Liquid launch vehicle high overload orbital guidance method, device and electronic equipment

Abstract

The present invention discloses a liquid carrier rocket high overload orbital entry guidance method, device and electronic equipment. First, the flight information of the target engine of the liquid carrier rocket is obtained when it is ignited; then, the equivalent working time is determined based on the flight information and the aftereffect impulse after the target engine is shut down; then, the shutdown time of the target engine is determined based on the equivalent working time and the flight information using an iterative guidance method; finally, the ignition time and shutdown time of the auxiliary power system of the liquid carrier rocket are determined based on the shutdown time, aftereffect impulse and the real-time orbit semi-major axis of the liquid carrier rocket, so that the liquid carrier rocket enters the preset target orbit. In this way, by fully considering the equivalent effect of the aftereffect impulse after shutdown when controlling the flight of the liquid rocket, the aftereffect impulse is used to propel the flight of the liquid rocket, thereby overcoming the deviation caused by the aftereffect impulse on the orbital entry and improving the accuracy of the liquid rocket's orbital entry.

Description

Technical Field

[0001] The present invention relates to the field of guidance and control technology, and in particular to a liquid carrier rocket high-overload orbital guidance method, device and electronic equipment. Background Art

[0002] When a multi-stage liquid rocket (such as a two-stage liquid rocket) uses a high-thrust liquid rocket engine, under the condition of high thrust and high overload direct orbital entry, even if the attitude control system maintains the original command tracking accuracy, the velocity deviation during orbital entry will increase significantly, affecting the orbital entry accuracy. Currently, the method of reducing the thrust before orbital entry is adopted to improve the orbital entry accuracy: if the second stage uses four engines, the thrust before orbital entry can be reduced by shutting down two engines at a time; if the second stage uses one engine, variable thrust can be used to reduce the thrust before orbital entry to a low thrust mode.

[0003] However, after adopting the above method, the axial overload generated by the high-thrust liquid rocket engine is still large, there is a large aftereffect impulse after shutdown, and the aftereffect impulse deviation is also large, which ultimately leads to a large orbital deviation.

[0004] Therefore, how to improve the orbital accuracy of liquid rockets is the problem we currently need to solve. Summary of the invention

[0005] In view of the above problems, the present invention is proposed to provide a liquid carrier rocket high-overload orbital guidance method, device and electronic equipment that overcome the above problems or at least partially solve the above problems, which can overcome the deviation of the rocket into orbit caused by the aftereffect impulse and improve the orbital insertion accuracy of the liquid rocket.

[0006] According to a first aspect of the present invention, a liquid launch vehicle high overload orbital guidance method is provided, comprising:

[0007] Obtain flight information when the target engine of a liquid launch vehicle is ignited;

[0008] According to the flight information and the aftereffect impulse after the target engine is shut down, the equivalent working time is determined, and the product of the equivalent working time and the thrust of the target engine is equal to the aftereffect impulse after the target engine is shut down;

[0009] According to the equivalent working time and flight information, the shutdown time of the target engine is determined by using the iterative guidance method;

[0010] According to the shutdown time of the target engine, the aftereffect impulse and the real-time orbital semi-major axis of the liquid carrier rocket, the ignition time and shutdown time of the auxiliary power system of the liquid carrier rocket are determined to enable the liquid carrier rocket to enter the preset target orbit.

[0011] Optionally, according to the equivalent working time and the flight information, an iterative guidance method is used to determine the shutdown time of the target engine, including:

[0012] According to the equivalent working time and flight information, the iterative guidance method is used to determine the program pitch angle, program yaw angle, orbital roots and remaining shutdown time according to the preset iterative calculation cycle;

[0013] When the remaining shutdown time is less than the preset time, the iterative calculation is stopped, and the shutdown time of the target engine is determined based on the programmed pitch angle, programmed yaw angle and equivalent working time obtained from the last iterative calculation.

[0014] Optionally, when the target engine is shut down at the shutdown time, the real-time orbital semi-major axis of the liquid carrier rocket is greater than ab, where a is the standard value of the preset target orbital semi-major axis, and b is the influence of the aftereffect impulse deviation on the preset target orbital semi-major axis.

[0015] Optionally, the preset iterative calculation period ranges from 100 to 300 milliseconds.

[0016] Optionally, the preset time ranges from 0.5 to 2 seconds.

