JPH04370354A - Space rocket using hydrogen generating explosive - Google Patents

Abstract

PURPOSE:To make it passible the temperature of an engine wall to be relatively low so as to provide safety and high propulsive force by injecting hydrogen gas, not only eliminating necessity for super low temperature but also enabling an injection speed to mostly increase at an equal temperature, by utilizing a propellant especially using a hydrogen generating explosive using chemical reaction of aluminum with water, in a space rocket using the hydrogen generating explosive. CONSTITUTION:A space rocket using a hydrogen generating explosive is provided with a propellant 1, consisting of the hydrogen generating explosive constituted of a porous aluminum unit and water provided in a main unit 5 having a nozzle 4, and a combustion chamber 3, provided in the above-mentioned main unit 5, and propelled by the propellant 1.

Description

[Detailed description of the invention]

0001

[Industrial Application Field] The present invention relates to a space rocket that uses hydrogen-generating gunpowder, and in particular, uses a propellant that uses hydrogen-generating gunpowder that uses a chemical reaction between aluminum and water, thereby requiring extremely low temperatures. To obtain a space rocket using a hydrogen-generating gunpowder that is safe and has high propulsion, which not only does not cause the engine to burn, but also allows the temperature of the engine chamber to be relatively low by injecting hydrogen gas, which can achieve the highest injection speed at the same temperature. Concerning new improvements for.

0002

2. Description of the Related Art Conventionally, this type of rocket has generally used a liquid fuel rocket propulsion device. In other words, typical examples are shown in Fig. 5. In Fig. 5, the symbol 1 indicates an oxidizing agent made of oxygen, fluorine, etc., and a fuel such as liquid hydrogen or hydrazine, which is stored at an extremely low temperature. A main body 5 having a fuel chamber 3 and a nozzle 4 is connected to the liquid propellant 1 via a pump 2. In the above configuration,
Liquid propellant 1 sent into combustion chamber 3 by pump 2
is ignited in the optimum state for combustion, and is injected from the nozzle 4 at high speed to obtain propulsive force.

0003

[Problems to be Solved by the Invention] Conventional rockets were constructed as described above, and therefore had the following problems. In other words, the liquid propellants mentioned above require extremely dangerous oxygen, fluorine, liquid hydrogen, hydrazine, etc. to be stored inside the rocket at extremely low temperatures, and extremely dangerous work such as sealing cryogenic fuel is required. could not be avoided. In addition, because this extremely low temperature liquid fuel was used to generate high-temperature gas such as water (H2O), which is a reaction product, to obtain propulsive force, the ejection velocity was large (roughly equal to the thermal velocity of the generated gas). In order to obtain this, the rocket had to be heated to a high temperature, and the materials used in rocket production had to be carefully considered, making it extremely expensive.

The present invention has been made to solve the above-mentioned problems. In particular, by using a propellant that uses hydrogen-generating gunpowder that uses a chemical reaction between aluminum and water, extremely low temperatures can be achieved. By injecting hydrogen gas, which is not necessary and can be ejected at the highest speed at the same temperature, the space rocket uses a safe and high-propulsion hydrogen-generating gunpowder that can keep the temperature of the engine wall relatively low. The purpose is to provide.

[0005]

[Means for Solving the Problems] A space rocket using hydrogen-generating gunpowder according to the present invention includes a propellant made of hydrogen-generating gunpowder, which is provided in a main body having a nozzle and is composed of a porous aluminum body and water, and It is configured to be propelled by the propellant.

A space rocket using another hydrogen-generating gunpowder according to the present invention includes a combustion chamber provided in a main body having a nozzle, a suspension chamber connected to the combustion chamber, and a pump installed in the suspension chamber. The main body is propelled using a slurry-type hydrogen generating agent as a propellant, which generates high-temperature hydrogen through a chemical reaction between the aluminum powder and water.

More specifically, the aluminum powder is protected with dry nitrogen.

[0008]

[Operation] In the space rocket using the hydrogen-generating gunpowder according to the present invention, among the aluminum and water that make up the propellant, when the aluminum is heated to near its melting point using an auxiliary means such as an ignition device, Reacts with water and generates heat. After this reaction has started, high-temperature hydrogen can be constantly generated by utilizing the generated heat to maintain the molten state of aluminum, and this high-temperature hydrogen is injected from the nozzle to propel the rocket. do. Furthermore, the reaction between aluminum and water is extremely slow near room temperature, and therefore the safety of the propellant can be maintained at an extremely high level.

[0009]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Preferred embodiments of a space rocket using hydrogen-generating gunpowder according to the present invention will be described in detail below with reference to the drawings. Note that the same reference numerals are used to describe the same or equivalent parts as in the conventional example. 1 to 4 are for showing a space rocket using hydrogen-generating gunpowder according to the present invention, in which FIG. 1 is a sectional view, FIG. 2 is a sectional view in an operating state, and FIG. 3 shows another embodiment. 4 is a block diagram showing another embodiment of FIG. 3.

In FIG. 1, the reference numeral 1 indicates a propellant made of hydrogen-generating gunpowder, which is provided in a longitudinal body 5 and is made of a porous aluminum body impregnated with water.
Its overall shape is a ring.

A hollow combustion chamber 3 is formed at the axial center of the propellant 1, and an ignition device 1A for, for example, an explosive is provided at the tip of the combustion chamber 3.

A nozzle 4 is formed at the rear end of the main body 5 so as to communicate with the combustion chamber 3, and in the configuration of the space rocket shown in FIG. When ignited, the aluminum melts and reacts violently with water, so the high-temperature hydrogen generated in the combustion chamber 3 is ejected from the nozzle 4 at high speed, creating the state shown in FIG. 2 and generating propulsive force.

In addition, in the case of a space rocket using a slurry-type hydrogen generating agent as another embodiment shown in FIG. A first pump 1 is connected to the suspension chamber 10.
The first tank 13 and the second tank 13 through the first and second pumps 12
A tank 14 is connected.

The first tank 13 contains powdered aluminum powder 13a protected with dry nitrogen or the like, and the second tank 14 contains water 1 as an oxidizing agent.
4a is built-in.

In the configuration of FIG. 3 described above, each pump 11
, 12 into the suspension chamber 10 are mixed in an optimal state for combustion, ignited in the combustion chamber 3, and combusted to generate high-temperature hydrogen. is injected backward from the nozzle 4 as shown by the arrow, generating thrust.

Although the combustion chamber 3 has been described as being for sludge combustion, this combustion chamber 3 can also be used in combination with a conventional solid fuel configuration, and the high temperature of this solid fuel can be utilized to combine water and aluminum. It is also possible to ignite the suspension,
The configuration in this case is shown in FIG. 4 as another embodiment.

In FIG. 4, the reference numeral 20 indicates a solid fuel, and this solid fuel 20 is provided in the combustion chamber 3, and the thermal energy generated by this solid fuel 20 is used to discharge the solid fuel from the suspension chamber 10. The suspension-type hydrogen generating gunpowder is ignited, and high-temperature hydrogen is injected from the nozzle 4 in the direction of the arrow to propel the main body 5.

[0018]

[Effects of the Invention] Since the space rocket using the hydrogen-generating gunpowder according to the present invention is constructed as described above, the following effects can be obtained. In other words, since the rocket was constructed using hydrogen-generating gunpowder as the propellant, it is not only extremely safe compared to conventional liquid fuels, but also allows the rocket engine to theoretically have the highest specific impulse at the same combustion temperature. .

[Brief explanation of drawings]

FIG. 1 is a sectional view showing a space rocket using hydrogen-generating gunpowder according to the present invention.

FIG. 2 is a sectional view showing the operating state of FIG. 1;

FIG. 3 is a sectional view showing another embodiment.

FIG. 4 is a sectional view showing another embodiment of FIG. 3;

FIG. 5 is a sectional view showing a conventional rocket.

[Explanation of symbols]

1 Propellant 3 Combustion chamber 4 Nozzle 5 Main body 10 Suspension chamber 11 1st pump 12 Second pump 13a Aluminum powder 14a Water

Claims (3)

[Claims] Claim 1: A propellant (1) comprising a hydrogen-generating gunpowder made of a porous aluminum body and water, provided in a main body (5) having a nozzle (4), and a combustion propellant provided in the main body (5). A space rocket using a hydrogen-generating gunpowder, characterized in that the space rocket is equipped with a chamber (3) and is propelled by the propellant (1). 2. A combustion chamber (3) provided in a main body (5) having a nozzle (4), a suspension chamber (10) connected to the combustion chamber (3), and a suspension chamber (10) connected to the combustion chamber (3). ) to the pump (1
Aluminum powder (13) supplied via aluminum powder (1,12)
a) and water (14a), the aluminum powder (
A space rocket using a hydrogen-generating gunpowder, characterized in that the main body (5) is propelled by using a slurry-type hydrogen-generating gunpowder that generates high-temperature hydrogen through a chemical reaction between 13a) and water (14a) as a propellant (1). . 3. The aluminum powder (13a) comprises:
A space rocket using a hydrogen-generating gunpowder according to claim 1, characterized in that it is protected with dry nitrogen.