CN103213692B - Method of actively adjusting balanced discharging of parallel connection tanks of satellite two component propelling system - Google Patents
Method of actively adjusting balanced discharging of parallel connection tanks of satellite two component propelling system Download PDFInfo
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Abstract
The invention relates to a method of actively adjusting the balanced discharging of parallel connection tanks of a satellite two component propelling system. A simulation model of a propelling system is firstly established; the current system mixing ratio r0 is calculated according to the current system state data; then the pressure difference dpo1 of oxidant tanks (MON-A and MON-B) and the pressure difference dpf1 of incendiary agent tanks (MMH-A and MMH-B) are calculated through an optimization algorithm according to the target value of the balanced discharging of the parallel connection tanks; the target pressure of each tank is finally calculated through the optimization algorithm by taking the r0 as the target value and the dpo1 and dpf1 as the initial conditions; and the pressure of the tanks can be adjusted to the target pressure point by utilizing gas bypasses when a satellite is in orbit, so that not only is the balanced discharging of the parallel connection tanks adjusted, but also the system mixing ratio is not influenced.
Description
Technical field
The present invention relates to the method for a kind of active adjustment satellite bipropellant propulsion system tank balance in parallel discharge, be applicable to the tank balance in parallel emission control of satellite bipropellant propulsion system.
Background technology
For the satellite bipropellant propulsion system of tank structure in parallel, an important problem is propellant balance discharge capacity.If the propellant space emission overbalance of two tanks in parallel, then after propellant in a tank is emptying, then continue the helium in tank to be discharged, make the ducted propellant gas enclosure of propellant, thruster and driving engine cannot work, and satellite life terminates.And in another tank, residual propellant will become slow-witted heavy, cannot use.For the satellite carrying propellant 3000kg, in every tank, adding amount is 934kg oxidizer or 566kg fuel, if the unbalance factor of tank parallel connection discharge is 3%, to have 28kg oxidizer latter stage to satellite life and 17kg fuel becomes slow-witted heavy, also additionally will consume 45kg propellant and these slow-witted heavy (propellants) are delivered to satellite orbit.If the unbalance factor of tank parallel connection discharge can be controlled to 1%, integrate and just can save about 60kg propellant.In addition, if tank in parallel discharge overbalance, will cause centroid of satellite deflection, when orbit maneuver engine can be caused time serious to light a fire, attitude is uncontrollable.Therefore, for the satellite platform of tank structure in parallel, the propellant balance emission problem of tank in parallel must solve.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming prior art, the method of active adjustment satellite bipropellant propulsion system tank balance in parallel discharge is provided, the method is based on balancing the propulsion system realization of discharging by active adjustment tank in parallel, the Stress control target of every tank is calculated according to tank balance emissions object in parallel, reach and both regulate tank in parallel to balance discharge, again the effect of not influential system mixture ratio.
Above-mentioned purpose of the present invention is mainly achieved by following technical solution:
The method of active adjustment satellite bipropellant propulsion system tank balance in parallel discharge, comprises the steps:
(1) Simulation Calculation of satellite bipropellant propulsion system is set up, setting gas cylinder and tank initial pressure and temperature, and the quality of propellant in tank, wherein two oxidizer tank initial pressures are designated as pto1, pto2, and two fuel tank initial pressures are designated as ptf1, ptf2;
(2) arranging two oxidizer tank pressure reduction dpo in satellite bipropellant propulsion system is independent variable, uses propulsion system simulation computation model to solve with dpo to be the oxidizer tank balance discharge of independent variable to compare yc
1;
(3) oxidizer tank emissions object value yo in parallel is set, and Offered target function J (dpo)=| yc
