Ejection seat inertial measurement module inertia state switching method, computer equipment and medium
By real-time judgment of the handle signal and sending a forced switch to pure inertial navigation signal, the problem of MEMS inertial measurement modules using erroneous data during emergency ejection of rocket ejection seats was solved, ensuring data accuracy and improving ejection performance.
Patent Information
- Application Number
- CN202511455978.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-10-13
- Publication Date
- 2026-01-13
AI Technical Summary
The MEMS inertial measurement module erroneously used aircraft inertial navigation data for correction during emergency ejection of rocket ejection seats, resulting in decreased data accuracy and affecting ejection performance.
The rocket ejection seat controller collects the handle signal in real time to determine whether the connection is lost. After confirming the connection is lost, it sends 2N packets to the MEMS inertial measurement module at intervals t to force a switch to pure inertial navigation. This prevents the module from correcting attitude data within time T until it enters pure inertial navigation mode. If the aircraft inertial navigation data can still be received, it switches to combined navigation mode to continue correction.
This effectively avoids the use of erroneous data correction by the MEMS inertial measurement module during ejection, ensuring data accuracy and improving the control performance of the ejection seat.
Smart Images
Figure CN121325548A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The application relates to the field of ejection escape, in particular to an ejection seat inertial measurement module inertial state switching method, a computer device and a medium. BACKGROUND
[0002] The controller of the rocket ejection seat is mainly composed of a MEMS inertial measurement module and a height sensor, and after emergency ejection occurs, the controller of the rocket ejection seat automatically selects an ejection control program according to real-time motion parameters of the seat to realize an ejection program control function. When no emergency ejection occurs, the MEMS inertial measurement module of the rocket ejection seat receives aircraft inertial navigation data in real time, and uses the aircraft inertial navigation data for transfer alignment and entering a combined navigation state, and then uses the aircraft inertial navigation data to correct the data of the MEMS inertial measurement module in real time; when the pilot pulls the handle to perform emergency ejection, the rocket ejection seat moves a certain stroke upward, the floating plug / jack connected between the seat and the aircraft is disconnected, and the MEMS inertial measurement module cannot receive the aircraft inertial navigation data and is converted into a pure inertial navigation state.
[0003] However, the MEMS inertial measurement module is fixedly connected to the rocket ejection seat, and the aircraft inertial navigation system is fixedly connected to the aircraft, when emergency ejection occurs, the rocket ejection seat moves upward relative to the aircraft, and there is a difference between the motion states of the MEMS inertial measurement module and the aircraft inertial navigation system, before the floating plug / jack connected between the rocket ejection seat and the aircraft is disconnected, the MEMS inertial measurement module still uses the data of the aircraft inertial navigation system to correct the attitude, which can cause the data precision of the MEMS inertial measurement module output to the controller of the rocket ejection seat to be poor, and affect the ejection performance of the rocket ejection seat. SUMMARY
[0004] The application aims to provide an ejection seat inertial measurement module inertial state switching method, a computer device and a medium, which can solve the problem of incorrect correction of the data of the MEMS inertial measurement module by using the aircraft inertial navigation data during the emergency ejection process of the ejection seat.
[0005] The application is implemented in the following manner: The application provides an ejection seat inertial measurement module inertial state switching method, which comprises the following steps: The controller of the rocket ejection seat collects handle signals in real time, and judges whether the handle signals are disconnected or not; After confirming that the handle signals are disconnected, the controller sends 2N packets of forced pure inertial navigation signals to the MEMS inertial measurement module every interval time t; After the MEMS inertial measurement module receives the continuous N packets of forced pure inertial navigation signals, the attitude data is no longer corrected within a time T, and the MEMS inertial measurement module is converted into a pure inertial navigation state; If the MEMS inertial measurement module can still receive the aircraft inertial navigation data after time T, the MEMS inertial measurement module switches to the combined navigation state to continue correcting the attitude data.
[0006] In some optional embodiments, the controller of the rocket ejection seat performs de-bouncing processing on the handle signal in real time.
[0007] In some optional embodiments, t is 2-3 ms.
[0008] In some optional embodiments, t is 2.5 ms.
[0009] In some optional embodiments, N is 2-4.
[0010] In some optional embodiments, N is 3.
[0011] In some optional embodiments, time T is the time between the handle signal disconnection as zero point to the disconnection of the floating plug / socket.
[0012] In some optional embodiments, the controller sends the forced pure inertial navigation signal to the MEMS inertial measurement module using the RS422 signal.
[0013] The application also provides a computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the above method when executing the computer program.
[0014] The application also provides a computer readable storage medium, which stores a computer program, wherein the computer program is executable on a processor to implement the steps of the above method.
