JPH0893558A - Hybrid rocket - Google Patents

Abstract

PURPOSE: To realize a decrease in system weight as well as to enable combustion efficiency to be drastically improved. CONSTITUTION: A hybrid rocket is provided with a liquid oxidizing agent housing chamber 4 in which a liquid oxidizing agent 3 is housed, a solid fuel combustion chamber 7 in which solid fuel 8 having self-burning property is filled, a mixing combustion chamber 10 for mixing fuel component excessive gas to be generated by self-burning of the solid fuel 8 with a liquid oxidizing agent and burning it, and a liquid oxidizing agent supplying means (a pressurizing chamber 5 and a piston 11 as a movable isolating mechanism) taking pressure in the solid fuel combustion chamber 7 as a driving source.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a hybrid rocket provided with a liquid oxidizer and a solid fuel and capable of producing propulsion by high temperature and high pressure gas produced by mixing and burning the solid fuel and the liquid oxidizer. is there.

[0002]

2. Description of the Related Art Conventionally, as a hybrid rocket as described above, there is one shown in FIG. 4, for example. In the illustrated hybrid rocket 51, a liquid oxidizer 53 is filled in a tank 54 provided in an intermediate portion of a fuselage 52, and a combustion chamber 56 provided in a tail portion of the fuselage 52 is loaded with a solid fuel 55 of an inner surface combustion type. There is. The tank 54 and the combustion chamber 56 are connected via a control valve 57 and an injector 58, and a pressurizer 59 composed of a cylinder of high-pressure gas, a control valve, etc. is provided at the front of the tank 54. A nozzle 60 is provided at the rear end of the combustion chamber 56.

The hybrid rocket 51 described above injects the liquid oxidizer 53 whose pressure is increased by the pressurizer 59 in the tank 54 into the combustion chamber 56 by the control valve 57 and the injector 58, and the liquid oxidizer 53 and the solids. The fuel component decomposed and evaporated on the inner surface of the fuel 55 is mixed and burned, and the high temperature and high pressure gas generated thereby is ejected from the nozzle 60 to obtain a propulsive force.

Such a hybrid rocket 51 is
For example, it is described on page 655 of "Handbook of Aerospace Engineering and Supplement" issued by Maruzen on April 25, 1983.

[0005]

However, in the above-described conventional hybrid rocket 51, the pressurized liquid oxidizer 53 is caused to flow along the inner surface of the solid fuel 55 to form a boundary layer in the machine axis direction. Since the fuel components decomposed and evaporated from the solid fuel 55 are diffused and burned to generate high-temperature and high-pressure gas, the combustion state of the solid fuel 55 depends on the distribution of the liquid oxidizer 53 due to the change in the flow. It is difficult to stabilize, there is a problem that the combustion efficiency is low, and it is difficult to obtain sufficient performance, and a pressurizer 59 which is a heavy load as a pressurizing source of the liquid oxidizer.
However, there is a problem that the system weight increases and the propulsive performance is deteriorated, and it is a problem to solve these problems.

[0006]

SUMMARY OF THE INVENTION The present invention has been made in view of the above-mentioned conventional problems, and a hybrid rocket capable of significantly improving combustion efficiency and reducing system weight. It is intended to be provided.

[0007]

A hybrid rocket according to the present invention, as claimed in claim 1, comprises a liquid oxidant storage chamber containing a liquid oxidant, and a solid fuel combustion chamber loaded with a solid fuel having self-combustibility. A mixture combustion chamber that mixes and combusts a fuel component excess gas generated by self-combustion of a solid fuel with a liquid oxidizer, and a liquid oxidant supply unit that uses the pressure in the solid fuel combustion chamber as a power source According to a second aspect of the present invention, the liquid oxidant supply means changes the volume of the pressure chamber adjacent to the liquid oxidant storage chamber and communicating with the solid fuel combustion chamber, and the volumes of the liquid oxidant storage chamber and the pressure chamber in inverse proportion to each other. A movable isolation mechanism is provided, and a regulating valve for changing the flow rate between the pressure chamber side and the atmosphere side is provided in a distribution pipe that connects the solid fuel combustion chamber and the pressure chamber. As a configuration, as claim 4. The movable isolation mechanism is a piston that isolates the liquid oxidant storage chamber and the pressure chamber, and the movable isolation mechanism is a bellows that isolates the liquid oxidant storage chamber and the pressure chamber. According to a sixth aspect, the liquid oxidant supply means is a turbo pump, and the above-mentioned configuration is means for solving the problem.

