JPH08288732A - Device for adjusting pointing direction of antenna - Google Patents

Abstract

PURPOSE: To improve the increment of weight of an adjusting device for adjusting the antenna pointing direction of a space navigation body, the reduction of load resistance performance and the reduction of rigidity of a mechanical part by arranging the adjusting device on a position having high having high affinity with the structure of the antenna. CONSTITUTION: After turning a stored antenna to the deployed state by a rotational driving mechanism 21 fixed to a satellite constituting body 1, an error around a yawing axis against a directional error is adjusted by a rotary shaft constituted of the mechanism 21 and a yawing hinge 22. An error around a roll axis is adjusted by moving an arm 25 by a rotational driving mechanism 23, vertically moving the strud end of an antenna 2 and rotating the antenna 2 around a roll hinge 24. The above constitution eases the concentration of the adjusting device into the antenna 2 or between the interface panels of the satellite and the reduction of load resistance performance against load applied to the adjusting device and the reduction of rigidity in a system due to the narrow span of supporting point can be improved.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an antenna pointing direction adjusting device for finely adjusting the pointing direction of an antenna communication beam of a so-called space navigation body such as a space shuttle or artificial satellite.

[0002]

2. Description of the Related Art An antenna mounted on an artificial satellite or the like is folded and housed in a satellite structure at the time of launch, as shown in FIG. In order to actually communicate with the ground, it is necessary to deploy the antenna as shown in FIG. In order to enable communication for antennas deployed in outer space,
It is necessary to direct the communication beam of the antenna to the ground station S on the earth E shown in FIG. The error in the pointing direction of the communication beam of the antenna is caused by the antenna expansion as shown in FIG. 12 and the deformation of the antenna reflector due to the on-orbit thermal deformation. Usually, a satellite is equipped with multiple communication antennas, and the deployment angle cannot be latched at a normal position during deployment, and the antennas are misaligned as shown in FIG. When the pointing direction changes due to the deformation of the reflector, the communication beam of the antenna causes a pointing error as shown in FIG. Conventionally, as a method of correcting this type of pointing error, the attitude angles of the satellites are adjusted so that the communication beams of the plurality of antennas do not impair the communication performance, or as shown in FIGS. 13 and 14. The directivity adjustment device was installed to adjust the directivity of the antenna individually. 11, FIG. 12, FIG. 13, and FIG.
In 4 a reference numeral 1 is a satellite structure, 2 is an antenna reflector, 3
Is a hinge for deploying the antenna reflector 2, and 4 is a feed for transmitting and receiving a communication beam. In FIGS. 13 and 14, 5 is an antenna pointing direction adjusting device in which two sets of rotary drive mechanisms that can rotate on the roll axis and yaw axis of the satellite are combined, and 6 is an antenna interface panel for mounting the deployment hinge 3 of the antenna. , 7 is a satellite interface panel for mounting an antenna pointing device,
Reference numeral 8 denotes an antenna pointing direction adjusting device in which two sets of translational drive mechanisms rotatable about the roll axis and the yaw axis of the satellite are combined.

The device shown in FIG. 15 has the structure shown in FIG.
It is an example of the antenna pointing direction adjusting device 5 in which a pair of rotary drive mechanisms is combined. Reference numeral 9 is a rotary type drive mechanism for driving a rotary axis c for adjusting the pointing direction corresponding to the satellite yaw axis,
Reference numeral 0 is a rotary drive mechanism for driving a rotary shaft d for adjusting the pointing direction corresponding to the satellite roll axis, and 11 is a yoke 11 connecting the drive mechanisms 9 and 10 described above.

Next, the operation will be described. The apparatus shown in FIG. 15 is equipped with the rotary drive mechanisms 9 and 10 that can be driven independently in response to the pointing error generated after the antenna is deployed, and thereby acts to cancel the pointing error that has occurred. Further, FIG. 16 shows the arrangement of the degrees of freedom of the device 5.
It can be seen from FIG. 16 that the device shown in FIG. 15 has a system rigid body number n of 3 and a system constraint degree of freedom r of 10. The degree of freedom of the system can be defined as "Equation 1".

