Output control method for separated parachute ejection in ejection lifesaving seat

Abstract

The invention discloses an output control method for separating parachute shooting in an ejection lifesaving seat, which comprises the following steps: separating parachute shooting electric detonators comprise two paths of separating electric detonators and one path of parachute shooting electric detonators, and the method comprises the following steps: detecting the separating electric detonators 1, 2 and the parachute shooting electric detonators in sequence when the ejection lifesaving seat is electrified for self-inspection; the ejection lifesaving seat sends the detection result of each electric detonator to the VMC through the health management data packet; and after the ejection lifesaving seat is judged to meet the releasing condition, the program controller measures the longitude, latitude, flight speed and height of the aircraft according to an inertial measurement module in the program controller, and dynamically controls the separation electric detonators and the parachute ejection electric detonators to output according to a time sequence. The problem that in an existing control mode of the ejection lifesaving seat, due to the fact that the static pressure measurement value cannot correctly reflect the real environment air pressure, the height data obtained based on the static pressure signals have large errors, and effective support cannot be provided for control over an ejection lifesaving system is solved.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of aircraft ejection rescue technology, and particularly to an output control method for the separation parachute in an ejection rescue seat. Background Technology

[0002] Ejection seats are critical equipment for pilots to escape in emergency situations. The ejection mechanism and parachute mechanism of the ejection seat play a vital role as core components in the ejection process. They are not only directly related to the pilot's life safety, but also affect the safety and reliability of the entire flight mission. Their efficient and reliable operation is an indispensable part of the modern flight safety assurance system.

[0003] The existing ejection seat controls the separation and parachute mechanisms as follows: At the moment of ejection, speed and altitude information are acquired based on the aircraft's static pressure signal. A suitable delay curve is then selected for this delay. The static pressure signal output from the seat-mounted altitude sensor is then collected in real-time until the altitude value corresponding to the collected static pressure signal falls below the controlled parachute deployment altitude. At this point, the separation and parachute detonators are activated. This existing control method relies heavily on static pressure signals to obtain speed and altitude. However, the complex airflow interference generated during ejection causes unstable ambient air pressure, making the static pressure measurement inaccurate to reflect the true environmental air pressure. This results in significant errors in the altitude data acquired based on the static pressure signal, failing to provide effective support for the ejection system's control. Summary of the Invention

[0004] The purpose of this invention is to provide an output control method for the separation parachute in an ejection seat, in order to solve the problem that the existing control method of ejection seats mainly relies on static pressure signals to obtain speed and altitude. Due to the complex airflow interference generated when the ejection seat exits the cabin, the surrounding air pressure is in an unstable state, which makes the static pressure measurement value unable to accurately reflect the real environmental air pressure. This results in a large error in the altitude data obtained based on the static pressure signal, and cannot provide effective support for the control of the ejection life-saving system.

[0005] The technical solution of this invention is as follows: This invention provides an output control method for the separation parachute in an ejection seat. The separation parachute detonation tube in the ejection seat includes two separation detonation tubes and one parachute detonation tube. The output control method includes: Step 1: During the power-on self-test of the ejection seat, the separation detonator 1, separation detonator 2, and parachute detonator are tested sequentially. Step 2: The ejection seat sends the test results of each detonator to the aircraft management computer (VMC) via a health management data package, so that ground crew can determine whether the ejection seat meets the launch conditions based on the test results of each detonator. Step 3: After determining in Step 2 that the ejection seat meets the launch conditions, the programmable controller uses its internal inertial measurement module to measure the longitude, latitude, flight speed, and altitude of the aircraft, and dynamically controls the separate detonators and parachute detonators to output in sequence.

[0006] 2. The output control method for the separation parachute in an ejection seat according to claim 1, characterized in that, in step 1, the detection method for each electro-explosive tube includes: Step 1.1: Enable the detection circuit of the electric detonator to be tested. It will only be enabled when the test is initiated to ensure the safety of the electric detonator in the non-detection state. Step 1.2: Detect the current connection status of the electric detonator. If the electric detonator is detected to be disconnected, no further detection of the electric detonator will be performed. Step 1.3: If the detonator is detected as connected in Step 1.2, turn on the current detonator detection switch, delay for 3ms, and then check the current detonator level signal at 0.05ms intervals. If the signal is low for 3 consecutive times, the current detonator self-test is considered normal, which is the non-trigger state. If the signal is not low for 3 consecutive times, stop the detection after 6 consecutive checks, and the current detonator self-test is considered abnormal, which is the trigger state. Step 1.4: Turn off the current electric detonator detection switch and shut down the electric detonator detection circuit to ensure the safety of the electric detonator in the non-detection state.

