CN105334756A - Agile satellite mission interpretation closed loop simulation verification system and method - Google Patents
Agile satellite mission interpretation closed loop simulation verification system and method Download PDFInfo
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Abstract
The invention provides an agile satellite mission interpretation closed loop simulation verification system and method. Efficiency of key links of simulation verification and inversion modification of current agile satellite mission planning can be effectively enhanced, and correct implementation of agile satellite mission planning can be guaranteed. With application of the agile satellite mission interpretation closed loop simulation verification system and method, firstly a satellite mission host mission interpretation function is simulated, a conventional satellite mission test bed is replaced, mission blocks are interpreted into instruction sets which can be performed by a satellite mission host and information of instruction names, parameters and performing time can be visually displayed in a form mode, and mission block interpretation results are automatically interpreted and abnormal information is outputted so that noting of error mission blocks on satellites can be avoided; secondly, the parameters in the mission blocks and mission block settings can be modified and the mission blocks can be generated again by the system, and iterative analysis is performed on the mission blocks so that correctness can be guaranteed, the risk caused by manual arrangement of the mission blocks can be avoided, and mission block generation efficiency and reliability can be enhanced; and finally the interpretation results of the finally generated correct mission blocks are compared with action sequences generated by a mission planning system so that correctness and rationality of mission planning can be verified.
Description
Technical field
The present invention relates to a kind of quick satellite task decipher closed-loop simulation verification system and method.
Background technology
That applies in all trades and professions along with space picture gos deep into gradually, the requirement of user to image data information is more and more higher, need more fast, Computer image genration pattern flexibly, this not only has huge commercial application value, also there is important application value in army, therefore improve the development trend that attitude maneuver ability has become earth observation satellite, and quick satellite generates to adapt to this demand just.Agile satellite attitude maneuvers ability is far away higher than traditional earth observation satellite, side-sway automotive imaging can not only be passed through, also by the motor-driven imaging of pitching, by this ability of rapid attitude maneuver on a large scale, the quick response to observed object and multi-modal imaging function can be realized, but, it is numerous that the application of rapid attitude maneuver imaging satellite faces number of tasks amount, imaging pattern is complicated, the difficulty that instruction sequence is various, the mission planning pattern that tradition simplifies is obviously inapplicable, therefore, mission planning technology becomes bottleneck and the gordian technique of development rapid attitude maneuver imaging satellite.Be limited to the resource-constrained reasons such as the computing power of spaceborne computer, also really cannot realize autonomous mission planning on star at present, and ground-based mission planning system obtains Preliminary Applications because possessing plurality of advantages, quick satellite have employed ground-based mission planning system just.In actual applications, designer needs according to specific tasks, the reasonable arrangement of satellite task and action is realized by ground-based mission planning system, first ground-based mission planning system generates action sequence on the star after planning, then according to action sequence, data block on the star treating upper note with the Form generation of task data block.Spaceborne computer comprises data block on the star of time and the form such as action, task parameters on star by execution, finally completes the imaging of target.But how to verify ground-based mission planning system, how to ensure the correct enforcement that quick satellite task is planned also not having the method for complete set for reference at present.
Summary of the invention
Technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, a kind of quick satellite task decipher closed-loop simulation verification system and method are provided, effectively can solve the key link such as checking emulation, amendment inverting of current quick satellite task planning, the correct enforcement that quick satellite task is planned can be ensured.