[0005]

[Equation 1]

Therefore, it is understood that the degree of freedom of the device 5 is calculated as in "Equation 2" and the degrees of freedom corresponding to the pitch axis and the yaw axis are secured.

[0007]

[Equation 2]

The apparatus shown in FIG. 17 is an antenna in which a translational drive mechanism capable of being independently driven corresponding to a pointing error generated after antenna deployment is combined with two translational drive mechanisms as shown in FIG. It is an example of the pointing device 8. 12 is an actuator with a rotating lead screw, 1
Reference numeral 3 denotes a lead bush portion of the actuator 12 for receiving the lead screw portion, and the screw portion is rotatably incorporated (corresponding to symbol S) with respect to the surroundings, and 14 supports the lead bush 13 rotatably (corresponding to the symbol K). Upper support that is driven in the vertical direction (corresponding to symbol E), 15 is a lower support that rotatably supports the actuator 12 part (corresponding to symbol C), 16 is the lower support 15 that rotates with respect to the satellite interface panel 7. Flexible (corresponding to symbol K)
The lower support leg 17 supports the upper support leg 17 for rotatably supporting the antenna interface panel 6 (corresponding to the symbol K), and the reference numeral 18 rotatably supports the support 19 for the satellite interface panel 7 ( A support leg 20 that supports the symbol support) and a mount 20 that is rotatably (corresponding to the symbol U) supported by the mounting support 19 on the antenna interface panel 6.

Next, the operation will be described. The device shown in FIG. 17 is equipped with a translational drive mechanism that can be independently driven in response to the pointing error generated after the antenna is deployed, and thereby acts to cancel the pointing error that has occurred. For example, to cancel the pointing error around the yaw axis, the actuator 12 is rotated in the same direction and the upper support 14 is moved up and down with respect to the mount 20. To cancel the pointing error around the roll axis, the actuators 12 are rotated in the opposite directions, and the upper supports 14 connected to each other are moved so that one side is on top and the other is on the mount 20. By rotating it. Also, FIG.
8 shows the degree of freedom of the device 8. 18 to 17, the system shown in FIG. 17 has a rigid body number n of 4 and a constraint degree of freedom r of the system of 16
It turns out that Therefore, it is understood that the number of degrees of freedom of the device 8 is calculated as in "Equation 3" and the degrees of freedom corresponding to the pitch axis and the yaw axis are secured.

[0010]

(Equation 3)

[0011]

[Problems to be Solved by the Invention]
In the device shown in (1), the mounting interface of the antenna pointing direction adjusting device is separated from the antenna structure, and the weight increase is remarkable because it is performed via the antenna interface panel and the satellite interface panel.

Further, in the conventional devices shown in FIGS. 13 and 14, the antenna pointing direction adjusting device is concentrated between the antenna interface panel and the satellite interface panel, so that the antenna pointing direction adjusting device acts at the time of launch or in orbit. Load resistance performance against the applied load decreases,
There is a problem that it is difficult to reduce the rigidity of the system because a member is inserted between the antenna structure and the antenna pointing direction adjusting device or the span of the supporting point is narrow.

The present invention has been made to solve the above-mentioned problems, and when the antenna pointing direction adjusting device is installed, the affinity with the antenna structure is enhanced and the function is shared with the antenna deploying hinge part. Accordingly, it is an object of the present invention to realize a structure that suppresses an increase in weight as much as possible, improves load bearing performance, and also reduces rigidity reduction.

[0014]

An antenna pointing direction adjusting device according to the present invention deploys an antenna at a position where a conventional antenna deploying hinge is located in order to enhance compatibility with an antenna structure. A mechanism for canceling the pointing error after that is provided.

Further, a mechanism for canceling the pointing error is provided at a position located between the antenna deploying structure and the antenna reflector structure, which is located before the antenna deploying hinge.

