JPH01249597A - Attitude control device - Google Patents

Abstract

PURPOSE:To contrive the extension of a life by constituting a device equipping a space navigating vehicle in its peripheral part with a sun light reflective object, provided to be movably adjustably arranged being opposed facing to the sun, and moving this object to be adjusted variably controlling incident light. CONSTITUTION:When a receiving part 15 inputs orbital information from a ground station or from another satellite, the receiving part 15 outputs this orbital information to a control arithmetic part 14 and an operation scheduler 17, and it plans a long period orbital control program in accordance with the orbital information, obtaining an orbital control amount in every orbital turn to be output to the arithmetic part 14. Simultaneously the arithmetic part 14 inputs the orbital information from the receiving part 15 and attitude information from a sensor part 16, and these orbital information and attitude information create a drive signal corresponding to the orbital control amount from the scheduler 17, controlling drive parts 13,... to be selectively driven responsively to this drive signal. Here because the driving parts 13,... control sun light reflective objects 11a... to be moved and an incident amount of sun energy, a sun light reflective object group 11 generates control force and control torque for controlling an orbit of the satellite and its attitude.

Description

DETAILED DESCRIPTION OF THE INVENTION [Object of the Invention] (Industrial Application Field) The present invention relates to an attitude control device used to control the orbit and attitude of a spacecraft such as a geostationary satellite.

(Prior Art) Conventionally, this type of attitude control device has been used to control the trajectory and attitude of the attitude control device. A propellant is used as the JJ source, and the necessary control force and control torque are obtained by controlling the injection of this propellant.

However, because the above-mentioned attitude control device uses propellant, which is a consumable item, as its driving source, its lifespan varies depending on the amount of propellant carried, so the propulsion rate varies depending on the spacecraft on which it is carried. The handling of the medicine was extremely troublesome because the amount of medicine had to be taken into account.

(Problems to be Solved by the Invention) As mentioned above, in the conventional attitude control device, the lifespan is determined by the amount of propellant loaded, which is subject to restrictions, and its handling is extremely troublesome. Ta.

This invention has been made in view of the above circumstances, and aims to provide an attitude control device that has a simple configuration and has a long service life without using consumables such as propellants. .

[Structure of the Invention] (Means for Solving the Problems) The present invention provides an attitude control device for controlling the orbit and attitude of a spacecraft, which adjusts the movement of the spacecraft so that its peripheral portion faces the sun. The spacecraft is equipped with freely disposed solar reflectors, and is configured to control the orbit and attitude of the spacecraft by moving and adjusting the solar reflectors to variably control incident light.

(Function) According to the above configuration, a controlling force for orbit control and a control torque for attitude control are applied to the spacecraft by the solar energy incident on the sunlight reflecting object.

Therefore, orbit correction and attitude control can be realized without using consumables such as propellants as in the past. This makes it possible to achieve as long a lifespan as possible and contribute to extending the lifespan of the spacecraft.

(Example) Hereinafter, an example of the present invention will be described in detail with reference to the drawings.

FIGS. 1 and 2 show an attitude control device according to an embodiment of the present invention, in which, for example, four sets of solar reflector groups 11 for orbit and attitude control are provided around the satellite main body 1o. is arranged via a support mechanism 12 (see FIG. 2). In this solar reflecting object group 11, solar reflecting objects 11a, each called a solar sail, are arranged at predetermined intervals, and receive solar energy to provide control force and attitude control necessary for orbit correction. Generates the necessary control torque. Each of the sunlight reflecting objects 11a of this sunlight reflecting object group 11 is connected to the support mechanism 12 through the driving section 13...
It is rotatably supported so that its movement can be freely adjusted. A control calculating section 14 is connected to each of the driving sections 13, and a first input terminal of the control calculating section 14 is connected to an output terminal of a receiving section 15 for receiving orbit information. The second input terminal of the control calculation section 14 is connected to the output terminal of a sensor section 16 for detecting attitude angle and attitude change rate, and the third input terminal is connected to the output terminal of the operation scheduler 17. is connected.

This operation scheduler 17 is connected to the receiving section 15, calculates an orbit error based on the orbit information, and outputs it to the control calculation section 14.

In the above configuration, when controlling the attitude of a satellite, first, orbit information is input to the receiving section 15 from a ground station or another satellite. Then, the receiving unit 15 outputs the orbit information to the control calculation unit 14 and the operation scheduler 17. The operation scheduler 17 formulates a long-term orbit control plan according to the orbit information, determines the orbit control fam for each orbit, and outputs it to the control calculation unit 14. At the same time, the control calculation unit 14 receives orbit information from the reception unit 15 and attitude information from the sensor unit 16, and outputs a drive signal that corresponds to the orbit information and attitude information from the operation scheduler 17 in the orbit control layer. and in response to this drive signal, the drive unit 13.
... selectively drive and control.

Here, the drive unit 13... is connected to each sunlight reflecting object 11a...
The amount of solar energy incident on the sunlight reflecting object 11a is controlled by controlling the movement of. As a result, the sunlight reflecting object group 11 generates control force and control torque for controlling the orbit and attitude of the satellite from solar energy, thereby controlling the orbit and attitude of the satellite.

In this way, the above-mentioned attitude control device disposes the solar reflecting object group 11 in a movable and adjustable manner around the satellite body 10, and variably controls the incident solar energy by adjusting the movement of the solar reflecting object group 11. By doing so, the control force for orbit control and the control torque for attitude control of the satellite are obtained. According to this, the lifespan is extended as much as possible by using infinitely usable solar energy as the drive source for attitude control, without using conventional consumables such as propellants. can be achieved. As a result, it can be applied to long-life satellites without special consideration, and
Improved handling is achieved as much as possible.

In the above embodiment, the sunlight reflecting object group 11, which is a combination of a plurality of sunlight reflecting objects 11a, is arranged at the 4B location, but the number is not limited to this. It is also possible to construct it using materials, and it is possible to form various arrangements and arrangements depending on the spacecraft used. Therefore, it goes without saying that the present invention is not limited to the above embodiments, and that various modifications can be made without departing from the spirit of the invention.

[Effects of the Invention] As detailed above, the present invention provides an attitude control device that does not use consumables such as propellants, has a simple configuration, and has a long service life. Can be done.

[Brief explanation of the drawing]

FIG. 1 is a circuit configuration diagram showing an attitude control device according to an embodiment of the present invention, and FIG. 2 is a diagram showing the arrangement of sunlight reflecting objects in FIG. 1. 10... Satellite main body, 11... Solar reflecting object group, 11
a...Solar reflector, 12...Support mechanism, 13...
- Drive section, 14... Control calculation section, 15... Receiving section,
16...Sensor unit, 17...Operation scheduler.

Claims (1)

[Claims] An attitude control device for controlling the orbit and attitude of a spacecraft, comprising: a solar reflector disposed around the spacecraft so as to be movably adjustable so as to face the sun; An attitude control device configured to control the trajectory and attitude of the spacecraft by adjusting movement and variably controlling incident light.