GB2335711A - Lateral thrust generation by decomposition - Google Patents
Lateral thrust generation by decomposition Download PDFInfo
- Publication number
- GB2335711A GB2335711A GB9906729A GB9906729A GB2335711A GB 2335711 A GB2335711 A GB 2335711A GB 9906729 A GB9906729 A GB 9906729A GB 9906729 A GB9906729 A GB 9906729A GB 2335711 A GB2335711 A GB 2335711A
- Authority
- GB
- United Kingdom
- Prior art keywords
- propellant
- decomposition
- decomposition chamber
- lateral thrust
- chamber
- 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.)
- Granted
Links
- 238000000354 decomposition reaction Methods 0.000 title claims abstract description 34
- 239000003380 propellant Substances 0.000 claims abstract description 36
- 239000007789 gas Substances 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 claims abstract description 14
- 238000007493 shaping process Methods 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims description 2
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 abstract description 7
- 239000012528 membrane Substances 0.000 abstract description 3
- 229910052751 metal Inorganic materials 0.000 abstract description 2
- 239000002184 metal Substances 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 description 10
- 238000010891 electric arc Methods 0.000 description 4
- 239000004449 solid propellant Substances 0.000 description 3
- QGZKDVFQNNGYKY-UHFFFAOYSA-N Ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000004913 activation Effects 0.000 description 1
- 229910021529 ammonia Inorganic materials 0.000 description 1
- 238000003421 catalytic decomposition reaction Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- PXBRQCKWGAHEHS-UHFFFAOYSA-N dichlorodifluoromethane Chemical compound FC(F)(Cl)Cl PXBRQCKWGAHEHS-UHFFFAOYSA-N 0.000 description 1
- 235000019404 dichlorodifluoromethane Nutrition 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 125000004435 hydrogen atom Chemical class [H]* 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000005979 thermal decomposition reaction Methods 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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/68—Decomposition chambers
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Air Bags (AREA)
- Plasma Technology (AREA)
- Testing Of Engines (AREA)
Abstract
A process for generating lateral thrust in a projectile by means of a propulsion unit, which has a decomposition chamber 1 and a supersonic nozzle 2 and uses a monergol propellant such as hydrazine, comprises the introduction of the propellant into the decomposition chamber 1 by electromagnetic valve 4 through tangential inlet 3 at high speed, so that, a propellant film 5 of defined thickness is produced on the wall of the chamber 1 and then decomposed by pyrotechnic heat source 7 arranged in the wall of the chamber 1. Pressurised hot gases produced by decomposition cause non-return valve (8, fig 2) to close inlet 3. Plural propulsion units may be connected to a common supply vessel (10, fig 3) pressurised by a metal membrane (11, fig 3).
Description
1 Process for crenerating lateral thrust 2335711 The present invention
relates to a process for generating lateral thrust, especially in a projectile, in which, in a propulsion unit which is arranged transversely relative to the longitudinal axis of the projectile and which has a decomposition chamber and a supersonic nozzle, a defined amount of a monergol propellant is introduced and is decomposed by a heat source, thereby to generate a desired lateral thrust of predetermined duration.
A process of this type is used in particular for correcting the position and trajectory of space projectiles; one or more propulsion unit (s), arranged transversely relative to the longitudinal axis of the projectile, can be provided and are ignited individually at predetermined times in order to carry out the desired correction.
Solid fuel propulsion units are often used for trajectory correction, one propulsion unit being necessary for each of the correction pulses which are to be emitted repeatedly, so that a multiplicity of solid fuel propulsion units have to be provided in the projectile, with correspondingly large mass and correspondingly large spatial requirements. For the actual lateral thrust control using a solid fuel gas generator, the flow of gas must be controlled using hot gas valves, for which complex activation devices are necessary.
A propulsion unit for the trajectory correction of space projectiles is known from EP-A 522270 and is composed of a housing in the form of an anode, which is, at the same time, the expansion nozzle, and of a rodshaped, electrically insulated cathode which is held centrally therein. The cathode is arranged in a combustion chamber into which propellant gases are injected, the tip of the cathode being spaced from the narrowed cross-section of the nozzle throat 2 by a small air gap. When there is a flow of gas, an electric arc is ignited between the anode and the cathode, from which electric arc the propellant gases can receive additional thermal energy. A portion of the propellant gases is injected into the combustion chamber via a central drilled hole in the cathode. The cathode tip, opposite the nozzle throat, is formed by an insert of tungsten. The propellant gas is usually a mixture of ammonia, gaseous nitrogen and gaseous hydrogen, which mixture is produced by thermal and/or catalytic decomposition of hydrazine (N2H4) and which, when it enters the combustion chamber, has a temperature of the order of from 500 to 6000C initially and which is heated in the electric arc to temperatures of from 10000 to 150000C before it leaves the expansion nozzle and there generates the desired lateral thrust.
