CN110017992A - A kind of liquid rocket dynamical system test run method and its device - Google Patents
A kind of liquid rocket dynamical system test run method and its device Download PDFInfo
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- 238000012360 testing method Methods 0.000 title claims abstract description 183
- 238000005183 dynamical system Methods 0.000 title claims abstract description 94
- 238000000034 method Methods 0.000 title claims abstract description 36
- 239000007788 liquid Substances 0.000 title claims abstract description 34
- 239000003381 stabilizer Substances 0.000 claims abstract description 8
- 238000007405 data analysis Methods 0.000 claims abstract description 7
- 238000004458 analytical method Methods 0.000 claims abstract description 6
- 239000003380 propellant Substances 0.000 claims description 30
- 238000009434 installation Methods 0.000 claims description 21
- 230000008569 process Effects 0.000 claims description 19
- 230000005540 biological transmission Effects 0.000 claims description 10
- 238000009825 accumulation Methods 0.000 claims description 4
- 238000004891 communication Methods 0.000 claims description 4
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- 239000003795 chemical substances by application Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000010304 firing Methods 0.000 description 4
- 239000007800 oxidant agent Substances 0.000 description 4
- 230000001590 oxidative effect Effects 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Natural products C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 230000002159 abnormal effect Effects 0.000 description 1
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- 239000000945 filler Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000003100 immobilizing effect Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
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Abstract
The present invention discloses a kind of liquid rocket dynamical system testing device and its method, and for the dynamical system section with landing bracket, which includes multiple lower margin fixed cells, counterweight element, control unit of engine, data acquisition measuring unit and analytical unit；Wherein, multiple lower margin fixed cells are respectively used to accept each stabilizer blade of the fixed landing bracket, the counterweight element is arranged on the landing bracket and/or the inside of dynamical system section, the control unit of engine is used to control the start stop operation of engine, the data acquisition measuring unit is used to acquire the trial condition parameter of dynamical system section, the analytical unit acquires the trial condition parameter of measuring unit acquisition according to the data and preset condition carries out data analysis, to obtain analysis result.It can effectively reduce test run cost on the basis of obtaining good examination effect using this programme.With good application prospect.
Description
Technical field
The present invention relates to rocket test run technical fields, and in particular to a kind of liquid rocket dynamical system test run method and its dress
It sets.
Background technique
Initial stage is developed in liquid rocket dynamical system, system design correctness is carried out by dynamical system test run
Confirmation can with verify product including the applicability etc. of the matching and product quality control method that work between each subsystem
By property.Therefore, dynamical system test run is examination important before dynamical system product delivers liquid rocket general assembly, verifying link.
It is well known that for liquid rocket dynamical system test run, since propellant is liquid medium, dynamical system portion
Section needs to be in plumbness in test run, and engine is located at below section, in favor of the normal conveying of propellant.The prior art
In, liquid rocket dynamical system test run technology mainly includes two kinds of typical dynamical system test run schemes also in developing stage.
One is the static firings that rocket is carried out on transmitting station, such as the transmitting station static firing of SpaceX company to try
It tests, the rocket for completing general assembly is placed on rocket launching pad and carries out corresponding test run test.It is limited by its specific implementation,
The test run scheme has the disadvantage that
It 1) is to be carried out under the conditions of rocket completes general assembly, once causing danger, loss is more huge, to the maturation of product
Degree requirement is higher, is suitable for the product mature application stage；That is, the test run scheme can not be suitable for the research and development of products stage.
2) in addition, the construction of transmitting station used in the program needs bigger capital investment.
Another kind is the dynamical system test run carried out on test bay by traditional mode, and dynamical system section passes through test run
Platform keeps perpendicular attitude to erect, and connect and fix with pylon by special interface.This solution provides multilayer working platform,
It can functionally support the dynamical system test run of large rocket.However, the limitation for the platform anatomic structures that are put to the test, there are it is following not
Foot:
1) test bay is affected to mechanics vibration environment, influences examination effect.