[0017] Optionally, the ignition time and shutdown time of the auxiliary power system of the liquid launch vehicle are determined according to the shutdown time of the target engine, the aftereffect impulse and the real-time orbit semi-major axis of the liquid launch vehicle, including:

[0018] According to the shutdown time and aftereffect impulse of the target engine, the ignition time of the auxiliary power system of the liquid launch vehicle is determined;

[0019] When the real-time orbital semi-major axis of the liquid launch vehicle is greater than a, the shutdown time of the auxiliary power system of the liquid launch vehicle is determined, where a is the standard value of the preset target orbital semi-major axis.

[0020] Optionally, the target engine is a second stage engine.

[0021] Optionally, the flight information includes the velocity, position, thrust, mass of the liquid launch vehicle and the ignition time of the target engine.

[0022] According to a second aspect of the present invention, there is provided a liquid carrier rocket high overload orbital guidance device, comprising:

[0023] An information acquisition module, used to obtain flight information when the target engine of a liquid carrier rocket is ignited;

[0024] The first processing module is used to determine the equivalent working time according to the flight information and the aftereffect impulse after the target engine is shut down, and the product of the equivalent working time and the thrust of the target engine is equal to the aftereffect impulse after the target engine is shut down;

[0025] The second processing module is used to determine the shutdown time of the target engine by using an iterative guidance method according to the equivalent working time and the flight information;

[0026] The third processing module is used to determine the ignition time and shutdown time of the auxiliary power system of the liquid carrier rocket according to the shutdown time of the target engine, the aftereffect impulse and the real-time orbital semi-major axis of the liquid carrier rocket, so as to enable the liquid carrier rocket to enter the preset target orbit.

[0027] According to a third aspect of the present invention, there is provided an electronic device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the computer program, the aforementioned liquid launch vehicle high overload orbital guidance method is implemented.

[0028] According to a fourth aspect of the present invention, there is provided a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the aforementioned liquid launch vehicle high-overload orbital guidance method.

[0029] The above one or more technical solutions in the embodiments of this specification have at least the following technical effects:

[0030] The embodiments of this specification provide a method, device and electronic device for guiding a liquid carrier rocket into orbit with a large overload. First, the flight information of the target engine of the liquid carrier rocket is obtained when it is ignited; then, the equivalent working time is determined based on the flight information and the aftereffect impulse after the target engine is shut down, and the product of the equivalent working time and the thrust of the target engine is equal to the aftereffect impulse after the target engine is shut down; then, based on the equivalent working time and the flight information, the shutdown time of the target engine is determined using an iterative guidance method; finally, based on the shutdown time of the target engine, the equivalent working time and the real-time orbit semi-major axis of the liquid carrier rocket, the ignition time and shutdown time of the auxiliary power system of the liquid carrier rocket are determined to enable the liquid carrier rocket to enter the preset target orbit. In this way, by fully considering the equivalent effect of the aftereffect impulse after shutdown when controlling the flight of the liquid rocket, the aftereffect impulse is used to propel the flight of the liquid rocket, thereby overcoming the deviation caused by the aftereffect impulse on the rocket's orbital entry and improving the orbital accuracy of the liquid rocket.

[0031] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, it can be implemented according to the contents of the specification. In order to make the above and other purposes, features and advantages of the present invention more obvious and easy to understand, the specific implementation methods of the present invention are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] By reading the detailed description of the preferred embodiment below, various other advantages and benefits will become clear to those of ordinary skill in the art. The accompanying drawings are only used for the purpose of illustrating the preferred embodiment and are not considered to be limiting of the present invention. Moreover, the same reference figures are used to represent the same parts throughout the accompanying drawings.

[0033] In the attached picture:

[0034] Figure 1 A schematic diagram of an electronic device in an embodiment of the present invention is shown.

[0035] Figure 2 A flow chart of a liquid carrier rocket high overload orbital guidance method in an embodiment of the present invention is shown.

[0036] Figure 3 A flow chart of another liquid carrier rocket high overload orbital guidance method in an embodiment of the present invention is shown.

[0037] Figure 4 A block diagram of a liquid carrier rocket high-overload orbital guidance device in an embodiment of the present invention is shown.

