JPH06288301A - Method and device for multi-stage acceleration - Google Patents

Abstract

PURPOSE:To reduce a payload on a missile to attain ultra-high speed by accelerating the missile by a ram jet part and a rocket engine installed therein at the second and third stages, respectively, after the missile has been accelerated by an electrical acceleration means at a first stage. CONSTITUTION:After a missile 1A provided with a payload 1 at its top has been launched by an electrical acceleration means, a ram jet part 5 of the missile 1A is ignited and, as the final stage, the rocket engine 2 of the missile 1A is ignited to multi-accelerate the missile. Thus the weight of the missile 1A can be reduced in comparison with the conventional case to attain ultra-high speed easily.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a multistage accelerating method and apparatus, and in particular, after accelerating a projectile by an electric accelerating means as a first stage, a ramjet section in a projectile and a second stage in a rocket engine. By accelerating the third stage, it relates to a new improvement for reducing the loading load on the flying object and obtaining an ultrahigh speed.

[0002]

2. Description of the Related Art As a conventional multi-stage acceleration method of this type, for example, a payload of 10 kg to 100
In the case of tons, it was launched only by the rocket engine installed in the projectile.

[0003]

Since the conventional multistage acceleration method is configured as described above, the following problems exist. That is, the Saturn V rocket used for the NASA Apollo program for lunar exploration has a total length of about 111
Since it has a total weight of 2,940 tons and requires a large amount of liquid hydrogen and an oxidizer, its danger is extremely high, and preparation for launch is a difficult task. The Japanese H-1 rocket also had a total length of about 40 m, a total weight of about 140 tons, and was launching a payload of about 0.5 tons into a geosynchronous orbit, so the size of the payload was abnormal. Met.

The present invention has been made to solve the above problems, and in particular, in the first stage, after accelerating the flying body by the electric accelerating means, the ramjet section and the rocket engine in the flying body are used. It is an object of the present invention to provide a multi-stage acceleration method and apparatus in which the second stage and the third stage are accelerated to reduce the load on the flying object and obtain an ultrahigh speed.

[0005]

According to the multi-stage acceleration method of the present invention, an electric accelerating means launches a projectile having a payload at its tip, and then ignites a ramjet portion of the projectile to make the final stage the flight. It is a method of igniting the rocket engine of the body to accelerate in multiple stages.

In the multistage accelerating device according to the present invention, a projectile having a rocket engine and a ramjet section behind a payload is loaded in a fixedly arranged electric accelerating means, and the projectile is initially initialized by the electric accelerating means. It is a configuration that accelerates.

More specifically, the electric accelerating means is composed of electrothermal chemical reaction means.

[0008]

In the multistage accelerating method and apparatus according to the present invention, first, as a first stage, a projectile having a payload at its tip is launched by an electrical accelerating means such as an electrothermal chemical reaction, and then a ramjet is produced during flight of the projectile. By igniting the section, it becomes the second stage and the mounted fuel can be reduced as much as possible, and at the end when the aircraft speed approaches the jet injection speed of about 5 km / s, the ramjet section is disconnected or the air intake port is opened. By closing and igniting the rocket engine, multi-stage firing with three-stage ignition can be achieved. Therefore,
Since the flying body is initially accelerated by the electric accelerating means in the first stage, the flying body itself can be composed of the ramjet unit and the rocket engine, and it is possible to easily achieve ultra-high speed with a small size and light weight.

[0009]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Preferred embodiments of the multistage acceleration method and apparatus according to the present invention will be described in detail below with reference to the drawings. Figure 1
4 to 4 show an apparatus applied to the multi-stage acceleration method according to the present invention, FIG. 1 is a sectional view showing a flying object, FIG. 2 is a sectional configuration view showing the apparatus, and FIG. 3 is an arrow A direction in FIG. 4 is a cross-sectional view showing the acceleration starting state of FIG.

In FIG. 1, reference numeral 1 denotes a payload provided at the tip of the flying vehicle 1A. The payload 1 is located at the tip of the rocket engine 2, and the rocket engine 2 is mounted on the sabot 4. It is attached to the air intake port 5a of the ramjet unit 5. Inside the body 3 of the ramjet unit 5, the solid fuel 3a and the nozzle 3b are provided.
Is provided with the payload 1, the rocket engine 2, the ramjet unit 5, and the sabot 4 described above.
Are configured.

