CN114112307A - Foundation simulation test method for propellant management in microgravity-variable speed environment - Google Patents
Foundation simulation test method for propellant management in microgravity-variable speed environment Download PDFInfo
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Abstract
The invention discloses a foundation simulation test method for propellant management in a microgravity-variable speed environment, which comprises the following steps: s1, preparing test facility conditions; s2, carrying out a plurality of tests on the test object in the test environment, observing the motion state of the test object and recording the motion data; s3, simulating the motion process of the test object and recording simulation data; and S4, obtaining test characteristic parameters of the test object in the motion process according to the recorded motion data, and comparing the test characteristic parameters with the characteristic parameters obtained according to the simulation data to verify the fluid management capacity and the transmission performance. The simulation method can realize the foundation simulation experiment research of the two-phase flow dynamics characteristics of the space on-orbit fluid and the propellant in the low-gravity and variable-gravity process of the propellant or the fluid in the acceleration change range of 1.5 multiplied by 10 < -2 > g0 to 1.6 multiplied by 10 < -1 > g0 in the simulated space microgravity environment.
Description
Technical Field
The invention relates to the technical field of propellant simulation tests, in particular to a foundation simulation test method for propellant management in a microgravity-variable speed environment.
Background
According to the overload condition of the spacecraft in the flying process, the movement of the fluid in the storage tank can be divided into a plurality of working conditions of weightlessness, micro-weight, low weight, constant weight and overweight, the dynamic characteristic research of small-amplitude linear shaking of the liquid-filled storage tank under the low-weight environment is mature at present, and the theoretical model of the storage tank is widely applied to the engineering design of the spacecraft.
However, with the development of the spacecraft, the liquid in the high-positioning-precision spacecraft storage tank shakes to face a new problem, the spacecraft has high positioning precision, and in the attitude maneuver stabilization process, the spacecraft storage tank faces a microgravity environment, the surface tension of the propellant in the storage tank begins to appear, so that the shaking of the propellant in the storage tank can be caused to present a complex shaking characteristic, and the high-precision attitude control of the platform is influenced. Especially under the condition of variable acceleration, how to further optimize propellant management, and research on related influence factors and laws of propellant design intermittent sinking become problems at present.
Disclosure of Invention
The invention aims to provide a foundation simulation test method for propellant management in a microgravity-speed change environment, which aims to solve the technical problem of researching propellant management under the condition that microgravity becomes accelerated in the prior art.
In order to solve the technical problems, the invention specifically provides the following technical scheme:
a foundation simulation test method for propellant management in a microgravity-variable speed environment comprises the following steps:
s1, preparing test facility conditions;
s2, carrying out a plurality of tests on the test object in the test environment, observing the motion state of the test object and recording the motion data;
s3, simulating the motion process of the test object and recording simulation data;
and S4, obtaining test characteristic parameters of the test object in the motion process according to the recorded motion data, and comparing the test characteristic parameters with the characteristic parameters obtained according to the simulation data to verify the fluid management capacity and the transmission performance.
As a preferable aspect of the present invention, the S1 includes:
s11, providing a microgravity environment by using microgravity tower falling equipment;
s12, creating a device for providing variable accelerated motion conditions and observation recording conditions for the test object in the microgravity environment;
s13, preparing a test observation object and a carrier of the test observation object.
As a preferable aspect of the present invention, in S13, the carrier of the test observation object is specifically a model test tank, the simulation test tank is used for hermetically storing a test fluid medium, and the test observation object is the test fluid medium;
wherein, according to the similarity principle, the simulation test storage box is provided with two storage boxes, including: a large model tank and a small model tank, and the test fluid medium comprises fluorinated liquid FC-72 and absolute ethyl alcohol.
As a preferable aspect of the present invention, the similarity principle includes motion similarity and geometric similarity:
the design principle of geometric similarity requires that dimensionless Bond numbers between the model test storage tank and the prototype storage tank under any working condition are equal, namely the formula is satisfied:
wherein, Bo: a bond number; ρ: the density of the liquid; r: simulating the radius of the test storage tank; σ: the surface tension of the liquid; a: ambient acceleration; m: a tower falling test model is adopted,
the formula of the Bonder number represents the ratio of the gravity borne by the fluid medium to the surface tension, and when the gravity is far smaller than the surface tension of the liquid, the surface tension plays a leading role;
according to the prototype tank bond number given by the acceleration a (determined by repositioning thrust and rocket upper-stage mass) when the rocket at the upper stage is repositioned, the acceleration a required to be applied by the model test tank is obtainedm：
am＝a(ρ/ρm)(R/Rm)2(σm/σ)
The principle of motion similarity aims to keep motion similarity between the two models so as to reflect the time (namely repositioning time) relation of the liquid migration process between the two models, and the dimensionless motion similarity weber numbers in fluid mechanics need to be equal, namely the formula is satisfied:
wherein v, vmThe characteristic speeds of liquid migration in the real tank and the model tank are respectively expressed, and the Weber formula expresses the ratio of inertia force to surface tension.
And carrying out dimension transformation on the Weber formula to enable the Weber formula to contain a time item, and obtaining:
wherein, tmRespectively, the characteristic time values of liquid migration in the real storage tank and the model storage tank.
As a preferable scheme of the present invention, in S2, test situations of the test object in the test environment are divided into two types, including a static condition test and a dynamic condition test, and the test object performs multiple tests under the static condition and the dynamic condition respectively;
under the static working condition state, the large model storage tank is selected as the test object, and the absolute ethyl alcohol is selected as the test fluid medium;
and under the dynamic working condition state, the small model storage tank is selected as the test object, and the fluorinated liquid FC-72 is selected as the test fluid medium.
As a preferable aspect of the present invention, in S3, the simulation process includes:
establishing a theoretical model according to the infiltration phenomenon of liquid and solid;
solving the free interface flow problem of the propellant according to an interface tracking method (VOF method) established under an Euler grid, repositioning characteristic time values of each process by establishing a control equation for describing fluid motion and according to a dimensionless parameter Bode equation of fluid mechanics,
wherein the bond number is defined as:
BO＝aR2/β
wherein β is σ/ρ,
the characteristic time values of the relocation processes are respectively expressed as:
t1indicating that the liquid has reached the bottom of the tank; t is t2Representing a fountain impact gas-liquid interface; t is t3Showing the fountain colliding with the roof of the tank; t is t4Indicating that liquid is exiting the top of the tank; t is t5Indicating that the gas fraction at the exit and in the vicinity is less than 5%;
t is obtained by numerical simulation calculation1、t2、t3、t4、t5。
In a preferred aspect of the present invention, in S12, the apparatus includes an acceleration applying module, an optical recording module and a data collecting and processing module,
the acceleration applying module is used for applying acceleration along a falling direction to the simulation test storage tank which freely falls in the falling cabin, the optical recording module is arranged on one side of the simulation test storage tank and is used for observing the motion process of a test fluid medium in the simulation test storage tank, and the data acquiring and processing module is in signal connection with the optical recording module and is used for acquiring and storing information observed and recorded by the optical recording module;
the acceleration applying module applies different forces to the simulation test storage box to generate different accelerations, the accelerations are determined according to different sizes and different working conditions, and the acceleration is set as amAnd is and
am＝a(ρ/ρm)(R/Rm)2(/m/σ)
a is amThe selection of the model is determined according to the size of the model storage tank and the physical property parameters of the experimental liquid.
