JP3402964B2 - Rocket engine igniter - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [0001] BACKGROUND OF THE INVENTION The present invention relates to a
A rocket engine that generates propulsion for a rocket
Rocket that ignites the propellant gas supplied to the combustor
It relates to an engine igniter. [0002] 2. Description of the Related Art Locations launched from the ground to outer space
The ignition of rocket engines installed in
Since then, a rocket engine igniter as shown in Fig. 3 has been used.
Have been used. In such an igniter, the gas is gasified and
Liquid serving as propellant gas supplied to the combustor of a ket engine
Hydrogen LH_TwoSuch as liquid fuel and liquefied oxygen LOX
And a fuel, not shown, for storing the respective liquid oxidizers
Fuel connected to tank and oxidizer tank respectively
A pipe 01 and an oxidant pipe 04 are provided.
1 and the oxidizer tube 04,
By opening the valve 02 and the oxidizer valve 05,
The liquid fuel and liquid stored in these tanks
A part of the body oxidant is extracted, and the fuel valve 02 and the oxidant are extracted.
As with the valve 05, the fuel pipe 01 and the oxidant pipe 04
The fuel heat exchanger 03 interposed in each and the oxidation
It is introduced and supplied to the agent heat exchanger 06. In these heat exchangers 03,06, the gas
Fuel GH_TwoAnd the oxidizer GOX
07 and installed in the igniter cylinder 07.
The combustion gas CG is ignited in the ignition cylinder 07
From the tip, supply a combustor for a rocket engine (not shown).
Propellant gas supplied separately to the combustor,
In this case, the fuel tank described above and the oxidant tank
Heat exchanger for fuel 03, oxidant heat
Heat exchanger or rocket provided separately from exchanger 06
Gasified with hard heat mass such as engine skirt
Ignition of propellant gas consisting of fuel gas and oxidizer gas
I'm trying to do it. [0005] However, such a rocket engine
The following problems are found in the igniter. (1) A long line composed of the fuel tube 01 and the oxidant tube 04
Pipes and the fuel interposed in these pipes 01 and 04, respectively.
From the heat exchanger 03 for the fuel and the heat exchanger 06 for the oxidant.
There is a problem due to the need for a heat exchanger. That is, the cryogenic liquefied oxygen LOX is stored at a very low temperature.
Oxidizer tank and cryogenic hydrogen LH_TwoSave
The fuel tank to be stored and the igniter tube 08 are arranged separately.
And the lengths of the fuel pipe 01 and the oxidizer pipe 04 become longer.
Therefore, the cost required for these pipes 01 and 04 is large.
And the space where these pipes 01 and 04 are arranged
Work cost increases due to the small size
Of rocket performance decrease due to weight increase and weight increase
There is. In particular, the oxidizer pipe 04 is connected to the oxidizer tank and the fuel tank.
Are arranged in series in the direction of the rocket's fuselage axis.
Deployed above the rocket engine during launch
The oxidizer tank is located further above the installed fuel tank
The length is longer because of the
Make the condition noticeable. Similarly, in the middle of these pipes 01 and 04,
If the cost required for the interposed heat exchangers 03,06 increases,
In both cases, there is a problem that the work cost required for installation increases
In both cases, there is a problem that the weight of the rocket increases.
You. Furthermore, these heat exchangers 03,06
The combustion gas generated by the engine is separated from the metal wall by one
Heat exchange by flowing body fuel or liquid oxidizer
Gasification, so that it may
Fuel or oxidant leaks into the combustion gas from the wall
The hot gas comes into contact with fuel or oxidizer,
Causing rocket engines to be destroyed.
There is also the risk that it may be (2) In addition, a combustion gas CG for ignition is generated.
Liquefied hydrogen LH in the fuel tank_TwoOne
Part of the liquefied oxidizer LOX in the oxidizer tank
There is also a defect due to use. That is, the fuel tank
Liquefied hydrogen LH_TwoAnd liquefied acid in the oxidizer tank
Element LOX is also used for rocket engines as described above.