For the dynamical system test bay in order to carry, fix dynamical system section, itself usual design comparison is thick and heavy, have than
Relatively firm feature, but the problem excessive there may be nargin.Excessively thick and heavy then presence changes original when power system operational
The case where mechanics vibration environment is distributed, or weaken mechanical environment vibration level, said circumstances will generate test run examination effect
It influences, so that the problem that should be exposed in test run becomes slight and ignored.Obviously, the event in terms of above-mentioned such as mechanical environment
Barrier hidden danger is brought into the actual flying test of rocket, and more serious consequence is caused.
2) test bay interface relationship is complicated, influences examination effect.
Other than normal load interface structure, gas supply feed flow, test etc. will also rely on test bay guarantee, cause to connect
It makes a slip of the tongue more.The complexity of test technology and the difficulty of coordination are not only increased, and is possible to change the original state of product,
Reduce the effect of examination.
3) test run prepares link increase, and run-in period extends.
Experiment process designs the process of self-test for being related to test bay, product and docks link with test bay, moreover, product exists
The total system matching test of product and test bay is increased after docking with test bay, to confirm the matching, correct of all multiplex roles
Property；And whether state of the product after appearing on the stage be normal (product may impact platform to product itself state in the process),
Run-in period is caused to be significantly increased.
4) construction investment is huge.
The construction infusion of financial resources demand of the test bay reaches more than one hundred million members, while construction period also will be at 1 year or more, can not
Business aerospace enterprise group suitable for establishment.
In view of this, it would be highly desirable to look for another way and be optimized for existing liquid rocket dynamical system test run technology, with effective
Take into account examination effect and test run cost.
Summary of the invention
In order to solve the above technical problems, the present invention provides a kind of liquid rocket dynamical system testing device and its method,
On the basis of obtaining good examination effect, test run cost can effectively reduce.
Liquid rocket dynamical system testing device provided by the invention, for the dynamical system section with landing bracket,
Including multiple lower margin fixed cells, counterweight element, control unit of engine, data acquisition measuring unit and analytical unit；Wherein,
Multiple lower margin fixed cells are respectively used to accept each stabilizer blade of the fixed landing bracket, and the counterweight element is arranged in institute
It states on landing bracket and/or the inside of dynamical system section, the control unit of engine is used to control the start and stop behaviour of engine
Make, the data acquisition measuring unit is used to acquire the trial condition parameter of dynamical system section, and the analytical unit is according to institute
The trial condition parameter and preset condition for stating data acquisition measuring unit acquisition carry out data analysis, to obtain analysis result.
Preferably, the lower margin fixed cell is embedded in carrying base, and the carrying base offers the hair
The diversion trench that the jet pipe of motivation is oppositely arranged.
Preferably, the lower margin fixed cell includes more rounded arrangement vertical bars, and adjacent two in the more vertical bars
Root is fixedly connected sequentially by cross bar, and the cross bar be from top to bottom set to it is multiple rows of；The top of the more vertical bars has
The installation interface being adapted to the stabilizer blade of the landing bracket.
Preferably, it is fixedly installed connecting flange at the top of the more vertical bars, is provided on the connecting flange described
Interface is installed, and the top surface of the connecting flange is flushed with the surface of the carrying base.
Preferably, the analytical unit is ground installation, and the control unit of engine and data acquisition measurement are single
The signaling interface of member establishes communication connection, and the two power supply by signal cable or wireless transmission with the analytical unit respectively
Interface passes through feed cable respectively and is electrically connected with ground power supply foundation.
Preferably, the control unit of engine and the controller of data acquisition measuring unit use the dynamical system
The controller for section of uniting, or using the controller independently of the dynamical system section.
Preferably, the counterweight element is made of the material compatible with the propellant of the liquid rocket dynamical system.
It preferably, further include the charging line and discharge pipe being connected to the propellant tank of the dynamical system section,
The other end of the charging line and the discharge pipe is connected to propellant source respectively.
Preferably, the propellant source uses, and there is propellant to transport tank car, and the propellant transport tank car has filling
Control system.