As a preferable scheme of the present invention, the variable thrust applying module includes a long straight rail, an object stage and a motor driving unit, the simulation test storage tank is disposed on the object stage, the object stage is slidably mounted on the long straight rail, the motor driving unit is connected to the object stage and drives the object stage to move and drive the simulation test storage tank to move at variable speeds, the acceleration applying module is connected to an external control module, the external control module is connected to the motor driving unit,
the external control module is used for sending a control instruction when receiving a trigger signal so as to regulate and control the motor driving unit to drive the objective table to move according to set motion parameters, and therefore a set acceleration value is applied to the simulation test storage box.
As a preferable scheme of the invention, the simulation test storage tank comprises a first semicircular tank body and a second semicircular tank body, the first tank body and the second tank body are fixedly connected through a flange, a sealing block is arranged at the connection position of the first tank body and the end part of the second tank body, and the sealing block is used for tightly abutting against the first tank body and the second tank body;
the first box body and the second box body are colorless transparent sealed tank bodies, and the thickness of the box bodies is not more than two millimeters.
As a preferred scheme of the invention, a plug-in base is arranged at the bottom of the simulation test storage box, the box body is installed on the objective table through the plug-in base, and the plug-in base comprises a connecting base body, and an installation groove, a plug-in boss, an installation part, a limiting block and a limiting groove which are arranged on the connecting base body;
the mounting groove is arranged at the top of the connecting seat body, the mounting parts are arranged at two sides of the top of the mounting groove, and the mounting parts are abutted to the first box body and/or the second box body through fastening bolts;
the limiting groove is formed in the bottom of the connecting seat body, the limiting blocks are formed on two sides of the limiting groove, the opposite-insertion protruding portions are arranged on the limiting blocks and protrude towards the outer sides of the limiting blocks, the objective table is provided with a mounting seat, grooves corresponding to the shape of the bottom of the inserting base in a concave-convex mode are formed in the mounting seat, and the opposite-insertion protruding portions are correspondingly inserted into the mounting seat in an inserting mode.
Compared with the prior art, the invention has the following beneficial effects:
the invention provides a foundation simulation test method for propellant management in a microgravity-variable speed environment, which adopts the test principle that the in-orbit gas/liquid distribution and the repositioning process of a propellant in a real upper-stage storage tank of a rocket under different space environments are analyzed and reproduced by observing the form distribution rule of a test liquid of a model storage tank arranged in a free-falling cabin and utilizing the fluid mechanics similarity principle, and are compared with a numerical simulation result to finally determine the characteristic time parameter of the propellant in the repositioning process under the set working condition.
The method comprises the following steps: s1, preparing test facility conditions; s2, carrying out a plurality of tests on the test object in the test environment, observing the motion state of the test object and recording the motion data; s3, simulating the motion process of the test object and recording simulation data; and S4, obtaining test characteristic parameters of the test object in the motion process according to the recorded motion data, and comparing the test characteristic parameters with the characteristic parameters obtained according to the simulation data to verify the fluid management capacity and the transmission performance.
The simulation method can realize the foundation simulation experiment research of the two-phase flow dynamics characteristics of the space on-orbit fluid and the propellant in the low-gravity and variable-gravity process of the propellant or the fluid in the acceleration change range of 1.5 multiplied by 10 < -2 > g0 to 1.6 multiplied by 10 < -1 > g0 in the simulated space microgravity environment.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
FIG. 1 is a block diagram of a simulation method according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of step S1 according to an embodiment of the present invention;
FIG. 3 is a graph showing the comparison result between numerical simulation data and test data of characteristic time values in the example of the present invention.
FIG. 4 is a structural view of a test apparatus to which an embodiment of the present invention is applied;
FIG. 5 is a schematic view of a connection between a simulation test reservoir and a docking station in an embodiment of the invention;
FIG. 6 is a schematic structural diagram of a partial structure of an insertion base according to an embodiment of the present invention;
the reference numerals in the drawings denote the following, respectively:
1-simulation test storage tank; 2-an acceleration application module; 3-an optical recording module; 4-a data acquisition processing module; 5-an external control module; 6-background light source; 7-a socket base; 8-a flange; 9-sealing the block; 11-a first box; 12-a second box; 21-long straight guide rail; 22-an object stage; 23-a motor drive unit; 31-high speed digital CCD; 32-analog CCD;
71-a mounting groove; 72-opposite insertion convex part; 73-a mounting portion; 74-a limiting block; 75-a limiting groove; 76-a connection seat body; 231-a servo motor; 232-human-computer interaction interface; 233-motor driver.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 and 2, the present invention provides a ground simulation test method for propellant management in a microgravity-variable speed environment, comprising the following steps:
s1, preparing experimental facility conditions;
s2, carrying out a plurality of tests on the test object in the prepared test environment, observing the motion state of the test object and recording the motion data;
s3, simulating the motion process of the test object and recording simulation data;
and S4, obtaining test characteristic parameters of the test object in the motion process according to the recorded motion data, and comparing the test characteristic parameters with the characteristic parameters obtained according to the simulation data to verify the fluid management capacity and the transmission performance.
S1 includes:
and S11, providing a microgravity environment by using microgravity tower falling equipment.
A. Microgravity tower falling facility
The microgravity tower falling facility can obtain microgravity time of several seconds, and is the most important and economic foundation microgravity experimental facility for microgravity scientific research. The experiment selects free fall experiment tower facility (belonging to mechanics research institute of Chinese academy of sciences) located in the Guancun of Beijing of the first capital of China.
