Rocket stage ratio calculation method, device, terminal equipment and medium

Abstract

The present invention discloses a method, apparatus, terminal device, and medium for calculating a rocket interstage ratio. The method comprises: calculating the total rocket mass of the rocket based on different preset rocket payloads and rocket measurement parameters; calculating first and second characteristic velocity curves for different second-stage rocket masses based on the rocket measurement parameters and target payload; calculating the target second-stage mass of the rocket based on the first and second characteristic velocity curves for different second-stage rocket masses; and calculating the rocket interstage ratio of the rocket based on the total rocket mass and the target second-stage mass. The present invention can solve technical problems in the prior art such as multiple calculations and high complexity involved in optimizing the rocket interstage ratio.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a method, device, terminal equipment and medium for calculating a rocket stage ratio. Background Art

[0002] Optimizing the interstage ratio of two-stage launch vehicles, without considering the recovery of a substage (i.e., the first stage), is a relatively mature problem. The solution is to adjust the interstage ratio parameters of the rocket to achieve the optimal launch capacity for a specific target orbit while meeting other pre-set constraints, based on a complete trajectory program.

[0003] However, in practice, while this approach can accurately find the optimal solution, the trajectory program requires multiple orbital insertion iterations for each payload capacity calculation, and the constant adjustment of configuration parameters also requires multiple orbital insertion calculations. Furthermore, if vertical recovery of the first stage is considered, the return trajectory of the first stage must also be factored in, further increasing the complexity of optimizing the inter-stage ratio. Summary of the Invention

[0004] The embodiment of the present application solves the technical problems of multiple calculations and high complexity involved in the optimization calculation of the rocket stage ratio in the prior art by providing a method for calculating the rocket stage ratio.

[0005] On the one hand, the present application provides a method for calculating a rocket stage ratio through an embodiment of the present application, characterized in that the method is applied to a rocket with a two-stage configuration, and includes:

[0006] Calculate the total mass of the rocket based on different preset rocket payloads and rocket measurement parameters;

[0007] Calculating a first characteristic velocity curve and a second characteristic velocity curve under different second-stage rocket masses based on the rocket measurement parameters and the target load, wherein the target load is determined based on the different rocket loads;

[0008] Calculating a target second-stage mass of the rocket based on the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses;

[0009] The rocket stage ratio of the rocket is calculated based on the total rocket mass and the target second-stage mass.

[0010] Optionally, the calculating the total mass of the rocket according to different preset rocket payloads and rocket measurement parameters includes:

[0011] Obtain rocket measurement parameters and set different rocket payloads;

[0012] Inputting the rocket measurement parameters and different rocket loads into Qi's formula to calculate the third characteristic velocity curve under different rocket loads;

[0013] The total mass of the rocket is calculated based on the third characteristic velocity curve under different rocket loads, the target load and the pre-assigned rocket characteristic velocity.

[0014] Optionally, calculating the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses according to the rocket measurement parameters and the target payload includes:

[0015] Get the target payload and set different second-stage rocket masses;

[0016] Inputting the target load, different masses of the second-stage rocket, and the rocket measurement parameters into the Qi formula, and calculating the first characteristic velocity curve under different masses of the second-stage rocket;

[0017] The target load, different masses of the second-stage rocket and the rocket measurement parameters are input into a pre-stored ballistic program to calculate and obtain the second characteristic velocity curve under different masses of the second-stage rocket.

[0018] Optionally, calculating the target second-stage mass of the rocket according to the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses includes:

[0019] The target second-stage mass of the rocket is calculated based on the respective changing trends of the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses.

[0020] Optionally, calculating the rocket stage ratio of the rocket based on the total rocket mass and the target second-stage mass includes:

[0021] Calculating the target first stage mass of the rocket based on the total rocket mass and the target second stage mass;

[0022] The rocket stage ratio of the rocket is calculated based on the target first-stage mass and the target second-stage mass.

[0023] Optionally, the method further comprises the following steps:

[0024] S1. Calculating the amount of unused fuel in the ascent phase of the first-stage rocket based on the separation velocity of the first-stage rocket and the rocket inter-stage ratio;

[0025] S2. Calculating the amount of fuel consumed to reach the first-stage return trajectory based on the separation velocity of the first-stage rocket;

[0026] S3. When the amount of unused fuel exceeds the amount of consumed fuel, the excess fuel is placed in the second-stage rocket, and the rocket stage ratio is reduced, and steps S1-S2 are repeated until the amount of unused fuel equals the amount of consumed fuel.

[0027] S4. Determine the rocket stage ratio used at the end as the optimal stage ratio of the rocket.

