CN103213692A - 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 discharging in parallel, 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 a propellant balance discharge capacity.If the propellant space emission overbalance of two tanks in parallel, then when a propellant emptying tank in after, continuing will be the discharge of the helium in the tank again, makes propellant gas enclosure in the propellant pipeline, and thruster and driving engine can't be worked, the satellite life end.And residual propellant will become slow-witted the weight in the another tank, can't use.For the satellite that carries propellant 3000kg, adding amount is 934kg oxidizer or 566kg fuel in every tank, if the unbalance factor of tank discharging in parallel is 3%, having 28kg oxidizer and 17kg fuel latter stage to satellite life becomes slow-witted heavyly, also wants additive decrementation 45kg propellant that these slow-witted weights (propellants) are delivered to satellite orbit.If the unbalance factor of tank discharging in parallel can be controlled to 1%, integrate and just can save about 60kg propellant.In addition, if tank in parallel discharging overbalance will cause satellite barycenter deflection, attitude is uncontrollable in the time of can causing the orbit maneuver engine igniting when serious.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 to overcome the above-mentioned deficiency of prior art, the method of active adjustment satellite bipropellant propulsion system tank balance discharging in parallel is provided, but this method realizes based on the propulsion system of active adjustment tank balance discharging in parallel, calculate the pressure control target of every tank according to tank balance emissions object in parallel, reach and both regulate tank balance discharging in parallel, do not influence the effect of system's mixture ratio again.
Above-mentioned purpose of the present invention mainly is achieved by following technical solution:
The method of active adjustment satellite bipropellant propulsion system tank balance discharging in parallel comprises the steps:
(1) sets up the Simulation Calculation of satellite bipropellant propulsion system, set gas cylinder and tank initial pressure and temperature, and the quality of the interior propellant of tank, wherein two oxidizer tank initial pressures are designated as pto1, pto2, and two fuel tank initial pressures are designated as ptf1, ptf2;
(2) be provided with that two oxidizer tank pressure reduction dpo are independent variable in the satellite bipropellant propulsion system, use the propulsion system Simulation Calculation to find the solution and compare yc as the oxidizer tank balance discharging of independent variable with dpo
1
(3) oxidizer tank emissions object value in parallel yo is set, and be provided with objective function J (dpo)=| yc
1-yo| uses the single argument optimizing algorithm to find the solution the optimal solution dpo1 that makes J (dpo)=0 based on step (2);
(4) be provided with that two fuel tank pressure reduction dpf are independent variable in the satellite bipropellant propulsion system, use the propulsion system Simulation Calculation to find the solution and compare yc as the fuel tank balance discharging of independent variable with dpf
2
(5) fuel tank emissions object value in parallel yf is set, and be provided with objective function J (dpf)=| yc
2-yf| uses the single argument optimizing algorithm to find the solution the optimal solution dpf1 that makes J (dpf)=0 based on step (4);
(6) initial pressure and the temperature of gas cylinder and tank are set once more in the propulsion system Simulation Calculation, and the quality of the interior propellant of 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 propulsion system realistic model to find the solution following parameter afterwards: this becomes the mixture ratio r0 of rail, the oxidizer tank downstream pressure p o0 of intersection, the fuel tank downstream pressure p f0 of intersection;
(7) target mixture ratio data r1 is set, if current mixture ratio r0 is less than target mixture ratio r1, execution in step (8), otherwise execution in step (11);
(8) the oxidizer tank downstream pressure p o of intersection being set is independent variable, and calling that the propulsion system Simulation Calculation finds the solution with po is the mixture ratio rc of system of independent variable;
(9) be provided with objective function J (po)=| rc-r1|, use the single argument optimizing algorithm to find the solution the optimal solution po1 that makes J (po)=0 based on step (8);
(10) output oxidizer tank goal pressure ptoA, ptoB and fuel tank goal pressure ptf1 ', ptf2 ', oxidizer tank goal pressure ptoA=pto1 '+(po1-po0) wherein, ptoB=pto2 '+(po1-po0);
(11) the fuel tank downstream pressure p f of intersection being set is independent variable, and calling that the propulsion system Simulation Calculation finds the solution with pf is the mixture ratio rc of system of independent variable;
(12) be provided with objective function J (pf)=| rc-r1|, use the single argument optimizing algorithm to find the solution the optimal solution pf1 that makes J (pf)=0 based on step (11);
(13) output oxidizer tank goal pressure pto1 ', pto2 ' and fuel tank goal pressure ptfA, ptfB, fuel tank goal pressure ptfA=ptf1 '+(pf1-pf0) wherein, ptfB=ptf2 '+(pf1-pf0).
