JP2002127999A - Rocket - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a rocket capable of ejecting an artificial satellite in a stable attitude. SOLUTION: Using plural electromagnets 17 to generate magnetic force to attract the artificial satellite 14, and controllers 18 to separately energize and deenergize the electromagnets 17, the attitude of the artificial satellite 14 when ejected in controlled by the magnetic force.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rocket equipped with an artificial satellite, and more particularly to a technique for controlling the attitude of an artificial satellite at the time of launch.

[0002]

2. Description of the Related Art Generally, a rocket equipped with an artificial satellite has an artificial satellite mounted on a mounting surface called a payload attach fitting (PAF) and resists a plurality of coiled springs arranged on the mounting surface. In this state, the artificial satellite is fastened to the mounting surface by mechanical fastening means such as a belt.

[0003] When the artificial satellite reaches the insertion point, the fastening state of the fastening means is released, whereby the spring force of the spring acts to eject the artificial satellite into outer space.

[0004]

However, as described above, if only the mechanical fastening state is released when the artificial satellite is ejected, the timing of disconnection from the rocket body for each fastened portion. There is a possibility that the attitude of the artificial satellite may be lost due to the timing shift, such as rotation of the artificial satellite.

The present invention has been made in view of the above circumstances, and has as its object to provide a rocket capable of launching an artificial satellite in a stable attitude.

[0006]

Means for Solving the Problems To solve the above problems, the present invention employs the following means. Claim 1
The invention according to the invention relates to a rocket equipped with an artificial satellite,
The present invention is characterized in that it is provided with a launch attitude control device that controls the attitude of the artificial satellite at the time of launch by magnetic force. Claim 2
In the rocket according to claim 1, in the rocket according to claim 1, the injection attitude control device has a plurality of electromagnets that generate a magnetic force for attracting an artificial satellite, and a controller that individually excites and demagnetizes the plurality of electromagnets. It is characterized by the following. According to a third aspect of the present invention, in the rocket according to the first aspect, the injection attitude control device measures a distance between the electromagnet that generates a magnetic force that attracts or repels the artificial satellite and the artificial satellite. It has a sensor and a controller that controls the magnetic force of the electromagnet based on the measurement result of the distance measurement sensor.

In this rocket, by controlling the attitude of the satellite by the magnetic force, the satellite can be launched in a stable attitude. That is, for example, by using a plurality of electromagnets that generate a magnetic force to attract the satellite and a controller that individually excites and demagnetizes the plurality of electromagnets, the timing at which the satellite is separated from the rocket body is controlled by the magnetic force, It is possible to suppress a partial shift in the timing of disconnecting the artificial satellite. Also,
For example, by using an electromagnet that generates a magnetic force to attract or repel an artificial satellite, a distance measuring sensor that measures the distance to the artificial satellite, and a controller that controls the magnetic force of the electromagnet based on the measurement result of the distance measuring sensor. The attitude of the satellite can be stably controlled by magnetic force while measuring the distance of the satellite from the rocket body.

[0008]

Embodiments of the present invention will be described below with reference to FIGS. FIG. 1 is an overall external view showing a rocket mounted on an artificial satellite, FIG. 2 is an explanatory view showing an assembled state of the artificial satellite, and FIG. 3 is a perspective view showing an injection attitude control device provided between the artificial satellite and the rocket. The rocket 10 has a single-stage rocket unit 1 as shown in FIG.
This is a multi-stage rocket composed of a single-stage rocket unit 12 and a two-stage rocket unit 12. On the end face (mounting surface 13) of the two-stage rocket unit 12, an artificial satellite 14 is mounted as shown in FIG. Note that the artificial satellite 14 is covered by the fairing 15 as shown in FIG.

On the mounting surface 13 of the two-stage rocket unit 12, a plurality of separation springs 16 formed in a coil shape as shown in FIG. And
Flange surface 14 a of artificial satellite 14 is separated spring 16
The artificial satellite 14 is placed on the mounting surface 13 of the two-stage rocket unit 12 by being superimposed on the mounting surface 13 against the spring force of It is assembled integrally.

In this embodiment, the mounting surface 13
In addition, there is provided an ejection attitude control device for evenly separating the artificial satellite 14 around the periphery. As shown in FIG. 3, the injection attitude control device includes a plurality of electromagnets 17 disposed on the mounting surface 13 and a controller 18 for controlling each electromagnet 17. The electromagnets 17 are arranged at predetermined intervals along the periphery of the mounting surface 13, and magnetically attract the flange surface 14 a of the artificial satellite 14 when excited and demagnetize the magnetic attraction force when demagnetized. It is to cancel.