[0007] 3. The output control method for the separation parachute in the ejection seat according to claim 1, characterized in that the health management data packet sent in step 2 includes a status bit of "Separation detonator 1 self-test status", "Separation detonator 2 self-test status", "Parachute detonator self-test status" and "Function failure status".

[0008] 4. The method for controlling the output of the separation parachute in an ejection seat according to claim 3, characterized in that step 2 includes: The ejection seat's internal controller reports the test results of the three detonators to the aircraft management computer (VMC) through three status positions: "Separation detonator 1 self-test status", "Separation detonator 2 self-test status", and "Parachute detonator self-test status"; and simultaneously reports "Function failure status". When both the separate electric detonator 1 and the separate electric detonator 2 fail to self-test, or when the parachute electric detonator fails to self-test, the programmable controller will report a failure through the "Function Failure Status". When all the electric detonators are in normal self-test, or when only one of the separate electric detonators 1 and 2 is in abnormal self-test and the parachute electric detonator is in normal self-test, the programmable controller will report that it is not in failure through the "function failure status".

[0009] 5. The method for controlling the output of the separation parachute in an ejection seat according to claim 1, characterized in that, before step 3, it further includes: After the programmable controller is powered on and initialized, the seat's hot battery charging is turned on to provide power for the ignition circuit of the electric detonator when each electric detonator is outputting; and the hot battery charging is required to be turned off before outputting any electric detonator.

[0010] 6. The output control method for the separation parachute in an ejection seat according to claim 1, characterized in that the programmable controller is pre-configured with preset parachute deployment speeds V corresponding to different longitude, latitude, and flight altitude regions. 预设 and preset parachute opening height H 预设 Step 3 includes: Step 3.1: The programmable controller obtains the preset parachute deployment speed V corresponding to the current longitude, latitude, and altitude region based on the aircraft's longitude, latitude, and flight altitude at the moment of ejection. 预设 and preset parachute opening height H 预设 ; Step 3.2: During the ejection process, the programmable controller obtains the real-time velocity V based on its internal inertial measurement module. 实时 and real-time height H 实时 First, determine whether V is satisfied. 实时 ≤V 预设 Next, determine whether H is satisfied. 实时 ≤H 预设 After determining that the above conditions are met simultaneously, the thermal battery is shut down, and the output of the separation electric detonator and the parachute electric detonator is controlled.

[0011] 7. The output control method for the separation parachute in an ejection seat according to claim 6, characterized in that the judgment process in step 3.2 includes: S1, determine whether V is satisfied. 实时 ≤V 预设 When the condition is met, execute S2; when V... 实时 >V 预设 At that time, the programmable controller determines the required delay time based on the real-time speed and real-time altitude. During the waiting delay, it cyclically checks whether the V value is satisfied. 实时 ≤V 预设 If the condition is met, then exit the speed determination and execute S2. S2, determine whether H is satisfied. 实时 ≤H 预设 When the condition is met, execute S3; when H... 实时 >H 预设 At that time, the programmable controller determines the required delay time based on the real-time speed and real-time altitude. During the waiting delay, it cyclically checks whether the H condition is met. 实时 ≤H 预设If the condition is met, then skip the height determination and execute S3. S3, the programmable controller shuts down the thermal battery and controls each separate electric detonator and parachute electric detonator to output in sequence.

[0012] 8. The method for controlling the output of the separation parachute in an ejection seat according to any one of claims 1 to 7, characterized in that the method of controlling the sequential output of each separation detonator and the parachute detonator is as follows: First, control the two separate detonators to output simultaneously, and after a preset delay, control the parachute detonator to output; the purpose of the delay is to ensure that sufficient space is formed between the pilot and the seat after separation.

