CH223977A - Missile bullet. - Google Patents
Missile bullet.Info
- Publication number
- CH223977A CH223977A CH223977DA CH223977A CH 223977 A CH223977 A CH 223977A CH 223977D A CH223977D A CH 223977DA CH 223977 A CH223977 A CH 223977A
- Authority
- CH
- Switzerland
- Prior art keywords
- spring
- valve body
- nozzle
- missile
- gases
- Prior art date
Links
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
- F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Safety Valves (AREA)
- Toys (AREA)
Description
Raketen-Gesehoss. Der Gegenstand vorliegender Erfindung ist ein Raketengeschoss, bei dem die Abbrenn- zeit der Treibladung verschieden eingestellt werden kann.
Die beiliegende Zeichnung zeigt ein Aus führungsbeispiel des Erfindungsgegenstandes. Fig. 1 zeigt das Raketengeschoss im Schnitt. Die Raketenkammer, die den Pulver körper c aufnimmt, besteht aus einer Metall hülse b, die an ihrem hintern Ende eine sich nach aussen erweiternde Gasausströmdüs-e f besitzt. Die Ausströmöffnung der Düse ist durch einen Ventilkörper e abgeschlossen, welcher Ventilkörper e durch eine Feder h gegen die Aus.strömöffnung gepresst wird.
Die Feder h selbst befindet sich in einem Kasten i, in welchem sie durch Drehen der Einstellschraube k auf gewünschte Spannung gepresst werden kann.
Der Raum zwischen Federkanten i und Düsenwand ist der Hauptsache nach für die Abströmung der Gase frei, nur eine Anzahl Metallstege g halten den Federkasten in seiner Lage fest und nehmen einen kleinen Bruchteil der Ausströmfläche der Düse für sich in Anspruch. Fig. 2 zeigt einen Quer schnitt C-D durch diese Stegpartie, und Fig. 3 zeigt einen Schnitt nach der Richtung A-B der Fig. 1.
Die Stege sind dieser Fig. 3 entsprechend nach vorn und hinten zum Zweck der Verminderung der Widerstände zugeschärft. Zudem sind sie zur Radial richtung sowie zur Abströmrichtung der Gase, .die in Fig. 3 mit dem Pfeil bezeichnet ist, schief gestellt, so dass die austretenden Gase das Geschoss um seine Längsachse drehen.
Der Pulverkörper wird durch irgendeine Zündvorrichtung a entflammt. Die Verbrenn gase füllen dann den Hohlraum zwischen Pulverkörper c und dem Ventilkörper e. Der fest aufsitzende Ventilkörper lässt die Gase erst dann nach der Düse entweichen, wenn der Gasdruck die Kraft der Feder h über windet.
Dadurch, dass der Gasdruck, unter wel- wel.chem die Raketenladung abbrennt, mit der Federspannung eingestellt werden kann, kann auch die Abbrennzeit der Treibladung eingestellt werden.
Missile frame. The subject matter of the present invention is a rocket projectile in which the burn-off time of the propellant charge can be set differently.
The accompanying drawing shows an exemplary embodiment from the subject of the invention. Fig. 1 shows the missile projectile in section. The rocket chamber, which receives the powder body c, consists of a metal sleeve b which, at its rear end, has an outwardly widening gas discharge nozzle f. The outflow opening of the nozzle is closed by a valve body e, which valve body e is pressed against the outflow opening by a spring h.
The spring h itself is located in a box i, in which it can be pressed to the desired tension by turning the adjusting screw k.
The space between the spring edges i and the nozzle wall is mainly free for the outflow of the gases, only a number of metal webs g hold the spring box in place and take up a small fraction of the nozzle's outflow area. FIG. 2 shows a cross section C-D through this web part, and FIG. 3 shows a section in the direction A-B of FIG.
The webs are sharpened to this Fig. 3 in accordance with the front and rear for the purpose of reducing the resistance. In addition, they are inclined to the radial direction and to the outflow direction of the gases, which is indicated by the arrow in FIG. 3, so that the escaping gases rotate the projectile about its longitudinal axis.
The powder body is ignited by any igniter a. The combustion gases then fill the cavity between the powder body c and the valve body e. The tightly seated valve body only lets the gases escape after the nozzle when the gas pressure overcomes the force of the spring h.
Because the gas pressure at which the rocket charge burns down can be adjusted with the spring tension, the burn time of the propellant charge can also be adjusted.
Claims (1)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH223977T | 1940-07-31 |
Publications (1)
Publication Number | Publication Date |
---|---|
CH223977A true CH223977A (en) | 1942-10-31 |
Family
ID=4453301
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CH223977D CH223977A (en) | 1940-07-31 | 1940-07-31 | Missile bullet. |
Country Status (1)
Country | Link |
---|---|
CH (1) | CH223977A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2583570A (en) * | 1945-06-28 | 1952-01-29 | Clarence N Hickman | Nozzle for rocket motors |
US5165229A (en) * | 1991-10-22 | 1992-11-24 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Thruster sealing system and apparatus |
-
1940
- 1940-07-31 CH CH223977D patent/CH223977A/en unknown
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2583570A (en) * | 1945-06-28 | 1952-01-29 | Clarence N Hickman | Nozzle for rocket motors |
US5165229A (en) * | 1991-10-22 | 1992-11-24 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Thruster sealing system and apparatus |
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