JP4632112B2 - Satellite launch method - Google Patents

Description

[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a satellite launching method suitable for use in launching a satellite with a multistage rocket.
[0002]
[Prior art]
Conventionally, when launching a satellite using a multi-stage rocket, an all-stage disposable system has been adopted.
[0003]
[Problems to be solved by the invention]
In the all-stage disposable system as described above, even if it is attempted to collect and reuse avionics and other equipment as much as possible, it is actually difficult to recover because the fall point is far from the launch site. After all, as long as the above-mentioned all-stage disposable method is adopted for the launch of the satellite, there is a problem that the launch cost cannot be expected to be reduced, and it has been a conventional problem to solve this problem.
[0004]
OBJECT OF THE INVENTION
The present invention has been made paying attention to the above-described conventional problems, and can recover most of the onboard equipment such as aviation control for rocket control, and the cost of launch can be reduced by reusing these recovered equipment. The object is to provide a satellite launch method capable of realizing a significant reduction.
[0005]
[Means for Solving the Problems]
In the satellite launch method according to claim 1 of the present invention, when launching a satellite with a multistage rocket, most of the rocket control is performed during the stage of the rise of combustion of the first stage rocket motor and the subsequent stage of inertia rise. After concentrating and launching the rocket motors and satellites in the second and subsequent stages to reach the altitude, and separating the recovery unit equipped with avionics for rocket control from the satellite side or rear end side of the second and subsequent stages The configuration is such that the rocket motors in the second and subsequent stages are sequentially burned and the satellite is put into a predetermined orbit, and the configuration of this satellite launch method is a means for solving the above-described conventional problems.
[0006]
In the satellite launching method according to claim 2 of the present invention, the recovery part is integrally separated from the nose fairing (for example, the decapitation fairing) arranged at the tip of the second and subsequent stages of the multistage rocket. In this way, when the satellite side is integrally separated from the nose fairing, it is desirable to separate the recovery unit from the nose fairing in order to reduce air resistance.
[0007]
The satellite launching method according to claim 3 of the present invention has a structure in which a deceleration means such as a hemispherical ribbon type droach chute or a guide surface type droch chute is provided in the recovery unit, and the satellite according to claim 4 of the present invention. The launching method has a configuration in which a glide means such as a stable wing suitable for use in the hypersonic region or a gliding parachute (parafoil) suitable for use in the low speed region is provided in the recovery unit.
[0008]
In the satellite launching method according to the present invention, each stage of the multistage rocket is called a rocket motor, but may be called a rocket engine. Rocket control refers to actions such as pitch angle change, attitude control, pointing control, spin provision, and spin-up.
[0009]
[Effects of the Invention]
In the satellite launching method according to claim 1 of the present invention, when launching a satellite with a multi-stage rocket, most of the rocket control is performed during the stage of the rise of combustion of the first stage rocket motor and the subsequent stage of inertia rise. Since it is concentrated and the rocket motors and satellites in the second and subsequent stages are launched to reach the altitude, the separated recovery unit falls (or falls) near the launch site, As a result, if the collected avionics is reused, the satellite launch cost will be greatly reduced.
[0010]
In the satellite launching method according to claim 2 of the present invention, since the collection unit is integrally separated from the nose fairing, the separation mechanism is less than the case where the collection unit and the nose fairing are individually separated. Therefore, the cost can be reduced.
[0011]
In the satellite launching method according to claim 3 of the present invention, aerodynamic heating is suppressed to a low level, and in the satellite launching method according to claim 4 of the present invention, the recovery unit can fly toward the launch site or the vicinity thereof. As a result, recovery becomes even easier.
[0012]
【The invention's effect】
In the satellite launching method according to the first aspect of the present invention, the collection unit on which the avionics is mounted can be dropped in the vicinity of the launch site, so that the collection unit can be easily collected. There is an excellent effect that it is possible to realize a significant reduction in utilization and the satellite launch costs associated therewith.
[0013]
Since the satellite launch method according to claim 2 of the present invention has the above-described configuration, the cost can be reduced by the amount of the separation mechanism compared with the case where the recovery unit and the nose fairing are individually separated. It has the excellent effect of being able to.
[0014]
In the satellite launching method according to claim 3 of the present invention, since it has the above-described configuration, it is possible to suppress aerodynamic heating that occurs when the recovery unit falls. Since the launch method has the above-described configuration, the collection unit can fly toward the launch site or the vicinity thereof, and as a result, an excellent effect that the collection can be performed more easily is brought about.