In the method for above-mentioned active adjustment satellite bipropellant propulsion system tank balance discharging in parallel, initial pressure pto1 ', the pto2 ' of two oxidizer tanks obtain by the following method in the step (6):
If the initial pressure of tank 1 is pto1 in (1) two oxidizer tank of step, the initial pressure of tank 2 is pto2, and pto1＜pto2, and then the initial pressure pto1 ' of tank 1 still is pto1 in the step (6), and the initial pressure pto2 ' of tank 2 is pto1+dpo1; Otherwise pto1 ' is pto2+dpo1, and pto2 ' is pto2;
Initial pressure ptf1 ', the ptf2 ' of two fuel tanks obtain by the following method:
If the initial pressure of tank 1 is ptf1 in (1) two fuel tank of step, the initial pressure of tank 2 is ptf2, and ptf1＜ptf2, then the initial pressure ptf1 ' of tank 1 still is ptf1 in the step (6), the initial pressure ptf2 ' of tank 2 is ptf1+dpf1, otherwise ptf1 ' is ptf2+dpf1, and ptf2 ' is ptf2.
In the method for above-mentioned active adjustment satellite bipropellant propulsion system tank balance discharging in parallel, the satellite bipropellant propulsion system comprises gas cylinder, pressure sensor, add valve, pressure reducer, check valve, often open electric blasting valve, propellant tank, the rail control engine, appearance control thruster and gas bypassing, wherein: propellant tank comprises two oxidizer tank MON-A, MON-B, two fuel tank MMH-A, MMH-B, between gas cylinder and every constituent element propellant tank, connect with gas bypassing, gas bypassing is formed by connecting by 2 latching valves and 1 air-capacitor, air-capacitor is between 2 latching valves, adds valve and is arranged on the gas bypassing upstream.
In the method for above-mentioned active adjustment satellite bipropellant propulsion system tank balance discharging in parallel, the gas bypassing two ends increase by first and often open electric blasting valve or normally closed electric blasting valve, play the fault isolation effect.
In the method for above-mentioned active adjustment satellite bipropellant propulsion system tank balance discharging in parallel, be provided with second between 2 gas bypassings and often open electric blasting valve, meet in the upstream by gas bypassing with the propellant steam of avoiding 2 kinds of constituent elements and blast.
The present invention compared with prior art has following beneficial effect:
(1) the present invention at first sets up the realistic model of propulsion system, calculate the current mixture ratio r0 of system according to current system state data, then according to tank balance emissions object value in parallel, calculate difference of pressure dpo1 between the oxidizer tank (MON-A and MON-B) and the difference of pressure dpf1 between the fuel tank (MMH-A and MMH-B) by optimizing algorithm, be expected value at last with r0, with dpo1 and dpf1 is initial condition (IC), calculate the goal pressure of every tank by optimizing algorithm, the staff just can utilize gas bypassing that tank pressure is adjusted to the goal pressure point, thereby reach the purpose of regulating tank balance discharging in parallel, and do not influence system's mixture ratio;
(2) through ground test, the present invention just tank balance discharge index in parallel controls in 0.8%, simultaneously can be with in the mixture ratio deviation control to 0.8%, be equivalent to save 5%～6% propellant, for 15 year life-span satellite of GEO track, be equivalent to 3～4 year life-span, so the inventive method has prolonged satellite life greatly.
(3) the present invention's tank balance in parallel discharge method is simple, and accurate and effective has stronger practicality and gives birth to.
Description of drawings
But Fig. 1 is the propulsion system structure figure of the present invention's active adjustment tank balance discharging in parallel;
Fig. 2 is the method for calculating diagram of circuit of active adjustment of the present invention tank balance discharging in parallel.
