JPH0455917A - Attitude controller applying magnetic moment - Google Patents

Abstract

PURPOSE:To quickly control the attitude of an artificial satellite by providing a magnetic core and the 1st and 2nd coils wound round the magnetic core orthogonally to each other. CONSTITUTION:The 1st and 2nd coils 1 and 2 are wound round the outer circumference of a magnetic core 4 having an external shape of a rectangular parallelepiped with the center axes of both cores set orthogonal to each other. At the same time, the core 4 has the permeability of mu. When the currents I1 and I2 are supplied to both coils 1 and 2, a torque T is produced to the core 4 to the axes of both coils 1 and 2. Therefore the torque T can be optionally set when the directions of the currents flowing to both coils 1 and 2 are inverted to each other. Then the value of the torque T can be optionally changed according to the levels of the currents supplied to both coils 1 and 2. Thus it is possible to quickly control the attitude of a space flying object like an artifical satellite, etc.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an attitude control device, and more particularly to an attitude control device that utilizes a magnetic moment.

[Conventional technology]

This type of attitude control device that uses conventional magnetism is
There is an attitude control device that passes current through a loop-shaped coil and uses the magnetic field generated by this current.

For example, such a conventional attitude control device that uses magnetism is mounted on an artificial satellite that navigates around the earth, and when a current is passed through this coil, a magnetic field is generated between the earth's magnetism and the current flowing through this coil. The satellite's attitude was controlled by torque.

[Problem to be solved by the invention]

Since the above-described conventional attitude control device uses the earth's magnetism, it generates a small amount of torque and has the disadvantage that it takes a long time to control the attitude of the artificial satellite using the attitude control device.

Furthermore, since the direction of the geomagnetic field near the earth is oriented in a specific direction depending on the position, there is a drawback that the required torque cannot be generated in any direction at any time.

Furthermore, when attempting to use such an attitude control device that uses geomagnetism on board a spacecraft that travels extremely far from the Earth, there is a drawback that it cannot be used because the geomagnetism is extremely small. was there.

An object of the present invention is to provide an attitude control device that does not have such drawbacks.

[Means to solve the problem]

An attitude control device using a magnetic moment according to the present invention is characterized by comprising a magnetic core, and first and second coils wound orthogonally to each other around the magnetic core.

〔Example〕

Next, the present invention will be explained with reference to the drawings.

FIG. 1 is a block diagram of an embodiment of the present invention, and FIG. 2 is a block diagram of a case where three attitude control devices of the present invention shown in FIG. 1 are used.

As shown in FIG. 3, when a current I is passed through a coil 3 with one turn wound in one plane, and the magnetic moment at the center O of the coil 3 generated by this current I is Pm, then Pm is perpendicular to the plane formed by the coil 3, is proportional to the magnitude of the current flowing through the coil 3, and points in the direction shown.

θ of the magnetic field H at a point Q that is separated by a distance Nr from the center O of the coil and makes an angle θ with the direction of the above-mentioned magnetic moment Pm.
The directional component Hθ can be expressed by the following formula.

Hθ=Pm−SIN(θ)/(4πμr”) Also, point Q
The magnetic field component Hr in the r direction is expressed by the following relational expression.

Hr=Pm -CO3(θ)/(4πμr3) However,
μ indicates the magnetic permeability of the material existing around the coil 3.

The magnetic field components Hθ and Hr are orthogonal to each other, and the magnetic field H is a vectorial combination of these magnetic field components.

As shown in FIG. 4, there are a first coil 1 and a second coil 2 wound with conductive material wires in two planes perpendicular to each other. Assume that electric currents 1 and 2 are applied to coil 1 and second coil 2, respectively, in the directions shown. Further, let R be the distance between the centers of these coils 1 and 2.

When a current 1 is flowing through the first coil 1, the magnetic moment generated by the first coil 1 is Pl, and similarly when a current I2 is flowing through the second coil 2, the magnetic moment generated by the first coil 1 is Pl. Let the generated magnetic moment be P2,
Let Hl and H2 be the magnetic fields generated by these magnetic moments P1 and P2, respectively.

The torque T1 acting on the first coil 1 due to the magnetic moment P1 generated by the coil 1 and the magnetic moment P2 generated by the coil 2 is expressed by the following equation.

TI=[Pl-P2/(4πμR3)] Similarly, the torque T2 acting on the coil 2 is expressed by the following equation.

T2=T1 where μ is the magnetic permeability of the material inside and around coils 1 and 2.

The direction of the torque T1 is perpendicular to the magnetic moment P1 and also perpendicular to the magnetic field H2 generated in the plane of the winding of the first coil 1 by the second coil 2, and the direction of the torque T1 is perpendicular to the magnetic moment P1 and also perpendicular to the magnetic field H2 generated in the plane of the winding of the first coil 1 by the second coil 2. When rotated, this right-handed thread occurs in the advancing direction.

