CN108919820B - Artificial intelligence writing method for combined distribution source codes of attitude and orbit control components of digital aircraft - Google Patents
Artificial intelligence writing method for combined distribution source codes of attitude and orbit control components of digital aircraft Download PDFInfo
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Abstract
The invention provides an artificial intelligence writing method for source codes distributed by a digital aircraft attitude and orbit control component combination. The attitude and orbit control component of the digital aircraft comprises a sensor and an actuating mechanism. On the basis of the part installation information and the part model codes, the artificial intelligence replaces a person to write a physical quantity input function, a part combination initialization function, a part combination state quantity refreshing function and a part combination physical effect calculation function of a digital aircraft attitude and orbit control part combination, and intelligent writing of attitude and orbit control part combination source codes in an aircraft closed-loop control system is achieved. The invention uses artificial intelligence to replace people, and intelligently writes the source code of the attitude and orbit control component combined in the whole set of digital aircraft simulation program according to the model code and the installation mode of the attitude and orbit control single component of the digital aircraft, thereby improving the writing efficiency and reducing the simulation cost of the aircraft.
Description
Technical Field
The invention relates to the field of aircraft design, in particular to an artificial intelligence writing method for source codes distributed by a digital aircraft attitude and orbit control component combination.
Background
In the design and development process of the aircraft, in order to ensure high reliability of the final application of the aircraft, a large number of mainstream methods of the existing design need to be adopted in the design, and simulation verification and ground test need to be carried out. Some of these ground tests are not completely reflective of the actual in-orbit behavior of the aircraft and are costly and therefore limited.
The simulation verification method of the digital aircraft has no limitation of environmental conditions, and the working condition of the aircraft can be well simulated as long as the model is established accurately enough, so that the simulation verification method is widely applied to aircraft design, and aircraft numerical simulation is already used for verification of the aircraft design.
In the process of building the digital aircraft, a large amount of source codes need to be written, and the workload is large. At present, the consistency of data transmission content and format in a digital aircraft simulation code is basically ensured by manpower, time and labor are wasted, a stable and standard data transmission format is difficult to form in the same simulation program, and the readability and maintainability of the code are reduced. The artificial intelligence is used for writing the source code of the digital aircraft instead of human, the source code of an aircraft simulation model can be independently written according to the specific design condition of the aircraft, the combined distribution of components is realized according to the structural design result of the aircraft and a single attitude and orbit control component model of the aircraft, and human is liberated from the heavy source code writing process of the digital aircraft.
Therefore, how to provide a method for writing artificial intelligence of source codes distributed by combining attitude and orbit control components of a digital aircraft is a problem which needs to be solved urgently by a person skilled in the art.
Disclosure of Invention
In view of the above, the invention provides an artificial intelligence writing method for source code combined distribution of digital aircraft attitude and orbit control components, which overcomes the defects of the prior art, uses an artificial intelligence programmer to replace a human to write the source code of the digital aircraft, and can intelligently write the source code of the attitude and orbit control components combined in the whole set of digital aircraft simulation program according to the model code and the installation mode of a single digital aircraft attitude and orbit control component, thereby improving the writing efficiency and reducing the simulation cost of the aircraft.
In order to achieve the purpose, the invention adopts the following technical scheme:
a digital aircraft attitude and orbit control component combined distribution source code artificial intelligence writing method comprises the following steps:
firstly, obtaining installation information and component combination mode information of a digital aircraft attitude and orbit control component according to a specific aircraft design;
collecting model functions of a single attitude and orbit control component of the digital aircraft; the model function comprises an initialization function, a state quantity refreshing function and a physical effect calculation function;
step three, defining the input quantity of a single component and the output quantity of the single component according to the model function of the digital aircraft attitude and orbit control single component in the step two;
writing a component combination physical quantity input function according to the combination mode information of the attitude and orbit control components defined in the step one, the input quantity of a single component and the output quantity of the single component defined in the step three and the component combination mode;
and step five, writing the initialization function of the component combination according to the component installation information and the component combination information in the step one, and the single component initialization function in the step two. The initialization function is used for setting initial values for the component internal variable group;
and step six, combining the state quantity refreshing function of the single component and the physical effect calculation function of the single component in the step two according to the combination information of the components in the step one, and generating the state quantity refreshing function of the component combination and the physical effect calculation function of the component combination.