[0015] The application has the following beneficial effects: the ejection seat inertial measurement module inertial state switching method provided by the application comprises the following steps: the controller of the rocket ejection seat collects the handle signal in real time, and judges whether the handle signal is disconnected; after confirming that the handle signal is disconnected, the controller sends 2N packets of forced pure inertial navigation signals to the MEMS inertial measurement module every interval t; after the MEMS inertial measurement module receives N packets of forced pure inertial navigation signals in succession, the attitude data is no longer corrected within time T, and the MEMS inertial measurement module switches to the pure inertial navigation state; if the MEMS inertial measurement module can still receive the aircraft inertial navigation data after time T, the MEMS inertial measurement module switches to the combined navigation state to continue correcting the attitude data. The ejection seat inertial measurement module inertial state switching method provided by the application solves the problem of incorrect use of aircraft inertial navigation data by the MEMS inertial measurement module to correct its own data during the emergency ejection process of the ejection seat. BRIEF DESCRIPTION OF DRAWINGS
[0016] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.
[0017] Figure 1 A flowchart illustrating the inertial state switching method of the ejection seat inertial measurement module provided in this application embodiment; Figure 2 The forced switch to pure inertial navigation signal is sent in the inertial state switching method of the ejection seat inertial measurement module provided in the embodiments of this application. Detailed Implementation
[0018] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of this application, but not all embodiments.
[0019] Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.
[0020] The features and performance of the ejection seat inertial measurement module inertial state switching method of this application will be further described in detail below with reference to embodiments.
[0021] like Figure 1 As shown in the figure, this application embodiment provides a method for switching the inertial state of an ejection seat inertial measurement module, including the following steps: Step 1: The controller of the rocket ejection seat collects the handle signal in real time and performs de-jitter processing to determine whether the handle signal is disconnected. Step 2: After confirming that the handle signal is disconnected, the controller sends 2N packets to the MEMS inertial measurement module using RS422 signal at intervals t to force a switch to pure inertial navigation signal; optional, t is 2-3ms; optional, t is 2.5ms; optional, N is 2-4; optional, N is 3.
[0022] When N is 3, the forced conversion to pure inertial navigation signal sent is as follows: Figure 2 As shown.
[0023] Step three, after the MEMS inertial measurement module receives the continuous N packets of forced pure inertial navigation signals, the attitude data is no longer corrected in time T, and the MEMS inertial measurement module enters the pure inertial navigation state; time T is the time between the handle signal disconnection as zero point and the floating plug / socket disconnection; Step four, if the MEMS inertial measurement module can still receive the aircraft inertial navigation data after time T, the MEMS inertial measurement module enters the combined navigation state to continue to correct the attitude data.
[0024] The inertial state switching method of the ejection seat inertial measurement module provided by the embodiment of the application can ensure that the MEMS inertial measurement module of the ejection seat can avoid being disturbed during the ejection of the ejection seat, and solve the problem of incorrect use of the aircraft inertial navigation data by the MEMS inertial measurement module to correct its own data during the emergency ejection of the ejection seat.
[0025] The embodiment of the application further provides a computer device, which comprises a memory, a processor and a computer program stored in the memory and executable on the processor, and the processor implements the steps of the above method when executing the computer program.
[0026] The embodiment of the application further provides a computer readable storage medium, which stores a computer program, and the computer program is executed by a processor to implement the steps of the above method.
[0027] The above described embodiments are part of the embodiments of the application, rather than all the embodiments. The detailed description of the embodiments of the application is not intended to limit the scope of the claimed application, but only represents selected embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the application.
Claims
1. A method for switching the inertial state of an ejection seat inertial measurement module, characterized in that, Includes the following steps: The controller of the rocket ejection seat collects the handle signal in real time to determine whether the handle signal is disconnected; After confirming that the handle signal is disconnected, the controller sends 2N packets to the MEMS inertial measurement module at intervals t to force a switch to pure inertial navigation signal; After receiving N consecutive packets of forced transition to pure inertial navigation signals, the MEMS inertial measurement module will no longer correct the attitude data within time T, and the MEMS inertial measurement module will enter the pure inertial navigation state. If the MEMS inertial measurement module is still able to receive aircraft inertial navigation data after time T, the MEMS inertial measurement module switches to integrated navigation mode to continue correcting the attitude data.
2. The method for switching the inertial state of the ejection seat inertial measurement module according to claim 1, characterized in that, The controller of the rocket ejection seat collects the hand handle signal in real time and then performs anti-shake processing.
3. The method for switching the inertial state of the ejection seat inertial measurement module according to claim 1, characterized in that, t is 2-3 ms.
4. The method for switching the inertial state of the ejection seat inertial measurement module according to claim 1, characterized in that, t is 2.5ms.
5. The method for switching the inertial state of the ejection seat inertial measurement module according to claim 1, characterized in that, N is 2-4.
6. The method for switching the inertial state of the ejection seat inertial measurement module according to claim 1, characterized in that, N is 3.
7. The method for switching the inertial state of the ejection seat inertial measurement module according to claim 1, characterized in that, Time T is the time between the moment the handle signal is disconnected (zero point) and the moment the floating plug / socket is disconnected.
8. The method for switching the inertial state of the ejection seat inertial measurement module according to claim 1, characterized in that, The controller uses an RS422 signal to send a forced switch to pure inertial navigation signal to the MEMS inertial measurement module.
9. A computer device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the computer program, implements the steps of the method according to any one of claims 1 to 8.
10. A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the method according to any one of claims 1 to 8.