[0028] Optionally, step S1 includes:

[0029] determining an upper limit value of fuel consumption in an ascent phase of the first-stage rocket according to a separation speed of the first-stage rocket;

[0030] Based on the fuel consumption upper limit and the rocket stage ratio, the amount of unused fuel in the ascent section of the first-stage rocket is calculated.

[0031] On the other hand, the present application provides a device for calculating a rocket stage ratio through an embodiment of the present application, the device comprising a first calculation module, a second calculation module, a third calculation module, and a fourth calculation module, wherein:

[0032] The first calculation module is used to calculate the total mass of the rocket according to different preset rocket payloads and rocket measurement parameters;

[0033] The second calculation module is used to calculate the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses according to the rocket measurement parameters and the target load, wherein the target load is determined according to the different rocket loads;

[0034] The third calculation module is used to calculate the target second-stage mass of the rocket based on the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses;

[0035] The fourth calculation module is used to calculate the rocket stage ratio of the rocket based on the total rocket mass and the target second-stage mass.

[0036] For the contents not introduced or described in the embodiments of the present application, please refer to the relevant introduction in the aforementioned method embodiments, which will not be repeated here.

[0037] On the other hand, the present application provides a terminal device through an embodiment of the present application, and the terminal device includes: a processor, a memory, a communication interface and a bus; the processor, the memory and the communication interface are connected through the bus and complete communication with each other; the memory stores executable program code; the processor runs the program corresponding to the executable program code by reading the executable program code stored in the memory, so as to execute the method for calculating the rocket stage ratio as described above.

[0038] On the other hand, the present application provides a computer-readable storage medium through an embodiment of the present application, wherein the computer-readable storage medium stores a program, and when the program runs on a terminal device, the method for calculating the rocket stage ratio as described above is executed.

[0039] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages: the present application calculates the total rocket mass of the rocket based on different preset rocket payloads and rocket measurement parameters; calculates the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses based on the rocket measurement parameters and the target payload, wherein the target payload is determined based on the different rocket payloads; calculates the target second-stage mass of the rocket based on the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses; and calculates the rocket stage ratio of the rocket based on the total rocket mass and the target second-stage mass. In the above solution, the present application calculates the target second-stage mass of the rocket based on the two characteristic velocity curves under different second-stage rocket masses, and finally calculates the current rocket stage ratio based on the total rocket mass and the target second-stage mass. This can reduce the number of calculations and the amount of calculations for the rocket stage ratio calculation, which is conducive to improving the convenience and accuracy of the rocket stage ratio calculation. At the same time, it also solves the technical problems of multiple calculations and high complexity involved in the optimization calculation of the rocket stage ratio in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the description of the embodiments. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0041] Figure 1 This is a flow chart of a method for calculating the rocket stage ratio provided in an embodiment of the present application.

[0042] Figure 2 This is a schematic diagram of a characteristic velocity curve under different rocket loads provided in an embodiment of the present application.

[0043] Figure 3 This is a schematic diagram of a characteristic velocity curve under different second-stage rocket masses provided in an embodiment of the present application.

[0044] Figure 4 This is a structural diagram of a rocket stage ratio calculation device provided in an embodiment of the present application.

[0045] Figure 5 This is a structural diagram of a terminal device provided in an embodiment of the present application. DETAILED DESCRIPTION

[0046] The embodiment of the present application solves the technical problems of multiple calculations and high complexity involved in the optimization calculation of the rocket stage ratio in the prior art by providing a method for calculating the rocket stage ratio.

[0047] The technical solution of the embodiment of the present application is to solve the above-mentioned technical problems, and the overall idea is as follows: according to different preset rocket payloads and rocket measurement parameters, the total rocket mass of the rocket is calculated; according to the rocket measurement parameters and the target load, the first characteristic velocity curve and the second characteristic velocity curve under different two-stage rocket masses are calculated, and the target load is determined according to the different rocket payloads; according to the first characteristic velocity curve and the second characteristic velocity curve under the different two-stage rocket masses, the target two-stage mass of the rocket is calculated; according to the total rocket mass and the target two-stage mass, the rocket stage ratio of the rocket is calculated.

[0048] In order to better understand the above technical solution, the above technical solution will be described in detail below with reference to the accompanying drawings and specific implementation methods.

[0049] First, the term "and / or" as used herein simply describes a relationship between associated objects, indicating that three possible relationships exist. For example, "A and / or B" can represent: A alone, A and B together, or B alone. Furthermore, the character " / " in this document generally indicates an "or" relationship between the associated objects.

[0050] This application starts from the basic physical principles, simplifies the rocket stage ratio optimization problem, and separates the problems of the ascent stage and the return stage of the two-stage configuration rocket, providing a fast stage ratio optimization method considering the vertical recovery of the single-stage rocket.

