KR101059437B1 - Satellite attitude control device and method using solar panel - Google Patents

Abstract

The present invention is a support shaft which is installed on both sides of the satellite so as to be projected by the drive unit, the support member is installed on the outer end of the support shaft having at least one or more mounting surfaces, and installed on the mounting surface of the support member, It is characterized by consisting of a rotating motor connected to the panel to rotate the solar panel.

According to the present invention, by modifying the structure of the satellite solar panel drive device, a plurality of solar panels can be rotatably installed on both sides of the satellite, so that the attitude of the satellite can be controlled in three axes.

Satellites, solar panels, solar radiation, momentum dumping, thrusters, attitude control

Description

Satellite attitude control device and method using solar panel {MOTION CONTROL APPARATUS OF SATELLITE AND METHOD THEREOF USING SOLAR ARRAY}

The present invention relates to a satellite attitude control device using a solar panel and a method thereof, and more particularly, by modifying the structure of the satellite solar panel drive device, a plurality of solar panels can be rotatably installed on both sides of the satellite. The present invention relates to a satellite attitude control apparatus using a solar panel capable of controlling posture in three axes and a method thereof.

In general, when the satellite is launched and enters the satellite's operating trajectory, the attitude control of the satellite is performed so that a payload such as an antenna or a camera of the satellite is directed in the correct direction.

In addition, during the operation of the satellite, the position of the satellite becomes unstable due to solar radiation pressure (sun radiation pressure), micro atmospheric influence, etc., which may require adjustment.

As such, there is a fuselage fixation stabilization method of the attitude control method for positioning the correct direction in order to adjust the unstable posture of the satellite, this fuselage fixation is to maintain a stable posture of the satellite using the momentum wheel.

On the other hand, the calculation of the control amount for the attitude control of the satellite is generally performed by the pitch axis in the direction perpendicular to the orbit of the satellite, the yaw axis in the center of the earth direction, and the roll axis in the orbital propagation direction of the satellite. It is performed on the coordinate system which consists of three reference axes to distinguish.

1 is a conceptual diagram illustrating a conventional momentum wheel assembly for satellite attitude control.

Looking at the conventional momentum wheel assembly for satellite attitude control with reference to this figure, the first momentum wheel 20 and the pitch axis (installed on the same axis as the roll axis (x), which is installed on one area of the satellite 10) and a second momentum wheel 21 provided on the same axis as y) and a third momentum wheel 22 provided on the same axis as the yaw axis z.

The attitude control of the satellite 10 is performed by reaction torque generated by the speed change of the first, second, and third momentum wheels 20, 21, and 22.

That is, when the attitude of the satellite 10 becomes unstable, at least one of the first, second, and third momentum wheels 20, 21, 22 provided on the same axis as the roll axis x, the pitch axis y, and the yaw axis z. By changing one or more rotations, the attitude of the satellite 10 is controlled by the reaction torque.

However, when the momentum wheels 20, 21, 22 are out of a predetermined momentum range, the satellite 10 may not be fully controlled.

In this case, by using a thruster (not shown) installed in the satellite 10, the momentum of the momentum wheels 20, 21, 22 should be changed to a stable range, which is called momentum dumping.

The thruster is a small rocket engine that obtains propulsion by injecting a chemical reaction heat generated by the combustion of propellant and an oxidant and a hot gas decomposed through a nozzle. Momentum dumping is performed at the same time as the control.

As described above, when the thruster is used, the fuel of the satellite 10 is consumed, and since it is directly related to the life of the satellite 10, methods for reducing fuel consumption have been urgently needed.

Therefore, in recent years, a method of performing momentum dumping using a solar panel together with a momentum wheel assembly has been attempted.

Figure 2 shows a satellite attitude control device using a solar panel.

Referring to the drawing, referring to the satellite attitude control apparatus using a conventional solar panel, the solar panel is rotatably installed on the rotary motor 30 and the rotary motor 30 respectively installed on both sides of the satellite 10. It consists of 40.

In the conventional satellite attitude control apparatus as described above, when the attitude of the satellite 10 is changed, the attitude of the satellite 10 is changed by the difference in solar radiation pressure acting on each solar panel 40 by rotating the solar panel 40. To control.

For example, when the satellite 10 has a posture misaligned in one direction of the x-axis, the solar panel 40 in the opposite direction to the misaligned direction is directed toward the sun so that the solar radiation pressure acts on the front surface, and the sun in the misaligned direction. The attitude of the satellite 10 is controlled by rotating the panel 40 and moving the satellite 10 in a direction opposite to the direction in which the satellite 10 is twisted due to the difference in solar radiation pressure.

