CN109188129B - Electric polarity test method for satellite two-component chemical propulsion subsystem - Google Patents
Electric polarity test method for satellite two-component chemical propulsion subsystem Download PDFInfo
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- CN109188129B CN109188129B CN201811007707.XA CN201811007707A CN109188129B CN 109188129 B CN109188129 B CN 109188129B CN 201811007707 A CN201811007707 A CN 201811007707A CN 109188129 B CN109188129 B CN 109188129B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/005—Testing of electric installations on transport means
- G01R31/008—Testing of electric installations on transport means on air- or spacecraft, railway rolling stock or sea-going vessels
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/50—Testing of electric apparatus, lines, cables or components for short-circuits, continuity, leakage current or incorrect line connections
- G01R31/66—Testing of connections, e.g. of plugs or non-disconnectable joints
- G01R31/67—Testing the correctness of wire connections in electric apparatus or circuits
Abstract
The invention relates to an electric polarity test method of a satellite two-component chemical propulsion subsystem, which is suitable for the technical field of ground test of spacecrafts. The test method only needs to use universal test tools such as the adapter box and the adapter cable, does not need matched special equipment, is convenient to implement, and has the advantages of low cost, high reliability, strong operability, strong flexibility and the like; the test method has wide application range and strong popularization, most of the existing satellite platforms adopt a scheme of a two-component unified propulsion system, and the method can be suitable for electrical performance test of the platforms.
Description
Technical Field
The invention relates to an electric polarity test method of a satellite two-component chemical propulsion subsystem, which is suitable for the technical field of ground test of spacecrafts, in particular to an electric performance test of the chemical propulsion subsystem in the ground test process of a communication satellite, and more particularly relates to a polarity test method of an independent valve body on a thruster of the chemical propulsion subsystem in the electric performance test.
Background
Most of the existing satellite platforms adopt a scheme of a two-component unified propulsion system, each thruster in the subsystem is respectively controlled by 2 electromagnetic valves to switch on and off an oxygen path and a fuel path, and the two electromagnetic valves are controlled by the same instruction to act simultaneously to release a propellant. In the propulsion pipeline system, 1 self-locking valve is respectively arranged on each branch oxygen path and each branch fuel path, and the self-locking valves of each branch oxygen path and each branch fuel path are controlled by the same command to act simultaneously as main switches of the paths.
Because the electromagnetic valve and the self-locking valve in the propulsion subsystem act in pairs, in a real load test, if one path of valve body fails, the other path of valve body can still control air injection, the normal function of the propulsion subsystem cannot be effectively verified, the effectiveness of a ground test is influenced, and hidden dangers are caused to the normal work of a satellite.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method solves the problem that the polarity of a single electromagnetic valve and a self-locking valve cannot be verified in the conventional testing method, and improves the test coverage and effectiveness.
The technical solution of the invention is as follows:
the electric polarity test method of the satellite two-component chemical propulsion subsystem comprises a propulsion line box, an A branch pipeline, a B branch pipeline and a plurality of thrusters;
the branch A pipeline comprises a branch A oxidant pipeline and a branch A combustion agent pipeline;
the B branch pipeline comprises a B branch oxidant pipeline and a B branch combustion agent pipeline;
the thruster communicated with the branch pipeline A is called as a branch thruster A, and the thruster communicated with the branch pipeline B is called as a branch thruster B;
the A branch oxidant pipeline is provided with a self-locking valve which is called as an A branch oxygen path self-locking valve;
the branch A combustion agent pipeline is provided with a self-locking valve which is called as a branch A combustion pipeline self-locking valve;
the B branch oxidant pipeline is provided with a self-locking valve which is called as a B branch oxygen path self-locking valve;
the branch B combustion agent pipeline is provided with a self-locking valve which is called as a branch B combustion path self-locking valve;
each branch A thruster is provided with two electromagnetic valves, wherein the electromagnetic valve communicated with the branch A oxidant pipeline is called a branch A thruster oxygen path electromagnetic valve, and the electromagnetic valve communicated with the branch A combustion agent pipeline is called a branch A thruster fuel path electromagnetic valve;
each branch B thruster is provided with two electromagnetic valves, wherein the electromagnetic valve communicated with the branch B oxidant pipeline is called a branch B thruster oxygen path electromagnetic valve, and the electromagnetic valve communicated with the branch B combustion agent pipeline is called a branch B thruster fuel path electromagnetic valve;