The specific embodiment
The present invention is described in further detail below in conjunction with the drawings and specific embodiments:
But be illustrated in figure 1 as the propulsion system structure figure of the present invention's active adjustment tank balance discharging 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, rail control engine 9, appearance control thruster 10, gas bypassing 11, first often opens electric blasting valve 12, the first normally closed electric blasting valve 14 and second is often opened electric blasting valve 15, wherein: between gas cylinder 1 and every constituent element propellant tank 8, connect with gas bypassing 11, gas bypassing 11 is formed by connecting by two latching valves 7 and an air-capacitor 13, and air-capacitor 13 is between two latching valves 7.Propellant tank 8 comprises two oxidizer tank MON-A, MON-B, two fuel tank MMH-A, MMH-B.
For improving the reliability of gas bypassing 11, increase by first at gas bypassing 11 two ends and often open electric blasting valve 12 or normally closed electric blasting valve 14, play the fault isolation effect.
For meeting in the upstream by gas bypassing 11, the propellant steam of avoiding 2 kinds of constituent elements blasts, between 2 gas bypassings 11, be provided with second and often open electric blasting valve 15, before using gases bypass 11, open quick-fried this and 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 every kind of constituent element by gas bypassing 11 respectively.
In order to test gas bypassing 11 performances on the ground, setting adds valve 3 in gas bypassing 11 upstreams.
In the propulsion system of Fig. 1, gas cylinder 1 is used to store high pressure gas (normally helium); Propellant tank 8 is used to store propellant; Be connected with check valve 5 by pressure reducer 4 between gas cylinder 1 and the propellant tank 8, and dispose necessary pressure sensor 2, add valve 3, often drive electric blasting valve 6 and latching valve 7; Pressure reducer 4 is used for high pressure gas to gas cylinder 1 and reduces pressure and inject propellant tank 8, to keep the pressure stability of propellant tank 8; Check valve 5 is used to prevent that the propellant tank 8 interior propellant steam back diffusion of different constituent elements from arriving the joint in pressure reducer downstream, avoids the danger of blasting; Pressure sensor 2 is used to measure the pressure of gas cylinder 1 and propellant tank 8; Add valve 3 and be used for terrestrial operation, give gas cylinder 1 and propellant tank 8 filling or discharging propellant and gas; Often open electric blasting valve 6 and be used to cut off connection between propellant tank 8 and the upstream steam line, cut-out opportunity is when the rail control engine is finished the work back or upstream steam line et out of order; Latching valve 7 is used for the break-make of control gaseous or propellant pipeline.
But the present invention at first sets up the realistic model of the propulsion system of above-mentioned active adjustment tank balance discharging in parallel, calculate the current mixture ratio r0 of system according to current system state data, then according to tank balance emissions object value in parallel, calculate difference of pressure dpo1 between the oxidizer tank (MON-A and MON-B) and the difference of pressure dpf1 between the fuel tank (MMH-A and MMH-B) by optimizing algorithm, be expected value at last with r0, with dpo1 and dpf1 is initial condition (IC), calculates the goal pressure of every tank by optimizing algorithm.The staff just can utilize gas bypassing that tank pressure is adjusted to the goal pressure point, thereby reaches the purpose of regulating tank balance discharging in parallel.
Be illustrated in figure 2 as the method for calculating diagram of circuit of active adjustment of the present invention tank balance discharging in parallel, specific implementation method of the present invention is as follows:
(1) sets up the Simulation Calculation of satellite bipropellant propulsion system, set gas cylinder and tank initial pressure and temperature, and the quality of the interior propellant of tank, wherein two oxidizer tank initial pressures are designated as pto1, pto2, and two fuel tank initial pressures are designated as ptf1, ptf2;
(2) be provided with that two oxidizer tank pressure reduction dpo are independent variable in the satellite bipropellant propulsion system, use the propulsion system Simulation Calculation to find the solution and compare yc1 as the oxidizer tank balance discharging of independent variable with dpo;
(3) oxidizer tank emissions object value in parallel yo is set, and be provided with objective function J (dpo)=| yc
1-yo| uses the single argument optimizing algorithm to find the solution the optimal solution dpo1 that makes J (dpo)=0 based on step (2);
