A parachute ejection method, ejection device, parachute and aircraft

Abstract

This application discloses a parachute ejection method, ejection device, parachute, and aircraft, relating to the field of parachute ejection technology. It effectively solves the problems of sensor zero-point drift and error escalation at low temperatures by dynamically correcting acceleration thresholds, employing redundant primary and backup sensor design, and adapting to multiple types of ejection execution modules. This covers different low-temperature ranges, ensuring accurate and reliable parachute ejection, avoiding delays or misjudgments, reducing aircraft crash losses and ground safety risks, and adapting to the emergency needs of various aircraft. This solution effectively eliminates threshold judgment delays and misjudgments in low-temperature environments.

Description

Technical Field

[0001] This application relates to the field of parachute ejection technology, specifically to a parachute ejection method, ejection device, parachute, and aircraft. Background Technology

[0002] With the increasing prevalence of consumer-grade target aircraft, industrial mapping aircraft, and personal powered parachutes, their applications have expanded to low-temperature regions such as the Qinghai-Tibet Plateau and polar regions, as well as special scenarios such as high-altitude operations and spacecraft recovery. This places higher demands on the reliability of emergency safety devices for these devices. In the event of loss of control, power failure, or a crash, these devices urgently require efficient emergency deceleration devices to avoid personnel casualties and equipment damage. As a core safety guarantee, the adaptability and stability of ejection parachutes directly affect operational safety.

[0003] The core working logic of a conventional acceleration-sensing ejection parachute is "abnormal acceleration detection → intelligent judgment → ejection trigger → parachute deployment." It collects three-dimensional acceleration data through an accelerometer, the control unit distinguishes emergency situations based on preset thresholds, and then ejects the parachute using springs or other means, relying on airflow to inflate and deploy. This technology has been successfully implemented in normal temperature environments and is widely applicable to common scenarios such as the transportation of small aircraft, model airplanes, and precision equipment.

[0004] However, in practical applications, technicians have found that when the ambient temperature of the aircraft drops to a certain level, the accelerometer will exhibit zero-point drift; and as the ambient temperature continues to drop, the error value of the sensor will increase accordingly, which will cause delays or misjudgments in the trigger threshold judgment. Summary of the Invention

[0005] Therefore, this application provides a parachute ejection method to solve the problems of threshold judgment delay and misjudgment caused by the measurement error of acceleration sensor in the prior art.

[0006] To achieve the above objectives, this application provides the following technical solution: In a first aspect, a parachute ejection method includes the following steps: The current temperature and current acceleration are obtained. The current temperature is the temperature obtained by the temperature sensor from the current flight environment of the target aircraft, and the current acceleration is the acceleration obtained by the acceleration sensor from the current flight acceleration of the target aircraft. Determine whether the current temperature is greater than a temperature threshold; If so, the preset acceleration threshold will be set as the dangerous acceleration threshold. If not, the acceleration threshold is adaptively adjusted, and the adjusted acceleration threshold is determined as the dangerous acceleration threshold. Determine whether the current acceleration is greater than the dangerous acceleration threshold; if so, determine that the target aircraft is in a dangerous state. If the duration of the danger exceeds a time threshold, a parachute ejection is triggered, wherein the duration of the danger is the duration during which the target aircraft is in the dangerous state.

[0007] Optionally, the adaptive adjustment of the acceleration threshold, and the determination of the adjusted acceleration threshold as the dangerous acceleration threshold, includes: Calculate the absolute value of the difference between the current temperature and the temperature threshold; Determine whether the absolute value of the difference is less than the temperature difference threshold; If so, the acceleration threshold is adjusted first adaptively, and the acceleration threshold after the first adaptive adjustment is determined as the dangerous acceleration threshold. If not, then the acceleration threshold is adjusted in a second adaptive manner based on preset conditions, and the acceleration threshold after the second adaptive adjustment is determined as the dangerous acceleration threshold.