The main technical parameters of the tower falling are as follows:
microgravity time: 3.6 seconds;
microgravity level: 10-5g0(double Chamber), 10-2～10-3g0(Single Chamber) (where g0Is the local gravitational acceleration);
experimental payload: 70kg (double compartment), 90kg (single compartment);
and (3) recovery overload: less than or equal to 15g0(wherein g is0Is the local gravitational acceleration);
B. and (3) dropping the cabin:
the falling cabin is important special equipment for carrying a test piece in a tower falling experiment system. In the experiment process, the falling cabin freely falls from the 83 m release platform, and the microgravity time of 3.5 seconds can be obtained. The falling cabin is divided into two types of double cabins and a single cabin, the total experimental load mass (including the weight of the inner cabin and the outer cabin and the carrying weight of a user) of the double cabins/the single cabin is 630kg, and in the embodiment, the single cabin type falling cabin (hereinafter called the single cabin) is selected.
The single-chamber characteristic of the tower falling experiment: the single cabin is suitable for the requirement of 10 on the microgravity level-2～10-3g0Compared with the double cabin, the single cabin has a much more compact and simpler structure. The functions and procedures of positioning and butt joint of the inner cabin and the outer cabin, no vacuum pumping, no locking-unlocking of the inner cabin and the like are mainly saved, and the assembly is convenient; the larger carrying load mass margin and geometric dimension margin are increased; the test piece is directly arranged on a special rack in the cabin.
The main technical parameters of a single cabin are as follows:
microgravity level (residual acceleration): up to 10-2～10-3g0Magnitude;
microgravity time: 3.6 s;
maximum experimental load weight (including cabin weight and user carrying weight): 630 kg;
the load space (the maximum effective space of user experimental equipment) in the cabin is less than or equal to phi 850 multiplied by 1500 mm;
the total weight of the user load is as follows: less than or equal to 90 kg.
And S12, creating a device for providing the test object with variable accelerated motion conditions and observation and recording conditions in the microgravity environment, wherein the device is arranged in the falling cabin.
The device comprises an acceleration applying module 2, an optical recording module 3 and a data acquisition and processing module 4,
the acceleration applying module 2 is used for applying acceleration along a falling direction to the simulation test storage tank which freely falls in the falling cabin, the optical recording module 3 is arranged on one side of the simulation test storage tank and used for observing the motion process of a test fluid medium in the simulation test storage tank, and the data acquiring and processing module 4 is in signal connection with the optical recording module 3 and used for acquiring and storing information observed and recorded by the optical recording module 3.
S13, preparing a test object and a carrier of the test object.
The carrier of the test observation object is specifically a model test storage tank, the simulation test storage tank is used for hermetically storing a test fluid medium, and the test observation object is the test fluid medium.
C. Propellant simulation storage tank
The tower drop test is based on the fluid mechanics similarity criterion as a theoretical basis, and ensures that the model test storage tank and the upper prototype propellant storage tank meet the following two aspects of fluid dynamics similarity:
(1) geometric similarity
Because of the limitation of the space size of the tower falling test equipment (falling cabin) and the microgravity test time, the tower falling test cannot be carried out by adopting a model of 1:1 of a real object generally, and a special scaling test model, generally a transparent organic glass model, needs to be selected and determined according to the similarity principle so as to facilitate the test observation. In this test, 2 small test tanks of different scaling sizes were used. The design principle is that dimensionless Bond numbers (Bond) between the model test storage tank and the prototype storage tank under any working condition are required to be equal, namely the formula is satisfied:
wherein, Bo: a bond number; ρ: the density of the liquid; r: simulating the radius of the test storage tank; σ: the surface tension of the liquid; a: ambient acceleration; m (subscript): a tower falling test model is adopted,
the physical meaning of equation (2.1) is the ratio of the gravitational force to the surface tension experienced by the fluid medium, and surface tension dominates when the gravitational force is much smaller than the surface tension of the liquid.
The acceleration a required to be applied by the model test storage box can be obtained according to the number of the prototype storage box Bond given by the acceleration a (determined by the repositioning thrust and the upper-stage mass of the rocket) when the upper-stage rocket is repositionedm：
am＝a(ρ/ρm)(R/Rm)2(σm/σ) (2.2)
According to the existing numerical simulation result, selecting appropriate similar parameters to ensure that: in the experimental equipment space, the effective space is enough to scale the model experiment storage box, the matched experimental test piece and the test, and in the experimental time, the microgravity time of 3.6 seconds provided by the microgravity falling tower can meet the experimental requirement.
(2) Similar in motion
On the premise that the static balance configuration of the fluid in the storage tank of the model test is similar to that of the propellant in the conventional upper-level real storage tank, namely the situation that the bond number is equal is met, the motion of the fluid between the two models is kept similar to reflect the time (namely the repositioning time) relation used in the liquid migration process between the two models. Thus, another dimensionless motion-like Webber (Webber) number is introduced to be equal, i.e. to satisfy the relation:
wherein v, vmCharacteristic velocities of liquid migration in the real tank and the model tank, respectively. The physical meaning of the formula (2.3) is the ratio of the inertial force to the surface tension.
The following dimension is applied to the above equation to make it contain the time term:
where t, tmRespectively, the characteristic time values of liquid migration in the real storage tank and the model storage tank.
The relationship between the characteristic time of the liquid motion of the model test storage tank and the characteristic time of the propellant motion in the upper-level real storage tank of the rocket in the propellant repositioning process is given by the following formula:
tm＝(a/am)R/Rm 1/2(ρσm/ρmσ)1/2 (2.5)
or tm＝t(Rm/R)3/2(ρmσ/ρσm)1/2 (2.6)
According to the similarity principle, the simulation test tanks in the present embodiment are provided in two, including: a large mold storage tank and a small mold storage tank.