[0013] The beneficial effects of this invention are as follows: This invention provides an output control method for the separation parachute in an ejection seat. The separation parachute detonator in the ejection seat includes two separation detonators and one parachute detonator. The two separation detonators (separation detonator 1 and separation detonator 2) are designed with dual redundancy, which significantly improves the reliability of the system. Even if one of them fails, the other can still ensure the completion of the pilot's separation from the seat. The separation detonator separates the pilot from the seat at the appropriate time to avoid the pilot being dragged or collided with by the seat during landing. The parachute detonator automatically deploys and releases the parachute after the pilot separates from the seat to ensure a safe landing for the pilot. The output control method for the separation parachute provided by this invention, after each electric detonator completes its self-test, sends the test results of each electric detonator to the VMC through a health management data packet. After the ground crew determines that the ejection seat meets the launch conditions, the programmable controller measures the longitude, latitude, flight speed and altitude of the aircraft based on its internal inertial measurement module, and dynamically controls each separation electric detonator and parachute electric detonator to output in sequence.

[0014] Compared to existing ejection seat control methods that primarily rely on static pressure signals to obtain speed and altitude, the complex airflow interference generated during ejection causes unstable ambient air pressure, making static pressure measurements inaccurate and leading to significant errors in altitude data obtained based on static pressure signals. This hinders effective support for the ejection system's control. The technical solution provided by this invention significantly improves the reliability, safety, and intelligence of the ejection seat's separation parachute's electric detonator through mechanisms such as power-on self-testing and health management data reporting, and dynamic control based on flight parameters. This effectively ensures the pilot's escape safety in emergency situations. Attached Figure Description

[0015] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0016] Figure 1 A flowchart illustrating the output control method for the separation parachute in an ejection seat according to an embodiment of the present invention; Figure 2 for Figure 1 The flowchart of the self-test method of each electric detonator in the output control method of the separation parachute in the ejection seat provided in the embodiment shown is as follows: Figure 3 for Figure 1 The flowchart illustrates the output control of each separation detonator and the detonator in the output control method for the separation parachute in the ejection seat provided in the illustrated embodiment. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0018] As explained in the background section, the separation mechanism and parachute mechanism, as core components of ejection seats, significantly impact the safety and reliability of the entire flight mission. Furthermore, prior to ejection, safety checks and early warnings are required for the separation and parachute detonators to detect potential malfunctions and prevent casualties. With the increasing complexity and variability of modern flight environments, pilots may be at different altitudes, speeds, and attitudes during ejection. Therefore, the separation and parachute mechanisms not only need high safety and reliability but also the ability to optimize the output timing of the separation and parachute detonators in real time based on varying conditions, ensuring the pilot's safe escape under diverse circumstances.

[0019] The following are specific explanations regarding the problems with the existing control methods for ejection seats: 1) Existing control methods mainly rely on static pressure signals to obtain speed and altitude. However, the complex airflow interference generated when the ejection seat exits the cabin causes the surrounding air pressure to be in an unstable state, making the static pressure measurement value unable to accurately reflect the real ambient air pressure. This results in a large error in the altitude data obtained based on the static pressure signal. Furthermore, since the entire ejection process of the ejection seat generally lasts only milliseconds, altitude measurement based on static pressure signals is unreliable during the ejection process and cannot provide effective support for the control of the ejection life-saving system. 2) The delay curve of the existing control method is usually based on fixed flight conditions and is preset. The control logic is relatively simple and lacks the ability to dynamically adjust the timing of the parachute separation according to real-time flight parameters. This results in the delay being too long or too short in complex flight environments and diverse flight conditions, which affects the success rate of ejection rescue. 3) The existing control method only begins to collect the static pressure signal of the altitude sensor in real time after the delay ends, and controls the separation and release of the parachute when the altitude is lower than the control parachute opening altitude. The data real-time performance is insufficient, which increases the time that the pilot is exposed to the dangerous environment during ejection and reduces the safety of ejection rescue. 4) The existing control method does not perform power-on detection and fault reporting for the separation and parachute electric detonator; 5) The existing control method adopts a single-channel separation electric detonator design, which has relatively low reliability. Once the circuit fails or the electric detonator itself fails, the entire separation system may not work properly. The separation electric detonator plays an important role in the ejection process. It can quickly and reliably separate the pilot from the seat under the strong impact force generated at the moment the seat exits the cabin, avoiding injury to the pilot due to the subsequent movement of the seat during high-speed ejection, while providing sufficient space for the pilot's parachute to deploy.

