CN209535509U - A kind of ground system test of Space radiation - Google Patents
A kind of ground system test of Space radiation Download PDFInfo
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- CN209535509U CN209535509U CN201821990927.4U CN201821990927U CN209535509U CN 209535509 U CN209535509 U CN 209535509U CN 201821990927 U CN201821990927 U CN 201821990927U CN 209535509 U CN209535509 U CN 209535509U
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Abstract
The utility model is suitable for space flight and promotes ground experiment field, provides a kind of ground system test of Space radiation, which includes: software analog subsystem, for mature assembly module to be modeled to simulated assembly module；Subsystem in kind, including each testing component module；Data acquisition control subsystem, the software analog subsystem, subsystem in kind realize data exchange by the data acquisition control subsystem；The software analog subsystem, subsystem in kind and data acquisition control subsystem are modeled to complete Space radiation.The utility model embodiment simulated assembly module mature by the simulation of software analog subsystem, make Space radiation that need not build complete system when carrying out system testing, and simulated assembly module and testing component module simulation is used to be tested at complete Space radiation, the test for realizing testing component module and complete machine, can greatly reduce complete machine lead time and testing expenses.
Description
Technical field
The utility model belongs to space flight and promotes ground experiment field more particularly to a kind of ground experiment of Space radiation
System.
Background technique
Space radiation, also known as " dynamical system " or " power device " are to be made using self-contained working medium by anti-
The system of thrust or torque is directly generated with principle.Space radiation is the chief component of aircraft.
Space radiation needs to carry out a large amount of ground experiment before being flown.However traditional ground experiment point
It is tested for component level product testing and Complex Structural System；Component level product testing is according to given experimental condition to needing to test
Subassembly product carry out routine tests, be only suitable for component level product testing, and Complex Structural System test produces all components
Product, which assemble, to be tested, can not to component level product carry out routine tests, this resulted in single products cannot combine it is whole
A system is tested for the property, and Complex Structural System test needs aptitude tests after all components assembling, this just needs huge
Testing cost.
Utility model content
The ground system test of the utility model embodiment offer Space radiation, it is intended to which how solve, which reduces space flight, pushes away
Into system ground experiment cost the problem of.
The utility model embodiment is achieved in that a kind of ground system test of Space radiation, the ground
Pilot system includes:
Software analog subsystem, for mature assembly module to be modeled to simulated assembly module；
Subsystem in kind, including each testing component module；
Data acquisition control subsystem, the software analog subsystem, subsystem in kind pass through the data acquisition control
Subsystem realizes data exchange；
The software analog subsystem, subsystem in kind and data acquisition control subsystem are modeled to complete space flight and promote
System.
Further, the data acquisition control subsystem is also used to the testing component mould in the subsystem in kind
Block parameter is acquired, controls.
Further, the software analog subsystem includes simulation pipeline, and by the mould of the simulation piping connection
Quasi- gas cylinder module, simulation gas circuit electric detonation valve module, simulation decompression valve module, simulation tank module, simulation fluid path electric blasting valve module,
Simulated engine module, when one or more modules in the software analog subsystem are disabled, forbidden module is by reality
Object subsystem replaces.
Further, the subsystem in kind include depressurize valve module, tank module, one in engine block or
Multiple modules.
Further, the data acquisition control system be used for the decompression valve module of subsystem in kind, tank module,
The parameter of any one or more modules is controlled, is acquired in engine block.
Further, the decompression valve module goes out including pressure reducing valve in kind, pressure reducing valve inlet pressure sensor, pressure reducing valve
Mouth pressure sensor, pressure reducing valve gas supply department, decompression valve inlet, decompression valve outlet.
Further, the tank module includes reservoir inlet pressure sensor, and reservoir outlet pressure sensor is in kind
Tank, tank gas supply department, liquid recovery part, reservoir inlet, reservoir outlet.
Further, the engine block includes engine inlet pressure sensor, engine, Propellant Supply
Portion, motor inlet.
Mature assembly module is modeled to simulated assembly module by software analog subsystem by the utility model embodiment,
Make Space radiation that need not build complete system when carrying out system testing, and uses simulated assembly module and testing component
Module simulation is tested at complete Space radiation, convenient for examining testing component module in entire Space radiation
Attribute of performance and adaptability to entire Space radiation, realize the test of testing component module and complete machine, can be significantly
The reduction complete machine lead time and testing expenses.
Detailed description of the invention
Fig. 1 is functional-block diagram provided by the embodiment of the utility model；
Fig. 2 is the block diagram that another embodiment of the utility model provides.
Specific embodiment
In order to make the purpose of the utility model, technical solutions and advantages more clearly understood, below in conjunction with attached drawing and implementation
Example, the present invention will be further described in detail.It should be appreciated that specific embodiment described herein is only used to explain
The utility model is not used to limit the utility model.