According to experimental requirements, the conventional upper-stage intermittent bottoming combined thrust scheme is 40N acting for 210 seconds, and 300N acting for 60 seconds, wherein the propellant tank is applied with an external repositioning acceleration of a certain magnitude. From conventional upper-grade mass, tank dimensions and propellant fuel and oxidizer physical parameters, the corresponding spatial repositioning acceleration a and tank propellant system Bond number Bo can be determined as follows:
(a) total mass M before one start1＝5860kg，
Acceleration a at 40N application1＝6.826×10-3m/s2(6.958×10-4g0)
The corresponding Bond numbers are: bo-1151.77 (fuel); bo-11(oxidizing agent) 89.54;
acceleration a at 300N2＝5.119×10-2m/s2(5.219×10-3g0)
Corresponding Bond number Bo-12388.2 (fuel); bo-12(oxidizing agent) 671.45;
(b) total mass M before secondary start2＝5429kg，
Acceleration a at 40N application1＝7.368×10-3m/s2(7.511×10-4g0)
Corresponding Bond number Bo-2155.88 (fuel); bo-21(oxidizing agent) 96.65;
acceleration a at 300N2＝5.526×10-2m/s2(5.633×10-3g0)；
Corresponding Bond number Bo-22419.13 (fuel); bo-22(oxidizing agent) ═ 724.84
In the tower drop test, the (negative) acceleration in the falling direction is applied to the free-falling model test tank by the acceleration application module 2 in the falling chamber, as shown in fig. 4,
the variable thrust applying module 2 comprises a long straight guide rail 21, an object stage 22 and a motor driving unit 23, the simulation test storage box is arranged on the object stage 22, the object stage 22 is slidably arranged on the long straight guide rail 21, the motor driving unit 23 is connected with the object stage 22 and drives the object stage 22 to move and drive the simulation test storage box to move in a variable speed,
the motor driving unit 23 comprises a servo motor 231, a visual human-computer interaction interface 232 and a motor driver 233, the human-computer interaction interface 232 and the servo motor 231 are connected with the motor driver 233, and the human-computer interaction interface 232 and the motor driver 233 are connected with the PLC.
The visual human-computer interaction interface 232 is used for setting the running stroke and acceleration parameters of the servo motor 231 before the experiment, and a worker can manually control the setting of the parameters through the human-computer interaction interface, which is the prior art and is not described in detail in this embodiment. The motor driver 233 is used for driving the servo motor 231 to move in the test process, and the servo motor 231 is used for driving the object stage 22 and the simulation test storage box to move for completing the test.
Applying different forces to the simulation test storage box through the acceleration applying module 2 to generate different accelerations, wherein the accelerations are determined according to different sizes and different working condition conditions, and the acceleration is set as amAnd is and
am＝a(ρ/ρm)(R/Rm)2(σm/σ) (2.7)
amthe selection of the test liquid is determined according to the size of the model storage tank and the physical property parameters of the test liquid.
The acceleration application module 2 is connected with an external control module 5, the external control module 5 is connected with a motor driving unit 23, and the acceleration application module 2 is controlled and started by the external control module 5. And the external control module 5 sends a control instruction when receiving the trigger signal so as to regulate and control the motor driving unit 23 to drive the object stage 22 to move according to the set motion parameters, thereby applying a set acceleration value to the simulation test storage tank.
The external control module 5 comprises a power supply and an external trigger unit, the power supply supplies power to the acceleration applying module for power distribution management, the external trigger unit comprises a timing module and a PLC (programmable logic controller), and the timing module counts time and reaches set time to trigger the PLC to send a regulation and control instruction to regulate and control the acceleration applying module 2 to start working. In the test process, the PLC controls the motor driver 233 to output actions according to the running stroke and the motion parameters set in the human-computer interaction interface 232, so that the servo motor 231 is regulated and controlled to drive the objective table 22 to drive the simulation test storage box 1 to move.
In an embodiment of the present invention, there is provided a method of determining a microgravity state: i.e. whether the tank 1 is in a microgravity state is simulated by the time setting.
For example, if the microgravity state can be entered after the simulated test storage tank 1 falls freely for T seconds through the priority test, T seconds can be set on the PLC controller, and after the whole device is pneumatically operated for T seconds, an external input signal transmits the signal to the PLC controller.
Therefore, the following embodiments are specifically provided to implement the above process:
preset time for representing that the analog test storage box 1 reaches a microgravity test state is preset in the PLC, the timing module is used for counting the motion time of the analog test storage box 1, when the motion time counted by the timing module reaches the preset time, the timing module forms an external trigger signal and sends the external trigger signal to the PLC, the PLC receives the external trigger signal and then forms a control instruction, and meanwhile, the PLC sends the control instruction to the motor driver 223, the optical recording module 3 and the data acquisition processing module 4 to regulate and control the optical recording module 2 and the data acquisition processing module 4 to start working.
The model test tank shape should be similar to the conventional upper prototype tank according to the above similarity criteria, actual tank size and acceleration, and the size reduction ratio should take into account the combined tower-dropping 3.6 second test time (not exceeded) and the variable acceleration values that the variable acceleration boosting system can achieve (tank stroke limit in the tank drop, etc.). Through comprehensive analysis, 2 similar models with different scaling sizes are selected in the test and are shown in table 1
TABLE 1 test tank model ratio and characteristic dimensions
| Prototype storage tank/mm | Large model/mm | Small model/mm | |
| Inner radius R | 480 | 55 | 35 |
| Internal diameter phi | 960 | 110 | 70 |
| Total height L | 1240 | 142.0 | 90.4 |
| Scaling ratio H | 1:8.72 | 1:13.71 |
The simulation test storage tank 1 is a colorless transparent sealed tank body made of organic glass, the simulation test storage tank 1 is columnar, and the flange of the simulation test storage tank 1 is designed eccentrically.
Specifically, as shown in fig. 5, the simulation test tank 1 includes a first semicircular tank 11 and a second semicircular tank 12, the first tank 11 and the second tank 12 are fixedly connected by a flange 8, and the first tank 11 and the second tank 12 are integrally columnar and form an integral tank 1 that is a colorless transparent sealed tank (the first tank 11 and the second tank 12 are both independent sealed tanks).
In order to observe and record the change of the fluid form in the storage tank conveniently, the thickness of the tank body is recommended to be not more than two millimeters so as to clearly display the change of the gas-liquid level form, accurately capture the change of a gas-liquid interface in the middle of the storage tank in a simulation test and reduce the visual error brought by optical refraction to the maximum extent.
Because two half-cycle boxes on two sides are independently sealed, and the sizes of the first box 11 and the second box 12 are the same or different, the two half-cycle boxes are set to be different in size, so that the fluid tension states in two models with different sizes can be observed simultaneously, and compared with the mode that one storage tank is subjected to multiple tests, the test time and the test cost are saved.
Considering that the sizes of the two side cases are different, the heights of the two side cases at the joint of the flange 8 are possibly inconsistent, and during variable-speed motion, the first case 11 and the second case 12 are easy to loosen and scatter, so that the observation is unstable, therefore, the sealing block 9 is arranged at the end joint of the first case 11 and the second case 12, and the sealing block 9 is used for tightly butting the first case 11 and the second case 12, so that the stability is improved.
The storage tank is directly placed on the objective table, lacks fixed stay, and in the variable speed motion process, easy unstability, this embodiment is through setting up connection structure in the storage tank bottom, further improves stability.