(4) be provided with that two fuel tank pressure reduction dpf are independent variable in the satellite bipropellant propulsion system, use the propulsion system Simulation Calculation to find the solution and compare yc2 as the fuel tank balance discharging of independent variable with dpf;
(5) fuel tank emissions object value in parallel yf is set, and be provided with objective function J (dpf)=| yc
2-yf| uses the single argument optimizing algorithm to find the solution the optimal solution dpf1 that makes J (dpf)=0 based on step (4);
(6) initial pressure and the temperature of gas cylinder and tank are set once more in the propulsion system Simulation Calculation, and the quality of the interior propellant of tank, wherein the initial pressure of two oxidizer tanks is designated as pto1 ', pto2 ', initial pressure pto1 ', the pto2 ' of two oxidizer tanks is benchmark with a less tank of pressure wherein, 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 (1) two oxidizer tank of step, the initial pressure of tank 2 is pto2, and pto1＜pto2, and then the initial pressure pto1 ' of tank 1 still is pto1 in the step (6), and the initial pressure pto2 ' of tank 2 is pto1+dpo1; If pto2＜pto1, then the initial pressure pto2 ' of tank 2 still is pto2 in the step (6), 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 is benchmark with a less tank of pressure wherein, 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 (1) two fuel tank of step, the initial pressure of tank 2 is ptf2, and ptf1＜ptf2, and then the initial pressure ptf1 ' of tank 1 still is ptf1 in the step (6), and the initial pressure ptf2 ' of tank 2 is ptf1+dpf1.If ptf2＜ptf1, then the initial pressure ptf2 ' of tank 2 still is ptf2 in the step (6), and the initial pressure ptf1 ' of tank 1 is ptf2+dpf1.
Use the propulsion system realistic model to find the solution following parameter afterwards: this becomes the mixture ratio r0 of rail, the oxidizer tank downstream pressure p o0 of intersection, the fuel tank downstream pressure p f0 of intersection;
(7) target mixture ratio data r1 is set, if current mixture ratio r0 is less than target mixture ratio r1, execution in step (8), otherwise execution in step (11);
(8) the oxidizer tank downstream pressure p o of intersection being set is independent variable, and calling that the propulsion system Simulation Calculation finds the solution with po is the mixture ratio rc of system of independent variable;
(9) be provided with objective function J (po)=| rc-r1|, use the single argument optimizing algorithm to find the solution the optimal solution po1 that makes J (po)=0 based on step (8);
(10) output oxidizer tank goal pressure ptoA, ptoB and fuel tank goal pressure ptf1 ', ptf2 ', oxidizer tank goal pressure ptoA=pto1 '+(po1-po0) wherein, ptoB=pto2 '+(po1-po0);
(11) the fuel tank downstream pressure p f of intersection being set is independent variable, and calling that the propulsion system Simulation Calculation finds the solution with pf is the mixture ratio rc of system of independent variable;
(12) be provided with objective function J (pf)=| rc-r1|, use the single argument optimizing algorithm to find the solution the optimal solution pf1 that makes J (pf)=0 based on step (11);
(13) output oxidizer tank goal pressure pto1 ', pto2 ' and fuel tank goal pressure ptfA, ptfB, fuel tank goal pressure ptfA=ptf1 '+(pf1-pf0) wherein, ptfB=ptf2 '+(pf1-pf0).
In the said method, set up the Simulation Calculation of satellite bipropellant propulsion system and the correlation computations of carrying out, referring to simulator system article (" numerical simulation of satellite propulsion system static response " [meeting paper] Su Longfei, Pan Hailin, Liang Junqiang, Zhang Bing, the academic annual meeting of the 2005-China cosmonautics meeting first).
The principle of aforementioned calculation method of the present invention is as follows:
Control the pressure of every tank in the tank structure in parallel by gas bypassing, and tank pressure has determined this tank to discharge the flow of propellant, thereby controlled tank balance discharging in parallel.For example, just can improve the flow of the oxidizer MON-1 of MON-A tank discharge, thereby control tank balance discharging in parallel by improving the pressure of tank MON-A.But for bipropellant propulsion system, when regulating tank balance discharging in parallel, also should be noted that and to have influence on system's mixture ratio index, the pressure that for example can not only increase tank MON-A is controlled tank balance discharging in parallel, because can increase the total flow of oxidizer MON-1 like this, thereby the system mixture ratio of influence departs from rated condition, therefore must simultaneously tank MMH-A and tank MMH-B be increased certain pressure separately, just can reach and both regulate tank balance discharging in parallel, not influence the effect of system's mixture ratio again.