[0016]

According to the present invention, the antenna has a high affinity with the antenna structure and can be deployed, and in order to cope with the canceling of pointing error, the antenna pointing direction adjusting device is provided at the position where the antenna deploying hinge is located or the antenna deploying structure. By providing it at a position located between the antenna reflector structures, it is possible to improve the increase in weight, the decrease in load bearing performance, and the decrease in mechanism rigidity that occur due to the cancellation of pointing errors. The disadvantages of the pointing device can be eliminated.

[0017]

【Example】

Example 1. FIG. 1 shows an antenna pointing direction adjusting device which is capable of adjusting the beam pointing direction of the antenna by equipping the structural material that connects the antenna and the artificial satellite structure with two sets of rotary drive mechanisms that can rotate about the roll axis and yaw axis of the satellite. It is a figure which shows an example. Reference numeral 21 in the drawing denotes a rotary drive mechanism a for performing an operation around the yaw axis including antenna deployment, and 22 denotes the rotary drive mechanism a.
21 a yaw hinge equipped with a spherical bearing whose axis coincides with the axis of rotation of 21 and serves as a structural interface with the satellite structure 1.
Reference numeral 3 is a rotary drive mechanism b, which is fixed to the output shaft of the rotary drive mechanism a21 and is used to perform an operation around the roll axis. Reference numeral 24 is a bearing which is connected to the shaft portion of the yaw hinge and serves as one structural interface of the antenna reflector. Is attached to the roll hinge, and 25 is the rotary drive mechanism b23.
Is an arm that is fixed to the output shaft of the antenna reflector and is rotatable about one of the structural interfaces of the antenna reflector about the roll axis and is slidable along a member sandwiching the axis.

FIG. 2 shows a layout of degrees of freedom of the above antenna pointing direction adjusting device. It can be seen from FIG. 2 that the device shown in FIG. 1 has a rigid body number n of 5 and a constraint degree of freedom r of 22. Therefore, it is understood that the degree of freedom of the apparatus of FIG. 1 is calculated as in "Equation 4" and the degrees of freedom corresponding to the pitch axis and the yaw axis are secured.

[0019]

[Equation 4]

Further, FIG. 3 shows a structural example of a mechanical portion of the antenna pointing direction adjusting device. According to the antenna directivity adjusting device configured as shown in the drawing, when the antenna 2 in the housed state is deployed, first, the rotary drive mechanism a21 that operates around the yaw axis (corresponding to symbol S) is operated. This puts the antenna in a deployed state. After that, with respect to the generated pointing error, the error about the yaw axis is adjusted by the rotary shaft (corresponding to the symbol S) composed of the rotary drive mechanism a21 and the yaw hinge 22 to which the spherical bearing is mounted similarly to the expansion. With respect to the error around the roll axis, the rotation drive mechanism b23 is rotated (corresponding to symbol T) to move the arm 25, and the arm 25 is freely rotatable (corresponding to symbol H) and slides along the arm. Possible (corresponding to the symbol)
Move the straddle end of the antenna 2 built in to up and down. By this operation, the antenna 2 is rotated around the roll hinge 24 (corresponding to the symbol te) and adjusted.

Example 2. In the first embodiment described above, the case where the rotary drive mechanism is used for canceling the error around the roll axis has been described, but in the present embodiment, the case where the actuator uses the translational drive mechanism will be described. FIG. 4 is a diagram showing an example in which a rotary drive mechanism that can rotate the yaw axis of the satellite is provided in the structural material that connects the antenna and the satellite structure, and a translational drive mechanism that moves the antenna straddle up and down is provided on the output shaft. Is. In the figure, 26 is a translational drive mechanism a for moving the antenna straddle up and down, 27 is a plate to which the lead bush 13 is rotatably attached, and 28 is a joint that rotatably connects the plate and the straddle of the antenna 2.