[0038] icon:

[0039] 100-electronic equipment; 10-liquid launch vehicle high overload orbital guidance device; 11-information acquisition module; 12-first processing module; 13-second processing module; 14-third processing module; 20-memory; 30-processor; 40-communication unit. DETAILED DESCRIPTION

[0040] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0041] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0042] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0043] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0044] When a multi-stage liquid rocket (such as a two-stage liquid rocket) uses a high-thrust liquid rocket engine, under the condition of high thrust and high overload direct orbital entry, even if the attitude control system maintains the original command tracking accuracy, the velocity deviation during orbital entry will increase significantly, affecting the orbital entry accuracy. Currently, the method of reducing the thrust before orbital entry is adopted to improve the orbital entry accuracy: if the second stage uses four engines, the thrust before orbital entry can be reduced by shutting down two engines at a time; if the second stage uses one engine, variable thrust can be used to reduce the thrust before orbital entry to a low thrust mode.

[0045] However, after adopting the above method, the axial overload generated by the high-thrust liquid rocket engine is still large, there is a large aftereffect impulse after shutdown, and the aftereffect impulse deviation is also large, which ultimately leads to a large orbital deviation.

[0046] Based on the above research content, this embodiment provides a liquid carrier rocket high overload orbital insertion guidance method. When controlling the flight of the liquid rocket, the equivalent effect of the aftereffect impulse after shutdown is fully considered, and the aftereffect impulse is used to propel the flight of the liquid rocket, thereby overcoming the deviation caused by the aftereffect impulse on the orbital insertion and improving the orbital insertion accuracy of the liquid rocket.

[0047] See also Figure 1 , Figure 1 FIG. 1 is a structural block diagram of an electronic device 100 provided in this embodiment. Figure 1As shown, the electronic device may include a liquid carrier rocket high overload orbital guidance device 10, a memory 20, a processor 30 and a communication unit 40. The memory 20 stores machine-readable instructions executable by the processor 30. When the electronic device 100 is running, the processor 30 and the memory 20 communicate through a bus, and the processor 30 executes the machine-readable instructions and executes the liquid carrier rocket high overload orbital guidance method.

[0048] The memory 20, the processor 30 and the communication unit 40 are electrically connected to each other directly or indirectly to realize signal transmission or interaction. For example, these elements can be electrically connected to each other through one or more communication buses or signal lines. The liquid launch vehicle high overload orbital guidance device 10 includes at least one software function module that can be stored in the memory 20 in the form of software or firmware. The processor 30 is used to execute the executable module stored in the memory 20 (for example, the software function module or computer program included in the liquid launch vehicle high overload orbital guidance device 10).

[0049] Among them, the memory 20 can be, but is not limited to, random access memory (Random Access Memory, RAM), read only memory (Read Only Memory, ROM), programmable read-only memory (Programmable Read-Only Memory, PROM), erasable programmable read-only memory (Erasable Programmable Read-Only Memory, EPROM), electrically erasable read-only memory (Electric Erasable Programmable Read-Only Memory, EEPROM), etc.

[0050] In some embodiments, the processor 30 is used to perform one or more functions described in the present embodiment. In some embodiments, the processor 30 may include one or more processing cores (e.g., a single-core processor (S) or a multi-core processor (S)). By way of example only, the processor 30 may include a central processing unit (CPU), an application specific integrated circuit (ASIC), an application specific instruction set processor (ASIP), a graphics processing unit (GPU), a physical processing unit (PPU), a digital signal processor (DSP), a field programmable gate array (FPGA), a programmable logic device (PLD), a controller, a microcontroller unit, a reduced instruction set computer (RISC) or a microprocessor, or any combination thereof.

[0051] For ease of explanation, only one processor is described in the electronic device 100. However, it should be noted that the electronic device 100 in this embodiment may also include multiple processors, so the steps performed by one processor described in this embodiment may also be performed jointly or individually by multiple processors. For example, if the processor of the server executes step A and step B, it should be understood that step A and step B may also be performed jointly by two different processors or individually in one processor. For example, the processor executes step A and the second processor executes step B, or the processor and the second processor execute steps A and B together.

[0052] In this embodiment, the memory 20 is used to store programs, and the processor 30 is used to execute the programs after receiving execution instructions. The process definition method disclosed in any implementation of this embodiment can be applied to the processor 30 or implemented by the processor 30.

[0053] The communication unit 40 is used to establish a communication connection between the electronic device 100 and other devices through a network, and to send and receive data through the network.

