in the form of a projection extending towards the outlet such that they are in parallel with the longitudinal axis (23), and ends thereof are rounded.
6. A nozzle-vane system (1 ) for 122-mm rockets according to the claim 1 , wherein vane rear guides (20) are located on the lugs (17), have the similar structure as the vane front guides (19) and stand as extending towards the outlet.
7. A nozzle-vane system (1 ) for 122-mm rockets according to the claim 1 , wherein the nozzle (10) comprises the channels (25) which are located around the outlet flange (13) and into which vane holding clamps are placed.
8. A nozzle-vane system (1 ) for 122-mm rockets according to the claim 1 , wherein the vane (40) comprises vane rear angles (42, 42') of 7° which are on the lower and upper surfaces at the rear side of the vane body (41 ) which is at a thickness of a thin meat, in a parabolic form or circularly arched.
9. A nozzle-vane system (1 ) for 122-mm rockets according to the claim 1 , wherein the vane (40) comprises vane side angles (43,43') of 5,5 ° which are on the lower and upper surfaces at the side of the vane body (41 ) which is at a thickness of a thin meat, in a parabolic form or circularly arched.
10. A nozzle-vane system (1 ) for 122-mm rockets according to the claim 1 , wherein it comprises two pin seating slots (44, 44') which are located on the other side and in the front and rear of the said body (41 ) and formed as circular sectioned with the expansion of the body (41 ) section.
1 1 . Pin seating slots (44, 44') according to the claim 10, wherein a pin hole (45) passes therethrough.
12. Pin seating slots (44,44') according to the claim 10, wherein it comprises vane channels (46, 46') which are located on the front side of the slots (44, 44'), into which vane front and rear guides (19, 20) on the nozzle (10) can seat, and of which inside is rounded and both sides are open.
13. A nozzle-vane system (1 ) for 122-mm rockets according to the claim 1 , wherein the vane (40) comprises a spring seating channel (47) which is just at the back of the pin seating slot (44') on the vane body (41 ) and recesses inwards.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| TR2005/02759A TR200502759A2 (en) | 2005-07-14 | 2005-07-14 | 122 mm. nozzle-aileron system for diameter rocket. |
| TR2005/02759 | 2005-07-14 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| WO2007007213A1 true WO2007007213A1 (en) | 2007-01-18 |
Family
ID=36693503
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/IB2006/050950 WO2007007213A1 (en) | 2005-07-14 | 2006-03-29 | A nozzle-vane system for a 122-mm diameter rocket |
Country Status (2)
| Country | Link |
|---|---|
| TR (2) | TR200502759A2 (en) |
| WO (1) | WO2007007213A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109238040A (en) * | 2018-07-24 | 2019-01-18 | 湖北泰和电气有限公司 | Empennage folding device, micro missile and empennage method for folding |
| CN112964138A (en) * | 2021-01-28 | 2021-06-15 | 陕西中天火箭技术股份有限公司 | Rotary folding tail wing of small-caliber rocket |
| CN114348237A (en) * | 2021-12-31 | 2022-04-15 | 洛阳瑞极光电科技有限公司 | Closing and locking mechanism for ejection port of folding wing surface of small aircraft |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4203569A (en) * | 1977-10-17 | 1980-05-20 | Bei Electronics, Inc. | Fin and nozzle unit for a free-flight rocket |
| US5390605A (en) * | 1992-08-11 | 1995-02-21 | Societe Nationale Des Poudres Et Explosifs | Stabilized and propelled decoy, emitting in the infra-red |
| RU2183817C1 (en) * | 2000-10-23 | 2002-06-20 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Guided missile |
-
2005
- 2005-07-14 TR TR2005/02759A patent/TR200502759A2/en unknown
-
2006
- 2006-03-29 WO PCT/IB2006/050950 patent/WO2007007213A1/en active Application Filing
- 2006-03-29 TR TR2008/00231T patent/TR200800231T2/en unknown
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4203569A (en) * | 1977-10-17 | 1980-05-20 | Bei Electronics, Inc. | Fin and nozzle unit for a free-flight rocket |
| US5390605A (en) * | 1992-08-11 | 1995-02-21 | Societe Nationale Des Poudres Et Explosifs | Stabilized and propelled decoy, emitting in the infra-red |
| RU2183817C1 (en) * | 2000-10-23 | 2002-06-20 | Государственное унитарное предприятие "Конструкторское бюро приборостроения" | Guided missile |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109238040A (en) * | 2018-07-24 | 2019-01-18 | 湖北泰和电气有限公司 | Empennage folding device, micro missile and empennage method for folding |
| CN112964138A (en) * | 2021-01-28 | 2021-06-15 | 陕西中天火箭技术股份有限公司 | Rotary folding tail wing of small-caliber rocket |
| CN114348237A (en) * | 2021-12-31 | 2022-04-15 | 洛阳瑞极光电科技有限公司 | Closing and locking mechanism for ejection port of folding wing surface of small aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| TR200502759A2 (en) | 2007-03-21 |
| TR200800231T2 (en) | 2008-02-21 |
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