On-orbit storage tank residual propellant reserve measuring system

Abstract

The invention discloses a system for measuring the remaining propellant reserve of an on-orbit storage tank. The device consists of an oxidant storage tank (1), an oxidant pipeline A (2), an oxidant electromagnetic valve A (3), an oxidant pipeline B (4), an ultrasonic flowmeter A (5), an oxidant electromagnetic valve B (6), an oxidant pipeline C (7), a fuel storage tank (8), a fuel pipeline A (9), a fuel electromagnetic valve A (10), a fuel pipeline B (11), an ultrasonic flowmeter B (12), a fuel electromagnetic valve B (13), a fuel pipeline C (14), an engine (15), a vibrator A (16), a vibrator B (17), a vibrator C (18) and a vibrator D (19). And the flow of the oxidant pipeline B (4) is measured through the ultrasonic flowmeter A (5), and the remaining oxidant reserve of the oxidant storage tank (1) is calculated. And the flow of the fuel pipeline B (11) is measured through an ultrasonic flowmeter B (12), and the remaining fuel reserve of the fuel storage tank (8) is calculated.

Description

Technical Field

[0001] The invention relates to a propellant reserve measuring system, in particular to an on-orbit tank remaining propellant reserve measuring system. Background Art

[0002] For aerospace vehicles, the amount of liquid propellant reserves is an extremely important parameter. It is an important basis for judging the service life of aerospace vehicles and one of the parameters for monitoring the working status of the propulsion system. In an environment with a gravity field, it is easy to measure the propellant. For example, a special flow meter can be set on the pipeline during ground testing, and a liquid level sensor can be set on the tank of the booster-stage rocket engine to solve this problem. However, in outer space, due to the influence of weightlessness, the distribution of liquid propellant in the tank is irregular, and it is difficult to measure the propellant reserves by conventional means. Summary of the invention

[0003] A set of transducers capable of transmitting and receiving ultrasonic waves is set up on the outside of the propellant pipeline and the fuel pipeline. Ultrasonic waves are transmitted alternately in the positive and negative directions to the flowing propellant. The propagation times t1 and t2 are respectively

[0004]

[0005] Where D is the inner diameter of the tube; c is the speed of sound; v is the flow velocity.

[0006] Establish a pulse sequence with each propagation time as the period, and measure the frequency difference Δf of each pulse. Then Δf is proportional to the flow velocity v.

[0007]

[0008] By measuring Δf, we can calculate

[0009]

[0010] Thus, we know the propellant mass flow rate

[0011]

[0012] Where ρ is the propellant density and D is the inner diameter of the propellant line.

[0013] Propellant mass flow Integrate to get the propellant consumption Δm

[0014]

[0015] The remaining storage capacity of the propellant tank m2 is calculated from the initial storage capacity m1 of the propellant tank and the propellant consumption Δm

[0016]

[0017] The propellant consists of an oxidizer and fuel, and the remaining reserves of the oxidizer and fuel are measured separately.

[0018] The advantages of the present invention compared with the prior art are:

[0019] (1) The ultrasonic flow meter adopts the external clamp type and is a non-contact measuring instrument. It will not change the existing pipeline structure and will not add additional flow resistance.

[0020] (2) It is suitable for measuring the remaining propellant reserves in on-orbit tanks. The flow measurement accuracy is almost unaffected by the temperature, pressure, density, viscosity and other parameters of the measured fluid.

[0021] (3) Easy to install and high measurement accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 Diagram of a system for measuring the remaining propellant reserves in an on-orbit tank

[0023] Figure 2 Ultrasonic flow meter A installation diagram

[0024] Figure 3 Installation diagram of ultrasonic flowmeter B

[0025] In the picture

[0026] 1. Oxidant tank 2. Oxidant pipeline A 3. Oxidant solenoid valve A

[0027] 4. Oxidant pipeline B 5. Ultrasonic flow meter A 6. Oxidant solenoid valve B

[0028] 7. Oxidant pipeline C 8. Fuel tank 9. Fuel pipeline A

[0029] 10. Fuel solenoid valve A 11. Fuel line B 12. Ultrasonic flow meter B

[0030] 13. Fuel solenoid valve B 14. Fuel line C 15. Engine

[0031] 16. Vibrator A 17. Vibrator B 18. Vibrator C

[0032] 19. Vibrator D DETAILED DESCRIPTION

[0033] The present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0034] An on-orbit tank remaining propellant reserve measurement system comprises an oxidizer tank (1), an oxidizer pipeline A (2), an oxidizer solenoid valve A (3), an oxidizer pipeline B (4), an ultrasonic flowmeter A (5), an oxidizer solenoid valve B (6), an oxidizer pipeline C (7), a fuel tank (8), a fuel pipeline A (9), a fuel solenoid valve A (10), a fuel pipeline B (11), an ultrasonic flowmeter B (12), a fuel solenoid valve B (13), a fuel pipeline C (14), an engine (15), a vibrator A (16), a vibrator B (17), a vibrator C (18), and a vibrator D (19).