[0054] In some embodiments, the network may be any type of wired or wireless network, or a combination thereof. By way of example only, the network may include a wired network, a wireless network, a fiber optic network, a telecommunications network, an intranet, the Internet, a local area network (LAN), a wide area network (WAN), a wireless local area network (WLAN), a metropolitan area network (MAN), a wide area network (WAN), a public switched telephone network (PSTN), a Bluetooth network, a ZigBee network, or a near field communication (NFC) network, or any combination thereof.

[0055] In this embodiment, the electronic device 100 can be, but is not limited to, a notebook computer, an ultra-mobile personal computer (UMPC), a netbook, a personal digital assistant (PDA), and the like. This embodiment does not impose any limitation on the specific type of the electronic device.

[0056] Understandably, Figure 1 The structure shown is for illustration only. The electronic device 100 may also have Figure 1 More or fewer components than shown, or with Figure 1 Different configurations are shown. Figure 1 The components shown may be implemented in hardware, software or a combination thereof.

[0057] based on Figure 1 The implementation architecture of this embodiment provides a liquid carrier rocket high overload orbit guidance method, which comprises Figure 1 The electronic device 100 shown in FIG. 1 performs the following operation based on Figure 1 The structure diagram of the electronic device 100 shown in the embodiment describes in detail the steps of a liquid launch vehicle overload orbit guidance method provided in this embodiment. Figure 2 As shown, the liquid carrier rocket high overload orbital guidance method includes steps 101 to 104:

[0058] Step 101: Acquire flight information of a target engine of a liquid carrier rocket when it is ignited.

[0059] The liquid launch vehicle of this embodiment can be a two-stage liquid launch vehicle or a three-stage liquid launch vehicle. If the liquid launch vehicle of this embodiment is a two-stage liquid launch vehicle, the target engine is a two-stage engine; if the liquid launch vehicle of this embodiment is a three-stage liquid launch vehicle, the target engine is a three-stage engine.

[0060] When the target engine is ignited, the flight information at that moment is obtained. It should be explained that the flight information includes the speed, position, thrust, mass of the liquid carrier rocket and the ignition time of the target engine.

[0061] Step 102: Determine the equivalent working time based on the flight information and the aftereffect impulse after the target engine is shut down. The product of the equivalent working time and the target engine thrust is equal to the aftereffect impulse after the target engine is shut down.

[0062] It should be noted that the aftereffect impulse of the target engine can be calculated. It is common to measure it through the target engine test. At the same time, the time required for the aftereffect impulse to complete the action after the target engine is shut down can also be calculated. In this embodiment, the time for the aftereffect impulse to complete the action after the target engine is shut down is about 2 seconds. Considering that after the target engine is shut down, the aftereffect impulse generated by it can be equivalent to the thrust action time when the target engine is working, so that its equivalent working time can be calculated. In other words, the product of the equivalent working time and the thrust of the target engine is equal to the aftereffect impulse after the target engine is shut down.

[0063] Step 103: According to the equivalent working time and flight information, the shutdown time of the target engine is determined by using an iterative guidance method.

[0064] After obtaining the equivalent working time and flight information, when iterative guidance is used to calculate the shutdown time of the target engine, the influence of the aftereffect impulse and the equivalent working time can be fully considered, thereby reducing the deviation caused by the aftereffect impulse after the target engine is shut down.

[0065] Step 104: According to the shutdown time of the target engine, the aftereffect impulse and the real-time orbital semi-major axis of the liquid launch vehicle, the ignition time and shutdown time of the auxiliary power system of the liquid launch vehicle are determined to enable the liquid launch vehicle to enter the preset target orbit.

[0066] It should be noted that after the target engine is shut down, the auxiliary power system of the liquid launch vehicle will not ignite immediately, but wait until the aftereffect impulse is exhausted before the auxiliary power system ignites. In this way, the aftereffect impulse after the target engine is shut down is used to control the flight of the liquid launch vehicle. Then, the auxiliary power system ignites and corrects the flight of the liquid launch vehicle to enter the preset target orbit. It is easy to understand that the preset target orbit is pre-designed, and its orbital semi-major axis is a known quantity.

[0067] Combination Figure 3 As shown, step 103 regarding "determining the shutdown time of the target engine by using an iterative guidance method according to the equivalent working time and flight information" may include the following steps:

[0068] Step 201: According to the equivalent working time and flight information, using the iterative guidance method and the preset iterative calculation cycle, the program pitch angle, program yaw angle, orbital roots and remaining shutdown time are determined;

[0069] Step 202: When the remaining shutdown time is less than the preset time, the iterative calculation is stopped, and the shutdown time of the target engine is determined based on the program pitch angle, program yaw angle and equivalent working time obtained by the last iterative calculation.

