DE1578225A1 - Spindle-shaped supersonic projectile with additional drive through rear heating - Google Patents
Spindle-shaped supersonic projectile with additional drive through rear heatingInfo
- Publication number
- DE1578225A1 DE1578225A1 DE19671578225 DE1578225A DE1578225A1 DE 1578225 A1 DE1578225 A1 DE 1578225A1 DE 19671578225 DE19671578225 DE 19671578225 DE 1578225 A DE1578225 A DE 1578225A DE 1578225 A1 DE1578225 A1 DE 1578225A1
- Authority
- DE
- Germany
- Prior art keywords
- spindle
- projectile
- shaped
- contour
- additional drive
- 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.)
- Pending
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
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/38—Range-increasing arrangements
- F42B10/42—Streamlined projectiles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
-
- 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
- F42B10/32—Range-reducing or range-increasing arrangements; Fall-retarding means
- F42B10/38—Range-increasing arrangements
- F42B10/40—Range-increasing arrangements with combustion of a slow-burning charge, e.g. fumers, base-bleed projectiles
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
- Carbon And Carbon Compounds (AREA)
Description
Societe financidre ά' ExpaüSIön' ComtiTercialeSociete financidre ά 'ExpaüSIön' ComtiTerciale
et Industrielle S.A. "SFINDEX", Samen , Schweiz.et Industrielle S.A. "SFINDEX", Sami, Switzerland.
PatentanwaltPatent attorney
Dipl.-Ing. Kurt HiekeDipl.-Ing. Kurt Hieke
8 München 23
Leopoldstraße 2078 Munich 23
Leopoldstrasse 207
Spindelförmiges Ueberschallgeschoss mit Zusatzantrieb durch HeckaufheizungSpindle-shaped supersonic projectile with additional drive through rear heating
Es sind Ueberschallgeschosse bekannt, die einen vorn und hinten spitzen, spindelförmigen Körper aufweisen und durch Verbrennung eines hinreichend rasch verbrennenden Treibstoffes im Bereich der dicksten Stelle oder in der Anström- ■ richtung gesehen, hinter derselben einen Zusatzantrieb erhalten. Bei diesem, als Heckaufheizung bekannten Zusatzantrieb besteht die Schwierigkeit in der Zündung des Treibstoffes. Ueblicherweise wird als Treibstoff eine Flüssigkeit, ein Flüssiggas oder ein hochkomprimiertes Gas benutzt, welches an oder hinter der dicksten Stelle des Spindelkörpers aus am Umfang verteilten Oeffnungen austritt und mit Hilfe des Sauerstoffes der Luft verbrennt. Eine solche Heckaufheizung ist erst wirkungsvoll und wirtschaftlich, wenn die Anströmgeschwindigkeit, also die Fluggeschwindigkeit, mindestens Mach 3 beträgt· Die Zündgeschwindigkeit des Treibstoffes muss daher entsprechend hoch sein, damitThere are known supersonic projectiles that have a front and have pointed, spindle-shaped bodies at the back and by burning a fuel that burns sufficiently quickly in the area of the thickest point or in the direction of flow ■ received an additional drive behind the same. With this additional drive known as rear heating the difficulty is in igniting the fuel. Usually a liquid is used as fuel, a liquid gas or a highly compressed gas is used, which is at or behind the thickest point of the spindle body emerges from openings distributed around the circumference and burns with the help of the oxygen in the air. Such Rear heating is only effective and economical if the approach velocity, i.e. the airspeed, is at least Mach 3 · The ignition velocity the fuel must therefore be correspondingly high so that
109851/0282109851/0282
die Flamme in der Ueberschallströmung nicht abreisst. Es gibt Brennstoffe, die diese Bedingung erfüllen, z.B. Aluminiumborhydrid. Solche Brennstoffe sind aber an der Luft selbstentzündlich, weshalb ihre Handhabung und technische Nutzung schwierig ist. Eine Unterbringung in z.B. aus einem Eohr abzufeuernden Geschossen scheint vorläufig noch nicht realisierbar zu sein.the flame does not tear off in the supersonic flow. There are fuels that meet this condition, e.g. Aluminum borohydride. Such fuels are self-igniting in the air, which is why their handling and technical Use is difficult. An accommodation in, for example, projectiles to be fired from an Eohr still seems to be for the time being not to be feasible.