the propulsion circuit box is used for controlling the on-off of all the electromagnetic valves and the self-locking valve, wherein the propulsion circuit box controls the oxygen path electromagnetic valve of the A-branch thruster and the fuel path electromagnetic valve of the A-branch thruster through a cable a; the propulsion line box controls the oxygen path electromagnetic valve of the branch thruster B and the fuel path electromagnetic valve of the branch thruster B through a cable B; the propelling line box controls the A branch oxygen path self-locking valve, the A branch combustion path self-locking valve, the B branch oxygen path self-locking valve and the B branch combustion path self-locking valve through a cable c;
the testing method comprises the following steps:
(1) the cable connection box is characterized in that a junction box a is connected between the cable a and the propelling line box in series, a junction box b is connected between the cable b and the propelling line box in series, and a junction box c is connected between the cable c and the propelling line box in series;
(2) releasing the pressure in the A branch oxidant pipeline, the A branch combustion agent pipeline, the B branch oxidant pipeline and the B branch combustion agent pipeline to 0 MPa;
(3) closing the self-locking valve of the branch oxygen path A, the self-locking valve of the branch combustion path A, the self-locking valve of the branch oxygen path B and the self-locking valve of the branch combustion path B by propelling the line box;
(4) pressurizing the A branch oxidant pipeline and the B branch oxidant pipeline to 0.3-0.4 MPa, namely keeping the pressure in the A branch combustion agent pipeline and the B branch combustion agent pipeline unchanged at 0 MPa;
(5) communicating the instruction passage of the A-branch thruster oxygen passage electromagnetic valve through the adapter box a, and disconnecting the instruction passage of the A-branch thruster fuel passage electromagnetic valve through the adapter box a; communicating the instruction passage of the B-branch thruster oxygen passage electromagnetic valve through the adapter box B, and disconnecting the instruction passage of the B-branch thruster fuel passage electromagnetic valve through the adapter box B; the switching box c is used for communicating the instruction passages of the A branch oxygen path self-locking valve and the B branch oxygen path self-locking valve, and the switching box c is used for disconnecting the instruction passages of the A branch fuel path self-locking valve and the B branch fuel path self-locking valve;
(6) after the self-locking valve of the branch A oxygen path is opened by the propelling line box, the propelling line box sends jet pulse to all the branch A thruster oxygen path electromagnetic valves in sequence, that is, assuming a total of n thrusters, i.e. the first, second, … ith and nth thrusters, after a jet pulse is sent to the first branch A thruster oxygen path electromagnetic valve by a propelling line box, sending jet pulse to the second A-branch thruster oxygen path electromagnetic valve through the propelling line box, repeating the steps until the nth A-branch thruster oxygen path electromagnetic valve is sent with jet pulse through the propelling line box, observing the jet effect of each A-branch thruster, if all the A-branch thrusters jet air, the polarity of the electromagnetic valves of the oxygen paths of all the A-branch thrusters is correct, and meanwhile, the polarity of the self-locking valves of the A-branch oxygen paths is correct; if the ith A-branch thruster does not jet air, the polarity of the electromagnetic valve of the oxygen path of the ith A-branch thruster is incorrect; if all the A branch thrusters do not jet air, the A branch oxygen path self-locking valve is incorrect in polarity; finally, closing the self-locking valve of the branch oxygen path A by pushing the line box; n is a natural number, and n is 1, 2 or 3 …;
(7) the method comprises the steps of relieving the pressure of an oxidant pipeline of a branch A and an oxidant pipeline of a branch B to 0MPa, opening a self-locking valve of an oxygen path of the branch B by a propelling line box, pressurizing the oxidant pipeline of the branch A and the oxidant pipeline of the branch B to 0.3-0.4 MPa, sequentially sending jet pulses to all the oxygen path electromagnetic valves of the thruster of the branch B by the propelling line box, namely, assuming that a total of n thrusters are respectively the first thruster, the second thruster, the … th ith thruster and the nth thruster, sending a jet pulse to the oxygen path electromagnetic valve of the first thruster of the branch B by the propelling line box, then sending jet pulses to the oxygen path electromagnetic valve of the second thruster of the branch B by the propelling line box, and repeating the steps until the jet pulses are sent to the oxygen path electromagnetic valve of the thruster of the nth thruster of the branch B by the propelling line box, and observing the jet effect of each thruster of the branch B, if all the B-branch thrusters jet air, the polarity of the electromagnetic valves of the oxygen paths of all the B-branch thrusters is correct, and meanwhile, the polarity of the self-locking valves of the oxygen paths of the B-branch thrusters is correct; if the ith B-branch thruster does not jet air, the polarity of the electromagnetic valve of the oxygen path of the ith B-branch thruster is incorrect; if all the B-branch thrusters do not jet air, the polarity of the self-locking valve of the B-branch oxygen path is incorrect; finally, closing the self-locking valve of the branch oxygen path B by pushing the line box;
(8) the method comprises the following steps that both the A branch oxidant pipeline and the B branch oxidant pipeline are decompressed to 0MPa, an instruction passage of a fuel passage electromagnetic valve of the A branch thruster is communicated through an adapter box a, and the instruction passage of an oxygen passage electromagnetic valve of the A branch thruster is disconnected through the adapter box a; communicating the instruction passage of the fuel passage electromagnetic valve of the B-branch thruster through the adapter box B, and disconnecting the instruction passage of the oxygen passage electromagnetic valve of the B-branch thruster through the adapter box B; the switching box c is used for communicating the instruction passages of the A-branch fuel passage self-locking valve and the B-branch fuel passage self-locking valve, and the switching box c is used for disconnecting the instruction passages of the A-branch oxygen passage self-locking valve and the B-branch oxygen passage self-locking valve; opening the A branch fuel path self-locking valve by pushing the circuit box;