The method of calculating of active adjustment of the present invention tank balance discharging in parallel can be realized following function:
1, accurately measures residual propellant.As shown in Figure 1, to measure propellant tank MON-A is example, confirm that before measurement normally closed electric blasting valve 14 has detonated, latching valve LV2, LV3, LV5 and LV6 are in closed condition, latching valve LV1 and LV4 are in opening, open latching valve LV5 then and make the high pressure gas in the gas cylinder charge into air-capacitor 13, close latching valve LV5 after waiting to stablize, open the gas injection propellant tank MON-A of latching valve LV6 immediately 13 li of air-capacitors.Gather the pressure that injects front and back air-capacitor 13 and propellant tank MON-A by pressure sensor 2 and change, can accurately calculate the residual propellant among the tank MON-A by surplus measurement model based on the equation of gas state.The method of measuring the residual propellant in other propellant tank 8 is similar.
2, ACTIVE CONTROL tank balance discharging in parallel.According to the tank residual propellant amount that accurately measures, can calculate the balance emission behaviour of tank in parallel.The pressure and temperature data of residual propellant amount and current system are brought in the corresponding tank balance discharging realistic model in parallel, can obtain the pressure reduction target that propellant tank of the same race (MON-A and MON-B, MMH-A and MMH-B) needs adjustment.Balance discharge index in parallel with adjustment propellant tank MON-A and MON-B is an example, according to result of calculation, if need to improve propellant tank MON-A pressure, confirm that at first normally closed electric blasting valve 14 has detonated, latching valve LV2, LV3, LV5 and LV6 are in closed condition, latching valve LV1 and LV4 are in opening, opening latching valve LV5 then makes the high pressure gas in the gas cylinder charge into air-capacitor 13, close latching valve LV5 after waiting to stablize, open the gas injection propellant tank MON-A of latching valve LV6 immediately with 13 li of air-capacitors, pressure changing according to propellant tank MON-A determines closing opportunity of latching valve LV6, makes the pressure reduction of propellant tank MON-A and MON-B reach expected value.Other adjustment situation is similar.
3, ACTIVE CONTROL system mixture ratio.According to the tank residual propellant amount that accurately measures, can calculate the mixture ratio of system, and the constituent element of residual propellant ratio.The pressure and temperature data of residual propellant amount and current system are brought in system's mixture ratio realistic model, and 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.For example, according to result of calculation, if need raising system mixture ratio, then need to improve the pressure of propellant tank MON-A and MON-B, confirm that at first normally closed electric blasting valve 14 has detonated, latching valve LV2, LV3, LV5 and LV6 are in closed condition, latching valve LV1 and LV4 are in opening, opening latching valve LV5 then makes the high pressure gas in the gas cylinder charge into air-capacitor 13, close latching valve LV5 after waiting to stablize, open latching valve LV6 immediately the gas of 13 li of air-capacitors is injected propellant tank MON-A,, make the pressure of propellant tank MON-A reach expected value according to closing opportunity of the pressure changing decision latching valve LV6 of propellant tank MON-A.Close latching valve LV1 and LV4 afterwards, open latching valve LV2 and LV3, opening latching valve LV5 again makes the high pressure gas in the gas cylinder charge into air-capacitor 13, close latching valve LV5 after waiting to stablize, open the gas injection propellant tank MON-B of latching valve LV6 immediately with 13 li of air-capacitors, pressure changing according to propellant tank MON-B determines closing opportunity of latching valve LV6, makes the pressure of propellant tank MON-B also reach expected value.The operation of reduction system mixture ratio is the pressure that improves propellant tank MMH-A and MMH-B, and operating process is similar.
4, the function as machinery decompression branch road backs up.If machinery decompression branch road (pressure reducer 4 and check valve 5 place pipelines) lost efficacy, can utilize gas bypassing 11 to finish the function of machinery decompression branch road.Pressure with control propellant tank MON-A and MON-B is example, confirm that at first normally closed electric blasting valve 14 has detonated, LV5 places closed condition with latching valve, latching valve LV1, LV2, LV3, LV4 and LV6 place opening, switch by control latching valve LV5 comes control gaseous to be injected into the propellant tank 8 from gas cylinder 1 then, and keeps the pressure stability of propellant tank 8.In addition, the switch of control latching valve LV6 also can be realized above-mentioned functions.The method of the pressure of control propellant tank MMH-A and MMH-B is similar.