[0008] Optionally, the first adaptive adjustment of the acceleration threshold means that when the absolute value of the difference between the current temperature and the temperature threshold is less than the temperature difference threshold, the correction range of the dangerous acceleration threshold is controlled within a first preset small percentage range.

[0009] Optionally, the second adaptive adjustment of the acceleration threshold means that when the absolute value of the difference between the current temperature and the temperature threshold is not less than the temperature difference threshold, the correction range of the dangerous acceleration threshold is controlled within a second preset upward adjustment range.

[0010] Secondly, a parachute ejection device for performing the parachute ejection method described in any one of the above claims, comprising: The parameter acquisition module is used to collect the flight environment temperature and the aircraft's acceleration values ​​in real time. The threshold correction module is used to retrieve preset temperature thresholds, dangerous acceleration thresholds, and time thresholds, and dynamically correct the dangerous acceleration thresholds based on the comparison results between the ambient temperature and the temperature thresholds. The triggering module is used to compare the acceleration value with the dangerous acceleration threshold in the corresponding state, determine whether the duration of the out-of-state reaches the time threshold, and generate an ejection signal when the triggering condition is met. The ejection execution module is used to receive the ejection signal and drive the parachute to eject, so as to adapt to the emergency ejection requirements in low temperature environments.

[0011] Optionally, the parameter acquisition module includes a main temperature sensor, a main acceleration sensor, and independent backup temperature sensors and independent backup acceleration sensors; the independent backup temperature sensors and the independent backup acceleration sensors adopt a high-frequency wake-up mode.

[0012] Secondly, the ejection execution module is any one of a spring ejection execution module, a nitrogen ejection execution module, or a rocket ejection execution module.

[0013] Optionally, the spring ejection module is preset with a lifting preload at room temperature.

[0014] Thirdly, a parachute includes the aforementioned parachute ejection device, a canopy, and parachute lines; wherein the canopy is connected to the ejection device, and the canopy is a composite fabric made of nylon and aramid fibers; the parachute lines are made of Kevlar fibers.

[0015] Fourthly, an aircraft including the aforementioned parachute.

[0016] Compared with the prior art, this application has at least the following beneficial effects: by dynamically correcting the acceleration threshold, redundancy design of primary and backup sensors, and adaptation of multiple types of ejection execution modules, it effectively solves the problems of sensor zero-point drift and error increase at low temperatures, covers different low temperature ranges, ensures accurate and reliable parachute ejection, avoids delays or misjudgments, reduces aircraft crash losses and ground safety risks, and adapts to the emergency needs of various aircraft. Attached Figure Description

[0017] To more intuitively illustrate the prior art and this application, exemplary drawings are provided below. It should be understood that the specific shapes and structures shown in the drawings should not generally be regarded as limiting conditions for implementing this application; for example, based on the technical concept disclosed in this application and the exemplary drawings, those skilled in the art are able to easily make conventional adjustments or further optimizations to the addition / reduction / classification, specific shapes, positional relationships, connection methods, size ratios, etc. of certain units (components).

[0018] Figure 1 A schematic flowchart illustrating the parachute ejection method provided in this application embodiment; Figure 2 A schematic diagram of the adaptive adjustment method in the parachute ejection method provided in the embodiments of this application; Figure 3 This is a schematic diagram of the control structure of the parachute ejection device provided in an embodiment of this application. Detailed Implementation

[0019] The present application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0020] In the description of this application: unless otherwise stated, "a plurality of" means two or more. The terms "first," "second," "third," etc., in this application are intended to distinguish the objects referred to and do not have any special meaning in terms of technical connotation (e.g., they should not be construed as an emphasis on importance or order). Expressions such as "including," "comprising," and "having" also mean "not limited to" (certain units, components, materials, steps, etc.).

[0021] The terms used in this application, such as "upper," "lower," "left," "right," and "middle," are generally used to facilitate intuitive understanding by referring to the accompanying drawings, and are not absolute limitations on the positional relationships in the actual product. Changes in these relative positional relationships, without departing from the technical concept disclosed in this application, should also be considered within the scope of this application.