1-yo|, uses single argument optimizing algorithm to solve the optimal solution dpo1 making J (dpo)=0 based on step (2);
(4) arranging two fuel tank pressure reduction dpf in satellite bipropellant propulsion system is independent variable, uses propulsion system simulation computation model to solve with dpf to be the fuel tank balance discharge of independent variable to compare yc
2;
(5) fuel tank emissions object value yf in parallel is set, and Offered target function J (dpf)=| yc
2-yf|, uses single argument optimizing algorithm to solve the optimal solution dpf1 making J (dpf)=0 based on step (4);
(6) initial pressure and the temperature of gas cylinder and tank are again set in propulsion system simulation computation model, and the quality of propellant in tank, wherein the initial pressure of two oxidizer tanks is designated as pto1 ', pto2 ', the initial pressure of two fuel tanks is designated as ptf1 ', ptf2 ', use the following parameter of propulsion system simulation model solution afterwards: this becomes the mixture ratio r0 of rail, oxidizer tank downstream intersection pressure p o0, fuel tank downstream intersection pressure p f0;
(7) Offered target mixture ratio data r1, if current mixing ratio r0 is less than target mix ratio r1, performs step (8), otherwise performs step (11);
(8) arranging oxidizer tank downstream intersection pressure p o is independent variable, and calling that propulsion system simulation computation model solves with po is the system mixture ratio rc of independent variable;
(9) Offered target function J (po)=| rc-r1|, uses single argument optimizing algorithm to solve the optimal solution po1 making J (po)=0 based on step (8);
(10) oxidizer tank goal pressure ptoA, ptoB and fuel tank goal pressure ptf1 ', ptf2 ' is exported, wherein oxidizer tank goal pressure ptoA=pto1 '+(po1-po0), ptoB=pto2 '+(po1-po0);
(11) arranging fuel tank downstream intersection pressure p f is independent variable, and calling that propulsion system simulation computation model solves with pf is the system mixture ratio rc of independent variable;
(12) Offered target function J (pf)=| rc-r1|, uses single argument optimizing algorithm to solve the optimal solution pf1 making J (pf)=0 based on step (11);
(13) oxidizer tank goal pressure pto1 ', pto2 ' and fuel tank goal pressure ptfA, ptfB is exported, wherein fuel tank goal pressure ptfA=ptf1 '+(pf1-pf0), ptfB=ptf2 '+(pf1-pf0).
In the method for above-mentioned active adjustment satellite bipropellant propulsion system tank balance in parallel discharge, in step (6), initial pressure pto1 ', the pto2 ' of two oxidizer tanks obtain by the following method:
If the initial pressure of tank 1 is pto1 in step (1) two oxidizer tank, the initial pressure of tank 2 is pto2, and pto1 < pto2, then in step (6), the initial pressure pto1 ' of tank 1 is still pto1, and the initial pressure pto2 ' of tank 2 is pto1+dpo1; Otherwise pto1 ' is pto2+dpo1, pto2 ' be pto2;
The initial pressure ptf1 ' of two fuel tanks, ptf2 ' obtain by the following method:
If the initial pressure of tank 1 is ptf1 in step (1) two fuel tank, the initial pressure of tank 2 is ptf2, and ptf1 < ptf2, then in step (6), the initial pressure ptf1 ' of tank 1 is still ptf1, the initial pressure ptf2 ' of tank 2 is ptf1+dpf1, otherwise ptf1 ' is ptf2+dpf1, ptf2 ' be ptf2.
In the method for above-mentioned active adjustment satellite bipropellant propulsion system tank balance in parallel discharge, satellite bipropellant propulsion system comprises gas cylinder, pressure sensor, add valve, pressure reducer, check valve, often open electric blasting valve, propellant tank, precise tracking, appearance control thruster and gas bypassing, wherein: propellant tank comprises two oxidizer tank MON-A, MON-B, two fuel tank MMH-A, MMH-B, connect with gas bypassing between gas cylinder and every constituent element propellant tank, gas bypassing is formed by connecting by 2 latching valves and 1 air-capacitor, air-capacitor is between 2 latching valves, add valve and be arranged on gas bypassing upstream.
In the method for above-mentioned active adjustment satellite bipropellant propulsion system tank balance in parallel discharge, gas bypassing two ends increase by first and often open electric blasting valve or normally closed electric blasting valve, play fault isolation effect.
In the method for above-mentioned active adjustment satellite bipropellant propulsion system tank balance in parallel discharge, arrange second between 2 gas bypassings and often open electric blasting valve, to be met in upstream by gas bypassing to avoid the propellant steam of 2 kinds of constituent elements and blast.
