CN102507106B - Method for monitoring leakage in on-orbit state for spacecraft - Google Patents

Abstract

The invention provides a method for monitoring leakage in an on-orbit state for a spacecraft. The method comprises the following procedures of: monitoring pressure after partitioning cabins; injecting a neon gas in a capsule, and balancing; performing sampling analysis; performing mass flow analysis; and calculating a leak rate. According to the method provided by the invention, a pressure change monitoring method, a mass spectrum analysis method and a mass flow method are comprehensively applied to calculation and analysis of the leak rate of a space station in the on-orbit state comprehensively; the gas temperature inside the capsule is measured, as well as the changes of the total pressure, the oxygen partial pressure, the carbon dioxide partial pressure and the water vapor partial pressure are measured when the pressure is monitored; a pressure change monitoring system is used for monitoring the pressure change quantity in the capsule by comprehensively using pressure parameters measured by an environmental control and life support system; and the leak rate of a capsule body is accurately calculated by applying the mass spectrum analysis method and the mass flow method.

Description

A kind of spacecraft in-orbit state leak monitoring method

Technical field

The present invention relates to a kind of spacecraft state leak monitoring method in-orbit, particularly relate to a kind of for station module body state leak monitoring method in-orbit.

Background technology

Leakage is the key factor affecting spacecraft normal transmission and operation troubles, especially to the significant threat of manned space station.Space station should possess leakage location under pressure Real-Time Monitoring in cabin, cabin body leakage failure testing and alarm, hermetically-sealed construction failure conditions and fast blockage technology, to avoid and to reduce the generation of serious accident.General Armament Department issues manned space flight follow-up work pre research project gordian technique guide, require research space station on-orbit leak detection, localization method and quick leak-checking technology, make space station period in orbit, can Timeliness coverage leakage problem, warning is sent to cosmonaut, leak position and leakage rate can be determined fast, and adopt an effective measure within the given time and prevent major accident from occurring, for the safe operation in-orbit of space station and the personal safety of cosmonaut provide safeguard.

The test of current China spacecraft cabin integral leakage generally adopts pressure change leak hunting method, and the method is that integral leakage is determined in the change of measuring tested spacecraft cabin pressure by absolute pressure meter or differential pressure gauge.And space station in-orbit under state leakage monitoring propose to judge leakage failure and levels of leakage with pressure variation monitoring method, but there is following problem in the method.

1) although pressure change leak hunting method intuitive and convenient, but space station in-orbit state leak monitoring is not only subject to the impact of temperature variation and gradient in cabin, and be subject to the combined influence that ring control life support system pressure regulates, spacefarer consumes and in cabin, humiture changes, these influence factors are not only closely related with pressure, and its influence value is far beyond levels of leakage under international space station in-orbit state.

2) traditional pressure change leakage monitoring method is applied to space station leakage monitoring in-orbit, and system architecture is very complicated, and can only judge the leakage failure of large magnitude, assesses very coarse, easily judges by accident.

Summary of the invention

The object of this invention is to provide a kind of spacecraft state leak monitoring method in-orbit, determine that spacecraft cabin leaks leak rate under state in-orbit quick and precisely to analyze.

Concrete scheme provided by the present invention is as follows:

Spacecraft of the present invention is state leak method in-orbit, comprises following flow process:

1) cabin section separates rear pressure monitoring: the hatch door of spacecraft each cabin section is closed, start the pressure variation monitoring system of each cabin section, pressure variation monitoring system comprises total-pressure probe, temperature sensor, differential pressure pick-up, partial pressure of carbon dioxide sensor, partial pressure of oxygen sensor, the pressure variety in the pressure parameter monitoring cabin that described pressure variation monitoring system synthesis utilizes ring control life support system to record;

2) cabin body injects neon and balances: by neon source, neon is injected to cabin body, the concentration of neon (Ne) in the body internal environment of cabin is brought up to 100ppm (0.01%) by 20ppm (0.002%), then cabin inner blower is utilized to be mixed by cabin body internal gas circulation, so that cabin body internal gas pressure and temperature reach balance;

3) sample analysis: start mass spectrometer in cabin, by its sampler to cabin body internal gas continuous circulation sample analysis, calculates the partial pressure change of cabin body inner initial time neon and section structure integral leakage by equation (1);

$Q_t=\frac{(P_t\·{\mathrm{\γ}}_t-P_1\·{\mathrm{\γ}}_1)\·V}{t\·{\mathrm{\γ}}_0}\·\·\·\left(1\right)$

In formula (1): P _tfor the stagnation pressure value of gas in time t rear deck, P ₁for the stagnation pressure initial value of gas in cabin, γ _tfor the concentration value of probe gas in time t rear deck, γ ₁for the concentration initial value of probe gas in cabin, γ ₀for the concentration value of benchmark container gas, V is cabin body internal volume, Q _tfor section structure integral leakage.