Rocket engine
Depending on the pressure in the fuel tank and oxidizer tank
Fluctuates, and the fuel heat exchanger 03 and the oxidant heat exchanger 0
LH supplied to 6_Two, And liquefied oxygen LOX
Supply amount fluctuates. In addition, these heat exchangers 03,06
As mentioned, heat exchange with rocket engine combustion gas
Liquefied hydrogen LH_TwoAnd liquefied oxidizer LOX
Rocket engine startup
Heat exchange depends on the heat exchange
Gas supplied from the heat exchangers 03 and 06 into the igniter cylinder 07
Fuel GH_TwoAnd supply of oxidant GOX change
May move. Because of this, rocket engines
The starting system becomes more complicated and the starting
The problem that setting of the ket engine sequence becomes difficult
There are conditions. [0010] The rocket engine igniter also includes
So-called liquid propulsion consisting of liquid fuel and liquid oxidizer
Use solid propellants instead of those that use drugs
Although solid propellants are used, combustion
Defects may occur due to the product. That is,
Products such as combustion gas generated in the igniter cylinder 07 are
Flows out to the combustor of the cut engine,
The solid product produced in the combustion chamber
Various problems may occur during baking. further,
When using solid propellants, once ignited, liquid propulsion
Combustion control by valve operation was not possible like medicine
Therefore, there is a problem that it cannot be reused. [0011] SUMMARY OF THE INVENTION The present invention
Rocket engine point using liquid propellant used
To solve the above-mentioned problems with firearms, rocket engines
Rocket engine start-up
Simplifies configuration, facilitates setup, and reduces equipment costs.
Rocket engine point that can reduce
It is an object to provide a firearm. [0012] For this reason, the location of the present invention
The following measures were used for the cut engine igniter. (1) Gasified fuel and oxidizer
Was introduced inside and ignited by the installed exciter.
Combustion gas is supplied to the combustor of a rocket engine and burned
Combustion gas that ignites the propellant gas separately introduced into the
Connected to the igniter tube that is made to live and enclosed inside
Fuel that is supplied to the igniter cylinder
A cartridge was provided. (2) Similar to the above-described fuel cartridge
The oxidizer gas connected to the above-mentioned igniter cylinder and enclosed inside
Oxidizer cartridge that supplies gas into the igniter cylinder
Luggage was provided. The fuel cartridge and the oxidant cartridge
Cartridges can be independent, separate cartridges.
Or partition the inside of one cartridge,
Gas and oxidizer gas are enclosed in separate compartments and individually ignited.
Into a one-piece cartridge that can be supplied into the cylinder.
You can also. Also, fuel cartridge and oxidizer
The capacity of the cartridge, and the fuel gas enclosed inside,
Or, the pressure of the oxidizing gas is used to ignite a rocket engine
The location that will be launched into outer space as described above
Used to ignite the first stage rocket engine
Is about 70 m / m φ × 150 m / m to 200 m / m
50 kg / cm^Two~ 100kg / cm
^TwoThe fuel gas or oxidizer gas of the degree
If used, use for ignition that takes about 10 seconds
Can be. Also, a fuel cartridge and an oxidizer car
The fuel and oxidizer to be filled in each of the
As mentioned, the propulsion gas supplied to the rocket engine
Be sure to use the same components as the fuel and oxidizer
Or other components, such as fuels,
Methane, propane, etc.
May be used. In addition,
Cartridge and oxidizer cartridge and igniter tube
Can be connected by a detachable mechanism.
The preferred one is preferred. The rocket engine igniter of the present invention
Means for supplying fuel gas into the igniter cylinder, and
Fuel cartridge containing gas and oxidizer gas in a gaseous state.
And supply from the oxidizer cartridge.
The fuel heat exchanger needed for the rocket engine
And oxidizer heat exchangers are no longer required, saving cost and weight.
High temperature gas and fuel during heat exchange
/ The possibility of oxidizer mixing disappears, rocket engine
The risk of destroying is reduced. Further, the fuel gas and the oxidizing gas are sealed.
Ignited fuel cartridge and oxidizer cartridge
By connecting to the barrel, the length of the fuel pipe and oxidizer pipe can be reduced.
Extremely short, especially for fuel cartridges and oxidizers
Cartridge can be connected to igniter cylinder by direct mounting mechanism
If they do, these fuel tubes and oxidizer tubes will be eliminated.