(9) pressurizing the A branch combustion agent pipeline and the B branch combustion agent pipeline to 0.3-0.4 MPa, and keeping the pressure in the A branch oxidant pipeline and the B branch oxidant pipeline at 0 MPa;
(10) sequentially sending jet pulses to all the A-branch thruster fuel path electromagnetic valves through a propelling line box, namely assuming that a total of n thrusters are respectively the first, the second, the … th and the nth, sending a jet pulse to the first A-branch thruster fuel path electromagnetic valve through the propelling line box, then sending the jet pulse to the second A-branch thruster fuel path electromagnetic valve through the propelling line box, and repeating the steps until the jet pulse is sent to the nth A-branch thruster fuel path electromagnetic valve through the propelling line box, and observing the jet effect of each A-branch thruster; if the ith A-branch thruster does not jet air, the polarity of a fuel path electromagnetic valve of the ith A-branch thruster is incorrect; if all the A branch thrusters do not jet air, the A branch combustion path self-locking valve is incorrect in polarity; finally, closing the branch fuel path self-locking valve A by pushing the line box;
(11) the A branch combustion agent pipeline and the B branch combustion agent pipeline are decompressed to 0MPa, the B branch combustion agent pipeline and the A branch combustion agent pipeline are pressurized to 0.3MPa-0.4MPa after the self-locking valve of the B branch combustion agent pipeline is opened through the propelling line box, then jet pulses are sequentially sent to all B branch thruster fuel pipeline electromagnetic valves through the propelling line box, namely, assuming that a total of n thrusters are respectively the first thruster, the second thruster, the … th and the nth thruster, after the first B branch thruster fuel pipeline electromagnetic valve is sent with a jet pulse through the propelling line box, the jet pulses are sent to the second B branch thruster fuel pipeline electromagnetic valve through the propelling line box, and the analogy is carried out in sequence until the nth B branch thruster fuel pipeline electromagnetic valve is sent with a jet pulse through the propelling line box, and the jet effect of each B branch thruster is observed, if all the B-branch thrusters jet air, the polarity of the fuel path electromagnetic valves of all the B-branch thrusters is correct, and meanwhile, the polarity of the self-locking valves of the fuel paths of the B-branch thrusters is correct; if the ith B-branch thruster does not jet air, the polarity of the fuel path electromagnetic valve of the ith B-branch thruster is incorrect; if all the thrusters of the branch B do not jet air, the polarity of the self-locking valve of the combustion path of the branch B is incorrect; and finally, closing the B branch combustion path self-locking valve by pushing the circuit box.
The invention has the advantages that:
(1) the problem that the existing testing method cannot solve is solved, the polarity of a single electromagnetic valve and a self-locking valve is effectively verified, various problems caused by polarity errors are avoided, the coverage of ground testing is improved, and the normal function of the satellite is ensured;
(2) the test method only needs to use universal test tools such as the adapter box and the adapter cable, does not need matched special equipment, is convenient to implement, and has the advantages of low cost, high reliability, strong operability, strong flexibility and the like;
(3) the test method has wide application range and strong popularization, most of the existing satellite platforms adopt a scheme of a two-component unified propulsion system, and the method can be suitable for electrical performance test of the platforms.
(4) The invention effectively and independently verifies the installation polarity of each electromagnetic valve and the self-locking valve in the conventional ground test process through independent control of instructions, blocks the linkage of the paired valve bodies by serially connecting the switching boxes, and performs polarity check on the single electromagnetic valve and the self-locking valve by adopting a means of performing independent air injection test on an oxygen path and a fuel path on the thruster.
Drawings
FIG. 1 is a schematic flow chart of a testing method of the present invention;
FIG. 2 is a diagram of the connection relationship of the test equipment of the present invention.
Detailed Description
The invention will be further described with reference to the following figures and specific examples:
the tools required by the method are the adapter box and the adapter cable, the adapter box and the adapter cable are connected in a mode shown in fig. 2, and the adapter box needs to be operated according to corresponding steps in the test process.
The invention relates to a satellite two-component chemical propulsion polarity test method, which mainly comprises the following steps: the connection adapter box, the connection gas circuit and the A, B branch and the oxygen circuit are subjected to cross recombination gas injection test. When the air injection test is carried out, the adapter box is operated to open a corresponding instruction passage, and the action effect of the valve body is verified in a hand feeling and hearing mode.