Technical solution of the present invention is: a kind of quick satellite task decipher closed-loop simulation verification system, it is characterized in that comprising: centralized control unit, star cope match-plate pattern definition unit, Verification rule definition unit, data format definition unit, generic logic processing unit, data reception processing unit, task data block emulation resolution data output unit and mission planning amendment invert data output unit;
Star cope match-plate pattern definition unit, carries out the definition of relative program control command template on quick Satellite, calls for centralized control unit;
Verification rule definition unit, the Verification rule of definition task data block, Verification rule comprises attitude maneuver data block proof rule, number posting lotus processing batch instruction Verification rule, calls for centralized control unit;
Data format definition unit, the data layout of definition task data block, calls for centralized control unit;
Generic logic processing unit, in completion system, the conventional data logical process of unit, calls for unit; Generic logic process comprises: carry out character to incoming task data block and unify conversion process, the conversion of UTC, Beijing time and Greenwich Mean Time, data layout process;
Data reception processing unit, carries out pre-service to the task data block received, and pretreated data is delivered to centralized control unit;
Centralized control unit, carries out logical process to task data block, if logical process has problem, will carry out warning and identification process; Logical process comprises: non-hexadecimal character process, the process of data space, data block length verification process, data block dominate head checking, data CRC check, data field format verification; After logical process, calling data form definition unit, verifies the data layout of task data block, the check results of data layout is carried out output display simultaneously, is convenient to designer and checks; In checking procedure, once mistake appears in process data layout, centralized control unit will carry out false alarm and identification process; After data block format verification, the Verification rule of the task data block of call parameters proof rule definition unit definition, the parameter information comprised in the task data block pass through data format check verifies, and if there is exception, centralized control unit will carry out false alarm and identification process; After Verification rule is passed through, centralized control unit carries out task data block emulation dissection process, on the quick Satellite now calling the definition of star cope match-plate pattern definition unit, relatively the data layout of the task data block of program control command template and the definition of data format definition unit carries out task data block emulation dissection process, resolves output unit afterwards the result after dissection process is carried out report output by the emulation of task data block; Meanwhile, centralized control unit calling task planning amendment invert data output unit, exports again by final task data block; In centralized control unit processing procedure, call generic logic processing unit simultaneously and carry out conventional data logical process;
Output unit is resolved in task block emulation, exports the statement form after resolving;
Mission planning amendment invert data output unit, carries out mission planning under operation, regenerates the task data block revised, again verify amended task data block and emulate dissection process.
In described star cope match-plate pattern definition unit, field and the structure of the definition of relative program control command template on quick Satellite comprise: coded instructions, instruction name, the execution time, mark, segment identification, instruction perform required time, whether be with parameter instruction, instruction time Δ T, parameter length, wherein the execution time is from relative time T0, coded instructions refers to Star Service coded instructions, instruction name and the instruction name corresponding to Star Service coded instructions, mark and segment identification are mainly used in distinguishing different section instruction, the instruction belonging to like-identified or segment identification will be carried out identical execution by task on star or not perform process, instruction execution required time defines the decimal system duration required for instruction execution, if this instruction is variable order, ginseng instruction items then whether is with to be 1, otherwise be 0, instruction time is the need of consideration Δ T, depend on this instruction in instruction template segment mark whether after spacer segment parameter, if variable order, variable element length value will be provided, and be two byte lengths, otherwise will 0 be defined as.
In described Verification rule definition unit, attitude maneuver data block proof rule is 32 bytes, defines condition code, valid data, defines number and passes antenna number, land station's numbering; Support parameter in task data block extract separately and resolve in detail, 32 byte attitude maneuver data blocks resolved item by item, comprise and resolve condition code code word, valid data code word, number passes antenna number code word, land station's numbering code word; Support reverse systematic function, by feature code value, after valid data parameter modification, regenerate 32 byte attitude maneuver data blocks.
Described centralized control unit introduces Iterator Design Pattern when carrying out parameter rule checking to task data block, by Iterator Design Pattern, can realize the dynamic change adjustment of parameter rule definition.When carrying out concrete parameter rule checking, first call iterator, obtain all parameter rule definition units of definition at present, these regular definition units may comprise the definition of attitude maneuver data rule, and number passes parameter rule definition, the definition of load parameter rule.After obtaining strictly all rules definition unit, according to concrete regular definition unit, by calling unified interface method, parameter rule authentication unit can carry out concrete parameter rule verification operation, thus realizes dynamic authentication parameter rule process.
The data layout of described data format definition unit definition task data block comprises: task build, Meta task number, Meta task number, Meta task start time, task attribute, the Meta task duration, the template number comprised, template number, template starts relative time, each section of template performs mark, spacer segment time, template parameter length and parameter information field.
Described centralized control unit introduces Iterator Design Pattern when carrying out data layout checking to task data block, by Iterator Design Pattern, can realize the dynamic change adjustment of data format definition.When carrying out concrete data layout checking, first iterator is called, obtain all data format definition unit of definition at present, centralized control unit is according to concrete data format definition unit, by calling unified interface method, data layout authentication unit carries out concrete data layout verification operation, thus realizes the process of dynamic authentication data layout.
Described mission planning amendment invert data output unit, carries out mission planning under operation, can regenerate the task data block revised, again verify amended task data block and emulate dissection process.