[0015]
【Example】
Hereinafter, the present invention will be described with reference to the drawings.
[0016]
1 and 2 are diagrams for explaining an embodiment of a satellite launching method according to the present invention.
[0017]
As shown in FIG. 2 (a), the multistage rocket R used in this embodiment is a three-stage rocket equipped with solid rocket motors 1, 2, 3, and is located outside the second stage solid rocket motor 2. A spin motor 4 is provided on the shell 2a, and a kick motor 6 that is ignited at an apogee point is provided on an artificial satellite 5 that is detachably coupled to the solid rocket motor 3 at the third stage.
[0018]
In this multistage rocket R, command receivers and pressure sensors that receive ignition commands are mounted on each stage, and the pitch angle of the multistage rocket R, attitude control, pointing control, spin application, Avionics for rocket control such as spin-up are collectively mounted on a capsule (collecting part) 7 located at the tip of the multistage rocket R.
[0019]
In this case, the capsule 7 is detachably connected to a decapitation type nose fairing 8 separated from the outer shell 2a of the second stage solid rocket motor 2 by the separation surface 2b, as shown in FIG. 2 (b). Thus, at the launch height, the nose fairing 8 is integrally separated from the second stage solid rocket motor 2 side.
[0020]
Further, as shown in FIG. 1, the capsule 7 is equipped with a hemispherical ribbon type drag chute 9 as a speed reducing means and a gliding parachute 10 as a gliding means.
[0021]
When launching the artificial satellite 5 with the multistage rocket R, first, when the first stage solid rocket motor 1 is ignited in step 1 and the multistage rocket R is launched from the launch site L, steps 2 and 3 are performed. Then, the solid rocket motor 1 is continuously burned up to step 4.
[0022]
Next, in step 5, as shown in FIG. 2 (c), when the first-stage solid rocket motor 1 is disconnected, the second-stage and subsequent solid rocket motors 2, 3 and the satellite 5 are lifted by inertia. In step 8, as shown in FIG. 2 (b), the capsule 7 is separated from the second stage solid rocket motor 2 side integrally with the nose fairing 8.
[0023]
Most of the rocket control is concentrated between the above-described rising stage due to combustion of the first-stage solid rocket motor 1 and the subsequent rising stage due to inertia, that is, pitch angle change in step 3, step 4 At the start of posture control in step S6, pointing control in step 6 is performed, and spin provision and spin-up are performed in step S7.
[0024]
Next, the second-stage solid rocket motor 2 to which the spin is applied and the capsule 7 and the nose fairing 8 are separated is ignited and burned in step 9, and then shown in FIG. 2 (e). Thus, when the 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, 10, the artificial satellite 5 is put into a predetermined orbit.
[0025]
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 type drag chute 9 is released and continues to descend while decelerating. At 13, the gliding parachute 10 is opened and glides to land on the ocean near the launch site L (or land on the land near the launch site L).
[0026]
Then, a recovery helicopter 12 that has received radio waves from a transmitter 11 such as a GPS or a radio beacon provided in the capsule 7 collects the capsule 7 and returns it.
[0027]
In the satellite launching method described above, most of the rocket control is concentrated between the stage of ascending due to combustion of the solid rocket motor 1 in the first stage and the subsequent stage of ascending due to inertia. Since the solid rocket motors 2 and 3 and the satellite 5 are launched to reach the altitude, the capsule 7 loaded with avionics that is cut off at the end of the stage falls (or falls) near the launch site L. It becomes.
[0028]
That is, the capsule 7 can be collected very easily. As a result, the cost of launching the artificial satellite 5 can be greatly reduced by reusing the collected avionics.
[0029]
Further, in the satellite launching method described above, the capsule 7 is separated from the nose fairing 8 integrally, so that the cost of the separation mechanism is less than that when the capsule 7 and the nose fairing 8 are individually separated. Reduction will be achieved.
[0030]
Furthermore, in the satellite launching method described above, the hemispherical ribbon type drag chute 9 is released when the capsule 7 is lowered, so that aerodynamic heating is reduced, and in addition, the gliding parachute 10 is installed at a low altitude. Since the capsule 7 is opened and glide, the capsule 7 can fly toward the launch site L or in the vicinity thereof, thereby further simplifying the collection.
[0031]
FIGS. 3 and 4 are diagrams for explaining another embodiment of the satellite launching method according to the present invention. The satellite launching method according to this embodiment is different from the satellite launching method according to the previous embodiment. As shown in FIG. 4 (a), the capsule (collecting part) 17 loaded with avionics for rocket control is arranged at the rear end 2c of the second-stage solid rocket motor 2, and other configurations Is the same as the satellite launch method according to the previous embodiment.
[0032]
In this embodiment, as shown in FIG. 4C, the capsule 17 is separated from the rear end 2c of the second-stage solid rocket motor 2 integrally with the interstage joint 2A at the launch height. ing.
[0033]