As shown in fig. 1, the method of the invention comprises the following steps:
(1) connecting 3 switching boxes in series between a propulsion line box and a load according to the diagram of fig. 2, wherein the switches of the switching boxes 1 and 2 are all switched off, and the switch of the switching box 3 is all switched on;
(2) respectively connecting an oxidant adding and discharging valve and a combustion agent adding and discharging valve of the propulsion subsystem with a service valve and an air supply pipeline, separately supplying air to the oxygen pipeline and the combustion pipeline, opening the oxidant adding and discharging valve and the combustion agent adding and discharging valve, and discharging the pressure of the pipelines to 0 MPa;
(3) powering up the propulsion subsystem, and sending an instruction to close the oxygen path and the fuel path self-locking valve of the branch A and the branch B;
(4) carry out the jet-propelled test to A branch oxygen way solenoid valve and auto-lock valve, specific process includes:
(a) pressurizing the oxidant pipeline to 0.3-0.4 MPa, and maintaining the pressure of the combustion agent pipeline at 0 MPa;
(b) switching on the oxygen path electromagnetic valve switch instruction paths of the adapter boxes 1 and 2, switching off the rest of the contacts, switching on the oxygen path self-locking valve switch instruction path of the adapter box 3, and switching off the rest of the contacts;
(c) sending an instruction to open the self-locking valve of the branch A oxygen path;
(d) and sending a command to sequentially open the A-branch thruster to jet air, observing the air jet effect of a nozzle of the thruster during air jet, and listening the action sound of an oxygen valve by ears, if the air is given out and the sound is generated at the same time, the polarity of the electromagnetic valve of the oxygen path of the corresponding thruster is proved to be correct, and the polarity of the self-locking valve of the A-branch oxygen path can also be proved to be correct. Otherwise, it is incorrect;
(e) sending a command to close the A branch oxygen path self-locking valve.
(5) Carry out the jet-propelled test to B branch oxygen way solenoid valve and auto-lock valve, specific process includes:
(a) the oxidant pipeline and the combustion agent pipeline are adjusted to be 0 MPa;
(b) sending an instruction to open a self-locking valve B branch oxygen path self-locking valve;
(c) pressurizing the oxidant pipeline to 0.3-0.4 MPa, and maintaining the pressure of the combustion agent pipeline at 0 MPa;
(d) and sending a command to sequentially open the B-branch thruster for jetting, observing the jetting effect of the nozzle of the thruster during jetting, listening the action sound of the oxygen valve by ears, and if the air is given out and the sound is generated at the same time, proving that the polarity of the electromagnetic valve of the oxygen path of the corresponding thruster is correct, and simultaneously proving that the polarity of the self-locking valve of the B-branch oxygen path is correct. Otherwise, it is incorrect;
(e) and sending a command to close the B branch oxygen path self-locking valve.
(6) Carry out the jet-propelled test to A branch fuel way solenoid valve and auto-lock valve, specific process includes:
(a) the oxidant pipeline and the combustion agent pipeline are adjusted to be 0 MPa;
(b) switching on the fuel way electromagnetic valve switch instruction passages of the adapter boxes 1 and 2, switching off the rest points, switching on the fuel way self-locking valve switch instruction passages of the adapter box 3, and switching off the rest contacts;
(c) sending a command to open the A branch fuel path self-locking valve;
(d) pressurizing the combustion agent pipeline to 0.3-0.4 MPa, and keeping the pressure of the oxidant pipeline at 0 MPa;
(e) and sending a command to sequentially open the A branch thruster to jet air, observing the air jet effect of a nozzle of the thruster during air jet, listening the action sound of the combustion valve by using ears, and if the air is given out and the sound is generated at the same time, proving that the polarity of the electromagnetic valve of the corresponding thruster combustion path is correct, and simultaneously proving that the polarity of the A branch combustion path self-locking valve is correct. Otherwise, it is incorrect;
(f) a command is sent to close the a branch fuel line auto-lock valve.
(7) Carry out the jet-propelled test to B branch fuel way solenoid valve and auto-lock valve, specific process includes:
(a) the oxidant pipeline and the combustion agent pipeline are adjusted to be 0 MPa;
(b) sending a command to open a B branch fuel path self-locking valve;
(c) pressurizing the combustion agent pipeline to 0.3-0.4 MPa, and keeping the pressure of the oxidant pipeline at 0 MPa;
(d) and sending a command to sequentially open the B-branch thruster for jetting, observing the jetting effect of a nozzle of the thruster during jetting, listening the action sound of the combustion valve by using ears, and if the air is given out and the sound is generated at the same time, proving that the polarity of the electromagnetic valve of the corresponding fuel path of the thruster is correct, and simultaneously proving that the polarity of the self-locking valve of the B-branch fuel path is correct. Otherwise, it is incorrect;
(e) a command is sent to close the B branch fuel line auto-lock valve.
(8) And powering off the propulsion subsystem, dismantling the line box, and dismantling the pipeline after the pressure of the satellite pipeline is filled to 0.2 MPa.