A propulsion unit of this type is subject, in thermal terms, to extraordinarily powerful stresses, in particular in the region of the cathode, owing to the concentration of the electric arc on a comparatively narrow region, in particular in the region of the cathode tip. This concentration of electric current diminishes the service life of this type of propulsion unit.
The use of monergols, for example, hydrazine, as the propellant for a projectile and, in particular, for a satellite, is known from DE-A 25 37 543. In this instance, a monergol is intended to indicate a fluid propellant which, when energy is supplied appropriately, supplies a decomposition gas by means of self-conversion and without addition of another substance, which decomposition gas can, for example, be used to pressurise the propellant.
DE-A 36 16 184 discloses the use of a pyrotechnic gas generator for the guidance of projectiles or final-phase guided missiles, a propellant charge being converted to gas in a combustion chamber, which gas is supplied to 'control nozzles in the event of guidance correction being necessary.
3 It is possible to operate this known gas generator in a manner suitable for control purposes only with constant pressure ratios within the combustion chamber, so that overpressure peaks in particular must be avoided. This can be effected by mechanical overpressure valves which substantially comprise a spring/mass system, but which require a large amount of space so that, in particular in final-phase guided missiles, they can no longer be arranged in the immediate vicinity of the combustion chamber. Furthermore, mechanical overpressure valves, because of the relatively large time constants of the spring/mass system, display poor response characteristics which do not meet practical requirements. The opening and closing characteristics of conventional, mechanical overpressure valves are also affected by excessively high tolerances which preclude their use for precision guidance arrangements. In order to overcome these disadvantages, this prior publication proposes the provision in the combustion chamber of a pressure sensor which is connected, on the output side, to an electronic ci rcuit for the detection of a desired pressure value, which is dependent on the temperature and a predetermined combustion rate of the propellant charge, the provision in the propellant charge of a temperature sensor, which is connected to the electronic circuit, and the fitting of a final control element which, when a pressure is detected in the combustion chamber that exceeds the desired pressure value, opens the combustion chamber in order to divert the pressure peak.
Thus, the present invention can provide a particularly simple and rapidly responsive process for generating lateral thrust in a projectile, using which process a thrust of high pulse density can be generated within a short space of time in a defined direction.
In accordance with one aspect of the present invention, there is provided a process for generating lateral thrust in a projectile, in which, in a propulsion unit which is arranged r 1 4 transversely relative to the longitudinal axis of the projectile and which comprises a decomposition chamber and a supersonic nozzle, a defined amount of a monergol propellant is introduced and is decomposed by a heat source, thereby to generate the desired lateral thrust of predetermined duration, in which process: monergol propellant is introduced, preferably controlled by an electromagnetic valve, into the decomposition chamber substantially tangentially at high speed so that a propellant film is produced on the wall having a thickness which is a function of the shaping of the wall, the rate of introduction and the duration of introduction; the propellant film is decomposed by a pyrotechnic heat source arranged in the wall of the decomposition chamber and near the supersonic nozzle; and hot gases resulting from the decomposition generate a pressure of from 500 to 800 bar in the decomposition chamber and a corresponding thrust in the supersonic nozzle.
The invention is explained below in greater detail, by way of example, with reference to the drawings in which the individual process steps are illustrated with reference to a propulsion unit generating lateral thrust.
In the drawings:
Figure 1 is a section through a controllable lateral thrust propulsion unit; Figure 2 is an enlarged illustration of the propellant inlet to the propulsion unit of Figure 1 and; Figure 3 is a schematic representation of the lateral thrust control unit having four lateral thrust propulsion units.
In the Figures, in which identical components are provided with identical reference symbols, the decomposition chamber of the propulsion unit serving to generate the lateral thrust is designated 1 and the crosssection of the propulsion unit decreases in the direction towards a supersonic nozzle 2 which is fitted therein and the cross-section of the supersonic nozzle 2 increases once more in a conventional manner starting from the point of connection with the decomposition chamber 1.