The present invention compared with prior art has following beneficial effect:
(1) first the present invention sets up the realistic model of propulsion system, current system mixture ratio r0 is calculated according to current system conditions data, then according to tank balance discharge expected value in parallel, the difference of pressure dpf1 between difference of pressure dpo1 between oxidizer tank (MON-A and MON-B) and fuel tank (MMH-A and MMH-B) is calculated by optimizing algorithm, last is expected value with r0, with dpo1 and dpf1 for initial condition (IC), the goal pressure of every tank is calculated by optimizing algorithm, staff just can utilize gas bypassing by tank pressure adjusting to goal pressure point, thus reach the object regulating the discharge of tank in parallel balance, and not influential system mixture ratio,
(2) through ground test, the present invention can just within tank parallel-balance emission norm controlling to 0.8%, simultaneously can by within mixture ratio deviation control to 0.8%, be equivalent to the propellant saving 5% ~ 6%, for GEO track 15 years term satellite, be equivalent to 3 ~ 4 year life-span, therefore the inventive method substantially prolongs satellite life.
(3) the present invention's tank in parallel balance discharge method is simple, and accurate and effective, has stronger practicality raw.
Accompanying drawing explanation
Fig. 1 is that the present invention can balance the propulsion system structure figure discharged by active adjustment tank in parallel;
Fig. 2 is the method for calculating diagram of circuit of active adjustment of the present invention tank balance in parallel discharge.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention is described in further detail:
Be illustrated in figure 1 the present invention and can balance the propulsion system structure figure discharged by active adjustment tank in parallel, propulsion system comprises gas cylinder 1 as seen from the figure, pressure sensor 2, add valve 3, pressure reducer 4, check valve 5, often open electric blasting valve 6, propellant tank 8, precise tracking 9, appearance control thruster 10, gas bypassing 11, first often opens electric blasting valve 12, first normally closed electric blasting valve 14 and second often opens electric blasting valve 15, wherein: connect with gas bypassing 11 between gas cylinder 1 and every constituent element propellant tank 8, gas bypassing 11 is formed by connecting by two latching valves 7 and an air-capacitor 13, air-capacitor 13 is between two latching valves 7.Propellant tank 8 comprises two oxidizer tanks MON-A, MON-B, two fuel tanks MMH-A, MMH-B.
For improving the reliability of gas bypassing 11, increasing by first at gas bypassing 11 two ends and often opening electric blasting valve 12 or normally closed electric blasting valve 14, playing fault isolation effect.
For avoiding the propellant steam of 2 kinds of constituent elements to be met in upstream by gas bypassing 11 and blasting, between 2 gas bypassings 11, arrange second often open electric blasting valve 15, before use gas bypassing 11, open quick-fried this second often open electric blasting valve 15, the connection of 2 groups of gas bypassings 11 is disconnected, and gas cylinder 1 is divided into 2 groups, be connected with 2 gas bypassings 11 respectively, and give propellant tank 8 air feed of often kind of constituent element respectively by gas bypassing 11.
In order to test gas bypassing 11 performance on the ground, arrange in gas bypassing 11 upstream and add valve 3.
In the propulsion system of Fig. 1, gas cylinder 1 is for storing high pressure gas (normally helium); Propellant tank 8 is for storing propellant; Be connected with check valve 5 by pressure reducer 4 between gas cylinder 1 and propellant tank 8, and configure necessary pressure sensor 2, add valve 3, often drive electric blasting valve 6 and latching valve 7; Pressure reducer 4 for reducing pressure to the high pressure gas in gas cylinder 1 and injecting propellant tank 8, to maintain the pressure stability of propellant tank 8; Check valve 5, for preventing propellant steam back diffusion in the propellant tank 8 of different constituent element to the joint in pressure reducer downstream, avoids danger of blasting; Pressure sensor 2 is for measuring the pressure of gas cylinder 1 and propellant tank 8; Add valve 3 for terrestrial operation, annotate to gas cylinder 1 and propellant tank 8 or discharge propellant and gas; Often open electric blasting valve 6 for cutting off the connection between propellant tank 8 and upstream steam line, cut-out opportunity be after precise tracking is finished the work or upstream steam line et out of order time; Latching valve 7 is for controlling the break-make of gas or propellant pipeline.
