Aerial parachute opener tester calibration system, method, and media
By simulating the static pressure source generation and data measurement of the actual parachute opening process, the problems of altitude output, static pressure stability and sensor error in the calibration of the aviation parachute opener tester were solved, achieving accurate calibration of altitude and altitude change rate, and improving measurement accuracy and safety.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- NAVAL AVIATION UNIV
- Filing Date
- 2025-07-25
- Publication Date
- 2026-07-21
AI Technical Summary
Existing aircraft parachute deployer test equipment fails to comprehensively test altitude output performance, static pressure gas source stability, sensor hysteresis error, and time measurement error during calibration, affecting the measurement accuracy and safety of the parachute deployer.
Employing a programmable altitude simulation module, a multi-source redundant clock module, and a data measurement module, the system generates a static pressure source to simulate the actual parachute opening process, collects air pressure changes, adjusts the flow meter, calculates the measurement difference, and adjusts the test instrument algorithm parameters to achieve accurate calibration of altitude and altitude change rate.
This improves the measurement accuracy of the aircraft parachute deployer tester, ensuring its safety and reliability in different environments and meeting the requirements for traceability of measurement values.
Smart Images
Figure CN122192717B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aviation parachute deployer technology, specifically relating to an aviation parachute deployer tester calibration system, method, and medium. Background Technology
[0002] The parachute deployer is the core control device in an aircraft parachute system. It is primarily used to trigger parachute deployment at specific altitudes, speeds, or under emergency conditions, ensuring the safe landing of manned spacecraft, drones, or airdropped cargo. To ensure the deployer functions correctly, testing equipment is used for simulation testing to ensure its relevant technical indicators meet pre-set requirements. As a testing device, the deployer test equipment requires regular calibration to ensure accurate performance indicators and meet traceability requirements.
[0003] Currently, the following problems exist in the periodic metrological calibration process of the aircraft parachute deployer test instrument: 1) Only the height measurement function of the tester was completed; the height output performance was not tested. When checking the height triggering performance of the parachute opener, the tester needs to generate a static pressure air source corresponding to the simulated height value and supply it to the opener. By simulating different heights, the tester's height triggering performance can be checked to see if it is normal. Without checking the height output performance, it is impossible to determine whether the static pressure air source output by the tester is stable and whether it can effectively test the height triggering performance of the opener.
[0004] 2) The height change rate parameter of the test apparatus was not detected, making it impossible to determine whether the static pressure change rate of the static pressure source output during the test was normal. The parachute opening trigger function at the extreme speed of the parachute opener is a very important indicator; inaccurate detection will endanger the safety of personnel and equipment.
[0005] 3) Only the forward stroke of the tester's height and airspeed parameters was tested, but the reverse stroke was not tested. Therefore, it is impossible to determine whether there is hysteresis error in the built-in sensors and data acquisition and conversion circuit module of the tester, and whether it will affect the overall performance of the tester.
[0006] 4) Using an electric stopwatch calibrator to calibrate the time parameters of the tester introduces a large time measurement error, which affects the accuracy of the static pressure change rate output measurement. Summary of the Invention
[0007] In view of the above-mentioned shortcomings of the prior art, the present invention provides an aviation parachute tester calibration system, method and medium to solve the above-mentioned technical problems.
[0008] In a first aspect, the present invention provides a calibration system for an aircraft parachute deployer tester, comprising: a programmable altitude simulation module, a multi-source redundant clock module, a data measurement module, and a control module; The control module is configured to, during the pre-calibration preparation phase, acquire the requirements of the calibration task and the simulation of the actual parachute opening scenario, generate calibration altitude control instruction information, and acquire calibration time synchronization instructions. The multi-source redundant clock module is configured to achieve time synchronization of all modules during the calibration process based on time synchronization instructions; The programmable altitude simulation module is configured to connect to the control module, adjust the dual-flow proportional flow meter to generate a static pressure source based on the calibration altitude control command information, simulate the real parachute opening process based on the static pressure source, collect the air pressure value changes during the simulated real parachute opening process, and adjust the static pressure source in conjunction with the dual-flow proportional flow meter based on the air pressure value changes. The data measurement module is configured to measure the static pressure value output by the programmable altitude simulation module in simulating the actual parachute opening process, and control the module to convert the static pressure value into a theoretical altitude value or a theoretical altitude change rate value. The aircraft parachute deployer tester is connected to the control module and the programmable altitude simulation module respectively. The aircraft parachute deployer tester works under static pressure source, and the control module obtains the current altitude value or altitude change rate value displayed by the aircraft parachute deployer tester. The control module calculates the measurement difference between the height value and the theoretical height value, or the height change rate value and the theoretical height change rate value, and adjusts the internal algorithm parameters or calibration curve of the tester based on the measurement difference.
