JP2003020000A - How to launch a satellite - Google Patents

Abstract

(57) [Summary] [PROBLEMS] To significantly reduce the launch cost of a satellite by collecting and reusing most of onboard equipment such as avionics for rocket control. SOLUTION: When launching a satellite 5 with a multi-stage rocket R, most of the rocket control is performed in a concentrated manner during a stage due to combustion of a first stage rocket motor 1 and a subsequent stage of inertia rise. The rocket motors 2 and 3 and the satellite 5 after the first stage are launched to reach the altitude, and the capsule 7 equipped with the avionics for rocket control is moved to the second position.
After disconnecting from the satellite 5 side of the aircraft after the first stage or the rear end 2c of the second stage, the rocket motors 2 and 3 of the second and subsequent stages are sequentially burned to put the satellite 5 into a predetermined orbit.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a satellite launching method suitable for launching a satellite with a multistage rocket.

[0002]

2. Description of the Related Art Conventionally, when launching a satellite using a multistage rocket, a full-stage disposable system has been adopted.

[0003]

In the all-stage disposable system as described above, even if an attempt is made to collect and re-use on-board equipment such as avionics as much as possible, the fall point is far from the launch range. In reality, it is difficult to recover, and after all, there is a problem that the launch cost cannot be expected to be reduced as long as the above-mentioned all-stage disposable system is used for launching the satellite. Had been a problem.

[0004]

SUMMARY OF THE INVENTION The present invention has been made by paying attention to the above-mentioned conventional problems, and it is possible to recover most of on-board equipment such as avionics for rocket control, and to reuse these recovered equipment. Therefore, it is an object of the present invention to provide a satellite launch method capable of realizing a significant reduction in launch cost.

[0005]

A method for launching a satellite according to claim 1 of the present invention is directed to launching a satellite with a multistage rocket by raising the first stage rocket motor and then increasing the inertia. Most of the rocket control is concentrated between stages to launch the rocket motors and satellites from the second stage onwards to reach the altitude, and the recovery unit equipped with avionics for rocket control is used on the satellites from the second stage onward. After being separated from the side or the rear end side, the rocket motors of the second and subsequent stages are sequentially burned to put the satellite into a predetermined orbit. The structure of the launch method of this satellite solves the above-mentioned conventional problems. As a means to

The satellite launch method according to claim 2 of the present invention is integrated with a nose fairing (for example, a decapsulated fairing) in which the recovery part is arranged at the tip of the second and subsequent stages of the multistage rocket. When the satellite is integrated with the nose fairing in this way, it is desirable to separate the collecting part from the nose fairing in order to reduce air resistance.

The satellite launching method according to claim 3 of the present invention is configured such that a deceleration means such as a hemispherical ribbon type drog chute or a guide surface type drog chute is provided in the recovery part, and the method of claim 4 of the present invention. The satellite launch method concerned is configured such that the recovery unit is provided with a stabilizing wing suitable for use in the hypersonic range and a gliding means such as a gliding parachute (parafoil) suitable for use in the low range.

In the satellite launch method according to the present invention, each stage of the multistage rocket is called a rocket motor, but it may also be called a rocket engine. Also,
Rocket control refers to actions such as pitch angle change, attitude control, pointing control, spin addition, and spin-up.

[0009]

In the satellite launching method according to the first aspect of the present invention, when the satellite is launched by the multi-stage rocket, the first rocket motor burns during the ascending and the subsequent inertial ascending stage. Most of the rocket control is concentrated to launch the rocket motors and satellites from the second stage onwards to reach the altitude, so the separated recovery unit falls (or descends) near the launch site. As a result, recovery will be facilitated, and as a result, if the recovered avionics is reused, the satellite launch cost will be significantly reduced.

In the satellite launching method according to claim 2 of the present invention, since the collecting part is integrally separated from the nose fairing, the separating mechanism is different from the case where the collecting part and the nose fairing are individually separated. The cost can be reduced by a small amount.

