Hybrid rockets and injectors for hybrid rockets

Abstract

To provide a hybrid rocket having improved efficiency of characteristic exhaustion speed, and an injector for a hybrid rocket that can improve the efficiency of the characteristic exhaustion speed of the hybrid rocket.SOLUTION: A hybrid rocket (1) comprises: a combustion chamber (3) having an accommodation portion for accommodating solid fuel (4), and a combustion region; a nozzle (9) in communication with the combustion chamber; an oxidant supply unit (10) located in the combustion chamber (3) closer to the nozzle (9) and being in communication with the combustion region; an oxidant supply source (5) connected to the oxidant supply unit (10); and a swirl flow applying mechanism (21) located at a tip of the oxidant supply unit (5) and applying a swirl flow to an oxidant (6) which is supplied to the combustion chamber (3). A fuel gas generated from the solid fuel (4) and the oxidant (6) are mixed and combusted in the combustion region.SELECTED DRAWING: Figure 1

Claims

[Claim 1] A combustion chamber having a containment section for solid fuel and a combustion region, A nozzle communicating with the combustion chamber, An oxidant supply unit located near the nozzle in the combustion chamber and communicating with the combustion region, An oxidizing agent supply source connected to the oxidizing agent supply unit, The system includes a swirling flow imparting mechanism located at the tip of the oxidizer supply section, which imparts a swirling flow to the oxidizer supplied to the combustion chamber, In the combustion region, the fuel gas generated from the solid fuel and the oxidizer are mixed and burned. The oxidizer supply unit includes a holder for holding the swirling flow imparting mechanism inside the combustion chamber. The holder has a flow path for the oxidizer provided between the oxidizer supply source and the swirling flow imparting mechanism, The swirling flow imparting mechanism is located at the tip of the flow path and has a plurality of supply ports that supply the oxidizer toward the side wall of the combustion chamber, The aforementioned swirling flow imparting mechanism is a disc-shaped member having a circular hollow portion in the center, The swirling flow imparting mechanism has an oxidizer supply passage arranged in an annular shape coaxial with the disc-shaped member, The aforementioned plurality of supply ports are connected to the oxidizer supply path and are provided along the outer circumference of the disc-shaped member, in a hybrid rocket. [Claim 2] A combustion chamber having a containment section for containing solid fuel and a combustion region, A nozzle communicating with the combustion chamber, An oxidant supply unit located near the nozzle in the combustion chamber and communicating with the combustion region, An oxidizing agent supply source connected to the oxidizing agent supply unit, The system includes a swirling flow imparting mechanism located at the tip of the oxidizer supply section, which imparts a swirling flow to the oxidizer supplied to the combustion chamber, In the combustion region, the fuel gas generated from the solid fuel and the oxidizer are mixed and burned. The oxidizer supply unit includes a holder for holding the swirling flow imparting mechanism inside the combustion chamber. The holder has a flow path for the oxidizer provided between the oxidizer supply source and the swirling flow imparting mechanism, The swirling flow imparting mechanism has a plurality of supply ports located at the tip of the flow path and positioned opposite the solid fuel, The aforementioned swirling flow imparting mechanism is a disc-shaped member having a circular hollow portion in the center, The plurality of supply ports are arranged in a ring along a virtual circle coaxial with the hollow portion, A hybrid rocket in which the plurality of supply ports are elliptical in shape, curved along the virtual circle when the swirling flow imparting mechanism is viewed from the solid fuel side in a plan view. [Claim 3] A combustion chamber having a containment section for containing solid fuel and a combustion region, A nozzle communicating with the combustion chamber, An oxidant supply unit located near the nozzle in the combustion chamber and communicating with the combustion region, An oxidizing agent supply source connected to the oxidizing agent supply unit, The system includes a swirling flow imparting mechanism located at the tip of the oxidizer supply section, which imparts a swirling flow to the oxidizer supplied to the combustion chamber, In the combustion region, the fuel gas generated from the solid fuel and the oxidizer are mixed and burned. The combustion chamber has a portion in the combustion region where the inner diameter is enlarged. The swirling flow imparting mechanism is provided integrally with the combustion chamber in the portion where the inner diameter has been enlarged. The swirling flow imparting mechanism is provided along the side wall of the combustion chamber and has a plurality of supply ports arranged to face the solid fuel, in a hybrid rocket. [Claim 4] The hybrid rocket according to any one of claims 1 to 3, wherein the swirling flow imparting mechanism imparts a swirling flow to the oxidizer so that it flows along the inner wall of the combustion chamber in the direction of the solid fuel. [Claim 5] The hybrid rocket according to any one of claims 1 to 4, wherein the oxidizing agent is a liquid. [Claim 6] The oxidizing agent is N ２ A hybrid rocket according to any one of claims 1 to 5, wherein the rocket is O. [Claim 7] The hybrid rocket according to any one of claims 1 to 6, wherein the solid fuel comprises a tetra-olglycidyl azide polymer.

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