The present invention also provides a kind of liquid rocket dynamical system test run methods, by the landing to the dynamical system section of test run
Bracket is fixedly installed on multiple lower margin fixed cells, and installs the counterweight element；After completing igniting preparation, according to default
Engine ignition test run process carry out test run operation, data analysis is carried out according to trial condition parameter and preset condition.
Preferably, the preset engine ignition test run process includes the operation of test run for the first time and whole examination successively executed
Vehicle operation；Wherein, the operation of test run for the first time is specially to enter shutdown programm after engine completes start-up course；The whole process
Test run operation is specially consistent with the practical flight operating condition of the dynamical system section.
Preferably, second of test run operation and third time are also executed between the operation of test run for the first time and whole test run operation
Test run operation；Wherein, second of test run operation is specially to increase on the basis of the time installation that the test run for the first time operates
There is the first pre-determined stability working time, the third time test run operation is specially on the time installation basis that second of test run operates
Upper increase had the second pre-determined stability working time.
Preferably, the second pre-determined stability working time is 2~5 times of the first pre-determined stability working time.
Preferably, subsequent test run operation is executed after the whole test run operation, the subsequent test run operation is specially described
The accumulation of dynamical system section working time.
For liquid rocket dynamical system test run scheme, the present invention, which looks for another way, is optimized design, makes full use of production
Product homegrown resource completes test run.Specifically, it is accepted and is fixed using the landing bracket of dynamical system section and lower margin fixed cell, together
When matching setting counterweight element obtain the stability margin of fixed form, realize being reliably fixed in commissioning process；Test run operation
In the process, the liquid propellant tank and pressurizing transmission system carried using dynamical system section, can meet engine ignition
The operating condition of work is applicable to 10t grades of dynamical system test runs.Compared with prior art, this programme has following beneficial skills
Art effect:
Firstly, having good examination effect.Landing bracket and lower margin fixed cell based on dynamical system section, we
Case has effectively evaded the problem of original mechanics vibration environment of the excessively thick and heavy influence dynamical system of testing stand is distributed, so that test run
The mechanical environment of examination effect and actual motion reaches unanimity；In addition, being store using the liquid propellant that dynamical system section carries
Case and pressurizing transmission system etc. reach engine start stop operation, eliminate the interfaces such as a large amount of external gas supply feed flow, test, reduce
The complexity of test technology and the difficulty of coordination, to effectively evade the possibility for changing product original state.So set,
The precision of examination effect can be greatly promoted.
Secondly, effectively reducing test run cost.On the one hand, the resource that this programme maximumlly utilizes product own simplifies
Dependence to ground installation, device investment is lower, can reach civilian level.Only need to improve the state of product itself before test run i.e.
Can have test run condition, eliminate the self-test of ground installation and coordinate the workload docked with ground installation, to substantially save
Capital investment simultaneously shortens the lead time.In addition, this programme can be realized the test run test of dynamical system section, even if occurring
When the extreme risk of one kind of exploding, product itself is only lost, loss can be greatly reduced compared to the scheme of traditional test bay.
Again, the test run method that this programme provides, the condition based on engine test is carried out, while being aided with incremental
Test method is analyzed by firing test data having dispersed risk by way of being stepped up the time of each test run, be conducive to and
Shi Faxian risk hidden danger, can effectively reduce the probability of happening of extreme risk.
Detailed description of the invention
Fig. 1 is the use state diagram of liquid rocket dynamical system testing device described in specific embodiment；
Fig. 2 is the structural schematic diagram of lower margin fixed cell shown in Fig. 1；
Fig. 3 is the assembly relation schematic diagram of lower margin fixed cell shown in Fig. 1.
In figure:
Instrument room 1, oxidant tank 2, incendiary agent tank 3, delivery pipe 4, engine 5, landing bracket 6, the first counterweight 71,
Second counterweight 72, control unit of engine 81, data acquisition measuring unit 82, analytical unit 83, lower margin fixed cell 9, installation
Interface 91, vertical bar 92, cross bar 93, connecting flange 94, carrying base 10, diversion trench 101.
