CN104792233A - Supercharging device and supercharging method for low-temperature rocket ground redundancy - Google Patents
Supercharging device and supercharging method for low-temperature rocket ground redundancy Download PDFInfo
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- CN104792233A CN104792233A CN201510210444.2A CN201510210444A CN104792233A CN 104792233 A CN104792233 A CN 104792233A CN 201510210444 A CN201510210444 A CN 201510210444A CN 104792233 A CN104792233 A CN 104792233A
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Abstract
The invention relates to a supercharging device and a supercharging method for low-temperature rocket ground redundancy. The device comprises pilot-operated type two-bit two-way normally closed solenoid valves, a two-bit three-way solenoid valve, manual stop valves and restriction orifices arranged on a low-temperature propellent supercharging gas source gas inlet pipeline; the second pilot-operated type two-bit two-way normally closed solenoid valve and the third pilot-operated type two-bit two-way normally closed solenoid valve are started, and tank pressurization is rapidly conducted by gas which passes through the second restriction orifice and the third restriction orifice. According to the supercharging device for the low-temperature rocket ground redundancy, the single-point problem of a low-temperature propellent rocket ground electric supercharging gas circuit is solved, it is guaranteed that a target requirement of narrow window launching is met, four independent solenoid valves are adopted to achieve a series-parallel connection redundant backup, by means of the restriction orifice with different hole diameters, rapid and high-precision supercharging before launching is guaranteed, and the reliability of the rocket launching is improved.
Description
Technical field
The present invention relates to a kind of cryogenic rocket launch control unit, specifically, relate to a kind of cryogenic rocket ground redundancy supercharging device.
Background technology
Both at home and abroad for Cryogenic Propellant Rocket provides ground supercharge usually to use single magnetic valve supercharging gas circuit air feed, general need continue to-4min before transmitting, and be that single-point is irredundant, reliability is relatively low, the progress of launching flow process directly can be had influence on once break down, even cause the termination of launching flow process, the target call that in task, " narrow window " is launched cannot be realized.Therefore a kind of ground redundancy boosting method must be studied, the fault that may occur during reply ground supercharging.
Summary of the invention
For above-mentioned deficiency of the prior art, the invention provides a kind of solving cannot the cryogenic rocket ground redundancy boosting method of supercharging and the more than difficult problem of supercharging.
The technical solution used in the present invention is:
A kind of cryogenic rocket ground redundancy supercharging device,
Comprise the pilot-operated type 2/2-way normally closed solenoid valve, two-bit triplet magnetic valve, hand stop valve and the restricting orifice that are arranged on cryogenic propellant pressurization air source air inlet pipeline;
The input of described cryogenic propellant pressurization air source air inlet pipeline and first throttle orifice plate parallel with one another, the input of the second restricting orifice, the input of the 3rd restricting orifice are connected;
The output of first throttle orifice plate is connected with the input of the first hand stop valve;
The output of the second restricting orifice is connected with the input of the 3rd pilot-operated type 2/2-way normally closed solenoid valve;
The output of the 3rd restricting orifice is connected with the input of the first pilot-operated type 2/2-way normally closed solenoid valve with the second pilot-operated type 2/2-way normally closed solenoid valve;
The output of the first pilot-operated type 2/2-way normally closed solenoid valve, the output of the second pilot-operated type 2/2-way normally closed solenoid valve, the output of the 3rd pilot-operated type 2/2-way normally closed solenoid valve are connected with the input of pilot-operated type two-bit triplet magnetic valve with the output of the first hand stop valve;
First output of two-bit triplet magnetic valve is connected with pressure piping output;
Pressure piping output is connected with the input of the second hand stop valve;
Output and the pressure piping of the second hand stop valve end of exitting is connected;
Second output and the pressure piping of two-bit triplet magnetic valve end of exitting is connected.
Described restricting orifice X1 aperture is 2.5-3.4 millimeter, to be 2.5-3.0 millimeter and X3 aperture be in X2 aperture: 0.7-1.5 millimeter.