4) mass flow analysis: by mass flowmeter, Real-Time Monitoring ring control life support system quality of filling gas and exhaust quality, reject spacefarer simultaneously and consume gaseous mass, by equation (2) analytical calculation cabin body drain rate.

$Q=\frac{{\∫}_0^{t_1}{q}_{v1}\·\mathrm{\ρ}-{\∫}_0^{t_2}{q}_{v2}\·\mathrm{\ρ}}{\mathrm{\Δt}}-1.375\·\·\·\left(2\right)$

In formula (2), for the mass rate of air feed and exhaust, unit (Pa.m ³/ s), if the mass rate calculated according to formula (2) is greater than 2.82Pa.m ³/ s, then show space station structures leakage failure.

The feature of technical solution of the present invention comprises:

1, the present invention considers that leakage monitoring influence factor is complicated in-orbit in space station, station module body pressure monitoring not only will monitor cabin body pressure change, and temperature in cabin, partial pressure of carbon dioxide, partial pressure of oxygen and steam partial pressure will be monitored, the discharge pressure change of rejecting ring control life support system air feed and spacefarer consume gas simultaneously, there is the special sensor group measuring pressure parameter in ring control life support system, spacefarer consumes gas flow by average moderately active value 576 (liter/sky).

2, the present invention proposes to inject neon to cabin body, the concentration of Ne in the body internal environment of cabin is brought up to 100ppm (0.01%) by 20ppm (0.002%), changed by mass spectrometer sample analysis initial time and the neon concentration in test moment, by the inner neon partial pressure change of formula (1) analytical calculation cabin body.

3, the non-general volumetric displacement meter of mass flowmeter of the present invention's employing, flow counts the vibration tube-type mass flowmeter of band integrator, gets rid of dynamic process gas density and changes the measuring error caused.

4, by mass flowmeter, Real-Time Monitoring ring control life support system quality of filling gas and exhaust quality, get rid of spacefarer simultaneously and consume gaseous mass, by formula (2) analytical calculation cabin body drain rate.

Accompanying drawing explanation

Fig. 1 is space station leakage monitoring analysis of Influential Factors figure in-orbit.

Fig. 2 is space station differential pressure leakage monitoring system schematic diagram in-orbit.

Fig. 3 is space station leakage monitoring mass spectrometry system schematic diagram in-orbit.

Fig. 4 is space station leakage monitoring mass flow analysis system schematic in-orbit.

Embodiment

What below introduce is embodiment as content of the present invention, further illustrates described content of the present invention below by embodiment.Certainly, describe the content that following detailed description is only example different aspect of the present invention, and should not be construed as the restriction scope of the invention.

Principle of the present invention is as follows: integrated application differential pressure leak detection method, mass spectrometric analysis method and mass rate method COMPREHENSIVE CALCULATING analysis space stand in rail levels of leakage, the temperature of measuring basis and body inside, tested cabin while monitoring differential pressure, in survey room, the change of general pressure, partial pressure of oxygen, partial pressure of carbon dioxide and steam partial pressure, utilizes ring control life support system monitoring pressure parameter and people to consume oxygen moderately active amount simultaneously.