The above-mentioned solid fuel is a substance having self-combustibility, and can be burned without depending on an oxidant, glycidyl azide polymer (GAP: Glycidyl Azide).
Polymer) can be used.

[0009]

In the hybrid rocket according to the first aspect of the present invention, the solid fuel is not combusted by diffusion but is self-combusted, and the combustion speed of the solid fuel depends on the difference in the distribution state due to the change in the flow of the liquid oxidizer. Therefore, the combustion state of the solid fuel is stabilized and the combustion efficiency is improved, and by adopting the liquid oxidant supply means, the pressure in the solid fuel combustion chamber serves as a power source for supplying the liquid oxidant.

In the hybrid rocket according to the second aspect of the present invention, as the liquid oxidant supply means, a movable isolation mechanism for changing the volumes of the pressure chamber and the liquid oxidant accommodating chamber, which communicate with the solid fuel combustion chamber, in inverse proportion to each other. By adopting it, the pressure in the solid fuel combustion chamber becomes a pressure source of the liquid oxidizer.

In the hybrid rocket according to the third aspect of the present invention, the flow rate to the pressure chamber side and the atmosphere side is changed by the adjusting valve provided in the flow pipe connecting the solid fuel combustion chamber and the pressure chamber. , Changing the pressure applied to the liquid oxidizer.

The hybrid rocket according to claim 4 of the present invention has a simpler and lighter structure by adopting the piston as the movable isolation mechanism, and the hybrid rocket according to claim 5 of the present invention has a movable isolation. By adopting a bellows as the mechanism, the structure becomes even lighter.

In the hybrid rocket according to the sixth aspect of the present invention, the turbo pump as the liquid oxidant supply means is driven by the pressure in the solid fuel combustion chamber, and thereby the liquid oxidant is supplied to the mixed combustion chamber.

[0014]

1 is a diagram showing an embodiment of a hybrid rocket according to claims 1 to 4 of the present invention.

The hybrid rocket 1 is provided with a tank 6 which forms a liquid oxidant accommodating chamber 4 accommodating the liquid oxidant 3 and a pressurizing chamber 5 adjacent to the head of the liquid oxidant accommodating chamber 4 in the middle of the airframe 2. The solid fuel combustion chamber 7 provided on the downstream side of the tank 6 has a self-combustible glycidyl azide polymer (G
A solid fuel 8 made of AP) is loaded, and a mixed combustion chamber 10 is provided between the solid fuel combustion chamber 7 and a nozzle 9 provided at the tail portion of the airframe 2. The solid fuel 8 is formed into an end face combustion type.

Inside the tank 6, there is provided a piston 11 as a movable isolation mechanism for changing the volumes of the liquid oxidant storage chamber 4 and the pressurizing chamber 5 in inverse proportion. In this embodiment, the pressurizing chamber 5 and the piston 11 as a movable isolation mechanism constitute a liquid oxidant supply means that uses the pressure in the solid fuel combustion chamber 7 as a power source.

The piston 11 is provided with an O-ring 12 at a sliding contact portion with the inner surface of the tank 6 so as to sufficiently seal the space between the liquid oxidant storage chamber 4 and the pressurizing chamber 5, and at the same time, the tank 6 The head 13 has a rod 13 slidably penetrating the head end plate 6a. An O-ring 14 is also provided between the head end plate 6 a and the rod 13.

The pressurizing chamber 5 is communicated with the solid fuel combustion chamber 7 by a flow pipe 15 provided outside the machine body 2.
Further, on the head side of the pressurizing chamber 5, there is provided an adjusting valve 17 for changing the flow rates to the pressurizing chamber 5 side and the atmosphere release channel 16 side.

