Rotary detonation engine test system

Abstract

The invention discloses a rotary detonation engine test system which is composed of a methane gas cylinder (1), a methane pipeline A (2), an electromagnetic valve A (3), a methane pipeline B (4), an electromagnetic valve B (5), a methane pipeline C (6), an oxygen gas cylinder (7), an oxygen pipeline A (8), an electromagnetic valve C (9), an oxygen pipeline B (10), an electromagnetic valve D (11), an oxygen pipeline C (12), an igniter (13), a pressure sensor (14) and a rotary detonation engine (15). The igniter (13) is a plasma igniter, is installed on the rotary detonation engine (15) and is used for igniting mixed gas of methane and oxygen entering the rotary detonation engine (15). The pressure sensor (14) is a water-cooled high-frequency pressure sensor and is used for measuring explosive wave pressure in the rotary detonation engine (15).

Description

Technical Field

[0001] The invention relates to an engine test system, in particular to a rotating detonation engine test system. Background Art

[0002] In order to seize the commanding heights of space, the world's major space powers have vigorously developed advanced space technology. After decades of development, the technology of traditional engines using isobaric combustion mode has become relatively mature, and it is very difficult to significantly improve their specific impulse, thrust-to-weight ratio and other performance. Breakthroughs in the principles of engine thermodynamic cycles have provided the possibility for further promoting the leapfrog development of my country's advanced propulsion technology. Detonation combustion uses a nearly isochoric combustion mode, which has a higher thermal cycle efficiency than the isobaric combustion mode, and has the potential to reduce the requirements of the supply pump system. Since the 21st century, research on engine applications based on detonation combustion has received widespread attention worldwide. Summary of the invention

[0003] The invention discloses a rotating detonation engine test system, which comprises a methane gas cylinder (1), a methane pipeline A (2), a solenoid valve A (3), a methane pipeline B (4), a solenoid valve B (5), a methane pipeline C (6), an oxygen gas cylinder (7), an oxygen pipeline A (8), a solenoid valve C (9), an oxygen pipeline B (10), a solenoid valve D (11), an oxygen pipeline C (12), an igniter (13), a pressure sensor (14), and a rotating detonation engine (15).

[0004] The igniter (13) is a plasma igniter, which is installed on the rotary detonation engine (15) and is used to ignite the mixed gas of methane and oxygen entering the rotary detonation engine (15).

[0005] The pressure sensor (14) is a water-cooled high-frequency pressure sensor, and is used to measure the explosion wave pressure in the rotary detonation engine (15).

[0006] The advantages of the present invention compared with the prior art are:

[0007] (1) The igniter (13) is a plasma igniter, which is installed on the rotary detonation engine (15) and is used to ignite the mixed gas of methane and oxygen entering the rotary detonation engine (15), and has high ignition reliability.

[0008] (2) The pressure sensor (14) is a water-cooled high-frequency pressure sensor used to measure the explosion wave pressure in the rotating detonation engine (15). The pressure sensor has a long service life.

[0009] (3) The system is simple and the construction cost is low.

[0010] (4) Methane is used as propellant, which has low cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 A rotating detonation engine test system diagram

[0012] In the figure

[0013] 1. Methane gas cylinder 2. Methane pipeline A 3. Solenoid valve A

[0014] 4. Methane pipeline B 5. Solenoid valve B 6. Methane pipeline C

[0015] 7. Oxygen cylinder 8. Oxygen pipeline A 9. Solenoid valve C

[0016] 10. Oxygen pipeline B 11. Solenoid valve D 12. Oxygen pipeline C

[0017] 13. Ignition 14. Pressure sensor 15. Rotating detonation engine DETAILED DESCRIPTION

[0018] The specific implementation modes of the present invention are further described in detail below with reference to the accompanying drawings.

[0019] A rotating detonation engine test system comprises a methane gas cylinder (1), a methane pipeline A (2), a solenoid valve A (3), a methane pipeline B (4), a solenoid valve B (5), a methane pipeline C (6), an oxygen gas cylinder (7), an oxygen pipeline A (8), a solenoid valve C (9), an oxygen pipeline B (10), a solenoid valve D (11), an oxygen pipeline C (12), an igniter (13), a pressure sensor (14), and a rotating detonation engine (15).