A kind of cryogenic rocket ground redundancy boosting method, comprises the steps:
At test phase:
After air-source inflow, open the first hand stop valve;
When pressure piping needs venting, open the second hand stop valve venting;
In the execution launch mission stage:
Start the second pilot-operated type 2/2-way normally closed solenoid valve and the 3rd pilot-operated type 2/2-way normally closed solenoid valve simultaneously, gas by two restricting orifice second restricting orifices and the 3rd restricting orifice fast by tank supercharging;
The 3rd pilot-operated type 2/2-way normally closed solenoid valve is disconnected after tank force value reaches the first setting supercharging value;
The second pilot-operated type 2/2-way normally closed solenoid valve is disconnected after at a slow speed tank being pressurized to the second setting value;
When startup second pilot-operated type 2/2-way normally closed solenoid valve or the 3rd pilot-operated type 2/2-way normally closed solenoid valve occur opening fault; Starting magnetic valve first pilot-operated type 2/2-way normally closed solenoid valve is that tank continues supercharging;
When tank reaches the second setting supercharging value, second pilot-operated type 2/2-way normally closed solenoid valve or the 3rd pilot-operated type 2/2-way normally closed solenoid valve occur cannot closing fault time, start the beneficial effect of pilot-operated type two-bit triplet solenoid valve shuts supercharging gas circuit hinge structure of the present invention:
Cryogenic rocket ground of the present invention redundancy supercharging device, solve the single-point problem of Cryogenic Propellant Rocket ground electric supercharging gas circuit, ensure that the realization of the target call that " narrow window " is launched, adopt 4 independently magnetic valve realize connection in series-parallel redundancy backup, by arranging the restricting orifice of different pore size, ensure the supercharging of penetrating front quick high accuracy, improve the reliability of rocket launching.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of cryogenic rocket ground of the present invention redundancy supercharging device.
Critical piece symbol description in accompanying drawing:
In figure:
1, first throttle orifice plate
2, the second restricting orifice
3, the 3rd restricting orifice
4, the first hand stop valve
5, the 3rd pilot-operated type 2/2-way normally closed solenoid valve
6, the first pilot-operated type 2/2-way normally closed solenoid valve
7, the second pilot-operated type 2/2-way normally closed solenoid valve
8, pilot-operated type two-bit triplet magnetic valve
9, the second hand stop valve.
Detailed description of the invention
Referring to drawings and Examples, the present invention will be described in detail:
Accompanying drawing 1 is known, a kind of cryogenic rocket ground redundancy supercharging device,
Comprise the pilot-operated type 2/2-way normally closed solenoid valve, two-bit triplet magnetic valve, hand stop valve and the restricting orifice that are arranged on cryogenic propellant pressurization air source air inlet pipeline;
The input of described cryogenic propellant pressurization air source air inlet pipeline and first throttle orifice plate 1 parallel with one another, the input of the second restricting orifice 2, the input of the 3rd restricting orifice 3 are connected;
The output of first throttle orifice plate 1 is connected with the input of the first hand stop valve 4;
The output of the second restricting orifice 2 is connected with the input of the 3rd pilot-operated type 2/2-way normally closed solenoid valve 5;
The output of the 3rd restricting orifice 3 is connected with the input of the first pilot-operated type 2/2-way normally closed solenoid valve 6 with the second pilot-operated type 2/2-way normally closed solenoid valve 7;
The output of the first pilot-operated type 2/2-way normally closed solenoid valve 7, the output of the second pilot-operated type 2/2-way normally closed solenoid valve 6, the output of the 3rd pilot-operated type 2/2-way normally closed solenoid valve 5 are connected with the input of pilot-operated type two-bit triplet magnetic valve 8 with the output of the first hand stop valve 4;
First output of two-bit triplet magnetic valve 8 is connected with pressure piping output;
Pressure piping output is connected with the input of the second hand stop valve 9;
Output and the pressure piping of the second hand stop valve 9 end of exitting is connected;
Second output and the pressure piping of pilot-operated type two-bit triplet magnetic valve 8 end of exitting is connected.