[0070] Specifically, after obtaining the equivalent working time and flight information, the iterative guidance method can be used according to the equivalent working time and flight information to perform calculations according to a preset iterative calculation cycle. The preset iterative calculation cycle can range from 100 to 300 milliseconds. Preferably, in this embodiment, the preset iterative calculation cycle is 100 milliseconds.

[0071] It should be noted that the so-called iterative guidance, to be precise, means that the rocket will adjust its flight trajectory according to its current position, the current speed, position and estimated orbital entry point during flight. When estimating the orbital entry point, the influence of the aftereffect impulse should be considered, and the required orbital entry point is calculated. Then, according to the spatial relative relationship between the current position and the orbital entry point, a new trajectory is planned to ensure the orbital entry accuracy and the attitude of the orbital entry. In this embodiment, the iterative calculation is performed again every 100 milliseconds to obtain a new program pitch angle, program yaw angle, orbital root number and remaining shutdown time, until the remaining shutdown time is less than the preset time, the iterative calculation is stopped. Optionally, the preset time ranges from 0.5 to 2 seconds. Preferably, in this embodiment, the preset time is 1 second. After stopping the iterative calculation, the program pitch angle, program yaw angle and remaining shutdown time obtained by the last iterative guidance are provided to the attitude control system to control the rocket flight, and after the remaining shutdown time, the shutdown time of the target engine is reached.

[0072] In addition, it should be noted that when the target engine is shut down at the shutdown time, the real-time orbital semi-major axis of the liquid carrier rocket is greater than ab, where a is the standard value of the preset target orbital semi-major axis, and b is the influence of the aftereffect impulse deviation on the preset target orbital semi-major axis. Both a and b can be calculated.

[0073] After the target engine is shut down, the liquid carrier rocket continues to fly. After the aftereffect impulse of the target engine has been exhausted, the auxiliary power system will be turned on to make flight corrections.

[0074] In an optional implementation, determining the ignition time and shutdown time of the auxiliary power system of the liquid launch vehicle according to the shutdown time of the target engine, the aftereffect impulse and the real-time orbit semi-major axis of the liquid launch vehicle comprises the following steps:

[0075] According to the shutdown time and aftereffect impulse of the target engine, the ignition time of the auxiliary power system of the liquid launch vehicle is determined;

[0076] When the real-time orbital semi-major axis of the liquid launch vehicle is greater than a, the shutdown time of the auxiliary power system of the liquid launch vehicle is determined, where a is the standard value of the preset target orbital semi-major axis.

[0077] It is easy to understand that in this embodiment, the aftereffect impulse is used to continue to promote the normal flight of the liquid carrier rocket, and the action time of the aftereffect impulse is used as a part of the calculation of the flight time of the liquid carrier rocket. Thus, after the target engine is shut down, the auxiliary power system is ignited after the action time of the aftereffect impulse, so as to correct the speed deviation caused by the aftereffect impulse deviation. In this embodiment, the axial overload can be measured to determine whether the aftereffect impulse has been completed, that is, when the axial overload is less than the preset binding value, the aftereffect impulse has been completed, and the auxiliary power system is ignited. The ignition time of the auxiliary power system can also be determined according to the aftereffect impulse action time measured by the test run. As mentioned above, in this embodiment, the aftereffect impulse action completion time is about 2 seconds, that is, the ignition time of the auxiliary power system can be determined according to the shutdown time of the target engine and the action time of the aftereffect impulse. For example, the target engine is shut down at 12:10:10, the auxiliary power system is ignited at 12:10:12, or the auxiliary power system is ignited at 12:10:13.

[0078] When the real-time orbit semi-major axis of the liquid launch vehicle is greater than a, the shutdown time of the auxiliary power system of the liquid launch vehicle is determined to enable the liquid launch vehicle to enter the preset target orbit, where a is the standard value of the semi-major axis of the preset target orbit.