[0020] In summary, there is an urgent need to propose a method for safety detection of the separation mechanism and the electric detonator in the parachute mechanism of ejection seats, as well as an output control method for the separation electric detonator and the parachute electric detonator. Based on this need, this invention provides an output control method for the separation parachute in an ejection seat. This control method can detect and report the on / off status of the separation electric detonator and the parachute electric detonator, and can optimize the timing of the parachute separation according to different flight conditions, thereby improving the system's safety, real-time performance, and flexibility, and further enhancing the reliability and success rate of ejection rescue.

[0021] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they may not be described again in some embodiments.

[0022] Figure 1This is a flowchart illustrating the output control method for the separation parachute in an ejection seat according to an embodiment of the present invention. In this embodiment, the electro-explosive tube structure in the ejection seat is configured as follows: the separation parachute electro-explosive tube consists of two separation electro-explosive tubes and one parachute electro-explosive tube. The two separation electro-explosive tubes (separation electro-explosive tube 1 and separation electro-explosive tube 2) employ a dual-redundancy design, significantly improving system reliability. Even if one tube fails, the other can still ensure the completion of the pilot's separation from the seat. The function of the separation electro-explosive tube is to separate the pilot from the seat at an appropriate time, preventing the pilot from being dragged or collided with by the seat during descent. The function of the parachute electro-explosive tube is to automatically deploy and release the parachute after the pilot separates from the seat, ensuring a safe landing for the pilot.

[0023] This invention relates to an output control method for the separation parachute in an ejection seat, comprising the following steps: high-safety detection of the electric detonation tube of the separation parachute; Step 1: High-safety test of separating the parachute electric detonator; During the power-on self-test of the ejection seat, the separation detonator 1, separation detonator 2, and parachute detonator are tested sequentially. Figure 2 As shown. The self-testing method for the power-on of the separate electric detonator 1, separate electric detonator 2, and parachute electric detonator is the same.

[0024] Step 2: After the detection of each electric detonator is completed, the ejection seat sends the detection results of each electric detonator to the aircraft management computer (VMC) through the health management data package, so that ground crew can determine whether the ejection seat meets the launch conditions based on the detection results of each electric detonator. Step 3: After determining in Step 2 that the ejection seat meets the launch conditions, the programmable controller uses its internal inertial measurement module to measure the longitude, latitude, flight speed, and altitude of the aircraft, and dynamically controls the separate detonators and parachute detonators to output in sequence.

[0025] In one implementation of this invention, such as Figure 2 As shown, taking the self-testing method of the separated electric detonator 1 as an example, the self-testing method of each electric detonator is explained, which specifically includes the following steps: 1.1 Enable the detection circuit of the electric detonator to be tested. It will only be enabled when the test is initiated, so as to ensure the safety of the electric detonator in the non-detection state. 1.2 Detect the connection status of the detonating tube 1. If the detonating tube is detected to be disconnected, no further detection of the detonating tube shall be performed. 1.3 If the detonator connection is detected as described in 1.2, turn on the detection switch for detonator 1. Delay for 3ms, then check the level signal of detonator 1 at 0.05ms intervals. If the signal is low for three consecutive tests, detonator 1 is considered to have normal self-testing, i.e., in a non-triggered state. If the signal is not low for three consecutive tests, stop detection after six consecutive checks, indicating a faulty self-test of detonator 1, i.e., in a triggered state. This detection method, through delay and debouncing, ensures the reliability of the detonator detection.

[0026] 1.4 Turn off the detection switch of the detonating tube 1 to shut down the detonating tube detection circuit, so as to ensure the safety of the detonating tube in the non-detection state.

[0027] It should be noted that the power-on self-test method is the same for the separate electric detonator 1, separate electric detonator 2, and the parachute electric detonator. Figure 2 The self-test of the separated electric detonator 1 is shown as an example.

