CN102507106A - 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 is in the method for rail state leakage monitoring

Technical field

The present invention relates to a kind of spacecraft in rail state leakage monitoring method, particularly relate to a kind of station module body that is used in rail state leakage monitoring method.

Background technology

Leakage is a key factor that influences spacecraft normal transmission and operation troubles, especially to the significant threat of manned space station.The space station should possess that the cabin internal pressure is monitored in real time, leakage positioning and fast blockage technology under cabin body leakage failure detection and warning, the hermetically-sealed construction failure conditions, to avoid and to reduce the generation of serious accident.General Armament Department's issue manned space flight follow-up work is research project gordian technique guide in advance; Require the research space station in rail leak detection, localization method and quick leak-checking technology, make the space station in orbit during, can in time find leakage problem; Send warning to the cosmonaut; Can confirm leak position and leakage rate fast, and in the given time, adopt an effective measure and prevent that major accident from taking place, for the personal safety rail safe operation and cosmonaut of space station provides safeguard.

China's spacecraft cabin integral leakage test at present generally adopts pressure to change leak hunting method, and this method is to confirm integral leakage through the variation that absolute pressure meter or differential pressure gauge are measured tested spacecraft cabin pressure.And space station leakage monitoring under the rail state proposes to judge leakage failure and levels of leakage with pressure variation monitoring method, but there is following problem in this method.

1) though pressure changes the leak hunting method intuitive and convenient; But the space station not only receives the influence of temperature variation and gradient in the cabin in rail state leakage monitoring; And receive that ring control life support system pressure is regulated, the spacefarer consumes and the cabin in the combined influence of humiture variation; These influence factors are not only closely related with pressure, and its influence value stands in levels of leakage under the rail state in the international space head and shoulders above.

2) traditional pressure changes leakage monitoring method and is applied to the space station at the rail leakage monitoring, and system architecture is very complicated, and can only judge the leakage failure of big magnitude, assess very coarsely, judges by accident easily.

Summary of the invention

The purpose of this invention is to provide a kind of spacecraft in rail state leakage monitoring method, under the rail state, leak leak rate so that spacecraft cabin is determined in analysis quick and precisely.

Concrete scheme provided by the present invention is following:

Spacecraft of the present invention comprises following flow process in rail state leakage method:

1) the cabin section is separated the back pressure monitoring: the hatch door of each cabin section of spacecraft 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 said pressure variation monitoring system synthesis utilization ring control life support system records;

2) the cabin body injects neon and balance: through the neon source; Inject neon to the 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%); Utilize the cabin inner blower that body internal gas circulation in cabin is mixed then, so that cabin body internal gas pressure and temperature reach balance;

3) sample analysis: start mass spectrometer in the cabin, to the continuous cycle sampling analysis of cabin body internal gas, calculate the inner initial time neon of cabin body partial pressure through equation (1) and change and the section structure integral leakage through its ST;

$Q_t=\frac{(P_{t}g{\mathrm{\γ}}_t-P_{1}g{\mathrm{\γ}}_1)\mathrm{gV}}{\mathrm{tg}{\mathrm{\γ}}_0}...\left(1\right)$

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

4) mass rate analysis: through mass flowmeter, monitoring ring control life support system quality of filling gas and exhaust quality are rejected spacefarer's spent gas quality, simultaneously through equation (2) analytical calculation cabin body drain rate in real time.

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

In the formula (2),

Be the mass rate of air feed and exhaust, (the Pa.m of unit ³/ s), if the mass rate that calculates according to formula (2) then shows space station structure leakage failure greater than 2.82Pa.m3/s.

The characteristics of technical scheme of the present invention comprise:

1, the present invention considers that the space station is complicated in rail leakage monitoring influence factor; Station module body pressure monitoring not only will be monitored cabin body pressure and changed; And to monitor temperature in the cabin, partial pressure of carbon dioxide, partial pressure of oxygen and steam partial pressure; Reject ring control life support system air feed discharge pressure simultaneously and change and spacefarer's spent gas, there is the sensor groups of special gaging pressure parameter in ring control life support system, and spacefarer's spent gas amount is by average moderate activity value 576 (liter/sky).

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

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

4, through mass flowmeter, monitoring calculation ring control life support system quality of filling gas and exhaust quality are got rid of spacefarer's spent gas quality, simultaneously through formula (2) analytical calculation cabin body drain rate in real time.

Description of drawings

Fig. 1 is that the space station is at rail leakage monitoring analysis of Influential Factors figure.

Fig. 2 is that the space station differential pressure is at rail leakage monitoring system synoptic diagram.

Fig. 3 is that the space station is at rail leakage monitoring mass spectrometry system synoptic diagram.

Fig. 4 is that the space station is at rail leakage monitoring mass rate analytic system synoptic diagram.