The present invention first set up above-mentioned can the realistic model of propulsion system of active adjustment tank balance in parallel discharge, current system mixture ratio r0 is calculated according to current system conditions data, then according to tank balance discharge expected value in parallel, the difference of pressure dpf1 between difference of pressure dpo1 between oxidizer tank (MON-A and MON-B) and fuel tank (MMH-A and MMH-B) is calculated by optimizing algorithm, last is expected value with r0, with dpo1 and dpf1 for initial condition (IC), calculated the goal pressure of every tank by optimizing algorithm.Staff just can utilize gas bypassing by tank pressure adjusting to goal pressure point, thus reaches the object regulating the discharge of tank in parallel balance.
Be illustrated in figure 2 the method for calculating diagram of circuit of active adjustment of the present invention tank balance in parallel discharge, concrete methods of realizing of the present invention is as follows:
(1) Simulation Calculation of satellite bipropellant propulsion system is set up, setting gas cylinder and tank initial pressure and temperature, and the quality of propellant in tank, wherein two oxidizer tank initial pressures are designated as pto1, pto2, and two fuel tank initial pressures are designated as ptf1, ptf2;
(2) arranging two oxidizer tank pressure reduction dpo in satellite bipropellant propulsion system is independent variable, uses propulsion system simulation computation model to solve with dpo to be the oxidizer tank balance discharge of independent variable to compare yc1;
(3) oxidizer tank emissions object value yo in parallel is set, and Offered target function J (dpo)=| yc
1-yo|, uses single argument optimizing algorithm to solve the optimal solution dpo1 making J (dpo)=0 based on step (2);
(4) arranging two fuel tank pressure reduction dpf in satellite bipropellant propulsion system is independent variable, uses propulsion system simulation computation model to solve with dpf to be the fuel tank balance discharge of independent variable to compare yc2;
(5) fuel tank emissions object value yf in parallel is set, and Offered target function J (dpf)=| yc
2-yf|, uses single argument optimizing algorithm to solve the optimal solution dpf1 making J (dpf)=0 based on step (4);
(6) initial pressure and the temperature of gas cylinder and tank are again set in propulsion system simulation computation model, and the quality of propellant in tank, wherein the initial pressure of two oxidizer tanks is designated as pto1 ', pto2 ', initial pressure pto1 ', the pto2 ' of two oxidizer tanks with the less tank of wherein pressure for benchmark, the initial pressure of another tank obtains according to two oxidizer tank pressure reduction dpo1, that is:
If the initial pressure of tank 1 is pto1 in step (1) two oxidizer tank, the initial pressure of tank 2 is pto2, and pto1 < pto2, then in step (6), the initial pressure pto1 ' of tank 1 is still pto1, and the initial pressure pto2 ' of tank 2 is pto1+dpo1; If pto2 < is pto1, then in step (6), the initial pressure pto2 ' of tank 2 is still pto2, and the initial pressure pto1 ' of tank 1 is pto2+dpo1.
Wherein the initial pressure of two fuel tanks is designated as ptf1 ', ptf2 '.Initial pressure ptf1 ', the ptf2 ' of two fuel tanks are with the less tank of wherein pressure for benchmark, and the initial pressure of another tank obtains according to two fuel tank pressure reduction dpf1, that is:
If the initial pressure of tank 1 is ptf1 in step (1) two fuel tank, the initial pressure of tank 2 is ptf2, and ptf1 < ptf2, then in step (6), the initial pressure ptf1 ' of tank 1 is still ptf1, and the initial pressure ptf2 ' of tank 2 is ptf1+dpf1.If ptf2 < is ptf1, then in step (6), the initial pressure ptf2 ' of tank 2 is still ptf2, and the initial pressure ptf1 ' of tank 1 is ptf2+dpf1.