2 and 3 show an electric accelerating means 10 using a well-known electrothermochemical reaction means which is responsible for the first stage acceleration when accelerating the flying body 1A. Is not limited to this electrothermal chemical reaction means, and other known means such as electrothermal acceleration can be used. The rocket engine 2 and the ramjet unit 5 can be connected to each other by using a well-known explosion bolt.

Reference numerals 11a and 11 in FIGS.
What is indicated by b and 11c is an electrothermal chemical reaction section as a plurality of electrothermal chemical reaction means using hydrogen gas at high temperature and high pressure obtained by using an electrothermal chemical reaction between water and aluminum (other materials may be used). Yes, each electrothermal chemical reaction part 1
1a, 11b, 11c are loaded in the respective loading holes 13a, 13b, 13c of the electrothermal chemical reaction tube 12 having an L-shaped overall shape, and the electric heating fuses 18a, 18b, 1 are respectively provided.
8c is connected.

A switch 14 and a power source 15 are connected in series between the electrothermal chemical reaction tube 12 and the electrothermal squib 18c of the electrothermal chemical reaction section 11c. The electrothermal chemical reaction tube 1
The high pressure gas introduction pipe portion 16 formed in 2 has an accelerating pipe 1 formed in a direction orthogonal to the high pressure gas introduction pipe portion 16.
7 is formed, and the acceleration tube 17 has a length of, for example, 100 m.
To 400 m. A protrusion 17 a is formed on the bottom of the acceleration tube 17.

Next, the acceleration method will be described. First, FIG.
As shown by, when the switch 14 is turned on after the flying body 1A is loaded into the accelerating tube 17, the electrothermal chemical reaction section 11c of the loading hole 13c starts the reaction, and the explosion energy after the start of the reaction is The wall of the loading hole 13b is broken to induce an electrothermal chemical reaction. After that, each of the remaining electrothermal chemistry parts 11b,
11a are successively induced to explode, and the spiral high-pressure gas introduction pipe 16 as shown in FIG. 3 is filled with a reaction product gas composed of high-temperature high-pressure hydrogen gas or the like. The high-pressure gas introduction pipe 16 is rotated and centrifuged. The generated light gas such as hydrogen pushes the flying body 1A while swirling around the protrusion 17a.
Is efficiently emitted through the first acceleration through the electric acceleration means 10. This launched projectile 1A disconnects the sabot 4 at an appropriate position according to a command from the ground, and at the same time, starts the ramjet unit 5 to perform the first additional speed (second step), and after that, Rocket engine 2
Is ignited and the final speed is reached after the third stage of acceleration. In the above-mentioned embodiment, the case where the flying body 1A is lifted up has been described, but when it is performed on the ground, the additional speed can be increased by the coil gun, the electromagnetic gun or the like when the rocket propulsion is completed.

[0015]

Since the multistage acceleration method and apparatus according to the present invention are configured as described above, the following effects can be obtained. That is, after the initial acceleration of the first stage of the flying object by the electric accelerating means, the ramjet section and the rocket engine perform two additional speeds. Super high speed (10km /
s) can be achieved. In addition, since the mass of the first-stage fuel in the conventional rocket (these masses are about 50% or more of the whole rocket) and the mass corresponding to the oxidizer of the second-stage fuel are not required, they are launched from the ground. The mass of the rocket when it is caused to be reduced by about 60 to 70%. On the contrary, the final launch mass (for example, a geostationary satellite) that is 60 to 70% larger can be launched.

[Brief description of drawings]

FIG. 1 is a sectional view showing a flying object according to the present invention.

FIG. 2 is a sectional view showing a multi-stage accelerator according to the present invention.

FIG. 3 is a configuration diagram from the arrow A side of FIG.

FIG. 4 is a configuration diagram showing an acceleration state of FIG.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Payload 1A Flying body 2 Rocket engine 5 Ramjet part 10 Electrical acceleration means 11a-11c Electrothermal chemical reaction part

Claims (3)

[Claims] 1. The payload by means of electrical acceleration means (10)
After launching the projectile (1A) having (1) at the tip, the ramjet section (5) of the projectile (1A) is ignited, and the rocket engine (2) of the projectile (1A) is used as the final stage. A multi-stage acceleration method characterized by igniting and multi-stage acceleration. 2. A flying body (1A) having a rocket engine (2) and a ramjet section (5) behind a payload (1) is loaded into a fixedly arranged electric acceleration means (10), (1A)
A multistage accelerating device, characterized in that the electric accelerating means (10) is used for initial acceleration. 3. The multistage accelerating apparatus according to claim 2, wherein the electric accelerating means (10) comprises electrothermal chemical reaction sections (11a to 11c).