CN103279122A - Method for constructing testing environment of satellite control system - Google Patents

Abstract

The invention discloses a method for constructing a testing environment of a satellite control system. The method comprises the following steps of classifying component parts of a satellite control system to be tested, establishing a standardized model of each part and performing modular packaging; classifying input and output ports in each standardized model according to respective signal type, and counting various signals of a single part model; performing number maximized configuration on hardware interfaces of test equipment according to types and numbers of parts possibly used by different satellite control systems; and fixedly connecting hardware interface signals of the test equipment and modular models, and fixedly connecting part models and a dynamical model to form a closed loop. By the method, the current situation of constructing the testing environment of the satellite control system by 'customizing for each satellite' is changed, the development speed is improved, the efficiency of constructing the testing environment is improved by modularizing and standardizing the interfaces, the method is convenient to use, and manpower, material resources and time cost are saved.

Description

A kind of satellite control system test environment construction method

Technical field

The invention belongs to the space flight measuring technology, when relating to ground test, quick foundation, recovery and the transplanting of test environment.

Background technology

The control system of satellite is the critical services subsystem of satellite, is responsible for attitude, the track control of satellite, and how the correctness of more effective access control scheme is the key of problem on ground.

The verification experimental verification work on ground comprises mathematical simulation and physical simulation.When the difference of physical simulation and mathematical simulation is physical simulation, needs to connect the true parts of satellite, and use some simulators, analog satellite is at the various states of rail flight, and this l-G simulation test is called " mould flies test ".Owing to be true parts, the physical characteristics of parts is more approaching true to the effect of system, and is also more effective to the checking of scheme.

Mould need be measurand with star upper-part, software, scheme before flying the test beginning, sets up test environment.The testing apparatus, the ground dynamics software that comprise a cover hardware in the test environment, and some other software is formed.

The terrestrial test environment of control system is because the difference of every satellite configuration and the difference of parts annexation all need " star one customization ".Therefore cause the test environment of different system different, can not be general, build and transplant difficulty, to people's requirement height.

Along with increasing of satellite development task, the establishment of original test environment, use pattern can not adapt to the satellite test demand of quick growth.

Summary of the invention

The technical matters that the present invention solves is: the present invention overcomes the deficiencies in the prior art, proposes a kind of satellite control system test environment construction method, at different satellite control systems, realizes quick foundation, recovery and the transplanting of its test environment.

Technical scheme of the present invention is: a kind of satellite control system test environment construction method, and step is as follows:

1) building block of satellite control system to be tested is classified according to sensor, controller, topworks;

2) sorted each building block in the step 1) is set up standardized model and carry out the modularization encapsulation, for each packaged standardized model reserves enough input interfaces and output interface;

3) with step 2) in input interface, the output interface of packaged each part standard model classify by signal type, and statistics obtains the corresponding input interface of various types of signal type, output interface quantity in each part standard model;

4) according to the needed unit type of different satellite control systems and number of components, the hardware interface of external test facility is maximized the quantity configuration;

5) external test facility that configures is connected with the standardized model of each parts, and the standardized model of each parts is connected with the satellite dynamics model, form closed loop, structure is finished.

The present invention's advantage compared with prior art is as follows:

(1) by setting up partial model and encapsulation, unifies external input, the output interface of single partial model, realized the flexible combination of multi-part, dissimilar parts, improved reusability.

(2) according to signal kinds and the quantity of unit interface, realize the signal maximization envelope design of hardware testing equipment, improve the versatility of hardware testing equipment, saved cost.

(3) the satellite control system test environment that has changed " star one customization " is set up present situation, has accelerated Development Schedule, has passed through modularization, standard interface, has promoted test environment and has set up efficient, and convenient the use saved human and material resources, time cost.

Description of drawings

Fig. 1 is satellite control system ground test theory diagram;

Fig. 2 forms and the configuration relation synoptic diagram for the control system test environment.

Embodiment

Satellite control system ground simulation test environment principle as shown in Figure 1.

By ground checkout equipment operation ground kinetic model, and according to each sensor mathematical model, generate the needed sensor signal of on-board equipment closed loop, produce actual signal by the ground checkout equipment signal source, controller carries out the sensor signals collecting on the star, and through the output of s operation control topworks, gather topworks's output on the star by ground checkout equipment hardware again, and through the topworks partial model, export to the ground kinetic model, thereby constitute complete closed circuit.

The building of terrestrial test environment namely will be set up on the star this closed loop with ground, builds test environment fast, transplants easily, and can recover fast when needs recover is a kind of challenge.

In order to realize the fast construction of satellite control system test environment, need implement according to the step of this method:

(1). the building block to satellite control system is classified according to sensor, controller, topworks, and combing goes out the function of each ingredient single part, external input, output interface.

(2). set up the standardized model of each single part, after reserving enough inputs, output interface, the funtion part of parts is carried out the modularization encapsulation.