Examples
The electric polarity test method of the satellite two-component chemical propulsion subsystem comprises a propulsion line box, an A branch line, a B branch line and four thrusters, wherein the four thrusters are respectively a thruster 1A, a thruster 2A, a thruster 1B and a thruster 1B;
the branch A pipeline comprises a branch A oxidant pipeline and a branch A combustion agent pipeline;
the B branch pipeline comprises a B branch oxidant pipeline and a B branch combustion agent pipeline;
wherein, the thruster 1A and the thruster 2A are thrusters communicated with the branch pipeline A; the thruster 1B and the thruster 1B are thrusters communicated with the branch pipeline B;
the A branch oxidant pipeline is provided with a self-locking valve which is called as an A branch oxygen path self-locking valve;
the branch A combustion agent pipeline is provided with a self-locking valve which is called as a branch A combustion pipeline self-locking valve;
the B branch oxidant pipeline is provided with a self-locking valve which is called as a B branch oxygen path self-locking valve;
the branch B combustion agent pipeline is provided with a self-locking valve which is called as a branch B combustion path self-locking valve;
the thruster 1A and the thruster 2A are respectively provided with two electromagnetic valves, wherein one electromagnetic valve is called an A-branch thruster oxygen path electromagnetic valve, and the other electromagnetic valve is called an A-branch thruster fuel path electromagnetic valve;
the thruster 1B and the thruster 1B are respectively provided with two electromagnetic valves, wherein one electromagnetic valve is called a B-branch thruster oxygen path electromagnetic valve, and the other electromagnetic valve is called a B-branch thruster fuel path electromagnetic valve;
the propulsion circuit box is used for controlling the on-off of all the electromagnetic valves and the self-locking valve, wherein the propulsion circuit box controls the oxygen path electromagnetic valve of the A-branch thruster and the fuel path electromagnetic valve of the A-branch thruster through a cable a; the propulsion line box controls the oxygen path electromagnetic valve of the branch thruster B and the fuel path electromagnetic valve of the branch thruster B through a cable B; the propelling line box controls the A branch oxygen path self-locking valve, the A branch combustion path self-locking valve, the B branch oxygen path self-locking valve and the B branch combustion path self-locking valve through a cable c, as shown in figure 2;
the testing method comprises the following steps:
(1) the cable connection box is characterized in that a junction box a is connected between the cable a and the propelling line box in series, a junction box b is connected between the cable b and the propelling line box in series, and a junction box c is connected between the cable c and the propelling line box in series;
(2) releasing the pressure in the A branch oxidant pipeline, the A branch combustion agent pipeline, the B branch oxidant pipeline and the B branch combustion agent pipeline to 0 MPa;
(3) closing the self-locking valve of the branch oxygen path A, the self-locking valve of the branch combustion path A, the self-locking valve of the branch oxygen path B and the self-locking valve of the branch combustion path B by propelling the line box;
(4) pressurizing the A branch oxidant pipeline and the B branch oxidant pipeline to 0.3-0.4 MPa, namely keeping the pressure in the A branch combustion agent pipeline and the B branch combustion agent pipeline unchanged at 0 MPa;
(5) communicating the instruction passage of the A-branch thruster oxygen passage electromagnetic valve through the adapter box a, and disconnecting the instruction passage of the A-branch thruster fuel passage electromagnetic valve through the adapter box a; communicating the instruction passage of the B-branch thruster oxygen passage electromagnetic valve through the adapter box B, and disconnecting the instruction passage of the B-branch thruster fuel passage electromagnetic valve through the adapter box B; the switching box c is used for communicating the instruction passages of the A branch oxygen path self-locking valve and the B branch oxygen path self-locking valve, and the switching box c is used for disconnecting the instruction passages of the A branch fuel path self-locking valve and the B branch fuel path self-locking valve;
(6) after the A branch oxygen path self-locking valve is opened through the propelling line box, the propelling line box sends jet pulse to the thruster 1A oxygen path electromagnetic valve, then the propelling line box sends jet pulse to the thruster 2A oxygen path electromagnetic valve, the jet effect of the thruster 1A and the thruster 2A is observed, if the thruster 1A and the thruster 2A both jet air, the polarities of the thruster 1A oxygen path electromagnetic valve and the thruster 2A oxygen path electromagnetic valve are correct, and meanwhile, the polarity of the A branch oxygen path self-locking valve is correct; if the thruster 1A does not jet air, the polarity of the electromagnetic valve of the oxygen path of the thruster 1A is incorrect; if the thruster 1A and the thruster 2A do not eject air, the polarity of the self-locking valve of the branch oxygen path A is incorrect; finally, closing the self-locking valve of the branch oxygen path A by pushing the line box;