Specifically, the insertion base 7 is provided at the bottom of the simulation test storage tank 1, and the simulation test storage tank 1 is mounted on the object stage 22 through the insertion base 7, as shown in fig. 5 and 6, the insertion base 7 includes a connection seat body 76, and an installation groove 71, an opposite insertion boss 72, an installation portion 73, a limit block 74, and a limit groove 75 which are provided on the connection seat body 71.
The mounting groove 71 is arranged at the top of the connecting seat body 76, the mounting parts 73 are arranged at two sides of the top of the mounting groove 71, and the mounting parts 73 are abutted to the first box body 11 and/or the second box body 12 through fastening bolts so as to fix the simulation test storage box 1 on the plugging base 7.
Spacing groove 75 is seted up in connecting pedestal 76 bottom, and stopper 74 is formed in spacing groove 75 both sides, to inserting bellying 72 and setting up on stopper 74, and to inserting bellying 72 to the protrusion in the stopper 74 outside, is provided with the mount pad on the objective table, sets up the recess that corresponds with 7 bottom shapes of grafting base are unsmooth on the mount pad, corresponds to inserting bellying 72 and pegs graft on the mount pad, and the installation is more stable. Through setting up grafting base 7, make the storage tank can stably follow the objective table variable speed and remove, reduce the experimental deviation because of the unstable factor causes, avoid experimental observation effect.
D. Model test liquid
In the test, the fluorinated liquid FC-72 and absolute ethyl alcohol (Ethanol) are selected as test fluid media preliminarily and are respectively used for storage tanks with different sizes and under the working conditions of Bond number. The main physical properties of the fluorinated liquid FC-72 and absolute Ethanol (Ethanol) are shown in Table 2.
TABLE 2 testing of fluid Medium Property parameters
The ratio of surface tension to density of the two experimental liquids is:
βFC-72＝5.95×10-6(ii) a And betaEthanol＝2.84×10-5
According to the formula (2.1), the fluorinated liquid FC-72 is selected under a certain Bond number, so that the variable thrust acceleration value of a tower falling test is smaller, and the test observation of the repositioning process under a larger Bond number can be realized within 3.6 seconds of tower falling microgravity time.
In accordance with the above principle, the acceleration variation range selected in the present embodiment is 0.15m/s in consideration of the space limitation (1500mm) in the tower falling unit cell2-1.6m/s2According to the specific sizes of different model storage tanks and physical property parameters of experimental liquid, the experimental implementation principle is as follows:
(a) the large model is used for simulating a large Bond number test corresponding to a large thrust 300N, and fluorinated liquid FC-72 is used as a test fluid medium;
(b) the small model is used for a small Bond number test under the condition of low thrust of 40N, and the test liquid adopts fluorinated liquid FC-72;
(c) the large model is used for a small Bond number test under the small thrust of 40N, and the test liquid adopts absolute ethyl alcohol (Ethanol).
S2, test
The test was performed according to the test parameters of table 3, and the test apparatus included an optical observation system and a data acquisition system in addition to the variable thrust electric propulsion system and the external controller.
The optical recording module comprises a CCD camera for observing the analog test storage box 1 and a background light source 6 for providing background light for the CCD camera, the background light source 6 and the CCD camera are respectively arranged on two sides of the analog test storage box 1, the CCD camera is provided with two high-speed digital CCD31 and two analog CCD32, the high-speed digital CCD31 is provided with a short-focus lens, the high-speed digital CCD31 is used for shooting the analog test storage box 1 in a front view mode, and the analog CCD32 is used for shooting the analog test storage box 1 in a overlooking mode.
Specifically, the high-speed digital CCD31 adopts CR-GM00-H1020 of DALSA corporation, canada, with a resolution of 1024 × 768 × 8 bits, a pixel size of 7.4 μm × 7.4 μm, a maximum acquisition rate of 117fps, an external size of 29 × 44 × 67mm3, a weight of less than 125g, and a power consumption of less than 4W, and by using gigabit-capable transmission, the time resolution scale of the repositioning process of the liquid in the liquid storage tank after the thrust is applied can be accurate to 0.01s magnitude by using the high-speed digital CCD 31. The analog CCD32 had a resolution of 720 x 576 x 8 bits and a frame rate of 25 fps.
The background light source 4 selects a white light emitting sheet, specifically, the background light source 4 and the high-speed digital CCD31 are respectively located at two sides of the analog test storage box 1, and the size of the white light emitting sheet is far larger than that of the analog test storage box 1, so that the projection of the analog test storage box 1 can be completely projected on the white light emitting sheet.
In the test process, the analog test storage box 1 needs to be placed in a falling cabin, the background light source 4, the high-speed digital CCD31 and the analog CCD32 are all fixed in the falling cabin, and the projection of the analog CCD32 can also be completely projected on the white luminescent sheet, so that the white luminescent sheet can completely provide background light for shooting of the high-speed digital CCD31 and the analog CCD 32.
The data acquisition and processing module 4 comprises a data terminal in signal connection with the CCD camera, the data terminal is a notebook computer, and in the actual use process, the notebook computer should be a portable and vibration-isolated model,
the data terminal comprises a data acquisition and transmission unit and a data storage unit, the data storage unit is used for storing shooting data received by the data terminal, the conventional notebook computer has a data storage function, and the data storage unit is not described in detail in the embodiment.
The data acquisition and transmission unit comprises acquisition software and a transmission cable and is used for acquiring shooting data of the CCD camera and transmitting the shooting data to the data terminal, the acquisition software can set an acquisition frame rate and an acquisition frame number, and when the external trigger signal triggers the camera, the acquisition software starts to control the camera to shoot pictures and the pictures are acquired through the gigabit network cable and stored in the memory of the notebook computer.
The multi-angle observation is realized by shooting through the two CCDs, the change of the vapor/liquid shape and the variable thrust relocation process in the liquid storage tank are clearly reflected, and background light with uniform light intensity is provided through the white light emitting sheet in the shooting process, so that a picture for clearly displaying the interface of the vapor phase and the liquid phase is shot by the CCD camera.
TABLE 3
The test result is obtained as a characteristic time value, T0、T1、T2、T3、T4、T5Wherein T is0Indicates the beginning of the load, T1Indicating the arrival of liquid at the bottom of the tank, T2Indicating the fountain collision gas-liquid interface, T3Indicating fountain collision against box top, T4Indicating the liquid leaving the top of the tank, T5Indicating that the bubbles in the reservoir are no longer moving towards the outlet.
