Spacecraft modeling technology state control method based on state machine

Abstract

According to the spacecraft modeling technology state control method based on the state machine, analysis is carried out according to the characteristics of the AIT stage of a deep space detector, and modeling is carried out on the technology state and the state transition process of the detector in the AIT stage based on the method theory of the finite state machine; a technical state management dimension and a management method of each state transition in an AIT stage are provided, a technical state control element and a state transition method are introduced into general assembly, test and experiment processes of a deep space probe complex system, and a model engineering practice process applying the strategy is given.

Description

Technical Field

[0001] The present invention relates to a state machine-based spacecraft modeling technical state control method, and in particular to a state machine modeling and state transfer description method to achieve technical state control of a multi-chamber complex configuration lunar probe in the AIT phase. Background Art

[0002] The unmanned automatic sampling and return mission of the third and fourth phases of the lunar exploration needs to complete orbiting, lunar landing, unmanned automatic sampling on the moon, lunar surface takeoff, lunar orbit rendezvous and docking, and reentry and return. In order to meet the mission requirements, the configuration of the probe has also evolved from the single cabin of my country's early lunar probes to an intelligent body with multiple cabins working in parallel. In the AIT (Assembly Integration & Test) stage of the development process of multi-cabin deep space probes, multiple cabins carry out general assembly, integration, and testing in parallel. General assembly and testing are always carried out crosswise or in parallel, and the probe has the general assembly / testing status of a single cabin, an interface between cabins, a two-cabin assembly, and a multi-cabin assembly. There are many assembly and test couplings, complex technical status, and great verification difficulties. Under such conditions, drawing on the effective experience of previous spacecraft technical status management, and targeting the new characteristics of the AIT stage of the unmanned lunar sampling and return probe, it is of great significance to achieve effective control of the technical status of the AIT stage to ensure the success of the mission.

[0003] A finite state machine (FSM) is a mathematical model of a system with discrete inputs and outputs. It has the structure of a dynamic system and can define a language using the accessibility of a subset of states. This system has a finite number of internal states.

[0004] A finite state machine M can be defined as a six-tuple (Σ, S, s0, δ, F, G), where the specific meanings of the elements are as follows:

[0005] 1) Σ is the input table, Σ = {σ0, σ1,…,σ n}, is a non-empty symbol set;

[0006] 2) S is a non-empty finite set of states S={s0,s1,…,s n},s i is a state of M;

[0007] 3) s0 is the initial state, s0∈S;

[0008] 4)δ is the state transition function, There is δ(s p ,a)=s q, where S×Σ is the Cartesian product of two sets, and M is in state s p When the character σ is input, its state will change to s q , and the input points to the next state;

[0009] 5) F is the final state set, s is the accepting state of M;

[0010] 6)G is a finite set of output functions.

[0011] In simple terms, FSM uses the input in Σ to control the state transition of FSM and form a corresponding state transition sequence. There are also many theoretical studies and applications in other fields for the method of using state machines to describe the system control process, such as formal modeling of the requirements layer of spacecraft operating systems, control system modeling, etc., which mainly use finite state machine modeling to describe and study the operation process of the system.

[0012] The current technical status management is mainly based on technical documents and relies on designers to record technical status changes. A large amount of technical status information is discretely distributed, and some information is implicit in the documents. Temporary technical status changes are carried out based on on-site processing orders or electrical measurement operation orders, which sever the inherent connection between the states, may result in inadequate status control and potential fault hazards.

[0013] In view of the characteristics of the AIT phase of the lunar unmanned sample return probe, the methodology of systems engineering was applied and the technical status and state transfer process of the probe in the AIT phase were modeled based on the finite state machine theory. A technical status control method for each state transfer in the AIT phase was proposed, and the technical status control elements and state transfer method were introduced into the assembly, testing and experimentation of the complex system of the lunar unmanned sample return probe to form a unified and refined technical status control model to ensure that there are no hidden dangers in the model development process. Summary of the invention

[0014] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide a spacecraft modeling technical status control method based on a finite state machine, to combine the spacecraft development technical process, to apply state machine elements to the development process spacecraft technical status control, to ensure that the final assembly, experiment, and test verification are completed fully, and to ensure that the AIT process is controlled and traceable.