(7) the method comprises the steps of relieving the pressure of an oxidant pipeline of a branch A and an oxidant pipeline of a branch B to 0MPa, opening a self-locking valve of an oxygen path of the branch B through a propelling line box, then pressurizing the oxidant pipeline of the branch A and the oxidant pipeline of the branch B to 0.3-0.4 MPa, sending jet pulses to an electromagnetic valve of an oxygen path of a thruster 1B through the propelling line box, then sending the jet pulses to an electromagnetic valve of an oxygen path of a thruster 2B through the propelling line box, observing the jet effects of the thruster 1B and the thruster 2B, and if the thruster 1B and the thruster 2B both jet air, indicating that the polarities of the electromagnetic valve of the oxygen path of the thruster 1B and the electromagnetic valve of the oxygen path of the thruster 2B are correct, and simultaneously indicating that the polarity of the self-locking valve of the oxygen path of the; if the thruster 1B does not jet air, the polarity of the electromagnetic valve of the oxygen path of the thruster 1B is incorrect; if the thruster 1B and the thruster 2B do not eject air, the polarity of the self-locking valve of the branch oxygen path B is incorrect; finally, closing the self-locking valve of the branch oxygen path B by pushing the line box;
(8) the method comprises the following steps that both the A branch oxidant pipeline and the B branch oxidant pipeline are decompressed to 0MPa, an instruction passage of a fuel passage electromagnetic valve of the A branch thruster is communicated through an adapter box a, and the instruction passage of an oxygen passage electromagnetic valve of the A branch thruster is disconnected through the adapter box a; communicating the instruction passage of the fuel passage electromagnetic valve of the B-branch thruster through the adapter box B, and disconnecting the instruction passage of the oxygen passage electromagnetic valve of the B-branch thruster through the adapter box B; the switching box c is used for communicating the instruction passages of the A-branch fuel passage self-locking valve and the B-branch fuel passage self-locking valve, and the switching box c is used for disconnecting the instruction passages of the A-branch oxygen passage self-locking valve and the B-branch oxygen passage self-locking valve; opening the A branch fuel path self-locking valve by pushing the circuit box;
(9) pressurizing the A branch combustion agent pipeline and the B branch combustion agent pipeline to 0.3-0.4 MPa, and keeping the pressure in the A branch oxidant pipeline and the B branch oxidant pipeline at 0 MPa;
(10) after the jet pulse is sent to the fuel path electromagnetic valve of the thruster 1A by propelling the line box, the jet pulse is sent to the fuel path electromagnetic valve of the thruster 2A by propelling the line box, the jet effect of the thruster 1A and the thruster 2A is observed, if the thruster 1A and the thruster 2A both jet air, the polarities of the fuel path electromagnetic valve of the thruster 1A and the fuel path electromagnetic valve of the thruster 2A are both correct, and the polarity of the branch fuel path auto-lock valve A is also correct; if the thruster 1A does not jet air, the polarity of the fuel path electromagnetic valve of the thruster 1A is incorrect; if the thruster 1A and the thruster 2A do not eject air, the polarity of the branch A combustion path self-locking valve is incorrect; finally, closing the branch fuel path self-locking valve A by pushing the line box;
(11) the method comprises the steps that a branch combustion agent pipeline A and a branch combustion agent pipeline B are decompressed to 0MPa, after a branch combustion agent self-locking valve B is opened through a propelling line box, the branch combustion agent pipeline A and the branch combustion agent pipeline B are both pressurized to 0.3MPa-0.4MPa, jet pulses are sent to a thruster 1B fuel path electromagnetic valve through the propelling line box, then the thruster 2B fuel path electromagnetic valve is sent with jet pulses through the propelling line box, the jet effects of the thruster 1B and the thruster 2B are observed, if the thruster 1B and the thruster 2B jet air, the thruster 1B fuel path electromagnetic valve and the thruster 2B fuel path electromagnetic valve are correct in polarity, and meanwhile, the branch combustion agent self-locking valve B is correct in polarity; if the thruster 1B does not jet air, the polarity of the fuel path electromagnetic valve of the thruster 1B is incorrect; if the thruster 1B and the thruster 2B do not eject air, the polarity of the branch B combustion path self-locking valve is incorrect, and finally the branch B combustion path self-locking valve is closed through the propelling line box.
The parts not described in the present invention belong to the known art in the field.
Claims (10)
1. The electric polarity test method of the satellite two-component chemical propulsion subsystem is characterized by comprising the following steps:
(1) the cable connection box is characterized in that a junction box a is connected between the cable a and the propelling line box in series, a junction box b is connected between the cable b and the propelling line box in series, and a junction box c is connected between the cable c and the propelling line box in series;
(2) releasing the pressure in the A branch oxidant pipeline, the A branch combustion agent pipeline, the B branch oxidant pipeline and the B branch combustion agent pipeline to 0 MPa;
(3) closing the self-locking valve of the branch oxygen path A, the self-locking valve of the branch combustion path A, the self-locking valve of the branch oxygen path B and the self-locking valve of the branch combustion path B by propelling the line box;
(4) pressurizing both the A branch oxidant pipeline and the B branch oxidant pipeline;
(5) communicating the instruction passage of the A-branch thruster oxygen passage electromagnetic valve through the adapter box a, and disconnecting the instruction passage of the A-branch thruster fuel passage electromagnetic valve through the adapter box a; communicating the instruction passage of the B-branch thruster oxygen passage electromagnetic valve through the adapter box B, and disconnecting the instruction passage of the B-branch thruster fuel passage electromagnetic valve through the adapter box B; the switching box c is used for communicating the instruction passages of the A branch oxygen path self-locking valve and the B branch oxygen path self-locking valve, and the switching box c is used for disconnecting the instruction passages of the A branch fuel path self-locking valve and the B branch fuel path self-locking valve;
