JPH04257800A - Direction variable thruster device - Google Patents

Abstract

PURPOSE:To simplify equipment, to save space, and to reduce weight by providing a module structure wherein the given number of gas injection nozzles of a plurality of gas injection nozzles are pointed to directions different from each other, a piping through which gas is fed to the module structure, and solenoid valves independently feeding and shutting off gas to a plurality of the respective gas injection nozzles. CONSTITUTION:Gas for a thruster is fed to a module structure 1 through a piping 3 for feeding gas. To generate a force through injection of gas through a plurality of injection nozzles 6, the given number of which is pointed to directions different from each other, of the module structure 1, a solenoid valve 4 is first opened to introduce gas to the interior of the module structure 1. The solenoid valve 2 of the injection nozzle 6 in a direction in which a force generated under above state is exerted is opened for a necessary time to generate a given force by means of which gas is injected. When gas is simultaneously injected through a plurality of the injection nozzles 6, the solenoid valve 2 of the corresponding injection nozzle 6 is opened. An opening and closing signal for the solenoid valve 2 is generated by means of electric wiring.

Description

[Detailed description of the invention]

0001

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a thruster device that is applied to spacecraft, rockets, etc. and is capable of varying the direction of force.

0002

[Prior Art] A conventional thruster device used in a spacecraft, rocket, etc. consists of a thruster structure consisting of a thruster nozzle, etc., an electromagnetic valve, and gas supply piping, as shown in Fig. 4, and can generate gas with one device. The force was limited to one direction only. In addition, (a) of FIG. 4 is a side view, (b)
is a view taken along arrow B in (a).

0003

SUMMARY OF THE INVENTION The conventional thruster device described above has the following problems to be solved.

That is, in conventional thruster devices, each device has one injection port, and the force that can be generated is limited to only one direction, that is, the direction of the injection port. To obtain this power, it was necessary to install a large number of these thruster devices. For example, to control rotational motion in three axes, it is necessary to install at least six thrusters. Also, in order to control rotation and translation at the same time,
Furthermore, it is necessary to add at least six thrusters. In this case, a large number of thruster devices are required for each part of the spacecraft, and this requires a large number of piping and wiring to the thruster devices, making the equipment complex and requiring a large amount of installation space, which is disadvantageous in terms of weight. There was a problem.

[0005] In order to solve the above-mentioned problems, the present invention uses a thruster device having a plurality of injection ports in different directions in one device, thereby creating a module that can generate force in multiple directions with one device. The purpose of this project is to provide a variable-direction thruster device that can significantly reduce the number of thrusters installed on spacecraft, etc., simplify equipment, save space, reduce weight, and is easy to repair and replace. do.

[0006]

[Means for Solving the Problems] As a means for solving the above problems, the present invention provides a thruster device that generates force for controlling the motion of spacecraft, rockets, etc. by injecting gas. A module structure with the required number of injection ports facing in different directions, piping that supplies gas to the module structure, and gas supplied from the piping to each of the plurality of gas injection ports. It is an object of the present invention to provide a variable direction thruster device characterized by being equipped with an electromagnetic valve that can be supplied and cut off independently.

[0007]

[Operations] Since the present invention is constructed as described above, it has the following functions.

That is, in a module structure in which a required number of gas injection ports are provided facing in different directions,
A gas supply pipe is provided, and a solenoid valve is installed so that the gas supplied from the same pipe can be independently supplied to and shut off from each injection port. If you open the valve only for the required amount of time,
Gas is injected from the nozzle and obtains the required force in that direction. Therefore, different forces can be obtained in desired directions. For example, when gas is to be simultaneously injected from a plurality of injection ports to control the motion of a spacecraft, each electromagnetic valve of the corresponding injection port is opened.

[0009]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Variable direction thruster devices according to first and second embodiments of the present invention and examples of their use will be explained with reference to FIGS. 1 to 3. Note that the same reference numerals are given to the same constituent members as in the previous embodiment, and the explanation thereof will be omitted.

First, a first embodiment will be explained with reference to FIG. Figure 1 is a diagram of this embodiment, where (a) is a side view and (b) is a side view.
) is a cross-sectional view taken along line B-B in FIG.

In FIG. 1, 1 has a cubic shape, and five of its six sides are provided with injection ports 6, which will be described later, for a total of five.
2 is an electromagnetic valve provided at each injection port 6 that can freely shut off and supply gas; 3 is a gas supply for supplying gas for injection to the module structure 1; 4 is a solenoid valve that is interposed between the module structure 1 and the gas supply pipe 3 to supply and shut off gas to the module structure 1 by opening and closing the same, 5 is a solenoid valve 4 and the module The connection part 6 with the structure 1 is an injection jet provided on all the six sides of the module structure 1 except for one side to which the gas supply piping 3 etc. is connected, that is, one on each of the five sides. This is an injection port for generating force. Note that the module structure 1 is not limited to a cubic shape, but may be spherical, cylindrical, or any other suitable shape.