According to the similarity principle, the characteristic time value obtained by the test is reversely deduced to the real characteristic time in the process of repositioning the real storage tank propellant, as shown in the table 4:
TABLE 4 rocket upper tank propellant repositioning characteristic time
S3, numerical simulation and theoretical modeling
When a liquid comes into contact with a solid, the liquid spreads along the surface of the solid, and this phenomenon is called wetting of the liquid with the solid. The degree of wetting is generally reflected in the contact angle θ, which reflects the relative magnitude of the attractive interaction (adhesion) between the liquid and solid molecules and the cohesive force between the liquid molecules. When solid, liquid and gas are contacted and in an equilibrium state, the contact angle satisfies the equation of Yong:
σ13＝σcosθ+σ12
σ，σ12，σ13surface tension coefficients of three interfaces of gas-liquid, liquid-solid and gas-solid respectively, and sigma, sigma when temperature and gas pressure are unchanged12And σ13Are all constants. Under such conditions, the above formula is equivalent to
θ＝Const
If 0< theta <90 deg., indicating that the adhesion is greater than the cohesion, the liquid wets the solid; if 90 ° <0<180 °, the adhesion is less than the cohesion and a non-wetting state is present.
In a microgravity environment, the hydrostatic surface is generally not planar due to surface tension, but rather exhibits a curved interface. The gas-liquid two-phase curved interface is related to the pressure difference between the two phases, given by the Laplace equation.
Where Δ p is the fluid interface pressure difference, σ is the surface tension coefficient, C is the average curvature of the interface,
R1and R2Two major radii of curvature.
In the absence of gravity (or other external field), the pressure difference Δ p is constant throughout the volume. The shape of the interface of the two phases then depends only on the effect of the contact angle theta and the surface tension, which is different from what is the case on earth. Capillary phenomena on earth are generally the result of a balance of hydrostatic pressure (gravity) and interfacial forces.
The fluid is an incompressible viscous fluid, and the continuity equation and Navier-Stokes equation describing the motion of the fluid are respectively
Wherein
In order to be the acceleration of the gravity,
for surface tension, τ is the viscous stress tensor for Newtonian fluids
τ＝2μS
The strain rate tensor S is given by
The fluid volume is determined by the volume function F. The governing differential equation of the volume function is
Wherein the fluid volume function F, defined on each spatial cell, is defined as the ratio of the volume occupied by the fluid in the cell to the volume of fluid that the cell can accommodate. By definition, the value of F is l when the cell is filled with fluid; and when the unit is empty, the value of F is 0. A unit has a free surface when the unit has an F value of 0< F < 1.
The boundary conditions are as follows: meeting the conditions of no penetration and no slippage on the wall of the tank, i.e.
In the formula:
is the fluid velocity;
is the wall velocity.
The equation is dispersed by a second-order windward format, the velocity and pressure coupling adopts a SIMPLE method, and the problem is solved by a finite element method.
S4 simulation calculation analysis of propellant bottom sinking process
Conventional cylindrical storage tank with volume of 0.7m3The cylindrical storage tank adopts a hemispherical bottom with a diameter
The length of the column section is 570 mm. Due to the axisymmetric structure, an axisymmetric calculation model is adopted in the numerical simulation process.
The bond number is defined as:
BO＝aR2beta where beta is sigma/rho
The characteristic time of each relocation process is respectively as follows:
t1indicating that the liquid has reached the bottom of the tank; t is t2Representing a fountain impact gas-liquid interface; t is t3Showing the fountain colliding with the roof of the tank; t is t4Indicating that liquid is exiting the top of the tank; t is t5Indicating the substantial end of the repositioning (exit and gas void fraction in the vicinity)<5％)。
The typical operating condition numerical analysis results are shown in table 6:
table 6 propellant management numerical simulation feature schedule
| Working conditions | Thrust force | Acceleration of a vehicle | Bo number | Filling in | t1 | t2 | | t4 | t5 | |
| 1 | 600 | 0.0455 | 288 | 80％ | 8 | - | - | 46 | 140 | |
| 2 | 300 | 0.0228 | 144 | 80％ | 10 | - | - | 86 | 182 |
The detailed numerical simulation results of the gas-liquid flow process in the model storage tank and the gas-liquid interface configuration distribution corresponding to different characteristic times t1, t2, t3, t4 and t5 under typical working conditions in the table are as follows.
Working condition 1: and simulating the change of a gas-liquid interface in the process of repositioning the propellant after the attitude control engine is started. And calculating that the working medium is propellant fuel, the filling rate is 80%, the sinking thrust is 600N, and the corresponding bond number is 288.
The initial interface of the gas and liquid is a plane, the liquid is positioned on the upper half part of the box body, and the gas is positioned on the lower half part of the box body.
Working condition 2: and simulating the change of a gas-liquid interface in the process of repositioning the propellant after the attitude control engine is started. Calculating that the working medium is propellant fuel, the filling rate is 80%, the sinking thrust is 300N, and the corresponding bond number is 144.
The initial interface of the gas and liquid is a plane, the liquid is positioned on the upper half part of the box body, and the gas is positioned on the lower half part of the box body.
From the simulation, table 7 results:
TABLE 7 propellant repositioning characteristic times given by typical model tank simulation calculations
S5, comparing numerical simulation and experimental results
According to the numerical simulation result of the full-size real storage tank, the bottom sinking process of the storage tank propellant is finished within 210 seconds under the rated working condition, namely the storage tank propellant is under the action of 40N thrust before the bottom sinking is finished.
Therefore, the numerical simulation and the experimental result are divided into the following two parts:
the first part is that numerical simulation and experiment comparison of a large tank model are carried out under the condition of corresponding 300N direct bottom sinking; the second part is full-size model numerical simulation and small tank model numerical simulation and experimental comparison under the corresponding 40N bottom sinking working condition.
And (3) reversely deducing the characteristic time value obtained by numerical simulation and experimental working conditions to the real characteristic time in the process of repositioning the propellant of the real storage tank, wherein the numerical value of the characteristic time and the experimental comparison result are shown in figure 3.
The process according to the above is summarized as follows:
a microgravity simulation test research of a top-level propellant repositioning dynamics process of a certain rocket is developed in hectometer falling towers in China by utilizing a falling tower variable thrust on-orbit fluid management experiment platform, the observation of the shape and position change process of a liquid propellant gas/liquid interface in a storage tank under different variable acceleration (bond number) conditions in a microgravity environment is successfully realized within a 3.5 second short-time microgravity period, and experimental data for simulating the real on-orbit working condition change rule of a space are obtained. The total 24 times of tower falling tests of static conditions (first type of working conditions) and dynamic conditions (second type of working conditions) are completed, the observation image data of the relocation test of 9 groups of working conditions are obtained, the analysis of the test results is consistent with the comparison of numerical simulation results, a large number of test results with engineering guidance significance are obtained, the analysis and the test method of the tower falling variable thrust simulation test are verified to be suitable for the experimental test and scientific research of variable gravity processes such as fluid weight positioning and the like and dynamic characteristic parameters in the microgravity environment, and engineering parameters and theoretical bases are provided for the design of the engineering model of China.