Use the following parameter of propulsion system simulation model solution afterwards: this becomes the mixture ratio r0 of rail, oxidizer tank downstream intersection pressure p o0, fuel tank downstream intersection pressure p f0;
(7) Offered target mixture ratio data r1, if current mixing ratio r0 is less than target mix ratio r1, performs step (8), otherwise performs step (11);
(8) arranging oxidizer tank downstream intersection pressure p o is independent variable, and calling that propulsion system simulation computation model solves with po is the system mixture ratio rc of independent variable;
(9) Offered target function J (po)=| rc-r1|, uses single argument optimizing algorithm to solve the optimal solution po1 making J (po)=0 based on step (8);
(10) oxidizer tank goal pressure ptoA, ptoB and fuel tank goal pressure ptf1 ', ptf2 ' is exported, wherein oxidizer tank goal pressure ptoA=pto1 '+(po1-po0), ptoB=pto2 '+(po1-po0);
(11) arranging fuel tank downstream intersection pressure p f is independent variable, and calling that propulsion system simulation computation model solves with pf is the system mixture ratio rc of independent variable;
(12) Offered target function J (pf)=| rc-r1|, uses single argument optimizing algorithm to solve the optimal solution pf1 making J (pf)=0 based on step (11);
(13) oxidizer tank goal pressure pto1 ', pto2 ' and fuel tank goal pressure ptfA, ptfB is exported, wherein fuel tank goal pressure ptfA=ptf1 '+(pf1-pf0), ptfB=ptf2 '+(pf1-pf0).
In said method, set up the Simulation Calculation of satellite bipropellant propulsion system and the correlation computations of carrying out, see simulator system article (" numerical simulation of satellite propulsion system static response " [meeting paper] Su Longfei, Pan Hailin, Liang Junqiang, Zhang Bing, 2005-China cosmonautics meeting first Annual Conference).
The principle of the above-mentioned method of calculating of the present invention is as follows:
Controlled the pressure of every tank in tank structure in parallel by gas bypassing, and tank pressure determines the flow that propellant discharged by this tank, thus control the discharge of tank in parallel balance.Such as by improving the pressure of tank MON-A, just can improve the flow of the oxidizer MON-1 that MON-A tank is discharged, thus control the discharge of tank in parallel balance.But for bipropellant propulsion system, while the discharge of adjustment tank balance in parallel, also should be noted that and can not have influence on system mixture ratio index, the pressure that such as only can not increase tank MON-A controls the discharge of tank in parallel balance, because the total flow of oxidizer MON-1 can be increased like this, thus influential system mixture ratio departs from rated condition, therefore tank MMH-A and tank MMH-B must be increased certain pressure separately simultaneously, just can reach and both regulate tank in parallel to balance discharge, again the effect of not influential system mixture ratio.
The method of calculating of active adjustment of the present invention tank balance in parallel discharge can realize following functions:
1, accurately residual propellant is measured.As shown in Figure 1, to measure propellant tank MON-A, confirm that normally closed electric blasting valve 14 detonates before measuring, latching valve LV2, LV3, LV5 and LV6 are in closed condition, latching valve LV1 and LV4 is in opening, then opening latching valve LV5 makes the high pressure gas in gas cylinder be filled with air-capacitor 13, closes latching valve LV5, open latching valve LV6 immediately by the gas inject propellant tank MON-A of air-capacitor 13 li after stable.The pressure change of air-capacitor 13 and propellant tank MON-A before and after being injected by pressure sensor 2 collection, namely by accurately calculating the residual propellant in tank MON-A based on the surplus measurement model of the equation of gas state.The method measuring the residual propellant in other propellant tank 8 is similar.
2, ACTIVE CONTROL tank balance in parallel discharge.According to accurately measuring the tank residual propellant amount obtained, the balance emission behaviour of tank in parallel can be calculated.The pressure and temperature data of residual propellant amount and current system are brought in corresponding tank balance discharge realistic model in parallel, the pressure reduction target that propellant tank of the same race (MON-A and MON-B, MMH-A and MMH-B) needs adjustment can be obtained.To adjust the parallel connection balance discharge index of propellant tank MON-A and MON-B, according to result of calculation, if desired propellant tank MON-A pressure is improved, first confirm that normally closed electric blasting valve 14 detonates, latching valve LV2, LV3, LV5 and LV6 is in closed condition, latching valve LV1 and LV4 is in opening, then opening latching valve LV5 makes the high pressure gas in gas cylinder be filled with air-capacitor 13, latching valve LV5 is closed after stable, open latching valve LV6 immediately by the gas inject propellant tank MON-A of air-capacitor 13 li, the closedown opportunity of latching valve LV6 is determined according to the pressure changing of propellant tank MON-A, the pressure reduction of propellant tank MON-A and MON-B is made to reach expected value.Other adjustment situation is similar.