[0020] The methane cylinder (1) is connected to the solenoid valve A (3) via a methane pipeline A (2), the solenoid valve A (3) is connected to the solenoid valve B (5) via a methane pipeline B (4), and the solenoid valve B (5) is connected to the rotary detonation engine (15) via a methane pipeline C (6). Methane enters the rotary detonation engine (15) from the methane cylinder (1) in sequence through the methane pipeline A (2), the solenoid valve A (3), the methane pipeline B (4), the solenoid valve B (5), and the methane pipeline C (6).

[0021] The oxygen cylinder (7) is connected to the solenoid valve C (9) through an oxygen pipeline A (8), the solenoid valve C (9) is connected to the solenoid valve D (11) through an oxygen pipeline B (10), and the solenoid valve D (11) is connected to the rotary detonation engine (15) through an oxygen pipeline C (12). Oxygen from the oxygen cylinder (7) passes through the oxygen pipeline A (8), the solenoid valve C (9), the oxygen pipeline B (10), the solenoid valve D (11), and the oxygen pipeline C (12) in sequence and enters the rotary detonation engine (15).

[0022] The igniter (13) is a plasma igniter, which is installed on the rotary detonation engine (15) and is used to ignite the mixed gas of methane and oxygen entering the rotary detonation engine (15).

[0023] The pressure sensor (14) is a water-cooled high-frequency pressure sensor, and is used to measure the explosion wave pressure in the rotary detonation engine (15).

[0024] The contents not described in detail in the present invention are well known to those skilled in the art.

Claims

1. A rotating detonation engine test system, characterized in that A rotating detonation engine test system comprises a methane gas cylinder (1), a methane pipeline A (2), a solenoid valve A (3), a methane pipeline B (4), a solenoid valve B (5), a methane pipeline C (6), an oxygen gas cylinder (7), an oxygen pipeline A (8), a solenoid valve C (9), an oxygen pipeline B (10), a solenoid valve D (11), an oxygen pipeline C (12), an igniter (13), a pressure sensor (14), and a rotating detonation engine (15).

2. According to the rotating detonation engine test system of claim 1, the methane cylinder (1) is connected to the solenoid valve A (3) through the methane pipeline A (2), the solenoid valve A (3) is connected to the solenoid valve B (5) through the methane pipeline B (4), and the solenoid valve B (5) is connected to the rotating detonation engine (15) through the methane pipeline C (6); methane enters the rotating detonation engine (15) from the methane cylinder (1) through the methane pipeline A (2), the solenoid valve A (3), the methane pipeline B (4), the solenoid valve B (5), and the methane pipeline C (6) in sequence.

3. According to the rotating detonation engine test system of claim 1, the oxygen cylinder (7) is connected to the solenoid valve C (9) through the oxygen pipeline A (8), the solenoid valve C (9) is connected to the solenoid valve D (11) through the oxygen pipeline B (10), and the solenoid valve D (11) is connected to the rotating detonation engine (15) through the oxygen pipeline C (12); oxygen enters the rotating detonation engine (15) from the oxygen cylinder (7) through the oxygen pipeline A (8), the solenoid valve C (9), the oxygen pipeline B (10), the solenoid valve D (11), and the oxygen pipeline C (12) in sequence.

4. According to the rotating detonation engine test system described in claim 1, the igniter (13) adopts a plasma igniter, which is installed on the rotating detonation engine (15) to ignite the mixed gas of methane and oxygen entering the rotating detonation engine (15), and has high ignition reliability.

5. According to the rotating detonation engine test system described in claim 1, the pressure sensor (14) adopts a water-cooled high-frequency pressure sensor to measure the explosion wave pressure in the rotating detonation engine (15), and the pressure sensor has a long service life.

6. The rotating detonation engine test system according to claim 1 uses methane as a propellant, and has low cost.

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