Cost and weight can be greatly reduced. Furthermore, the fuel gas supplied to the ignition device
And the oxidizer gas supply from the rocket engine propulsion
Rocket engine because it is separated from the
The ignition condition of the igniter does not depend on the rising condition. This
This simplifies the system when starting the rocket engine
Rocket engine sequence at start-up
Becomes easier. Further, fuel and acid supplied to the igniter cylinder
The source of the oxidizer is the fuel cartridge and oxidizer cartridge.
As a result, it can be easily replaced. [0021] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A rocket engine according to the present invention will be described below.
An embodiment of the igniter will be described with reference to the drawings. Figure
1 is a first embodiment of a rocket engine igniter according to the present invention.
FIG. As shown in the figure, the fuel gas GH_TwoAnd oxidizer
Gas GOX is divided into two compartments,
The cartridges 1 are sealed in the cartridges 1 respectively. What
In this embodiment, fuel such as methane, propane, and hydrogen is used.
Gas GH_TwoAnd oxidizing gases such as oxygen and oxidizing compounds
The GOX will use the fuel car for convenience as
Called cartridge 11 and oxidant cartridge 13
I will. Fuel cartridge 11 and oxidizer cart
The ridge 13 is provided with gas passages 12 and 14, respectively.
And 50 kg / cm
^Two~ 100kg / cm^TwoFuel gas GH pressurized to a degree_Two,
And oxidant gas GOX can be sealed inside,
Filled fuel gas GH_TwoAnd oxidant gas GOX
To be discharged to the department. At the outlet of the gas passages 12 and 14, a valve 2 is provided.
Is provided, and on the outer peripheral surface outside the valve 2
A connection part 3 provided with a male screw is formed. On the other hand, fuel gas G
H_TwoAnd oxidant gas GOX are introduced, and a location (not shown)
Ignition of the combustor of a cut engine, generating combustion gas
LetIgnition tube4 has a connection with two female threads
Parts 41 and 42 are provided. And one connection
41 is screwed with the connecting portion 3 of the cartridge 1 to be integrated into one.
Cartridge 1Ignition tube4 and other
In one connection port 42,Ignition tubeFuel gas introduced in 4
GH_TwoAnd ignition for igniting oxidant gas GOX
Screwed in the same manner as the connecting portion 51 provided on the
TA5Ignition tube4 A rocket engine igniter according to the present embodiment
The fuel cartridge is constructed as described above.
The jaws 11 and the oxidant cartridge 13
50-100 kg / cm^TwoFuel gas of moderate pressure
SUGH_TwoAnd the oxidizing gas GOX are closed by closing the valve 2.
And the spill has been stopped, but the rocket engine igniter
When the fuel cell is used, opening the valve 2 allows the fuel
Cartridge 11 and oxidant cartridge 13
Combustion gas GH enclosed in each_TwoAnd oxidant gas GOX
Is a gas provided on each of the cartridges 11 and 13.
Through the passages 12 and 14 independentlyIgnition tubeIntroduced within 4
AndIgnition tube4 to form a combustible mixture. The combustible air-fuel mixture formed in the igniter cylinder 4
In addition, the flammable mixture
Aiki is ignited and becomes combustion gas CG. The combustion gas CG is
Ignition tube4Rocket engine fuel
Fuel introduced into the burner and separately introduced into the combustor
An ignition device that ignites the propellant gas mixed with an oxidizer
Act. As described above, the rocket engine of the present embodiment
The gin igniter is a fuel gas GH supplied into the igniter cylinder 4.
_Two, And oxidant gas GOX are enclosed inside in a gaseous state
Then, the connecting portion 3 is connected to the connecting portion 41 and directly attached to the ignition device tube 4.
Fuel cartridge 11 and oxidant cartridge
Conventional rocket engine ignition
Heat exchanger 03 and oxidant heat required by the heat exchanger
The heat exchangers 06 and 06 become unnecessary, and these heat exchangers 03 and 06 are used.