FIG. 5 shows a layout of degrees of freedom of the above antenna pointing direction adjusting device. It can be seen from FIG. 5 that the device shown in FIG. 4 has a rigid body number n of 4 and a constraint degree of freedom r of the system of 16. Therefore, it can be seen that the degree of freedom of the apparatus of FIG. 4 is calculated as in the above “Equation 3” and the degrees of freedom corresponding to the pitch axis and the yaw axis are secured.

FIG. 6 shows a structural example of the mechanical section of the above antenna pointing direction adjusting device. According to the antenna directivity adjusting device configured as shown in the figure, when the antenna 2 in the housed state is deployed, first, the rotary drive mechanism 17 that operates around the yaw axis is operated (corresponding to symbol S). This puts the antenna in a deployed state. After that, with respect to the generated pointing error, the error around the yaw axis is adjusted by the rotary shaft (corresponding to the symbol S) that is composed of the rotary drive mechanism 21 and the yaw hinge 22 with the spherical bearings similarly to the expansion. I do. Regarding the error around the roll axis, by operating the translational drive mechanism a22 fixed to the output shaft of the rotary drive mechanism 21, the lead bush 13 and the plate 27 are moved.
Moves up and down (corresponding to symbol G), and moves the straddle end of the antenna 2 up and down through a joint 28 (corresponding to symbol 2). This operation causes the antenna 2 to roll the roll hinge 24.
It is rotated around (corresponding to the symbol te) and adjusted.

Example 3. In the above-described first and second embodiments, the case where the antenna pointing direction adjusting device is provided at the position where the conventional antenna deployment hinge is located has been described, but in the present embodiment, the antenna deployment structure and the antenna reflector ahead of the antenna deployment hinge are described. A case where the antenna pointing direction adjusting device is provided at a position located between the straddle structures will be described. FIG. 7 is a diagram showing an example of a configuration of the above antenna pointing direction adjusting device in which two sets of rotary drive mechanisms that are rotatable about a roll axis and a yaw axis are provided. Reference numeral 29 in the figure denotes an antenna deployment structure that is deployed by the antenna deployment hinge 3 and supports the antenna 2. The antenna pointing direction adjusting device 5 in the figure has the same degree of freedom configuration as the device presented in FIGS. 13 and 15, and the number of rigid bodies n of the system is 3 and the constraint degree of freedom r of the system is 10. I understand. Therefore, FIG.
The degree of freedom of the device is calculated as in the above "Equation 2", and the degrees of freedom corresponding to the pitch axis and the yaw axis are secured.

FIG. 8 shows a structural example of the above antenna pointing direction adjusting device. According to the antenna directivity adjusting device configured as shown in the drawing, since the expansion hinge 3 is used when the antenna 2 in the housed state is expanded, it is operated only in accordance with the directivity error of each axis generated after the expansion. It However, in the antenna directivity adjusting device according to the present embodiment, the installation position is located between the antenna deployment structure 29 and the straddle structure of the antenna reflector 2 as compared with the antenna directivity adjusting device shown in the conventional example. Since an interface can be constructed so that the load path is clear and the span of the rotating part of the mechanism can be widened, the load resistance can be improved. Reference numeral 30 in the figure denotes an output shaft interface connected to the straddle structure of the antenna reflector 2.

Example 4. In the third embodiment described above, the case where the antenna directivity adjusting device is equipped with two sets of rotatable drive mechanisms of the roll axis and the yaw axis has been described.
In this embodiment, a case where the antenna directivity adjusting device is equipped with two sets of translational drive mechanisms will be described. FIG. 9 is a diagram showing an example of the configuration of the above antenna pointing direction adjusting device in which two sets of translational drive mechanisms are provided. Reference numeral 25 in the figure denotes an antenna deployment structure that is deployed by the antenna deployment hinge 3 and supports the antenna 2. The antenna pointing direction adjusting device 8 in the figure has the same degree of freedom configuration as the device shown in FIGS. 14 and 17, and the number of rigid bodies n of the system is 3 and the constraint degree of freedom r of the system is 10. I understand. Therefore, FIG.
The degree of freedom of the device is calculated as in the above "Equation 2", and the degrees of freedom corresponding to the pitch axis and the yaw axis are secured.

