A method, device and storage medium for designing flight timing sequence of hot launch takeoff phase

Abstract

This application provides a method, device, and storage medium for designing the takeoff flight sequence for a hot launch. This method is specifically designed for the sea-based hot launch of large solid-propellant carrier rockets. The takeoff flight sequence design primarily involves arranging the chronological order of the rocket's key actions during the takeoff phase and designing the criteria for each action. This application ensures that, even in dynamic, high-sea conditions, the rocket reliably receives takeoff signals and executes each action according to established procedures. This ensures the rocket's normal liftoff and safe first-stage flight control.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace timing design, and in particular to a method, device and storage medium for designing the flight timing of a hot launch takeoff phase. Background Art

[0002] Traditional launch vehicles rely primarily on fixed launch towers for real-time launches, with relatively fixed launch locations. With the continuous development of my country's space industry, the frequency of launches is increasing. Sea-based launch technology enhances launch flexibility, providing support for future high-frequency commercial launches. Compared to land-based launches, the sea environment is more dynamic, and during launch testing, waves can have a certain impact on the rocket's motion. The design of the takeoff flight sequence plays a crucial role in ensuring a smooth and safe launch and flight. Summary of the Invention

[0003] To address the aforementioned technical issues, this application proposes a method, device, and computer-readable storage medium for designing the flight sequence for the takeoff phase of a rocket hot launch. This application addresses the design of a sea-based guide frame hot launch for a large solid-propellant carrier rocket. The technical solutions employed in this application are as follows:

[0004] A method for designing a hot launch takeoff flight sequence is disclosed. The method is applied in a high sea state dynamic environment and comprises the following steps:

[0005] Step 1: Based on the characteristics of the rocket's hot launch on the sea, sort out the timing sequence of the rocket's takeoff phase;

[0006] Step 2: Select a pair of redundant takeoff contacts to sense rocket takeoff, and use the connection state of the takeoff contacts as a criterion for rocket takeoff;

[0007] Step 3: Design the rocket liftoff criterion to ensure the first stage is under control after the rocket leaves the guide frame;

[0008] Step 4: Combine multiple deviations to analyze the time interval when the rocket receives the takeoff signal;

[0009] Step 5: Analyze the time interval and safety distance from takeoff to departure in a dynamic environment;

[0010] Step 6: Analyze the impact of the dynamic environment to ensure that the takeoff contacts are not triggered incorrectly, and when the takeoff contacts are connected multiple times, the arrow software will not respond multiple times.

[0011] Furthermore, in step 1, the sequential actions of the rocket takeoff segment include ignition of the first-stage engine, rocket takeoff, and rocket separation.

[0012] Furthermore, in step 2, the rocket take-off criterion includes: if the take-off contact is in the connected state, it is determined that the rocket has taken off; if the take-off contact is in the disconnected state, it is determined that the rocket has not taken off.

[0013] Furthermore, in step 3, the rocket liftoff criterion is the rocket flight altitude difference.

[0014] Furthermore, in step 4, the deviation includes engine performance, wave heave, and takeoff contact point compression.

[0015] Furthermore, in step 5, during the time interval from takeoff to separation from the launch pad in a dynamic environment, the rocket is in an uncontrolled state.

[0016] Furthermore, in step 5, the determination of leaving the frame is used as a first-stage launch control condition to ensure that the tail section of the rocket is at a certain distance from the guide frame when leaving the frame, and no structural interference occurs during the first-stage launch control.

[0017] Furthermore, in step 6, the arrow software will not respond multiple times, including: the arrow uses the takeoff signal as a connection and hold signal, and the arrow software will no longer respond after receiving the signal again after connection.

[0018] An electronic device comprises: one or more processors; and a memory for storing one or more programs, wherein when the one or more programs are executed by the one or more processors, the electronic device implements the above method.

[0019] A computer-readable storage medium stores a computer program, which implements the above method when executed by a processor.