[0051] Rockets use the high-speed backjet generated by the combustion of chemical fuel to form an accelerating thrust. If other external forces such as gravity and resistance are not considered, the total velocity increment generated by this thrust can be obtained using the classic "Qi's formula". For the convenience of description, this application refers to the total velocity increment obtained by Qi's formula as the "provided input velocity increment", which can also be called the characteristic velocity, and is denoted by the symbol V0. The process of a rocket actually launched from the ground to send a certain payload into the target orbit is to make the payload reach the specified on-orbit energy after overcoming factors such as gravity and resistance. The on-orbit energy here is actually specific mechanical energy, including potential energy and kinetic energy. Taking a 700km high circular orbit as an example, the on-orbit velocity of the satellite is about 7500m / s, and the velocity increment V0 provided by the rocket will be larger than 7500m / s, because part of the velocity increment needs to be used to increase potential energy, which is commonly known as "gravity loss". Under the conditions of the same orbital altitude, different target orbital inclinations, and different launch points, this part of the gravity loss will also be different, because this will bring in different contributions from the earth's rotation, which in turn affects the trajectory shape, because gravity loss is related to factors such as target altitude, orbital shape, and acceleration performance (thrust-to-weight ratio).

[0052] Taking a 700km high circular sun-synchronous orbit as an example, gravity loss is typically around 2000m / s (when the target orbit inclination and launch point are fixed, this factor also depends on the orbit insertion method and the rocket's thrust-to-weight ratio during the active phase, involving detailed design and optimization of the orbit insertion trajectory. Since this is not the focus of this application, this application only considers typical cases). In addition to gravity loss, the rocket will pass through the atmosphere during the ascent phase of flight. V0 must also include the component required to overcome atmospheric drag, namely "drag loss." This component is relatively small for launch vehicles, with typical values ​​generally ranging from 100m / s to 200m / s. Taking all of the above into consideration, to deliver a certain payload into the target orbit, the "required velocity increment V1" of the rocket must include the following three factors: the satellite's orbit insertion velocity, gravity loss, and drag loss; some literature also refers to this as the "characteristic velocity V1" of the rocket's orbit insertion. Furthermore, the velocity increment V0 provided by the rocket must be greater than or equal to the characteristic orbit insertion velocity V1. For a 700km circular sun-synchronous orbit, V1 should be on the order of 10,000m / s.

[0053] This application significantly simplifies the optimization problem of two-stage rockets by incorporating complex factors such as gravity loss and drag loss into the characteristic velocity V1 and identifying typical characteristic velocities under typical target orbits. This allows for rapid preliminary optimization of two-stage rockets without the need for a ballistic program. This preliminary optimization can roughly determine the rocket size that meets the target orbit's carrying capacity requirements. Once the size is determined, the ballistic program can be used to further refine the carrying capacity. The essence of this optimization is to maximize (V0-V1), and the final optimization process takes into account the recovery of the first stage.

[0054] See Figure 1 , is a flow chart of a method for calculating the rocket stage ratio provided in an embodiment of the present application. Figure 1 The method shown is applied to a rocket having a two-stage configuration, and the method specifically includes the following steps:

[0055] S101. Calculate the total mass of the rocket according to different preset rocket payloads and rocket measurement parameters.

[0056] In one specific embodiment, the present application can obtain rocket measurement parameters and set different rocket payloads. The rocket measurement parameters and different rocket payloads are input into the Qi formula to calculate the third characteristic velocity curve under different rocket payloads. The total rocket mass of the rocket is then calculated based on the third characteristic velocity curve under different rocket payloads, the target payload, and the pre-assigned rocket characteristic velocity.

[0057] In a specific implementation, the present application can set rocket payloads of different masses based on rocket measurement parameters such as engine thrust, specific impulse, structural coefficient, engine layout, etc. provided by the overall power professional. Optionally, the range of the total rocket mass can also be set according to the rocket takeoff thrust-to-weight ratio constraint. Furthermore, the present application brings these parameters (such as rocket measurement parameters, different rocket payloads and the range of the total rocket mass, etc.) into the Qi formula, taking into account the recovery of a sub-stage (specifically the launch vehicle located in the first stage, hereinafter referred to as the first-stage rocket) can temporarily reserve fuel for recovery at a fixed percentage, which can be set to 8% for liquid hydrogen-methane engines. For each total rocket mass, the rocket inter-stage ratio is adjusted to maximize V0, and the third characteristic velocity curve V0m(M, M0) of the maximum V0 with the total rocket mass M under different rocket payloads M0 is obtained. Among them, the Qi formula can be shown as the following formula (1):

[0058]

[0059] Among them, V is the rocket velocity increment, U is the engine specific impulse, M is the initial rocket mass, and m is the rocket mass after the fuel is burned out.