[0028] In one implementation of this invention, in step 2, a health management data packet is sent, for example, via RS422, and the health management data packet includes status bits for "Separated detonator 1 self-test status," "Separated detonator 2 self-test status," "Parachute detonator self-test status," and "Function failure status." The specific sending method in step 2 includes: The ejection seat's internal controller reports the test results of the three detonators to the aircraft management computer (VMC) through three status positions: "Separation detonator 1 self-test status", "Separation detonator 2 self-test status", and "Parachute detonator self-test status"; and simultaneously reports "Function failure status". When both the separating electric detonator 1 and the separating electric detonator 2 malfunction during self-test, or when the parachute electric detonator malfunctions during self-test, the programmable controller will report a failure through the "functional failure status" (functional failure refers to a fault that completely affects the lifesaving function). When all detonating tubes self-test normally, or when only one of the separation detonating tubes 1 and 2 self-tests abnormally while the parachute detonating tube self-tests normally, the programmable controller will report a "functional failure status" indicating that it is not faulty. This means that the basic life-saving function of the ejection seat separation parachute is not affected, and the aircraft can be deployed in an emergency. Therefore, ground crew can determine whether each detonating tube self-tests normally and whether it meets the deployment conditions by checking these statuses.

[0029] In one implementation of this invention, step 3, the output control of each separate detonator and parachute detonator in the ejection seat, is implemented as follows: The programmable controller is equipped with ignition circuits for detonating the individual detonating tubes and parachute detonating tubes, and features a capacitor management strategy and a dynamic control strategy based on flight parameters. (1) Capacitor management strategy: In order to ensure the reliable output of the ignition circuit inside the programmable controller used to detonate each electric detonator, the hot battery charging of the seat is turned on after the programmable controller is powered on and initialized; the hot battery charging is required to be turned off before outputting any electric detonator.

[0030] (2) Dynamic control based on flight parameters: The programmable controller measures the longitude, latitude, flight speed and altitude of the aircraft based on its internal inertial measurement module, and dynamically controls the output of each separate electric detonator and parachute electric detonator.

[0031] like Figure 3 The diagram shown is a schematic flowchart illustrating the output control of the separate detonating tubes and parachute detonating tubes in the ejection seat according to an embodiment of the present invention. The programmable controller is pre-configured with preset parachute deployment speeds V corresponding to different longitudes, latitudes, and flight altitudes within latitude and longitude regions. 预设 and preset parachute opening height H 预设 The output control flow in step 3 includes: Step 3.1: The programmable controller obtains the preset parachute deployment speed V corresponding to the current longitude, latitude, and altitude region based on the aircraft's longitude, latitude, and flight altitude at the moment of ejection. 预设 and preset parachute opening height H 预设 ; Step 3.2: During the ejection process, the programmable controller obtains the real-time velocity V based on its internal inertial measurement module. 实时 and real-time height H 实时 First, determine whether V is satisfied. 实时 ≤V 预设 Next, determine whether H is satisfied. 实时 ≤H 预设 After determining that the above conditions are met simultaneously, the thermal battery is shut down, and the output of the separation electric detonator and the parachute electric detonator is controlled.

[0032] In one implementation, the judgment process in step 3.2 includes: S1, determine whether V is satisfied. 实时 ≤V 预设 When the condition is met, execute S2; when V... 实时 >V 预设 At that time, the programmable controller determines the required delay time based on the real-time speed and real-time altitude. During the waiting delay, it cyclically checks whether the V value is satisfied. 实时 ≤V 预设 If the condition is met, then exit the speed determination and execute S2. S2, determine whether H is satisfied. 实时 ≤H 预设 When the condition is met, execute S3; when H... 实时 >H 预设At that time, the programmable controller determines the required delay time based on the real-time speed and real-time altitude. During the waiting delay, it cyclically checks whether the H condition is met. 实时 ≤H 预设 If the condition is met, then skip the height determination and execute S3. S3, the programmable controller shuts down the thermal battery and controls the separation of the electric detonator and the parachute electric detonator to output in sequence.