Specific embodiment
It is with reference to the accompanying drawing and specific real in order to make those skilled in the art more fully understand technical solution of the present invention
Applying example, the present invention is described in further detail.
Without loss of generality, present embodiment is using dynamical system section shown in Fig. 1 as description main body, clearly to illustrate this
Apply for the liquid rocket dynamical system test run scheme proposed.Test run test is carried out after the completion of the dynamical system section general assembly, by upper
It is disposed with instrument room 1, oxidant tank 2, incendiary agent tank 3, delivery pipe 4 and engine 5 under, there is included landing
The auxiliary such as bracket 6 and pressurizing transmission system are constituted.It should be appreciated that the above-mentioned functional component Fei Benshen to test run dynamical system section
Where central inventive point please, specific implementation does not constitute substantial limit to the claimed technical solution of the application.
Referring to Figure 1, this illustrates liquid rocket dynamical system testing device described in present embodiment.
The testing device can steadily fix the dynamical system section to test run.Specifically include the ground of multiple fixed settings
Foot fixed cell 9, each lower margin fixed cell 9 correspond to each stabilizer blade 61 of landing bracket 6, and accept fix respectively.It is somebody's turn to do
Land bracket 6 and the interface of dynamical system section cover carrying design and power transmission design, matching via master-plan
It is good.
Wherein, counterweight element may be provided on landing bracket 6, may also be arranged on the inside of dynamical system section；As schemed
To show, the first counterweight 71 is placed on landing bracket 6, and the second counterweight 72 is placed in the top storehouse of dynamical system section, certainly, counterweight list
The configuration of member should be contemplated that circumferential load equalization on the whole.
In order to avoid the abnormal leakage of propellant may cause safety problem, counterweight element is used and liquid rocket dynamical system
The material that the propellant of system is compatible is made, that is to say, that no matter in which way the first counterweight 71 and the second counterweight 72, are such as fallen
It falls, immerse, when touching propellant, will not all be chemically reacted with propellant, therefore ensure that the safety of trial run and run can
By property.
Wherein, control unit of engine 81 is used to control the start stop operation of its engine, and data acquire measuring unit 82 and use
In the trial condition parameter of acquisition dynamical system section, analytical unit 83 acquires the test run shape that measuring unit 82 acquires according to data
State parameter and preset condition carry out data analysis, to obtain analysis result.Here, " preset condition " is to judge dynamical system section
Trial condition parameter whether meet the design requirement of corresponding product, can be specifically determined according to master-plan index.When
So, should " preset condition " be not limited to specific value, generally according to needing to be set as corresponding threshold range.
Specifically, the immobilizing foundation of lower margin fixed cell 9 can have some strength for ground or prefabricated formed
Base 10 is carried, by taking ground as an example, lower margin fixed cell 9 is preferably embedded in ground, and offers the spray of engine 5 on ground
The diversion trench 101 that pipe 51 is oppositely arranged, to form the space for adapting to engine row's flame, so that it is high to support the high temperature being discharged by engine
Compression ignition gas is simultaneously guided to safe direction and is released.Similarly, 101 specific size of diversion trench and requirement resistant to high temperature can bases
It is determined in design basis.
It should be noted that the specific constructive form of the lower margin fixed cell 9 can be realized using various structures mode, and
Shape can be also not intended to be limited in any, as long as forming the installation interface 91 being adapted to the stabilizer blade 61 of landing bracket 6 at the top of it, and shape
Within the scope of the present application at firm connection relationship.Certainly, the stress of the lower margin fixed cell 9 and carrying root
It is determined according to dynamical system test run scale.
Preferably, please also refer to Fig. 2 and Fig. 3, wherein Fig. 2 is the structural schematic diagram of lower margin fixed cell, and Fig. 3 is
The assembly relation schematic diagram of the lower margin fixed cell.