[0060] For example, see Figure 2 Schematic diagrams showing several possible third characteristic speed curves. Figure 2 In the paper, the maximum velocity increment curves under three rocket loads are calculated: 2t (tons), 2.5t and 3t.

[0061] Furthermore, the present application can determine the total mass of the rocket, i.e., the rocket scale, based on the third characteristic velocity curve V0m(M, M0) under different rocket loads, and based on the selected target load and the pre-assigned rocket characteristic velocity (e.g., 10,000 m / s). Figure 2In the example shown, if the user's desired target payload is 2 tons, the total mass of the rocket can be calculated to be around 250 tons. Furthermore, the present application can accurately calculate the number of rocket engines based on the calculated total mass and the thrust of a single engine.

[0062] S102. Calculate a first characteristic velocity curve and a second characteristic velocity curve under different second-stage rocket masses according to the rocket measurement parameters and the target load, wherein the target load is determined according to the different rocket loads.

[0063] In one specific embodiment, the present application obtains a target payload and sets different second-stage rocket masses. The present application then inputs the target payload, different second-stage rocket masses, and the rocket measurement parameters into a Qi formula to calculate a first characteristic velocity curve for each second-stage rocket mass. The target payload, different second-stage rocket masses, and the rocket measurement parameters are then input into a pre-stored ballistics program to calculate a second characteristic velocity curve for each second-stage rocket mass.

[0064] In specific implementation, this application utilizes a ballistic program to perform detailed optimization of the rocket's inter-stage ratio. Since the characteristic velocity V1 includes gravity losses, which are related to the thrust-to-weight ratio of the first and second stages of the rocket, for ease of description, this application allows the second-stage rocket mass to take different values, fix the second-stage thrust-to-weight ratio, and then introduce the target payload and rocket measurement parameters into a preset ballistic program to calculate the first characteristic velocity curve V1(M, M2) for a fixed second-stage rocket mass M2 and different total rocket masses M. Simultaneously, this application can also use the Qi formula to calculate the second characteristic velocity curve (i.e., velocity increment curve) V0(M, M2) provided for each second-stage rocket mass M2, and furthermore, these curves can be plotted on the same VM plane.

[0065] For example, see Figure 3 A schematic diagram showing the first and second characteristic velocity curves for different second stage rocket masses. Figure 3 In the figure, the first characteristic velocity curve V0 and the second characteristic velocity curve V1 are shown when the mass of the second-stage rocket is 32t, 37t and 42t respectively.

[0066] S103. Calculate the target second-stage mass of the rocket according to the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses.

[0067] This application calculates the target secondary mass of the rocket based on the changing trends of the first characteristic velocity curve and the second characteristic velocity curve under different secondary rocket masses. Specifically, this application can observe the changing trends of the V0-V1 curve (V0 minus V1) based on the V1 curve and V0 curve under different secondary rocket masses to find the target secondary mass corresponding to the minimum V1 curve. The target secondary mass refers to the mass of the second stage of the rocket.

[0068] For example, citing Figure 3 The example, from Figure 3 It can be seen that to optimize payload capacity, the second-stage mass cannot be too large; 32 tons is ideal, and the maximum value of V0-V1 is generally around 250 tons. In this example, the optimal stage ratio between the first and second stages is between 6 and 7. Further reducing the target second-stage mass and increasing the second-stage thrust-to-weight ratio could further increase payload capacity. However, the first-stage mass would be too large, resulting in a higher separation velocity, making recovery difficult. A low second-stage mass would also shorten the second-stage column, complicating the design of the second-stage tank. Therefore, the selection of the second-stage mass must take these constraints into account.

[0069] S104. Calculate the rocket stage ratio of the rocket based on the total rocket mass and the target second-stage mass.

[0070] In a specific embodiment, the present application can calculate the target first stage mass of the rocket based on the total rocket mass and the target second stage mass. Specifically, the target first stage mass is the total rocket mass minus the target second stage mass. The target first stage mass refers to the mass of the first stage of the rocket. Furthermore, the present application will calculate the rocket inter-stage ratio based on the target first stage mass and the target second stage mass. Specifically, the rocket inter-stage ratio is equal to the ratio of the target first stage mass to the target second stage mass.

[0071] The above results are based on a purely fixed percentage of the first-stage's fuel used for return. However, the first-stage's return phase is subject to various constraints, particularly the recovery distance and the maximum power of the aerodynamic deceleration phase, which limits the speed of the first-stage separation point. In this embodiment, the first-stage forward recovery point is limited to within 750 km of the launch point, requiring the first-stage separation speed to be no higher than 2500 m / s. Prior to step S104, the rocket's total mass was already determined, so the first-stage's fuel consumption during the ascent phase became a fixed value rather than a fixed percentage. Previously, a rough 8% reserve was considered for the first stage. Considering the recovery of the first stage, the two-stage configuration will need to be re-evaluated.