Through ground test, the present invention just tank balance discharge index in parallel controls in 0.8%, can be equivalent to save 5%～6% propellant with in the mixture ratio deviation control to 0.8% simultaneously, for 15 year life-span satellite of GEO track, be equivalent to 3～4 year life-span.
The above; only be the specific embodiment of the best of the present invention, but protection scope of the present invention is not limited thereto, anyly is familiar with those skilled in the art in the technical scope that the present invention discloses; the variation that can expect easily or replacement all should be encompassed within protection scope of the present invention.
The content that is not described in detail in the specification sheets of the present invention belongs to this area professional and technical personnel's known technology.
Claims (5)
1. the method for active adjustment satellite bipropellant propulsion system tank balance discharging in parallel is characterized in that comprising the steps:
(1) sets up the Simulation Calculation of satellite bipropellant propulsion system, set gas cylinder and tank initial pressure and temperature, and the quality of the interior propellant of tank, wherein two oxidizer tank initial pressures are designated as pto1, pto2, and two fuel tank initial pressures are designated as ptf1, ptf2;
(2) be provided with that two oxidizer tank pressure reduction dpo are independent variable in the satellite bipropellant propulsion system, use the propulsion system Simulation Calculation to find the solution and compare yc1 as the oxidizer tank balance discharging of independent variable with dpo;
(3) oxidizer tank emissions object value in parallel yo is set, and be provided with objective function J (dpo)=| yc
1-yo| uses the single argument optimizing algorithm to find the solution the optimal solution dpo1 that makes J (dpo)=0 based on step (2);
(4) be provided with that two fuel tank pressure reduction dpf are independent variable in the satellite bipropellant propulsion system, use the propulsion system Simulation Calculation to find the solution and compare yc2 as the fuel tank balance discharging of independent variable with dpf;
(5) fuel tank emissions object value in parallel yf is set, and be provided with objective function J (dpf)=| yc
2-yf| uses the single argument optimizing algorithm to find the solution the optimal solution dpf1 that makes J (dpf)=0 based on step (4);
(6) initial pressure and the temperature of gas cylinder and tank are set once more in the propulsion system Simulation Calculation, and the quality of the interior propellant of 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 propulsion system realistic model to find the solution following parameter afterwards: this becomes the mixture ratio r0 of rail, the oxidizer tank downstream pressure p o0 of intersection, the fuel tank downstream pressure p f0 of intersection;
(7) target mixture ratio data r1 is set, if current mixture ratio r0 is less than target mixture ratio r1, execution in step (8), otherwise execution in step (11);
(8) the oxidizer tank downstream pressure p o of intersection being set is independent variable, and calling that the propulsion system Simulation Calculation finds the solution with po is the mixture ratio rc of system of independent variable;
(9) be provided with objective function J (po)=| rc-r1|, use the single argument optimizing algorithm to find the solution the optimal solution po1 that makes J (po)=0 based on step (8);
(10) output oxidizer tank goal pressure ptoA, ptoB and fuel tank goal pressure ptf1 ', ptf2 ', oxidizer tank goal pressure ptoA=pto1 '+(po1-po0) wherein, ptoB=pto2 '+(po1-po0);
(11) the fuel tank downstream pressure p f of intersection being set is independent variable, and calling that the propulsion system Simulation Calculation finds the solution with pf is the mixture ratio rc of system of independent variable;
(12) be provided with objective function J (pf)=| rc-r1|, use the single argument optimizing algorithm to find the solution the optimal solution pf1 that makes J (pf)=0 based on step (11);
(13) output oxidizer tank goal pressure pto1 ', pto2 ' and fuel tank goal pressure ptfA, ptfB, fuel tank goal pressure ptfA=ptf1 '+(pf1-pf0) wherein, ptfB=ptf2 '+(pf1-pf0).
