CH157231A - Method and device for moving vehicles by means of the recoil of expanding gases. - Google Patents
Method and device for moving vehicles by means of the recoil of expanding gases.Info
- Publication number
- CH157231A CH157231A CH157231DA CH157231A CH 157231 A CH157231 A CH 157231A CH 157231D A CH157231D A CH 157231DA CH 157231 A CH157231 A CH 157231A
- Authority
- CH
- Switzerland
- Prior art keywords
- propellant
- explosive
- recoil
- explosion
- shell
- Prior art date
Links
- 239000007789 gas Substances 0.000 title claims description 10
- 238000000034 method Methods 0.000 title claims description 9
- 239000002360 explosive Substances 0.000 claims description 17
- 239000003380 propellant Substances 0.000 claims description 15
- 238000004880 explosion Methods 0.000 claims description 14
- 239000000126 substance Substances 0.000 claims description 8
- 230000033001 locomotion Effects 0.000 claims 1
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 10
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 description 5
- 235000011187 glycerol Nutrition 0.000 description 5
- 229910017604 nitric acid Inorganic materials 0.000 description 5
- SNIOPGDIGTZGOP-UHFFFAOYSA-N Nitroglycerin Chemical compound [O-][N+](=O)OCC(O[N+]([O-])=O)CO[N+]([O-])=O SNIOPGDIGTZGOP-UHFFFAOYSA-N 0.000 description 3
- 229960003711 glyceryl trinitrate Drugs 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000004570 mortar (masonry) Substances 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H11/00—Marine propulsion by water jets
- B63H11/12—Marine propulsion by water jets the propulsive medium being steam or other gas
- B63H11/14—Marine propulsion by water jets the propulsive medium being steam or other gas the gas being produced by combustion
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/023—Aircraft characterised by the type or position of power plants of rocket type, e.g. for assisting taking-off or braking
-
- 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
- F02K7/02—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 the jet being intermittent, i.e. pulse-jet
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Ocean & Marine Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Colloid Chemistry (AREA)
Description
Verfahren und Vorrichtung zur Fortbewegung von Fahrzeugen vermittelst des Rückstosses expandierender Gase. Die Erfindung bezieht sich auf ein Ver fahren zur Fortbewegung von Fahrzeugen vermittelst des Rückstosses expandierender Gase und eine Vorrichtung zur Durchfüh rung des Verfahrens.
Das Verfahren zeichnet sich dadurch aus, dass durch den Ausdehnungsdruck von bei. Explosionen entstehenden Gasen eines Explo sivstoffes, der unmittelbar vor der Explosion durch Verbindung von wenigstens zwei nicht explosiven Stoffen in wenigstens einem am Fahrzeug befestigten Treibkörper erzeugt und in diesem zur Explosion gebracht wird, eine das Fahrzeug antreibende Kraft ent steht.
Es können zum Beispiel Glyzerin und Salpetersäure in den Treibkörper geführt werden, die sich in diesem zu dem den Explosivstoff bildenden Nitroglyzerin ver binden.
Die Zeichnung stellt ein an einem Flug zeug angebrachtes Ausführungsbeispiel einer zur Durchführung des Verfahrens geeigneten Vorrichtung dar.
Fig. 1 zeigt einen Aeroplan mit der Vor richtung von der Seite gesehen; Fig. 2 zeigt diesen Aeroplan von oben gesehen; Fig. 3 zeigt einen Treibkörper der Vor richtung im Schnitt.
Der Aeroplan 1 ist mit zwei zu beiden Seiten seines Kopfes angeordneten Treib- körpern versehen. Jeder Treibkörper weit eine Schale 2 auf, die auf einer hohlen Welle 3 aufgekeilt ist, welche in den Na ben 4 gelagert ist und vermittelst des Schneckenrades 5 der Schnecke 6 und des Handrades 7 gedreht werden kann, so dass zwecks raschen Steigens und Senkens des Aeroplans der Treibkörper um eine zur Längsaxe des Aeroplans stehende Axe ver- schwenkt werden kann.
Die Vorrichtung weist. zwei Behälter g und 9 auf, von denen der eine zur Fassung des Glyzerins und der andere zur Fassung der Salpetersäure dient. Durch Druckluft, die diesen Behältern aus der Flasche 10 durch die Rohrleitung 11, die das Druck- redu.zierventil 12 aufweist., zuströmt, wird ein Druck auf die Flüssigkeiten in den Be hältern ausgeübt. Dadurch werden das Gly zerin und die Salpetersäure vermittelst den Rohrleitungen 18, 13' und 14, 14' den Treibkörpern der Vorrichtung zugepresst.
Die Durchflussmengen dieser Rohrleitungen lassen sich durch zwei Doppelventile, die durch die Handräder 15 und 16 betätigt werden, für jeden Treibkörper entsprechend dem nötigen Mischungsverhältnis und dem gewünschten Treibeffekt des zur Verwen dung kommenden Explosivstoffes regulieren.
