JP2882938B2 - Rocket engine injector - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rocket engine having a throttling function, which is capable of extremely low thrust in space, and is most suitable for lunar landers, Mars landers, and other propulsion means for space station docking. Related to an injector for use.

[0002]

2. Description of the Related Art FIG. 4 is a system diagram of a single element variable injector according to a conventional throttling type rocket engine. An oxidant flow control valve (movable) 4 and a fuel flow control valve (movable) 5 are provided downstream of the oxidant main valve 6 and the fuel main valve 7, and the flow control is performed here.

[0003] In addition, 8 is an injector, 9 is a combustion chamber,
An actuator 11 drives the oxidant main valve 6 and the fuel main valve 7.

[0004]

The above-mentioned conventional rocket engine injector has the following problems to be solved.

That is, the conventional rocket engine injector having a throttling function has a problem that its performance is inferior because it has only a single injection port.

An object of the present invention is to provide a rocket engine injector having a plurality of fuel and oxidizer injection ports and an injection means capable of simultaneously adjusting the injection amount.

[0007]

According to the present invention, there is provided a rocket engine injector for combusting a fuel and an oxidant into a combustion chamber while injecting the fuel and an oxidant thereof in an adjustable manner in order to solve the above-mentioned problem. the injection port with each plurality comprising, from the same time a very small amount injection quantity from the injection port
It is possible to continuously adjust up to a large amount and
The amount of thrust generated can be adjusted to any size
Is intended to provide a rocket engine injector, characterized by comprising comprises injection means that.

[0008]

The present invention is configured as described above and has the following effects.

That is, since a plurality of fuel injection ports and an oxidant injection port, each of which can simultaneously adjust the injection amount, are provided, the propellant such as the fuel and the oxidant is evenly dispersed in the combustor. The combustion in the vessel is performed uniformly, and the combustion efficiency is improved.

Further, by controlling a plurality of injection ports simultaneously, it is possible to control the thrust without sacrificing performance.

Further, since the amount of the propellant can be adjusted simultaneously for a plurality of ports , the combustion control can be performed uniformly and accurately by the homogeneous propellant, and the thrust is required in space.
Adjust from very low thrust to very high thrust
And the adjustment of the magnitude of the thrust can be performed continuously .

[0012]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described with reference to FIGS. Note that the same reference numerals are given to constituent members having the same functions as those of the conventional example, and description thereof will be omitted unless necessary.

FIG. 1 is a schematic longitudinal sectional view of this embodiment, FIG. 2 is an enlarged view of an injector 8a of FIG. 1, FIG. 3 is a main component of FIG.
That is, it is a diagram of two surfaces (side cross section and lower surface) of the oxidant flow control valve 4a and the fuel flow control valve 5a.

In these figures, 1 is an injection surface of the injector 8a, 2 is an oxidizing agent injection hole formed in a plurality of holes in the main body of the injector 8a, and 3 is a cross-section of a plurality of local arrangements of the oxidizing agent injection hole 2. In the form of a plurality of fuel injection holes (FIG. 2B), a plurality of fuel injection holes 4a are formed concentrically on the surface of the disk body, and are cylindrically shaped in the direction of the injection surface 1. Oxidant flow control valve having fluid holes opened in the openings (FIGS. 3A and 3B), 5
Reference numeral a denotes a fuel flow control valve having a plurality of annular concentric tubes having fluid holes formed in the direction of the injection surface 1 at substantially equal intervals along each circumference thereof, and 10 denotes a propellant tank. Other configurations are the same as those of the conventional example, although there are some differences in shape and the like corresponding to the state of the mounting position and the like.

1 and 2, the oxidant flow control valve 4a and the fuel flow control valve 5a are driven (moved) up and down by the actuator 11 with respect to the main body of the injector 8a. It is configured.

The oxidant and fuel ejected from the oxidant flow control valve 4a and the fuel flow control valve 5a into the injector 8a are injected into the combustion chamber 9 from the oxidant injection hole 2 and the fuel injection hole 3, respectively. It is configured to:

FIG. 3 (a) is a side sectional view thereof.
The oxidant flow control valve 4a is integrally formed as shown in FIG. 3 (b), and its side cross section is shown in FIG. 3 (c).
As shown in (d), the fuel flow control valve 5a is also integrally formed as shown in the bottom view, and is configured so that the respective flow rates can be surely adjusted simultaneously.

