GB2238857A - Device for the obturation of a nozzle for a gas generator of a flying projectile - Google Patents
Device for the obturation of a nozzle for a gas generator of a flying projectile Download PDFInfo
- Publication number
- GB2238857A GB2238857A GB9026535A GB9026535A GB2238857A GB 2238857 A GB2238857 A GB 2238857A GB 9026535 A GB9026535 A GB 9026535A GB 9026535 A GB9026535 A GB 9026535A GB 2238857 A GB2238857 A GB 2238857A
- Authority
- GB
- United Kingdom
- Prior art keywords
- gas generator
- plug
- nozzle
- projectile
- combustion
- 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.)
- Withdrawn
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 21
- 230000000694 effects Effects 0.000 claims abstract description 8
- 239000007789 gas Substances 0.000 claims description 24
- 239000000843 powder Substances 0.000 claims description 2
- 239000004449 solid propellant Substances 0.000 claims description 2
- 230000007659 motor function Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000001960 triggered effect Effects 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
- F02K9/76—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with another rocket-engine plant; Multistage rocket-engine plants
-
- 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
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Chemical & Material Sciences (AREA)
- Fluid Mechanics (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Slot Machines And Peripheral Devices (AREA)
- Devices For Medical Bathing And Washing (AREA)
- Portable Nailing Machines And Staplers (AREA)
- Plasma Technology (AREA)
Abstract
The invention provides the storage of a quantity of energy at the end of combustion of a gas generator equipping, for example, a flying projectile. This energy, which is not required for the motor function of the projectile, may permit, for example, a self-ejection of the compartment containing the gas generator. To achieve this, the invention relates to a device for the obturation of at least one opening of a gas generator comprising a plug (10) and a system (19, 21) for fastening the plug to the gas generator. In the course of the combustion of the product contained within the gas generator, the fastening system is released; this permits the plug (10), which is positioned close to the opening, to move under the effect of the reduced pressure created at the location of the opening by the combustion of the product, and thus to come to obturate the opening. <IMAGE>
Description
DEVICE FOR THE OBTURATION OF A NOZZLE FOR A GAS GENERATOR
OF A FLYING PROJECTILE
The invention relates to a device for the automatic obturation of at least one nozzle of a gas generator equipping a flying projectile. It relates, more particularly, to a propulsion unit of a flying projectile which must be ejected after an active propulsion phase.
Certain flying projectiles, for example missiles, self-propelled rockets or similar projectiles, which are fired by gun effect, comprise various modules (propulsion unit, parachute, military payload, etc...) each acting, during a specified period, on the trajectory of the flying projectile. In the course of this trajectory, certain modules must be ejected in order, on the one hand, to permit the utilisation of the other modules and, on the other hand, to improve the performance levels of said projectile, especially by a reduction of mass.
Ejection systems are known, permitting the separation of modules contained within a flying projectile; these ejection systems, which are composed, for example, of spring elements, which are triggered at a predetermined instant, permit the jettisoning, for example, of a propulsion unit when the latter is at the end of its operation. Other systems make use, for example, of a gas generator which, when it is ignited, transmits gases to an actuator chamber. As the pressure in the actuator chamber increases and, on the other hand, the chamber is previously embrittled at one or more locations, the chamber behaves as a piston which permits the ejection of the module under consideration, in our case a propulsion unit.This system is costly and difficult to place in position, as it requires on the one hand special arrangements within the projectile, especially with regard to the gas ducts of the gas generator leading to the actuator chamber and the electrical supply wiring and on the other hand, a large available space within the projectile.
The object of the invention is to remedy the aforementioned disadvantages by providing a device for the obturation of at least one nozzle of a gas generator permitting the storage of the gases at the end of combustion in order to facilitate, for example, the selfejection of the propulsion unit equipping the projectile, the performance levels of which are improved when its mass is reduced.
The subject of the invention is a device for the obturation of a nozzle for a gas generator of a flying projectile, the generator containing a product which, under the effect of a combustion, liberates gases which are ejected through at least one opening, wherein the device comprises a plug and a system for fastening the plug to the propulsion unit, such that the combustion of the product releases the fastening system, the plug moving under the effect of a reduced pressure created at the location of the nozzle by the combustion of the product, in order to obturate the nozzle.