[0033] It should be noted that the timing sequence for controlling the output of the separation detonator and the parachute detonator is as follows: first, control the two separation detonators to output simultaneously, and then, after a certain delay, control the parachute detonator to output. The delay is to ensure sufficient space is created between the pilot and seat after separation, thereby preventing mutual interference.

[0034] This invention provides an output control method for the separation parachute in an ejection seat. The separation parachute detonator in the ejection seat includes two separation detonators and one parachute detonator. The two separation detonators (separation detonator 1 and separation detonator 2) are designed with dual redundancy, which significantly improves the reliability of the system. Even if one of them fails, the other can still ensure the completion of the pilot's separation from the seat. The separation detonators separate the pilot from the seat at the appropriate time to prevent the pilot from being dragged or collided with by the seat during landing. The parachute detonator automatically deploys and releases the parachute after the pilot separates from the seat to ensure a safe landing for the pilot. The output control method for the separation parachute provided by this invention, after each electric detonator completes its self-test, sends the test results of each electric detonator to the VMC through a health management data packet. After the ground crew determines that the ejection seat meets the launch conditions, the programmable controller measures the longitude, latitude, flight speed and altitude of the aircraft based on its internal inertial measurement module, and dynamically controls each separation electric detonator and parachute electric detonator to output in sequence.

[0035] Compared to existing ejection seat control methods that primarily rely on static pressure signals to obtain speed and altitude, the complex airflow interference generated during ejection causes unstable ambient air pressure, making static pressure measurements inaccurate and leading to significant errors in altitude data obtained based on static pressure signals. This hinders effective support for the ejection system's control. The technical solution provided by this invention significantly improves the reliability, safety, and intelligence of the ejection seat's separation parachute's electric detonator through mechanisms such as power-on self-testing and health management data reporting, and dynamic control based on flight parameters. This effectively ensures the pilot's escape safety in emergency situations.

[0036] The following is an illustrative description of the implementation method of the output control method for the separation parachute in the ejection seat provided by the present invention.

[0037] Implementation Example In this implementation example, based on the state analysis of the ejection rescue process and software safety design principles, a high-safety detection and optimized control strategy for the ejection seat separation parachute electric detonator is proposed. The specific scheme is as follows: (1) The separation parachute detonator consists of two separation detonators and one parachute detonator. The two separation detonators are separation detonator 1 and separation detonator 2. Each separation detonator can separate the pilot from the seat at the appropriate time to avoid the pilot being dragged or collided with the seat during the descent. After the pilot is separated from the seat, the parachute detonator can automatically launch and deploy the parachute to ensure that the pilot can obtain a stable descent speed in a short time and avoid injury caused by high-speed descent.

[0038] (2) High-safety testing of the separation parachute electric detonator, the testing methods include: 2.1 During the power-on self-test of the separation parachute electric detonator, the separation electric detonator 1, the separation electric detonator 2, and the parachute electric detonator are tested sequentially. This testing mechanism ensures that the electric detonators are in normal working condition during the ejection process, avoiding separation or parachute failure due to electric detonator malfunction, thereby significantly improving the reliability of the separation parachute electric detonator.

[0039] 2.2 After the separation of the detonating tube is completed, the ejection seat sends a health management data packet to the aircraft management computer (VMC) via RS422. Health management is a real-time health status reporting data packet sent by the ejection seat to the VMC via RS422. The health management data includes status bits for "Separation Detonating Tube 1 Self-test Status", "Separation Detonating Tube 2 Self-test Status", "Parachute Detonating Tube Self-test Status", and "Function Failure Status". The software reports the status of the three separation parachute detonator self-tests to the aircraft management computer (VMC) via three status bits: "Separation Detonator 1 Self-Test Status," "Separation Detonator 2 Self-Test Status," and "Parachute Detonator Self-Test Status." Simultaneously, if both separation detonators 1 and 2 fail their self-tests, or if the parachute detonator fails its self-test, the software reports a failure via the "Function Failure Status" bit. If only one of separation detonators 1 or 2 fails and the parachute detonator self-test is normal, the basic life-saving function of the ejection seat's separation parachute remains unaffected, allowing for deployment during emergency sorties. This mechanism ensures that faults are promptly detected and addressed by ground personnel, preventing safety hazards caused by delayed fault detection.