[0015] The technical solution of the present invention is: a spacecraft modeling technical state control method based on a state machine, comprising:

[0016] For each key node in the detector development process, a finite state set S is established;

[0017] Establish a digital model for all states in the set S;

[0018] According to the development technology process and related technical documents, the input condition set Σ that causes state changes is constructed, and then the transfer function δ of all states in the development process is obtained;

[0019] According to the obtained transfer function δ, a state control model of state transfer technology based on state machine is established;

[0020] The state machine-based state transfer technical state control model is applied to carry out full-cycle and full-process technical state control.

[0021] The digital model is established for all states in the set S, including:

[0022] A 22-dimensional vector Sn is introduced and numbered; n∈[1,N], where N represents the total number of development process states; digital modeling is carried out for the contents represented by the above dimensions.

[0023] The contents represented by each dimension of Sn include: final assembly and parking status, measurement and control data transmission link, power supply status, and test product status.

[0024] The contents of each dimension that needs to be managed in the state include:

[0025] Assembly and parking status assembly-state, measurement and control digital transmission link link-state, power supply status power-state, test product status product-state, thermistor tmr-state and heating circuit ht-state.

[0026] The input condition set Σ that causes the state change is constructed, including:

[0027] According to the model development technical process and the relevant technical documents of AIT stage assembly, electrical test documents and environmental test, sort out the differences between various states and determine the conversion relationship between various states;

[0028] The 22-dimensional vector digital model Sn is traversed to obtain the state differences between multiple states, that is, the input condition set Σ that causes the state change is obtained.

[0029] The transfer function δ of all states in the construction process includes:

[0030] When the detector completes the state transfer process, two parameters are involved, one is the input condition set Σ, and the other is the digital model of the detector state; the state transfer process involves the final assembly state parameters in the input condition set Σ, and the above-mentioned final assembly state parameters are characterized in the constructed digital model to determine the transfer function δ.

[0031] The assembly status parameters include: compartment combination information, equipment installation information, measurement and control data transmission link status, and power supply status; the transfer function δ is expressed as:

[0032] State 下一个状态 =δ(assembly-state 当前状态 ,link-state 当前状态 ,power-state 当前状态 ,tmr-state 当前状态 , State 当前状态 ....), the state of each variable in this function is voted on by the relevant parameters in the state transition process.

[0033] The establishment of a technical state control model based on state machine state transfer includes: using digital models to determine all state models of all nodes in the development technology process or AIT process technology process; applying all constructed state models to establish a technical state control model based on state machine state transfer in the form of a directed graph for the development process.

[0034] When the development process is established in the form of a directed graph to establish a technical state control model based on the state transfer of the state machine, the state transfer process is determined by the transfer function δ, and the current state s n It is related to the constructed input condition σ, σ∈Σ; the state transfer function is recorded as δ(s n ,σ)=s n+1 , where: s n 、s n+1 ∈S, indicating that in state s n When the input signal Σ and the current state s n When the condition σ is met, it will transfer to state s n+1 , abbreviated as δ(s n ,σ,s n+1 ); the state transfer function includes three situations: the current state transfers to the next state, the current state transfers to the current state, and the current state transfers to the initial state or a specific state; all states Sn are connected with directed line segments, and the state transfer is completed under the action of the constructed input condition set Σ, that is, the state control model of the state transfer technology based on the state machine is obtained:

[0035] δ1(s n ,σ1,s n+1 ): current state s n Satisfy the input condition σ1 of the development technology process, from the current state s n Transfer to next state s n+1 ;

[0036] δ2(s n ,σ2,s n ): current state sn Satisfy the input condition σ2 of the development technology process, from the current state s n Transfer to present state n ;

[0037] δ3(s n ,σ3,s j，j＝0,1,…n+1 ): current state s n Satisfy the input condition σ3 of the development technology process and transfer from the current state to the initial state or a specific state.

[0038] The beneficial effects of the present invention are:

[0039] (1) Finite state machines are used to model the technical process of probe development / technical status management in the AIT phase. The technical status, file system, and status control table of the probe are modeled, which helps to design a digital status management system and lays a good technical foundation for the transformation of spacecraft status management from document-driven to digital model-driven.