In the satellite launch method according to claim 3 of the present invention, aerodynamic heating is suppressed to a small level. In the satellite launch method according to claim 4 of the present invention, the recovery section is directed toward the launch field or its vicinity. It will be possible to fly and collection will be even easier.

[0012]

According to the satellite launch method of the first aspect of the present invention, since the collecting part having the avionics can be dropped near the launch site, the collecting part can be easily collected, and therefore, It is possible to recycle the collected avionics and to significantly reduce the satellite launch cost, which is a very excellent effect.

Since the satellite launching method according to claim 2 of the present invention has the above-mentioned structure, the number of separating mechanisms can be reduced as compared with the case where the collecting part and the nose fairing are individually separated. The excellent effect that the cost can be reduced is brought about.

Since the satellite launching method according to claim 3 of the present invention has the above-mentioned configuration, it is possible to suppress aerodynamic heating that occurs when the recovery unit drops,
Since the satellite launch method according to claim 4 of the present invention has the above-described configuration, the recovery unit can be made to fly toward the launch field or its vicinity, and as a result, the recovery can be performed even more easily. That is a very good effect.

[0015]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below with reference to the drawings.

1 and 2 are views for explaining an embodiment of a satellite launch method according to the present invention.

As shown in FIG. 2A, the multistage rocket R used in this embodiment is a solid rocket motor 1, 2,
3 is a three-stage rocket equipped with a spin motor 4 on the outer shell 2a of the second-stage solid rocket motor 2 and an artificial satellite that is separably coupled to the third-stage solid rocket motor 3. 5 is provided with a kick motor 6 which is ignited at the apogee point.

In this multi-stage rocket R, a command receiver for receiving an ignition command and a pressure sensor are mounted in each stage, and the pitch angle of the multi-stage rocket R is changed, the attitude control, the pointing control, and the spin control are performed. Avionics for rocket control such as granting and spin-up are collectively mounted on a capsule (recovery unit) 7 located at the tip of the multistage rocket R.

In this case, the capsule 7 is separably connected to the decapsulated nose fairing 8 which is separated from the outer shell 2a of the second stage solid rocket motor 2 and the separation surface 2b, as shown in FIG. As shown in (), the nose fairing 8 is integrally separated from the second-stage solid rocket motor 2 side at the launch altitude.

Further, as shown in FIG. 1, the capsule 7 has a hemispherical ribbon drog chute 9 as a speed reducing means.
Is equipped with a gliding parachute 10 as a glide means.

In launching the artificial satellite 5 with this multistage rocket R, first, in step 1, when the first stage solid rocket motor 1 is ignited and the multistage rocket R is launched from the launch field L, step 2 , 3 to step 4, the solid rocket motor 1 continues to burn.

Next, in step 5, as shown in FIG. 2C, when the first-stage solid rocket motor 1 is disconnected, the second-stage solid rocket motors 2 and 3 and the satellite 5 are 2) The capsule 7 is separated from the second-stage solid rocket motor 2 side together with the nose fairing 8 in step 8 as shown in FIG. 2 (b). Be done.

The above-mentioned first stage solid rocket motor 1
Most of the rocket control is concentrated during the combustion ascent and subsequent inertial ascent stages, ie pitch angle change in step 3, attitude control start in step 4, pointing control in step 6. The spin application and spin-up in step 7 are performed.

Next, in step 9, the second-stage solid rocket motor 2 to which the spin has been applied and the capsule 7 and the nose fairing 8 have been separated is ignited and burned. ), The third stage solid rocket motor 3 separated from the second stage is ignited and burned, and finally the kick motor 6 of the artificial satellite 5 separated from the third stage is ignited at the apogee point. Then, step 10
At, the artificial satellite 5 is put into a predetermined orbit.

On the other hand, the capsule 7 is separated from the nose fairing 8 in step 11 as shown in FIG. 2 (d), and in step 12, the hemispherical ribbon drog chute 9 is discharged to decelerate while descending. Continue, step 13
At, the gliding parachute 10 is opened and glide to land on the ocean near the launch field L (or land on the land near the launch field L).

