US3079755A - Propelling device and method - Google Patents

Description

March 5, 1963 H. B. FORNEY PROPELLING DEVICE AND METHOD 3 Sheets-Sheet 1 Filed Dec. 27, 1955 Q m N MN 3 I... f 4... N I II I H I I I/ I n fl H E 3 N w Q E m H N w. 2. II II I l I I fi Q Q Q Q NH QNW. NQ Q Q Jmb u m Iii 31m? ffarry B. ?517Z 5/ H [2 L 75 March 5, 1963 H. B. FORNEY PROPELLING DEVICE AND METHOD 3 Sheets-Sheet 2 Filed D80. 2'7, 1955 LTLF'E 21277 T Ham" B. $51126 I f 2 7. 5

March 5, 1963 H. B. EORNEY 3,079,755

PROPELLING DEVICE AND METHOD Filed Dec. 27, 1955 3 Sheets-Sheet 3 E i i I :q EN a) 1 Q E i f 1 1 E 1' J $1 E R's firaizfmf v Hafry B. 5f119 w a, %M; w%

il L775 United States Patent 3,b?9,755 Patented Mar. 5, 1%53 free 3,tl79,755 PROPELLENG DEVICE AND METHQD Harry it. Forney, Richmond; Va, assiguor to Thompson Rama Wooldridge, Inc, Cleveland, Ohio, a, corporation of Ghio Filed Dec. 27, 1955, Ser. No. 555,485 2 Claims. (Cl. 60-3932) This invention relates generally to a propelling device and method. and more particularly to a device for generating'a jet of gases and sustaining decomposition ofa fluid propellant. Specifically, the invention deals .Witha rocket engine and a process of regeneratively decomposing amonopropellant;v in engine.

' There are two phases in the operation of a monopropellant rocketthe initiation phase. which is a transient condition of greater or lesser duration, and a steady-state operation phase. constant ignition source mustbe provided in order to'initiate combustion in the fresh incoming propellant. Norma'lly this is provided by a recirculation 'zone in which part of the hot decomposition products are fed back to the region wherein the fresh propellant is being injected.

The mechanism is ordinarily that of a recirculating eddy in the internal fiowprocesses. the amount of heat that can be transferred by this pr'ocess is not sufiicient to maintain the decomposition process,-

and all reaction is quenched. In the present invention this difiiculty is overcome by providing mechanical meansous,'however, refers only to that period of time requiredto establish the steady-state condition, and this may vary from a matter of seconds to a matter of minutes, but at some point the glow plug is normally turned off. The well known magnesium igniter acts as a chemically energized glow plug in providing a hot clinker. This clinker remains hot a sufliciently long period to carry,

the over-all reaction through the initiation phase and into the continuous phase. A minimum chamber size exists in which transition to the steady-state phase never occurs that is, the engines run only over the lifetime of the hot clinker. Most probably, in such cases, the electrical glow plug would have to be continuous over the entire run. This situation though occurs only with very small.

chambers. On the other hand, even with operable chambets, is, those above the size that require truly continuous ignition, undesirable amounts of carbon form both with.

the electric glow plug and with the magnesium igniter.

In the past, in devices for generating a jet of gases, such as rocket engines or the like, the fuel or propellant has been heated prior to injection into the reaction chamber. However, when heating the fuel or propellant before injection into a reaction chamber, at best only evaporation is achieved.

In the present invention, a rocket engine or device for generating a jet of gases includes a housing having a reaction or decomposition chamber. A heat exchanger or regenerator is positioned within the reaction chamber for transferring thermal energy to a propellant introduced into the chamber. for initially raising the chamber pressure and tempera: ture and the temperature of the heat exchanger to an energy level sufficient to initiate decomposition of the propellant. Evaporation and decompsitionofthe propellant the reaction chamber of a; rocket:

In the steady-state operationJphase, a.