[0072] In an optional embodiment, the present application may further include the following implementation steps:

[0073] S1. Calculate the amount of unused fuel in the ascent segment of the first-stage rocket based on the separation speed of the first-stage rocket and the inter-stage ratio of the rocket.

[0074] In a specific embodiment, the present application can determine an upper limit value for fuel consumption during the ascent phase of the first-stage rocket based on the separation velocity of the first-stage rocket. Furthermore, the amount of unused fuel during the ascent phase of the first-stage rocket can be calculated based on the upper limit value for fuel consumption and the rocket stage ratio.

[0075] In a specific implementation, this application can determine the upper limit of the fuel consumption during the ascent phase of the first-stage rocket based on the separation speed limit of the first-stage rocket. Using this value as a starting point and based on the previously obtained rocket stage ratio, the unused fuel percentage (or unused fuel amount, etc.) of the first-stage ascent phase is recalculated. If the recalculated fuel percentage is greater than the previously considered 8%, it indicates that the mass of the first-stage rocket may be too large.

[0076] S2. Calculate the amount of fuel consumed to reach the first-stage return trajectory based on the separation speed of the first-stage rocket.

[0077] S3. When the amount of unused fuel exceeds the amount of consumed fuel, the excess fuel is placed in the second-stage rocket, and the rocket stage ratio is reduced, and steps S1-S2 are repeated until the amount of unused fuel is equal to the amount of consumed fuel.

[0078] S4. Determine the rocket stage ratio used at the end as the optimal stage ratio of the rocket.

[0079] This application uses the separation velocity of the first-stage rocket as an initial value, inputting it into a preset return trajectory program to calculate the first-stage return trajectory and the amount of fuel consumed to reach the first-stage return trajectory. If, after deducting the safety margin, a large amount of fuel remains, this indicates that the first-stage is indeed too large. Transferring this excess fuel to the second-stage rocket, increasing its mass and reducing the inter-stage ratio, will further enhance the carrying capacity. By reducing the inter-stage ratio, while maintaining the same fuel for the first-stage ascent, S1-S2 is re-executed to calculate the ascent trajectory and the first-stage return trajectory until there is just enough fuel for the first-stage return. The inter-stage ratio used at this point is the optimal / optimal inter-stage ratio for first-stage recovery.

[0080] It should be noted that in actual operations, in addition to considering that the reserved fuel is just enough to recover the first stage, the overload of the landing stage should also be considered not to be too large, so part of the fuel may need to be used as counterweight, especially when the efficiency of the first stage structure is very high.

[0081] By implementing the embodiments of the present application, the present application calculates the total rocket mass of the rocket based on different preset rocket payloads and rocket measurement parameters; calculates the first characteristic velocity curve and the second characteristic velocity curve under different two-stage rocket masses based on the rocket measurement parameters and the target payload, wherein the target payload is determined based on the different rocket payloads; calculates the target two-stage mass of the rocket based on the first characteristic velocity curve and the second characteristic velocity curve under the different two-stage rocket masses; and calculates the rocket stage ratio of the rocket based on the total rocket mass and the target two-stage mass. In the above scheme, the present application calculates the target two-stage mass of the rocket based on the two characteristic velocity curves under different two-stage rocket masses, and finally calculates the current rocket stage ratio based on the total rocket mass and the target two-stage mass. This can reduce the number of calculations and the amount of calculations for the rocket stage ratio calculation, which is conducive to improving the convenience and accuracy of the rocket stage ratio calculation. At the same time, it also solves the technical problems of multiple calculations and high complexity involved in the optimization calculation of the rocket stage ratio in the prior art.

[0082] Based on the same inventive concept, another embodiment of the present application provides a device and terminal equipment corresponding to the method for calculating the rocket stage ratio described in the embodiment of the present application.

[0083] See Figure 4 , is a schematic diagram of the structure of a rocket stage ratio calculation device provided in an embodiment of the present application. Figure 4 The device shown includes: a first calculation module 401, a second calculation module 402, a third calculation module 403 and a fourth calculation module 404, wherein:

[0084] The first calculation module 401 is used to calculate the total mass of the rocket according to different preset rocket payloads and rocket measurement parameters;

[0085] The second calculation module 402 is configured to calculate a first characteristic velocity curve and a second characteristic velocity curve under different second-stage rocket masses based on the rocket measurement parameters and the target load, wherein the target load is determined based on the different rocket loads;

[0086] The third calculation module 403 is used to calculate the target second-stage mass of the rocket based on the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses;

[0087] The fourth calculation module 404 is used to calculate the rocket stage ratio of the rocket based on the total rocket mass and the target second-stage mass.