[0020] The following technical effects can be achieved through the embodiments of this application: This application ensures that the rocket reliably receives the takeoff signal and executes various actions according to the established procedures in a high-sea dynamic environment. It can ensure the normal release of the rocket and the safe launch and control of the first stage flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application, a brief introduction is given below to the drawings required for use in the embodiments or descriptions of the prior art. Obviously, the drawings described below are some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0022] Figure 1 Schematic diagram of the flow of the timing design method of this application. DETAILED DESCRIPTION

[0023] To make the purpose, technical solutions, and advantages of the embodiments of this application more clear, the technical solutions in the embodiments of this application will be clearly and completely described below in conjunction with the drawings in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0024] The flight timing design of the takeoff phase mainly includes the chronological arrangement of the key actions of the rocket in the takeoff phase and the design of the criteria for the rocket to perform each action. Figure 1 This is a flow chart of the timing design method of this application. The method includes:

[0025] Step 1: Based on the characteristics of the rocket's hot launch on the sea, sort out the timing sequence of the rocket's takeoff phase;

[0026] The timing sequence of the rocket takeoff phase includes the ignition of the first-stage engine, the rocket taking off, and the rocket leaving the launcher;

[0027] Step 2: Select a pair of redundant takeoff contacts to sense rocket takeoff, and use the connection state of the takeoff contacts as a criterion for rocket takeoff;

[0028] The rocket take-off criterion includes: if the take-off contact is in the connected state, it is determined that the rocket has taken off; if the take-off contact is in the disconnected state, it is determined that the rocket has not taken off;

[0029] Because in a dynamic environment, the rocket will move with the waves, etc., it is difficult to set the appropriate motion speed or acceleration criteria, and there is a possibility of false triggering. This application uses a pair of redundant takeoff contacts to sense the rocket takeoff, so as to achieve the purpose of preventing false triggering before the rocket takes off and accurately sending the takeoff signal after takeoff.

[0030] Step 3: Design the rocket liftoff criterion to ensure the first stage control after the rocket leaves the guide frame;

[0031] The rocket lift-off criterion is the rocket flight altitude difference;

[0032] Since the launch is at sea, the rocket uses a guide frame for erection and hot launch, which requires ensuring that the first stage is launched after the rocket leaves the guide frame. The rocket release criterion must consider the impact of dynamic environments such as waves on the criterion, and ensure that the rocket has completely flown out of the guide frame when the criterion is met. Due to the hollow structure of the guide frame, it is difficult to install hardware sensors. Selecting the rocket's flight altitude difference can reduce the impact of the dynamic environment on the determination of rocket release;

[0033] Step 4: Combine multiple deviations to analyze the time interval when the rocket receives the takeoff signal;

[0034] The deviation includes engine performance, heave of waves, and compression deviation when the takeoff contact is connected;

[0035] In step 4, engine performance, wave heave, and takeoff contact compression can be considered as deviations. For example, when the engine's internal ballistic performance is high, the waves are at the heave crest, and the takeoff contact compression deviation is negative, the shortest takeoff time can be obtained. When the engine's internal ballistic performance is low, the waves are at the heave trough, and the takeoff contact compression deviation is positive, the longest takeoff time can be obtained.

[0036] Step 5: Analyze the time interval and safety distance from takeoff to departure in a dynamic environment;

[0037] In the time interval from takeoff to separation in a dynamic environment, the rocket is in an uncontrolled state. Separation from the launch frame will be judged as a first-stage launch control condition to ensure that the tail section of the rocket is at a certain distance from the guide frame when it leaves the launch frame, and no structural interference will occur during the first-stage launch control. Affected by the dynamic environment, engine performance, etc., the time from takeoff to separation is a dynamic range.

[0038] Step 6: Analyze the impact of the dynamic environment to ensure that the takeoff contacts are not falsely triggered, and that the onboard software does not respond multiple times when the takeoff contacts are connected multiple times.

[0039] In step 6, the arrow software will not respond multiple times, including: the arrow uses the takeoff signal as a connection and hold signal, and the arrow software will no longer respond after receiving the signal again after connection.