The reference numeral 3 designates a tangentially arranged propellant inlet, by means of which the propellant, that is, a monergol, is introduced, controlled by an electromagnetic valve 4, tangentially into the decomposition chamber 1. The propellant film resulting from the introduction of the monergol into the decomposition chamber 1 is designated 5 and the surface thereof 6. The thickness of the propellant film 5 in the decomposition chamber 1 is a function of the shaping of the wall of the decomposition chamber 1, the rate of introduction and the duration of introduction of the propellant.
A pyrotechnic heat source which is provided in the wall of the decomposition chamber near the point of connection of the decomposition chamber 1 to the supersonic nozzle 2 is designated 7 and ensures that the monergol introduced into the decomposition chamber 1 is decomposed so that hot gases are generated having a high pressure of from approximately 500 to 800 bar and, when they expand, generate a corresponding large thrust in the supersonic nozzle 2.
The propulsion unit having the decomposition chamber 1 and the supersonic nozzle 2 is arranged perpendicularly relative to the longitudinal axis of the projectile, a defined amount of monergol propellant being introduced by the electromagnetic valve 4 tangentially and at high speed, as already described. The resultant propellant film 5 reaches the pyrotechnic heat source 7, which is accommodated in the decomposition chamber, leading to the beginning of a spontaneous decomposition of the entire propellant present in the decomposition chamber. During the time for which the high pressure is present in the decomposition chamber 1 the 6 propellant inlet 3 is closed by a f luid non-return valve 8, as schematically illustrated in the enlarged representation of the propellant inlet 3 in Figure 2.
As a result, the electromagnetic control valve 4 is subject only to the low pressure necessary for the supply of monergol.
The functioning of the pyrotechnic heat source 7 is continuously maintained from the beginning to the end of the generation of the lateral thrust, whereas the supply of propellant to the decomposition chamber 1 is enabled only when lateral thrust is required.
Figure 3 shows schematically the arrangement of four of the lateral thrust propulsion units in a projectile, which units are connected to a common supply vessel 10 for the monergol propellant. The supply vessel 10 is subdivided into two chambers by a membrane, for example, a metal membrane 11, the first chamber being filled with a pressurising gas 13 which urges the monergol propellant 12, which is arranged in the other chamber, in the direction towards the four lateral thrust propulsion units 1, 1, 1, 1, the connection line between the supply vessel 10 and the individual control valves for the four propulsion units being provided with a pyrovalve 9.
Claims (4)
1. Process for generating lateral thrust in a projectile, in which, in a propulsion unit which is arranged transversely relative to the longitudinal axis of the projectile and which comprises a decomposition chamber and a supersonic nozzle, a defined amount of a monergol propellant is introduced and is decomposed by a heat source, thereby to generate the desired lateral thrust of predetermined duration, in which process:
monergol propellant is introduced, preferably controlled by an electromagnetic valve, into the decomposition chamber substantially tangentially at high speed so that a propellant f ilm is produced on the wall having a thickness which is a function of the shaping of the wall, the rate of introduction and the duration of introduction; the propellant film is decomposed by a pyrotechnic heat source arranged in the wall of the decomposition chamber and near the supersonic nozzle; and hot gases resulting from the decomposition generate a pressure of from 500 to 800 bar in the decomposition chamber and a corresponding thrust in the supersonic nozzle.
2. A process according to claim 1, wherein, during the time for which the said pressure is present in the decomposition chamber and the corresponding thrust in the supersonic nozzle, the inlet aperture for the monergol propellant is closed by a fluid non-return valve.
3. A process according to claim 1 or claim 2, wherein the pyrotechnic heat source generates the heat continuously from the beginning to the end of the decomposition.