3, active control system mixture ratio.According to accurately measuring the tank residual propellant amount obtained, the mixture ratio of system can be calculated, and the constituent element ratio of residual propellant.The pressure and temperature data of residual propellant amount and current system be brought in system mixture ratio realistic model, the propellant tank (MON-A, MON-B and MMH-A, MMH-B) that can obtain 2 kinds of constituent elements needs the pressure amplitude of adjustment.Such as, according to result of calculation, if desired system mixture ratio is improved, then need the pressure improving propellant tank MON-A and MON-B, first confirm that normally closed electric blasting valve 14 detonates, latching valve LV2, LV3, LV5 and LV6 is in closed condition, latching valve LV1 and LV4 is in opening, then opening latching valve LV5 makes the high pressure gas in gas cylinder be filled with air-capacitor 13, latching valve LV5 is closed after stable, open latching valve LV6 immediately by the gas inject propellant tank MON-A of air-capacitor 13 li, the closedown opportunity of latching valve LV6 is determined according to the pressure changing of propellant tank MON-A, the pressure of propellant tank MON-A is made to reach expected value.Close latching valve LV1 and LV4 afterwards, opened self-locking valve LV2 and LV3, opening latching valve LV5 again makes the high pressure gas in gas cylinder be filled with air-capacitor 13, latching valve LV5 is closed after stable, open latching valve LV6 immediately by the gas inject propellant tank MON-B of air-capacitor 13 li, determine the closedown opportunity of latching valve LV6 according to the pressure changing of propellant tank MON-B, make the pressure of propellant tank MON-B also reach expected value.The operation of reduction system mixture ratio is the pressure improving propellant tank MMH-A and MMH-B, and operating process is similar.
4, as the function backup of machinery decompression branch road.If machinery decompression branch road (pressure reducer 4 and check valve 5 place pipeline) lost efficacy, gas bypassing 11 can be utilized to complete the function of machinery decompression branch road.To control the pressure of propellant tank MON-A and MON-B, first confirm that normally closed electric blasting valve 14 detonates, latching valve LV5 is placed in closed condition, latching valve LV1, LV2, LV3, LV4 and LV6 are placed in opening, then the switch by controlling latching valve LV5 controls gas and is injected into propellant tank 8 from gas cylinder 1, and maintains the pressure stability of propellant tank 8.In addition, the switch controlling latching valve LV6 also can realize above-mentioned functions.The method controlling the pressure of propellant tank MMH-A and MMH-B is similar.
Through ground test, the present invention just within tank parallel-balance emission norm controlling to 0.8%, by within mixture ratio deviation control to 0.8%, can be equivalent to the propellant saving 5% ~ 6% simultaneously, for GEO track 15 years term satellite, be equivalent to 3 ~ 4 year life-span.
The above; be only the detailed description of the invention of the best of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.
The content be not described in detail in specification sheets of the present invention belongs to the known technology of professional and technical personnel in the field.
Claims (4)
1. the method for active adjustment satellite bipropellant propulsion system tank balance in parallel discharge, is characterized in that comprising the steps:
(1) Simulation Calculation of satellite bipropellant propulsion system is set up, setting gas cylinder and tank initial pressure and temperature, and the quality of propellant in tank, wherein two oxidizer tank initial pressures are designated as pto1, pto2, and two fuel tank initial pressures are designated as ptf1, ptf2;
(2) arranging two oxidizer tank pressure reduction dpo in satellite bipropellant propulsion system is independent variable, uses propulsion system simulation computation model to solve with dpo to be the oxidizer tank balance discharge of independent variable to compare yc
1;
(3) oxidizer tank emissions object value yo in parallel is set, and Offered target function J (dpo)=| yc
1-yo|, uses single argument optimizing algorithm to solve the optimal solution dpo1 making J (dpo)=0 based on step (2);
(4) arranging two fuel tank pressure reduction dpf in satellite bipropellant propulsion system is independent variable, uses propulsion system simulation computation model to solve with dpf to be the fuel tank balance discharge of independent variable to compare yc