Die Erfindung will mit technischen Mitteln am Geschosskörper auch langsam zündende und weniger gefährliche Brennstoffe in der Ueberschallströmung zum kontinuierlichen Brennen bringen und damit für den Zusatzantrieb von Ueberschallgeschossen verwendbar machen,.The invention also aims to use technical means on the projectile body to ignite slowly and less dangerous fuels Bring it to continuous burning in the supersonic flow and thus for the additional drive of supersonic projectiles make usable.
Die Erfindung betrifft ein spindelförmiges Ueberschallgeschoss mit Zusatzantrieb durch Heckaufheizung mit als Minimalkörper geformter Kontur und Treibstoff-Austrittsöffnungen im Bereich der dicksten Stelle, welches dadurch gekennzeichnet ist, dass der Spindelkörper hinter den Treibstoff-Austrittsöffnungen eine konische Erweiterung aufweist, die eine zweite schwächere Stosswelle erzeugt. Diese zweite Stosswelle unterhält in wirkungsvoller Weise die Verbrennung üblicher Treibstoffe, z.B. von Wasserstoff, bei einer Luftströmung mit einer Ueberschallgeschwindigkeit.The invention relates to a spindle-shaped supersonic projectile with additional drive through rear heating with as Minimal body shaped contour and fuel outlet openings in the area of the thickest point, which thereby is characterized in that the spindle body has a conical widening behind the fuel outlet openings, which generates a second, weaker shock wave. This second shock wave effectively maintains the Combustion of common fuels, e.g. of hydrogen, with an air flow with a supersonic speed.
Die Grosse dieser zweiten Stosswelle ist abhängig vom Winkel und Durchmesser des Konus. Zweckmässig setzt sich stromab von der Aussenkante der konischen Erweiterung die Geschosskontur wiederum als Minimalkörper oder in einer für den Verbrennungsschub günstigen Kontur ohne Absatz fort.The size of this second shock wave depends on the Angle and diameter of the cone. Appropriately downstream of the outer edge of the conical enlargement is the The projectile contour continues as a minimal body or in a contour that is favorable for the combustion thrust without a shoulder.
109851/0282109851/0282
_ 3 —_ 3 -
Ein Ausführungsbeispiel der Erfindung wird anhand der Zeichnung näher erläutert. In der Zeichnung ist der Umriss eines Ueberschallgeschosses mit einem vorn und hinten spitzen, spindelförmigen Geschosskörper dargestellt. Das Geschoss erzeugt die, Kopfwelle 1 und hat im Vorderteil eine als Minimalkörper geformte Kontur. Stromab von seiner Spitze hat es im Bereich der dicksten Stelle am Umfang gleichmässig verteilte Treibstoff-Austrittsöffnungen 2. Als Bereich der dicksten Stelle gilt die Zone, wo die Tangenten an die Mantellinie mindestens annähernd parallel zur Geschossachse verlaufen. Hinter den Austrittsöffnungen 2 hat der Geschossmantel eine konische Erweiterung 3» welche eine kleinere zweite Stosswelle 4 erzeugt. Der Geschosshinterteil 5 setzt sich mit seiner dicksten Stelle ohne Absatz direkt an die Aussenkante der konischen Erweiterung 3 an· Der Hinterteil ist ebenfalls als Minimalkörper ausgebildet oder wird in seiner Kontur 6 dem Verbrennungsvorgang so angepasst, dass für Schub und Stabilisierung das erreichare Optimum erzielt wird.An embodiment of the invention is based on the Drawing explained in more detail. In the drawing is the outline of a supersonic projectile with a front and a rear pointed, spindle-shaped projectile body shown. The bullet creates the head wave 1 and has a in the front part Contour shaped as a minimal body. Downstream from its tip, it is uniform in the area of the thickest point on the circumference distributed fuel outlet openings 2. The area of the thickest point is the zone where the tangents to the Surface line at least approximately parallel to the floor axis get lost. Behind the outlet openings 2, the projectile jacket has a conical enlargement 3 »which is a smaller one second shock wave 4 generated. The bullet rear part 5 sets with its thickest point without a shoulder directly on the outer edge of the conical extension 3 · The rear part is also designed as a minimal body or its contour 6 is adapted to the combustion process so that the achievable optimum is achieved for thrust and stabilization.