In very small chambers,

An igniter is mounted in the casing.

is achieved by placing the heat exchanger within the reaction. chamber; The heat exchanger is arranged to-have the. fresh. propellant flow over one surface and the pro-- pellant products of decomposition flow over another surface and out an exhaust port. The propellant products. of decomposition maintain an energy level within the reaction chamber sufiicient to sustain decomposition of the propellant.

Alsoin the. present. invention, the igniter is of such a type which discharges a gaseous exhaust or product into the reaction chamber. In. other words, essentially no solid residue is introduced into the reaction chamber by the igniter. the propellant and" operation of the gasgenerating'device in a carbon free manner. The igniter may be a pyrotecbnic: type, and preferably of the smokeless variety.

Accordingly, it is an. object. of this invention to provide a device for generating a. jet of gases by decomposing a propellant in a reaction chamber.. t

Still another object of this. invention isto provide device'for, generating a jet'of gases including a reaction chamber with means therein that is capable of transtaining decomposition of a monopropellant.

A still further object of this invention is to provide a device for generating ajet of. gases including a reaction chamber having a heat exchanger therein that is capable of effecting a greater heat. exchange operation.

Another object of this invention is inv the. provision of a device for generating a jet of gases by decomposing a monopropellant in. a reaction chamber that is capable of sustaining decomposition of the monopropellant without the aid of anoutside constant ignition source.

A still further object of this invention is to provide a device for generating a jet of gases by decomposing a propellant in a reaction chamberhaving a heat exchanger therein, wherein an igniter discharges hot. gases into the reaction chamber for raising, the'chamber pressure and temperature and the regenerator temperature to an energy level sufiicient to initiate decomposition of the propellant.

Another object of this invention resides in the provision of a device for generating a jet of gases by decomposing a monopropellant in a reaction chamber having a regenerator therein, wherein a pyrotechnic igniter is provided to discharge hot gases into the reaction chamber for raising the chamber pressure and temperature and the regenerator temperature to an energy level sufficient to initiate decomposition of the propellant.

Another object of this invention is to provide adevice for generating a jet of gases by decomposing, a mono propellant in a reaction chamber, wherein decomposition is initiated by an igniter, and wherein ignition and operation is in a carbon free manner.

A further object of this invention is in the provision of a rocket motor having a heat exchanger forpreheating the propellant wherein the heat exchanger is ener-- gized by the propellant products ofdecomposition.

Other objects, features, and advantages of the illVI1-- tion will be apparent from the following detailed'description, taken in conjunction with the accompanying sheets with some parts in elevation and othersbrok'en away for purposes of clarity, of a device for generatinga jet of gases embodying the invention;

Therefore, the igniter provides ignition of 3 FIGURE 2 is an enlarged transverse sectional view, with some parts in elevation, taken substantially along line 11-11 in FIGURE 1 and looking in the direction of the arrows;

FIGURE 3 is a substantially axial sectional view, with some parts in elevation and other parts broken away for.

purposes of clarity, of a modified form of the invention; FIGURE 4 is a substantially axial sectional view, with some parts in elevation, and other parts broken for purposes of clarity, illustrating still another form of the invention;

FIGURE 5 is an enlarged transverse sectional view, taken substantially along line V-V of FIGURE 4 and looking in the direction of the arrows;

FIGURE 6 is a substantially axial sectional view, with some parts in elevation and others broken away for purposes of clarity, of still a difierent form of the invention; and

FIGURE 7 is a transverse sectional view, taken substantially along line VllVli in FIGURE 6 and looking in the direction of the arrows.

As shown on the drawings:

The present invention is primarily useful in connection with aircraft and jet propelled vehicles where it may be desired to provide a supply of energy from a device which occupies a small amount of volumetric space. Specifically, a jet of gases is generated which may, for example, drive .a turbine for generating electrical or hydraulic power. Energy is extracted from a rocket propellant or the like by decomposing the propellant in a reaction or decomposition chamber. The pressure of the propellant gases is converted into kinetic energy by delivering the gases through a nozzle or exhaust orifice.