The solid fuel combustion chamber 7 and the mixed combustion chamber 10 are partitioned by a partition wall 18. The partition wall 18 includes an igniter 19 for igniting the solid fuel on the solid fuel combustion chamber 7 side, and a plurality of orifices 18 a communicating with the solid fuel combustion chamber 7 and the mixed combustion chamber 10 to burn the solid fuel 8. The fuel component excess gas generated by the above is ejected from the orifices 18a into the mixed combustion chamber 10.

Further, in the liquid oxidant storage chamber 4, the airframe 2
The end portion on the head side of the liquid oxidant supply pipe 20 provided along the outer side of is connected. The end portion of the liquid oxidant supply pipe 20 on the tail side communicates with the mixed combustion chamber 10 via a plurality of injection holes 18b provided in the partition wall 18. Therefore, the liquid oxidant storage chamber 4 and the injection hole 18 b of the partition wall 18 are directly connected by the liquid oxidant feed pipe 20.

In the hybrid rocket 1 having the above structure, first, when the solid fuel 8 is ignited by the igniter 19, the solid fuel 8 having self-combustibility is solid fuel combustion chamber at a constant speed without depending on the oxidizer. Burns within 7. The fuel component excess gas generated by this is the partition wall 1
It is ejected into the mixed combustion chamber 10 through the eight orifices 18a.

When the pressure in the solid fuel combustion chamber 7 rises due to the start of combustion of the solid fuel 8, a part of the gas is introduced into the pressurizing chamber 5 through the flow pipe 15, and the piston 11 is tailed. Press in the direction. As a result, the liquid oxidant 3 is pressurized as the volume of the liquid oxidant storage chamber 4 is reduced, and the liquid oxidant 3 is sent to the plurality of injection holes 18 b of the partition wall 18 via the liquid oxidant feed pipe 20. It is injected into the mixed combustion chamber 10 through the injection hole 18b.

In the hybrid rocket 1, the liquid oxidizer 3 and the fuel component excess gas are mixed and burned in the mixed combustion chamber 10, and the high temperature and high pressure gas generated by this mixing and burning is nozzled. Propulsive force is obtained by ejecting from 9.

In this way, the hybrid rocket 1
Unlike the conventional case, the combustion speed of the solid fuel 8 is not influenced by the difference in the distribution state due to the change in the flow of the liquid oxidizer 3, so that the mixed combustion chamber 10 is passed through the orifice 18a.
The amount of gas ejected into the inside, that is, the amount of fuel component excess gas generated by the combustion of the solid fuel 8 is kept constant, and the mixing and combustion of this fuel component excess gas and the liquid oxidant 3 is very much. Stable and sufficient combustion efficiency can be obtained.

Further, since the hybrid rocket 1 employs the piston 10 which is a movable isolation mechanism for changing the volumes of the pressurizing chamber 5 communicating with the solid fuel combustion chamber 7 and the liquid oxidant containing chamber 4 in inverse proportion, The pressurizer, which is a heavy load used for pumping the liquid oxidizer, is abolished, and the pressure in the solid fuel combustion chamber 7 is used as a pressure source for the liquid oxidizer 3, so that the liquid oxidizer has a simple structure. 3 can be pumped.

Further, in the hybrid rocket 1, the adjusting valve 17 provided in the flow pipe 15 which connects the solid fuel combustion chamber 7 and the pressurizing chamber 5 to each other allows the gas to flow to the pressurizing chamber 5 side and the atmosphere release channel 16 side. In order to change the flow rate and adjust the thrust or further stabilize the combustion state, it is possible to change the pressure applied to the liquid oxidizer 3 and adjust the injection amount.

FIG. 2 is a diagram showing an embodiment of a hybrid rocket according to claims 1 to 3 and 5 of the present invention.
The same parts as those in the previous embodiment are designated by the same reference numerals and detailed description thereof will be omitted.

The hybrid rocket 31 of this embodiment
In the tank 6, there is provided a bellows 41 as a movable isolation mechanism that changes the volumes of the liquid oxidant storage chamber 4 and the pressurizing chamber 5 in inverse proportion. The bellows 41 has its end portion attached to the tail end plate 6b of the tank 6 in a sealed manner, and completely separates the liquid oxidant storage chamber 4 and the pressurizing chamber 5. In this embodiment, the pressurizing chamber 5 and the bellows 41 as a movable isolation mechanism constitute a liquid oxidant supply means that uses the pressure in the solid fuel combustion chamber 7 as a power source.