[0040] (3) Optimized control of the split-launch parachute electric detonator 3.1 Capacitor Management: To ensure sufficient power when the detonating tube of the separation parachute is output, the hot battery charging is turned on after the software is powered on and initialized; the hot battery charging is turned off before the detonating tube of the output parachute is separated. This mechanism avoids the problem of detonating tube failure due to insufficient capacitor power and further improves the reliability of the system.

[0041] 3.2 Dynamic Control Based on Flight Parameters: The software dynamically controls the output of the separation parachute's electric detonator based on the aircraft's longitude, latitude, flight speed, and altitude. Specifically: (a) The software sets different preset parachute deployment speeds V based on the aircraft's latitude, longitude, and altitude at the moment of ejection. 预设 and preset parachute opening height H 预设 Flight altitude not exceeding When m, H 预设 = m, V 预设 = km / h, flight altitude greater than At time m, the system determines in real-time whether the location is in a high-altitude region based on longitude and latitude. When the longitude and latitude information is valid and the location is in a high-altitude region, V... 预设 = km / h, H 预设 = m; when latitude and longitude information is valid and the location is in a low-altitude area, V 预设 = km / h, H 预设 = m; When latitude and longitude information is invalid, V 预设 = km / h, H 预设 = m.

[0042] (b) During ejection, the ejection seat acquires real-time velocity V. 实时 and real-time height H 实时 The software first determines whether V is satisfied. 实时 ≤V 预设 Next, determine whether H is satisfied. 实时 ≤H 预设 Finally, the output of the separation parachute electric detonator is controlled.

[0043] (c) When V 实时 >V 预设 At that time, the software selects different delay times based on real-time speed and altitude. While waiting for the delay During the process, iteratively checks whether V is satisfied. 实时 ≤V 预设 If the condition is met, then exit the speed determination and execute H. 实时 and H预设 The judgment; when V 实时 ≤V 预设 At that time, the software continues to execute H without delay. 实时 and H 预设 The judgment; (d) When H 实时 >H 预设 At that time, the software selects different delay times based on real-time speed and altitude. While waiting for the delay During the process, iteratively checks whether H is satisfied. 实时 ≤H 预设 If the conditions are met, the height determination is skipped, and the output of the separation parachute electric detonator is controlled; when H 实时 ≤H 预设 At that moment, the software immediately controls the output of the separation parachute electric detonator; (e) The output timing of the separation parachute detonator is as follows: first control the output of the separation detonator, and after a delay of Nms (Nms can be 15ms, 20ms, 25ms or 30ms), control the output of the parachute detonator.

[0044] While the embodiments disclosed in this invention are as described above, they are merely illustrative of the embodiments to facilitate understanding of the invention and are not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and variations in the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection for this invention shall still be determined by the scope defined in the appended claims.

Claims

1. A method for output control of the separation parachute in an ejection seat, characterized in that, The ejection seat's separation parachute detonator includes two separation detonators and one parachute detonator. The output control method includes: Step 1: During the power-on self-test of the ejection seat, the separation detonator 1, separation detonator 2, and parachute detonator are tested sequentially. Step 2: The ejection seat sends the test results of each detonator to the aircraft management computer (VMC) via a health management data package, so that ground crew can determine whether the ejection seat meets the launch conditions based on the test results of each detonator. Step 3: After determining in Step 2 that the ejection seat meets the launch conditions, the programmable controller uses its internal inertial measurement module to measure the longitude, latitude, flight speed, and altitude of the aircraft, and dynamically controls the separate detonators and parachute detonators to output in sequence.

2. The output control method for the separation parachute in an ejection seat according to claim 1, characterized in that, In step 1, the detection method for each electric detonator includes: Step 1.1: Enable the detection circuit of the electric detonator to be tested. It will only be enabled when the test is initiated to ensure the safety of the electric detonator in the non-detection state. Step 1.2: Detect the current connection status of the electric detonator. If the electric detonator is detected to be disconnected, no further detection of the electric detonator will be performed. Step 1.3: If the detonator is detected as connected in Step 1.2, turn on the current detonator detection switch, delay for 3ms, and then check the current detonator level signal at 0.05ms intervals. If the signal is low for 3 consecutive times, the current detonator self-test is considered normal, which is the non-trigger state. If the signal is not low for 3 consecutive times, stop the detection after 6 consecutive checks, and the current detonator self-test is considered abnormal, which is the trigger state. Step 1.4: Turn off the current electric detonator detection switch and shut down the electric detonator detection circuit to ensure the safety of the electric detonator in the non-detection state.