[0088] Optionally, the first calculation module 401 is specifically configured to:

[0089] Obtain rocket measurement parameters and set different rocket payloads;

[0090] Inputting the rocket measurement parameters and different rocket loads into Qi's formula to calculate the third characteristic velocity curve under different rocket loads;

[0091] The total mass of the rocket is calculated based on the third characteristic velocity curve under different rocket loads, the target load and the pre-assigned rocket characteristic velocity.

[0092] Optionally, the second calculation module 402 is specifically configured to:

[0093] Get the target payload and set different second-stage rocket masses;

[0094] Inputting the target load, different masses of the second-stage rocket, and the rocket measurement parameters into the Qi formula, and calculating the first characteristic velocity curve under different masses of the second-stage rocket;

[0095] The target load, different masses of the second-stage rocket and the rocket measurement parameters are input into a pre-stored ballistic program to calculate and obtain the second characteristic velocity curve under different masses of the second-stage rocket.

[0096] Optionally, the third calculation module 403 is specifically configured to:

[0097] The target second-stage mass of the rocket is calculated based on the changing trends of the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses.

[0098] Optionally, the fourth calculation module 404 is specifically configured to:

[0099] Calculating the target first stage mass of the rocket based on the total rocket mass and the target second stage mass;

[0100] The rocket stage ratio of the rocket is calculated based on the target first-stage mass and the target second-stage mass.

[0101] Optionally, the apparatus further includes a processing module 405, wherein the processing module 405 is configured to perform the following steps:

[0102] S1. Calculating the amount of unused fuel in the ascent phase of the first-stage rocket based on the separation velocity of the first-stage rocket and the rocket inter-stage ratio;

[0103] S2. Calculating the amount of fuel consumed to reach the first-stage return trajectory based on the separation velocity of the first-stage rocket;

[0104] S3. When the amount of unused fuel exceeds the amount of consumed fuel, the excess fuel is placed in the second-stage rocket, and the rocket stage ratio is reduced, and steps S1-S2 are repeated until the amount of unused fuel equals the amount of consumed fuel.

[0105] S4. Determine the rocket stage ratio used at the end as the optimal stage ratio of the rocket.

[0106] Optionally, the processing module 405 is specifically configured to:

[0107] determining an upper limit value of fuel consumption in an ascent phase of the first-stage rocket according to a separation speed of the first-stage rocket;

[0108] Based on the fuel consumption upper limit and the rocket stage ratio, the amount of unused fuel in the ascent section of the first-stage rocket is calculated.

[0109] Please refer to 5, which is a structural diagram of a terminal device provided in an embodiment of the present application. Figure 5 The terminal device 50 shown includes: at least one processor 501, a communication interface 502, a user interface 503 and a memory 504. The processor 501, the communication interface 502, the user interface 503 and the memory 504 can be connected via a bus or other means. In the embodiment of the present invention, the connection via the bus 505 is used as an example.

[0110] The processor 501 may be a general-purpose processor, such as a central processing unit (CPU).

[0111] The communication interface 502 may be a wired interface (e.g., an Ethernet interface) or a wireless interface (e.g., a cellular network interface or a wireless local area network interface) for communicating with other terminals or websites. In an embodiment of the present invention, the communication interface 502 is specifically used to obtain information such as rocket measurement parameters and target payload.

[0112] The user interface 503 may be a touch panel, including a touch screen and a touch screen, for detecting operation instructions on the touch panel, a physical button or a mouse, or a display screen for outputting and displaying images or data.

[0113] Memory 504 may include volatile memory, such as random access memory (RAM); non-volatile memory, such as read-only memory (ROM), flash memory, hard disk drive (HDD), or solid-state drive (SSD); or a combination of the aforementioned types of memory. Memory 504 is used to store a set of program codes, and processor 501 is used to call the program codes stored in memory 504 and perform the following operations:

[0114] Calculate the total mass of the rocket based on different preset rocket payloads and rocket measurement parameters;

[0115] Calculating a first characteristic velocity curve and a second characteristic velocity curve under different second-stage rocket masses based on the rocket measurement parameters and the target load, wherein the target load is determined based on the different rocket loads;

[0116] Calculating a target second-stage mass of the rocket based on the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses;

[0117] The rocket stage ratio of the rocket is calculated based on the total rocket mass and the target second-stage mass.

[0118] Optionally, the calculating the total mass of the rocket according to different preset rocket payloads and rocket measurement parameters includes:

[0119] Obtain rocket measurement parameters and set different rocket payloads;

[0120] Inputting the rocket measurement parameters and different rocket loads into Qi's formula to calculate the third characteristic velocity curve under different rocket loads;

[0121] The total mass of the rocket is calculated based on the third characteristic velocity curve under different rocket loads, the target load and the pre-assigned rocket characteristic velocity.