While any type of propellant may be employed with the present invention, preferably a monopropellant is employed, such as ethylene oxide or hydrazine. In the rocket engine field, a monopropellant may be defined as a single fluid which contains within itself all ingredients necessary to produce useful energy by means of decom position.

While it may be appreciated that the present invention is most useful in connection with aircraft and rocket powered vehicles, other uses and purposes may be apparent to one skilled in the art.

Referring now to FIGURES 1 and 2, an engine or device for generating a jet of gases, generally designated by the numeral 10, includes a housing 11 or casing having a reaction or decomposition chamber 12 formed therein. The housing 11 may be of any form, but in this instance, is formed from a pair of cup shaped members welded together at their open ends defining a front end 'wall 11a connected to a rear end wall 1117 by a cylindrical wall He. Thus, a substantially cylindrical air tight reaction chamber 12 is formed therein although the chamber may take any other suitable form.

Disposed within the reaction chamber 12 is a heat exchanger or regenerator 13 which nominally functions to preheat the fresh propellant injected into the reaction chamber. The heat exchanger may take any desirable form which is capable of being disposed in the reaction chamber. However, in this embodiment, the heat exchanger 13 is formed from an elongated length of tubing which is helically wound in the form of a coil spring. The tubing may be arranged in other shapes such as by being formed in a spiral coil. The coils are generally concentric with the cylindrical walls of the reaction chamber, and the outer peripheries are slightly spaced from the chamber walls. One end of the coiled tubing is open at 14 into which the propellant products of decomposition flow. The coil having the open end 14 is angularly cut, as seen most clearly in FIGURE 2 to provide easy access of the decomposition products into the heat exchanger. However, the end coil may merely be perforated or the very end ofthe tubing cut off transversely. In other words, other forms of openings at this end of the tubing may be employed. The other end of the tubing carries an axially extending portion 15 from the adjacent coil which is suitably secured to the adjacent end wall 11a by welding or other equivalent means for communicating the heat exchanger with an exhaust port 16 in the end wall 11a. The exhaust port is provided with a nozzle or orifice to convert the pressure of the propellant gases into kinetic energy.

The housing 11 and the heat exchanger or regenerator may be-constructed of any suitable type of material which will withstand the operating temperature in decomposing the propellant. Preferably, the heat exchanger may be formed from copper or stainless steel or other material which also has suitable heat transferring characteristics. A rocket propellant, such as a monopropellant is in troduced or injected into the reaction chamber 12 through the end wall lit: by a fitting 17. Alternatively, the monopropellant may be introduced through the cylindrical wall lie of the casing by a fitting 18. And, if desired, the monopropeliant maybe introduced into the reaction chamber through both of the fittings 17 and 18 simultaneously. The end wall 11a and the cylindrical wall are suitably tapped to receive threaded ends of the fittings 17 and 18 in tight sealing relationship. While not shown, it is understood that the fittings 17 and 18 will be connected with other conduits or piping which lead to a propellant tank or reservoir.

Where it may be desired to control the propellant flow into the reaction chamber, a pressure picloup 19 is suitably threaded in a tapped bore in the housing portion 11c for carrying a signal to control valves or the like (not shown) which control the flow of propellant through the fitting 17 and 18 and into the reaction chamber 12. Otherwise, this pressure pick-up 19 may be employed for controlling other apparatus or instrumentation.

The end wall ills of the casing 11 is provided with a tapped bore for receiving the threaded end of a pyrotechm'c igniter 20 in sealing relationship therewith. Alternatively, the igniter 20 may be of a solid-propellant type, or other type of igniter which is capable of introducing hot gases into the reaction chamber 12. Preferably, the pyrotechnic igniter is of the smokeless type wherein essentially no solid residue exists in the hot exhaust gases. It is desired that only a gaseous product or exhaust be introduced into the reaction chamber by the igniter 20. A squib 21 or" any suitable type, which may be activated by a small dry cell battery, is carried on the pyrotechnic igniter housing for energizing the igniter. of operation of the pyrotechnic igniter may be quite brief, but capable of raising the reaction chamber pressure and temperature and the temperature of the heat exchanger to an energy level sufiicient to initiate decomposition of a monopropellant injected into the chamber.