FIG. 10 shows a structural example of the above antenna pointing direction adjusting device. According to the antenna directivity adjusting device configured as shown in the drawing, since the expansion hinge 3 is used when the antenna 2 in the housed state is expanded, it is operated only in accordance with the directivity error of each axis generated after the expansion. It However,
In the antenna directivity adjusting device according to the present embodiment, compared with the antenna directivity adjusting device shown in the conventional example, the installation position is located between the antenna deployment structure 29 and the straddle structure of the antenna reflector 2, so that the load Since an interface can be constructed so that the route is clear and the span of the mechanism can be widened, load bearing capacity can be improved.

[0028]

Since the present invention is configured as described above, when canceling the pointing error of the antenna, the antenna pointing direction adjusting device has high affinity with the antenna structure and the antenna deploying hinge is located. It is possible to improve the weight increase of the antenna directivity adjusting device, the reduction of load bearing performance, and the reduction of mechanism rigidity by installing it in the position where it is located or between the antenna deployment structure and the antenna reflector structure. Has the effect of

[Brief description of drawings]

FIG. 1 is a diagram showing an embodiment in which two sets of rotary drive mechanisms according to the first embodiment of the present invention are provided and an antenna pointing direction adjusting device is configured.

FIG. 2 is a diagram showing a degree-of-freedom layout according to the first embodiment of the present invention.

FIG. 3 is a diagram showing a configuration example of a mechanical portion of the antenna directivity adjusting device according to the first embodiment of the present invention.

FIG. 4 is a diagram showing an embodiment in which an antenna directivity adjusting device is configured by combining a rotary drive mechanism and a translational drive mechanism according to a second embodiment of the present invention.

FIG. 5 is a diagram showing a degree-of-freedom layout according to a second embodiment of the present invention.

FIG. 6 is a diagram showing a configuration example of a mechanism portion of an antenna pointing direction adjusting device according to a second embodiment of the present invention.

FIG. 7 is a view showing an embodiment in which an antenna pointing direction adjusting device is configured by being installed between an antenna structure and an antenna deploying structure according to a third embodiment of the present invention and equipped with two sets of rotary drive mechanisms. .

FIG. 8 is a diagram showing a configuration example of a mechanical portion of an antenna pointing direction adjusting device according to a third embodiment of the present invention.

FIG. 9 is a diagram showing an embodiment in which an antenna pointing direction adjusting device is configured by being installed between an antenna structure and an antenna deploying structure according to a fourth embodiment of the present invention and equipped with two sets of translational drive mechanisms. .

FIG. 10 is a diagram showing a configuration example of a mechanical portion of an antenna directivity adjusting device according to a fourth embodiment of the present invention.

FIG. 11 is a diagram showing an example of a storage state of a conventional antenna on an artificial satellite.

FIG. 12 is a diagram showing an example of a conventional antenna deployment and pointing error.

FIG. 13 is a diagram showing an embodiment in which two sets of rotary drive mechanisms are provided in the conventional antenna pointing direction adjusting mechanism to configure an antenna pointing direction adjusting device.

FIG. 14 is a diagram showing an embodiment in which two sets of rotary type drive mechanisms are provided in the conventional antenna pointing direction adjusting mechanism to configure the antenna pointing direction adjusting device.

FIG. 15 is a diagram showing an example of the configuration of a mechanical section that constitutes an antenna directivity adjusting device by equipping a conventional antenna directivity adjusting mechanism with two sets of rotary drive mechanisms.

FIG. 16 is a diagram showing a degree-of-freedom layout according to an embodiment of a mechanical section that constitutes an antenna directivity adjusting device by equipping the conventional antenna directivity adjusting mechanism with two sets of rotary drive mechanisms.