When launching the artificial satellite 5 by the satellite launch method according to this embodiment, as shown in FIG. 3, steps 1 to 8 proceed in the same procedure as the satellite launch method according to the previous embodiment. At 8 ', the capsule 17 is cut off together with the interstage joint 2A from the rear end 2c of the second stage solid rocket motor 2 to which the spin is applied and the nose fairing 18 is cut off. 4 (e), the third-stage solid rocket motor 3 separated from the second stage is ignited and burned, and finally the artificial satellite 5 separated from the third stage. When the kick motor 6 is ignited at the apogee point, the artificial satellite 5 is put into a predetermined orbit in step 10.
[0034]
On the other hand, the capsule 17 discharges the hemispherical ribbon-type drag chute 9 in step 12 and continues to descend while decelerating. In step 13, the gliding parachute 10 is opened and glides to land on the ocean near the launch site L. (Or landing on land near the launch site L), the recovery helicopter 12 receiving the radio wave from the transmitter 11 such as GPS or radio beacon provided in the capsule 17 collects the capsule 17 and returns it.
[0035]
Also in the satellite launching method according to this embodiment, the capsule 17 can be easily recovered. Therefore, the cost of launching the artificial satellite 5 can be significantly reduced by reusing the recovered avionics. It becomes.
[0036]
Also, in this satellite launching method, aerodynamic heating can be suppressed to a low level, and the capsule 17 can fly toward the launch site L or in the vicinity thereof, thereby making recovery easier.
[0037]
In this embodiment, the capsule 17 arranged at the rear end 2c of the second-stage solid rocket motor 2 is housed in the nozzle 2d of the solid rocket motor 2. However, the present invention is not limited to this. For example, as shown in FIGS. 5A and 5B, the capsule 17 may be disposed beside the nozzle 2d of the solid rocket motor 2 and fixed to the interstage joint 2A.
[0038]
FIG. 6 is a diagram for explaining still another embodiment of the satellite launching method according to the present invention. In the satellite launching method according to this embodiment, a stable wing 10A suitable for use in the hypersonic region is provided. The winged aircraft 7 </ b> A having the recovery unit is used, and the other configuration is the same as that of the previous embodiment.
[0039]
In this embodiment, the moving distance in the horizontal direction is extended in the hypersonic region, and the winged aircraft 7A can be returned to the launch site L, so that the recovery cost can be further reduced. .
[0040]
In the above-described embodiment, the case where each stage of the multistage rocket R is a solid rocket motor has been shown. However, the present invention is not limited to this, and a liquid rocket engine can be adopted as the first stage. It is.
[Brief description of the drawings]
FIG. 1 is an explanatory diagram of a launch sequence 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. 1 (a), a simplified cross-sectional explanatory view when the nose fairing is separated from the second stage together with the capsule (b), a simplified cross-sectional explanation of the separated first stage. FIG. 3 (c) is a simplified cross-sectional explanatory view (d) when the capsule is separated from the nose fairing, and a simplified cross-sectional explanatory view (e) when the second stage is separated from the third stage. It is launch sequence explanatory drawing which shows the other Example of the launch method of the satellite concerning this.
FIG. 4 is a cross-sectional explanatory view of the multistage rocket in FIG. 3 (a), a simplified cross-sectional explanatory view when the nose fairing is separated from the second stage (b), cut away from the rear end of the airframe after the second stage. Capsule, interstage joint and simplified cross-sectional explanatory diagram of the first stage (c), simplified cross-sectional explanatory diagram of the separated nose fairing (d), and simplified cross-sectional explanatory diagram when the third stage is separated from the second stage (e).
FIG. 5 is a cross-sectional explanatory view (a) of the multistage rocket showing another example of the arrangement of the capsule of the multistage rocket in FIG. 3; the capsule, the interstage joint, and 1 separated from the rear end of the airframe after the second stage It is a simplified cross-section explanatory drawing (b) of a step.
FIG. 6 is an operation explanatory view showing still another embodiment of the satellite launching 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 airframe after second stage)
5 Artificial satellites 7, 17 capsules (collection unit)
7A winged aircraft (collection unit)
8 Nose Fairing 9 Hemispherical Ribbon Type Drag Shoot (Decelerator)
10 Gliding parachute (glide means)
10A Stabilized wing (glide means)
R Multistage rocket

Claims (4)

When launching a satellite with a multistage rocket, most of the rocket control is concentrated between the stage of the rise of the first stage rocket motor by combustion and the subsequent stage of inertia rise, Launch the satellite, reach the altitude, disconnect the recovery unit equipped with avionics for rocket control from the satellite side or rear end side of the second and subsequent aircrafts, and then sequentially burn the second and subsequent rocket motors to satellite A satellite launching method characterized in that the satellite is put into a predetermined orbit. The satellite launching method according to claim 1, wherein the recovery unit is integrally separated from a nose fairing disposed at the tip of the second and subsequent airframes of the multistage rocket. The satellite launching method according to claim 1, wherein a speed reduction means is provided in the recovery unit. The satellite launching method according to claim 1, wherein glide means is provided in the recovery unit.

Images