In operation of the engine, the squib 21 is activated by a source of electrical energy such as a small dry cell battery. This action energizes the pyrotechnic igniter which introduces hot gases into the reaction chamber 12. The chamber pressure and temperature and the heat exchanger temperature is thusly elevated by the hot gas discharge of the igniter to an energy level sufiicient to cause decomposition of a monopropellant. A monopropell'ant such as ethylene oxide or hydrazine is then injected or introduced into the reaction chamber through the fitting 17 or 18 which readily decomposes due to the energy level condition in the chamber. The monopropellant products of decomposition flow through the tubing of the regenerator and are released through the exhaust port 16. The monopropellant products of decomposition, in turn, maintain the chamber pressure and temperature and the heat exchanger temperature at such an energy level as to sustain decomposition of the monopropellant subsequent to the introduction of the hot gases into the reaction chamher by the igniter 29. Thermal energy is transferred from the monopropellant products of decomposition to the freshly introduced monopropellant through the medium of the heat exchanger 13, and by the means of the heat The duration exchanger achieves evaporation and decompositionofthe incoming monopropellant. Thus, subsequent to the initialenergization of the pyrotechnic igniter 20, decomposition of fresh monopropellant is-maintained within the reaction chamber 12 by the existence of the regenerative heat exchanger 13.

The combination of the pyrotechnic igniter and the heat exchanger disposed within the reaction chamber permits in the case of monopropellants ignition and operation in the heat exchanger thereby increasing the efficiency of the engine. By mounting the heat exchanger within the reaction chamber, the efiiciency has not only been greatly increased, but the space'requi'rement's have been greatly reduced.

Referring to FIGURE 3, a modified engine or device for generating a jet of gases, generally designated by the numeral 16A, is illustrated which is generally similarto' the embodiment disclos'ed'in FIGURES 1 a'nd2..

In this embodiment, a larger size regenerator or heat exchanger 22 is supported within the reaction chamber 12. This heat exchanger is also formed from a length of tubing which is spirally or helically wound, but in this embodiment, the outer peripheries of the coils are sized to engage the cylindrical walls of the reaction chamber.

One other diif-erence lies in the elimination of one of the propellant inlets to the reaction chamber, wherein this embodiment, only the fitting 17 in the'end wall 11a is'provided for introducing the propellant into the chamber. It is not necessary that two propellant inlets be provided for introducing the propellant into the reaction chamber 12. Moreover, the fact that the coils of the regenerator engage the cylindrical walls of'thereaction chamber has no effect on the operation of the engine, although this arrangement provides for easier supporting of the heat exchanger Within the reaction chamber; The operation of this embodiment is substantially identical as the operation of the embodiment in FIGURES l and 2, and therefore will not be set out in detail.

A still diiterent embodiment, shown in FIGURES 4 and 5, is provided with a still different shaped heat exchanger. In this embodiment, the engine or gas generating device 103 includes the housing 11 formedfrorn a pair of cup shaped members to define the reaction chamber 12 similar to the first embodiments. The housing 11 is again provided with end walls 11a and 11b and a cylindrical connecting wall 110, and defines a substantially cylindrically shaped reaction chamber within the housing.

In this embodiment, the regenerator or heat exchanger "3 is in the shape of a can or hollow cylinder having an open and a closed end. The heat exchanger includes a cylindrical wall 23a which defines with the cylindrical walls of the reacton chamber an annular passageway, and an end wall 23b in slightly spaced relationship from the housing end wall 11!) to define a disk-shaped collecting chamber. To support the heat exchanger 23 within the reaction chamber, a plurality of annularly arranged supporting members 24 are connected at one end to the end wall 23b of the heat exchanger and at the other end to the end wall 11b of the housing. These supporting members further serve to assure the spacing between the housing end wall and the heat exchanger end wall. While the heat exchanger cylindrical wall 23a appears to be spaced at a considerable distance from the inner cylindrical wall of the reaction chamber, it may be appreciated that this distance can be quite small and that the heat exchanger 23 may be more or less supported on the cylindrical walls of the reaction chamber. It is only necessary that sufficient space he provided between the regenerator heatexchanger is somewhat different.

pyrotechnic igniter 20 is energized to introduce through 6-, and reaction-chamber wall to allow flow of gases there between.