Cryogenic rocket ground of the present invention redundancy supercharging device, the first hand stop valve is Non-follow control supercharge; Second hand stop valve is the venting of Non-follow control pressure piping; Magnetic valve is a kind of pilot-operated type 2/2-way normally closed solenoid valve, for controlling electronic supercharge; Magnetic valve 8 is a kind of pilot-operated type two-bit triplet normally open solenoid valves, for controlling to cut off electronic supercharging.
Described plate X1, X2 are different with X3 aperture, realize controlling different pumping rate and precision.
Described restricting orifice X1 aperture is 2.5-3.4 millimeter, X2 aperture is 2.5-3.0 millimeter, can realize the large discharge supercharging to tank of not annotating, and controls pressurization time; X3 aperture is: 0.7-1.5 millimeter, to the low discharge supercharging of tank after filling, can control supercharging precision.
A kind of cryogenic rocket ground redundancy boosting method, comprises the steps:
At test phase:
After air-source inflow, open the first hand stop valve JF1;
For cryogenic rocket tank hand supercharging air feed, the solenoid valves time can be reduced like this, increase the magnetic valve life-span;
When pressure piping needs venting, open the second hand stop valve JF2 and exit;
In the execution launch mission stage:
Start the second pilot-operated type 2/2-way normally closed solenoid valve and the 3rd pilot-operated type 2/2-way normally closed solenoid valve simultaneously, gas by two restricting orifice second restricting orifices and the 3rd restricting orifice fast by tank supercharging; The 3rd pilot-operated type 2/2-way normally closed solenoid valve is disconnected after tank force value reaches the first setting supercharging value; The second pilot-operated type 2/2-way normally closed solenoid valve is disconnected after at a slow speed tank being pressurized to the second setting value; Ensure that pressurization time in turn ensure that supercharging precision.
When startup second pilot-operated type 2/2-way normally closed solenoid valve or the 3rd pilot-operated type 2/2-way normally closed solenoid valve occur opening fault; Starting magnetic valve first pilot-operated type 2/2-way normally closed solenoid valve is that tank continues supercharging;
When tank reaches the second setting supercharging value, the second pilot-operated type 2/2-way normally closed solenoid valve or the 3rd pilot-operated type 2/2-way normally closed solenoid valve occur cannot closing fault time, start pilot-operated type two-bit triplet solenoid valve shuts supercharging gas circuit.
Cryogenic rocket ground of the present invention redundancy supercharging device, solve the single-point problem of Cryogenic Propellant Rocket ground electric supercharging gas circuit, ensure that the realization of the target call that " narrow window " is launched, adopt 4 independently magnetic valve realize connection in series-parallel redundancy backup, by arranging the restricting orifice of different pore size, ensure the supercharging of penetrating front quick high accuracy, improve the reliability of rocket launching.
Claims (3)
1. a cryogenic rocket ground redundancy supercharging device, is characterized in that,
Comprise the pilot-operated type 2/2-way normally closed solenoid valve, two-bit triplet magnetic valve, hand stop valve and the restricting orifice that are arranged on cryogenic propellant pressurization air source air inlet pipeline;
The input of described cryogenic propellant pressurization air source air inlet pipeline and first throttle orifice plate parallel with one another, the input of the second restricting orifice, the input of the 3rd restricting orifice are connected;
The output of first throttle orifice plate is connected with the input of the first hand stop valve;
The output of the second restricting orifice is connected with the input of the 3rd pilot-operated type 2/2-way normally closed solenoid valve;
The output of the 3rd restricting orifice is connected with the input of the first pilot-operated type 2/2-way normally closed solenoid valve with the second pilot-operated type 2/2-way normally closed solenoid valve;
The output of the first pilot-operated type 2/2-way normally closed solenoid valve, the output of the second pilot-operated type 2/2-way normally closed solenoid valve, the output of the 3rd pilot-operated type 2/2-way normally closed solenoid valve are connected with the input of pilot-operated type two-bit triplet magnetic valve with the output of the first hand stop valve;
First output of two-bit triplet magnetic valve is connected with pressure piping output;
Pressure piping output is connected with the input of the second hand stop valve;
Output and the pressure piping of the second hand stop valve end of exitting is connected;
Second output and the pressure piping of two-bit triplet magnetic valve end of exitting is connected.
