JPS6364896A - Attitude controller for space missile - Google Patents

Abstract

(57) [Abstract] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an improvement of an attitude control device for a spacecraft.

[Conventional technology]

FIGS. 4 and 5 show examples of attitude control devices that have been put into practical use. In the figure (11 is the spacecraft main body equipped with an attitude control device, (2) is a propellant controller that controls the flow of propellant, (3) is a propellant tank that stores propellant, (4)
is a propulsion device for changing the attitude of the spacecraft, and (5) is (
(4) is a propulsion device for changing the attitude of the spacecraft in the opposite direction, and (6) is a pipe for flowing propellant.

A conventional attitude control device is configured as described above.

When trying to control the attitude of the spacecraft (the propellant in the propellant tank 31 is controlled by the control device (2)), the attitude of the spacecraft is controlled by the thrust of the propulsion machine 4) and (5).

[Problem that the invention seeks to solve]

As mentioned above, conventional attitude control systems for spacecraft require propellant to be stored in the spacecraft in advance to obtain thrust for attitude control.

Propellant is consumed each time attitude control is performed, and if the propellant runs out, attitude control becomes impossible.

It no longer functions as a spacecraft. Therefore, the lifespan of a spacecraft in orbit depends on the amount of propellant, and if a long life is required, the weight of the propellant becomes very heavy.

This invention was made to solve this problem, and its purpose is to perform attitude control of a spacecraft without the need for propellant.

[Means for solving problems]

The attitude control device according to the present invention provides a rotational trick when plasma in outer space collides with a spacecraft flying in the plasma to generate braking force, and if the colliding surface is asymmetrical with respect to the center of gravity. Taking advantage of the fact that the equivalent collision cross section for plasma changes depending on the potential of the object that is generated and collides with it, a voltage is applied to a fixed electrode directly exposed to space.

By controlling the voltage, the attitude of the spacecraft is controlled.

[Function] In this invention, the only energy required for control 1ζ is electric power, which can be supplied from a solar cell in a spacecraft, and the life limit due to the propellant is fA < Y.
do.

〔Example〕

FIG. 1 is an external view showing one embodiment of the present invention, and FIG.
The figure is a block diagram thereof. (l) is the conventional one and all (
They are the same. (7) is a power source for applying voltage for posture control; (8) is an electrode for applying voltage to control posture; and (9) is an electric wire for transmitting electricity.

αl is a control device that selects the electrode to which a voltage is applied and further controls the voltage.

FIG. 3 is a diagram showing the interaction between the electrode (8) in FIG. 1 and plasma, where (8) is the electrode and αD is the plasma flow.

α2 is the equivalent collision cross section when a potential is applied.

In the attitude control device configured as described above.

When no voltage is applied to the electrode (8), the plasma flow a3 collides with the electrode (8), as shown in Fig. 3, 1b+, and the resulting torque exerted by the electrode (8) is the same, so the spacecraft is Maintain your posture.

By operating the control device Ql), one of the electrodes (8
), the plasma flow αυ of one electrode (8) collides with the other electrode (8) as shown in Figure 3, 1b+, and the plasma flow αυ becomes larger than the electrode (8). The collision will now occur with an equivalent collision cross section α.

The torque applied to one electrode (8) is greater than the other electrode (8) to which no voltage is applied, and a force is applied to the spacecraft 1ζ to change its attitude, and as a result, it is possible to control its attitude. Become.

Furthermore, by adjusting the applied voltage using the control device α, it is possible to control the magnitude of the posture control force.

〔Effect of the invention〕

In addition to the above, this invention is based on solar cells, etc. (because the attitude can be controlled by electric power, there is no need to use propellants that generate force for attitude control), and the weight of the spacecraft is reduced ( It is possible.

Furthermore, it becomes possible to significantly extend the life of a spacecraft, which was determined mainly by the amount of propellant, and contribute to the practical application and popularization of space vehicles.

[Brief explanation of drawings]

1 and 2 are diagrams showing one embodiment of the present invention, and FIG.
This figure shows the interaction between electrodes and plasma flow due to voltage application, and FIGS. 4 and 5 are diagrams showing a conventional attitude control device. In the figure, fil is the spacecraft body, and (2) is the propellant tank. (3) is a propellant tank, (4) and (5) are propulsion machines, (
6) is piping. (7) is the power supply, (8) is the electrode, (9) is the electric wire, Q(1
is a control device. αυ is the plasma flow, and α3 is the equivalent collision cross section. Note that the same line numbers in Figure 9 indicate the same or corresponding parts.

Claims (1)

[Claims] installed on a spacecraft so as to be directly exposed to outer space,
A plurality of electrodes located in different directions, a power source that applies voltage to the electrodes, and the fact that when voltage is applied to the electrodes, the equivalent collision cross section for plasma in space changes depending on the potential. and means for controlling the attitude of the spacecraft by controlling the voltage applied to the electrodes.