As shown in Fig. 2, the lower margin fixed cell 9 includes more rounded arrangement vertical bars 92, it is adjacent in more vertical bars 92
Two are fixedly connected sequentially by cross bar 93, cross bar 93 have it is multiple rows of, and from top to bottom interval setting, stable structure is consequently formed
Lower margin fixed cell 9, manufacturing cost is relatively low.Here, there is the stabilizer blade 61 with landing bracket 6 at the top of more vertical bars 92
The installation interface 91 of adaptation.
Can be in the fixed further setting connecting flange 94 in the top of more vertical bars 92, and be provided on connecting flange 94
Interface 91 is installed, is reliably connected in order to be realized using threaded fastener with corresponding pin 61.It is enclosed by vertical bar 92 and cross bar 93
It closes the lower margin fixed cell 9 formed and different modes can be used and embed and be limited to ground, such as, but not limited to concrete prefabricated mode
It is fixed, the top surface of the connecting flange 94 after the completion of being embedded in is flushed with ground surface.So set, fixed structure is placed in earth's surface
Face can also reduce the center of gravity of superstructure hereinafter, in addition to stabilized structure, and then it is steady to be greatly improved the operation in commissioning process
It is qualitative.
In addition, analytical unit 83 is ground installation, Ground analysis workplace specifically may be provided at；Correspondingly, engine control
Unit 81 processed and the signaling interface of data acquisition measuring unit 82 establish communication link by signal cable with analytical unit 83 respectively
It connects, naturally it is also possible to establish communication connection by the way of wireless transmission.Control unit of engine 81 and data acquisition measurement are single
First 82 power interfaces pass through feed cable respectively and are electrically connected with ground power supply foundation.It is understood that ordinary skill
Personnel can realize upper signal connection and electrical connection based on the prior art, and therefore, this article will not repeat them here.
Wherein, the controller of control unit of engine 81 can use the controller of dynamical system section itself, or adopt
With the controller independently of the dynamical system section.Certainly, using the controller of dynamical system section itself, under trial condition,
Need to be disconnected with arrow on control system (bus) connection, cooperation be electrically connected between ground and signal transmission connection, i.e.,
The primary demand of test run control operation can be met.
Similarly, the controller of dynamical system section can also be used in the controller of data acquisition measuring unit 82, or adopts
With the controller independently of dynamical system section.
This programme further includes being connected to the propellant tank of dynamical system section (oxidant tank 2, incendiary agent tank 3)
The other end of charging line and discharge pipe, charging line and discharge pipe is connected to (not shown) with propellant source respectively.
As further preferred, propellant source uses, and there is propellant to transport tank car, and propellant, which transports tank car, has filling control system.
So set, be only made of filling, discharge pipe and tank car using the charging method based on propellant transport tank car, particularly,
For 10t grades of dynamical system test runs, filling can be completed using the control system that tank car carries, significantly reduce cost.
This programme preferably uses liquid oxygen methane propellant, because liquid oxygen/methane has low cost, easily acquisition, purity is high, specific impulse
Performance is high, and sparking mode is simple, it is easy to accomplish repeatedly lights a fire, without the advantages that cleaning after engine test, to be this programme
Carry out dynamical system test run based on homegrown resource and is possibly realized the technical guarantee that provides the foundation.
In addition to aforementioned liquids Rocket propulsion system testing device, present embodiment also provides a kind of liquid fire of application apparatus
Landing bracket to the dynamical system section of test run is specifically fixedly installed on multiple institutes by arrow dynamical system test run method
Lower margin fixed cell is stated, and counterweight element is installed；After completing igniting preparation, carried out according to preset engine ignition test run process
Test run operation carries out data analysis according to trial condition parameter and preset condition.
The execution process of test run method described in present embodiment, is summarized as follows:
Step S1, product prepare.
The preparation of dynamical system section includes that product completes general assembly, completes the proving run of electrical system, dynamical system
Test.Also, engine has succeeded test run, and here, engine belongs to component or single machine most crucial in dynamical system test run, together
When be also total system power, thermal environment condition source.Whether its own state quality directly determines can in dynamical system test run
There is catastrophic failure, the liquid-propellant rocket engine to test run should successfully complete engine test.