Zur möglichst stossfreien Übertragung der Energie der expandierenden Gase auf den Treibkörper ist dieser, wie Fig. 3 zeigt, mit der Schale 2 versehen, deren Bodenmitte eine Erhöhung 17 aufweist. In dieser Er höhung 17 sind die Rohrleitungen 13 und 13' eingebettet, die das Glyzerin und die Sal petersäure den Kanälen 18 und 19 zuführen, so dass sieh die beiden Flüssigkeiten an der Verbrennungsstelle 20 zusammen vermengen und durch ihre Verbindung das explosive Nitroglyzerin bilden, das dort zur Explosion gebracht wird.
Das Glyzerin und die Salpetersäure strömen der Explosionsstelle 20 kontinuier lich zu, trotzdem erfolgt die Gasentwicklung des Nitroglyzerins in intermittierenden Ex plosionen, denn bei jeder Explosion wird der an der Explosionsstelle durch Verbindung von zwei nicht explosiven Substanzen gebildete Explosivstoff aufgezehrt und wird ein, wenn auch noch so kleine Zeitintervall bis zur Bildung einer neuen Menge Explosivstoffes nötig sein. Es wird auch praktisch niemals möglich sein, die explosivstoffbildenden Substanzen einander so rasch zuzuführen und unter sich zu verbinden, als der Ex plosivstoff durch die Explosion aufgezehrt wird. Zur besseren Verwertung der Energie der Explosionsgase kann die Schale 2 bis zur Form des Mörsers vertieft werden.
Bei Beginn des Betriebes muss der Ex plosivstoff, wenn er durch seine Bildung nicht selber explodiert, durch Erschütterung oder Zündung zur Explosion, gebracht wer den, Dazu können zum Beispiel die Zündung durch elektrische Funkenbildung, die Glüh- zündung, die Erschütterung durch Explosiv stoffexplosionen, oder die Zufuhr von Sauer stoff verwendet werden. Nach einigen Ex plosionen wird die Explosionsstelle derart erhitzt, dass -der durch die Hitze explodierende Explosivstoff durch die Rückstrahlung der Wärme des Treibkörpers ohne besondere Vor kehrungen explodiert.
Das beschriebene Verfahren zur Fort bewegung von Fahrzeugen hat gegenüber demjenigen mit Explosionsmotor und Pro peller Vorteile. Es ist einfacher, da zu seiner Durchführung schnell bewegte und so mit sieh rasch abnützende Mechanismen nicht nötig sind; es ermöglicht grössere Fahr geschwindigkeit und ist bei der Verwendung von Betriebsstoffen mit gleicher Eigenschaft wie die oben angeführten Treibstoffe unemp findlich gegen Temperatur- und Luftdruck schwankungen und verwendbar im luftver dünnten und luftleeren Raum.
Gegenüber demjenigen mit Raketenver brennung ist es bei Verwendung der an geführten Betriebsstoffe insofern vorteil- hafter, als, die mitzuführenden Stoffe im Verhältnis zu ihrer Treibkraft bedeutend leichter und nicht explosiv und auch nicht oder fast nicht verbrennbar, somit weniger gefährlich sind.
Method and device for moving vehicles by means of the recoil of expanding gases. The invention relates to a method for moving vehicles by means of the recoil of expanding gases and a device for implementing the method.
The process is characterized in that the expansion pressure of at. Explosive gases of an explosive substance, which is generated immediately before the explosion by combining at least two non-explosive substances in at least one propellant attached to the vehicle and is caused to explode in this, a vehicle driving force is ent.
For example, glycerine and nitric acid can be fed into the propellant, which then bind to the nitroglycerine which forms the explosive.
The drawing shows an exemplary embodiment of a device suitable for carrying out the method, attached to an aircraft.
Fig. 1 shows an airplane with the device seen from the side; Fig. 2 shows this airplan seen from above; Fig. 3 shows a propulsion body of the device in section.
The airplane 1 is provided with two propellants arranged on both sides of its head. Each propellant body has a shell 2, which is keyed on a hollow shaft 3, which is mounted in the Na ben 4 and can be rotated by means of the worm wheel 5 of the worm 6 and the hand wheel 7, so that for the purpose of rapid rise and fall of the plane the propellant can be pivoted about an axis standing to the longitudinal axis of the airplane.
The device has. two containers g and 9, one of which is used to hold the glycerine and the other to hold the nitric acid. By means of compressed air that flows into these containers from the bottle 10 through the pipe 11, which has the pressure reducing valve 12, pressure is exerted on the liquids in the containers. As a result, the glycerin and the nitric acid are pressed through the pipes 18, 13 'and 14, 14' of the propellants of the device.
The flow rates of these pipes can be regulated by two double valves, which are operated by the handwheels 15 and 16, for each propellant according to the required mixing ratio and the desired propellant effect of the explosive used.
In order to transfer the energy of the expanding gases to the propellant body as smoothly as possible, the propellant body is, as FIG. 3 shows, provided with the shell 2, the bottom center of which has an elevation 17. In this elevation 17 the pipes 13 and 13 'are embedded, which supply the glycerine and the nitric acid to the channels 18 and 19, so that the two liquids mix together at the point of combustion 20 and through their connection form the explosive nitroglycerine, which is detonated there.