Cost required for these heat exchangers
If the work cost required for mounting 6 can be eliminated
In both cases, the weight of the rocket body can be reduced. The heat exchange of these heat exchangers 03,06
High-temperature rocket engine
Combustion gas and fuel gas GH_TwoOr combustion gas and oxidizer
The possibility of gas GOX mixing disappears,
The risk of destruction can be completely avoided. In addition, conventional
Fuel tube 01 needed for rocket engine igniter,
And the oxidizer tube 04 can be completely eliminated.
Cost of these fuel tubes 01, oxidizer tubes, or
Eliminate the work costs required to install them
And the weight of the rocket body can be reduced. Further, the fuel gas supplied to the ignition cylinder 4
GH_TwoAnd oxidizer gas GOX are supplied by rockets
Separate fuel cartridge from engine propulsion gas supply
Cartridge 11 and oxidant cartridge 13
Ignition of the igniter when the rocket engine starts up
The state is no longer affected. This allows the ignition state of the igniter
In order to maintain a stable state,
The system for starting the engine can be simplified, making setting difficult
The setting of the rocket engine sequence at the start was
It will be easier. Further, the fuel gas G supplied to the igniter cylinder 4
H_TwoAnd the oxidizer gas GOX are supplied by the fuel cartridge.
And the oxidizer cartridge 13
From the fuel gas GH_TwoAnd oxidant gas GOX easily
It becomes exchangeable. Next, FIG. 2 shows a rocket engine point of the present invention.
It is sectional drawing which shows 2nd Embodiment of a firearm. As shown in the figure, the rocket of the present embodiment
In the engine igniter, the fuel gas GH _TwoEncapsulating fuel
Cartridge 15 and an oxidizer gas for sealing the oxidizer gas GOX.
Cartridge 17 separately, and each cartridge 1
Valves at each of gas passage outlets 12, 14 of 5, 17
21 and 22 are provided, and the outside of the valves 21 and 22 is ignited.
Of the three connecting portions 43, 44, 45 provided in the barrel 4,
It is screwed and connected directly to the connecting parts 43 and 45 provided on both sides.
Like that. For this reason, an
Ita 5 is connected to the fuel introduced from the connecting portions 43 and 45, respectively.
Gas GH_TwoAnd the oxidizing gas GOX are mixed well
To the central connecting portion 44. In the rocket engine igniter of this embodiment,
Has the same function and effect as the first embodiment described above.
And this configuration
In the first embodiment, one valve 2 is sufficient.
However, there is a disadvantage that the two valves 21 and 22 increase.
On the other hand, fuel gas GH_TwoAnd oxidant gas GOX are valve 2
There is no risk of contamination on the upstream side of
Higher reliability compared to the first type
The advantage is obtained. [0032] As described above, the rocket energy of the present invention is
According to the engine igniter, according to the configuration shown in the claims.
The following effects can be obtained. (1) Cost required for equipment and equipment installation
Work costs can be reduced. (2) The rocket weight can be reduced and the payload can be increased.
The performance of the rocket can be improved. (3) The risk of destruction of a rocket engine or the like can be avoided,
Can be highly reliable. (4) The system for starting the engine can be simplified,
Rocket engine sequence can be easily set.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 shows a first embodiment of a rocket engine igniter according to the present invention.
FIG. 2 is a sectional view showing an embodiment. FIG. 2 is a second embodiment of the rocket engine igniter according to the present invention.
FIG. 3 is a cross-sectional view showing an embodiment. FIG. 3 is a side view showing a conventional rocket engine igniter. [Description of Signs] 1 Cartridge 11, 15 Fuel cartridge 12, 17 Fuel gas passage 13 Oxidant cartridge 14 Oxidant gas passage 2, 21, 22 Valve 3 Cartridge connection part 4 Ignition tube 41, 42, 43, 44, 45 Connection part 5 Exciter 51 Exciter connection part

Claims (1)

(57) [Claim 1] Combustion gas generated by introducing gasified fuel and oxidant into an igniter cylinder and igniting with an exciter installed in the igniter cylinder, In a rocket engine igniter for igniting a propellant gas introduced into a combustor of a rocket engine, a fuel cartridge connected to the igniter tube to supply the fuel gas enclosed therein to the igniter, A rocket engine igniter, comprising an oxidant cartridge for supplying the oxidant gas enclosed in the igniter into the igniter.