2. the method for active adjustment satellite bipropellant propulsion system according to claim 1 tank balance discharging in parallel, it is characterized in that: initial pressure pto1 ', the pto2 ' of two oxidizer tanks obtain by the following method in the described step (6):
If the initial pressure of tank 1 is pto1 in (1) two oxidizer tank of step, the initial pressure of tank 2 is pto2, and pto1＜pto2, and then the initial pressure pto1 ' of tank 1 still is pto1 in the step (6), and the initial pressure pto2 ' of tank 2 is pto1+dpo1; Otherwise pto1 ' is pto2+dpo1, and pto2 ' is pto2;
Initial pressure ptf1 ', the ptf2 ' of two fuel tanks obtain by the following method:
If the initial pressure of tank 1 is ptf1 in (1) two fuel tank of step, the initial pressure of tank 2 is ptf2, and ptf1＜ptf2, then the initial pressure ptf1 ' of tank 1 still is ptf1 in the step (6), the initial pressure ptf2 ' of tank 2 is ptf1+dpf1, otherwise ptf1 ' is ptf2+dpf1, and ptf2 ' is ptf2.
3. the method for active adjustment satellite bipropellant propulsion system according to claim 1 and 2 tank balance discharging in parallel, 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), rail control engine (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, between gas cylinder (1) and every constituent element propellant tank (8), connect with gas bypassing (11), 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), adds valve (3) and is arranged on gas bypassing (11) upstream.
4. the method for active adjustment satellite bipropellant propulsion system according to claim 3 tank balance discharging in parallel, 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 the fault isolation effect.
5. the method for active adjustment satellite bipropellant propulsion system according to claim 3 tank balance discharging in parallel, it is characterized in that: be provided with second between described 2 gas bypassings (11) and often open electric blasting valve (15), meet in the upstream by gas bypassing (11) with the propellant steam of avoiding 2 kinds of constituent elements and blast.
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| CN201310121563.1A CN103213692B (en) | 2013-04-09 | 2013-04-09 | Method of actively adjusting balanced discharging of parallel connection tanks of satellite two component propelling system |
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| CN104034481A (en) * | 2014-05-07 | 2014-09-10 | 北京空间飞行器总体设计部 | Tank-distributively arranged spacecraft-used propellant counterweight method |
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN104401506A (en) * | 2014-10-23 | 2015-03-11 | 上海卫星工程研究所 | Zero-counterweight barycenter deploying method for parallel tiling tank satellite |
| CN106198033A (en) * | 2016-06-23 | 2016-12-07 | 中国空间技术研究院 | A kind of satellite engine/motor specific impulse computational methods in-orbit |
| CN106516167A (en) * | 2016-11-03 | 2017-03-22 | 上海卫星工程研究所 | High precision propellant filling method for high orbit satellite with parallel-connection flat-laid storage tanks |
| CN106660641A (en) * | 2014-06-19 | 2017-05-10 | 空中客车防务和空间公司 | Method for controlling the orbit of a satellite in earth orbit, satellite and system for controlling the orbit of such a satellite |
| CN106768915A (en) * | 2016-11-16 | 2017-05-31 | 上海卫星工程研究所 | The electric blasting valve ground polarity test method of satellite bipropellant propulsion system |
| CN106762224A (en) * | 2016-11-21 | 2017-05-31 | 北京控制工程研究所 | A kind of Large Copacity half manages formula surface tension propellant tank balance charging method in parallel |
| CN107701330A (en) * | 2017-09-14 | 2018-02-16 | 北京控制工程研究所 | A kind of system mixing ratio Active Control Method for being not based on gas bypassing |
| CN107776916A (en) * | 2017-09-14 | 2018-03-09 | 北京控制工程研究所 | A kind of method based on the adjustment discharge without gas bypassing propulsion system |
| CN106439494B (en) * | 2016-09-13 | 2018-08-21 | 北京控制工程研究所 | A kind of asymmetric gas path module for dual mode satellite propulsion system |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4609169A (en) * | 1984-08-14 | 1986-09-02 | The United States Of America As Represented By The Secretary Of The Air Force | Propellant tank resupply system |
| US5116000A (en) * | 1989-12-18 | 1992-05-26 | Aerospatiale Societe Nationale Industrielle | Adaptable system for storing liquid under pressure and spacecraft propellant storage applications thereof |