[0079] The embodiment of this specification provides a liquid carrier rocket high overload orbital guidance method. First, the flight information of the target engine of the liquid carrier rocket is obtained when it is ignited; then, the equivalent working time is determined based on the flight information and the aftereffect impulse after the target engine is shut down, and the product of the equivalent working time and the thrust of the target engine is equal to the aftereffect impulse after the target engine is shut down; then, based on the equivalent working time and the flight information, the shutdown time of the target engine is determined using an iterative guidance method; finally, based on the shutdown time of the target engine, the aftereffect impulse and the real-time orbit semi-major axis of the liquid carrier rocket, the ignition time and shutdown time of the auxiliary power system of the liquid carrier rocket are determined to enable the liquid carrier rocket to enter the preset target orbit. In this way, by fully considering the equivalent effect of the aftereffect impulse after shutdown when controlling the flight of the liquid rocket, the aftereffect impulse is used to propel the flight of the liquid rocket, thereby overcoming the deviation caused by the aftereffect impulse on the orbital entry and improving the orbital entry accuracy of the liquid rocket.

[0080] Based on the same inventive concept, Figure 4 As shown, the embodiment of this specification also provides a liquid launch vehicle high overload orbital guidance device 10, including: an information acquisition module 11, a first processing module 12, a second processing module 13 and a third processing module 14.

[0081] The information acquisition module 11 is used to obtain the flight information of the target engine of the liquid carrier rocket when it is ignited;

[0082] The first processing module 12 is used to determine the equivalent working time according to the flight information and the aftereffect impulse after the target engine is shut down, and the product of the equivalent working time and the thrust of the target engine is equal to the aftereffect impulse after the target engine is shut down;

[0083] The second processing module 13 is used to determine the shutdown time of the target engine by using an iterative guidance method according to the equivalent working time and the flight information;

[0084] The third processing module 14 is used to determine the ignition time and shutdown time of the auxiliary power system of the liquid launch vehicle according to the shutdown time of the target engine, the aftereffect impulse and the real-time orbit semi-major axis of the liquid launch vehicle, so as to enable the liquid launch vehicle to enter the preset target orbit.

[0085] In an optional implementation, the second processing module 13 is further used for:

[0086] According to the equivalent working time and flight information, the iterative guidance method is used to determine the program pitch angle, program yaw angle, orbital roots and remaining shutdown time according to the preset iterative calculation cycle;

[0087] When the remaining shutdown time is less than the preset time, the iterative calculation is stopped, and the shutdown time of the target engine is determined based on the programmed pitch angle, programmed yaw angle and equivalent working time obtained from the last iterative calculation.

[0088] In an optional implementation, the second processing module 13 is further used for:

[0089] When the target engine is shut down at the shutdown time, the real-time orbit semi-major axis of the liquid carrier rocket is greater than ab, where a is the standard value of the preset target orbit semi-major axis, and b is the influence of the aftereffect impulse deviation on the preset target orbit semi-major axis.

[0090] In an optional implementation, the third processing module 14 is further used for:

[0091] According to the shutdown time and aftereffect impulse of the target engine, the ignition time of the auxiliary power system of the liquid launch vehicle is determined;

[0092] When the real-time orbital semi-major axis of the liquid launch vehicle is greater than a, the shutdown time of the auxiliary power system of the liquid launch vehicle is determined, where a is the standard value of the preset target orbital semi-major axis.

[0093] In summary, the embodiment of this specification provides a liquid carrier rocket high overload orbital guidance device, firstly obtains the flight information of the target engine of the liquid carrier rocket when it is ignited; then, according to the flight information and the aftereffect impulse after the target engine is shut down, the equivalent working time is determined, and the product of the equivalent working time and the thrust of the target engine is equal to the aftereffect impulse after the target engine is shut down; then, according to the equivalent working time and the flight information, the shutdown time of the target engine is determined by using the iterative guidance method; finally, according to the shutdown time of the target engine, the aftereffect impulse and the real-time orbit semi-major axis of the liquid carrier rocket, the ignition time and shutdown time of the auxiliary power system of the liquid carrier rocket are determined, so that the liquid carrier rocket enters the preset target orbit. In this way, by fully considering the equivalent effect of the aftereffect impulse after the shutdown when controlling the flight of the liquid rocket, the aftereffect impulse is used to propel the flight of the liquid rocket, thereby overcoming the deviation caused by the aftereffect impulse to the orbital entry, and improving the orbital entry accuracy of the liquid rocket.

[0094] Technicians in the relevant field can clearly understand that, for the convenience and simplicity of description, the specific working process of the liquid carrier rocket high-overload orbit-entry guidance device described above can refer to the corresponding process in the aforementioned method, and will not be elaborated here.