[0040] This application is designed for the sea-based guide frame hot launch of large solid-propellant carrier rockets. The rocket takeoff segment is defined as the period from issuing the rocket ignition command to the rocket leaving the frame (leaving the guide frame). After the first-stage engine is ignited, the rocket engine thrust pushes the rocket away from the launch platform, and the rocket takes off for autonomous flight. After the rocket flies in the guide frame for a period of time, it detaches from the guide frame and leaves the frame. The rocket takeoff sequence is the ignition of the first-stage engine, the rocket takeoff, and the rocket leaving the frame. The rocket takeoff is the starting point of the flight on the arrow, and the rocket leaving the frame is the starting point of the first-stage flight control. The key to the design of the takeoff segment flight sequence is to design a reasonable takeoff and departure criterion. The rocket takeoff is given based on a pair of redundant takeoff contact sensitivities. The rocket leaving the frame is determined based on the altitude difference of the rocket flight.

[0041] The functions described above in this application may be performed at least in part by one or more hardware logic components. For example, and without limitation, exemplary types of hardware logic components that may be used include: field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), systems on chips (SOCs), load programmable logic devices (CPLDs), and the like.

[0042] In addition, although adopting specific order to describe each operation, this should be understood as requiring such operation to be carried out in the specific order shown or in sequential order, or requiring that all illustrated operations should be carried out to obtain desired results. Under certain circumstances, multitasking and parallel processing may be advantageous. Similarly, although comprising some specific implementation details in the above discussion, these should not be interpreted as limiting the scope of the present disclosure. Some features described in the context of separate embodiment can also be implemented in a single implementation in combination. On the contrary, the various features described in the context of a single implementation also can be implemented in a plurality of implementations individually or in the mode of any suitable subcombination.

[0043] Although the subject matter has been described in language specific to structural features and / or device logical actions, it should be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or actions described above. Rather, the specific features and actions described above are merely example forms of implementing the claims.

Claims

1. A method for designing a flight sequence for a hot launch takeoff phase, which is applied in a high sea state dynamic environment, is characterized in that: The method comprises the following steps: Step 1: Based on the characteristics of the rocket's hot launch on the sea, sort out the timing sequence of the rocket's takeoff phase; Step 2: Select a pair of redundant takeoff contacts to sense rocket takeoff, and use the connection state of the takeoff contacts as a criterion for rocket takeoff; Step 3: Design the rocket liftoff criterion to ensure the first stage control after the rocket leaves the guide frame; Step 4: Combine multiple deviations to analyze the time interval when the rocket receives the takeoff signal; Step 5: Analyze the time interval and safety distance from takeoff to departure in a dynamic environment; Step 6: Analyze the impact of the dynamic environment to ensure that the takeoff contacts are not falsely triggered, and that the onboard software does not respond multiple times when the takeoff contacts are connected multiple times. In step 4, the deviation includes engine performance, wave heave, and takeoff contact point compression; In step 6, the onboard software will not respond multiple times, including: the rocket will use the takeoff signal as a hold signal, and the onboard software will no longer respond after receiving the signal again after being connected; this method is designed for the sea-based guide frame hot launch of large solid-propellant carrier rockets, and the rocket takeoff segment is defined as from issuing the rocket ignition command to the rocket leaving the guide frame. After the first-stage engine is ignited, the rocket engine thrust pushes the rocket away from the launch platform, and the rocket takes off for autonomous flight. After the rocket flies in the guide frame for a period of time, it detaches from the guide frame and leaves the frame; the rocket takeoff segment timing actions are, in sequence, the first-stage engine ignition, rocket takeoff, and rocket departure; the rocket takeoff serves as the starting point of the onboard flight, and the rocket departure serves as the starting point of the first-stage flight segment launch control. The rocket takeoff is given based on a pair of redundant takeoff contact sensitivities, and the rocket departure is determined based on the altitude difference of the rocket flight.

2. The method according to claim 1, characterized in that In step 5, during the time interval from takeoff to separation from the launch pad in a dynamic environment, the rocket is in an uncontrolled state.

3. The method according to claim 1 or 2, characterized in that In step 5, the determination of leaving the frame is used as a first-stage launch control condition to ensure that the tail section of the rocket is a certain distance away from the guide frame when leaving the frame, and no structural interference will occur during the first-stage launch control.

4. An electronic device, comprising: one or more processors; and a memory for storing one or more programs, which, when executed by the one or more processors, enables the electronic device to implement the method according to any one of claims 1 to 3.

5. A computer-readable storage medium having a computer program stored thereon, wherein when the program is executed by a processor, the method according to any one of claims 1 to 3 is implemented.

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