In-this embodiment, the propellant or monopropellant is again introduced into the reaction chamber through theend wall 111: and the fitting 17. However, the pyrotechnic igniter 20 is connected to the end wall 11a by an elbow fitting 25 for introducing the hot gases into the reaction chamber and open end of the regenerator 23.

Another difference over the other embodiments lies in the positioning of the exhaust port 16, which now is formed in substantially the center of the opposite end wall 11b.

The principle of operation of the engine lilb is identical with that of the other embodiments, even though the arrangement ofthe components and the shape of the In'operation, the

the elbow 25 a blast of hot gases into the reaction chamber 12. and the open end of the heat exchanger 23; This action elevates the reaction chamber pressure and temperature and the heat exchanger temperature to an energy level sufficient to initiate decomposition of a monopropellant which. is then injected or introduced into the reaction. chamber through the fitting 17. The monopropellant hits the inside of the heat exchanger and wall 23b and splat- 1 ters in all directions before-taking a path toward the open end of the heat exchanger and adjacent the inner surface of the heat exchanger. cylindrical wall 23a. Due to the energy level conditions set up by the pyrotechnic igniter 20, the monopr'opellant begins to decompose; and the products of decomposition flow'around the open end of the heat exchanger and back along the annular passageway defined by the cylindrical walls of the reaction cham her and the outer cylindrical surface of the heat exchanger cylindrical wall 230'. As the products of decomposition flow towards the end wall 11b of the housing, thermal energy is imparted to the heat exchanger 23 and, in turn, transferred to the fresh monopropellant. The products of decomposition then collect in the disk-shaped chamber defined by the housing end wall 11b and the heat exchanger end wall 23b and are released through the exhaust port 16; Thus, thermal energy is transferred from the products of decomposition through the heat exchanger cylindri'calwall 23a and the end wall 23b to the incoming fresh monopropellant introduced into the reaction chambet and the open end of'the heat exchanger 23. And, as in the other embodiments, the products of decomposition maintain the energy level within the reaction chamber at a point sufiicient to maintain decomposition of the monopropellant after the pyrotechnic igniter has been deenergized.

A still different form of the invention is illustrated in FIGURES 6 and 7, wherein an engine or gas generating device 10C includes the same type of housing 11 as set forth in the other embodiments.

In this embodiment, a regenerator or heat exchanger 26 is again positioned within the reaction chamber 12, and the heat exchanger is in the form of an elongated accordion pleated member. This member is hollow and open at the end adjacent the housing end wall 11a, and closed at the other-end by an end wall 26a near the other housing end wall 11b. The interior of the heat exchanger intercommu'nicates'with the exhaust port 16 disclosed in the housing end wall 11]; through a connecting tube 26b that is connected at one end to an aperture in the heat exchanger end wall 26a and at the other end to the inner surface of the housing end wall 11b in registry with the exhaust port 16.

The monopropellant is introduced into the reaction chamber through the housing end wall 11b and the fitting 17 mounted therein. It may be noted that the inlet is substantially centrally located in the end wall 11b, while the exhaust port 16 is positioned radially outwardly from the monopropellant inlet. Introduction of the hot gases from the pyrotechnic igniter is also through the end wall 11b which mounts the igniter.