Preferably, in the method for writing the source code artificial intelligence distributed to the digital aircraft attitude and orbit control component combination, in the step one, the installation information of the digital aircraft attitude and orbit control component comprises two representation methods.
Representation method 1: the mounting information of the component is represented using the mounting position coordinates and the mounting vector of the component.
Representation method 2: the mounting information of the component is represented using the mounting position coordinates of the component and the mounting matrix of the component.
The component combination mode information of the attitude and orbit control component of the digital aircraft is defined as the combination selected from all components in the same class in the design result of the digital aircraft. For example, there are 4 momentum wheels in the digital aircraft design result, which are designated A, B, C, D. The combination contains only the first 3 momentum wheels, denoted ABC.
Preferably, in the method for writing artificial intelligence by assigning source codes to the attitude and orbit control component combination of the digital aircraft, in the second step,
the initialization function sets the installation information of the component and the specific initial values of the internal state quantities of the component. Specific initial value input forms include, but are not limited to, direct writing inside the emulation program code, reading an external file, and transferring data between processes.
Preferably, in the method for writing artificial intelligence by assigning source codes to the attitude and orbit control component combination of the digital aircraft, in the third step,
the input quantity of the sensor comprises physical quantity provided by a physical environment simulation module, and the output quantity of the sensor comprises digital signals required by the attitude trajectory control system and physical quantity required by the physical environment simulation module.
The input quantity of the execution mechanism comprises instructions generated by the attitude orbit control system, and the output quantity of the execution mechanism comprises physical quantity required by the physical environment simulation module.
Preferably, in the method for writing artificial intelligence by assigning source codes to the digital aircraft attitude and orbit control component combinations, the finally obtained source codes for assigning the digital aircraft attitude and orbit control component combinations include:
1) input function of component combination physical quantity
2) Component combination state quantity refresh function
3) Component combination physical effect calculation function
4) Component assembly initialization function
5) Component internal variable set
Wherein the component internal variable group includes component mounting information and component internal state quantities.
According to the technical scheme, compared with the prior art, the artificial intelligence is used for replacing a person to write the digital aircraft attitude and orbit control component combination distribution source code, the digital aircraft source code can be independently written according to task requirements and a model code and an installation mode of a single digital aircraft attitude and orbit control component, and the person is liberated from a heavy digital aircraft source code writing process. The invention particularly writes the simulation code of the attitude and orbit control component combination in the whole set of aircraft source codes automatically and intelligently by the standardized description of the installation information and the combination mode of the components in the aircraft design result and the collection of the model function of a single component, thereby reducing the simulation cost of the aircraft.
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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 is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic diagram of data transmission relationship of a attitude and orbit control system of a digital aircraft according to the present invention;
fig. 2 is a schematic overall flow chart of the artificial intelligence writing method for distributing source codes to the attitude and orbit control component combination of the digital aircraft according to the invention.
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.
The invention provides an artificial intelligence writing method for source code combined distribution of attitude and orbit control components of a digital aircraft, which overcomes the defects of the prior art, uses artificial intelligence to replace a human to write the source code of the digital aircraft, solves the problems of code writing, data connection relation in attitude and orbit control component combined distribution and the like in the writing process, can intelligently write the source code combined by the components according to the structural design result of the aircraft and a single attitude and orbit control component model, improves the writing efficiency and reduces the simulation cost of the aircraft.
Referring to fig. 1, fig. 1 is a schematic diagram of data transmission relationship of a attitude and orbit control system of a digital aircraft according to the present invention. On the basis, fig. 2 shows an overall flow diagram of the artificial intelligence writing method for distributing the source codes to the attitude and orbit control component combination of the digital aircraft. The artificial intelligent writing method for the source code combined distribution of the attitude and orbit control components of the digital aircraft specifically comprises the following steps:
step S101: and obtaining the installation information and the component combination mode information of the attitude and orbit control component of the digital aircraft according to the specific aircraft design.