4. A process for generating lateral thrust, substantially as hereinbefore described with reference to the accompanying drawings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19813330A DE19813330C2 (en) | 1998-03-26 | 1998-03-26 | Process for generating a transverse thrust |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB9906729D0 GB9906729D0 (en) | 1999-05-19 |
| GB2335711A true GB2335711A (en) | 1999-09-29 |
| GB2335711B GB2335711B (en) | 2000-05-17 |
Family
ID=7862402
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9906729A Expired - Fee Related GB2335711B (en) | 1998-03-26 | 1999-03-23 | Process for generating lateral thrust |
Country Status (3)
| Country | Link |
|---|---|
| DE (1) | DE19813330C2 (en) |
| FR (1) | FR2776716B1 (en) |
| GB (1) | GB2335711B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112901374B (en) * | 2020-12-21 | 2022-02-22 | 中国人民解放军国防科技大学 | Manual flow regulating device |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4203775A1 (en) * | 1992-02-10 | 1993-08-12 | Erno Raumfahrttechnik Gmbh | Hydrazine fuelled propulsion unit with decomposition chamber - has injection bores inclined to lines perpendicular to one or more injector head outer surfaces |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3142541A (en) * | 1961-08-18 | 1964-07-28 | Chandler Evans Corp | Gas generator for rocket propellants |
| DE1776010A1 (en) * | 1968-09-03 | 1971-09-16 | Messerschmitt Boelkow Blohm | Process for conveying liquid fuels for gas generators or rocket combustion chambers, and conveying system for carrying out the process |
| FR2283390A1 (en) * | 1974-08-26 | 1976-03-26 | Centre Nat Etd Spatiales | DEVICE FOR PRESSURIZING A LIQUID MONERGOL IN A TANK FOR THIS PURPOSE |
| US3956885A (en) * | 1974-09-03 | 1976-05-18 | Avco Corporation | Electrothermal reactor |
| GB1534601A (en) * | 1976-07-23 | 1978-12-06 | Secr Defence | Electrothermal gas thrusters |
| DE3616184A1 (en) * | 1985-08-21 | 1987-02-26 | Rheinmetall Gmbh | PRESSURE VALVE FOR A PYROTECHNICAL GAS GENERATOR |
| GB2190729A (en) * | 1986-05-21 | 1987-11-25 | Plessey Co Plc | Solid propellant burn rate control device |
| DE4122756A1 (en) * | 1991-07-10 | 1993-02-11 | Erno Raumfahrttechnik Gmbh | ENGINE FOR SPACING BODIES |
-
1998
- 1998-03-26 DE DE19813330A patent/DE19813330C2/en not_active Expired - Fee Related
-
1999
- 1999-03-23 GB GB9906729A patent/GB2335711B/en not_active Expired - Fee Related
- 1999-03-24 FR FR9903686A patent/FR2776716B1/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4203775A1 (en) * | 1992-02-10 | 1993-08-12 | Erno Raumfahrttechnik Gmbh | Hydrazine fuelled propulsion unit with decomposition chamber - has injection bores inclined to lines perpendicular to one or more injector head outer surfaces |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2776716A1 (en) | 1999-10-01 |
| DE19813330C2 (en) | 2000-04-13 |
| GB2335711B (en) | 2000-05-17 |
| FR2776716B1 (en) | 2002-01-04 |
| GB9906729D0 (en) | 1999-05-19 |
| DE19813330A1 (en) | 1999-09-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4821508A (en) | Pulsed electrothermal thruster | |
| US4821509A (en) | Pulsed electrothermal thruster | |
| US4715261A (en) | Cartridge containing plasma source for accelerating a projectile | |
| US4895062A (en) | Combustion augmented plasma gun | |
| US6216445B1 (en) | Micro pulsed plasma thruster and method of operating same | |
| EP0220556B1 (en) | Combustion augmented plasma amplification system | |
| US5909001A (en) | Method of generating a high pressure gas pulse using fuel and oxidizer that are relatively inert at ambient conditions | |
| US4913029A (en) | Method and apparatus for accelerating a projectile through a capillary passage with injector electrode and cartridge for projectile therefor | |
| US5233903A (en) | Gun with combined operation by chemical propellant and plasma | |
| US5485721A (en) | Arcjet for a space flying body | |
| EP1811163A2 (en) | Gas augmented rocket engine | |
| US5648052A (en) | Liquid monopropellant gas generator | |
| US4967637A (en) | Projectile accelerating device | |
| US5425231A (en) | Gas fed pulsed electric thruster | |
| US20020134767A1 (en) | Plasma torch comprising electrodes separated by an air gap and igniter incorporating same | |
| GB2228296A (en) | Electric arc thruster | |
| GB2335711A (en) | Lateral thrust generation by decomposition | |
| US3533233A (en) | Hot gas generator utilizing a mono-propellant fuel | |
| GB1534601A (en) | Electrothermal gas thrusters | |
| US4765565A (en) | Pressure relief valve arrangement for a pyrotechnic gas generator | |
| US6519928B2 (en) | Process for the production of a transverse thrust in a flying object | |
| US5503058A (en) | Vectored plasma arc device | |
| US5697212A (en) | Rocket propellant tank self-pressurization | |
| Hasegawa et al. | Laser ignition characteristics of GOX/GH2 and GOX/GCH4 propellants | |
| EP0382000B1 (en) | A gun with combined operation by chemical propellant and plasma |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 20070323 |