' Again, the general principle of operation of the gas generating device ltic is, in Connection with the decomposition of the monopropellant in the reaction chamber 12, substantially identical as the operation of the engines 16, A and 16B. Initially, the pyrotechnic igniter 20 is energized which introduces into the reaction chamber 12 through the housing end wall 1112 a stream of hot gases that raise the reaction chamber pressure and temperaiure and the heat exchanger temperature to an energy level sufiicient to initiate decomposition of a monopropellant. The incoming monopropellant, being introduced through the housing end wall 11b flows over the outer surfaces of the heat exchanger 26 and through the several passageways defined by the pleated shape. As the monopropellant decomposes, the products of. decomposition are directed into the open end of the heat exchanger to flow therethrough and exit through the exhaust port 16. While the products of decomposition flow through the interior f the heat exchanger, thermal energy is transferred through the walls of the heat exchanger and to the incoming fresh monopropellant, and as. in the other embodiments, the products of decomposition maintain an energy level condition within the reaction chamber which is capable of substaining decomposition of the monopropellant after the pyrotechnic igniter 20 has been deenergized or spent.

From the foregoing, it will be seen that a rocket engine or device for generating a jet of gases has been provided of simple construction, compact in size, having a minimum of parts, that is extremely eificient, and capable of starting and operating in a carbon free manner.

it will be understood that modifications and variations may be efifected without departing from the scope of the novel concepts of the present invention, but it is understood that this application is to be limited only by the scope of the appended claims. 1

I claim as my invention:

1. A device for generating a jet of gases and sustaining decomposition of a fluid monopropellant such as used in a rocket engine comprising in combination a housing member having a wall defining -aclosed air-tight cylin-V drically shaped reaction chamber, a helically wound elongated length of tubular material positioned within said chamber concentric'with the chamber and with the outer periphery of the coil spaced inwardly from the chamber walls to form an annular portion of the reaction chamber between the chamber wall and coil, the area within said coil forming a cylindrical portion of the reaction chamber, means defining an opening at one end of the coil communicating'with the reaction chamber, the inside of said tubular material of the coil defining an inner portion of the reaction chamber, means defining an exhaust port in said well of said housing member with the other end of said coil connected to the wall to discharge through said exhaust port, orifice means located in said exhaust port to convert the pressure of the propellant gases through said coil and out of said port to kinetic energy, a first monopropellant fitting connected to the Wall of said housing and opening into said annular portion of the reaction chamber, a second monopropellant fitting connected to the wall of said housing and opening into said cylindrical portion of said reaction chamber, a pry-otechnic igniter having a pyrotechnic chamber with an open discharge end, said igniter positioned with said open discharge end secured to and extending through the wall of said housing and opening'into said reaction chamber outside of said coil adjacent the open end thereof so that monopropellant fuel will be ignited in said annular portion and said cylindrical portion and will continue burning to said inner portion, the burning monopropellant gases flowing into said inner portion from both or" said annular and cylindrical portions, and an electric igniter in said pyrotechnic chamber for igniting pyrotechnic ignition material to ignite and cause decomposition of the monopropellant directed into the reaction chamber from said first and second monopropellant fittings.

2. A device for generating a jet of gases and sustaining decomposition of a fluid monopropellant such as used in a rocket engine comprising in combination a housing member having a wall defining a closed air-tight reaction chamber, a helically wound elongated coil of tubular material positioned within said chamber and dividing said reaction chamber into a first outer portion outside of said tubular material of said coil and asecond inner portion within said tubular material of said coil, an opening in one end of the coil defined by-an angular cut across said one end providing an elongated entry opening for decomposition products from said first outer portion flowing to said second inner portion of thereaction chamber, means defining an exhaust port in said Wall of said housing member with the other end of said coil connected to the wall to discharge through said exhaust port, orifice means located in said exhaust port to convert the pressure of propellant gases flowing through said coil and out of said port to kinetic energy, a monopropellant fitting connected to the wall of said housing and opening into said reaciton chamber to direct monopropellant fuel into said outerportion of said reaction chamber, a pyrotechnic igniter having a pyrotechnic chamber with an open end, said igniter positioned with said open end secured to and extending through the wall of said housing and opening directly into said first outer portion of said reactionchamber outside of said coil and adjacent said one open end of the coil to ignite the monopropellant in said first outer portion of the reaction chamber just before it flows into said second inner portion, and an electrical igniter in said pyrotechnic chamber for igniting pyrotechnic ignition material to direct a jet of burning pyrotechnic material into said outer portion of the reaction chamber to ignite and cause the decomposition of monopropellant directed into the first outer portion of the reaction chamber through the monopropellant fitting.