The glycerine and nitric acid flow continuously to the explosion point 20, but the gas development of the nitroglycerine takes place in intermittent explosions, because with each explosion the explosive formed at the explosion point by combining two non-explosive substances is consumed and becomes one, if still such a small time interval may be necessary until a new quantity of explosive is formed. It will also practically never be possible to supply the explosive-forming substances to one another and to combine them with one another as quickly as the explosive is consumed by the explosion. For better utilization of the energy of the explosion gases, the shell 2 can be deepened to the shape of the mortar.
At the start of operation, if the explosive material does not explode by itself, it must be caused to explode by shock or ignition. This can include, for example, ignition by electrical sparking, glow ignition, vibration by explosive material explosions, or the supply of oxygen can be used. After a few explosions, the point of explosion is heated in such a way that the explosive that explodes due to the heat explodes without any special precautions due to the reflection of the heat from the propellant.
The method described for moving vehicles forward has advantages over that with an explosion engine and propeller. It is simpler since fast moving and thus rapidly wearing mechanisms are not necessary for its implementation; it enables greater driving speed and is insensitive to temperature and air pressure fluctuations when using supplies with the same properties as the fuels listed above and can be used in air-less and evacuated rooms.
Compared to that with rocket combustion, it is more advantageous when using the operating materials listed, as the substances to be carried in relation to their propulsive power are significantly lighter and non-explosive and also not or almost non-combustible, thus less dangerous.
Claims (1)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH157231T | 1930-04-30 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CH157231A true CH157231A (en) | 1932-09-15 |
Family
ID=4411396
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CH157231D CH157231A (en) | 1930-04-30 | 1930-04-30 | Method and device for moving vehicles by means of the recoil of expanding gases. |
Country Status (1)
| Country | Link |
|---|---|
| CH (1) | CH157231A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2422744A (en) * | 1944-09-30 | 1947-06-24 | Gen Tire & Rubber Co | Auxiliary jet power means for aircraft |
| US2431132A (en) * | 1943-06-07 | 1947-11-18 | Aerojet Engineering Corp | System of propulsion |
| US2474183A (en) * | 1949-06-21 | Rocket propulsion by reacting | ||
| US2479888A (en) * | 1943-07-06 | 1949-08-23 | Reaction Motors Inc | Controlling system for reaction motors |
| US2489051A (en) * | 1943-08-16 | 1949-11-22 | American Cyanamid Co | Rocket propulsion utilizing hydrocarbon, sulfate turpentine, nitric acid, and sulfuric acid or oleum |
| US2500334A (en) * | 1944-06-19 | 1950-03-14 | Aerojet Engineering Corp | Jet motor operable by monopropellant and method of operating it |
| US2563022A (en) * | 1944-02-12 | 1951-08-07 | Daniel And Florence Guggenheim | Fuel feeding mechanism for detonating combustion apparatus |
| US2573471A (en) * | 1943-05-08 | 1951-10-30 | Aerojet Engineering Corp | Reaction motor operable by liquid propellants and method of operating it |
| US3151446A (en) * | 1959-12-15 | 1964-10-06 | Arthur R Parilla | Propulsion devices |
| US3173250A (en) * | 1960-05-05 | 1965-03-16 | North American Aviation Inc | Reverse flow thrust chamber |
-
1930
- 1930-04-30 CH CH157231D patent/CH157231A/en unknown
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2474183A (en) * | 1949-06-21 | Rocket propulsion by reacting | ||
| US2573471A (en) * | 1943-05-08 | 1951-10-30 | Aerojet Engineering Corp | Reaction motor operable by liquid propellants and method of operating it |
| US2431132A (en) * | 1943-06-07 | 1947-11-18 | Aerojet Engineering Corp | System of propulsion |
| US2479888A (en) * | 1943-07-06 | 1949-08-23 | Reaction Motors Inc | Controlling system for reaction motors |
| US2489051A (en) * | 1943-08-16 | 1949-11-22 | American Cyanamid Co | Rocket propulsion utilizing hydrocarbon, sulfate turpentine, nitric acid, and sulfuric acid or oleum |
| US2563022A (en) * | 1944-02-12 | 1951-08-07 | Daniel And Florence Guggenheim | Fuel feeding mechanism for detonating combustion apparatus |
| US2500334A (en) * | 1944-06-19 | 1950-03-14 | Aerojet Engineering Corp | Jet motor operable by monopropellant and method of operating it |
| US2422744A (en) * | 1944-09-30 | 1947-06-24 | Gen Tire & Rubber Co | Auxiliary jet power means for aircraft |
| US3151446A (en) * | 1959-12-15 | 1964-10-06 | Arthur R Parilla | Propulsion devices |
| US3173250A (en) * | 1960-05-05 | 1965-03-16 | North American Aviation Inc | Reverse flow thrust chamber |
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