3. The output control method for the separation parachute in an ejection seat according to claim 1, characterized in that, The health management data packet sent in step 2 includes status bits for "Separation of detonating tube 1 self-test status", "Separation of detonating tube 2 self-test status", "Parachute detonating tube self-test status", and "Function failure status".

4. The output control method for the separation parachute in an ejection seat according to claim 3, characterized in that, Step 2 includes: The ejection seat's internal programmable controller reports the test results of the three detonators to the aircraft management computer (VMC) through three status positions: "Separation detonator 1 self-test status", "Separation detonator 2 self-test status", and "Parachute detonator self-test status"; and simultaneously reports "Function failure status". When both the separate electric detonator 1 and the separate electric detonator 2 fail to self-test, or when the parachute electric detonator fails to self-test, the programmable controller will report a failure through "functional failure status". When all the electric detonators are in normal self-test, or when only one of the separate electric detonators 1 and 2 is in abnormal self-test and the parachute electric detonator is in normal self-test, the programmable controller will report that it is not in failure through "functional failure status".

5. The output control method for the separation parachute in an ejection seat according to claim 1, characterized in that, Before step 3, the following are also included: After the programmable controller is powered on and initialized, the seat's hot battery charging is turned on to provide power for the ignition circuit of the electric detonator when each electric detonator is outputting; and the hot battery charging is required to be turned off before outputting any electric detonator.

6. The output control method for the separation parachute in an ejection seat according to claim 1, characterized in that, The programmable controller is pre-configured with preset parachute deployment speeds V corresponding to different longitudes, latitudes, and flight altitudes within latitude and longitude regions. 预设 and preset parachute opening height H 预设 Step 3 includes: Step 3.1: The programmable controller obtains the preset parachute deployment speed V corresponding to the current longitude, latitude, and altitude region based on the aircraft's longitude, latitude, and flight altitude at the moment of ejection. 预设 and preset parachute opening height H 预设 ; Step 3.2: During the ejection process, the programmable controller obtains the real-time velocity V based on its internal inertial measurement module. 实时 and real-time height H 实时 First, determine whether V is satisfied. 实时 ≤V 预设 Next, determine whether H is satisfied. 实时 ≤H 预设 After determining that the above conditions are met simultaneously, the thermal battery is shut down, and the output of the separation electric detonator and the parachute electric detonator is controlled.

7. The output control method for the separation parachute in an ejection seat according to claim 6, characterized in that, The judgment process in step 3.2 includes: S1, determine whether V is satisfied. 实时 ≤V 预设 When the condition is met, execute S2; when V... 实时 >V 预设 At that time, the programmable controller determines the required delay time based on the real-time speed and real-time altitude. During the waiting delay, it cyclically checks whether the V requirement is met. 实时 ≤V 预设 If the condition is met, then exit the speed determination and execute S2. S2, determine whether H is satisfied. 实时 ≤H 预设 When the condition is met, execute S3; when H... 实时 >H 预设 At that time, the programmable controller determines the required delay time based on the real-time speed and real-time altitude. During the waiting delay, it cyclically checks whether the H condition is met. 实时 ≤H 预设 If the condition is met, then skip the height determination and execute S3. S3, the programmable controller shuts down the thermal battery and controls each separate electric detonator and parachute electric detonator to output in sequence.

8. The output control method for the separation parachute in an ejection seat according to any one of claims 1 to 7, characterized in that, The method for controlling the sequential output of each separate electric detonator and parachute electric detonator is as follows: First, control the two separate detonators to output simultaneously, and after a preset delay, control the parachute detonator to output; the purpose of the delay is to ensure that sufficient space is formed between the pilot and the seat after separation.

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