Step S2, assembling product.Product is erect to test run region, landing bracket is connect and fixed with foundation bolt；
And complete the installation of counterweight element.
Step S3 completes igniting and prepares.It specifically includes and completes oxidant tank 2, incendiary agent tank 3 and pressure-increasing unit pipeline
The airtight test of equal air-channel systems；Meanwhile complete the connection of power supply and signal cable, and by repropellenting pipeline one end with
The connection of tank filler, the other end is connect with the outlet(discharge) flange of propellant transport tank car, after propellant completes filling, removes filling
Pipeline, transport tank car are withdrawn.
Step S4 carries out test run operation according to preset engine ignition test run process, according to trial condition parameter and in advance
If condition carries out data analysis.
Here, which can be designed based on difference to test run product, specific to wrap
Include the following test run operation successively executed:
1) test run for the first time operates.The test run for the first time operation is specially to enter shutdown journey after engine completes start-up course
Sequence；That is, time installation is the summation of engine start unused time for the first time, generally within 8s.I.e. engine is completed
Shutdown programm is immediately entered after start-up course.This stage can verify whether engine starts shutdown under the conditions of system-wide
Normally；Simultaneously as pressurizing transmission system is synchronous with the starting of engine, therefore it can check the starting of pressurizing transmission system
It is whether normal；On the other hand, in engine starting process, power, thermal environment are also increasing, and can find the change of environmental condition in time
Change whether beyond expected and influence to support construction etc., convenient for being taken timely measure before test run next time.
2) second of test run operates.Second of test run operation is specially the time installation base operated in the test run for the first time
Increasing on plinth had the first pre-determined stability working time, such as, but not limited to, on the basis of first time, test run was normal, second of examination
The vehicle time is the steady operation section time for increasing by 5~10s on the basis of first time test run.That is engine start is to rated condition
Afterwards, the stable work time of 5~10s is kept under rated condition.May determine that engine performance, pressurizing transmission system performance,
Whether the power thermal environment of generation meets expection.
3) third time test run operates.Third time test run operation is specially on the time installation basis that second of test run operates
Upper increase had the second pre-determined stability working time, wherein the second pre-determined stability working time was the first pre-determined stability working time
2~5 times, namely on the basis of second of test run by the stable section working time increase by 2~5 times.Each subsystem of main detection
With the performance indicator of single machine whether there is or not exceeding expected variation, and judge whether the trend that oriented unfavorable direction is developed.
4) whole test run operation.Whole process test run operation is specially the practical flight operating condition one with the dynamical system section
It causes.After being judged preceding test run three times normally, whole test run can be carried out and time installation reaches dynamical system section in reality
Working time in-flight.Total system is verified, it is considered that dynamical system test run task is completed after total system is succeeded in the test run.
5) subsequent test run operation.The subsequent test run operation is specially the accumulation of the dynamical system section working time.Entirely
After the completion of journey test run, it can decide whether to carry out subsequent test run as needed.Test run later mainly accumulates power system operational
Time verifies the reliability of product；The followed by service life knows the real situation test, test dynamical system product when working normally it is attainable most
Long accumulation or stream time.
It should be noted that the preset engine ignition test run process in the test run method, wherein second of test run is grasped
Work, third time test run operation and subsequent test run operation can be selected according to specific product master-plan, theoretically simultaneously
It is unrestricted in here it is preferable to determine test run number of operations.
Particularly, the progressive relationship of above-mentioned test run number of operations is one of the central inventive point of the application, by gradually increasing
Add the mode of the time of each test run to disperse risk, analyzed by firing test data, is conducive to find risk hidden danger in time, effectively
Reduce loss when occurrence risk.The application of equivalent way is carried out in the application using the design concept as long as should be appreciated that
In the range of being claimed.
The above is only the preferred embodiment of the present invention, it is noted that those skilled in the art are come
It says, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications also should be regarded as
Protection scope of the present invention.