For example: the gyro model of single shaft, the sun sensor model of single shaft, single infrared earth sensor model, single momenttum wheel model, magnetic torquer model etc.It is the parts single model that all foundation can be general one by one that uses in the satellite control system.Gyrounit with single shaft is example below, is described as follows:

The input interface of single gyro comprises: the inertia angular velocity of the installation vector of input axis of gyro on satellite, celestial body, the angular velocity that manually adds disturb, the angular speed pulse equivalency of gyro.

The output interface of single gyro comprises: the angular velocity of gyro sensitivity on input shaft, the positive and negative pulse increment in the single cycle of gyro.

The function of the single gyro of encapsulation: be embodied as the function of a C language, by above-mentioned input, by mathematical computations, obtain the function of above-mentioned output.

Miscellaneous part also all is established as unified single partial model respectively.

(3). the input in each standardized model in (2), output interface are divided into hardware simulation amount, digital quantity, pulsed quantity according to signal type separately, numerical variable realizes as integer, floating type, double word type etc. basic type, and counts the quantity of the various types of signal of single partial model.

The gyro model in (2) for example, if dispose 6 on different gyro in certain model, the input signal that then needs is numerical variable and realizes, the installation vector of input axis of gyro on satellite is embodied as the double-precision floating point vector array of a 1*3, and the inertia angular velocity of celestial body, the angular velocity that manually adds disturb, the angular speed pulse equivalency of gyro all is embodied as the double-precision floating point book; In the output interface, gyro responsive angular velocity on input shaft is embodied as a double-precision floating point number, and the positive and negative pulse increment in the single cycle of gyro needs hardware to be embodied as two-way pulse hardware signal.

The input of the single parts of other types, output interface carry out statistic of classification respectively according to the method described above.

(4). when carrying out the hardware design of external test facility, unit type, number of components and the basis (3) that may use according to different satellite control systems count analog quantity input, analog quantity output, digital quantity input, the digital quantity output that will use, the hardware interface total quantity of communication interface etc. maximizes the quantity configuration.

For example: above-mentioned gyro pulse interface, can be designed to 12 the tunnel, satisfy the output demand of 6 gyros, in addition, the control system of other models may be used 12 gyros, 24 tunnel pulse interfaces are reserved 12 tunnel pulse output interfaces when designing like this, make this hardware device have the ability of 6 gyros of expansion in addition.The hardware adaptive mechanism of raising equipment.

(5). utilize commercial configuration software (being used to provide the development environment of setting up hardware and software contacts) that hardware interface signal and the modularization model of testing apparatus are connected firmly, and partial model and self-editing kinetic model are connected firmly the formation closed loop.

For example: the increment that connects firmly positive negative pulse stuffing in the model soon of above-mentioned gyro signal, by the output of pulse output hardware port, namely the positive negative pulse stuffing increment of gyro angular velocity in the single cycle is converted into the pulse signal output of hardware.

With other numerical variables be defined as with kinetic model in the same title of variable used, and use as the external variable of kinetic model, thereby realized connecting firmly of partial model and kinetic model.

After finishing above-mentioned (5) portion, finished once the core foundation of the test environment that overlaps control system.Afterwards, need utilize real time operating system, the identity function that relates in good closed circuit of association is carried out task division, as shown in Figure 2, be divided into hardware integrated circuit board data acquisition task, the partial model calculation task, the kinetic model calculation task, hardware signal source output task, database manipulation task, some other auxiliary task.

Wherein hardware integrated circuit board data acquisition task is finished the signals collecting of satellite control system parts, as the input of modularization model; The partial model calculation task is to finish packaged function, mainly is to calculate; The kinetic model calculation task is finished classical satellite dynamics and is calculated, and is converted into the input of each partial model; The numeral that output task in hardware signal source is finished partial model is input to the conversion of hardware signal; The database manipulation task is finished the warehouse-in hold function of the data that above-mentioned each task uses, and makes things convenient for the inquiry of process data.Other tasks have comprised some auxiliary operation function outside the main task.

Sequential and priority according to tested object are carried out task scheduling, and the good man-machine interaction interface externally is provided.When needs when same testing apparatus realizes the different model test assignment, equipment according to current task is formed, revise the unit type and the number that are connected with kinetic model, revise partial model to the hardware mapping address of device hardware output, task scheduling number in the retouching operation system and order are namely finished building of test environment.When new hardware testing equipment, also can be easily be transplanted on the new equipment software section is parallel,

The present invention does not specify part and belongs to techniques well known.

Claims (1)

1. satellite control system test environment construction method is characterized in that step is as follows:

1) building block of satellite control system to be tested is classified according to sensor, controller, topworks;

2) sorted each building block in the step 1) is set up standardized model and carry out the modularization encapsulation, for each packaged standardized model reserves enough input interfaces and output interface;

3) with step 2) in input interface, the output interface of packaged each part standard model classify by signal type, and statistics obtains the corresponding input interface of various types of signal type, output interface quantity in each part standard model;

4) according to the needed unit type of different satellite control systems and number of components, the hardware interface of external test facility is maximized the quantity configuration;

5) external test facility that configures is connected with the standardized model of each parts, and the standardized model of each parts is connected with the satellite dynamics model, form closed loop, structure is finished.

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