The falling tower micro-gravity-variable flow of the inventionThe novel technical method of the body management simulation research and experiment can be used for simulating the propellant or fluid in the space microgravity environment at 1.5 multiplied by 10-2g0To 1.6X 10-1g0The simulation experiment research of the dynamic characteristics of the two-phase flow of the space on-orbit fluid and the propellant in the process of low gravity and variable gravity in the acceleration variation range is completed, and the simulation experiment verification of the related problems in the related space propellant management engineering design is completely applicable. The experimental research method can also be used for other microgravity experimental platforms (such as weightless airplanes, spaceships, space stations and the like).
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The above embodiments are only exemplary embodiments of the present application, and are not intended to limit the present application, and the protection scope of the present application is defined by the claims. Various modifications and equivalents may be made by those skilled in the art within the spirit and scope of the present application and such modifications and equivalents should also be considered to be within the scope of the present application.
Claims (10)
1. A foundation simulation test method for propellant management in a microgravity-variable speed environment is characterized by comprising the following steps:
s1, preparing test facility conditions;
s2, carrying out a plurality of tests on the test object in the test environment, observing the motion state of the test object and recording the motion data;
s3, simulating the motion process of the test object and recording simulation data;
and S4, obtaining test characteristic parameters of the test object in the motion process according to the recorded motion data, and comparing the test characteristic parameters with the characteristic parameters obtained according to the simulation data to verify the fluid management capacity and the transmission performance.
2. The method for simulating a propellant-managed foundation in a microgravity-variable speed environment as recited in claim 1, wherein said S1 comprises:
s11, providing a microgravity environment by using microgravity tower falling equipment;
s12, creating a device for providing variable accelerated motion conditions and observation recording conditions for the test object in the microgravity environment;
s13, preparing a test observation object and a carrier of the test observation object.
3. The method of ground based simulation test for propellant management in a microgravity-variable speed environment as set forth in claim 2, wherein in S13, the carrier of the test observation object is a simulation test tank for hermetically storing a test fluid medium, and the test observation object is the test fluid medium;
wherein, according to the similarity principle, the simulation test storage box is provided with two storage boxes, including: a large model tank and a small model tank, and the test fluid medium comprises fluorinated liquid FC-72 and absolute ethyl alcohol.
4. A ground-based simulation test method for propellant management in a microgravity-variable speed environment according to claim 3 wherein the similarity principles include kinematic similarity and geometric similarity:
the design principle of geometric similarity requires that dimensionless Bond numbers between the model test storage tank and the prototype storage tank under any working condition are equal, namely the formula is satisfied:
wherein, Bo: a bond number; ρ: the density of the liquid; r: simulating the radius of the test storage tank; σ: the surface tension of the liquid; a: ambient acceleration; m: a tower falling test model is adopted,
the formula of the Bonder number represents the ratio of the gravity borne by the fluid medium to the surface tension, and when the gravity is far smaller than the surface tension of the liquid, the surface tension plays a leading role;
according to the prototype tank bond number given by the acceleration a (determined by repositioning thrust and rocket upper-stage mass) when the rocket at the upper stage is repositioned, the acceleration a required to be applied by the model test tank is obtainedm：
am＝a(ρ/ρm)(R/Rm)2(σm/σ)
The principle of motion similarity aims to keep motion similarity between the two models so as to reflect the time (namely repositioning time) relation of the liquid migration process between the two models, and the dimensionless motion similarity weber numbers in fluid mechanics need to be equal, namely the formula is satisfied:
wherein v, vmRespectively representing the characteristic speeds of liquid migration in a real storage tank and a model storage tank, wherein the Weber formula represents the ratio of inertia force to surface tension;
and carrying out dimension transformation on the Weber formula to enable the Weber formula to contain a time item, and obtaining:
wherein, tmRespectively, the characteristic time values of liquid migration in the real storage tank and the model storage tank.
5. The method for ground based simulation test of propellant management in microgravity-variable speed environment according to claim 4, wherein in S2, the test conditions of the test object in the test environment are divided into two types, including static condition test and dynamic condition test, and the test object is tested for multiple times under the static condition and the dynamic condition respectively;
under the static working condition state, the large model storage tank is selected as the test object, and the absolute ethyl alcohol is selected as the test fluid medium;
and under the dynamic working condition state, the small model storage tank is selected as the test object, and the fluorinated liquid FC-72 is selected as the test fluid medium.
6. The method for ground based simulation test of propellant management in a microgravity-variable speed environment as claimed in claim 5, wherein in the step S3, the simulation process is:
establishing a theoretical model according to the infiltration phenomenon of liquid and solid;
solving the free interface flow problem of the propellant according to an interface tracking method (VOF method) established under an Euler grid, repositioning characteristic time values of each process by establishing a control equation for describing fluid motion and according to a dimensionless parameter Bode equation of fluid mechanics,
wherein the bond number is defined as:
BO＝aR2/β
wherein β is σ/ρ,
the characteristic time values of the relocation processes are respectively expressed as:
t1indicating that the liquid has reached the bottom of the tank; t is t2Representing a fountain impact gas-liquid interface; t is t3Showing the fountain colliding with the roof of the tank; t is t4Indicating that liquid is exiting the top of the tank; t is t5Indicating that the gas fraction at the exit and in the vicinity is less than 5%;
t is obtained by numerical simulation calculation1、t2、t3、t4、t5。
7. The ground-based simulation test method for propellant management in a microgravity-variable speed environment according to claim 5, wherein in the step S12, the device comprises an acceleration application module (2), an optical recording module (3) and a data acquisition and processing module (4);
the acceleration applying module (2) is used for applying acceleration along a falling direction to the simulation test storage tank which freely falls in a falling cabin, the optical recording module (3) is arranged on one side of the simulation test storage tank and is used for observing the motion process of a test fluid medium in the simulation test storage tank, and the data acquisition and processing module (4) is in signal connection with the optical recording module (3) and is used for acquiring and storing information observed and recorded by the optical recording module (3);
the acceleration applying module (2) applies different forces to the simulation test storage box to generate different accelerations, the accelerations are determined according to different sizes and different working condition conditions, and the acceleration is set as amAnd is and
am＝a(ρ/ρm)(R/Rm)2(σm/σ)
a is amThe selection of the model is determined according to the size of the model storage tank and the physical property parameters of the experimental liquid.