Further features and advantages of the invention will become evident on reading the detailed description hereinbelow, which is given with reference to the accompanying drawings, in which:
- Figure 1 shows a view of a flying projectile having a longitudinal axis XX', this flying projectile being equipped with various modules;
- Figure 2 shows a propulsion unit of the projectile of Figure 1, equipped with an obturating device in which the invention is embodied;
- Figure 3 shows a propulsion unit of the projectile of Figure 1, equipped, with another embodiment of an obturating device in which the invention is embodied.
Figure 1 represents the diagram of a flying projectile 1 equipped with an automatic obturation device in which the invention is eddodied for a proOO1sion unit 2, this device not being visible in Figure 1. The projectile 1 comprises a certain number of modules, a part of which is shown in Figure 1. The projectile 1 is equipped, for example, with a propulsion unit 2 positioned at the rear of the projectile, with a pressure chamber 3 placed between the propulsion unit 2 and a parachute 4 serving, for example, as a braking device when the flying projectile encounters the ground by virtue of a homing head (not shown) and with a front part 5 containing, inter alia, a military payload (not shown).
After firing of the projectile 1, for example, from a launch site, wings (not shown) at the periphery of the projectile are unfolded; some are positioned, for example, at the rear of the projectile in order to ensure the stability of the latter; others are positioned at the centre of the projectile in order to permit the piloting of the latter. The wings having passed from the folded position along the longitudinal axis of the projectile to the unfolded position in which the profile of the wing is parallel to the longitudinal axis of the projectile, the propulsion unit, after a predetermined delay, is ignited to increase the range of the projectile.
Figure 2 shows the diagram of a propulsion unit 2 of the projectile 1 equipped with a device in which the invention is exdied. The propulsion unit 2 which is delimited, for example, by a casing 6 possesses, for example, at least one nozzle 7 which is positioned, for example, on the rear face 8 of the propulsion unit 2. The propulsion unit 2 contains a product 9 which, under the effect of a combustion, liberates gases which are ejected through the nozzle 7 to give the required thrust to the projectile in order to increase its range. The product is, for example, a solid propellant; it may likewise be a powder.The propulsion unit 2 comprises a device for the obturation of the nozzle which is described by way of an illustrative embodiment; this device is placed, for example, in the product 9 and comprises a plug 10 positioned, for example, in the vicinity of the neck 11 of the nozzle. The plug necessarily has a diameter greater than the diameter of the nozzle in order to ensure a complete obturation. The shape of this plug is, for example, conical, so as to be matched to the shape of the nozzle. This plug 10 is fixed, for example, on a first end 12 of an arm 13 parallel to an axis XX' which is the longitudinal axis of the projectile 1.A second end 14 of the arm 13 comprises a guidance system and a system for fastening in the product permitting the retention of the assembly composed of the plug and of the arm in the position shown in Figure 2 during a combustion phase; this combustion phase does not correspond to the complete combustion of the product contained within the propulsion unit, but it corresponds to the propulsion phase of the projectile, permitting the imparting to said projectile of a maximum range. The second end 14 of the arm 13 is connected to the guidance system composed, for example, of a solid cylinder 15 within which there is machined a cavity 16 which permits an insertion of the assembly into a shaft 17 positioned on the front part 18 of the propulsion unit 2. The cylinder 15 comprises, for example, an escapement 19 serving as a system for fastening within the product 9.This escapement 19 is placed, for example, at the periphery of the cylinder 15. The cross-section of this escapement 19 is determined in such a manner that the fastening system as defined is released as soon as the combustion front has reached the escapement. This step is represented in broken lines in Figure 2. The location of the fastening system within the product 9 is determined on the one hand as a function of the combustion volume required for the propulsion of the projectile in order to impart to it an optimal range and on the other hand as a function of the minimum combustion volume to ensure the self-ejection of the gas generator.
The plug 10, which is placed in the vicinity of the neck 11 of the nozzle 7, being subjected to a slight reduced pressure, is drawn towards the neck 11 of the nozzle 7, entraining with it the assembly which is fixed to it. This translation of the assembly permitting the obturation of the neck 11 of the nozzle 7 takes place parallel to the longitudinal axis XX' of the projectile.