Spacecraft in-orbit leakage monitoring comprise cabin section separate after pressure monitoring, cabin body inject neon and balance, the flow process such as sample analysis, mass flow analysis and mass flow analysis.Cabin section separates rear pressure monitoring step, each cabin, space station section hatch door is closed, start each cabin section pressure variation monitoring system, the raw packing pressure parametric synthesis of integrated application total-pressure probe, temperature sensor, differential pressure pick-up, partial pressure of carbon dioxide sensor, partial pressure of oxygen sensor and ring control judges pressure change in cabin, space station in-orbit leakage monitoring analysis of Influential Factors figure as shown in Figure 1, leak pressure monitoring system schematic diagram is as shown in Figure 2 in-orbit in space station; Cabin body injects neon and equilibrium step, by neon source, neon is injected to cabin body, the concentration of Ne in the body internal environment of cabin is brought up to 100ppm (0.01%) by 20ppm (0.002%), and this gas concentration meets spacefarer's physiological requirements of living for a long time does not simultaneously affect spacefarer's health status.Then utilize blower fan to be mixed by cabin body internal gas circulation, cabin body internal gas pressure and temperature reach balance; Sample analysis step, by its sampler to cabin body internal gas continuous circulation sample analysis, by the partial pressure change of formula (1) analytical calculation cabin body inner initial time neon and cabin body drain rate, leakage monitoring mass spectrometry system schematic diagram is as shown in Figure 3 in-orbit in space station; Mass flow analysis step, by ring control life support system mass flowmeter, Real-Time Monitoring ring control life support system quality of filling gas and exhaust quality, get rid of spacefarer simultaneously and consume gaseous mass, by formula (2) analytical calculation cabin body drain rate, leakage monitoring mass flow analysis system schematic is as shown in Figure 4 in-orbit in space station.

Claims (3)

1. spacecraft state leak monitoring method in-orbit, comprises following flow process:

1) cabin section separates rear pressure monitoring: the hatch door of spacecraft each cabin section is closed, start the pressure variation monitoring system of each cabin section, pressure variation monitoring system comprises total-pressure probe, temperature sensor, differential pressure pick-up, partial pressure of carbon dioxide sensor, partial pressure of oxygen sensor, the pressure variety in the pressure parameter monitoring cabin that described pressure variation monitoring system synthesis utilizes ring control life support system to record;

2) cabin body injects neon and balances: by neon source, neon is injected to cabin body, the concentration of neon (Ne) in the body internal environment of cabin is brought up to 100ppm by 20ppm, then cabin inner blower is utilized to be mixed by cabin body internal gas circulation, so that cabin body internal gas pressure and temperature reach balance;

3) sample analysis: start mass spectrometer in cabin, by its sampler to cabin body internal gas continuous circulation sample analysis, calculates the partial pressure change of cabin body inner initial time neon and section structure integral leakage by equation (1);

$Q_t=\frac{(P_t\·{\mathrm{\γ}}_t-P_1\·{\mathrm{\γ}}_1)\·V}{t\·{\mathrm{\γ}}_0}\·\·\·\left(1\right)$

In formula (1): P _tfor the stagnation pressure value of gas in time t rear deck, P ₁for the stagnation pressure initial value of gas in cabin, γ _tfor the concentration value of probe gas in time t rear deck, γ ₁for the concentration initial value of probe gas in cabin, γ ₀for the concentration value of benchmark container gas, V is cabin body internal volume, Q _tfor section structure integral leakage.

4) mass flow analysis: by mass flowmeter, Real-Time Monitoring ring control life support system quality of filling gas and exhaust quality, reject spacefarer simultaneously and consume gaseous mass, by equation (2) analytical calculation cabin body drain rate;

$Q=\frac{{\∫}_0^{t_1}{q}_{v1}\·\mathrm{\ρ}-{\∫}_0^{t_2}{q}_{v2}\·\mathrm{\ρ}}{\mathrm{\Δt}}-1.375\·\·\·\left(2\right)$

In formula (2), for the mass rate of air feed and exhaust, unit Pa.m ³/ s, if the mass rate calculated according to formula (2) is greater than 2.82Pa.m ³/ s, then show space station structures leakage failure.

2. the method for claim 1, it is characterized in that, space station in-orbit under state leakage monitoring influence factor complicated, station module body pressure monitoring not only will monitor cabin body pressure change, and temperature in cabin, partial pressure of carbon dioxide, partial pressure of oxygen and steam partial pressure will be monitored, the pressure parameter simultaneously utilizing ring control life support system to record measures air demand and air capacity.

3. the method for claim 1, is characterized in that, mass rate counts the vibration tube-type mass flowmeter of band integrator, gets rid of dynamic process gas density and changes the measuring error caused.