(6) after the A branch oxygen path self-locking valve is opened by the propelling line box, the propelling line box sequentially sends jet pulses to all the A branch thruster oxygen path electromagnetic valves, and the jet effect of each A branch thruster is observed, if all the A branch thrusters jet air, the polarity of all the A branch thruster oxygen path electromagnetic valves is correct, and meanwhile, the polarity of the A branch oxygen path self-locking valve is correct; if the A branch thruster does not jet air, the polarity of the electromagnetic valve of the oxygen path of the A branch thruster is incorrect; if all the A branch thrusters do not jet air, the A branch oxygen path self-locking valve is incorrect in polarity; finally, closing the self-locking valve of the branch oxygen path A by pushing the line box;
(7) the method comprises the steps that both the A branch oxidant pipeline and the B branch oxidant pipeline are decompressed to 0MPa, after the B branch oxygen path self-locking valve is opened through a propelling line box, both the A branch oxidant pipeline and the B branch oxidant pipeline are pressurized, then jet pulses are sequentially sent to all B branch thruster oxygen path electromagnetic valves through the propelling line box, the jet effect of each B branch thruster is observed, if all B branch thrusters jet air, the polarity of all B branch thruster oxygen path electromagnetic valves is correct, and meanwhile, the polarity of the B branch oxygen path self-locking valve is correct; if the B branch thruster does not jet air, the polarity of the electromagnetic valve of the oxygen path of the B branch thruster is incorrect; if all the B-branch thrusters do not jet air, the polarity of the self-locking valve of the B-branch oxygen path is incorrect; finally, closing the self-locking valve of the branch oxygen path B by pushing the line box;
(8) the method comprises the following steps that both the A branch oxidant pipeline and the B branch oxidant pipeline are decompressed to 0MPa, an instruction passage of a fuel passage electromagnetic valve of the A branch thruster is communicated through an adapter box a, and the instruction passage of an oxygen passage electromagnetic valve of the A branch thruster is disconnected through the adapter box a; communicating the instruction passage of the fuel passage electromagnetic valve of the B-branch thruster through the adapter box B, and disconnecting the instruction passage of the oxygen passage electromagnetic valve of the B-branch thruster through the adapter box B; the switching box c is used for communicating the instruction passages of the A-branch fuel passage self-locking valve and the B-branch fuel passage self-locking valve, and the switching box c is used for disconnecting the instruction passages of the A-branch oxygen passage self-locking valve and the B-branch oxygen passage self-locking valve; opening the A branch fuel path self-locking valve by pushing the circuit box;
(9) pressurizing both the branch A combustion agent pipeline and the branch B combustion agent pipeline, and keeping the pressure in the branch A oxidant pipeline and the branch B oxidant pipeline at 0 MPa;
(10) sequentially sending jet pulses to all the A-branch thruster fuel path electromagnetic valves through the propelling line box, observing the jet effect of each A-branch thruster, and if all the A-branch thrusters jet air, indicating that all the A-branch thruster fuel path electromagnetic valves are correct in polarity and simultaneously indicating that the A-branch fuel path self-locking valves are correct in polarity; if the branch thruster A does not jet air, the polarity of the fuel path electromagnetic valve of the branch thruster A is incorrect; if all the A branch thrusters do not jet air, the A branch combustion path self-locking valve is incorrect in polarity; finally, closing the branch fuel path self-locking valve A by pushing the line box;
(11) the method comprises the steps that a branch A combustion agent pipeline and a branch B combustion agent pipeline are decompressed to 0MPa, a branch B combustion agent self-locking valve is opened through a propelling line box, then the branch A combustion agent pipeline and the branch B combustion agent pipeline are pressurized, jet pulses are sequentially sent to all branch B thruster fuel line electromagnetic valves through the propelling line box, the jet effect of each branch B thruster is observed, if all branch B thrusters jet air, the polarity of all branch B thruster fuel line electromagnetic valves is correct, and meanwhile, the polarity of the branch B combustion line self-locking valve is correct; if the branch thruster B does not jet air, the polarity of the fuel path electromagnetic valve of the branch thruster B is incorrect; if all the thrusters of the branch B do not jet air, the polarity of the self-locking valve of the combustion path of the branch B is incorrect; and finally, closing the B branch combustion path self-locking valve by pushing the circuit box.
2. The method for testing electrical polarity of a satellite two-component chemical propulsion subsystem of claim 1, wherein: in the step (4), the branch A oxidant pipeline and the branch B oxidant pipeline are pressurized to 0.3MPa-0.4 MPa.
3. The method for testing electrical polarity of a satellite two-component chemical propulsion subsystem of claim 1, wherein: in the step (6), the method for sequentially sending the jet pulse to all the branch thruster oxygen path electromagnetic valves through the propelling line box comprises the following steps: assuming that a total of n thrusters are respectively the first thruster, the second thruster, the … ith thruster and the nth thruster, after a jet pulse is sent to the oxygen path electromagnetic valve of the first A branch thruster by the propelling line box, the jet pulse is sent to the oxygen path electromagnetic valve of the second A branch thruster by the propelling line box, and so on until the jet pulse is sent to the oxygen path electromagnetic valve of the nth A branch thruster by the propelling line box.