However, in the conventional satellite attitude control apparatus using the solar panel, since only one solar panel 40 is installed on each side of the satellite 10, the satellite 10 can be controlled in only one axis direction. There was a problem that can not be controlled in the three-axis direction.

The present invention is to solve the above problems, an object of the present invention is to change the structure of the satellite solar panel drive device to install a plurality of solar panels on both sides of the satellite rotatably, so that the satellite three-axis direction The present invention provides a satellite attitude control apparatus and method using a solar panel capable of controlling posture.

According to the present invention, the support shaft is installed on both sides of the satellite to be protruding by the drive unit, the support member is installed on the outer end of the support shaft and having at least one mounting surface, and the mounting surface of the support member Is installed in, but is connected to the solar panel is achieved by a rotating motor for rotating the solar panel.

In addition, the rotary motor may be composed of a first rotary motor and a second rotary motor installed on both sides of the support member so that the drive shaft is perpendicular to the support shaft.

Also, the axis in the longitudinal direction of the satellite is called the x axis, the axis perpendicular to the satellite longitudinal direction is called the y axis, the axis located at the top of the y axis parallel to the x axis is the x1 axis, and the axis located at the bottom of the y axis parallel to the x axis is x2. In the axis, the first and second solar panels are rotatable based on the x1 axis on both sides of the x1 axis, and the third and fourth solar panels are rotatable on the x2 axis, respectively, on both ends of the x2 axis. The satellite can be attitude controlled in the x, y, z axis direction as some or all are directed in the direction in which the solar radiation pressure acts.

In addition, directing the first and third solar panels in a direction in which the solar radiation pressure acts and rotate the second and fourth solar panels in different directions, or rotate the first and third solar panels in different directions and By directing the solar panels in the direction in which the solar radiation pressure acts, the satellites can be attitude controlled about the y axis.

In addition, the first and second solar panels are rotated in the same direction and the third and fourth solar panels are directed in the direction of the solar radiation pressure, or the first and the second solar panels in the direction of the solar radiation pressure. And by rotating the third and fourth solar panels in the same direction, the satellite can be attitude controlled about the x axis.

The first and second solar panels may be rotated in different directions, and the third and fourth solar panels may be rotated in opposite directions, but the first and third solar panels may be rotated in the same direction, and the second and fourth solar panels may be rotated. By rotating in the same direction with each other, the satellite can be attitude controlled relative to the z axis.

As a result, since a plurality of solar panels are rotatably installed on both sides of the satellite so that the satellite can be controlled in three axes, the satellite fuel is not used for the momentum dumping that can be performed even when the reaction torque is small. There is an effect to save.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described in detail with reference to the accompanying drawings.

In this case, the coordinate system shown in the drawing is located at the center of the satellite 100 and is shown only outside the satellite 100 for convenience of illustration, and the torques described below are rotated with respect to the center of the satellite 100. It means to generate.

Satellite attitude control device using a solar panel according to the present invention, as shown in Figure 3, the support shaft 200 is installed on both sides of the satellite 100, and is installed on the outer end of the support shaft 200 The support member 300 and the driving shaft are installed on both sides of the one support member 300 so as to be perpendicular to the support shaft 200, respectively, and are connected to the first solar panel 500 and the second solar panel 510, respectively. The first rotary motor 400 and the second rotary motor 410 for rotating the solar panel 500 and the second solar panel 510, and the other support member 300 of the driving shaft is perpendicular to the support shaft 200. A third rotating motor 420 installed at both sides and connected to the third solar panel 520 and the fourth solar panel 530 to rotate the third solar panel 520 and the fourth solar panel 530, and The fourth rotary motor 430 is configured.

First, the support shaft 200 is formed in a rod shape having a circular cross section is installed on both sides of the satellite 100, the outer surface of the satellite 100 by a drive unit (not shown) installed inside the satellite 100 As a reference, it is installed so that it can be sunk in and out of the satellite 100.

Here, the support shaft 200 is not limited to being formed in the shape of a rod having a circular cross section, and includes a rectangular or polygonal cross section.

In addition, the driving unit (not shown) includes all driving means (eg, a step motor, a cylinder, etc.) capable of allowing the support shaft 200 to be sunk into and out of the satellite 100.

The support shaft 200 is recessed into the interior of the satellite 100 to reduce the volume of the satellite 100 before the satellite 100 is launched, but when the satellite 100 is launched and climbs into orbit, the satellite is driven by the driving unit. Protrudes out of 100).