[0040] (2) A state vector describing the technical status was constructed, the elements that need to be controlled in the AIT phase of the detector were clarified, and a unified technical status standard was established to control the technical status of complex models at the global level and achieve the reusability and reproducibility of the technical status;

[0041] (3) Based on the technical status control strategy of the finite state machine model, a dynamic control table is combined with a static organization table to characterize the state changes of the detector during the AIT stage and establish a continuous, consistent, and traceable technical status evolution control mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 Schematic diagram of the modeling technology status control method

[0043] Figure 2 It is the state transition diagram of the AIT process or development process of a multi-cabin deep space probe;

[0044] Figure 3 It is a schematic diagram of the system implementation mechanism of the state transfer process;

[0045] Figure 4 This is a state transition diagram. DETAILED DESCRIPTION

[0046] The specific embodiments of the present invention are further described in detail below with reference to the accompanying drawings.

[0047] like Figure 1 As shown, the present invention proposes a method for controlling the technical state of a spacecraft modeling based on a state machine, and the steps are as follows:

[0048] (1) Based on the detector development technical process, determine the key nodes of the entire development process and establish a finite state set S.

[0049] To simplify the numbering data, the corresponding flight events can be numbered according to the chronological order of the events, such as: S 01 , S 02 , S 03 They respectively indicate that cabin 1, cabin 2, and cabin 3 / 4 assemblies have completed the assembly of propulsion products and the installation of prototype products, and have entered the final assembly test hall, waiting for the A-stage test status of the single cabin electrical performance test... The corresponding development node status numbers are S1, S2, S3..., S N , N is the total number of development process states;

[0050] (2) Establish a digital model for all states in set S;

[0051] (3) Based on the development technology process and relevant technical documents, construct a set of input conditions Σ that cause state changes;

[0052] (4) According to the development technology process and relevant technical documents, construct the transfer function δ of all states in the development process;

[0053] (5) Establish a technical state control model based on state machine state transition;

[0054] (6) Apply the model to carry out technical status control and carry out full-cycle and full-process technical status control.

[0055] by Figure 2 Medium S 72 To S 82 Taking transfer as an example, the implementation mechanism of transfer and control is further explained. 72 Indicates the status of thermal balance test and thermal vacuum test of cabin 3; S 82 Indicates the status of thermal balance test and thermal vacuum test of cabin 3 / 4 assembly; the detector status remains at S 72 In the state, the 22-dimensional vector of the static organization table only contains the state information of compartment 1. Driven by event E22, the system changes the elements in the 22-dimensional vector according to the dynamic control table and determines whether it has reached S 82 , meeting the requirements of thermal balance test and thermal vacuum test status of cabin 3 / 4 assembly.

[0056] For state transfer, assembly and parking status, test products, cable status, etc. are very typical dynamic changes and are important parameters for technical state control. Based on the dynamic control table, all elements in all state vectors are traversed in the static organization table, and finally all state elements are incrementally recorded to obtain a new static organization table to represent the latest test state. The state transfer process is completed in the digital tool as follows Figure 3 As shown, the dotted part in the figure can be implemented by designing a data management system based on a finite state machine model, and is implemented in a tabular manner in the current model.

[0057] The system implementation process corresponding to this operation is as follows:

[0058] ① Read the static organization table to obtain the information of each element in the current state. To obtain the attribute information of each state element from the data structure of the 22-dimensional vector, it is necessary to traverse each element of the entire static organization table;

[0059] ② The dynamic control table drives the change of the detector state. This dynamic table drives the state change of all elements in the detector static organization table. The state change in the example is the change of elements such as the state of the test compartment, the test product and the cable state;

[0060] ③After the state changes, write the relevant information into the static organization table to determine whether the new state reaches the test state designed in the AIT process.