Embodiment

What below introduce is the embodiment as content according to the invention, through embodiment said content of the present invention is further illustrated below.Certainly, describe following embodiment and only be the content of 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 following: integrated application differential pressure leak hunting method, mass spectrometric analysis method and mass rate method COMPREHENSIVE CALCULATING analysis space stand in the rail levels of leakage; Measuring basis and tested cabin body temperature inside in the monitoring differential pressure; General pressure, partial pressure of oxygen, partial pressure of carbon dioxide and steam partial pressure change in the survey room, utilize ring control life support system monitoring pressure parameter and people's consume oxygen moderate activity simultaneously.

Spacecraft comprises that at the rail leakage monitoring cabin section is separated the back pressure monitoring, the cabin body injects neon and flow processs such as balance, sample analysis, mass rate analysis and mass rate analysis.The cabin section is separated back pressure monitoring step; Each cabin section hatch door of space station is closed; Start each cabin section pressure variation monitoring system; 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 are given birth to the packing pressure parametric synthesis and are judged that the cabin internal pressure changes, and the space station is as shown in Figure 1 at rail leakage monitoring analysis of Influential Factors figure, and the space station is as shown in Figure 2 at rail leak pressure monitoring system synoptic diagram; The cabin body injects neon and equilibrium step; Through the neon source; Inject neon to the cabin body, the concentration of Ne in the body internal environment of cabin is brought up to 100ppm (0.01%) by 20ppm (0.002%), this gas concentration satisfies spacefarer's physiological requirements of living does not for a long time influence simultaneously spacefarer's health status.Utilize blower fan that body internal gas circulation in cabin is mixed then, cabin body internal gas pressure and temperature reach balance; The sample analysis step; Through its ST to the continuous cycle sampling analysis of cabin body internal gas; Change and cabin body drain rate through the inner initial time neon of formula (1) analytical calculation cabin body partial pressure, the space station is as shown in Figure 3 at rail leakage monitoring mass spectrometry system synoptic diagram; The mass rate analytical procedure; Through ring control life support system mass flowmeter; Real-time monitoring calculation ring control life support system quality of filling gas and exhaust quality; Get rid of spacefarer's spent gas quality simultaneously, through formula (2) analytical calculation cabin body drain rate, the space station is as shown in Figure 4 at rail leakage monitoring mass rate analytic system synoptic diagram.

Claims (5)

1. spacecraft comprises following flow process in rail state leakage monitoring method:

1) the cabin section is separated the back pressure monitoring: the hatch door of each cabin section of spacecraft 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 said pressure variation monitoring system synthesis utilization ring control life support system records;

2) the cabin body injects neon and balance: through the neon source; Inject neon to the 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%); Utilize the cabin inner blower that body internal gas circulation in cabin is mixed then, so that cabin body internal gas pressure and temperature reach balance;

3) sample analysis: start mass spectrometer in the cabin, to the continuous cycle sampling analysis of cabin body internal gas, calculate the inner initial time neon of cabin body partial pressure through equation (1) and change and the section structure integral leakage through its ST;

$Q_t=\frac{(P_{t}g{\mathrm{\γ}}_t-P_{1}g{\mathrm{\γ}}_1)\mathrm{gV}}{\mathrm{tg}{\mathrm{\γ}}_0}...\left(1\right)$

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

4) mass rate analysis: through mass flowmeter, monitoring ring control life support system quality of filling gas and exhaust quality are rejected spacefarer's spent gas quality, simultaneously through equation (2) analytical calculation cabin body drain rate in real time.

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

In the formula (2),

Be the mass rate of air feed and exhaust, (the Pa.m of unit ³/ s), if the mass rate that calculates according to formula (2) then shows space station structure leakage failure greater than 2.82Pa.m3/s.

2. the method for claim 1; It is characterized in that; Space station leakage monitoring influence factor under the rail state is complicated; Station module body pressure monitoring not only will be monitored cabin body pressure and changed, and will monitor temperature in the cabin, partial pressure of carbon dioxide, partial pressure of oxygen and steam partial pressure, and the pressure parameter that utilizes ring control life support system to record is simultaneously measured air demand and air capacity.

3. the method for claim 1; It is characterized in that; Inject neon to the cabin body; The concentration of Ne in the body internal environment of cabin is brought up to 100ppm (0.01%) by 20ppm (0.002%), by mass spectrometer sampling and analysis initial time and test neon concentration constantly, through the inner neon partial pressure of equation (1) analytical calculation cabin body variable quantity.

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

5. the method for claim 1 is characterized in that, through mass flowmeter, monitoring calculation ring control life support system quality of filling gas and exhaust quality are rejected spacefarer's spent gas quality, simultaneously through formula (2) analytical calculation cabin body drain rate in real time.

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