In addition, the support member 300 is formed in a hexahedral shape to have at least one or more installation surfaces, one surface of which is fixed to an outer end of the support shaft 200.

In the present embodiment, the support member 300 is described as being formed in a hexahedral shape, but includes all formed in a circular or polygonal shape.

On the other hand, the rotation motor is the first rotation motor 400 and the second rotation motor 410 is installed on both sides of the one side support member 300 so that the drive shaft is perpendicular to the support shaft 200, the drive shaft is the support shaft 200 ) Is composed of a third rotary motor 420 and a fourth rotary motor 430 which are installed on both sides of the other support member 300 to be perpendicular to.

The first to fourth rotary motors 400, 410, 420, and 430 installed as described above are connected to the first to fourth solar panels 500, 510, 520, and 530, respectively. Rotate 500, 510, 520, 530.

Here, when the axis in the longitudinal direction of the satellite 100 in the x-axis, the axis perpendicular to the satellite longitudinal direction in the y-axis, the axis perpendicular to the x-axis and the y-axis in the z-axis, when the satellite 100 is launched to the orbit x The satellite 100 is designed such that the axis is located on the same axis as the roll axis, the y axis is the pitch axis, and the z axis is the same axis as the yaw axis.

When the axis located at the top of the y axis in parallel with the x axis is referred to as the x1 axis, and the axis located at the bottom of the y axis in parallel with the x axis is referred to as the x2 axis, the first solar panel 500 and the second solar panel 510 are x1. The third solar panel 520 and the fourth solar panel 530 are installed to be positioned on the x2 axis.

Hereinafter, the operation of the satellite attitude control device using a solar panel according to the present invention will be described.

4 is a diagram illustrating a process of converting solar radiation pressure into force by reaching a solar panel.

With reference to this figure, the equation for obtaining the force for attitude control of the satellite 100 will be described.

First, the force of the solar radiation pressure on the solar panel can be obtained by multiplying the solar panel area (SAcosθ) perpendicular to the sun and the solar radiation pressure, and this value (Fp) is parallel to the force (Fn) perpendicular to the solar panel You have to redistribute the components by force (Ft).

This is because the vertical force and the horizontal force are calculated differently by the rate (υ) at which the solar particles are reflected on the solar panel.

In other words, the vertical force is expressed as the sum of the solar particles because the incident direction and the reflection direction are opposite to each other on the surface of the solar panel, and the horizontal force is the same as the incident direction and the reflection direction. Is displayed.

The above principle is expressed by the following equation.

In order to obtain the force for the attitude control of the satellite 100 from the above two forces, each component is calculated to obtain two new forces Fy and Fz.

Fy is a force required for attitude control of the satellite 100 with respect to the yaw axis, and Fz is a force required for attitude control of the satellite 100 with respect to the roll axis and the pitch axis.

The component is calculated and expressed as follows.

The attitude control of the satellite 100 is performed by the forces Fz and Fy acting on the solar panel by the solar radiation pressure obtained as described above.

Hereinafter, a method of controlling the attitude of the satellite 100 using the satellite attitude control device using the solar panel will be described.

Portions overlapping each other according to each example in which the satellite 100 is attitude controlled will be omitted.

First, as shown in FIG. 5, the first and third solar panels 500 and 520 are oriented in the direction in which the solar radiation pressure is applied, and the second and fourth solar panels 510 and 530 are rotated in different directions. When the first and third solar panels 500 and 520 are rotated in different directions and the second and fourth solar panels 510 and 530 are oriented in a direction in which solar radiation pressure is applied, the satellite 100 is based on the y axis. Posture is controlled.

For example, the first solar panel 500 and the third solar panel 520 are oriented in the direction in which the solar radiation pressure is applied, and the second solar panel 510 is formed in the negative direction with respect to the x axis. 4 When the solar panel 530 is rotated in the (+) direction, the force difference occurs depending on the area of the solar panel perpendicular to the solar radiation pressure, and the satellite 100 has the first and third suns based on the y axis. A positive pitch torque that tries to rotate toward the panels 500, 520 occurs. (+,-Are determined by the right hand coordinate system.)

That is, only Fz acts on the first solar panel 500 and the third solar panel 520, but Fz and Fy act simultaneously on the second solar panel 510 and the fourth solar panel 530. Since the Fz acting on the 500 and the third solar panel 520 is larger than the Fz acting on the second solar panel 510 and the fourth solar panel 530, the satellite 100 has the first solar panel based on the y axis. And rotates toward 500 and the third solar panel 520.

At this time, Fy acts on the second solar panel 510 and the fourth solar panel 530, but because they act in opposite directions, the z-axis torques cancel each other so that the satellite 100 does not rotate about the z-axis. .