4. The method for testing electrical polarity of a satellite two-component chemical propulsion subsystem of claim 1, wherein: in the step (7), the branch A oxidant pipeline and the branch B oxidant pipeline are pressurized to 0.3MPa-0.4 MPa.
5. The method for testing electrical polarity of a satellite two-component chemical propulsion subsystem of claim 1, wherein: in the step (7), the method for sequentially sending the jet pulse to all the B-branch thruster oxygen path electromagnetic valves by the propelling line box comprises the following steps: assuming that a total of n thrusters are respectively the first, the second, the ith and the nth … thrusters, after a jet pulse is sent to the first B-branch thruster oxygen path electromagnetic valve through the propelling line box, the jet pulse is sent to the second B-branch thruster oxygen path electromagnetic valve through the propelling line box, and so on until the jet pulse is sent to the nth B-branch thruster oxygen path electromagnetic valve through the propelling line box.
6. The method for testing electrical polarity of a satellite two-component chemical propulsion subsystem of claim 1, wherein: and (9) pressurizing the branch A combustion agent pipeline and the branch B combustion agent pipeline to 0.3-0.4 MPa.
7. The method for testing electrical polarity of a satellite two-component chemical propulsion subsystem of claim 1, wherein: in the step (10), the method for sequentially sending the jet pulse to all the branch thruster fuel path electromagnetic valves by propelling the path box comprises the following steps: assuming that a total of n thrusters are respectively the first thruster, the second thruster, the … th thruster and the nth thruster, after an air injection pulse is sent to the first A branch thruster fuel path electromagnetic valve through the propelling line box, the air injection pulse is sent to the second A branch thruster fuel path electromagnetic valve through the propelling line box, and so on until the air injection pulse is sent to the nth A branch thruster fuel path electromagnetic valve through the propelling line box.
8. The method for testing electrical polarity of a satellite two-component chemical propulsion subsystem of claim 1, wherein: in the step (11), the branch A combustion agent pipeline and the branch B combustion agent pipeline are pressurized to 0.3MPa-0.4 MPa.
9. The method for testing electrical polarity of a satellite two-component chemical propulsion subsystem of claim 1, wherein: in the step (11), the method for sequentially sending the jet pulses to all the fuel path electromagnetic valves of the B-branch thruster by propelling the path box comprises the following steps: assuming that a total of n thrusters are respectively the first, the second, the ith and the nth … thrusters, after an air jet pulse is sent to the first B-branch thruster fuel path electromagnetic valve through the propelling line box, the air jet pulse is sent to the second B-branch thruster fuel path electromagnetic valve through the propelling line box, and the rest is done in sequence until the air jet pulse is sent to the nth B-branch thruster fuel path electromagnetic valve through the propelling line box.
10. The method for testing electrical polarity of a satellite two-component chemical propulsion subsystem of claim 1, wherein: the double-component chemical propulsion subsystem comprises a propulsion line box, an A branch line, a B branch line and a plurality of thrusters;
the branch A pipeline comprises a branch A oxidant pipeline and a branch A combustion agent pipeline;
the B branch pipeline comprises a B branch oxidant pipeline and a B branch combustion agent pipeline;
the thruster communicated with the branch pipeline A is called as a branch thruster A, and the thruster communicated with the branch pipeline B is called as a branch thruster B;
the A branch oxidant pipeline is provided with a self-locking valve which is called as an A branch oxygen path self-locking valve;
the branch A combustion agent pipeline is provided with a self-locking valve which is called as a branch A combustion pipeline self-locking valve;
the B branch oxidant pipeline is provided with a self-locking valve which is called as a B branch oxygen path self-locking valve;
the branch B combustion agent pipeline is provided with a self-locking valve which is called as a branch B combustion path self-locking valve;
each branch A thruster is provided with two electromagnetic valves, wherein the electromagnetic valve communicated with the branch A oxidant pipeline is called a branch A thruster oxygen path electromagnetic valve, and the electromagnetic valve communicated with the branch A combustion agent pipeline is called a branch A thruster fuel path electromagnetic valve;
each branch B thruster is provided with two electromagnetic valves, wherein the electromagnetic valve communicated with the branch B oxidant pipeline is called a branch B thruster oxygen path electromagnetic valve, and the electromagnetic valve communicated with the branch B combustion agent pipeline is called a branch B thruster fuel path electromagnetic valve;
the propulsion circuit box is used for controlling the on-off of all the electromagnetic valves and the self-locking valve, wherein the propulsion circuit box controls the oxygen path electromagnetic valve of the A-branch thruster and the fuel path electromagnetic valve of the A-branch thruster through a cable a; the propulsion line box controls the oxygen path electromagnetic valve of the branch thruster B and the fuel path electromagnetic valve of the branch thruster B through a cable B; the propelling line box controls the A branch oxygen path self-locking valve, the A branch combustion path self-locking valve, the B branch oxygen path self-locking valve and the B branch combustion path self-locking valve through a cable c.
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