[0095] Based on the above, this embodiment provides a readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the liquid carrier rocket high overload orbital guidance method of any of the aforementioned embodiments is implemented.

[0096] Those skilled in the art can clearly understand that, for the convenience and brevity of description, the specific working process of the readable storage medium described above can refer to the corresponding process in the aforementioned method, and will not be described in detail here.

[0097] The above are only various embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A liquid launch vehicle high overload orbit guidance method, characterized in that: include: Obtain flight information when the target engine of a liquid launch vehicle is ignited; Determine an equivalent working time according to the flight information and the aftereffect impulse of the target engine after being shut down, wherein the product of the equivalent working time and the thrust of the target engine is equal to the aftereffect impulse of the target engine after being shut down; According to the equivalent working time and the flight information, using an iterative guidance method, determining the shutdown time of the target engine; According to the shutdown time of the target engine, the aftereffect impulse and the real-time orbital semi-major axis of the liquid carrier rocket, the ignition time and the shutdown time of the auxiliary power system of the liquid carrier rocket are determined to enable the liquid carrier rocket to enter a preset target orbit.

2. The liquid carrier rocket overload orbit guidance method according to claim 1, characterized in that: The method of determining the shutdown time of the target engine by using an iterative guidance method according to the equivalent working time and the flight information includes: According to the equivalent working time and the flight information, using an iterative guidance method and a preset iterative calculation cycle, a program pitch angle, a program yaw angle, a number of orbital elements and a remaining shutdown time are determined; When the remaining shutdown time is less than the preset time, the iterative calculation is stopped, and the shutdown time of the target engine is determined based on the program pitch angle, program yaw angle and equivalent working time obtained by the last iterative calculation.

3. The liquid carrier rocket overload orbit guidance method according to claim 2, characterized in that: When the target engine is shut down at the shutdown time, the real-time orbit semi-major axis of the liquid carrier rocket is greater than ab, where a is the standard value of the preset target orbit semi-major axis, and b is the influence of the aftereffect impulse deviation on the preset target orbit semi-major axis.

4. The liquid carrier rocket overload orbit guidance method according to claim 2, characterized in that: The preset time ranges from 0.5 to 2 seconds.

5. The liquid carrier rocket overload orbit guidance method according to claim 1, characterized in that: The step of determining the ignition time and the shutdown time of the auxiliary power system of the liquid launch vehicle according to the shutdown time, the aftereffect impulse and the real-time orbit semi-major axis of the target engine comprises: Determining the ignition time of the auxiliary power system of the liquid launch vehicle according to the shutdown time and the aftereffect impulse of the target engine; When the real-time orbital semi-major axis of the liquid launch vehicle is greater than a, the shutdown time of the auxiliary power system of the liquid launch vehicle is determined, wherein a is a preset target orbital semi-major axis standard value.

6. The liquid carrier rocket overload orbit guidance method according to claim 1, characterized in that: The flight information includes the speed, position, thrust, mass of the liquid launch vehicle and the ignition time of the target engine.

7. The liquid carrier rocket overload orbit guidance method according to claim 1, characterized in that: The target engine is a two-stage engine.

8. A liquid launch vehicle high overload orbital guidance device, characterized in that: include: An information acquisition module, used to obtain flight information when the target engine of a liquid carrier rocket is ignited; A first processing module is used to determine an equivalent working time according to the flight information and the aftereffect impulse of the target engine after being shut down, wherein the product of the equivalent working time and the thrust of the target engine is equal to the aftereffect impulse of the target engine after being shut down; A second processing module is used to determine the shutdown time of the target engine by using an iterative guidance method according to the equivalent working time and the flight information; The third processing module is used to determine the ignition time and shutdown time of the auxiliary power system of the liquid carrier rocket according to the shutdown time of the target engine, the aftereffect impulse and the real-time orbital semi-major axis of the liquid carrier rocket, so as to enable the liquid carrier rocket to enter a preset target orbit.

9. An electronic device, characterized in that: The electronic device includes: a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, the liquid carrier rocket high-overload orbital guidance method described in any one of claims 1-7 is implemented.

10. A computer-readable storage medium, characterized in that: A computer program is stored thereon, and when the program is executed by a processor, the liquid carrier rocket high-overload orbital guidance method as described in any one of claims 1-7 is implemented.

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