The satellite 100 is attitude-controlled based on the y-axis by the force as described above.

Of course, when the first solar panel 500 and the third solar panel 520 are rotated in different directions, the second solar panel 510 and the fourth solar panel 530 are oriented in a direction in which the solar radiation pressure is applied. It is natural that the satellite 100 rotates toward the second and fourth solar panels 510 and 530 so that a negative pitch torque is generated.

In addition, as shown in FIG. 6, the first and third solar panels 500 and 520 are oriented in the direction in which the solar radiation pressure is applied, and the second and fourth solar panels 510 and 530 are rotated in the same direction. When the first and third solar panels 500 and 520 are rotated in the same direction, and the second and fourth solar panels 510 and 530 are oriented in the direction in which the solar radiation pressure is applied, the satellite is based on the y and z axes. Posture is controlled.

For example, the first solar panel 500 and the third solar panel 520 are oriented in the direction in which the solar radiation pressure is applied, and the second solar panel 510 and the fourth solar panel 530 are (−). In the case of rotating in the direction of force), a force difference occurs depending on the area of the solar panel placed perpendicular to the solar radiation pressure, and the satellite 100 tries to rotate toward the first and third solar panels 500 and 520 based on the y axis. A positive pitch torque is generated.

That is, only Fz acts on the first solar panel 500 and the third solar panel 520, but Fz and Fy act simultaneously on the second solar panel 510 and the fourth solar panel 530. Since the Fz acting on the 500 and the third solar panel 520 is larger than the Fz acting on the second solar panel 510 and the fourth solar panel 530, the satellite 100 has the first solar panel based on the y axis. And rotates toward 500 and the third solar panel 520.

In addition, since Fy acting on the second solar panel 510 and the fourth solar panel 530 acts in the same direction, the satellite 100 generates the same torque with respect to the z-axis so that the satellite 100 is also referred to the z-axis. Posture is controlled.

The satellite 100 is attitude-controlled based on the y-axis and the z-axis by the action of the force as described above.

In addition, as shown in FIG. 7, the first and second solar panels 500 and 510 are rotated in the same direction, and the third and fourth solar panels 520 and 530 are oriented in the direction in which the solar radiation pressure is applied. If the first and second solar panels 500 and 510 are oriented in the direction in which the solar radiation pressure is applied, and the third and fourth solar panels 520 and 530 are rotated in the same direction, the satellite 100 is in an attitude based on the x axis. Controlled.

For example, the first solar panel 500 and the second solar panel 510 are rotated in the (-) direction with respect to the x-axis, and the third solar panel 520 and the fourth solar panel 530 are rotated. When the solar radiation pressure is directed in the direction in which the solar radiation pressure is applied, the force difference occurs according to the area of the solar panel placed perpendicular to the solar radiation pressure, and the satellite 100 has the third and fourth solar panels 520 and 530 based on the x-axis. (+) Roll torque that tries to rotate toward) occurs.

That is, only Fz acts on the third solar panel 520 and the fourth solar panel 530, but Fz and Fy act simultaneously on the first solar panel 500 and the second solar panel 510. Since the Fz acting on the 520 and the fourth solar panel 530 is larger than the Fz acting on the first solar panel 500 and the second solar panel 510, the satellite 100 has a third solar panel based on the x-axis. 520 and the fourth solar panel 530 is rotated.

In this case, Fy acts on the first solar panel 500 and the second solar panel 510 in the same direction, but torques are generated in different directions with respect to the z-axis so that the satellite 100 does not rotate about the z-axis. do.

The satellite 100 is attitude-controlled based on the y-axis by the force as described above.

Of course, when the third solar panel 520 and the fourth solar panel 530 are rotated in the same direction, the first solar panel 500 and the second solar panel 510 are directed in the direction in which the solar radiation pressure acts. It is natural that the satellite 100 rotates toward the first and second solar panels 500 and 510 so that a negative roll torque is generated.

In addition, as shown in FIG. 8, the first and second solar panels 500 and 510 are rotated in different directions, and the third and fourth solar panels 520 and 530 are oriented in the direction in which the solar radiation pressure is applied. When the first and second solar panels 500 and 510 are directed in the direction in which the solar radiation pressure is applied, and the third and fourth solar panels 520 and 530 are rotated in different directions, the satellite 100 has the x axis and the z direction. It is attitude controlled about the axis.