2. cryogenic rocket ground redundancy supercharging device according to claim 1, is characterized in that: described restricting orifice X1 aperture is 2.5-3.4 millimeter, to be 2.5-3.0 millimeter and X3 aperture be in X2 aperture: 0.7-1.5 millimeter.
3. a cryogenic rocket ground redundancy boosting method, is characterized in that, comprise the steps:
At test phase:
After air-source inflow, open the first hand stop valve;
When pressure piping needs venting, open the second hand stop valve venting;
In the execution launch mission stage:
Start the second pilot-operated type 2/2-way normally closed solenoid valve and the 3rd pilot-operated type 2/2-way normally closed solenoid valve simultaneously, gas by two restricting orifice second restricting orifices and the 3rd restricting orifice fast by tank supercharging;
The 3rd pilot-operated type 2/2-way normally closed solenoid valve is disconnected after tank force value reaches the first setting supercharging value;
The second pilot-operated type 2/2-way normally closed solenoid valve is disconnected after at a slow speed tank being pressurized to the second setting value;
When startup second pilot-operated type 2/2-way normally closed solenoid valve or the 3rd pilot-operated type 2/2-way normally closed solenoid valve occur opening fault; Starting magnetic valve first pilot-operated type 2/2-way normally closed solenoid valve is that tank continues supercharging;
When tank reaches the second setting supercharging value, the second pilot-operated type 2/2-way normally closed solenoid valve or the 3rd pilot-operated type 2/2-way normally closed solenoid valve occur cannot closing fault time, start pilot-operated type two-bit triplet solenoid valve shuts supercharging gas circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510210444.2A CN104792233B (en) | 2015-04-29 | 2015-04-29 | The redundancy pressurizer of cryogenic rocket ground and boosting method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510210444.2A CN104792233B (en) | 2015-04-29 | 2015-04-29 | The redundancy pressurizer of cryogenic rocket ground and boosting method |
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| CN104792233A true CN104792233A (en) | 2015-07-22 |
| CN104792233B CN104792233B (en) | 2016-11-23 |
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| CN105299441A (en) * | 2015-09-16 | 2016-02-03 | 北京航天发射技术研究所 | Gas supply gas circuit for controlling filling valve |
| CN106525441A (en) * | 2016-11-03 | 2017-03-22 | 北京航天试验技术研究所 | High precision and high reliability ground pressurization system for rocket engine test |
| CN109763914A (en) * | 2019-01-24 | 2019-05-17 | 北京蓝箭空间科技有限公司 | A kind of methane autogenous pressurization system with redundancy feature |
| CN111828202A (en) * | 2020-07-20 | 2020-10-27 | 航天科工火箭技术有限公司 | Test bed system of liquid rocket engine |
| CN115306586A (en) * | 2022-08-02 | 2022-11-08 | 北京航天试验技术研究所 | Propellant storage tank pressure control device and control method thereof |
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Cited By (7)
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| CN109763914A (en) * | 2019-01-24 | 2019-05-17 | 北京蓝箭空间科技有限公司 | A kind of methane autogenous pressurization system with redundancy feature |
| CN109763914B (en) * | 2019-01-24 | 2024-03-26 | 蓝箭航天空间科技股份有限公司 | Methane autogenous supercharging system with redundancy function |
| CN111828202A (en) * | 2020-07-20 | 2020-10-27 | 航天科工火箭技术有限公司 | Test bed system of liquid rocket engine |
| CN115306586A (en) * | 2022-08-02 | 2022-11-08 | 北京航天试验技术研究所 | Propellant storage tank pressure control device and control method thereof |
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