Next, the operation of the above structure will be explained. In FIG. 1, gas for the thruster is supplied to the module structure 1 through a gas supply pipe 3. In order to generate force by injecting gas from the injection port 6 present in the module structure 1, the electromagnetic valve 4 is first opened to introduce gas into the module structure 1. In this state, if the electromagnetic valve 2 attached to the injection port 6 in the direction in which the desired force is to be generated is opened for the required time, gas is injected and the required force is obtained. For example, when injecting gas from a plurality of injection ports 6 at the same time to control the motion of a spacecraft equipped with the variable direction thruster device of this embodiment, the electromagnetic valve 2 of each corresponding injection port 6 is opened. . Note that the opening/closing signal for the electromagnetic valve 2 is provided from outside the present embodiment by electrical wiring (not shown).

If any abnormality or failure occurs in the module structure 1 and it needs to be repaired or replaced, it can be easily done by closing the electromagnetic valve 4 and removing only the module structure 1 at the connection part 5. can be done.

Next, a second embodiment will be explained with reference to FIG. FIG. 2 is a diagram of the second embodiment, where (a) is a side view and (b) is a side view.
) is a cross-sectional view taken along line B-B in FIG.

In the first embodiment, one module structure 1 is provided with five injection ports 6, whereas in the second embodiment, the module structure 1a is provided with 10 injection ports (two in groups on each surface). do)
This is an example including the injection port 6. Each component is the same as in the first embodiment. According to this embodiment, by changing the number of open (operated) electromagnetic valves 2 to 0, 1, and 2 for the two injection ports 6 that are paired on each side of the module structure 1a,
It has the advantage that the magnitude of the force can also be changed. Although this embodiment is an example in which two injection ports 6 are provided on each surface of the module structure 1a, two or more injection ports 6 may be provided as necessary. In that case, there is an advantage that the magnitude of the force on each surface can be further diversified.

FIG. 3 is an explanatory diagram of the case where the first or second embodiment described above is installed on a spacecraft as a reference example. Translational and rotational motion control is performed by installing a total of 20 conventional thruster devices. In this case, if the variable direction thruster device of the first or second embodiment is installed, the purpose can be achieved with four pieces because they are modularized. In this case, there is an advantage that the mounting position can be selected flexibly compared to an example using a conventional thruster device.

As described above, according to the first and second embodiments,
A plurality of injection ports 6 are attached to one module structure 1, 1a in different directions, and this is used as a directionally variable force generation unit, that is, it is modularized and used in a spacecraft, etc. Compared to conventional thruster devices that generate force in only one direction, this has the advantage that the number of thrusters can be significantly reduced. Furthermore, since it is modularized, it has the advantage that only one installation work is required, whereas conventional equipment requires multiple installation work.

Furthermore, since it is modularized, there is an advantage that only one space is required for equipment, as opposed to the plurality of equipment spaces that were conventionally required.

[0019] Further, by modularization, the plurality of injection ports 6 can be compactly integrated, which has the advantage of reducing weight.

Furthermore, modularization has the advantage that maintenance is easy because a plurality of injection ports 6 can be removed from a spacecraft or the like at the same time for inspection, repair, replacement, etc.

[0021]

Effects of the Invention Since the present invention is constructed as described above, it has the following effects.

(1) A plurality of injection ports provided in one module structure injects gas in multiple directions by independently controlling the opening and closing of each electromagnetic valve, thereby simultaneously injecting gas in multiple directions. can generate force.

(2) Since it is constructed as a module structure having a plurality of injection ports, the number of thrusters to be attached to a spacecraft or the like can be significantly reduced, and equipment can be simplified, space saved, and weight reduced. Also, the selection of mounting position is flexible.

(3) By closing the electromagnetic valve of the gas supply piping and attaching and detaching the module structure at the connecting portion, repair and replacement of each module becomes easy.

(4) If a plurality of injection ports are arranged in a specific direction within one module structure,
The amount of gas ejected can be adjusted by changing the number of openings of each electromagnetic valve, and the level of force in the same direction can be changed.

[Brief explanation of the drawing]

FIG. 1 is a diagram of a directionally variable thruster device according to a first embodiment of the present invention, in which (a) is a side view, (b) is a sectional view taken along line B-B in (a), and (c) is (a). ) is a view taken in the direction of arrow C.

FIG. 2 is a diagram of a directionally variable thruster device according to a second embodiment of the present invention, in which (a) is a side view, (b) is a view taken along the line B-B in (a), and (c) is a view in (a). FIG.

FIG. 3 is an explanatory diagram showing, for reference, a case in which the first or second embodiment is installed on a spacecraft.

FIG. 4 is a diagram of a conventional thruster device, in which (a) is a side view;
(b) is a view taken along arrow B in (a).

[Explanation of symbols]

1, 1a Module structure 2 Solenoid valve 3 Gas supply piping 4 Solenoid valve 5 Connection part 6 Injection port

Claims (1)

[Claims] Claim 1: A thruster device that generates force for controlling the motion of a spacecraft, rocket, etc. by injecting gas, in which a required number of gas injection ports are provided facing in different directions. the module structure, a pipe that supplies gas to the module structure, and an electromagnetic valve that can independently supply and shut off the gas supplied from the pipe to each of the plurality of gas injection ports. A directionally variable thruster device characterized by: