JPH1073051A - Solid rocket and propulsion control method therefor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve thrust with a same solid propellant rate to more extent by filling solid propellant through an insulation in the inner surface of a pressure container, and providing with oxidizing agent for insulation combustion, in a solid rocket provided with a nozzle downstream from the solid propellant. SOLUTION: A solid rocket 1 is formed in such a constitution that an insulation 3 is arranged in the inner surface of a pressure container 2, solid propellant 4 is filled inside thereof, a nozzle 5 is arranged downstream from the solid propellant 4, and an igniter is arranged upstream and downstream from the solid propellant 4. Oxidizing agent container 7 for storing liquid oxidizing agent is arranged outside the pressure container 2, and the oxidizing agent container 7 and a combustion chamber 2a in the pressure container 2 are connected to each other by a liquid piping 8. Solid propellant 4 is ignited and burnt by an igniter so as to obtain thrust, the liquid oxidizing agent 6 is supplied to the combustion chamber 2a, it is brought into contact with the insulation 3 so as to generate combustion, its combustion gas is injected from the nozzle 5 so as to obtain thrust to more extent.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a solid rocket used as a means for propelling a flying object, and to a propulsion control method used for controlling the propulsion of the solid rocket.

[0002]

2. Description of the Related Art Flying means (rockets) can be roughly classified into those using liquid propellants and those using solid propellants.

[0003] Among them, when a solid propellant is used, the structure is simple, it can be fired immediately, a relatively large specific thrust can be obtained, and it can be stored for a long time. Therefore, it is used in various fields such as for artificial satellites and meteorological observations in comparison with liquid propellants.

FIG. 3 shows an example of a conventional solid rocket. In the solid rocket 31 shown in FIG. 3, an insulation 33 is provided on the inner surface of a pressure vessel (combustion vessel) 32 having a substantially cylindrical shape. This insulation 3
3, a solid propellant 34 is loaded, and a nozzle 35 is provided on the downstream side of the solid propellant 34. The upstream side (for example, the center of the head) and the downstream side (for example, near the nozzle 35) of the solid propellant 34 ), An igniter as an igniter (not shown)
The structure is prepared for.

In the solid rocket 31 having such a structure, a solid propellant 3 is provided by an igniter (not shown).
4 is burned and the combustion gas is ejected from the nozzle 35 to obtain a thrust.

[0006] After the combustion of the solid propellant 34 is completed, the insulation 33 is generated as a very small residual thrust due to thermal decomposition.

[0007]

In such a solid rocket, for example, in the case of a solid rocket (motor) for the upper stage, the specific thrust Isp is about 300 kg · sec / kg when the amount of the solid propellant is about 100 to several hundred kg. However, there is a problem that further improvement of thrust and realization of finer propulsion control with the same solid propellant amount are desired.

[0008]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems, and has been made in consideration of the above problem. In a solid rocket using a solid propellant as a propulsion source, the thrust of the same solid propellant is further increased. The purpose of the present invention is to make it possible to realize improvement and finer propulsion control.

[0009]

According to a first aspect of the present invention, there is provided a solid rocket including a solid propellant loaded on an inner surface of a pressure vessel via an insulation and a downstream side of the solid propellant. A solid rocket with a nozzle on the side is characterized by having an oxidizing agent for insulation combustion.

[0010] In an embodiment of the solid rocket according to the present invention, as described in claim 2, an oxidizing agent is provided inside the pressure vessel,
As described in claim 3, the oxidizing agent may be provided outside the pressure vessel.

[0011] Similarly, in the embodiment of the solid rocket according to the present invention, as described in claim 4, a configuration using a liquid oxidant as the oxidant can be adopted. According to a fifth aspect of the present invention, the inside of the pressure vessel provided with the insulation and the inside of the oxidant vessel containing the liquid oxidant can be connected by a liquid pipe. As described above, a configuration having a pressurized gas container containing a pressurized gas for pressing the liquid oxidant in the oxidant container can be provided.

In this case, the opening of the valve provided in the middle of the piping and / or
Alternatively, a configuration having a control mechanism for controlling the supply / stop of the liquid oxidant into the pressure vessel with the degree of pressurization by the pressurized gas can be employed.

The solid rocket propulsion control method according to the present invention is characterized in that a solid propellant is loaded into an inner surface of a pressure vessel via an insulation and a downstream side of the solid propellant is provided. In controlling the propulsion of a solid rocket having a nozzle, the propulsion is controlled by burning the insulation in accordance with the end of combustion of the solid propellant.

In the embodiment of the method for controlling the propulsion of a solid rocket according to the present invention, the combustion of the insulation is performed by supplying the liquid oxidant into the pressure vessel. In this case, in this case, as described in claim 10, the supply / stop of the liquid oxidant to the inside of the pressure vessel is performed by pressurization / pressurization stoppage by the pressurized gas, Claim 1
As described in 1, the supply of the liquid oxidant into the pressure vessel is performed when the thrust due to the combustion of the solid propellant becomes 10% or less of the main thrust (the time after the thrust becomes zero). Is also included.).

The solid rocket and the method of controlling its propulsion according to the present invention have the above-described configuration, but the shape of the pressure vessel (combustion vessel) is not particularly limited. In the case of (motor), a spherical shape may be used, or a cylindrical shape may be used.

As the insulation provided on the inner surface of the pressure vessel, rubber-like insulation is used, and ethylene-propylene rubber (EPDM, EPM) and natural rubber (N
R) • isoprene rubber (IR), terminal carboxyl group polybutadiene rubber (CTPB), terminal hydroxyl group polybutadiene rubber (HTPB) and the like, and in addition, resin-based polymer materials (FRP) and the like can also be used. Not done.

Further, the solid propellant loaded inside the insulation is not particularly limited. For example, as a oxidizing agent, ammonium perchlorate (A
P), ammonium nitrate (AN), nitronium perchlorate (NP), potassium perchlorate (KP), cyclotrimethylenetrinitramine (RDX), cyclotetramethylenetetranitramine (HMX), etc. Polysulfide (PS), polyvinyl chloride (PVC), polyurethane (PU), terminal carboxyl group polybutadiene (CTPB), terminal hydroxyl group polybutadiene (HTPB), etc. It is also possible to use a mixture of a plasticizer, a combustion catalyst, a metal fuel (Al, Mg, Be, B, Zr, etc.), a vibration-combustion inhibitor (Al, Zr, ZrC, etc.), etc. Can be used.

The solid rocket and its propulsion control method according to the present invention are characterized in that the thrust is controlled by burning the insulation in accordance with the termination of the combustion of the solid propellant. It is characterized in that it is provided with an oxidizing agent for burning the insulation.

Examples of such oxidizing agents for insulation combustion include nitrous oxide (N ₂ O), nitrous oxide (N ₂ O ₄ ; NTO), nitric acid (HNO ₃ ), and hydrogen peroxide (H ₂ O). ₂ O ₂ ) and the like are used, and this is not particularly limited, but a liquid oxidizing agent is more preferably used.

Such an oxidizing agent for the combustion for insulation may be provided inside the pressure vessel or provided outside the pressure vessel, and may be provided inside the pressure vessel provided with the insulation. And the inside of the oxidizing agent container containing the liquid oxidizing agent can be connected by piping.

Then, the pressurized gas contained in the pressurized gas container can be used so that the liquid oxidant in the oxidant container can be sent into the pressure vessel through the pipe.

Further, a valve is provided in the pipe connecting the pressure vessel and the oxidant container, and by controlling the opening of the valve, the supply of the liquid oxidant into the pressure vessel is controlled. Insulation combustion can be started, the degree of combustion can be adjusted, combustion can be stopped, or combustion can be stopped and then re-burned.

Alternatively, by controlling the supply of the pressurized gas from inside the pressurized gas container, the supply of the liquid oxidant into the pressure container is controlled to start the combustion of the insulation or the combustion of the combustion. The degree can be adjusted, the combustion can be stopped, or the combustion can be stopped and then re-burned.

In this case, when dinitrogen monoxide (laughing gas; N ₂ O) is used as the liquid oxidizing agent, the liquid oxidizing agent can sometimes be fed into the pressure vessel without using a pressurized gas.

[0025]

According to the solid rocket according to the present invention,
A solid propellant was loaded into the inner surface of the pressure vessel via insulation, and a solid rocket equipped with a nozzle on the downstream side of the solid propellant was equipped with an oxidizing agent for insulation combustion. Since the insulation can be burned at the end of the combustion of the medicine, it is possible to obtain the thrust by the combustion of the insulation. Therefore, the thrust can be further improved by the amount of the thrust, and the finer propulsion control can be performed.

And, as described in claim 2,
By providing the oxidizing agent inside the pressure vessel, it is possible to simplify the appearance as a whole as in the prior art. Providing an oxidizing agent outside the pressure vessel has a remarkably excellent effect that a conventional solid rocket can be adopted without largely changing it.

Further, by using a liquid oxidizing agent as the oxidizing agent, it is possible to easily supply / stop and control the supply amount of the oxidizing agent. In addition, it is possible to perform finer control, such as burning / stopping insulation, controlling the amount of combustion, and reburning after stopping the combustion once, further improving the orbit insertion accuracy when used as an upper rocket motor, for example. Is significantly improved.

Further, as set forth in claim 5, the inside of the pressure vessel provided with the insulation and the inside of the oxidant container containing the liquid oxidant are connected by a pipe, so that the insulation is provided. This has the significant advantage that the separation of the oxidant from the liquid oxidant and the supply of the liquid oxidant to the insulation can be made more reliable.

Further, according to a sixth aspect of the present invention, a pressurized gas container containing a pressurized gas for pressing a liquid oxidant in the oxidant container is provided. By the pressurization, the pressurization stop, and the pressure control, the remarkably excellent effect that the supply / stop of the liquid oxidant to the insulation and the control of the supply amount can be easily performed is brought about.

Further, as described in claim 7, the supply / stop of the liquid oxidant into the pressure vessel is controlled by the opening degree of a valve provided in the pipe and / or the degree of pressurization by the pressurized gas. The provision of a control mechanism for controlling has a remarkably excellent effect that the supply control of the liquid oxidant to the insulation in the pressure vessel can be more finely adjusted.

In the method for controlling the propulsion of a solid rocket according to the present invention, the solid propellant is loaded into the inner surface of the pressure vessel via the insulation, and the propulsion of the solid rocket having a nozzle downstream of the solid propellant is controlled. In this case, the propulsion is controlled by burning the insulation in accordance with the end of the combustion of the solid propellant, so that in addition to the conventional thrust of only the combustion of the solid propellant, a thrust by the combustion of the insulation can be obtained. It is possible to obtain a remarkably excellent effect that it is possible to obtain more thrust and to perform finer propulsion control at the same amount of solid propellant as before.

And, as described in claim 9,
By performing the combustion of the insulation by supplying the liquid oxidant to the inside of the pressure vessel, it is possible to easily control the supply / stop of the oxidant and the supply amount. A remarkably excellent effect is achieved in that finer propulsion control, such as combustion amount control and further reburning after stopping the combustion, is possible.

Further, as described in claim 10,
By supplying and stopping the liquid oxidizing agent to the inside of the pressure vessel by pressurizing and stopping the pressurization by the pressurized gas, the pressurizing and stopping by the pressurized gas and the liquid to the insulation by the pressure control are controlled. A remarkably excellent effect is obtained in that the supply / stop of the oxidant and the control of the supply amount can be easily performed.

Further, as described in claim 11, the supply of the liquid oxidant into the pressure vessel is performed when the thrust by the combustion of the solid propellant becomes 10% or less of the main thrust. By doing so, it is possible to obtain a continuous thrust, and for example, an extremely excellent effect that it is possible to further improve the accuracy of orbital insertion of the artificial satellite by the upper rocket (motor) is brought about.

[0035]

FIG. 1 shows an embodiment of a solid rocket according to the present invention. The solid rocket 1 shown in FIG. 1 has an inner surface of a pressure vessel (combustion vessel) 2 having a substantially cylindrical shape. An insulation 3 is provided, a solid propellant 4 is loaded inside the insulation 3, and a nozzle 5 is provided on the downstream side of the solid propellant 4, so that an upstream side (for example, the center of the head) of the solid propellant 4 An igniter (not shown) as an igniter is provided on the downstream side (for example, near the nozzle 5).

Further, outside the pressure vessel 2 (in other embodiments, it may be inside), an oxidant container 7 containing a liquid oxidant 6 is provided. The liquid pipe 8 connects the combustion chamber 2a to the liquid chamber 8a.
A valve 9 is provided in the middle of the process, and the oxidant container 7 contains a pressurized gas (for example, He gas) for pressing the liquid oxidant 6 contained in the oxidant container 7. It has a structure in which a pressurized gas container 10 is connected via a gas pipe 11.

In the solid rocket 1 having such a structure, the solid propellant 4 is ignited and burned by an igniter (not shown), and thrust is obtained by ejecting the combustion gas from the nozzle 5.

When the combustion of the solid propellant 4 is completed, the valve 9 is opened at a desired degree of opening, and the pressurized gas in the pressurized gas container 10 is set to the desired degree of pressurization, thereby obtaining the liquid oxidant 6. By pressing the liquid oxidant 6 into the pressure vessel 2
Of the insulation 3 in a heated or thermally decomposed state to cause combustion by causing the liquid oxidant 6 to come into contact with the insulation 3, and the combustion gas of the insulation 3 is ejected from the nozzle 5 to generate thrust. obtain.

[0039] Figure 2 is intended to illustrate the changes due to thrust of time in propulsion control method for a solid rocket according to the invention, the main thrust is obtained by igniting a solid propellant 4 at time T _0, the solid in about 10% or less and since the time T ₁ of the thrust combustion of propellant 4 is approaching the end of the main thrust feeds feeding a liquid oxidizer 6 by opening the valve 9 and thereby the combustion of insulation 3 between the time _{T 1} to time _{T 2,} insulation 3
To obtain thrust by combustion.

Further, by reducing or stopping the supply of the liquid oxidizing agent 6 by reducing the opening degree of the valve 9 and then restarting it, the thrust by the combustion of the insulation 3 is reduced or stopped and further recovered. For example, by using the rocket motor for an artificial satellite (upper stage), it is possible to finely control the position of the artificial satellite, and further improve the accuracy of orbital insertion of the artificial satellite. Can be.

As a specific example, when the terminal hydroxyl group polybutadiene (HTPB) is used for the insulation and the nitric oxide (N ₂ O) is used as the oxidizing agent, the combustion of the solid propellant is almost completed. When the insulation is burned by supplying the oxidizing agent, a thrust of about 260 kg can be obtained with respect to the main thrust of about several tons by the solid propellant, and about 10% is obtained by the combustion of the insulation. An increase in thrust before and after was realized.

[Brief description of the drawings]

FIG. 1 is an explanatory sectional view of a solid rocket according to an embodiment of the present invention.

FIG. 2 is a graph showing a change in thrust with time in a method for controlling propulsion of a solid rocket according to one embodiment of the present invention.

FIG. 3 is an explanatory sectional view of a solid rocket according to a conventional example.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Solid rocket 2 Pressure container 3 Insulation 4 Solid propellant 5 Nozzle 6 Liquid oxidizer 7 Oxidizer container 8 Liquid piping 9 Valve 10 Pressurized gas container 11 Gas piping

Claims (11)

[Claims] 1. A solid rocket having a solid propellant loaded on an inner surface of a pressure vessel via an insulation and a nozzle provided on a downstream side of the solid propellant is provided with an oxidizing agent for insulation combustion. Characterized solid rocket. 2. The solid rocket according to claim 1, wherein an oxidizing agent is provided inside the pressure vessel. 3. The solid rocket according to claim 1, wherein the oxidizing agent is provided outside the pressure vessel. 4. The solid rocket according to claim 1, wherein a liquid oxidizer is used as the oxidizer. 5. The solid rocket according to claim 1, wherein the inside of the pressure vessel provided with the insulation and the inside of the oxidant container containing the liquid oxidant are connected by piping. 6. The solid rocket according to claim 4, further comprising a pressurized gas container containing a pressurized gas for pressing a liquid oxidant in the oxidant container. 7. A control mechanism for controlling the supply / stop of the liquid oxidant into the pressure vessel according to the degree of opening of a valve provided in the middle of the pipe and / or the degree of pressurization by the pressurized gas. A solid rocket according to any one of the above. 8. A method for loading a solid propellant into an inner surface of a pressure vessel via insulation and controlling the propulsion of a solid rocket having a nozzle on the downstream side of the solid propellant in accordance with the end of combustion of the solid propellant. And controlling the propulsion by burning the insulation. 9. The solid rocket propulsion control method according to claim 8, wherein the combustion of the insulation is performed by supplying a liquid oxidizing agent into the pressure vessel. 10. Supply of a liquid oxidant into the pressure vessel
The method for controlling the propulsion of a solid rocket according to claim 9, wherein the stopping is performed by pressurization with pressurized gas and stop of pressurization. 11. The propulsion control of a solid rocket according to claim 9, wherein the supply of the liquid oxidant into the pressure vessel is performed when the thrust by the combustion of the solid propellant becomes 10% or less of the main thrust. Method.