| US5251852A (en) * | 1991-09-06 | 1993-10-12 | General Electric Company | Thermal fuel transfer and tank isolation to reduce unusable fuel |
| US5263666A (en) * | 1988-12-16 | 1993-11-23 | General Electric Co. | Spacecraft with increased stationkeeping fuel load |
| CN1114624A (en) * | 1993-12-23 | 1996-01-10 | 休斯航空公司 | Integrated storage and transfer system and method for spacecraft propulsion systems |
| WO2012042400A1 (en) * | 2010-09-30 | 2012-04-05 | Astrium Limited | System for the recovery, storage and utilisation of atmospheric gas for use as a vehicle propellant |
-
2013
- 2013-04-09 CN CN201310121563.1A patent/CN103213692B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4609169A (en) * | 1984-08-14 | 1986-09-02 | The United States Of America As Represented By The Secretary Of The Air Force | Propellant tank resupply system |
| US5263666A (en) * | 1988-12-16 | 1993-11-23 | General Electric Co. | Spacecraft with increased stationkeeping fuel load |
| US5116000A (en) * | 1989-12-18 | 1992-05-26 | Aerospatiale Societe Nationale Industrielle | Adaptable system for storing liquid under pressure and spacecraft propellant storage applications thereof |
| US5251852A (en) * | 1991-09-06 | 1993-10-12 | General Electric Company | Thermal fuel transfer and tank isolation to reduce unusable fuel |
| CN1114624A (en) * | 1993-12-23 | 1996-01-10 | 休斯航空公司 | Integrated storage and transfer system and method for spacecraft propulsion systems |
| WO2012042400A1 (en) * | 2010-09-30 | 2012-04-05 | Astrium Limited | System for the recovery, storage and utilisation of atmospheric gas for use as a vehicle propellant |
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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 |
| CN104034481A (en) * | 2014-05-07 | 2014-09-10 | 北京空间飞行器总体设计部 | Tank-distributively arranged spacecraft-used propellant counterweight method |
| CN106660641A (en) * | 2014-06-19 | 2017-05-10 | 空中客车防务和空间公司 | Method for controlling the orbit of a satellite in earth orbit, satellite and system for controlling the orbit of such a satellite |
| CN104260901A (en) * | 2014-09-11 | 2015-01-07 | 上海卫星工程研究所 | Modular two-component propulsion system |
| CN104260901B (en) * | 2014-09-11 | 2016-08-24 | 上海卫星工程研究所 | Modular bipropellant propulsion system |
| CN104401506A (en) * | 2014-10-23 | 2015-03-11 | 上海卫星工程研究所 | Zero-counterweight barycenter deploying method for parallel tiling tank satellite |
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| CN106439494B (en) * | 2016-09-13 | 2018-08-21 | 北京控制工程研究所 | A kind of asymmetric gas path module for dual mode satellite propulsion system |
| CN106516167A (en) * | 2016-11-03 | 2017-03-22 | 上海卫星工程研究所 | High precision propellant filling method for high orbit satellite with parallel-connection flat-laid storage tanks |
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| CN107701330A (en) * | 2017-09-14 | 2018-02-16 | 北京控制工程研究所 | A kind of system mixing ratio Active Control Method for being not based on gas bypassing |
| CN107776916A (en) * | 2017-09-14 | 2018-03-09 | 北京控制工程研究所 | A kind of method based on the adjustment discharge without gas bypassing propulsion system |
| CN107776916B (en) * | 2017-09-14 | 2019-06-18 | 北京控制工程研究所 | A method of the adjustment discharge based on no gas bypassing propulsion system |
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| CN109533397A (en) * | 2018-11-02 | 2019-03-29 | 中国空间技术研究院 | A kind of electric propulsion electronics depressurized system design method |
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| CN109932165A (en) * | 2019-03-05 | 2019-06-25 | 北京控制工程研究所 | A kind of the restricting element debugging verification system and method for long-life gas circuit |
| CN110525694A (en) * | 2019-07-23 | 2019-12-03 | 中国空间技术研究院 | A kind of propulsion system mixture ratio control method considering tank pressure gap in parallel |
| CN110525693A (en) * | 2019-07-23 | 2019-12-03 | 中国空间技术研究院 | A kind of parallel connection tank propulsion system overall balance emissions adjustment method |
| CN113148235A (en) * | 2020-01-09 | 2021-07-23 | 中国空间技术研究院 | Method for adjusting transverse mass center of satellite of parallel storage box |
| CN111452998A (en) * | 2020-04-16 | 2020-07-28 | 北京控制工程研究所 | Water-based propulsion system optimal efficiency determination method based on multi-target optimization |
| CN111426364A (en) * | 2020-04-16 | 2020-07-17 | 北京控制工程研究所 | Propellant residual quantity measuring method based on multi-source data fusion |
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