Statement form after output unit output is resolved in described task block emulation comprises: instruction sequence and form inversion sequence, wherein instruction sequence comprises: UTC value when the satellite and the rocket are separated, task block code word, Meta task number, the Meta task number finally processed, the Meta task start time finally processed, the Meta task attribute finally processed, the Meta task duration finally processed, the template number that the Meta task finally processed comprises, instruction name, order parameter, instruction starts to perform Beijing time, instruction starts to perform Greenwich Mean Time, instruction starts to perform the UTC time, during appearance control star, form inversion sequence comprises: data content, and code word illustrates, instruction block number, Meta task number, template number, other information or error message
A kind of quick satellite task decipher closed-loop simulation verification method, step is as follows:
(1) configuration task information, before carrying out task decipher emulation, needs to carry out mission bit stream configuration to task data block, different task types, the mission bit stream that flexible customization is different, these mission bit streams comprise: star cope match-plate pattern defines, the definition of Verification rule, data format definition;
(2) task data block is noted in checking, format verification is carried out to task data block, comprises data length checking, data head checking, check code word checking, Meta task number conflict checking, the checking of Meta task time verifying, task attribute, template parameter checking, template attributes checking, the checking of attitude maneuver data layout; Meanwhile, simulation on-board processing unit carries out nine serious mistake mode treatment to upper note task data block, comprises and has 1. exceeded maximum permission Meta task quantity; 2. the Meta task that the task data block inside of upper note comprises has exceeded maximum permission number; 3. the template of certain Meta task has exceeded maximum number of byte; 4. multiple Meta task does not arrange according to time order and function order; 5. template does not arrange according to time order and function order; 6. the end time of previous Meta task is larger than the end time of a rear Meta task; 7. the start time of last Meta task of data inserting block is greater than the initial time of insertion position; 8. the end time of last Meta task of data inserting block is greater than the end time of insertion position; 9. other mistakes; If it is entirely true checking to be noted task data block, then enter step (3); If checking is not passed through, then point out according to authentication failed type, jump to step (4);
(3) task simulation is resolved, first, task simulation parsing on star is carried out to the task data block that ground task grouping generates, according to task data block format, task data block is finally resolved to instruction sequence, abnormal information also exports by automatic interpretation task block interpretation result, avoid wrong task block being noted satellite secondly, task data block is carried out form inverting, the format information that inverting becomes quick satellite system to identify, the action sequence that the interpretation result of the task data block finally generated and task grouping generate is compared simultaneously, the correctness of validation task planning and rationality, finally, according to Meta task number, detailed decipher process is carried out, further thinning processing result to batch instruction in task data block and attitude maneuver data block, task simulation enters step (5) after resolving and terminating, if satellite system designer produces objection to analysis result, need amendment task data block, then enter step (4),
(4) mission planning amendment inverting, once ground-based mission planning system generation task data block is wrong, can be modified to the wrong parameter in task block by human-computer interaction interface, regenerate task block and iterative analysis is carried out to ensure correctness to task block, avoid the risk that manual layout task block is brought, improve efficiency and the reliability of task block generation; If revised, now enter step (1);
(5) if task decipher closed-loop simulation is correct, then this task data block will be submitted to ground control station, and upper note carries out specific tasks execution to satellite, terminate; If satellite system designer goes out current task query need amendment, then enter step (4).
The present invention compared with prior art has the following advantages:
(1) Star Service emulation.Also do not have ready-made technology to carry out reference at present, more common way carries out Star Service test envelope test simulation.But Star Service test envelope, to mission planning data block format checking limitation, can only carry out part checking, once checking is not passed through, task amendment inverting cannot be carried out.In addition, Star Service test envelope cannot cover third-party authentication object, such as cannot verify the motor-driven data block of appearance control, cannot proof load processing batch instruction etc., and Star Service test envelope is higher to application environmental requirement simultaneously, needs specific equipment.And the present invention can not only cover all format verification, and emulation parsing can be carried out, cover third-party authentication object, generate the instruction sequence that satellite system designer can intuitively see, checking is not passed through or does not meet the place of designer's requirement, mission planning amendment inverting can be carried out.Use this method simultaneously, require lower for machine environment, can carry out whenever and wherever possible, effectively can solve the key link such as checking emulation, amendment inverting of current quick satellite task planning, the correct enforcement that quick satellite task is planned can be ensured.
(2) close-loop feedback.The present invention is an iterative process, by task data block after task block checking, task block emulation parsing, mission planning amendment inverting, regenerates the task data block that ground-based mission planning system exports.By the present invention, the parameter in task block, Operation system setting are modified, regenerated task block and carry out iterative analysis to ensure its correctness to it, avoid the risk that manual layout task block is brought, improve efficiency and the reliability of task block generation.This amendment, inverting, decipher process can constantly be carried out repeatedly, and method is flexible.
(3) precise alignment.Compared with traditional simulation system, the present invention not only can carry out emulation decipher process, and can generative approach Shi Zhiguan instruction sequence, the form inversion sequence seen, facilitates mission planning designer intuitively to revise.The action sequence that the interpretation result of the correct task block finally generated and task grouping generate is compared simultaneously, can validation task planning correctness and rationality.
(4) the anti-solution of finger is criticized.Utilize the present invention, logarithm posting lotus processing batch instruction parameter, attitude maneuver data block can carry out decipher in detail in real time, more directly perceived to the interpretation of data block correctness; Support automatically to generate number biography, load processing batch instruction parameter, attitude maneuver data block, regenerate task data block more precisely convenient.
(5) applying flexible.Use the present invention, can flexible configuration be carried out.Invention introduces the Iterator Design Pattern in Design Mode, can dynamically adapting different parameter rule definition and data format definition, different models, by configuring different parameter rule definition and data format definition, just can adapt to the needs of different task type.Meanwhile, different templates can be customized for different model or task type, realize the flexible adjustment of task type, adapt to more model needs.
(6) the invention provides a total solution, can be realized by software programming, greatly reduce the workload that artificial nucleus is right, decrease the workload of the intermediate links such as checking, emulation, planning amendment, improve work efficiency.
Accompanying drawing explanation
Fig. 1 is task decipher closed-loop simulation authentication function iteration diagram of the present invention;
Fig. 2 is task decipher closed-loop simulation authentication module structural drawing of the present invention;
Fig. 3 is the Iterator Design Pattern class figure that the present invention introduces;
Fig. 4 is parameter rule dynamic authentication realization flow figure of the present invention;
Fig. 5 is data layout dynamic authentication realization flow figure of the present invention;
Fig. 6 is centralized control unit Processing tasks data block of the present invention emulation process of analysis figure;
Fig. 7 is that task decipher closed-loop simulation of the present invention checking uses flow chart of steps.
Embodiment
Be illustrated in figure 1 function iteration diagram of the present invention, major function comprises three broad aspect: above note task block emulation parsing, the checking of upper note task block and mission planning amendment inverting function.
It is that the task data block generated ground task grouping carries out task simulation parsing on star that major function is resolved in upper note task block emulation, according to upper note data block format, task data block is finally resolved to instruction sequence and instruction Starting Executing Time, wherein instruction sequence comprises instruction name and order parameter, instruction Starting Executing Time comprise Beijing time, Greenwich Mean Time, the UTC time and appearance control star time.Simultaneously, upper note task data block is carried out form inverting by system, the format information that inverting becomes onboard system to identify, its form inverting mainly comprises code word on format content, the corresponding star of format content, format content illustrates, format order block number, form Meta task number, template number and other information or error message etc.
Upper note task block checking major function is to before upper note task block emulation parsing, carry out task block checking to upper note data block, the number that main checking upper note task data block format, upper note task attitude maneuver data block, upper note task agent contain passes and load command parameter information.Meanwhile, system can be simulated on-board processing unit and carry out nine serious mistake mode treatment to upper note task block, comprises and has 1. exceeded maximum permission Meta task quantity; 2. the Meta task quantity that the task block inside of upper note comprises has exceeded maximum permission number; 3. the template of certain task has exceeded maximum number of byte; 4. multiple Meta task does not arrange according to time order and function order; 5. template does not arrange according to time order and function order; 6. the end time of previous Meta task is larger than the end time of a rear task; 7. the start time of last Meta task of data inserting block is greater than the initial time of insertion position; 8. the end time of last Meta task of data inserting block is greater than the end time of insertion position; 9. other mistakes.For verifying the item do not passed through, alert process is carried out identification process with different colours to error items by system simultaneously, is convenient to designer and carries out quick position to abnormal task data block.
Mission planning amendment inverting function is mainly modified to mission planning content, and again generates task data block.Once ground-based mission planning system generation task data block is wrong, designer can to modify operation for mission planning data, and again apply this instrument generation task data block, carry out star being noted by data block or contrasting with the task data block that ground-based mission planning system regenerates, confirm that ground-based mission planning system generates the correctness of data block.
As shown in Figure 1, task decipher closed-loop simulation verification system three zones, by the task data block composition iterative function generated with ground-based mission planning system, also namely this instrument is used, task data block can be verified through upper note task block, upper note task block emulation resolve, mission planning amendment inverting after, regenerate ground-based mission planning system export task data block.
The checking of task decipher closed-loop simulation is implemented module and is mainly comprised: centralized control unit, star cope match-plate pattern definition unit, Verification rule definition unit, data format definition unit, generic logic processing unit, data reception processing unit, task block emulation resolution data output unit and mission planning amendment invert data output unit.System module structural drawing is illustrated in fig. 2 shown below.
Star cope match-plate pattern definition unit mainly carries out the definition of relative program control command template on quick Satellite.The quick satellite stage in orbit, can handling and dirigibility for improving satellite, control to adopt on ground to the operation of load and note task data block form, on star, Star Service main frame Automatically invoked template carries out the operation control mode that decipher generates instruction.Star cope match-plate pattern definition unit definition primary fields and structure comprise: coded instructions, instruction name, the execution time, mark, segment identification, instruction perform required time, whether be with parameter instruction, instruction time Δ T, parameter length.Wherein the execution time is from relative time T0, coded instructions refers to Star Service coded instructions, instruction name and the instruction name corresponding to Star Service coded instructions, mark and segment identification are mainly used in distinguishing different section instruction, the instruction belonging to like-identified or segment identification will be carried out identical execution by task on star or not perform process, instruction performs the decimal system duration required for required time main definitions instruction execution, if this instruction is variable order, ginseng instruction items then whether is with to be 1, otherwise be 0, instruction time is the need of consideration Δ T, depend on this instruction in instruction template segment mark whether after spacer segment parameter.If variable order, variable element length value will be provided, and be generally two byte lengths, otherwise will 0 be defined as.
Parameter rule definition unit main definitions is noted task attitude maneuver data block, several posting lotus processing batch instruction parameter rule definition information that upper note task agent contains.Such as go up in note task attitude maneuver data block 32 bytes, certain byte defines condition code, valid data, certain byte defines number and passes antenna number, land station's numbering etc., by defining this information, system will carry out parameter information verification according to respective rule to upper note task data block, once not be inconsistent with the rule of definition, system will carry out alarm.Parameter in task block is extracted separately and is carried out detailed analytical capabilities by simultaneity factor support, and as 32 byte attitude maneuver data blocks resolved item by item, condition code code word, valid data code word, number passes antenna number code word etc.Meanwhile, system also supports reverse systematic function, as by feature code value, after the parameter modifications such as valid data, regenerates 32 byte attitude maneuver data blocks.
Different satellite model, definition for parameter rule may be different, for quick satellite, also there is different phase the definition of parameter rule is changed, system needs adapt to this kind of change and there will not be large change, and this just needs to introduce a kind of Iterator Design Pattern (ITERATOR).Iterator Design Pattern provides each element in a kind of method sequential access aggregate objects, and don't needs the internal representation exposing this object.As shown in Fig. 3 of the present invention, Iterator defines the interface of iterator access and traversal element; ConcreteIterator achieves concrete iterator; Aggregate defines container, creates the interface of corresponding iterator objects; ConcreteAggregate is concrete container, achieves the interface creating corresponding iterator, and this operation returns the suitable example of of ConcreteIterator; Client is caller, and the Iterator Design Pattern of all establishments is for caller.
By Iterator Design Pattern, the dynamic change adjustment of parameter rule definition can be realized.As shown in Fig. 4 of the present invention, when carrying out concrete parameter rule checking, first system calls iterator, all parameter rule definition units of acquisition definition at present, these regular definition units may comprise the definition of attitude maneuver data rule, the definition of number biography parameter rule, the definition of load parameter rule and other rules unit to be defined.After obtaining strictly all rules definition unit, according to concrete regular definition unit, by calling unified interface method, parameter rule authentication unit carries out concrete parameter rule verification operation, thus realizes dynamic authentication parameter rule process.
Data format definition unit main definitions is noted the format information required for task data block, typical data format information comprises task build, Meta task number, Meta task number, Meta task start time, task attribute, Meta task duration, the template number comprised, template number, template start relative time, each section of template performs mark, spacer segment time, template parameter length and parameter information field.
As shown in Fig. 5 of the present invention, for the checking of data format definition unit, adopt Iterator Design Pattern, thus adapt to the change adjustment of data format definition unit.When carrying out concrete data layout checking, first system calls iterator, obtain all data format definition unit of definition at present, these data format definition unit may comprise task block header format definition unit, a Meta task number format definition unit, Meta task form definition unit and other format unit to be defined.After obtaining all data format definition unit, according to concrete data format definition unit, by calling unified interface method, data layout authentication unit carries out concrete data layout verification operation, thus realizes the process of dynamic authentication data layout.
The main task of data reception processing unit is input and the interrelated logic process of task data block, is the data input module of whole system.
The process of the main completion system logical block of generic logic processing unit, calls for system, such as carries out character to input block and unifies conversion process, the Logical processing unit such as conversion of UTC, Beijing time and Greenwich Mean Time.
Output unit is resolved in task block emulation, and export the statement form after resolving, statement form comprises: instruction sequence and form inversion sequence.Wherein instruction sequence comprises: UTC value when the satellite and the rocket are separated, task block code word, Meta task number, the Meta task number finally processed, the Meta task start time finally processed, the Meta task attribute (sexadecimal) finally processed, the Meta task mission duration finally processed, the template number that the Meta task finally processed comprises, instruction name, order parameter, instruction start to perform Beijing time, when instruction starts to perform Greenwich Mean Time, instruction starts to perform UTC time, appearance control star; Form inversion sequence comprises: data content, code word, explanation, instruction block number, Meta task number, template number, other information or error message.
Mission planning amendment invert data output unit, carries out mission planning under operation, regenerates the task data block revised, and can re-start checking and emulation dissection process to amended task data block
Centralized control unit is system essential core module, is responsible for calling each system module.For typical task data block emulation process of analysis as shown in Figure 6: first system carries out logical process to the task data block received by data reception processing unit, if logical process has problem, system will carry out warning and identification process, as contained non-hexadecimal character etc. in data block.After Logical processing unit, carry out the verification of task data block format, format check result is carried out output display simultaneously, be convenient to designer and check.In checking procedure, once processing format mistake, the task that the task block inside of such as upper note comprises has exceeded 13 etc., and system will be reported to the police also identification process.After data block format verification, the parameter information comprised in the data block passed through format check verifies by system, and if there is exception, such as variable element totally 5, parameter information only has 4 etc., and system will carry out warning also identification process.After all passing through, system will carry out task data block emulation dissection process, and calling task block emulation is simultaneously resolved output unit and the result after dissection process is carried out report output.For system alarm and the place of identification process, satellite system designer can carry out mission planning amendment according to type of alarm, amendment completes, mission planning under operation can be carried out, regenerate the mission planning data block revised, amended mission planning data block is again verified and emulated dissection process, thus completes quick satellite task decipher closed loop flow process.
As shown in Fig. 7 of the present invention, a kind of quick satellite task decipher closed-loop simulation verification method, use step is in actual use as follows:
(1) configuration task information, before carrying out task decipher emulation, needs to carry out mission bit stream configuration to task data block, different task types, the mission bit stream that flexible customization is different, these mission bit streams comprise: star cope match-plate pattern defines, the definition of Verification rule, data format definition;
(2) task data block is noted in checking, format verification is carried out to task data block, comprises data length checking, data head checking, check code word checking, Meta task number conflict checking, the checking of Meta task time verifying, task attribute, template parameter checking, template attributes checking, the checking of attitude maneuver data layout; Meanwhile, simulation on-board processing unit carries out nine serious mistake mode treatment to upper note task data block, comprises and has 1. exceeded maximum permission Meta task quantity; 2. the Meta task that the task data block inside of upper note comprises has exceeded maximum permission number; 3. the template of certain Meta task has exceeded maximum number of byte; 4. multiple Meta task does not arrange according to time order and function order; 5. template does not arrange according to time order and function order; 6. the end time of previous Meta task is larger than the end time of a rear Meta task; 7. the start time of last Meta task of data inserting block is greater than the initial time of insertion position; 8. the end time of last Meta task of data inserting block is greater than the end time of insertion position; 9. other mistakes; If it is entirely true checking to be noted task data block, then enter step (3); If checking is not passed through, then point out according to authentication failed type, jump to step (4);
(3) task simulation is resolved, first, task simulation parsing on star is carried out to the task data block that ground task grouping generates, according to task data block format, task data block is finally resolved to instruction sequence, abnormal information also exports by automatic interpretation task block interpretation result, avoid wrong task block being noted satellite secondly, task data block is carried out form inverting, the format information that inverting becomes quick satellite system to identify, the action sequence that the interpretation result of the task data block finally generated and task grouping generate is compared simultaneously, the correctness of validation task planning and rationality, finally, according to Meta task number, detailed decipher process is carried out, further thinning processing result to batch instruction in task data block and attitude maneuver data block, task simulation enters step (5) after resolving and terminating, if satellite system designer produces objection to analysis result, need amendment task data block, then enter step (4),
(4) mission planning amendment inverting, once ground-based mission planning system generation task data block is wrong, can be modified to the wrong parameter in task block by human-computer interaction interface, regenerate task block and iterative analysis is carried out to ensure correctness to task block, avoid the risk that manual layout task block is brought, improve efficiency and the reliability of task block generation; If revised, now enter step (1);
(5) if task decipher closed-loop simulation is correct, then this task data block will be submitted to ground control station, and upper note carries out specific tasks execution to satellite, terminate; If satellite system designer goes out current task query need amendment, then enter step (4).
Claims (9)
1. a quick satellite task decipher closed-loop simulation verification system, it is characterized in that comprising: centralized control unit, star cope match-plate pattern definition unit, Verification rule definition unit, data format definition unit, generic logic processing unit, data reception processing unit, task data block emulation resolution data output unit and mission planning amendment invert data output unit;
Star cope match-plate pattern definition unit, carries out the definition of relative program control command template on quick Satellite, calls for centralized control unit;
Verification rule definition unit, the Verification rule of definition task data block, Verification rule comprises attitude maneuver data block proof rule, number posting lotus processing batch instruction Verification rule, calls for centralized control unit;
Data format definition unit, the data layout of definition task data block, calls for centralized control unit;
Generic logic processing unit, in completion system, the conventional data logical process of unit, calls for unit; Generic logic process comprises: carry out character to incoming task data block and unify conversion process, the conversion of UTC, Beijing time and Greenwich Mean Time, data layout process;
Data reception processing unit, carries out pre-service to the task data block received, and pretreated data is delivered to centralized control unit;
Centralized control unit, carries out logical process to task data block, if logical process has problem, will carry out warning and identification process; Logical process comprises: non-hexadecimal character process, the process of data space, data block length verification process, data block dominate head checking, data CRC check, data field format verification; After logical process, calling data form definition unit, verifies the data layout of task data block, the check results of data layout is carried out output display simultaneously, is convenient to designer and checks; In checking procedure, once mistake appears in process data layout, centralized control unit will carry out false alarm and identification process; After data block format verification, the Verification rule of the task data block of call parameters proof rule definition unit definition, the parameter information comprised in the task data block pass through data format check verifies, and if there is exception, centralized control unit will carry out false alarm and identification process; After Verification rule is passed through, centralized control unit carries out task data block emulation dissection process, on the quick Satellite now calling the definition of star cope match-plate pattern definition unit, relatively the data layout of the task data block of program control command template and the definition of data format definition unit carries out task data block emulation dissection process, resolves output unit afterwards the result after dissection process is carried out report output by the emulation of task data block; Meanwhile, centralized control unit calling task planning amendment invert data output unit, exports again by final task data block; In centralized control unit processing procedure, call generic logic processing unit simultaneously and carry out conventional data logical process;
Output unit is resolved in task block emulation, exports the statement form after resolving;
Mission planning amendment invert data output unit, carries out mission planning under operation, regenerates the task data block revised, again verify amended task data block and emulate dissection process.
2. the quick satellite task decipher closed-loop simulation verification system according to claim, it is characterized in that: in described star cope match-plate pattern definition unit, field and the structure of the definition of relative program control command template on quick Satellite comprise: coded instructions, instruction name, the execution time, mark, segment identification, instruction perform required time, whether be with parameter instruction, instruction time Δ T, parameter length, wherein the execution time is from relative time T0, coded instructions refers to Star Service coded instructions, instruction name and the instruction name corresponding to Star Service coded instructions, mark and segment identification are mainly used in distinguishing different section instruction, the instruction belonging to like-identified or segment identification will be carried out identical execution by task on star or not perform process, instruction execution required time defines the decimal system duration required for instruction execution, if this instruction is variable order, ginseng instruction items then whether is with to be 1, otherwise be 0, instruction time is the need of consideration Δ T, depend on this instruction in instruction template segment mark whether after spacer segment parameter, if variable order, variable element length value will be provided, and be two byte lengths, otherwise will 0 be defined as.
3. the quick satellite task decipher closed-loop simulation verification system according to claim, it is characterized in that: in described Verification rule definition unit, attitude maneuver data block proof rule is 32 bytes, define condition code, valid data, define number and pass antenna number, land station's numbering; Support parameter in task data block extract separately and resolve in detail, 32 byte attitude maneuver data blocks resolved item by item, comprise and resolve condition code code word, valid data code word, number passes antenna number code word, land station's numbering code word; Support reverse systematic function, by feature code value, after valid data parameter modification, regenerate 32 byte attitude maneuver data blocks.
4. the quick satellite task decipher closed-loop simulation verification system according to claim, it is characterized in that: when described centralized control unit carries out parameter rule checking to task data block, introduce Iterator Design Pattern, by Iterator Design Pattern, the dynamic change adjustment of parameter rule definition can be realized.When carrying out concrete parameter rule checking, first call iterator, obtain all parameter rule definition units of definition at present, these regular definition units may comprise the definition of attitude maneuver data rule, and number passes parameter rule definition, the definition of load parameter rule.After obtaining strictly all rules definition unit, according to concrete regular definition unit, by calling unified interface method, parameter rule authentication unit can carry out concrete parameter rule verification operation, thus realizes dynamic authentication parameter rule process.
5. the quick satellite task decipher closed-loop simulation verification system according to claim, is characterized in that: the data layout of described data format definition unit definition task data block comprises: task build, Meta task number, Meta task number, the Meta task start time, task attribute, Meta task duration, the template number comprised, template number, template starts relative time, and each section of template performs mark, spacer segment time, template parameter length and parameter information field.
6. the quick satellite task decipher closed-loop simulation verification system according to claim, it is characterized in that: when described centralized control unit carries out data layout checking to task data block, introduce Iterator Design Pattern, by Iterator Design Pattern, the dynamic change adjustment of data format definition can be realized.When carrying out concrete data layout checking, first iterator is called, obtain all data format definition unit of definition at present, centralized control unit is according to concrete data format definition unit, by calling unified interface method, data layout authentication unit carries out concrete data layout verification operation, thus realizes the process of dynamic authentication data layout.
7. the quick satellite task decipher closed-loop simulation verification system according to claim, it is characterized in that: described mission planning amendment invert data output unit, carry out mission planning under operation, the task data block revised can be regenerated, amended task data block is again verified and emulated dissection process.
8. the quick satellite task decipher closed-loop simulation verification system according to claim, it is characterized in that: the statement form after output unit output is resolved in described task block emulation comprises: instruction sequence and form inversion sequence, wherein instruction sequence comprises: UTC value when the satellite and the rocket are separated, task block code word, Meta task number, the Meta task number finally processed, the Meta task start time finally processed, the Meta task attribute finally processed, the Meta task duration finally processed, the template number that the Meta task finally processed comprises, instruction name, order parameter, instruction starts to perform Beijing time, instruction starts to perform Greenwich Mean Time, instruction starts to perform the UTC time, during appearance control star, form inversion sequence comprises: data content, and code word illustrates, instruction block number, Meta task number, template number, other information or error message.
9. a quick satellite task decipher closed-loop simulation verification method, is characterized in that step is as follows:
(1) configuration task information, before carrying out task decipher emulation, needs to carry out mission bit stream configuration to task data block, different task types, the mission bit stream that flexible customization is different, these mission bit streams comprise: star cope match-plate pattern defines, the definition of Verification rule, data format definition;
(2) task data block is noted in checking, format verification is carried out to task data block, comprises data length checking, data head checking, check code word checking, Meta task number conflict checking, the checking of Meta task time verifying, task attribute, template parameter checking, template attributes checking, the checking of attitude maneuver data layout; Meanwhile, simulation on-board processing unit carries out nine serious mistake mode treatment to upper note task data block, comprises and has 1. exceeded maximum permission Meta task quantity; 2. the Meta task that the task data block inside of upper note comprises has exceeded maximum permission number; 3. the template of certain Meta task has exceeded maximum number of byte; 4. multiple Meta task does not arrange according to time order and function order; 5. template does not arrange according to time order and function order; 6. the end time of previous Meta task is larger than the end time of a rear Meta task; 7. the start time of last Meta task of data inserting block is greater than the initial time of insertion position; 8. the end time of last Meta task of data inserting block is greater than the end time of insertion position; 9. other mistakes; If it is entirely true checking to be noted task data block, then enter step (3); If checking is not passed through, then point out according to authentication failed type, jump to step (4);
(3) task simulation is resolved, first, task simulation parsing on star is carried out to the task data block that ground task grouping generates, according to task data block format, task data block is finally resolved to instruction sequence, abnormal information also exports by automatic interpretation task block interpretation result, avoid wrong task block being noted satellite secondly, task data block is carried out form inverting, the format information that inverting becomes quick satellite system to identify, the action sequence that the interpretation result of the task data block finally generated and task grouping generate is compared simultaneously, the correctness of validation task planning and rationality, finally, according to Meta task number, detailed decipher process is carried out, further thinning processing result to batch instruction in task data block and attitude maneuver data block, task simulation enters step (5) after resolving and terminating, if satellite system designer produces objection to analysis result, need amendment task data block, then enter step (4),
(4) mission planning amendment inverting, once ground-based mission planning system generation task data block is wrong, can be modified to the wrong parameter in task block by human-computer interaction interface, regenerate task block and iterative analysis is carried out to ensure correctness to task block, avoid the risk that manual layout task block is brought, improve efficiency and the reliability of task block generation; If revised, now enter step (1);
(5) if task decipher closed-loop simulation is correct, then this task data block will be submitted to ground control station, and upper note carries out specific tasks execution to satellite, terminate; If satellite system designer goes out current task query need amendment, then enter step (4).
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