[0122] Optionally, calculating the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses according to the rocket measurement parameters and the target payload includes:

[0123] Get the target payload and set different second-stage rocket masses;

[0124] Inputting the target load, different masses of the second-stage rocket, and the rocket measurement parameters into the Qi formula, and calculating the first characteristic velocity curve under different masses of the second-stage rocket;

[0125] The target load, different masses of the second-stage rocket and the rocket measurement parameters are input into a pre-stored ballistic program to calculate and obtain the second characteristic velocity curve under different masses of the second-stage rocket.

[0126] Optionally, calculating the target second-stage mass of the rocket according to the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses includes:

[0127] The target second-stage mass of the rocket is calculated based on the changing trends of the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses.

[0128] Optionally, calculating the rocket stage ratio of the rocket based on the total rocket mass and the target second-stage mass includes:

[0129] Calculating the target first stage mass of the rocket based on the total rocket mass and the target second stage mass;

[0130] The rocket stage ratio of the rocket is calculated based on the target first-stage mass and the target second-stage mass.

[0131] Optionally, the processor 501 is further configured to perform the following steps:

[0132] S1. Calculating the amount of unused fuel in the ascent phase of the first-stage rocket based on the separation velocity of the first-stage rocket and the rocket inter-stage ratio;

[0133] S2. Calculating the amount of fuel consumed to reach the first-stage return trajectory based on the separation velocity of the first-stage rocket;

[0134] S3. When the amount of unused fuel exceeds the amount of consumed fuel, the excess fuel is placed in the second-stage rocket, and the rocket stage ratio is reduced, and steps S1-S2 are repeated until the amount of unused fuel equals the amount of consumed fuel.

[0135] S4. Determine the rocket stage ratio used at the end as the optimal stage ratio of the rocket.

[0136] Optionally, step S1 includes:

[0137] determining an upper limit value of fuel consumption in an ascent phase of the first-stage rocket according to a separation speed of the first-stage rocket;

[0138] Based on the fuel consumption upper limit and the rocket stage ratio, the amount of unused fuel in the ascent section of the first-stage rocket is calculated.

[0139] Since the terminal device introduced in this embodiment is the terminal device used to implement the method for calculating the rocket inter-stage ratio in the embodiment of this application, based on the method for calculating the rocket inter-stage ratio introduced in the embodiment of this application, those skilled in the art can understand the specific implementation of the terminal device of this embodiment and its various variations, so how the terminal device implements the method in the embodiment of this application will not be described in detail here. As long as those skilled in the art implement the terminal device used by the method for calculating the rocket inter-stage ratio in the embodiment of this application, it falls within the scope of protection of this application.

[0140] The technical solutions in the above-mentioned embodiments of the present application have at least the following technical effects or advantages: the present application calculates the total rocket mass of the rocket based on different preset rocket payloads and rocket measurement parameters; calculates the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses based on the rocket measurement parameters and the target payload, wherein the target payload is determined based on the different rocket payloads; calculates the target second-stage mass of the rocket based on the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses; and calculates the rocket stage ratio of the rocket based on the total rocket mass and the target second-stage mass. In the above-mentioned solution, the present application calculates the target second-stage mass of the rocket based on the two characteristic velocity curves under different second-stage rocket masses, and finally calculates the current rocket stage ratio based on the total rocket mass and the target second-stage mass. This can reduce the number of calculations and the amount of calculations for the rocket stage ratio calculation, which is conducive to improving the convenience and accuracy of the rocket stage ratio calculation. At the same time, it also solves the technical problems of multiple calculations and high complexity involved in the optimization calculation of the rocket stage ratio in the prior art.

[0141] It will be understood by those skilled in the art that embodiments of the present invention may be provided as methods, systems, or computer program products. Thus, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware. Furthermore, the present invention may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to magnetic disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0142] The present invention is described with reference to flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowcharts and / or block diagrams, as well as combinations of processes and / or blocks in the flowcharts 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, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowcharts and / or block diagrams. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0143] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0144] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 The steps for the function specified in one or more boxes.

[0145] Although the preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0146] Obviously, those skilled in the art may make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if such changes and modifications fall within the scope of the claims and their equivalents, the present invention is intended to include such changes and modifications.