In fact, the shaft 17 inserted into the cylinder 15 ensures the guidance of the assembly of the device permitting the assurance of the path of the latter within the propulsion unit 2. It is essential that the fastening system remains fixed in the course of firing of the projectile in order to avoid certain problems which may interfere with the correct operation of said projectile.
The cross-section of the various components of the device in which the invention is embodied is adapted to facilitate construction. The plug 10, the arm 13, the cylinder 15, the escapement 19 and the shaft 17 are made, for example, from tungsten or from carbon-containing composite, that is to say from materials withstanding the erosion and the thermal stress of the combustion gases.
After the obturation of the neck 11 of the nozzle 7, the combustion of the product contained within the propulsion unit 2 continues, and the pressure within the latter increases. In order to avoid a pressure increase which is too large, within the propulsion unit 2, which would involve for example an explosion, caps 20, for example numbering two in Figure 1, are positioned on the front face 18 of the propulsion unit 2 connected to the pressure chamber 3. These caps which are made, for example, of alumina, have a specified cross-section which, under the action of a certain pressure contained within the propulsion unit, permits the escape of gases, for example, within the pressure chamber 3. As this pressure chamber 3 is fed by caps which are embrittled beforehand at various locations, the chamber accordingly behaves as a piston which ensures the ejection of the propulsion unit.
As a result of this, the propulsion unit itself permits its ejection from the projectile, this taking place in a manner more rapid and more reliable and independent of the combustion time of the propellant which is generally dependent upon the temperature. In fact, in the majority of the cases cited, the ejection of the propulsion unit is followed by the deployment of a braking system of the parachute type which is expelled in the longitudinal axis of the projectile where a homing head has detected the ground in such a manner as to incline, for example, the direction of the projectile by an angle close to 45.. In order to prevent any damage to the braking system by the propulsion unit when it has acquired a certain speed, it is necessary to increase the time separating the ejection of the propulsion unit and the deployment of the braking system.The use of the end of the combustion of the product contained within the propulsion unit which is not necessary to increase the range of the projectile favours a more rapid ejection, while reducing the risks and maintaining the performance levels of the projectile.
Other obturation devices comprising a plug and a fastening system may be constructed. To do this, it is necessary to modify; for example, the shape, the size, the linking mechanisms and the fixings of the components making up the device. In the case of a fastening system, it is possible to use, for example, at least one wire 21 shown in Figure 3, which become detached from fixing points 22 under the effect of the combustion; in the example described, two wires 21 are used. As these wires 21 are attached, for example, at one of their ends 23 to the casing 6 of the propulsion unit and at the other end 24 to the cylinder 15, when the combustion front arrives at the location of the wire 21 the latter is consumed and thus releases the obturating device which can slide parallel to the longitudinal axis XX' of the projectile and thus come to close the neck 11 of the nozzle.
Accordingly, the invention permits the storage of a quantity of gas in a gas generator and more particularly in a propulsion unit. These gases may serve, for example, for a self-ejection of said propulsion unit, but may be used for other purposes, for example the deployment of a braking system.
Claims (10)
1. A device for the obturation of a nozzle for a gas generator of a flying projectile , the generator containing a product which, under the effect of a combustion, liberates gases which are ejected through at least one nozzle , wherein the device comprises a plug and a system for fastening the plug to the gas generator, such that the combustion of the product releases the fastening system , the plug
moving under the effect of a reduced pressure created at the location of the nozzle by the escape of the gases, in order to obturate the nozzle
2. An obturating device according to Claim 1, wherein the fastening system is an escapement
positioned on a cylinder connected to the plug
by an arm , and it is placed in the product
3.An obturating device according to Claim 2, wherein the cylinder comprises a cavity within which a shaft is inserted to ensure the guidance of the plug towards the nozzle
4. An obturating device according to Claim 1, therein the product contained within the gas generator is a solid propellant.