Die konische Erweiterung kann durch entsprechende Bemessung des Winkels und des äusseren Durchmessers leicht dem jeweiligen Bedürfnis angepasst werden, um eine für die Dauerzündung des geweiligen Treibstoffes hinreichende zweite Stosswelle zu erzeugen, die nicht mehr Widerstand hervorruft als unumgänglich notwendig ist. Beispielsweise kann xt einer Konusfläche von 28° bei einer Luftströmung von Mach 3 Wasserstoff zum kontinuierlichen Brennen gebracht werden. ORIGIN^-The conical widening can easily be adapted to the respective Need to be adapted to a second sufficient for the continuous ignition of the propellant To generate a shock wave that does not cause more resistance than is absolutely necessary. For example, can xt a cone surface of 28 ° with an air flow of Mach 3 hydrogen brought to continuous burning will. ORIGIN ^ -
109851/0282109851/0282
Claims (2)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH1813266A CH477668A (en) | 1966-12-15 | 1966-12-15 | Spindle-shaped supersonic projectile with additional drive through rear heating |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE1578225A1 true DE1578225A1 (en) | 1971-12-16 |
Family
ID=4430706
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DE19671578225 Pending DE1578225A1 (en) | 1966-12-15 | 1967-12-14 | Spindle-shaped supersonic projectile with additional drive through rear heating |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US3545212A (en) |
| CH (1) | CH477668A (en) |
| DE (1) | DE1578225A1 (en) |
| FR (1) | FR1552302A (en) |
| GB (1) | GB1173098A (en) |
| SE (1) | SE315533B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4170875A (en) * | 1976-06-10 | 1979-10-16 | The United States Of America As Represented By The Secretary Of The Air Force | Caseless rocket design |
| GB9001892D0 (en) * | 1990-01-26 | 1990-08-08 | Jack Colin | A technique for hypervelocity drag reduction by atmospheric heating |
| RU2671452C2 (en) * | 2016-02-24 | 2018-10-31 | Ринад Алиманович Мухамедзянов | Hypersonic aircraft |
| US10928168B2 (en) * | 2017-11-10 | 2021-02-23 | Curtis E. Graber | Noise control system and method for small caliber ammunition |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3008669A (en) * | 1955-01-05 | 1961-11-14 | Frank I Tanczos | Ramjet missile |
| US3074668A (en) * | 1958-12-10 | 1963-01-22 | Snecma | Burner for hot fuel |
| US3363421A (en) * | 1963-01-30 | 1968-01-16 | Gen Applied Science Lab Inc | Supersonic engine |
-
1966
- 1966-12-15 CH CH1813266A patent/CH477668A/en not_active IP Right Cessation
-
1967
- 1967-12-07 SE SE16827/67A patent/SE315533B/xx unknown
- 1967-12-14 GB GB56887/67A patent/GB1173098A/en not_active Expired
- 1967-12-14 DE DE19671578225 patent/DE1578225A1/en active Pending
- 1967-12-14 US US690539A patent/US3545212A/en not_active Expired - Lifetime
- 1967-12-15 FR FR1552302D patent/FR1552302A/fr not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| GB1173098A (en) | 1969-12-03 |
| FR1552302A (en) | 1969-01-03 |
| CH477668A (en) | 1969-08-31 |
| SE315533B (en) | 1969-09-29 |
| US3545212A (en) | 1970-12-08 |
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