In the aircraft body coordinate system, there are two methods for representing the installation information of the single part. The first representation method uses the mounting position coordinates and the mounting vector of the component. The second expression method uses the mounting position coordinates of the component and the mounting matrix of the component. Different representation methods need to be selected according to different types of the components.
And under the coordinate system of the aircraft body, the total number of the attitude and orbit control components belonging to the same component type is recorded as N. The total number of sensors of the component type, such as a star sensor in a digital aircraft, is 1, i.e., N is 1; the total number of actuators of the component type of the momentum wheel in the digital aircraft is 4, namely N is 4, and the rest can be analogized. N is the total number of attitude and orbit control components of the same type actually contained in the digital aircraft.
In the attitude and orbit control component of the same component type, the total number of different combinations is marked as C. The number of components contained in each combination is denoted MjSatisfy the following requirements
1≤j≤C
For example, a digital aircraft includes 4 momentum wheels, denoted as N-4. The 4 momentum wheels share 2 combination modes of ' three forward mounting ' and ' three forward mounting and ' oblique mounting ', and are marked as C-2. The combined mode of "three forward mounting" includes three momentum wheels, which are marked as M13. The combined mode of 'three-forward mounting and one-oblique mounting' includes 4 momentum wheels, which are marked as M2＝4。
In N parts of the attitude and orbit control part of the same part type, the installation position coordinate of the ith part is the coordinate of the origin of the instrument coordinate system of the part under the coordinate system of the aircraft body and is marked as Si：
Si＝(xsi,ysi,zsi)
The second method is selected to represent the installation information of the star sensor in the attitude and orbit control component of the digital aircraft. The mounting matrix of the ith star sensor in the N star sensors is defined as a coordinate transformation matrix transformed from the satellite body coordinate system to the part instrument coordinate system and is recorded as Lsb_i。
The first method is selected to represent the installation information of the part aiming at the actuating mechanism of the part type of the momentum wheel in the attitude and orbit control part of the digital aircraft. The mounting vector of the ith momentum wheel in the N momentum wheels is marked as V in the satellite body coordinate systemi。
Vi＝(xvi,yvi,zvi)
Step S102: model functions of a single part of the attitude and orbit control of the digital aircraft are collected. The model function comprises an initialization function, a state quantity refreshing function and a physical effect calculation function.
The initialization function sets an initial value of the component internal state quantity according to the aircraft design result before the simulation is started. Taking the momentum wheel as an example, the initialization function sets t of the momentum wheel0The initial rotation speeds at all times are omega0314rad/s and 0.05kg m rotor moment of inertia2. The initialization function is also responsible for setting the installation information of the component.
And the state quantity refreshing function calculates the state quantity at the next moment according to the simulation step length, the state quantity information at the previous moment, the external input physical quantity and the physics formula, and replaces the state quantity at the previous moment. Taking the momentum wheel as an example, the simulation step length is dt equal to 0.1s, and the rotating speed at the last moment is ω0314rad/s, the motor generates a moment M of 0.1 N.m under the action of certain external voltage and current, and the formula of physics is adopted
Mdt＝Jdω
Get the next time t1The rotational speed omega of the moment wheel1Is composed of
ω1＝314.2rad/s
The physical effect calculation function is responsible for calculating the physical effect generated by the component to the outside within a simulation step length, including but not limited to mechanical effect, electromagnetic effect, thermal effect and digital signal output to the outside. The average value of the torque output by the momentum wheel to the outside along the axial direction is within a simulation step, the average value of the component power supply voltage and the passing current is within a simulation step, and the heat released to the outside is within a simulation step. The digital signals comprise a measured value of the internal rotating speed of the momentum wheel, a measured value of the shaft temperature and the like.
Step S103: and defining the input quantity and the output quantity of the single component according to the model function of the digital aircraft attitude and orbit control single component in the step S102.
For the sensor, a physical environment simulation module RTC of a digital aircraft simulation program provides physical quantity required by the component for the sensor, and the physical quantity is calculated through a state quantity refreshing function and a physical effect calculating function of the sensor, so that a digital signal is provided for an attitude orbit control system ADCS of the digital aircraft, and partial physical quantity is provided for the physical environment simulation module RTC.
Taking a star sensor as an example, a physical environment simulation module RTC of a digital aircraft simulation program provides a quaternion Q for describing the current attitude of the aircraft in the spring minute point geocentric inertial coordinate system for the ith star sensor1iCalculating the attitude quaternion Q of the ith component instrument coordinate system relative to the spring minute point geocentric inertia coordinate system through the state quantity refreshing function and the physical effect calculation function of the ith star sensor2iAnd sending the data to an attitude trajectory control system ADCS of the digital aircraft. The input physical quantity of the ith component is Q1iThe output physical quantity of the ith component is Q2i. The remaining physical quantities are defined analogously.
For the actuator, the actuator needs to receive a command sent by the attitude trajectory control system ADCS, and send a physical quantity to the physical environment simulation module RTC after calculation by the state quantity refresh function and the physical effect calculation function.
Taking the momentum wheel as an example, the ith momentum wheel receives a rotor angular acceleration command A sent by an attitude orbit control system ADCSiAfter being calculated by the state quantity refreshing function and the physical effect calculating function, the physical quantity, such as the output torque M, is sent to the RTC of the physical environment simulation modulei. Input physical quantity of ith component is AiThe output physical quantity of the ith component is Mi. The remaining physical quantities are defined analogously.
Step S104: the component combination physical quantity input function is written for the component combination mode according to the combination mode information of the attitude and orbit control components defined in step S101, and the input quantity of the single component and the output quantity of the single component defined in step S103.
For the sensor, the physical quantity in the physical environment simulation module RTC is obtained by a component combination physical quantity input function through function parameters and the like, and an internal variable group of the component is written, wherein the number of the variable group is equal to the number N of the component. And the state quantity refreshing function calculates according to the internal variable group of the component, and updates the state quantity in the variable group. And the physical effect calculation function calculates according to the internal variable group of the component, outputs the digital signal to an attitude orbit control system (ADCS), and outputs the rest physical effects to a physical environment simulation module (RTC).
For the execution mechanism, the input function of the component combination physical quantity obtains instruction information from the attitude trajectory control system ADCS in the modes of function parameters and the like, and writes the instruction information into the variable groups in the components, wherein the number of the variable groups is equal to the number N of the components. And the state quantity refreshing function calculates according to the internal variable group of the component, and updates the state quantity in the variable group. And the physical effect calculation function calculates according to the internal variable group of the component and outputs the calculation result to the physical environment simulation module RTC.
Step S105: the initialization function of the component combination is written in accordance with the component mounting information and the component combination information in step S101, and the individual component initialization function in step S102. The initialization function is used to set initial values for the set of variables within the component.
Taking the momentum wheel as an example: the initialization function of the momentum wheel combination writes initial values for the installation positions of the N momentum wheels, the installation vectors of the N momentum wheels and the internal state quantities of the components including the rotational inertia of the N momentum wheels respectively.
Step S106: and according to the combination information of the components in the step S101, selectively calling the state quantity refreshing function of the single component in the step S102 in the state quantity refreshing function of the component combination, and selectively calling the physical effect computing function of the single component in the physical effect computing function of the component combination.