5. An obturating device according to Claim 1, wherein the product contained within the gas generator is a powder.
6. An obturating device according to Claim 1, wherein the gas generator is a propulsion unit.
7. An obturating device according to Claim 1, wherein the fastening system comprises at least one wire fixed at a first end at a fixing point
to a casing of the gas generator and at a second end to a cylinder connected to the plug by an arm
8. An obturating device according to Claim 1, wherein the plug has a conical shape.
9. An obturating device according to Claim 1, wherein the plug is positioned in the vicinity of a neck of the nozzle.
10. A device for obturating a nozzle for a gas generator of a flying projectile substantially as described hereinbefore with reference to the accompanying drawings and as shown in Figure 2 or in Figure 3 of those drawings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR8916263A FR2655723B1 (en) | 1989-12-08 | 1989-12-08 | DEVICE FOR SEALING A NOZZLE FOR A GAS GENERATOR EQUIPPED WITH A FLYING MACHINE. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB9026535D0 GB9026535D0 (en) | 1991-01-23 |
| GB2238857A true GB2238857A (en) | 1991-06-12 |
Family
ID=9388298
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9026535A Withdrawn GB2238857A (en) | 1989-12-08 | 1990-12-06 | Device for the obturation of a nozzle for a gas generator of a flying projectile |
Country Status (3)
| Country | Link |
|---|---|
| FR (1) | FR2655723B1 (en) |
| GB (1) | GB2238857A (en) |
| IT (1) | IT1241020B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5435128A (en) * | 1993-11-15 | 1995-07-25 | Thiokol Corporation | Pyrotechnically driven nozzle restrictor |
| RU2461729C1 (en) * | 2011-08-02 | 2012-09-20 | Николай Евгеньевич Староверов | Self-adjusted two-mode nozzle (versions) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1516072A (en) * | 1976-02-12 | 1978-06-28 | Messerschmitt Boelkow Blohm | Projectiles having a pressure gas accumulator |
| GB1538192A (en) * | 1968-05-18 | 1979-01-10 | Karlsruhe Augsburg Iweka | Cartridge-type missile |
| WO1979000658A1 (en) * | 1978-02-23 | 1979-09-06 | S Landstroem | An arrangement for launching interference material |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2613497A (en) * | 1947-04-01 | 1952-10-14 | Macdonald Gilmour Craig | Controllable rocket thrust device |
| US3230704A (en) * | 1961-10-30 | 1966-01-25 | Thiokol Chemical Corp | Rocket engine |
| US3329089A (en) * | 1964-12-24 | 1967-07-04 | Herbert L Harrison | Retention-release mechanism for reaction motors and rocket interstages |
| US3691770A (en) * | 1966-12-02 | 1972-09-19 | Us Navy | Thrust control means for a solid propellant rocket motor |
| DE2320076A1 (en) * | 1973-04-19 | 1974-11-14 | Norbert Mieseler | ADJUSTABLE ROCKET MOTOR |
| GB2156290B (en) * | 1984-03-27 | 1988-06-02 | British Aerospace | Rockets and rocket motors |
-
1989
- 1989-12-08 FR FR8916263A patent/FR2655723B1/en not_active Expired - Fee Related
-
1990
- 1990-12-06 GB GB9026535A patent/GB2238857A/en not_active Withdrawn
- 1990-12-07 IT IT67979A patent/IT1241020B/en active IP Right Grant
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1538192A (en) * | 1968-05-18 | 1979-01-10 | Karlsruhe Augsburg Iweka | Cartridge-type missile |
| GB1516072A (en) * | 1976-02-12 | 1978-06-28 | Messerschmitt Boelkow Blohm | Projectiles having a pressure gas accumulator |
| WO1979000658A1 (en) * | 1978-02-23 | 1979-09-06 | S Landstroem | An arrangement for launching interference material |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5435128A (en) * | 1993-11-15 | 1995-07-25 | Thiokol Corporation | Pyrotechnically driven nozzle restrictor |
| RU2461729C1 (en) * | 2011-08-02 | 2012-09-20 | Николай Евгеньевич Староверов | Self-adjusted two-mode nozzle (versions) |
Also Published As
| Publication number | Publication date |
|---|---|
| IT1241020B (en) | 1993-12-27 |
| IT9067979A0 (en) | 1990-12-07 |
| FR2655723A1 (en) | 1991-06-14 |
| FR2655723B1 (en) | 1993-01-22 |
| GB9026535D0 (en) | 1991-01-23 |
| IT9067979A1 (en) | 1991-06-09 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |