A method and device for calculating the starting-up time of integrated attitude and orbit control

Abstract

The application provides a method and device for calculating the integrated start-up time of attitude and orbit control, and the method comprises the following steps: obtaining the start-up number and start-up identifier of an engine to determine the start-up mode of the engine; configuring a weighting coefficient according to the start-up mode; and calculating the integrated start-up time according to the weighting coefficient and the start-up mode. The application calculates the integrated start-up time by assigning different weighting parameters to different start-up modes, so that the parameter adjustment is simple and flexible, the method is applicable to various spacecraft platforms in the case of simple design, the telemetry, tracking and control software is no longer tightly bound to the spacecraft platform, the method has good universality, is convenient to apply, reduces unnecessary software changes, and reduces the influence on the safety of the software system.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of engine scheduling, and particularly relates to a method and device for calculating the opening time of an integrated attitude and orbit control. BACKGROUND

[0002] A spacecraft is usually equipped with dozens of engines of different types, which have different thrust sizes and installation positions and are used to maintain or change the attitude and orbit of the spacecraft in operation. One or more types and one or more engines are usually combined to use the engines to produce different degrees of reasoning output to achieve the desired attitude or nominal orbit of the spacecraft.

[0003] As shown in FIG. 1, a spacecraft is equipped with one A-type large-thrust main engine, four B-type medium-thrust engines, and eight C-type small-thrust engines, a total of 13 engines of three types, which are used for the control and maintenance of the attitude and orbit of the spacecraft during on-orbit operation (hereinafter referred to as attitude and orbit control). Figure 1 Generally, when the number of engines of the same type is odd, only one control mode is adopted, that is, all the engines of the same type are started; and when the number of engines of the same type is even, the control mode of starting the even-numbered engines at symmetrical positions is adopted.

[0004] When the same type of engine is started alone or multiple types of engines are combined to start for the attitude and orbit control of the spacecraft, the following factors will have an impact:

[0005] First, the shutdown action of the engine is not completed instantaneously, but is a continuous process for a short period of time, and the shutdown process has a post-effect on the control effect of the spacecraft. Therefore, when evaluating the control effect, the theoretically preset continuous opening time length cannot be directly used, but a weighting coefficient needs to be multiplied;

[0006] Second, when the engine is working, it usually continuously opens, maintains stable thrust output within the theoretically preset continuous opening time length, and then shuts down. In addition, the engine also adopts the mode of short-interval pulse ignition to intermittently open for a short time within the theoretically preset continuous opening time length to output thrust. Therefore, when evaluating the control effect, the theoretically preset continuous opening time length cannot be directly used, but a weighting coefficient needs to be multiplied;

[0007] Third, the propelling pipeline of the engine is usually in a vacuum state, and the propellant needs to be filled before opening and the residual propellant needs to be blown away after shutdown, which will also affect the control effect of the spacecraft. Therefore, the weighting coefficient of the previous factor needs to be adjusted according to the type of the engine.

[0008] Finally, when different types of engines are started in combination, due to different orbit control strategy designs, the engines of different types may not be ignited at the same time, and the duration of the continuous operation of the engines of different types is also not the same.

[0009] In summary, in order to comprehensively evaluate the overall thrust generated by the propulsion system, accurately calculate the overall state of the spacecraft including fuel consumption, spatial position change, speed change and other factors, judge whether the control is successful, and set the subsequent state, it is necessary to calculate a comprehensive operation time length according to the type and number of engines assembled on the spacecraft, and in combination with the actual use mode of the engine, to obtain data that approximates the real situation as much as possible, and to provide a basis for measurement and control implementation. SUMMARY

[0010] The present application provides a method and device for calculating the integrated operation time of attitude and orbit control, to at least solve the problem that the integrated operation time of attitude and orbit control cannot be accurately estimated at present, the measurement and control software function is fixedly bound with a specific spacecraft platform, and the flexibility, universality and expandability are poor.

[0011] According to a first aspect of the present application, a method for calculating the integrated operation time of attitude and orbit control is provided, comprising:

[0012] The number of engine starts and the start identifier are obtained to determine the start mode of the engine;

[0013] The weighting coefficient is configured according to the start mode;

[0014] The integrated operation time is calculated according to the weighting coefficient and the start mode.

[0015] In an embodiment, when the start mode is a single start mode, the weighting coefficient is configured according to the start mode, comprising:

[0016] If the number of engine starts is odd or two, the weighting coefficient is set to

[0017] If the number of engine starts is an even number greater than two, different weighting coefficients are configured for each engine.

[0018] In an embodiment, when the start mode is a combined start, the weighting coefficient is configured according to the start mode, comprising:

[0019] The weighting coefficient is looked up according to the start identifier of all engines.

[0020] In an embodiment, when the start mode is a single start, the integrated operation time is calculated according to the weighting coefficient and the start mode, comprising:

[0021] The integrated operation time is directly calculated by multiplying the obtained theoretical operation time by the weighting coefficient.

[0022] In an embodiment, when the starting mode is the combined starting, the comprehensive starting duration is calculated according to the weighting coefficient and the starting mode, comprising:

[0023] judging whether to calculate the comprehensive starting duration by the maximum value method;

[0024] if yes, taking the maximum value of the comprehensive starting duration of each type of engine as the comprehensive starting duration;

[0025] if no, calculating the comprehensive duration of each type of engine according to the weighting coefficient, and adding the comprehensive durations of the engines to obtain the comprehensive starting duration.

[0026] According to another aspect of the present application, a posture and orbit control comprehensive starting duration calculation device is also provided, comprising:

[0027] an acquisition unit configured to acquire the starting number and the starting identifier of the engine to determine the starting mode of the engine;

[0028] a weighting coefficient configuration unit configured to configure the weighting coefficient according to the starting mode;

[0029] a comprehensive starting duration calculation unit configured to calculate the comprehensive starting duration according to the weighting coefficient and the starting mode.

[0030] In an embodiment, when the starting mode is the separate starting mode, the weighting coefficient configuration unit comprises:

[0031] a first configuration module configured to set the weighting coefficient as 1 if the starting number of the engine is an odd number or two;

[0032] a second configuration module configured to configure different weighting coefficients for the engines respectively if the starting number of the engine is an even number greater than two.

[0033] In an embodiment, when the starting mode is the combined starting, the weighting coefficient configuration unit comprises:

[0034] a third configuration module configured to look up the weighting coefficient set in advance according to the starting identifier of all the engines.

[0035] In an embodiment, when the starting mode is the separate starting, the comprehensive starting duration calculation unit comprises:

[0036] a first calculation module configured to directly calculate the comprehensive starting duration according to the acquired theoretical starting duration multiplied by the weighting coefficient.

[0037] In an embodiment, when the starting mode is the combined starting, the comprehensive starting duration calculation unit comprises:

[0038] a judging module, configured to judge whether to calculate the comprehensive start-up time length by using a maximum value method;

[0039] a maximum value calculating module, configured to, if yes, take the maximum value of the comprehensive start-up time length of each type of engine as the comprehensive start-up time length;

[0040] a second calculating module, configured to, if no, calculate the comprehensive start-up time length of each type of engine according to the weighting coefficient, and add the comprehensive start-up time length of each type of engine to obtain the comprehensive start-up time length.

[0041] The application calculates the comprehensive start-up time length by assigning different weighting parameters to different starting modes, so that the parameter adjustment is simple and flexible, and the application is suitable for various spacecraft platforms in the case of simple design, the TT&C software and the spacecraft platform are no longer tightly bound, the application is good in universality, convenient to apply, unnecessary software changes are reduced, and the influence on the safety of the software system is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0042] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description only constitute some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0043] Figure 1 is a layout diagram of an engine of a spacecraft in the prior art.

[0044] Figure 2 is a method for calculating a comprehensive start-up time length of attitude and orbit control provided by the present application.

[0045] Figure 3 is a weighting coefficient configured according to a starting mode when the starting mode is a single starting mode in the embodiment of the present application.

[0046] Figure 4 is a comprehensive start-up time length calculated according to the weighting coefficient and the starting mode when the starting mode is a combined starting in the embodiment of the present application.

[0047] Figure 5 is a method and device for calculating a comprehensive start-up time length of attitude and orbit control implemented in the embodiment of the present application.

[0048] Figure 6 is a device for calculating a comprehensive start-up time length of attitude and orbit control provided by the present application.

[0049] Figure 7 is a structure block diagram of a weighting coefficient configuration unit in the embodiment of the present application.

[0050] Figure 8A structure block diagram of a comprehensive start-up time length calculation unit in an embodiment of the present application.

[0051] Figure 9 A specific embodiment of an electronic device in an embodiment of the present application. DETAILED DESCRIPTION

[0052] The technical solutions in the embodiments of the present application will be clearly and completely described in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0053] With the increasing demand for diversity, the types of spacecraft platforms gradually increase, and the assembly and use of engines are flexible and diverse. The TT&C software system still uses the existing scheme, and only the scheme, algorithm and software are written for each specific spacecraft platform. The TT&C software function is fixedly bound to the specific spacecraft platform, and the flexibility, universality and scalability are poor. Whenever a new spacecraft platform is put into use or a new engine configuration mode appears, the corresponding TT&C software must be specially coded and developed to realize the specific requirements in the scheme, which causes the TT&C software system to be frequently changed, resulting in a significant decline in the stability and safety of the TT&C software system.

[0054] Taking the spacecraft in Figure 1 as an example, as shown in Table 1, when only the same type of engine is started (hereinafter referred to as single start), the A-type engine has one use mode; the B-type engine has two use modes of 2B and 4B, respectively indicating 2 and 4 B-type engines starting; and the C-type engine has four use modes of 2C, 4C, 6C and 8C, respectively indicating 2, 4, 6 and 8 C-type engines starting.

[0055] Table 1: List of single start modes of the same type of engine

[0056] A-type engine B-type engine C-type engine A 2B 2C 4B 4C 6C 8C

[0057] Further, as shown in Table 2, when multiple types of engines are started (hereinafter referred to as combined start), the A and B type engines have two combined start modes, the A and C type engines have four combined start modes, the B and C type engines have eight combined start modes, and the A, B and C type engines have eight combined start modes.

[0058] Table 2: List of combined start modes of multiple types of engines

[0059] A+B combination A+C combination B+C combination A+B+C combination A+2B A+2C 2B+2C A+2B+2C A+4B A+4C 2B+4C A+2B+4C A+6C 2B+6C A+2B+6C A+8C 2B+8C A+2B+8C 4B+2C A+4B+2C 4B+4C A+4B+4C 4B+6C A+4B+6C 4B+8C A+4B+8C

[0060] The technical problem to be solved by this application is how to provide a method and device for calculating the integrated startup time of attitude and orbit control, and to provide a standard parameter configuration interface format so that the calculation model of the telemetry and control software is universal. By adjusting the configuration parameters, it can be flexibly adapted to different spacecraft, thereby improving the stability, security, flexibility of use and multi-task versatility of the telemetry and control software system.

[0061] Therefore, this application provides a method for calculating the integrated start-up time of attitude and orbit control, such as... Figure 2 As shown, it includes:

[0062] S201: Obtain the number of engines started and the start identifier to determine the engine starting method.

[0063] S202: Configure weighting coefficients according to the startup method.

[0064] S203: Calculate the overall startup time based on the weighting coefficient and startup method.

[0065] In one specific embodiment, suppose the spacecraft is equipped with N types of engines, and the model designations of each engine are α1, α2, ..., α3. i ..., α N The number of engines installed for each model are x1, x2, ..., x i ... x N ,i=1,2,…,N. Wherein, the engine model identifier α i Using uppercase English letters, i.e., α i ∈{A、…、Z}, which facilitates identification by operators and monitoring and control software.

[0066] Given that the number of engines of the same model assembled is odd, only one control method is adopted, namely, starting all engines of that model; given that the number of engines of the same model assembled is even, control is adopted by starting an even number of engines in symmetrical positions. Therefore, for the i-th type of engine, its assembled quantity is x. i When x i When the number is odd, there is only one way: activate all x. i This type of engine; when x i When the number is even, the number of times this engine model can be started is a multiple of 2.

[0067] Let y be the number of ways to start the i-th model engine individually. i The species, obviously:

[0068]

[0069] In the single starting mode, the engine starting identifier is represented in the format of [number][letter] (hereinafter referred to as single starting identifier), wherein the number represents the starting number of the engine, and the letter represents the model identifier of the engine:

[0070]

[0071] wherein j = 1, 2, …, y i , α i ∈ {A, …, Z}.

[0072] For example:

[0073] Suppose the model identifier of the i1th engine is F, and 3 engines of this type are installed, i.e. Then, the engine of this type has only one starting mode, and the starting identifier is “3F”.

[0074] Suppose the model identifier of the i2th engine is B, and 4 engines of this type are installed, i.e. Then, the engine of this type has a total of 2 starting modes, and the starting identifiers are “2B” and “4B” respectively.

[0075] In the combined starting mode, the engine starting identifier is represented in the format of “+” connecting the single starting identifiers (hereinafter referred to as combined starting identifier).

[0076] For example:

[0077] “2B+4C” represents starting 2 B-type engines and 4 C-type engines;

[0078] “A+4B+8C” represents starting all A-type engines, 4 B-type engines, and 8 C-type engines.

[0079] Hereinafter, the single starting identifier and the combined starting identifier are collectively referred to as the starting identifier.

[0080] In an embodiment, when the starting mode is the single starting mode, the weighting coefficients are configured according to the starting mode, as shown in Figure 3 including:

[0081] S301: If the starting number of the engine is an odd number or 2, set the weighting coefficient to

[0082] S302: If the starting number of the engine is an even number greater than 2, different weighting coefficients are configured for each of them.

[0083] In a specific embodiment, each single starting mode has a corresponding weighting coefficient, and the weighting coefficient corresponding to the jth usage mode of the i th model engine is j = 1, 2, …, yi .

[0084] A standard format of the weighting coefficient configuration table is shown in Table 3.

[0085] Table 3 Weighting coefficient configuration table of the ith type engine

[0086]

[0087] In an embodiment, when the starting mode is the combined starting, the weighting coefficient is configured according to the starting mode, including:

[0088] The weighting coefficient is looked up according to the starting identification of all the engines.

[0089] In a specific embodiment, obviously, when the engines of two different types are combined started, the number of the combined starting modes is the product of the number of the individual starting modes of the two types of engines, i.e. the individual starting modes of the ith type engine and the ith type engine are and the number of the combined starting modes of the two is .

[0090] For a spacecraft equipped with N types of engines, when t types of engines (2≤t≤N) are combined started, the number of the combined starting modes is the product of the number of the individual starting modes of the t types of engines:

[0091] In engineering applications, it is not necessary to list the corresponding weighting coefficients of each combined starting mode one by one. In the combined starting mode, the individual starting identification of each type of engine can be automatically interpreted by the measurement and control software, and after the corresponding weighting coefficient is automatically looked up, the weighting coefficient is substituted into the formula for calculation according to the specific comprehensive starting time calculation method.

[0092] In an embodiment, when the starting mode is the individual starting, the comprehensive starting time is calculated according to the weighting coefficient and the starting mode, including:

[0093] The comprehensive starting time is directly calculated by multiplying the weighting coefficient by the theoretical starting time.

[0094] In a specific embodiment, in the individual starting mode, the comprehensive starting time is directly calculated by multiplying the weighting coefficient by the theoretical starting time.

[0095] In an embodiment, when the starting mode is the combined starting, the comprehensive starting time is calculated according to the weighting coefficient and the starting mode, as shown in Figure 4 , including:

[0096] S401: Determine whether to calculate the comprehensive starting time by the maximum value method.

[0097] S402: If yes, take the maximum value of the comprehensive starting time of each type of engine as the comprehensive starting time.

[0098] S403: If no, calculate the comprehensive starting time of each type of engine according to the weighting coefficient, and add the comprehensive starting time of each type of engine to obtain the comprehensive starting time.

[0099] In a specific embodiment, under the combined starting mode, due to different control strategies and state settings, it is possible to take the comprehensive starting time of each type of engine, and it is also possible to take the maximum value of the comprehensive starting time of each type of engine, that is, there are two calculation methods:

[0100] Summation method: add the comprehensive starting time of each type of engine;

[0101] Maximum value method: take the maximum value of the comprehensive starting time of each type of engine.

[0102] Therefore, it is necessary to clearly set the calculation method corresponding to each starting identifier.

[0103] In fact, the calculation method of the comprehensive starting time under the single starting mode can be classified as the "summation method" under the combined starting mode.

[0104] Table 4: Comprehensive starting time calculation method setting table

[0105] Start identification Calculation method A plus 4B+8C plus A+2B+6C max

[0106] As shown in Table 4, a standard format of the comprehensive starting time calculation method setting table is given, and the calculation method adopted by each starting identifier is listed in the table, wherein the "calculation method" column is filled with "plus" indicating the summation method and "max" indicating the maximum value method. According to this method, the calculation method corresponding to each starting mode can be flexibly set, and it can be adjusted at any time according to the actual situation. However, this method still has shortcomings and still needs to be set and filled in for each starting identifier.

[0107] In fact, based on the summary of engineering practice experience and control strategy design mechanism, the summation method is adopted in most cases, and the maximum value method is adopted in a few cases. Therefore, the filling of Table 4 can be simplified, and only the starting identifier that adopts the maximum value method needs to be filled in, and the summation method is adopted by default for other starting identifiers, which greatly reduces the parameter setting workload and error probability.

[0108] Therefore, Table 4 can be further simplified to a maximum value method calculation comprehensive starting time setting table, as shown in Table 5:

[0109] Table 5: Maximum value method calculation comprehensive starting time setting table

[0110] Start identification Calculation method A+2B+6C max

[0111] Taking the settings in Table 5 as an example, the theoretical starting time of A, 2B and 6C is Δ1, Δ2 and Δ3 respectively, and the corresponding weighting coefficients are q1, q2 and q3 respectively through the weighting coefficient configuration table, so the comprehensive starting time corresponding to the starting identifier "A+2B+6C" listed in Table 5 should be max(Δ1×q1, Δ2×q2, Δ3×q3).

[0112] The starting identifiers not listed in Table 5 are calculated by the summation method, for example:

[0113] The comprehensive starting time corresponding to the starting identifier "A" should be Δ1×q1.

[0114] The comprehensive starting time corresponding to the starting identifier "A+2B" should be Δ1×q1+Δ2×q2.

[0115] The comprehensive starting time corresponding to the starting identifier "2B+6C" should be Δ2×q2+Δ3×q3.

[0116] The method and device for calculating the comprehensive starting time of attitude and orbit control realized by the application are shown in Figure 5 First, the engine starting identifier is obtained from the control strategy file of the spacecraft; second, the engine starting identifier is identified to identify each individual starting identifier therein; third, the weighting coefficient corresponding to each individual starting identifier is determined; then, the comprehensive starting time calculation method is determined; finally, the comprehensive starting time is calculated. The calculation method of the control strategy file of the spacecraft has a mature design, and the specific details are not involved herein.

[0117] The steps of the method are described as follows:

[0118] Step one, as shown in identifier 1 in Figure 5 , the engine starting identifier is directly obtained from the control strategy file of the spacecraft.

[0119] Step two, as shown in identifier 2 in Figure 5 , the engine starting identifier is identified to identify each individual starting identifier therein, that is, whether there is a "+" sign in the starting identifier obtained in the previous step is determined:

[0120] · If there is no "+" sign, it is a single starting mode, and the single starting identifier is directly stored;

[0121] · If there is a "+" sign, it is a combined starting mode, and the starting identifiers on both sides of the "+" sign are extracted and stored one by one until all the individual starting identifiers are extracted.

[0122] Step three, as shown in identifier 3 in Figure 5As shown in the middle mark 3, the weighted coefficient configuration table is traversed, and the weighted coefficient corresponding to each single start-up mark identified in the previous step is determined.

[0123] Step four, as shown in Figure 5 As shown in the middle mark 4, the maximum value method is used to calculate the comprehensive start-up time length setting table, and it is judged whether the engine start-up mark obtained in step one appears in the table:

[0124] Yes, the maximum value method is used, and step five is entered;

[0125] No, the summation method is used, and step six is entered;

[0126] Step five, as shown in Figure 5 As shown in the middle mark 5, the maximum value of the comprehensive start-up time length of each type of engine is taken.

[0127] Step six, as shown in Figure 5 As shown in the middle mark 6, the comprehensive start-up time lengths of each type of engine are added.

[0128] Based on the same inventive concept, the embodiment of the present application also provides a pose and orbit control comprehensive start-up time length calculation device, which can be used to implement the method described in the above embodiment, as described in the following embodiment. Since the principle of solving the problem of the pose and orbit control comprehensive start-up time length calculation device is similar to that of the pose and orbit control comprehensive start-up time length calculation method, the implementation of the pose and orbit control comprehensive start-up time length calculation device can be referred to the implementation of the pose and orbit control comprehensive start-up time length calculation method, and the repeated parts will not be described again. The term "unit" or "module" used below can be a combination of software and / or hardware that implements a predetermined function. Although the system described in the following embodiment is preferably implemented in software, hardware, or a combination of software and hardware is also possible and is conceived.

[0129] According to another aspect of the present application, a pose and orbit control comprehensive start-up time length calculation device is also provided, as shown in Figure 6 , comprising:

[0130] The acquisition unit 601 is configured to acquire the start-up number and start-up mark of the engine to determine the start-up mode of the engine.

[0131] The weighted coefficient configuration unit 602 is configured to configure the weighted coefficient according to the start-up mode.

[0132] The comprehensive start-up time length calculation unit 603 is configured to calculate the comprehensive start-up time length according to the weighted coefficient and the start-up mode.

[0133] In an embodiment, when the start-up mode is a single start-up mode, as shown in Figure 7 , the weighted coefficient configuration unit 602 comprises:

[0134] The first configuration module 701 is configured to set the weighting coefficient as

[0135] The second configuration module 702 is configured to set different weighting coefficients for the engines if the number of the engines is an even number greater than two.

[0136] In an embodiment, when the starting mode is the combined starting, the weighting coefficient configuration unit comprises:

[0137] The third configuration module is configured to search the weighting coefficient set in advance according to the starting identification of all the engines.

[0138] In an embodiment, when the starting mode is the single starting, the integrated starting duration calculation unit comprises:

[0139] The first calculation module is configured to directly calculate the integrated starting duration according to the theoretical starting duration multiplied by the weighting coefficient.

[0140] In an embodiment, when the starting mode is the combined starting, as shown in Figure 8 the integrated starting duration calculation unit 603 comprises:

[0141] The judging module 801 is configured to judge whether to calculate the integrated starting duration by using the maximum value method;

[0142] The maximum value calculation module 802 is configured to, if yes, take the maximum value of the integrated starting duration of each type of engine as the integrated starting duration;

[0143] The second calculation module 803 is configured to, if no, calculate the integrated starting duration of each type of engine according to the weighting coefficient, and add the integrated starting duration of each type of engine to obtain the integrated starting duration.

[0144] The integrated starting duration calculation method and device provided by the application give a simple and clear description rule for the starting identification, have good readability and recognition, are easy to be read and processed by personnel, and are simple and flexible in parameter adjustment. In the case of simple design, the method and device are suitable for various spacecraft platforms, the measurement and control software and the spacecraft platform are no longer tightly bound, have good universality, are convenient to apply, reduce unnecessary software changes, and reduce the influence on the safety of the software system.

[0145] The embodiment of the application further provides a specific implementation of an electronic device capable of implementing all the steps in the method in the above-mentioned embodiments, which is described below with reference to Figure 9 The electronic device specifically comprises the following contents:

[0146] The processor 901, the memory 902, the communications interface 903, the bus 904 and the nonvolatile memory 905;

[0147] The processor 901, the memory 902, the communications interface 903 and the nonvolatile memory 905 communicate with each other through the bus 904;

[0148] The processor 901 is configured to invoke a computer program stored in the memory 902 and the nonvolatile memory 905, and the processor executes the computer program to implement all steps of the method in the above embodiments, for example, the processor executes the computer program to implement the following steps:

[0149] S201: Obtain the start number and the start identifier of the engine to determine the start mode of the engine.

[0150] S202: Configure a weighting coefficient according to the start mode.

[0151] S203: Calculate a comprehensive start-up duration according to the weighting coefficient and the start mode.

[0152] The embodiments of the present application also provide a computer readable storage medium capable of implementing all steps of the method in the above embodiments, and the computer readable storage medium stores a computer program, and the computer program is executed by a processor to implement all steps of the method in the above embodiments, for example, the processor executes the computer program to implement the following steps:

[0153] S201: Obtain the start number and the start identifier of the engine to determine the start mode of the engine.

[0154] S202: Configure a weighting coefficient according to the start mode.

[0155] S203: Calculate a comprehensive start-up duration according to the weighting coefficient and the start mode.

[0156] The various embodiments in this specification are described in a progressive manner. Similar or identical parts between embodiments can be referred to mutually. Each embodiment focuses on its differences from other embodiments. In particular, for hardware + program embodiments, since they are basically similar to method embodiments, the description is relatively simple; relevant parts can be referred to the descriptions in the method embodiments. Although the embodiments in this specification provide the method operation steps as shown in the embodiments or flowcharts, more or fewer operation steps may be included based on conventional or non-inventive means. The order of steps listed in the embodiments is merely one possible execution order among many steps and does not represent the only execution order. In actual device or terminal product execution, the methods can be executed in the order shown in the embodiments or drawings or in parallel (e.g., in a parallel processor or multi-threaded processing environment, or even a distributed data processing environment). The terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, product, or apparatus that includes a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, product, or apparatus. Without further limitations, the presence of other identical or equivalent elements in the process, method, product, or apparatus that includes said elements is not excluded. For ease of description, the above devices are described in terms of function, divided into various modules. Of course, in implementing the embodiments of this specification, the functions of each module can be implemented in one or more software and / or hardware, or the module implementing the same function can be implemented by a combination of multiple sub-modules or sub-units, etc. The device embodiments described above are merely illustrative. For example, the division of units is only a logical functional division; in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some interfaces; the indirect coupling or communication connection between devices or units may be electrical, mechanical, or other forms. This invention is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It should be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing device to produce a machine, such that the instructions, which are executable by the processor of the computer or other programmable data processing device, produce instructions for implementing the process. Figure 1 One or more processes and / or boxes Figure 1appreciated that embodiments of the present specification can be provided as a method, a system, or a computer program product. Therefore, embodiments of the present specification can take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, embodiments of the present specification can take the form of a computer program product on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROMs, optical storage devices, etc.) embodying computer-readable program code thereon for use by a computer. The foregoing description, for purpose of copyrights, is included for informational purposes only. Any slight change, modification, or improvement made during the implementation of the present specification can be included in the scope of the claims of the present specification. In the description of the present specification, the description of the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the embodiments of the present specification. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. In addition, the skilled person in the art can combine and combine the different embodiments or examples described in the present specification and the features of the different embodiments or examples without contradiction. The above is only an embodiment of the embodiments of the present specification and is not intended to limit the embodiments of the present specification. The embodiments of the present specification can have various changes and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the embodiments of the present specification shall be included in the scope of the claims of the embodiments of the present specification.