[0061] The step (2) constructs a digital model of the technical status, specifically:

[0062] (2.1) First, we introduce a 22-dimensional vector S n , n∈[1,N] and numbered, N represents the total number of development process states; the contents represented by each dimension of Sn include: final assembly and parking state, measurement and control data transmission link, power supply state, and test product state;

[0063] (2.2) Digital modeling is carried out for the contents represented in each dimension. The meanings of some elements that need to be managed in the state are defined as follows:

[0064] 1) Assembly-state, assemble-state∈{cabin 1 is parked alone, compartment 2 is parked alone, compartment 3 is parked alone, compartment 1 and compartment 2 are electrically connected, compartment 3 and compartment 4 are electrically connected, compartment 1 / 2 assembly is parked, compartment 3 / 4 assembly is parked, compartment 1 / 2 / 3 / 4 assembly is parked};

[0065] 2) Measurement and control data transmission link link-state, link-state∈{0,1}, 0 represents wired measurement and control data transmission, 1 represents wireless measurement and control data transmission;

[0066] 3) Power supply state power-state, power-state∈{0,1}, 0 indicates power supply from the instrument plug, 1 indicates power supply from the solar wing interface;

[0067] 4) Product state of the test product-state, product-state∈[1,Pn ],P n Indicates the number of detector supporting products.

[0068] 5) Thermistor tmr-state, tmr-state∈[0,TMR n ], TMR n Indicates the number of thermistor designs implemented and welded;

[0069] 6) Heating circuit ht-state, ht-state∈[0,H n ], H n Indicates the number of heating circuits designed, implemented and welded…

[0070] In the early stage of engineering practice, a tabular approach was used to complete engineering management in 22 dimensions, and digital tools were developed in the later stage.

[0071] The step (3) constructs a set of input conditions Σ that cause state changes, specifically:

[0072] (3.1) Based on the model development technical process and the AIT stage assembly, electrical test documents and environmental test related technical documents, sort out the differences between each state and determine the conversion relationship between each state;

[0073] (3.1) Traverse the 22-dimensional vector Sn digital model described in step (2) to obtain the state differences between multiple states, that is, obtain the input condition set Σ that causes the state change;

[0074] A unified global description model of technical status is established based on the static organization table, which forms a description standard of the technical status. Based on the file system, the relationship between the technical status elements in each state of the AIT stage is standardized. The dynamic control table gives the variable part of each element in the state migration of the AIT stage as the input condition of the finite state machine state transfer, and records the state changes of each stage of the AIT stage as the basis for carrying out the next stage of work after the detector state migration in the AIT stage.

[0075] The step (4) constructs the transfer function δ of all states in the development process, specifically:

[0076] (4.1) According to the model development technical process and the relevant technical documents of the AIT stage assembly, electrical test documents and environmental test, determine each state and related conditions, and determine the conversion relationship between each state;

[0077] Design a complete and continuous state transition rule, and support the following file information for activities during the AIT process:

[0078] IDS table related to each subsystem of the detector: IDS table of each subsystem equipment;

[0079] Cable network related documents: cable matching table, low-frequency cable contact table, cable network connection diagram, device table and transfer electrical connector design report, device arrow interface design report, device separation electrical connector design report, etc.;

[0080] Device-ground interface and power supply documents: device-ground connection diagram, power supply interface diagram, grounding requirements and connection diagram, etc.;

[0081] Related documents for the whole device information flow design: remote control command table, telemetry parameter table, remote control command usage guidelines, telemetry parameter processing methods and requirements, telemetry outline, digital data format, bus communication protocol, software user requirements, information flow analysis report, etc.;

[0082] Outline of testing for whole device and subsystem: Outline of electrical testing for whole device and subsystem during assembly, outline of electrical testing for environmental testing (ESD, EMC, mechanics, thermal balance, thermal vacuum, etc.), outline of electrical testing for special tests, etc.;

[0083] General assembly related documents: configuration layout design report, thermistor, heater matching and welding technical requirements, comprehensive test process parts layout and installation requirements, etc.;

[0084] Environmental test related documents: environmental test plan and outline, environmental test assembly technical process, environmental test electrical measurement outline and details, environmental test summary, etc.;

[0085] Files related to the initial status setting of the device on the device;

[0086] Related documents for ground comprehensive testing: test details for each stage, comprehensive test safety measures, commonly used test forms for comprehensive testing, etc.

[0087] (4.2) The detector state transfer process involves two parameters, one is the input condition set Σ, and the other is the digital model of the detector state. The assembly state parameters involved in the state transfer process include: cabin combination information, equipment installation information, measurement and control data transmission link status, and power supply status. The digital model constructed in step (2) characterizes them and determines the transfer function δ, which is expressed as State (下一个状态) =δ(assembly-state (当前状态) ,link-state (当前状态) ,power-state (当前状态) ,tmr-state (当前状态), State (当前状态) ....), the state of each variable in the function is voted on by the relevant parameters in the state transition process, where the specific number of parameters is determined by the number of dimensions of Sn described in step (2).

[0088] Digital modeling is performed based on the spacecraft status information contained in the state machine of each development node, such as the assembly and parking status, measurement and control data transmission link status, power supply status, etc. mentioned in (2.2). Taking the transition from the ascender thermal test state to the landing and ascent assembly thermal test state in the thermal test as an example, the state transition process of the development node is set as S (着陆上升组合体状态) =δ(assembly-state (上升器) ,link-state (上升器) ,power-state (上升器) ,tmr-state (上升器) , S (上升器) ....), the specific modeling process is as follows:

[0089] ① In the current S (上升器) Based on the state, traverse the input function, that is, the 22 dimensions of the dynamic organization table, and transition to the next state;

[0090] ②Parameter assembly-state in the state transfer function (着陆上升组合体状态) ,link-state (着陆上升组合体状态) ,power-state (着陆上升组合体状态) ,tmr-state (着陆上升组合体状态) Modeling, for example:

[0091] The detector needs to have the following status: the cabin assembly status meets the requirements, the measurement and control data transmission link meets the requirements, the power supply status is normal, etc., that is: (月面采样) →(assembly-state (着陆上升组合体状态) ,link-state (着陆上升组合体状态) ,power-state (着陆上升组合体状态) ,tmr-state (着陆上升组合体状态) , ...), so the mathematical model that can implement the spacecraft state transfer function can be expressed as:

[0092] A.assembly-state: The spacecraft module assembly can support the entire process of the next development node. If the assembly is in place, the assembly parameter P 1(舱段) =1, otherwise P 1(舱段) =0;

[0093] B.link-state: The developer has confirmed the state of the measurement and control data transmission link. If the measurement and control data transmission link state can support the entire working process of the next development node, the link parameter P 2(链路) =1, otherwise P 2(链路) =0;

[0094] C.tmr-state: The detector heating circuit has been assembled and the number of assemblies required for the test has been completed. If it has been unlocked, the device status parameter P 3(回路) =1, otherwise P 3(回路) =0.

[0095] Therefore, when P 1(舱段) =1 and P 2(链路) =1 and P 3(回路) =1, it can trigger the (上升器) Status based on S (着陆上升组合体状态) .

[0096] The step (5) establishes a technical state control model based on the state transition of the state machine, specifically:

[0097] (5.1) Determine all state models of all nodes in the development technology flow or AIT process technology flow using the digital model described in step (2);

[0098] (5.2) Apply all the state models constructed in (5.1) to establish a spacecraft technology state control model based on a state machine in the form of a directed graph for the development process, where the state transition process is determined by the transfer function δ and is related to the current state s n It is related to the input condition σ constructed in step (3), σ∈Σ; the state transfer function is recorded as δ(s n ,σ)=s n+1 , where: s n 、s n+1 ∈S, indicating that in state s n When the input signal Σ and the current state s n When the condition σ is met, it will transfer to state s n+1 , abbreviated as δ(s n ,σ,s n+1 ); the state transfer function includes three situations: the current state transfers to the next state, the current state transfers to the current state, and the current state transfers to the initial state or a specific state. The basic state transfer process is as follows Figure 4 As shown. Connect all states Sn with directed lines and complete the state transfer under the input condition set Σ constructed in step (3), and you will get the state control model of state transfer technology based on state machine:

[0099] δ1(s n ,σ1,sn+1 ): current state s n The input condition σ1 constructed in step (3) of the development technology process is satisfied, and the current state s n Transfer to next state s n+1 ;

[0100] δ2(s n ,σ2,s n ): current state s n The input condition σ2 constructed in step (3) of the development technology process is satisfied, and the current state s n )Transfer to the present state n );

[0101] δ3(s n ,σ3,s j，j＝0,1,…n+1 ): current state s n The input condition σ3 constructed in step (3) of the development technology process is satisfied, and the state is transferred from the current state to the initial state or a specific state.

[0102] The following example uses the AIT process operation status of the unmanned lunar sample return probe as an example to illustrate.

[0103] The initial state of the whole device assembled and subjected to electrical performance test after the delivery of the prototype product is taken as the initial state of the finite state machine model, and the state of the detector after the thermal test is completed is taken as the final state of the finite state model. The state transition of the entire AIT process of the detector is graphically represented. Figure 2 The state transition process of the detector's compartments / assemblies and the detector as a whole during the AIT phase assembly, testing and experiment is described in the form of a finite state machine state transition diagram. The events E listed in Table 1 are the input conditions of the finite state machine model.

[0104] After completing the acceptance of the prototype product, the installation of propulsion components, and the installation of products, cabin 1, cabin 2, and cabin 3 / 4 assembly are parked in the final assembly hall as the initial state of the system. Then, A / B electrical testing of each cabin, system-level testing in the single cabin / assembly state, wireless simulated flight testing in the assembly state and the detector as a whole, D-stage electrical testing / EMC testing / mechanical testing modification and docking of each cabin, thermal testing modification and docking of each cabin, etc. are carried out to complete the final assembly, testing and experimentation specified in the prototype technical process and finally reach the final state of the AIT cycle.

[0105] Table 1 State transfer input (dynamic control table)

[0106]

[0107]

[0108] Figure 2 The meaning is as follows:

[0109] S 01 , S 02 , S 03 They respectively indicate that the cabin 1, cabin 2, and cabin 3 / 4 assemblies have completed the installation of propulsion products and the installation of prototype products, and have entered the final assembly test hall, waiting for the single cabin electrical performance test A phase test status;

[0110] S 11 , S 12 , S 13 Respectively indicate the test status of phase A of the electrical performance test of cabin 1, cabin 2, and cabin 3 / 4 combination;

[0111] S 21 , S 22 , S 23 Respectively indicate the test status of phase B of the electrical performance test of cabin 1, cabin 2, and cabin 3 / 4 combination;

[0112] S 31 Indicates the interface test between compartment 1 and compartment 2 and the test status of the wired system level mode in phase B of the electrical performance test of the assembly;

[0113] S 41 Indicates the wireless simulated flight test status of the cabin 1 / 2 assembly during the electrical performance test C phase;

[0114] S 32 Indicates the test status of the wired system level mode of the electrical performance test phase B of the cabin section 3 / 4 assembly;

[0115] S 42 Indicates the wireless simulated flight test status of the cabin section 3 / 4 assembly during the C phase of the electrical performance test;

[0116] S5 indicates the wireless simulated flight test status of the C phase of the electrical performance test of the detectors in each compartment;

[0117] S6 indicates the detector electrical performance test D stage, EMC test, and mechanical test status;

[0118] S 71 Indicates the status of the heat balance test phase III of the cabin 1 / 2 assembly;

[0119] S 81 Indicates the status of the thermal balance test phase I of the cabin 1 / 2 assembly;

[0120] S 91 Indicates the status of the thermal balance test phase II and thermal vacuum test of the cabin 1 / 2 assembly;

[0121] S 72Indicates the status of thermal balance test and thermal vacuum test of compartment 3;

[0122] S 82 Indicates the status of thermal balance test and thermal vacuum test of cabin 3 / 4 assembly;

[0123] S f Indicates the final status of each compartment after completing the thermal test.

[0124] Using finite states to describe and model the state evolution of the detector during the AIT phase is also very helpful in extracting technical state elements and carrying out technical state control work, conducting state management under the same state through static organization tables, and conducting state control during state migration through dynamic control tables.