Claims

1. A method for calculating rocket stage ratio, characterized in that: Applied to a rocket having a two-stage configuration, the method comprises: Calculate the total mass of the rocket based on different preset rocket payloads and rocket measurement parameters; Calculating a first characteristic velocity curve and a second characteristic velocity curve under different second-stage rocket masses based on the rocket measurement parameters and the target load, wherein the target load is determined based on the different rocket loads; Calculating a target second-stage mass of the rocket based on the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses; Calculating a rocket stage ratio of the rocket based on the total rocket mass and the target second-stage mass; Calculating the target secondary mass of the rocket according to the first characteristic velocity curve and the second characteristic velocity curve under the different secondary rocket masses includes: Calculating the target second-stage mass of the rocket based on the changing trends of the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses; Based on the V1 curve and V0 curve under different second-stage rocket masses, the changing trend of the V0-V1 curve is observed to find the target second-stage mass corresponding to the minimum V1 curve; the target second-stage mass refers to the mass of the second-stage rocket in the rocket.

2. The method according to claim 1, characterized in that Calculating the total mass of the rocket according to different preset rocket payloads and rocket measurement parameters includes: Obtain rocket measurement parameters and set different rocket payloads; Inputting the rocket measurement parameters and different rocket loads into Qi's formula to calculate the third characteristic velocity curve under different rocket loads; The total mass of the rocket is calculated based on the third characteristic velocity curve under different rocket loads, the target load and the pre-assigned rocket characteristic velocity.

3. The method according to claim 1, characterized in that Calculating the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses according to the rocket measurement parameters and the target payload includes: Get the target payload and set different second-stage rocket masses; Inputting the target load, different masses of the second-stage rocket, and the rocket measurement parameters into the Qi formula, and calculating the first characteristic velocity curve under different masses of the second-stage rocket; The target load, different masses of the second-stage rocket and the rocket measurement parameters are input into a pre-stored ballistic program to calculate and obtain the second characteristic velocity curve under different masses of the second-stage rocket.

4. The method according to claim 1, wherein Calculating the rocket stage ratio of the rocket according to the total rocket mass and the target second-stage mass includes: Calculating the target first stage mass of the rocket based on the total rocket mass and the target second stage mass; The rocket stage ratio of the rocket is calculated based on the target first-stage mass and the target second-stage mass.

5. The method according to claim 1, wherein The method further comprises the following steps: S1. Calculating the amount of unused fuel in the ascent phase of the first-stage rocket based on the separation velocity of the first-stage rocket and the rocket inter-stage ratio; S2. Calculating the amount of fuel consumed to reach the first-stage return trajectory based on the separation velocity of the first-stage rocket; S3. When the amount of unused fuel exceeds the amount of consumed fuel, the excess fuel is placed in the second-stage rocket, and the rocket stage ratio is reduced, and steps S1-S2 are repeated until the amount of unused fuel equals the amount of consumed fuel. S4. Determine the rocket stage ratio used at the end as the optimal stage ratio of the rocket.

6. The method according to claim 5, characterized in that The step S1 comprises: determining an upper limit value of fuel consumption in an ascent phase of the first-stage rocket according to a separation speed of the first-stage rocket; Based on the fuel consumption upper limit and the rocket stage ratio, the amount of unused fuel in the ascent section of the first-stage rocket is calculated.

7. A device for calculating rocket stage ratio, characterized in that: The device includes a first calculation module, a second calculation module, a third calculation module and a fourth calculation module, wherein: The first calculation module is used to calculate the total mass of the rocket according to different preset rocket payloads and rocket measurement parameters; The second calculation module is used to calculate the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses according to the rocket measurement parameters and the target load, wherein the target load is determined according to the different rocket loads; The third calculation module is used to calculate the target second-stage mass of the rocket based on the first characteristic velocity curve and the second characteristic velocity curve under the different second-stage rocket masses; The third calculation module is specifically used to calculate the target second-stage mass of the rocket based on the changing trends of the first characteristic velocity curve and the second characteristic velocity curve under different second-stage rocket masses; Based on the V1 curve and V0 curve under different second-stage rocket masses, observe the changing trend of the V0-V1 curve and find the target second-stage mass corresponding to the minimum V1 curve; the target second-stage mass refers to the mass of the second-stage rocket in the rocket; The fourth calculation module is used to calculate the rocket stage ratio of the rocket based on the total rocket mass and the target second-stage mass.

8. A terminal device, characterized in that: The terminal device includes: a processor, a memory, a communication interface and a bus; the processor, the memory and the communication interface are connected through the bus and communicate with each other; the memory stores executable program code; the processor runs the program corresponding to the executable program code by reading the executable program code stored in the memory, so as to execute the method for calculating the rocket stage ratio as described in any one of claims 1 to 6 above.

9. A computer-readable storage medium, characterized in that The computer-readable storage medium stores a program, which, when run on a terminal device, executes the method for calculating the rocket stage ratio as described in any one of claims 1-6.

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