[0022] The following is combined with Figures 1 to 3 The illustrated embodiments describe the technical solution of the present invention: This application provides a parachute ejection method, including the following embodiments: Example

[0023] A parachute ejection method is implemented when the ambient temperature is above -10℃. The preset temperature threshold is -10℃, the temperature difference threshold is 10℃, the preset acceleration threshold is 1.5g, and the time threshold is 0.2s. After takeoff, the current temperature and acceleration are collected in real time. If the current temperature exceeds the temperature threshold, the preset 1.5g is directly designated as the dangerous acceleration threshold. The current acceleration is continuously monitored. When the current acceleration exceeds 1.5g and the dangerous duration exceeds 0.2s, parachute ejection is immediately triggered. This ensures accurate triggering under normal temperature conditions without sensor zero-point drift, adapting to conventional operational scenarios. Example

[0024] A parachute ejection method was developed for ambient temperatures ranging from -10°C to -20°C, with preset parameters consistent with Example 1. During flight, the current temperature and acceleration were collected in real-time. If the current temperature was found to be below a temperature threshold, the absolute value of the difference between the current temperature and the temperature threshold was calculated to be 5°C, which was less than the temperature difference threshold. A first adaptive adjustment was made to the preset acceleration threshold, controlling the correction range of the dangerous acceleration threshold within ±5%, resulting in a dangerous acceleration threshold of 1.575g. When the current acceleration exceeded 1.575g and the dangerous duration exceeded 0.2s, an ejection signal was triggered to compensate for measurement errors caused by sensor zero-point drift within this temperature range. Example

[0025] A parachute ejection method is implemented when the ambient temperature is between -20℃ and -40℃, with preset parameters remaining constant. The current temperature is collected in real-time and is below a temperature threshold. The absolute value of the difference between the current temperature and the temperature threshold is calculated to be between 10℃ and 30℃, and this absolute value is not less than the temperature difference threshold. A second adaptive adjustment is made to the preset acceleration threshold, controlling the correction range of the dangerous acceleration threshold to be increased by 15% to 25%, resulting in a dangerous acceleration threshold of 1.725g to 1.875g. When the current acceleration exceeds the corresponding adjusted dangerous acceleration threshold and the dangerous duration exceeds 0.2s, an ejection command is generated, adapting to the increased sensor detection error as the temperature decreases. Example

[0026] The parachute ejection method for ambient temperatures below -40℃ uses the same preset parameters as in the previous embodiment. The real-time collected temperature is significantly lower than the temperature threshold, with an absolute difference exceeding -30℃. The dangerous acceleration threshold is increased by 25% according to the upper limit of the second adaptive adjustment, set at 1.875g. The current acceleration and the duration of the danger are continuously monitored. When both conditions are met—current acceleration greater than 1.875g and dangerous duration exceeding 0.2s—parachute ejection is triggered to offset the cumulative error of the sensors under extreme low temperatures, ensuring emergency reliability in extreme environments.

[0027] In some embodiments, a parachute ejection device is also provided for executing the parachute ejection method described in embodiments 1 to 4. The device includes a parameter acquisition module, a threshold correction module, a judgment trigger module, and a spring ejection execution module. The parameter acquisition module includes a main temperature sensor, a main acceleration sensor, and independent backup temperature and acceleration sensors. The independent backup sensors employ a high-frequency wake-up mode to collect the flight environment temperature and aircraft acceleration values ​​in real time and transmit them to the threshold correction module. The threshold correction module retrieves preset threshold values ​​and dynamically corrects the dangerous acceleration threshold based on the comparison result between the ambient temperature and the temperature threshold. The judgment trigger module compares the acceleration value with the dangerous acceleration threshold for the corresponding state, determines whether the duration of exceeding the state reaches a time threshold, and generates an ejection signal when the condition is met. After receiving the signal, the spring ejection execution module releases the elastic potential energy of the pre-tensioned spring. This spring is pre-tensioned by 15% at room temperature to offset the elastic force attenuation at low temperatures, ejecting the parachute from the parachute compartment. The structure is simple and reliable, suitable for the lightweight requirements of micro-UAVs.