Claims (14)
1. a kind of liquid rocket dynamical system testing device, for the dynamical system section with landing bracket, which is characterized in that
Include:
Multiple lower margin fixed cells are respectively used to accept each stabilizer blade of the fixed landing bracket；
Counterweight element, is arranged on the landing bracket and/or the inside of dynamical system section；
Control unit of engine, for controlling the start stop operation of engine；
Data acquire measuring unit, for acquiring the trial condition parameter of dynamical system section；
Analytical unit acquires the trial condition parameter of measuring unit acquisition according to the data and preset condition carries out data point
Analysis, to obtain analysis result.
2. liquid rocket dynamical system testing device according to claim 1, which is characterized in that the lower margin fixed cell
It is embedded in carrying base, and the carrying base offers the diversion trench that the jet pipe of the engine is oppositely arranged.
3. liquid rocket dynamical system testing device according to claim 1, which is characterized in that the lower margin fixed cell
Including more rounded arrangement vertical bars, adjacent two in the more vertical bars are fixedly connected sequentially by cross bar, and the cross bar
It is from top to bottom set to multiple rows of；There is the installation being adapted to the stabilizer blade of the landing bracket to connect at the top of the more vertical bars
Mouthful.
4. liquid rocket dynamical system testing device according to claim 3, which is characterized in that the top of the more vertical bars
Portion is fixedly installed connecting flange, is provided with the installation interface on the connecting flange, and the top surface of the connecting flange with
The surface of the carrying base flushes.
5. liquid rocket dynamical system testing device according to any one of claim 1 to 4, which is characterized in that described
Analytical unit is ground installation, the control unit of engine and the data acquisition measuring unit signaling interface respectively with institute
It states analytical unit and communication connection is established by signal cable or wireless transmission, and the two power interface passes through feed cable respectively
It is electrically connected with ground power supply foundation.
6. liquid rocket dynamical system testing device according to claim 5, which is characterized in that the engine control is single
The controller of the first and described data acquisition measuring unit uses the controller of the dynamical system section, or using independently of institute
State the controller of dynamical system section.
7. liquid rocket dynamical system testing device according to claim 1, which is characterized in that the counterweight element uses
The material compatible with the propellant of the liquid rocket dynamical system is made.
8. liquid rocket dynamical system testing device according to claim 1, which is characterized in that further include and the power
The charging line and discharge pipe of the propellant tank connection of system section, the charging line and the discharge pipe it is another
End is connected to propellant source respectively.
9. liquid rocket dynamical system testing device according to claim 8, which is characterized in that the propellant source uses
Tank car is transported with propellant, the propellant transport tank car has filling control system.
10. using the test run method of liquid rocket dynamical system testing device described in any one of claims 1 to 9, feature
It is, the landing bracket to the dynamical system section of test run is fixedly installed on multiple lower margin fixed cells, and institute is installed
State counterweight element；After completing igniting preparation, test run operation is carried out according to preset engine ignition test run process, according to test run shape
State parameter and preset condition carry out data analysis.
11. test run method according to claim 10, which is characterized in that the preset engine ignition test run process packet
Include the operation of test run for the first time successively executed and whole test run operation；Wherein, the operation of test run for the first time is specially that engine is completed
Enter shutdown programm after start-up course；The whole process test run operation is specially the practical flight work with the dynamical system section
Condition is consistent.
12. test run method according to claim 11, which is characterized in that the operation of test run for the first time and whole test run operation
Between also execute second of test run operation and third time test run operation；Wherein, second of test run operation is specially described
Increasing on the basis of the time installation of the operation of test run for the first time had the first pre-determined stability working time, and the third time test run operation is specific
For operated in second of test run time installation on the basis of increase had the second pre-determined stability working time.
13. test run method according to claim 12, which is characterized in that the second pre-determined stability working time is described
2~5 times of first pre-determined stability working time.
14. test run method according to claim 13, which is characterized in that execute subsequent test run after the whole process test run operation
Operation, the subsequent test run operation are specially the accumulation of the dynamical system section working time.
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