Taking the "three-side-up" configuration of the momentum wheel as an example, 4 momentum wheels are installed, and the number of the momentum wheels is recorded as a momentum wheel A, a momentum wheel B, a momentum wheel C and a momentum wheel D. In the "three-pronged" configuration, the combination of components includes only the momentum wheel A, B, C. Only 3 of the 4 momentum wheels are called in the state quantity refreshing function of the component combination and the physical effect calculation function of the component combination, and the rest one is not called.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (7)
1. The artificial intelligence writing method for the source code combined distribution of the attitude and orbit control components of the digital aircraft is characterized by comprising the following steps of:
firstly, obtaining installation information and component combination mode information of a digital aircraft attitude and orbit control component according to a specific aircraft design;
collecting model functions of a single attitude and orbit control component of the digital aircraft; the model function comprises an initialization function, a state quantity refreshing function and a physical effect calculation function;
step three, defining the input quantity of a single component and the output quantity of the single component according to the model function of the digital aircraft attitude and orbit control single component in the step two;
writing a component combination physical quantity input function according to the combination mode information of the attitude and orbit control components defined in the step one, the input quantity of a single component and the output quantity of the single component defined in the step three;
step five, writing the initialization function of the component combination according to the component installation information and the component combination information in the step one and the single component initialization function in the step two;
the initialization function is used for setting initial values for the component internal variable group;
step six, combining the state quantity refreshing function of the single component and the physical effect calculation function of the single component in the step two according to the combination information of the components in the step one to generate a state quantity refreshing function of the component combination and a physical effect calculation function of the component combination;
in the third step, the first step is that,
the attitude and orbit control component of the digital aircraft is defined as a sensor and an actuating mechanism;
the input quantity of the sensor comprises physical quantity provided by a physical environment simulation module, and the output quantity of the sensor comprises a digital signal required by the attitude orbit control system and physical quantity required by the physical environment simulation module;
the input quantity of the executing mechanism comprises an instruction generated by the attitude orbit control system, and the output quantity of the executing mechanism comprises a physical quantity required by the physical environment simulation module.
2. The digital aircraft attitude and orbit control component combination assignment source code artificial intelligence writing method of claim 1, characterized in that in the first step,
the installation information of the attitude and orbit control component of the digital aircraft uses two representation methods:
representation method 1: representing mounting information of the component using the mounting position coordinates and a mounting vector of the component;
representation method 2: the mounting information of the component is represented using the mounting position coordinates of the component and the mounting matrix of the component.
3. The digital aircraft attitude and orbit control component combination assignment source code artificial intelligence writing method of claim 2, wherein in the first step, the representation method is selected according to different categories to which the components belong.
4. The method for writing artificial intelligence on a source code assigned to a digital aircraft attitude and orbit control component combination according to claim 1, wherein in step two, the initialization function sets initial values of component installation information and component internal state quantities according to the input initial values, and the input initial values for the initialization function are in the form of, but not limited to, direct internal writing of simulation program codes, external file reading, and inter-process data transfer.
5. The digital aircraft attitude and orbit control component combination assignment source code artificial intelligence writing method of claim 1, characterized in that in the third step,
for a sensor, a physical quantity input function of a component combination physical quantity obtains a physical quantity in a physical environment simulation module RTC in a function parameter mode, and a variable group in the component is written in, wherein the number of the variable group is equal to the number of the components;
the state quantity refreshing function calculates according to the internal variable group of the component, and updates the state quantity in the variable group; and the physical effect calculation function calculates according to the internal variable group of the component, outputs the digital signal to an attitude orbit control system (ADCS), and outputs the rest physical effects to a physical environment simulation module (RTC).
6. The digital aircraft attitude and orbit control component combination assignment source code artificial intelligence writing method of claim 1, characterized in that in the third step,
for an execution mechanism, a component combination physical quantity input function acquires instruction information from an attitude orbit control system (ADCS) in a function parameter mode, and writes the instruction information into component internal variable groups, wherein the number of the variable groups is equal to the number of components;
the state quantity refreshing function calculates according to the internal variable group of the component, and updates the state quantity in the variable group; and the physical effect calculation function calculates according to the internal variable group of the component and outputs the calculation result to the physical environment simulation module RTC.
7. The digital aircraft attitude and orbit control component combination assignment source code artificial intelligence writing method of claim 1,
the finally obtained combined distribution source code of the attitude and orbit control component of the digital aircraft comprises the following steps:
1) input function of component combination physical quantity
2) Component combination state quantity refresh function
3) Component combination physical effect calculation function
4) Component assembly initialization function
5) Component internal variable set
Wherein the component internal variable group includes component mounting information and component internal state quantities.
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