The utility model embodiment is provided with software analog subsystem, data acquisition control subsystem, is simulated by software
Mature assembly module is modeled to simulated assembly module by subsystem, then realizes software by the data acquisition control subsystem
The data exchange of analog subsystem, subsystem in kind, build Space radiation need not when carrying out system testing completely
System, and simulated assembly module and testing component module simulation is used to be tested at complete Space radiation, convenient for inspection
Attribute of performance of the testing component module in entire Space radiation and the adaptability to entire Space radiation are tested, is realized
The test of testing component module and complete machine can greatly reduce complete machine lead time and testing expenses.
As shown in Figure 1, the utility model provides a kind of ground system test of Space radiation, the ground system test
It include: software analog subsystem 1, for simulating mature simulated assembly module；Subsystem 2 in kind, including each testing component mould
Block；Data acquisition control subsystem 3, the software analog subsystem 1, subsystem 2 in kind pass through data acquisition control
System 3 realizes data exchange；The software analog subsystem 1, subsystem 2 in kind and data acquisition control subsystem 3 are modeled to
Complete Space radiation.The data acquisition control subsystem 3 is also used to the testing component mould in the subsystem 2 in kind
Block parameter is acquired, controls.Specifically, software analog subsystem is responsible for the performance of the mature assembly module of simulation, given
Parametric environmental in can calculate the output characteristics of product；Data collection system can acquire any to be measured in subsystem in kind
The input parameter and output parameter of assembly module, can also be with the input of arbitrarily simulate assembly module in acquisition software analog subsystem
Parameter and output parameter, and the parameter information in subsystem in kind and software analog subsystem is subjected to real-time exchange；Son in kind
System is responsible for the test of testing component module (i.e. actual products).
Wherein, which includes simulation pipeline, and by the simulation gas cylinder mould of the simulation piping connection
Block 11, simulation gas circuit electric detonation valve module 12, simulation decompression valve module 13, simulation tank module 14, simulation fluid path electric blasting valve module
15, simulated engine module 16, when one or more modules in the software analog subsystem 1 are disabled, forbidden mould
Block is replaced by subsystem 2 in kind.It is to be understood that when needing to test a certain testing component module, in software analog subsystem 1
The middle corresponding module of disabling, uses the testing component module to replace software simulated assembly module as subsystem 2 in kind, to be measured to this
Assembly module is tested.The utility model can apply a testing component module (newly grinding product or non-matured product)
Entire Space radiation workflow is realized in conjunction with software analog subsystem 1；Some testing component can be also examined simultaneously
Whether the working condition in entire Space radiation meets entire space flight to module (newly grinding product or non-matured product) pushes away
Into the performance requirement of system.
Mature assembly module is modeled to simulated assembly mould by software analog subsystem 1 by the utility model embodiment
Block, then by the data exchange of the data acquisition control subsystem 3 realization software analog subsystem 1, subsystem 2 in kind, make
Space radiation need not build complete system when carrying out system testing, and use simulated assembly module and testing component mould
Block is modeled to complete Space radiation and is tested, convenient for examining testing component module in entire Space radiation
Attribute of performance and adaptability to entire Space radiation realize the test of testing component module and complete machine, can be greatly
Reduce complete machine lead time and testing expenses.
In an alternative embodiment of the utility model, which only includes decompression valve module 21, tank mould
One or more modules in block 22, engine block 23.The data acquisition control system 3 is used for subtracting to subsystem 2 in kind
Pressure valve module 21, tank module 22, the parameter of any one or more modules is controlled, is acquired in engine block 23.Its
In, which includes material object pressure reducing valve 211, pressure reducing valve inlet pressure sensor 212, decompression valve outlet pressure biography
Sensor 213, pressure reducing valve gas supply department 214, decompression valve inlet 215, decompression valve outlet 216；The tank module 22 includes tank
Inlet pressure transducer 221, reservoir outlet pressure sensor 222, tank 223 in kind, tank gas supply department 224, liquid return
Receipts portion 225, reservoir inlet 226, reservoir outlet 227；The engine block 23 includes engine inlet pressure sensor 231, hair
Motivation 232, Propellant Supply portion 233, motor inlet 234 etc..The utility model embodiment can be to decompression valve module 21, tank
One or more modules in module 22, engine block 23 are tested.
The concrete operations mode of the utility model embodiment are as follows:
When being all mature component in Space radiation, the performance parameter of gas cylinder is input to simulation gas cylinder module 11
In, the parameter of gas circuit electric blasting valve is input in simulation gas circuit electric detonation valve module 12, and pressure reducing valve performance parameter is input to simulation decompression
Valve module 13, tank performance parameter are input to simulation tank module 14, fluid path electric blasting valve performance parameter is input to simulation fluid path electricity
Quick-fried valve module 15, engine performance parameter are input in simulated engine module 16, then carry out simulation calculating to whole system.