Claims

1. A method for calculating an integrated on-time of attitude and orbit control, characterized in that, The method comprises the following steps: acquiring the number of starts and start identifiers of the engines to determine the start mode of the engines; the start identifier comprises a single start identifier and a combined start identifier, the single start identifier is in the format of numbers and letters, the numbers represent the number of starts of the engine, and the letters represent the model of the engine, and the start mode formed by the single start identifier is a single start mode; the combined start identifier is in the format of connecting single start identifiers with "+" signs, and the start mode formed by the combined start identifier is a combined start mode; when the number of starts of the engine is odd, there is only one single start identifier, which is represented as the number of starts of the engine and letters; when the number of starts of the engine is even, the number of single start identifiers is equal to the number of starts of the engine divided by 2, and the corresponding single start identifier is represented as an even number less than or equal to the number of starts of the engine and letters; configuring a weighting coefficient according to the start mode; calculating the comprehensive start-up time according to the weighting coefficient and the start mode; when the start mode is a single start mode, configuring the weighting coefficient according to the start mode comprises: if the number of starts of the engine is odd or two, setting the weighting coefficient as ; i represents the i-th model of the engine; if the number of starts of the engine is an even number greater than two, configuring different weighting coefficients for the engines respectively; when the start mode is a combined start, configuring the weighting coefficient according to the start mode comprises: looking up the weighting coefficients set in advance according to the start identifiers of all the engines; when the start mode is a single start, calculating the comprehensive start-up time according to the weighting coefficient and the start mode comprises: directly calculating the comprehensive start-up time by multiplying the acquired theoretical start-up time by the weighting coefficient; when the start mode is a combined start, calculating the comprehensive start-up time according to the weighting coefficient and the start mode comprises: judging whether to calculate the comprehensive start-up time by using the maximum value method; if yes, taking the maximum value of the comprehensive start-up times of the engines of different models as the comprehensive start-up time; if no, calculating the comprehensive start-up times of the engines of different models according to the weighting coefficients, and adding the comprehensive start-up times of the engines of different models to obtain the comprehensive start-up time.

2. An attitude and orbit control integrated start-up time length calculation device, characterized in that, The method for calculating the comprehensive start-up time of the attitude and orbit control system according to claim 1 comprises: an acquisition unit configured to acquire the number of starts and start identifiers of the engines to determine the start mode of the engines; a weighting coefficient configuration unit configured to configure a weighting coefficient according to the start mode; a comprehensive start-up time calculation unit configured to calculate the comprehensive start-up time according to the weighting coefficient and the start mode.

3. The attitude and orbit control integrated start-up time length calculation apparatus according to claim 2, characterized by, when the start mode is a single start mode, the weighting coefficient configuration unit comprises: a first configuration module configured to set the weighting coefficient as if the number of starts of the engine is odd or two; a second configuration module configured to configure different weighting coefficients for the engines respectively if the number of starts of the engine is an even number greater than two.

4. The attitude and orbit control integrated start-up time length calculation apparatus according to claim 2, characterized by, when the start mode is a combined start, the weighting coefficient configuration unit comprises: a third configuration module configured to look up the weighting coefficients set in advance according to the start identifiers of all the engines.

5. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, The processor implements the steps of the attitude and orbit control integrated start-up time length calculation method of claim 1 when executing the program.

6. A computer-readable storage medium having stored thereon a computer program, characterized in that, The computer program implements the steps of the attitude and orbit control integrated start-up time length calculation method of claim 1 when executed by the processor.

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