[0035] The oxidant tank (1) is connected to the oxidant solenoid valve A (3) via the oxidant pipeline A (2), the oxidant solenoid valve A (3) is connected to the oxidant solenoid valve B (6) via the oxidant pipeline B (4), an ultrasonic flow meter A (5) is installed on the outer wall of the oxidant pipeline B (4), and the oxidant solenoid valve B (6) is connected to the engine (15) via the oxidant pipeline C (7).

[0036] The oxidant flows out of the oxidant tank (1) and enters the engine (15) through the oxidant pipeline A (2), the oxidant solenoid valve A (3), the oxidant pipeline B (4), the oxidant solenoid valve B (6), and the oxidant pipeline C (7). The oxidant solenoid valve A (3) is the outlet valve of the oxidant tank (1), the oxidant solenoid valve B (6) is the inlet valve of the engine (15), and the ultrasonic flowmeter A (5) is used to measure the flow rate of the oxidant flowing through the oxidant pipeline B (4).

[0037] A fuel tank (8) is connected to a fuel solenoid valve A (10) via a fuel pipeline A (9), the fuel solenoid valve A (10) is connected to a fuel solenoid valve B (13) via a fuel pipeline B (11), an ultrasonic flow meter B (12) is mounted on an outer wall of the fuel pipeline B (11), and the fuel solenoid valve B (13) is connected to an engine (15) via a fuel pipeline C (14).

[0038] Fuel flows out of the fuel tank (8) and enters the engine (15) through the fuel pipeline A (9), the fuel solenoid valve A (10), the fuel pipeline B (11), the fuel solenoid valve B (13), and the fuel pipeline C (14). The fuel solenoid valve A (10) is the outlet valve of the fuel tank (8), the fuel solenoid valve B (13) is the inlet valve of the engine (15), and the ultrasonic flow meter B (12) is used to measure the fuel flow rate flowing through the fuel pipeline B (11).

[0039] Figure 2This is the installation diagram of ultrasonic flowmeter A. Vibrator A and vibrator B are the two vibrators of ultrasonic flowmeter A. According to the requirements of 10 times the pipe diameter upstream of the measuring point and 5 times the pipe diameter downstream of the straight pipe section, the position of ultrasonic flowmeter A is arranged to ensure that the oxidant has a stable flow state at this location. Vibrators A and B are installed on the outside of the oxidant pipeline to send and receive ultrasonic waves. In the figure, θ=45°. Vibrators A and B alternately emit ultrasonic pulses in the forward and reverse directions to the flowing oxidant. The frequency difference Δf of each pulse is measured o , calculate the oxidant flow rate v o , So we know the oxidant mass flow rate ρ o is the oxidant density, D o is the inner diameter of the oxidant line. Integrate to get the oxidant consumption Δm o , The initial storage capacity of the oxidizer tank is m o1 and oxidant consumption Δm 。 , calculate the remaining reserve of the oxidizer tank m o2 ,

[0040] Figure 3 This is the installation diagram of ultrasonic flowmeter B. Vibrator C and vibrator D are the two vibrators of ultrasonic flowmeter B. According to the requirements of 10 times the pipe diameter upstream of the measuring point and 5 times the pipe diameter downstream of the straight pipe section, the position of ultrasonic flowmeter B is arranged to ensure that the fuel at this location has a stable flow state. Vibrators C and D are installed on the outside of the fuel pipeline to send and receive ultrasonic waves. In the figure, θ = 45°. Vibrators C and D alternately emit ultrasonic pulses in the positive and negative directions to the flowing fuel. The frequency difference Δf of each pulse is measured f , calculate the fuel flow rate v f , So we know the fuel mass flow rate ρ f is the fuel density, D f is the inner diameter of the fuel line. Integrate to get the fuel consumption Δm f , The initial fuel tank capacity m f1 and fuel consumption Δm f , calculate the remaining fuel tank capacity m f2 ,

[0041] The contents not described in detail in the present invention are well known to those skilled in the art.