For example, by rotating the first solar panel 500 in the (-) direction with respect to the x axis, the second solar panel 510 is rotated in the (+) direction, and the third solar panel 520 and the fourth sun. When the panel 530 is oriented in the direction in which the solar radiation pressure acts, the force difference occurs depending on the area of the solar panel perpendicular to the solar radiation pressure, and the satellite 100 has the third and fourth suns based on the x-axis. Positive roll torque is generated that attempts to rotate toward the panels 520, 530.

That is, only Fz acts on the third solar panel 520 and the fourth solar panel 530, but Fz and Fy act simultaneously on the first solar panel 500 and the second solar panel 510, thereby causing the third solar panel. Since the Fz acting on the 520 and the fourth solar panel 530 is larger than the Fz acting on the first solar panel 500 and the second solar panel 510, the satellite 100 has the third solar axis based on the x-axis. It rotates toward the panel 520 and the fourth solar panel 530.

In addition, the Fy acting on the first solar panel 500 and the second solar panel 510 acts in different directions, but torques are generated in the same direction with respect to the z-axis, so that the satellite 100 also has a posture based on the z-axis. Controlled.

The satellite 100 is attitude-controlled based on the x-axis and the z-axis by the action of the force as described above.

9, the first and second solar panels 500 and 510 are rotated in different directions, and the third and fourth solar panels 520 and 530 are rotated in different directions, respectively. When the three solar panels 500 and 520 are rotated in the same direction and the second and fourth solar panels 510 and 530 are rotated in the same direction, the satellite is attitude-controlled based on the z axis.

For example, the first solar panel 500 and the third solar panel 520 are rotated in the (+) direction, and the second solar panel 510 and the fourth solar panel 530 are rotated in the (−) direction. In the case of rotation by, the positive yoke torque is generated by Fy generated by all solar panels because both Fz and Fy acting on the solar panel exist but Fz cancels each other.

Therefore, the satellite 100 is not attitude controlled on the x-axis or the y-axis, but only on the z-axis.

It is to be understood that both the foregoing general description and the following detailed description of the present invention are exemplary and explanatory and are intended to provide further explanation of the invention as claimed. It will be understood that various changes and modifications may be made without departing from the scope of the present invention.

1 is a conceptual diagram illustrating a conventional moment wheel assembly.

2 is a front view showing a satellite attitude control device using a conventional solar panel.

Figure 3 is a perspective view of the satellite attitude control apparatus using the solar panel installed on the satellite installed in the present invention.

4 is a diagram showing that the solar radiation pressure acts on the satellite solar panel.

5 to 9 are operational state diagrams of the satellite attitude control device using a solar panel according to the present invention.

<Description of the symbols for the main parts of the drawings>

 10: satellite 20: the first momentum wheel

 21: second momentum wheel 22: third momentum wheel

 30: rotating motor 40: solar panel

100: satellite 200: support shaft

300: support member 400: first rotation motor

410: second rotation motor 420: third rotation motor

430: fourth rotation motor 500: the first solar panel

510: second solar panel 520: third solar panel

530: fourth solar panel

Claims (6)

delete delete The axis in the satellite longitudinal direction is referred to as the x axis, the axis perpendicular to the satellite longitudinal direction is called the y axis, the axis located at the top of the y axis parallel to the x axis is referred to as the x1 axis, and the axis located at the bottom of the y axis parallel to the x axis is called the x2 axis. When the first and second solar panels are rotatable based on the x1 axis at both ends of the x1 axis, and the third and fourth solar panels are rotatable based on the x2 axis at both ends of the x2 axis. Satellite attitude control method using a solar panel, characterized in that the satellite is attitude-controlled in the x, y, z-axis direction as a part or all of the solar panel is directed in the direction of the solar radiation pressure. The method of claim 3, Directing the first and third solar panels in a direction in which solar radiation pressure is applied and rotating the second and fourth solar panels in different directions, or rotating the first and third solar panels in different directions and A satellite attitude control method using a solar panel, characterized in that the satellite is attitude-controlled based on the y-axis by directing the solar panel in the direction of the solar radiation pressure. The method of claim 3, Rotate the first and second solar panels in the same direction and orient the third and fourth solar panels in the direction of solar radiation pressure, or direct the first and second solar panels in the direction of solar radiation pressure and 3,4 Satellite attitude control method using a solar panel, characterized in that the satellite is attitude-positioned on the x-axis by rotating the solar panels in the same direction. The method of claim 3, Rotate the first and second solar panels in different directions and rotate the third and fourth solar panels in different directions, rotate the first and third solar panels in the same direction and rotate the second and fourth solar panels in the same direction. A satellite attitude control method using a solar panel, characterized in that the satellite is attitude-controlled based on the z-axis by rotating in the direction.

Images