[0028] It should be noted that the main temperature sensor and main acceleration sensor may miss the optimal ejection time at low temperatures. By adding independent backup temperature sensors and independent backup acceleration sensors, and adopting a low-temperature sleep and high-frequency wake-up mode, the independent backup sensors are woken up every 10ms to sample. When the main sensor fails due to low temperature, the independent backup sensors automatically switch to perform redundancy compensation.

[0029] It should also be noted that different ejection actuators are used depending on the model of the target aircraft. Spring ejection actuators are used in micro UAVs to ensure lightweight requirements; nitrogen ejection actuators are used in industrial-grade surveying aircraft carrying precision instruments; and rocket ejection actuators are used for heavy-load emergency protection requirements of large cargo and special operation aircraft.

[0030] In some embodiments, a parachute is also provided, including the parachute ejection device described above; the canopy is connected to the parachute ejection device and is made of a composite fabric blended with nylon and aramid fibers, which has high strength tear resistance in low-temperature environments; the parachute ropes are made of Kevlar fibers and the nodes are prevented from becoming brittle through a glue-free weaving process.

[0031] In some embodiments, an aircraft is also provided, including the parachute described above.

[0032] Example Effect Verification: A 10kg-class industrial-grade surveying drone was selected, and uncontrolled fall scenarios were simulated under different temperature environments to comprehensively verify the technical effects of each example. Before verification, the preset temperature threshold was -10℃, the preset acceleration threshold was 1.5g, the time threshold was 0.2s, and the temperature difference threshold was 10℃.

[0033] In a normal temperature environment of 25℃, the drone experienced an acceleration of 2.0g after losing control, which lasted for 0.22s and triggered ejection. The parachute deployed within 1.0s, and the landing speed was 4.0m / s. In an environment of -15℃, the corrected dangerous acceleration threshold is 1.575g. When the drone crashes, the acceleration reaches 1.6g and lasts for 0.21s, triggering ejection. The deployment time is 1.1s, and the landing speed is 4.2m / s. In an environment of -30℃, the corrected dangerous acceleration threshold is 1.725g. When the acceleration reaches 1.8g and lasts for 0.2s, ejection occurs. The deployment time is 1.2s, and the landing speed is 4.3m / s. In a -50℃ environment, the corrected dangerous acceleration threshold is 1.875g. Ejection is triggered after 0.23s of acceleration reaching 1.9g, with a deployment time of 1.3s and a landing speed of 4.5m / s. Repeated tests were conducted using spring-assisted, nitrogen-assisted, and rocket-assisted ejection systems. The spring-assisted ejection system had a response time of 200ms at all temperatures, the nitrogen-assisted ejection system had a response time of 60ms, and the rocket-assisted ejection system had a response time of 50ms. All three ejection methods achieved a 100% parachute deployment success rate, with no entanglement, failure to deploy, or other malfunctions. No brittleness or breakage was observed in the canopy or parachute lines. This verifies the reliability and accuracy of the proposed technical solution across different temperature ranges and effectively solves the problem of ejection delay or misjudgment caused by sensor errors in low-temperature environments.

[0034] The technical features of the above embodiments can be combined in any way (as long as there is no contradiction in the combination of these technical features). For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described; these embodiments not explicitly written should also be considered to be within the scope of this specification.

[0035] The present application has been described in a relatively specific and detailed manner above through general descriptions and specific embodiments. It should be understood that, based on the technical concept of the present application, several conventional adjustments or further innovations can be made to these specific embodiments; however, as long as they do not depart from the technical concept of the present application, the technical solutions obtained by these conventional adjustments or further innovations also fall within the protection scope of the claims of the present application.