Then, the collecting helicopter 12, which receives the radio wave from the transmitter 11 such as GPS or radio beacon provided in the capsule 7, collects the capsule 7 and returns it.

In the above-described satellite launch method, most of the rocket control is concentrated between the first stage solid rocket motor 1 ascending by combustion and the subsequent ascending inertial stage. Since the solid rocket motors 2 and 3 and the satellite 5 after the eye are launched to reach the altitude, the avionics-equipped capsule 7 separated at the end of the above stage falls (or descends) near the launch field L. It will be).

That is, the recovery of the capsule 7 becomes very simple, and as a result, the cost of launching the artificial satellite 5 can be greatly reduced by reusing the recovered avionics.

In addition, in the satellite launch method described above,
Since the capsule 7 and the nose fairing 8 are integrally separated, compared with the case where the capsule 7 and the nose fairing 8 are individually separated, the separation mechanism is small.
The cost can be reduced.

Further, in the above-described satellite launch method, the hemispherical ribbon type drog chute 9 is discharged when the capsule 7 descends, so that aerodynamic heating can be suppressed to a small extent, and in addition, gliding at a low altitude. Since the parachute 10 is opened for gliding, the capsule 7 can be made to fly toward the shooting field L or its vicinity, and the collection is further facilitated.

3 and 4 are diagrams for explaining another embodiment of the satellite launch method according to the present invention. The satellite launch method according to this embodiment is the same as the satellite launch method according to the previous embodiment. The difference is that, as shown in FIG. 4 (a), a capsule (recovery unit) 17 equipped with rocket control avionics is arranged at the rear end 2c of the second-stage solid rocket motor 2. Other configurations are the same as the satellite launch method according to the previous embodiment.

In this embodiment, as shown in FIG. 4 (c), the capsule 17 is separated from the rear end 2c of the second stage solid rocket motor 2 at the launch altitude integrally with the interstage joint 2A. It is like this.

When the artificial satellite 5 is launched by the satellite launch method according to this embodiment, as shown in FIG. 3, steps 1 to 8 follow the same procedure as the satellite launch method according to the previous embodiment. Then, in step 8 ′, the second stage solid rocket motor 2 with the spin imparted and the nose fairing 18 separated
After the capsule 17 is separated from the rear end 2c together with the interstage joint 2A and ignited and burned in step 9, as shown in FIG. 4 (e), the third stage separated from the second stage. When the solid rocket motor 3 is ignited and burned, and finally the kick motor 6 of the artificial satellite 5 separated from the third stage is ignited at the apogee point, the artificial satellite 5 is put into a predetermined orbit in step 10. Becomes

On the other hand, the capsule 17 continues to descend while releasing the hemispherical ribbon type drog chute 9 in step 12 and decelerating, and in step 13, opens the gliding parachute 10 and glides to the sea near the launch site L. Upon landing (or landing on the land near the launch site L), the collecting helicopter 12 which receives radio waves from the transmitter 11 such as the GPS or the radio beacon provided in the capsule 17 collects the capsule 17 and returns it.

Also in the satellite launch method according to this embodiment, the capsule 17 can be easily recovered,
Therefore, by reusing the collected avionics, the launch cost of the artificial satellite 5 can be significantly reduced.

In the case of this satellite launch method,
Aerodynamic heating can be suppressed to a small level, and the capsule 17 can be made to fly toward the launch site L or in the vicinity thereof, so that recovery is further facilitated.

In this embodiment, the capsule 17 arranged at the rear end 2c of the second stage solid rocket motor 2 is
Although the case where the nozzle is housed in the nozzle 2d of the solid rocket motor 2 is shown, the present invention is not limited to this.
As shown in FIGS. 5A and 5B, the capsule 17 may be arranged beside the nozzle 2d of the solid rocket motor 2 and fixed to the interstage joint 2A.