FIG. 17 is a diagram showing an example of the configuration of a mechanical section that constitutes an antenna directivity adjusting device by equipping a conventional antenna directivity adjusting mechanism with two sets of translational drive mechanisms.

FIG. 18 is a diagram showing a degree-of-freedom layout according to an embodiment of a mechanism section that is provided with two sets of translational driving mechanisms and constitutes an antenna pointing direction adjusting device in the conventional antenna pointing direction adjusting mechanism.

[Explanation of symbols]

1 satellite structure, 2 antenna reflectors, 3 hinges,
4 feed, antenna directivity adjusting device combining 5 sets of rotary drive mechanism, 6 antenna interface panel, 7 satellite interface panel, 8 2
Antenna directivity adjusting device combining a set of translational drive mechanisms, 9 yaw axis rotary drive mechanism, 10 roll axis rotary drive mechanism, 11 yoke, 12 actuator, 13
Lead bush, 14 upper support, 15 lower support, 16 lower support leg, 17 upper support leg, 18 support leg, 19 support, 20 mount, 21 rotary drive mechanism a, 22
Yaw hinge, 23 Rotational drive mechanism b, 24 Roll hinge, 25 Arm, 26 Translational drive mechanism a, 27
Plate, 28 joints, 29 antenna deployment structure, 30 output axis interface, angle deviation, a-directional error, rotation axis corresponding to yaw axis, rotation axis corresponding to roll axis, upper support 14 vertical movement direction, cover
Upper support 14 rotation support direction, upper support leg 17 rotation support direction, actuator 12 rotation support direction, lower support leg 16 rotation support direction, co-mount 20 rotation support direction, support leg 1
9 rotation support direction, cylinder bush rotation direction, sway axis rotation direction, pitch axis rotation direction, roll axis rotation direction, rotation rotation mechanism b23 rotation direction, antenna 2 strage end rotation direction, two arms 25 sliding direction, terro hinge rotation direction, g translational drive mechanism a22 drive direction, knurled bush 13 rotation direction, two joint 28 rotation direction, E earth, S ground station.

Claims (4)

[Claims] 1. A device provided in an antenna of a space navigation body for finely adjusting the pointing direction of a communication beam emitted from the antenna on orbit when performing communication, wherein the antenna and the space navigation body are connected. An antenna characterized in that the structural material is equipped with two sets of rotary drive mechanisms that can rotate on the roll axis and the yaw axis of the space navigation body, and the antenna can be deployed and the beam pointing direction of the antenna can be adjusted. Directional adjustment device. 2. An apparatus provided in an antenna of a space navigation body for finely adjusting the pointing direction of a communication beam radiated from the antenna on orbit when performing communication, wherein the antenna and the space navigation body are connected. An antenna pointing direction adjusting device, characterized in that a structural type is combined with a rotary type drive mechanism and a translational type drive mechanism capable of rotating about a roll axis and a yaw axis of a spacecraft. 3. A device provided in an antenna of a space navigation body for finely adjusting the pointing direction of a communication beam radiated from the antenna on orbit when performing communication, wherein the antenna and the space navigation body are connected. The structure has an antenna deployment hinge, and two sets of rotary drive mechanisms rotatable about the roll axis and the yaw axis of the space navigation body are provided between the antenna reflector rear surface and the antenna reflector deployment structure located ahead of the hinge. The antenna pointing direction adjusting device is characterized in that the beam pointing direction of the antenna can be adjusted. 4. A device provided in an antenna of a space navigation body for finely adjusting the pointing direction of a communication beam radiated from the antenna when performing communication on orbit, wherein the antenna and the space navigation body are connected. The structure has an antenna deployment hinge, and two sets of translational drive mechanisms rotatable about the roll axis and the yaw axis of the space navigation body are provided between the antenna reflector rear surface and the antenna reflector deployment structure located ahead of the hinge. The antenna pointing direction adjusting device is characterized in that the beam pointing direction of the antenna can be adjusted.