References Cited in the file of this patent UNITED STATES PATENTS

Claims (1)

1. A DEVICE FOR GENERATING A JET OF GASES AND SUSTAINING DECOMPOSITION OF A FLUID MONOPROPELLANT SUCH AS USED IN A ROCKET ENGINE COMPRISING IN COMBINATION A HOUSING MEMBER HAVING A WALL DEFINING A CLOSED AIR-TIGHT CYLINDRICALLY SHAPED REACTION CHAMBER, A HELICALLY WOUND ELONGATED LENGTH OF TUBULAR MATERIAL POSITIONED WITHIN SAID CHAMBER CONCENTRIC WITH THE CHAMBER AND WITH THE OUTER PERIPHERY OF THE COIL SPACED INWARDLY FROM THE CHAMBER WALLS TO FORM AN ANNULAR PORTION OF THE REACTION CHAMBER BETWEEN THE CHAMBER WALL AND COIL, THE AREA WITHIN SAID COIL FORMING A CYLINDRICAL PORTION OF THE REACTION CHAMBER, MEANS DEFINING AN OPENING AT ONE END OF THE COIL COMMUNICATING WITH THE REACTION CHAMBER, THE INSIDE OF SAID TUBULAR MATERIAL OF THE COIL DEFINING AN INNER PORTION OF THE REACTION CHAMBER, MEANS DEFINING AN EXHAUST PORT IN SAID WALL OF SAID HOUSING MEMBER WITH THE OTHER END OF SAID COIL CONNECTED TO THE WALL TO DISCHARGE THROUGH SAID EXHAUST PORT, ORIFICE MEANS LOCATED IN SAID EXHAUST PORT TO CONVERT THE PRESSURE OF THE PROPELLANT GASES THROUGH SAID COIL AND OUT OF SAID PORT TO KINETIC ENERGY, A FIRST MONOPROPELLANT FITTING CONNECTED TO THE WALL OF SAID HOUSING AND OPENING INTO SAID ANNULAR PORTION OF THE REACTION CHAMBER, A SECOND MONOPROPELLANT FITTING CONNECTED TO THE WALL OF SAID HOUSING AND OPENING INTO SAID CYLINDRICAL PORTION OF SAID REACTION CHAMBER, A PRYOTECHNIC IGNITER HAVING A PYROTECHNIC CHAMBER WITH AN OPEN DISCHARGE END, SAID IGNITER POSITIONED WITH SAID OPEN DISCHARGE END SECURED TO AND EXTENDING THROUGH THE WALL OF SAID HOUSING AND OPENING INTO SAID REACTION CHAMBER OUTSIDE OF SAID COIL ADJACENT THE OPEN END THEREOF SO THAT MONOPROPELLANT FUEL WILL BE IGNITED IN SAID ANNULAR PORTION AND SAID CYLINDRICAL PORTION AND WILL CONTINUE BURNING TO SAID INNER PORTION, THE BURNING MONOPROPELLANT GASES FLOWING INTO SAID INNER PORTION FROM BOTH OF SAID ANNULAR AND CYLINDRICAL PORTIONS, AND AN ELECTRIC IGNITER IN SAID PYROTECHNIC CHAMBER FOR IGNITING PYROTECHNIC IGNITION MATERIAL TO IGNITE AND CAUSE DECOMPOSITION OF THE MONOPROPELLANT DIRECTED INTO THE REACTION CHAMBER FROM SAID FIRST AND SECOND MONOPROPELLANT FITTINGS.

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