Next, the operation of the above configuration will be described.

In FIG. 1, the propellant is pumped from a propellant tank 10, passes through an oxidizer main valve 6 and a fuel main valve 7, and is injected into an injector 8a.
The fuel is further injected into the combustion chamber 9 to perform combustion. The oxidant flow control valve 4a and the fuel flow control valve 5a are located downstream of the oxidizer main valve 6 and the fuel main valve 7, and the opening degree changes the flow rate of the propellant, thereby changing the thrust.

Also, these two oxidizing agent flow control valves 4
a, the fuel flow control valve 5a is driven by the actuator 11.

These oxidant flow control valves 4 shown in FIG.
a, details of the injector 8a including the fuel flow control valve 5a are shown in FIG.
Shown in The oxidant flow control valve 4a and the fuel flow control valve 5a simultaneously change the area of the plurality of oxidant injection holes 2 and the fuel injection holes 3 to control the flow rate.

As described above, according to the present embodiment, a large number of oxidizing agent injection holes which are arranged concentrically and evenly on the injection surface 1 by the oxidizing agent flow control valve 4a and the fuel flow adjusting valve 5a which move up and down. Since the propellant (fuel and oxidant) is injected from the fuel injection hole 2 and the fuel injection hole 3, the propellant is distributed in the combustion chamber 9 at a uniform concentration, and the combustion is performed homogeneously. However, there is an advantage that the combustion efficiency is improved and the thrust is increased.

In this embodiment, as compared with the conventional example having a single injection port, substantially the same amount of propellant is used for a large number of oxidizing agent injection holes 2.
And the fuel is injected by the fuel injection holes 3 so that the injection holes 1
The injection amount per piece is extremely small, and therefore, the lower limit of the flame maintaining ability is extremely small, and there is an advantage that the control lower limit of combustion and, therefore, the control lower limit of thrust remarkably increases (decreases). Further, since the combustion efficiency is increased as described above, the thrust is correspondingly increased, and there is an advantage that the upper limit of the thrust is increased.

Further, since the flow rate per injection port is significantly reduced, there is an advantage that the accuracy of flow rate adjustment is increased and the thrust can be controlled accurately over a wide range.

[0025]

The present invention has the following effects because it is configured as described above.

That is, since a plurality of (many) injection ports of fuel and oxidant are provided and injection means capable of adjusting their flow rates at the same time are provided, the flow rate of the propellant can be accurately controlled, and furthermore, the propellant can be continuously controlled. Can be changed, and the accuracy of thrust control is improved.

Further , the flow rates of the fuel and the oxidizing agent are simultaneously adjusted.
To be injected into the combustion chamber.
Fuel to oxidizer ratio also varies with flow rate adjustment
It not, it is the injection of a homogeneous propellant, combustion efficiency is up,
Thrust increases.

[0028] by trace injection control propellant, it is generated and control of very small thrust, a plurality (multiple
To increase the opening by simultaneous adjustment of
Therefore, generation and control of an extremely large thrust can be performed.

[Brief description of the drawings]

FIG. 1 is a schematic longitudinal sectional view of a rocket engine injector according to one embodiment of the present invention,

FIGS. 2A and 2B are enlarged views of the injector 8a of FIG. 1, wherein FIG. 2A is a side sectional view, FIG.

FIGS. 3A and 3B are two side views of an oxidant flow control valve 4a and a fuel flow control valve 5a (hereinafter, only symbols are referred to) in FIG. 2, wherein FIG. 3A is a side sectional view of 4a [aa in FIG. (B) is a bottom view of 4a, (c) is a side sectional view of 5a (c- in (d)).
(equivalent to arrow c), (d) is a bottom view of 5a,

FIG. 4 is a longitudinal sectional view of a conventional example.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Injection surface 2 Oxidant injection hole 3 Fuel injection hole 4a Oxidant flow control valve 5a Fuel flow control valve 6 Oxidant main valve 7 Fuel main valve 8a Injector 9 Combustion chamber 10 Propellant tank 11 Actuator

Claims (1)

(57) [Claims] 1. A rocket engine injector to burn while injecting fuel into the combustion chamber and oxidant injection quantity adjustable, the injection port of fuel and oxidizing agent with each plurality comprising, injection from the injection ports Is the amount very small at the same time ?
To the combustion chamber.
The amount of thrust to be generated
Rocket engine injector, characterized by comprising comprises Kill injection means.