Claims

1. A spacecraft modeling technical state control method based on a state machine, characterized in that: include: For each key node in the detector development process, a finite state set S is established; Establish a digital model for all states in the set S; According to the development technology process and related technical documents, the input condition set Σ that causes state changes is constructed, and then the transfer function δ of all states in the development process is obtained; According to the obtained transfer function δ, a state control model of state transfer technology based on state machine is established; The state machine-based state transfer technical state control model is applied to carry out full-cycle and full-process technical state control.

2. A method for controlling a spacecraft modeling technology state based on a state machine according to claim 1, characterized in that: The digital model is established for all states in the set S, including: A 22-dimensional vector Sn is introduced and numbered; n∈[1,N], where N represents the total number of development process states; digital modeling is carried out for the contents represented by the above dimensions.

3. A method for controlling a spacecraft modeling technology state based on a state machine according to claim 2, characterized in that: The contents represented by each dimension of Sn include: final assembly and parking status, measurement and control data transmission link, power supply status, and test product status.

4. A method for controlling a spacecraft modeling technology state based on a state machine according to claim 3, characterized in that: The contents of each dimension that need to be managed in the state include: assembly and parking state assembly-state, measurement and control digital transmission link link-state, power supply state power-state, test product state product-state, thermistor tmr-state and heating circuit ht-state.

5. The method for controlling the technical state of a spacecraft model based on a state machine according to claim 3, characterized in that: The input condition set Σ that causes the state change is constructed, including: According to the model development technical process and the relevant technical documents of AIT stage assembly, electrical test documents and environmental test, sort out the differences between various states and determine the conversion relationship between various states; The 22-dimensional vector digital model Sn is traversed to obtain the state differences between multiple states, that is, the input condition set Σ that causes the state change is obtained.

6. The spacecraft modeling technical state control method based on state machine according to claim 3 is characterized in that: The transfer function δ of all states in the construction process includes: When the detector completes the state transfer process, two parameters are involved, one is the input condition set Σ, and the other is the digital model of the detector state; the state transfer process involves the final assembly state parameters in the input condition set Σ, and the above-mentioned final assembly state parameters are characterized in the constructed digital model to determine the transfer function δ.

7. A method for controlling a spacecraft's technical state based on a state machine according to claim 6, characterized in that: The assembly status parameters include: compartment combination information, equipment installation information, measurement and control data transmission link status, and power supply status; the transfer function δ is expressed as: State 下一个状态 =δ(assembly-state 当前状态 ,link-state 当前状态 ,power-state 当前状态 ,tmr-state 当前状态， State 当前状态… ), the state of each variable in this function is voted on by the relevant parameters in the state transition process.

8. The spacecraft modeling technical state control method based on state machine according to claim 3 is characterized in that: The establishment of a technical state control model based on state machine state transfer includes: using digital models to determine all state models of all nodes in the development technology process or AIT process technology process; applying all constructed state models to establish a technical state control model based on state machine state transfer in the form of a directed graph for the development process.

9. A method for controlling a spacecraft modeling technology state based on a state machine according to claim 8, characterized in that: When the development process is established in the form of a directed graph to establish a technical state control model based on the state transfer of the state machine, the state transfer process is determined by the transfer function δ, and the current state s n It is related to the constructed input condition σ, σ∈Σ; the state transfer function is recorded as δ(s n ,σ)=s n+1 , where: s n 、s n+1 ∈S, indicating that in state s n When the input signal Σ and the current state s n When the condition σ is met, it will transfer to state s n+1 , abbreviated as δ(s n ,σ,s n+1 ); the state transfer function includes three situations: the current state transfers to the next state, the current state transfers to the current state, and the current state transfers to the initial state or a specific state; all states Sn are connected with directed line segments, and the state transfer is completed under the action of the constructed input condition set Σ, that is, the state control model of the state transfer technology based on the state machine is obtained: δ1(s n ,σ1,s n+1 ): current state s n Satisfy the input condition σ1 of the development technology process, from the current state s n Transfer to next state s n+1 ; δ2(s n ,σ2,s n ): current state s n Satisfy the input condition σ2 of the development technology process, from the current state s n Transfer to present state n ; δ3(s n ,σ3,s j，j＝0,1,…n+1 ): current state s n Satisfy the input condition σ3 of the development technology process and transfer from the current state to the initial state or a specific state.

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