2;
(5) fuel tank emissions object value yf in parallel is set, and Offered target function J (dpf)=| yc
2-yf|, uses single argument optimizing algorithm to solve the optimal solution dpf1 making J (dpf)=0 based on step (4);
(6) initial pressure and the temperature of gas cylinder and tank are again set in propulsion system simulation computation model, and the quality of propellant in tank, wherein the initial pressure of two oxidizer tanks is designated as pto1 ', pto2 ', the initial pressure of two fuel tanks is designated as ptf1 ', ptf2 ', use the following parameter of propulsion system simulation model solution afterwards: this becomes the mixture ratio r0 of rail, oxidizer tank downstream intersection pressure p o0, fuel tank downstream intersection pressure p f0;
The initial pressure pto1 ' of two oxidizer tanks, pto2 ' obtain by the following method:
If the initial pressure of tank 1 is pto1 in step (1) two oxidizer tank, the initial pressure of tank 2 is pto2, and pto1<pto2, then in step (6), the initial pressure pto1 ' of tank 1 is still pto1, and the initial pressure pto2 ' of tank 2 is pto1+dpo1; Otherwise pto1 ' is pto2+dpo1, pto2 ' be pto2;
The initial pressure ptf1 ' of two fuel tanks, ptf2 ' obtain by the following method:
If the initial pressure of tank 1 is ptf1 in step (1) two fuel tank, the initial pressure of tank 2 is ptf2, and ptf1<ptf2, then in step (6), the initial pressure ptf1 ' of tank 1 is still ptf1, the initial pressure ptf2 ' of tank 2 is ptf1+dpf1, otherwise ptf1 ' is ptf2+dpf1, ptf2 ' be ptf2;
(7) Offered target mixture ratio data r1, if current mixing ratio r0 is less than target mix ratio r1, performs step (8), otherwise performs step (11);
(8) arranging oxidizer tank downstream intersection pressure p o is independent variable, and calling that propulsion system simulation computation model solves with po is the system mixture ratio rc of independent variable;
(9) Offered target function J (po)=| rc-r1|, uses single argument optimizing algorithm to solve the optimal solution po1 making J (po)=0 based on step (8);
(10) oxidizer tank goal pressure ptoA, ptoB and fuel tank goal pressure ptf1 ', ptf2 ' is exported, wherein oxidizer tank goal pressure ptoA=pto1 '+(po1-po0), ptoB=pto2 '+(po1-po0);
(11) arranging fuel tank downstream intersection pressure p f is independent variable, and calling that propulsion system simulation computation model solves with pf is the system mixture ratio rc of independent variable;
(12) Offered target function J (pf)=| rc-r1|, uses single argument optimizing algorithm to solve the optimal solution pf1 making J (pf)=0 based on step (11);
(13) oxidizer tank goal pressure pto1 ', pto2 ' and fuel tank goal pressure ptfA, ptfB is exported, wherein fuel tank goal pressure ptfA=ptf1 '+(pf1-pf0), ptfB=ptf2 '+(pf1-pf0).
2. the method for active adjustment satellite bipropellant propulsion system according to claim 1 tank balance in parallel discharge, it is characterized in that: described satellite bipropellant propulsion system comprises gas cylinder (1), pressure sensor (2), add valve (3), pressure reducer (4), check valve (5), often open electric blasting valve (6), propellant tank (8), precise tracking (9), appearance control thruster (10) and gas bypassing (11), wherein: propellant tank (8) comprises two oxidizer tank MON-A, MON-B, two fuel tank MMH-A, MMH-B, connect with gas bypassing (11) between gas cylinder (1) and every constituent element propellant tank (8), described gas bypassing (11) is formed by connecting by 2 latching valves (7) and 1 air-capacitor (13), air-capacitor (13) is between 2 latching valves (7), add valve (3) and be arranged on gas bypassing (11) upstream.
3. the method for active adjustment satellite bipropellant propulsion system according to claim 2 tank balance in parallel discharge, it is characterized in that: described gas bypassing (11) two ends increase by first and often open electric blasting valve (12) or normally closed electric blasting valve (14), play fault isolation effect.
4. the method for active adjustment satellite bipropellant propulsion system according to claim 2 tank balance in parallel discharge, it is characterized in that: arrange second between 2 gas bypassings (11) and often open electric blasting valve (15), to be met in upstream by gas bypassing (11) to avoid the propellant steam of 2 kinds of constituent elements and blast.
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| CN104034481B (en) * | 2014-05-07 | 2015-07-01 | 北京空间飞行器总体设计部 | Tank-distributively arranged spacecraft-used propellant counterweight method |
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