This torque T1 causes the first coil 1 to receive a force that causes it to rotate clockwise around the torque T1.

Similarly, the torque T2 has a direction in which it advances when the right-handed screw is rotated from the direction of the magnetic moment P2 toward the direction of the magnetic field H2 generated on the inner surface of the second coil 2 by the magnetic moment P1.

Due to the torque T2, the second coil 2 receives a force that causes it to rotate clockwise around the torque T2.

The total torque T generated by passing current through these two first coil 1 and second coil 2 is as shown below.

T=271 =2P1・P2/(4πμR3) FIG. 1 is a block diagram showing an embodiment of the present invention.

The windings of the first coil 1 and the second coil 2 are wound around the outer periphery of a magnetic core 4 whose outer shape is a rectangular parallelepiped so that their central axes are orthogonal to each other.

Further, the magnetic permeability of the above-mentioned magnetic core 4 is μ.

When electric currents 1 and 12 are applied to the first coil and the second coil as shown in the figure, the torque T generated in the magnetic core 4 is generated in the direction shown in the figure.

That is, the direction of the torque T is a direction perpendicular to the axis of the first coil 1 and the axis of the second coil 2 described above.

The direction of the torque T can be arbitrarily set by reversing the directions of the currents flowing through the first coil 1 and the second coil 2 described above.

Further, the magnitude of the torque T can be set to an arbitrary value depending on the magnitude of the current flowing through the first coil 1 and the second coil 2.

Although the embodiment shown in FIG. 1 uses a magnetic core having a cubic outer shape, the outer shape of the magnetic core 4 may be spherical, for example.

In addition, in the embodiment shown in FIG. 1 described above, the first coil 1 and the second coil 2 each have a single winding, but these coils have multiple windings, each of which is arranged in one plane. As is clear from the previous explanation, the attitude control device using the magnetic moment shown in Fig. 1 is fixed to the main body of an artificial satellite, and the first By passing current through the coil 1 and the second coil 2, the attitude of the above-mentioned artificial satellite can be changed around an axis perpendicular to the plane formed by the coils 1 and 2.

Figure 2 uses three attitude control devices shown in Figure 1 above.
2 is a configuration diagram showing a case where it is fixed on an artificial satellite body 20. FIG.

All units 10 to 12 are the same as the attitude control device shown in FIG.

When current is passed through the first coil 1 and second coil 2 of these units 10 to 12, the directions of torque generated by each unit are Tx, Ty, and Tz, respectively.

These torque directions Tx, Ty, and Tz are made parallel to the three axes X, Y, and Z, which are orthogonal to each other, respectively.
By fixing each of the above-mentioned units 10 to 12 on the satellite main body 20 and appropriately setting the current flowing through the first coil 1 and second coil 2 provided in each of these units, this artificial satellite can be constructed. It is clear from the above explanation that the attitude of the object can be controlled in any direction.

Note that by using superconducting materials for each of the first coil 1 and the second coil 2, it is possible to realize an attitude control device using magnetic moment with extremely low power consumption.

〔Effect of the invention〕

As explained above, by mounting the attitude control device using the magnetic moment of the present invention on a spacecraft such as an artificial satellite, the attitude of the above-mentioned spacecraft can be controlled regardless of the presence or absence of geomagnetism. .

Further, the attitude control device using the magnetic moment of the present invention can be operated even in outer space where there is no earth's magnetism.

As is clear from the embodiment shown in FIG. 2 described above, by attaching three attitude control devices using the magnetic moment of the present invention to a space vehicle such as an artificial satellite, the attitude of this artificial satellite can be adjusted arbitrarily. can be controlled in the direction of

[Brief explanation of drawings]

Fig. 1 is a block diagram of an embodiment of the present invention, Fig. 2 is a block diagram showing a case where three posture control devices of the present invention shown in Fig. 1 are used, and Fig. 3 is a block diagram showing the configuration of an embodiment of the present invention. FIG. 4 is an explanatory diagram showing the relationship between current, magnetic moment, and magnetic field, and FIG. 4 is an explanatory diagram of the torque acting between two coils. 1...first coil, 2...second coil, 3...
・Coil, 4...Magnetic core, 10-12...Unit,
20...Satellite body.

Claims (1)

[Claims] 1. An attitude control device using a magnetic moment, comprising a magnetic core and first and second coils wound orthogonally to each other around the magnetic core. 2. Two or three posture control devices according to claim 1 are provided,
An attitude control device using a magnetic moment characterized in that the directions of the torques generated by each of these attitude control devices are arranged orthogonal to each other.