8. The ground simulation test method for propellant management in microgravity-variable speed environment according to claim 3, wherein the variable thrust application module (2) comprises a long straight guide rail (21), an object stage (22) and a motor drive unit (23), the simulation test tank is arranged on the object stage (22), the object stage (22) is slidably mounted on the long straight guide rail (21), the motor drive unit (23) is connected with the object stage (22) and drives the object stage (22) to move and drive the simulation test tank to move at variable speed, the acceleration application module (2) is connected with an external control module (5), and the external control module (5) is connected with the motor drive unit (23);
the external control module (5) is used for sending a control instruction when receiving a trigger signal so as to regulate and control the motor driving unit (23) to drive the object stage (22) to move according to set motion parameters, and therefore a set acceleration value is applied to the simulation test storage box.
9. The ground-based simulation test method for propellant management in a microgravity-variable speed environment according to claim 8, wherein the simulation test tank comprises a first semi-circular tank body (11) and a second semi-circular tank body (12), the first tank body (11) and the second tank body (12) are fixedly connected through a flange (8), a sealing block (9) is arranged at the end connection position of the first tank body (11) and the second tank body (12), and the sealing block (9) is used for tightly abutting the first tank body (11) and the second tank body (12);
the first box body (11) and the second box body (12) are colorless transparent sealed tank bodies, and the thickness of the box bodies is not more than two millimeters.
10. The foundation simulation test method for propellant management in microgravity-variable speed environment according to claim 9, wherein a plug-in base (7) is arranged at the bottom of the simulation test storage tank, the tank body is mounted on the objective table (22) through the plug-in base (7), and the plug-in base (7) comprises a connection base body (76), and a mounting groove (71), a plug-in boss (72), a mounting portion (73), a limit block (74) and a limit groove (75) which are arranged on the connection base body (71);
the mounting groove (71) is arranged at the top of the connecting seat body (76), the mounting parts (73) are arranged at two sides of the top of the mounting groove (71), and the mounting parts (73) are abutted to the first box body (11) and/or the second box body (12) through fastening bolts;
the limiting groove (75) is formed in the bottom of the connecting base body (76), the limiting blocks (74) are formed on two sides of the limiting groove (75), the opposite-insertion bosses (72) are arranged on the limiting blocks (74), the opposite-insertion bosses (72) protrude towards the outer side of the limiting blocks (74), mounting seats are arranged on the objective table, grooves corresponding to the shape of the bottom of the inserting base (7) in a concave-convex mode are formed in the mounting seats, and the opposite-insertion bosses (72) are correspondingly inserted into the mounting seats in a inserting mode.
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030056838A1 (en) * | 2001-09-21 | 2003-03-27 | Grayson Gary D. | Variable-gravity anti-vortex and vapor-ingestion-suppression device |
| RU2010149031A (en) * | 2010-11-30 | 2012-06-10 | Государственное образовательное учреждение высшего профессионального образования "Омский государственный технический университет" (R | METHOD FOR MODELING THE PROCESS OF GASIFICATION OF RESIDUES OF LIQUID ROCKET FUEL AND DEVICE FOR IMPLEMENTATION |
| CN102941929A (en) * | 2012-10-31 | 2013-02-27 | 北京控制工程研究所 | Microgravity experiment system and experiment method for verifying fluid transmission performance of plate type storage box |
| CN103017852A (en) * | 2012-12-28 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Method for measuring quantity of liquid propellant in storage tank |
| CN103293557A (en) * | 2013-04-08 | 2013-09-11 | 北京控制工程研究所 | Method for verifying performance microgravity test of hydraulic accumulator in plate-type propellant management device |
| KR101409939B1 (en) * | 2013-01-16 | 2014-06-20 | 한국항공우주연구원 | Ultra low temperature liquid propellant collecting apparatus for reigniting propulsion engine of rocket |
| US20180281992A1 (en) * | 2015-04-22 | 2018-10-04 | Keystone Engineering Company | Center of mass control of liquid tanks for spacecraft use |
| CN113343372A (en) * | 2021-04-21 | 2021-09-03 | 中国人民解放军63921部队 | Ellipsoid-bottom cylindrical propellant storage tank equivalent stress analysis method |
-
2021
- 2021-12-27 CN CN202111611453.4A patent/CN114112307B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030056838A1 (en) * | 2001-09-21 | 2003-03-27 | Grayson Gary D. | Variable-gravity anti-vortex and vapor-ingestion-suppression device |
| RU2010149031A (en) * | 2010-11-30 | 2012-06-10 | Государственное образовательное учреждение высшего профессионального образования "Омский государственный технический университет" (R | METHOD FOR MODELING THE PROCESS OF GASIFICATION OF RESIDUES OF LIQUID ROCKET FUEL AND DEVICE FOR IMPLEMENTATION |
| CN102941929A (en) * | 2012-10-31 | 2013-02-27 | 北京控制工程研究所 | Microgravity experiment system and experiment method for verifying fluid transmission performance of plate type storage box |
| CN103017852A (en) * | 2012-12-28 | 2013-04-03 | 中国人民解放军国防科学技术大学 | Method for measuring quantity of liquid propellant in storage tank |
| KR101409939B1 (en) * | 2013-01-16 | 2014-06-20 | 한국항공우주연구원 | Ultra low temperature liquid propellant collecting apparatus for reigniting propulsion engine of rocket |
| CN103293557A (en) * | 2013-04-08 | 2013-09-11 | 北京控制工程研究所 | Method for verifying performance microgravity test of hydraulic accumulator in plate-type propellant management device |
| US20180281992A1 (en) * | 2015-04-22 | 2018-10-04 | Keystone Engineering Company | Center of mass control of liquid tanks for spacecraft use |
| CN113343372A (en) * | 2021-04-21 | 2021-09-03 | 中国人民解放军63921部队 | Ellipsoid-bottom cylindrical propellant storage tank equivalent stress analysis method |
Non-Patent Citations (2)
| Title |
|---|
| LI, ZG 等: "《Simulating Propellant Reorientation of Vehicle Upper Stage in Microgravity Environment》", 《MICROGRAVITY SCIENCE AND TECHNOLOGY》 * |
| 陈亮 等: "低温推进剂贮箱压力变化的CFD仿真", 《航空动力学报》 * |
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