Claims

1. A system for measuring the remaining propellant reserves in an on-orbit tank, characterized in that The invention comprises an oxidant tank (1), an oxidant pipeline A (2), an oxidant solenoid valve A (3), an oxidant pipeline B (4), an ultrasonic flow meter A (5), an oxidant solenoid valve B (6), an oxidant pipeline C (7), a fuel tank (8), a fuel pipeline A (9), a fuel solenoid valve A (10), a fuel pipeline B (11), an ultrasonic flow meter B (12), a fuel solenoid valve B (13), a fuel pipeline C (14), an engine (15), a vibrator A (16), a vibrator B (17), a vibrator C (18), and a vibrator D (19).

2. An on-orbit tank remaining propellant reserve measurement system according to claim 1, wherein the oxidizer tank (1) is connected to the oxidizer solenoid valve A (3) through the oxidizer pipeline A (2), the oxidizer solenoid valve A (3) is connected to the oxidizer solenoid valve B (6) through the oxidizer pipeline B (4), the ultrasonic flowmeter A (5) is installed on the outer wall of the oxidizer pipeline B (4), and the oxidizer solenoid valve B (6) is connected to the engine (15) through the oxidizer pipeline C (7); the oxidizer flows out of the oxidizer tank (1) and enters the engine (15) via the oxidizer pipeline A (2), the oxidizer solenoid valve A (3), the oxidizer pipeline B (4), the oxidizer solenoid valve B (6), and the oxidizer pipeline C (7); the oxidizer solenoid valve A (3) is the outlet valve of the oxidizer tank (1), the oxidizer solenoid valve B (6) is the inlet valve of the engine (15), and the ultrasonic flowmeter A (5) is used to measure the oxidizer flow rate flowing through the oxidizer pipeline B (4).

3. An on-orbit tank remaining propellant reserve measurement system according to claim 1, wherein the fuel tank (8) is connected to a fuel solenoid valve A (10) through a fuel pipeline A (9), the fuel solenoid valve A (10) is connected to a fuel solenoid valve B (13) through a fuel pipeline B (11), an ultrasonic flowmeter B (12) is installed on the outer wall of the fuel pipeline B (11), and the fuel solenoid valve B (13) is connected to an engine (15) through a fuel pipeline C (14); fuel flows out of the fuel tank (8) and enters the engine (15) via the fuel pipeline A (9), the fuel solenoid valve A (10), the fuel pipeline B (11), the fuel solenoid valve B (13), and the fuel pipeline C (14); the fuel solenoid valve A (10) is an outlet valve of the fuel tank (8), the fuel solenoid valve B (13) is an inlet valve of the engine (15), and the ultrasonic flowmeter B (12) is used to measure the fuel flow rate flowing through the fuel pipeline B (11).

4. According to the on-orbit tank remaining propellant reserve measurement system of claim 1, vibrator A and vibrator B are two vibrators of ultrasonic flowmeter A; the position of ultrasonic flowmeter A is arranged according to the requirements of a straight pipe section 10 times the pipe diameter upstream and a straight pipe section 5 times the pipe diameter downstream of the measuring point to ensure that the oxidant at this location has a stable flow state; vibrator A and vibrator B are installed on the outside of the oxidant pipeline for sending and receiving ultrasonic waves; θ=45° in the figure; vibrator A and vibrator B alternately emit ultrasonic pulses in positive and negative directions to the flowing oxidant; the frequency difference Δf of each pulse is measured o , calculate the oxidant flow rate v o , So we know the oxidant mass flow rate ρ o is the oxidant density, D o is the inner diameter of the oxidant pipeline; for the oxidant mass flow rate Integrate to get the oxidant consumption Δm o , The initial storage capacity of the oxidizer tank is m o1 and oxidant consumption Δm o , calculate the remaining storage capacity of the oxidizer tank m o2 , 5. According to the on-orbit tank remaining propellant reserve measurement system of claim 1, vibrator C and vibrator D are two vibrators of ultrasonic flowmeter B; the position of ultrasonic flowmeter B is arranged according to the requirements of 10 times the pipe diameter distance upstream of the measuring point and 5 times the pipe diameter distance downstream of the straight pipe section to ensure that the fuel at this location has a stable flow state; vibrator C and vibrator D are installed on the outside of the fuel pipeline for sending and receiving ultrasonic waves; θ=45° in the figure; vibrator C and vibrator D alternately emit ultrasonic pulses in positive and negative directions to the flowing fuel; the frequency difference Δf of each pulse is measured f , calculate the fuel flow rate v f , So we know the fuel mass flow rate ρ f is the fuel density, D f is the inner diameter of the fuel line; for the fuel mass flow Integrate to get the fuel consumption Δm f , The initial fuel tank capacity m f1 and fuel consumption Δm f , calculate the remaining fuel tank capacity m f2 ,

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