The system test of Space radiation can be realized by aforesaid operations.
As shown in Fig. 2, in the Space radiation decompression valve module 21 (or other modules) be newly grind product or it is non-at
When ripe product, simulation decompression valve module 13 in software analog subsystem 1 is disabled, replaces simulation pressure reducing valve with decompression valve module 21
Module 13, the outlet pressure and flow of the acquisition simulation gas circuit electric detonation valve module 12 of data acquisition control subsystem 13, according to this pressure
Power controls pressure reducing valve gas supply department 214, so that the pressure parameter of pressure reducing valve inlet pressure sensor 212 and simulation gas circuit electric detonation
The outlet pressure of valve module 12 is identical, depressurizes the flow parameter of valve inlet 215 and the outlet stream of simulation gas circuit electric detonation valve module 12
Pressure parameter that is identical, while acquiring pressure reducing valve outlet pressure sensor 213 is measured, the flow parameter of valve outlet 216 is depressurized, will flow
Amount parameter and pressure parameter collecting, pass to software analog subsystem 1, as simulation tank module 14 inlet pressure parameter and
Flow parameter is handed over by the data of software analog subsystem 1, data acquisition control subsystem 2 and subsystem 3 in kind in this way
It changes to form a completely new ground system test, Space radiation parameter is simulated.Production is newly ground in test through the above steps
The attribute of performance of product or non-matured product in Space radiation and the adaptability to entire Space radiation.
The above is only the preferred embodiment of the utility model only, is not intended to limit the utility model, all at this
Made any modifications, equivalent replacements, and improvements etc., should be included in the utility model within the spirit and principle of utility model
Protection scope within.
Claims (8)
1. a kind of ground system test of Space radiation, which is characterized in that the ground system test includes:
Software analog subsystem, for mature assembly module to be modeled to simulated assembly module；
Subsystem in kind, including each testing component module；
Data acquisition control subsystem, the software analog subsystem, subsystem in kind pass through the data acquisition control subsystem
System realizes data exchange；
The software analog subsystem, subsystem in kind and data acquisition control subsystem are modeled to complete space flight and promote system
System.
2. the ground system test of Space radiation as described in claim 1, which is characterized in that the data acquisition control
Subsystem is also used to be acquired the testing component module parameter in the subsystem in kind, control.
3. the ground system test of Space radiation as described in claim 1, which is characterized in that the software simulates subsystem
System includes simulation pipeline, and is subtracted by the simulation gas cylinder module of the simulation piping connection, simulation gas circuit electric detonation valve module, simulation
Pressure valve module simulates tank module, simulates fluid path electric blasting valve module, simulated engine module, in the software analog subsystem
One or more modules it is disabled when, forbidden module is replaced by subsystem in kind.
4. the ground system test of Space radiation as described in claim 1, which is characterized in that the material object subsystem packet
Include decompression valve module, tank module, one or more modules in engine block.
5. the ground system test of Space radiation as claimed in claim 4, which is characterized in that the data acquisition control
System be used for decompression valve module to subsystem in kind, tank module, in engine block any one or more modules ginseng
Number is controlled, is acquired.
6. the ground system test of Space radiation as claimed in claim 4, which is characterized in that the decompression valve module packet
Include pressure reducing valve in kind, pressure reducing valve inlet pressure sensor, pressure reducing valve outlet pressure sensor, pressure reducing valve gas supply department, decompression
Valve inlet, decompression valve outlet.
7. the ground system test of Space radiation as claimed in claim 4, which is characterized in that the tank module includes
Reservoir inlet pressure sensor, reservoir outlet pressure sensor, tank, tank valve gas supply department, liquid recovery part, storage in kind
Tank inlet, reservoir outlet.
8. the ground system test of Space radiation as claimed in claim 4, which is characterized in that the engine block packet
Include engine inlet pressure sensor, engine, Propellant Supply portion, motor inlet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821990927.4U CN209535509U (en) | 2018-11-29 | 2018-11-29 | A kind of ground system test of Space radiation |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201821990927.4U CN209535509U (en) | 2018-11-29 | 2018-11-29 | A kind of ground system test of Space radiation |
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| CN209535509U true CN209535509U (en) | 2019-10-25 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625347A (en) * | 2018-11-29 | 2019-04-16 | 宁波天擎航天科技有限公司 | A kind of ground system test of Space radiation |
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2018
- 2018-11-29 CN CN201821990927.4U patent/CN209535509U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625347A (en) * | 2018-11-29 | 2019-04-16 | 宁波天擎航天科技有限公司 | A kind of ground system test of Space radiation |
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