The controller 18 excites the electromagnet 17 to apply an attractive force to the artificial satellite 14 before the fastening state of the artificial satellite 14 by the above-mentioned fastening means is released, and the fastening state is released. At a predetermined timing, the electromagnet 17 is demagnetized to release its magnetic attraction force. Here, each electromagnet 17 is set to be simultaneously excited and demagnetized. At least a part of the flange surface 14 a of the artificial satellite 14 is made of a magnetic material so as to be attracted by the magnetic force of the electromagnet 17.

The rocket 10 constructed as described above is launched by the ignition of the first-stage rocket unit 11, and when the first-stage rocket unit 11 finishes burning, the first-stage rocket unit 1
1 is separated from the two-stage rocket unit 12. Thereafter, the fairing 15 is separated and the artificial satellite 1 is separated as shown in FIG.
4 is exposed. When a predetermined point (orbital position) is reached after the ignition of the two-stage rocket portion 12, the mechanical fastening state by the fastening means (not shown) is released, so that the spring force of the separation spring 16 acts to perform the two-stage rocket portion. A satellite 14 is launched from the rocket unit 12.

At this time, the controller 18 excites each electromagnet 17 and releases the artificial satellite 1 prior to releasing the fastening state.
4 is the mounting surface 1 of the two-stage rocket unit 12
Adsorb to 3. Then, after releasing the fastening state, the magnetic attraction forces of all the electromagnets 17 are simultaneously released at the same timing.

That is, the rocket 10 of the present embodiment has
Since the timing at which the artificial satellite 14 is separated from the rocket body is controlled by a magnetic force instead of a mechanical mechanism, the timing of the separation is constant in the circumferential direction of the mounting surface 13 and partial displacement hardly occurs. Therefore, the artificial satellite 14 can be emitted in a stable attitude without breaking the attitude of the artificial satellite 14.

In the above embodiment, the case where at least a part of the flange surface 14a of the artificial satellite 14 is made of a magnetic material has been described. Next, the flange surface 14a of the artificial satellite 14 is made of a conductive material. An embodiment in such a case will be described. FIG. 4 shows another embodiment of the present invention. The injection attitude control device in FIG. 4 has a distance measuring sensor 19 for measuring the distance of the artificial satellite 14 from the mounting surface 13 in addition to the electromagnet 17 and the controller 18. It is configured.

In the present embodiment, when the artificial satellite 14 is separated from the mounting surface 13 of the two-stage rocket unit 12, the distance from the artificial satellite 14 is measured by the distance measuring sensor 19. The controller 18 excites the electromagnet 17 to generate a magnetic force acting between the flange surfaces 14a of the artificial satellite 14 in the direction of repulsion or attraction, and keeps the attitude of the artificial satellite 14 constant based on the measurement result of the distance measuring sensor 19. , The magnetic force of each electromagnet 17 is individually controlled. Thereby, while measuring the distance of the artificial satellite 14 from the rocket main body, the attitude of the artificial satellite 14 can be stably controlled by the magnetic force.

The various shapes and combinations of the constituent members shown in the above-described embodiment are merely examples, and can be variously changed based on design requirements without departing from the gist of the present invention. For example, in each of the above-described embodiments, an example in which the present invention is applied to a two-stage rocket 10 including a single-stage rocket unit 11 and a two-stage rocket unit 12 has been described. It can also be applied to rockets.

[0018]

As described above, according to the present invention, it is possible to suppress the partial deviation of the timing at which the artificial satellite is separated by the magnetic force, or to measure the artificial satellite by the magnetic force while measuring the distance of the artificial satellite from the rocket body. By changing the attitude of the satellite, the satellite can be launched in a stable attitude.

[Brief description of the drawings]

FIG. 1 is an overall external view showing a rocket according to the present invention.

FIG. 2 is an explanatory diagram showing an assembled state of an artificial satellite.

FIG. 3 is a perspective view showing an injection attitude control device provided on a mounting surface of a rocket unit.

FIG. 4 shows another embodiment according to the present invention,
It is explanatory drawing of an injection attitude | position control apparatus.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 10 ... Rocket 12 ... Two-stage rocket part 16 ... Separation spring 17 ... Electromagnet 18 ... Controller 19 ... Distance measuring sensor

Claims (3)

[Claims] 1. A rocket equipped with an artificial satellite, comprising a launch attitude control device for controlling the attitude of the artificial satellite at the time of launch by magnetic force. 2. The apparatus according to claim 1, wherein the launch attitude control device includes a plurality of electromagnets for generating a magnetic force for attracting an artificial satellite, and a controller for individually exciting and demagnetizing the plurality of electromagnets. The rocket described. 3. An ejection attitude control device comprising: an electromagnet for generating a magnetic force for attracting or repelling an artificial satellite; a distance measuring sensor for measuring a distance to the artificial satellite; and an electromagnet based on a measurement result of the distance measuring sensor. The rocket according to claim 1, further comprising a controller for controlling a magnetic force.