In the hybrid rocket 31, a part of the gas is introduced into the pressurizing chamber 5 as the solid fuel 8 starts to be combusted, and the bellows 41 is pushed toward the tail by the pressure of the gas, so that the bellows 41 is pushed. The liquid oxidizer 3 is pressurized while compressing the liquid 41, and the liquid oxidizer 3 is injected with the injection holes 18 b of the partition wall 18.
Is injected into the mixed combustion chamber 10.

As described above, in the above-described hybrid rocket 31, since the bellows 41, which is the movable separating mechanism, is adopted, the structure as the pressurizing means for the liquid oxidizer 3 is further simplified and the weight is greatly reduced. It will be.

FIG. 3 is a diagram showing an embodiment of a hybrid rocket according to claims 1 and 6 of the present invention. The same parts as those in the previous embodiment are designated by the same reference numerals and detailed description thereof will be omitted.

The hybrid rocket 51 of this embodiment
Is equipped with a turbo pump 52 as a liquid oxidant supply means, which uses the pressure in the solid fuel combustion chamber 7 as a power source, on the tail side of the liquid oxidant storage chamber 4 loaded with the liquid oxidant 3.

The partition wall 53 for partitioning the solid fuel combustion chamber 7 and the mixed combustion chamber 10 is hollow and annular in the circumferential direction, and has injection holes 53a on its inner peripheral surface at regular intervals. A gas injector 54, which is hollow and has an annular shape and has an injection hole 54a, is provided on the mixing combustion chamber 10 side of the partition wall 53, similarly to the partition wall 53.

The turbo pump 52 is provided on the intake side of the drive unit.
A flow pipe 15 that communicates with the solid fuel combustion chamber 7 is connected, and a liquid oxidant feed pipe 20 that communicates with the hollow portion of the partition wall 53 is connected to the pump portion that communicates with the liquid oxidant storage chamber 4. A gas supply pipe 55 communicating with the hollow portion of the gas injector 54 is connected to the exhaust side of the drive unit.

The hybrid rocket 51 uses the solid fuel 8
Along with the start of combustion, a part of the gas is introduced into the turbo pump 52 via the flow pipe 15. That is, the turbo pump 52 is driven by the pressure in the solid fuel combustion chamber 7 during the combustion of the solid fuel 8, the liquid oxidizer 3 is supplied to the partition wall 53 through the liquid oxidant feed pipe 20, and the injection of the partition wall 53 is performed. The liquid oxidizer 3 is injected into the mixed combustion chamber 10 through the hole 53a.

The gas used to drive the turbo pump 52 (fuel component excess gas) is sent to the gas injector 54 via the gas feed pipe 55, and the injection hole 54a of the gas injector 54 is supplied.
Is injected into the mixed combustion chamber 10 from the above, and is added to the mixing / combustion of the fuel component excess gas generated by the combustion of the solid fuel 8 and the liquid oxidizer 3 and used without waste.

Like the hybrid rocket 51,
Even when the turbo pump 52 is adopted as the liquid oxidant supply means using the pressure in the solid fuel combustion chamber 7 as a power source, the structure is simplified and the weight is reduced.

In each of the hybrid rockets 1, 31, and 51 of the above-described embodiments, the solid fuel 8 is formed as an end-face combustion type, but the invention is not limited to this, and for example, the solid fuel 8 is used. It is also possible to use an internal combustion type in which the hollow section is formed in a star shape so that the combustion area is constant, or an internal combustion type.

[0039]

As described above, according to the hybrid rocket according to the first aspect of the present invention, it becomes possible to burn the solid fuel at a stable speed, and the fuel component excess gas generated by this combustion is generated. Since it is possible to mix with a liquid oxidizer and perform stable combustion, it is possible to significantly improve the combustion efficiency, and the liquid oxidant supply means that uses the pressure in the solid fuel combustion chamber as a power source can reduce heavy weight. A certain pressurizer can be abolished, and the pressure in the solid fuel combustion chamber can be used to pump the liquid oxidizer with a simple structure, so the system weight can be significantly reduced, and the propulsion performance can be reduced with the weight reduction. Can be increased.