FIG. 6 is a diagram for explaining still another embodiment of the satellite launch method according to the present invention. The satellite launch method according to this embodiment is suitable for use in the hypersonic range. The winged aircraft 7A having the blades 10A is used as the recovery unit, and the other configurations are the same as those in the previous embodiment.

In this embodiment, the moving distance in the horizontal direction is extended in the hypersonic range, and the winged aircraft 7A can be returned to the launch site L, so that the recovery cost can be further reduced. It will be.

In the above-described embodiment, the case where all the stages of the multistage rocket R are solid rocket motors is shown, but the invention is not limited to this, and the liquid rocket engine is adopted in the first stage. It is also possible.

[Brief description of drawings]

FIG. 1 is a launch sequence explanatory diagram showing an embodiment of a satellite launch method according to the present invention.

2 is a cross-sectional explanatory view of the multistage rocket in FIG.
(a), Simplified cross-sectional explanatory view when the nose fairing is separated from the second stage together with the capsule (b), Simplified cross-sectional explanatory view of the separated first stage (c), When the capsule is separated from the nose fairing 3D is a simplified cross-sectional explanatory view (d) and a simplified cross-sectional explanatory view (e) when the second to third stages are separated.

FIG. 3 is a launch sequence diagram showing another embodiment of the satellite launch method according to the present invention.

4 is a cross-sectional explanatory view of the multistage rocket in FIG.
(a), a simplified cross-sectional explanatory view when the nose fairing is separated from the second stage (b), a capsule separated from the rear end of the aircraft after the second stage, an interstage joint and a simplified cross-sectional explanation of the first stage FIG. 6 (c) is a simplified cross-sectional explanatory view (d) of the separated nose fairing and a schematic cross-sectional explanatory view (e) when the second to third stages are separated.

5 is a cross-sectional explanatory view (a) and 2 of the multistage rocket showing another arrangement example of the capsules of the multistage rocket in FIG.
FIG. 6B is a simplified cross-sectional explanatory view (b) showing the capsule, the interstage joint, and the first stage separated from the rear end of the machine body after the first stage.

FIG. 6 is an operation explanatory view showing still another embodiment of the satellite launch method according to the present invention.

[Explanation of symbols]

1,2,3 Solid rocket motor 2c Rear end of second stage solid rocket motor (rear end of second and subsequent stages) 5 Satellite 7,17 Capsule (recovery part) 7A Winged aircraft (recovery part) 8 Nose fairing 9 Hemispherical ribbon type drog chute (reduction means) 10 Gliding parachute (glide means) 10A Stabilizer wing (glide means) R Multistage rocket

   ─────────────────────────────────────────────────── ─── Continued front page    (72) Inventor Masahisa Honda             2-2-1 Otemachi, Chiyoda-ku, Tokyo Stock             Ceremony Company IHI Aerospace             Within (72) Inventor Takashi Makino             2-2-1 Otemachi, Chiyoda-ku, Tokyo Stock             Ceremony Company IHI Aerospace             Within

Claims (4)

[Claims] 1. When launching a satellite with a multi-stage rocket, most of the rocket control is concentrated during the ascending stage due to combustion of the rocket motor in the first stage and the subsequent stage of ascending inertia. After launching the subsequent rocket motor and satellite to reach the altitude, after disconnecting the recovery part equipped with avionics for rocket control from the satellite side or the rear end side of the aircraft from the second stage onwards, the rocket motors from the second stage onwards are removed. A method for launching satellites, which comprises sequentially burning and launching the satellites into a predetermined orbit. 2. The method for launching a satellite according to claim 1, wherein the recovery part is integrally separated from the nose fairing arranged at the tip of the second and subsequent stages of the multistage rocket. 3. The method for launching a satellite according to claim 1, wherein the recovery unit is provided with deceleration means. 4. The satellite launch method according to claim 1, wherein the recovery unit is provided with gliding means.