Claims

1. A parachute ejection method for deploying a parachute when an aircraft experiences abnormal acceleration, characterized in that, Includes the following steps: The current temperature and current acceleration are obtained. The current temperature is the temperature obtained by the temperature sensor from the current flight environment of the target aircraft, and the current acceleration is the acceleration obtained by the acceleration sensor from the current flight acceleration of the target aircraft. Determine whether the current temperature is greater than a temperature threshold; If so, the preset acceleration threshold will be set as the dangerous acceleration threshold. If not, the acceleration threshold is adaptively adjusted, and the adjusted acceleration threshold is determined as the dangerous acceleration threshold. Determine whether the current acceleration is greater than the dangerous acceleration threshold; if so, determine that the target aircraft is in a dangerous state. If the duration of the danger exceeds a time threshold, a parachute ejection is triggered, wherein the duration of the danger is the duration during which the target aircraft is in the dangerous state.

2. The parachute ejection method according to claim 1, characterized in that, The adaptive adjustment of the acceleration threshold, and the determination of the adjusted acceleration threshold as the dangerous acceleration threshold, includes: Calculate the absolute value of the difference between the current temperature and the temperature threshold; Determine whether the absolute value of the difference is less than the temperature difference threshold; If so, the acceleration threshold is adjusted first adaptively, and the acceleration threshold after the first adaptive adjustment is determined as the dangerous acceleration threshold. If not, then the acceleration threshold is adjusted in a second adaptive manner based on preset conditions, and the acceleration threshold after the second adaptive adjustment is determined as the dangerous acceleration threshold.

3. The parachute ejection method according to claim 2, characterized in that, The first adaptive adjustment of the acceleration threshold means that when the absolute value of the difference between the current temperature and the temperature threshold is less than the temperature difference threshold, the correction range of the dangerous acceleration threshold is controlled within a first preset small percentage range.

4. The parachute ejection method according to claim 2, characterized in that, The second adaptive adjustment of the acceleration threshold refers to: when the absolute value of the difference between the current temperature and the temperature threshold is not less than the temperature difference threshold, the correction range of the dangerous acceleration threshold is controlled within a second preset upward adjustment range.

5. A parachute ejection device, characterized in that, A parachute ejection method for performing any one of claims 1-4 includes: The parameter acquisition module is used to collect the flight environment temperature and the aircraft's acceleration values ​​in real time. The threshold correction module is used to retrieve preset temperature thresholds, dangerous acceleration thresholds, and time thresholds, and dynamically correct the dangerous acceleration thresholds based on the comparison results between the ambient temperature and the temperature thresholds. The triggering module is used to compare the acceleration value with the dangerous acceleration threshold in the corresponding state, determine whether the duration of the exceeding state reaches the time threshold, and generate an ejection signal when the triggering condition is met. The ejection execution module is used to receive the ejection signal and drive the parachute to eject, so as to adapt to the emergency ejection requirements in low temperature environments.

6. The parachute ejection device according to claim 5, characterized in that, The parameter acquisition module includes a main temperature sensor, a main acceleration sensor, and independent backup temperature sensors and independent backup acceleration sensors; the independent backup temperature sensors and independent backup acceleration sensors adopt a high-frequency wake-up mode.

7. The parachute ejection device according to claim 5, characterized in that, The ejection execution module can be any one of a spring ejection execution module, a nitrogen ejection execution module, or a rocket ejection execution module.

8. The parachute ejection device according to claim 7, characterized in that, The spring ejection module has a preset lifting preload at room temperature.

9. A parachute, characterized in that, include: Parachute ejection device as described in claims 5-8; A canopy, attached to the ejection device, wherein the canopy is a composite fabric made of nylon and aramid fibers; The paracord is made of Kevlar fiber.

10. An aircraft, characterized in that, Includes the parachute as described in claim 9.

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