In the hybrid rocket according to the second aspect of the present invention, as the liquid oxidant supply means, a movable isolation mechanism for inversely proportionally changing the volumes of the pressure chamber and the liquid oxidant accommodating chamber, which communicate with the solid fuel combustion chamber, is used. By adopting this, as in the case of claim 1, the liquid oxidizer can be pressure-fed with a simple structure by utilizing the pressure in the solid fuel combustion chamber, and the system weight can be greatly reduced and The propulsion performance can be improved as the weight is reduced.

According to the hybrid rocket of the third aspect of the present invention, the pressure applied to the liquid oxidizer can be changed by the adjusting valve, whereby the thrust is adjusted or the combustion state is further stabilized. be able to.

In the hybrid rocket according to the fourth aspect of the present invention, by adopting the piston as the movable isolation mechanism, a simpler and lighter structure can be obtained in addition to the above effect. In the hybrid rocket according to Item 5, by adopting the bellows as the movable isolation mechanism, in addition to the above effects, further weight reduction can be realized, which can contribute to the improvement of propulsion performance.

Further, in the hybrid rocket according to claim 6 of the present invention, the turbo pump is used as the liquid oxidant supply means whose power source is the pressure in the solid fuel combustion chamber, so that the structure is simplified and accordingly It is possible to realize weight reduction and further enhance the liquid oxidizer supply function.

[Brief description of drawings]

FIG. 1 is a cross-sectional view showing an embodiment of a hybrid rocket according to claims 1 to 4 of the present invention with the head side omitted.

FIG. 2 is a cross-sectional view showing an embodiment of a hybrid rocket according to claims 1 to 3 and 5 of the present invention with the head side omitted.

FIG. 3 is a sectional explanatory view showing an embodiment of a hybrid rocket according to claims 1 and 6 of the present invention with the head side omitted.

FIG. 4 is a cross-sectional view showing a conventional hybrid rocket with the head side omitted.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 Hybrid rocket 3 Liquid oxidizer 4 Liquid oxidizer storage chamber 5 Pressurization chamber (liquid oxidizer supply means) 7 Solid fuel combustion chamber 8 Solid fuel 10 Mixed combustion chamber 11 Piston (liquid oxidizer supply means) as a movable isolation mechanism 15 flow pipe 17 adjusting valve 31 hybrid rocket 41 movable bellows (liquid oxidant supply means) 51 hybrid rocket 52 turbo pump (liquid oxidant supply means)

 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Inventor Taku Kuwahara 2 Takaracho, Kanagawa-ku, Yokohama, Kanagawa Nissan Motor Co., Ltd. (72) Hiroaki Odajima 2 Takara-cho, Kanagawa, Yokohama, Kanagawa Nissan Motor Co., Ltd. In the company

Claims (6)

[Claims] 1. A liquid oxidant storage chamber containing a liquid oxidant, a solid fuel combustion chamber loaded with a solid fuel having self-combustibility, a fuel component excess gas generated by self-combustion of the solid fuel, and a liquid oxidant. A hybrid rocket comprising: a mixed combustion chamber that mixes and combusts with each other, and a liquid oxidant supply unit that uses the pressure in the solid fuel combustion chamber as a power source. 2. The liquid oxidant supply means changes the volume of the pressure chamber adjacent to the liquid oxidant storage chamber and communicating with the solid fuel combustion chamber, and the volumes of the liquid oxidant storage chamber and the pressure chamber in inverse proportion. The hybrid rocket according to claim 1, further comprising a movable isolation mechanism. 3. The hybrid according to claim 2, wherein the flow pipe connecting the solid fuel combustion chamber and the pressurizing chamber is provided with a regulating valve for changing the flow rate to the pressurizing chamber side and the atmosphere side. rocket. 4. The hybrid rocket according to claim 2, wherein the movable isolation mechanism is a piston that isolates the liquid oxidant containing chamber and the pressurizing chamber from each other. 5. The hybrid rocket according to claim 2, wherein the movable isolation mechanism is a bellows that isolates the liquid oxidant storage chamber and the pressurizing chamber. 6. The hybrid rocket according to claim 1, wherein the liquid oxidant supply means is a turbo pump.