[0009] In one optional implementation, the programmable height simulation module includes: a sensor unit, an embedded system unit, and a dual-flow proportional flow meter; The sensor unit collects air pressure values and air pressure change values during the simulated real parachute opening process. These values are then converted into altitude parameters and altitude change rate parameters by the built-in pressure / altitude conversion module and pressure change value / altitude change rate module. Feedback signals are generated based on these altitude parameters and altitude change rate parameters. The embedded system unit calculates the static pressure source command to be output based on the calibration control command and the feedback signal from the sensor unit. The air generator is equipped with a servo motor, a negative pressure generator, and a pressure vessel. The servo motor drives the rotating machinery inside the negative pressure generator to work through calibration control commands and feedback signals from the sensor unit, generating a negative pressure air source. The air source is output to or stopped by the programmable solenoid valve. The dual-flow-control proportional flow meter is connected to the volume generator and adjusts the negative pressure gas source to obtain the required static pressure source based on the static pressure source command output.
[0010] In one alternative implementation, the inlet and outlet of the flow meter are each equipped with a proportional control valve that can automatically adjust its opening. The opening of the proportional valve is adjusted based on the static pressure source command to be output, so as to regulate the negative source air pressure passing through and generate the required static pressure source.
[0011] In an optional implementation, a multi-source redundant clock module provides a master clock signal via a GPS / BeiDou receiver and a rubidium atomic clock as a backup clock, providing a synchronization time reference for the programmable altitude simulation module, the aircraft parachute tester, and the control module.
[0012] In an optional implementation, the multi-source redundant clock module employs a Kalman filter algorithm to fuse multi-source signals from the GPS / BeiDou receiver and the rubidium atomic clock.
[0013] In an optional implementation, the data measurement module also measures the ambient temperature of the aircraft parachute tester in real time, and the control module corrects the static pressure value based on the temperature compensation algorithm and the real-time ambient temperature, converting the corrected static pressure value into a theoretical altitude value or a theoretical altitude change rate value.
[0014] Secondly, the present invention provides a calibration method for an aircraft parachute deployer tester. When the above system is implemented, the aircraft parachute deployer tester calibration method is performed, and the method includes: During the pre-calibration preparation phase, the requirements for calibration tasks and simulated actual parachute opening scenarios are obtained, calibration altitude control instruction information is generated, and calibration time synchronization instructions are obtained. The static pressure source is generated by adjusting the dual-flow proportional flow meter based on the calibration height control command information. The static pressure source is used to simulate the real umbrella opening process. The air pressure value changes during the simulated real umbrella opening process are collected. The static pressure source is adjusted in combination with the dual-flow proportional flow meter based on the air pressure value changes. The static pressure value output during the simulated actual parachute opening process is measured and converted into a theoretical altitude value or a theoretical altitude change rate value. The aircraft parachute opener tester operates under a static pressure source and displays the current altitude value or altitude change rate value. Calculate the measurement difference between the height value and the theoretical height value, or the height change rate value and the theoretical height change rate value, and adjust the internal algorithm parameters or calibration curve of the tester based on the measurement difference.
[0015] In one optional implementation, air pressure values and air pressure change values are collected during the simulated real parachute opening process. These values are then converted into altitude parameters and altitude change rate parameters by the built-in pressure / altitude conversion module and pressure change value / altitude change rate module. Feedback signals are then generated based on the altitude parameters and altitude change rate parameters. Based on the calibration control command and the feedback signal from the sensor unit, the static pressure source command to be output is calculated. The negative pressure generator is driven by calibration control commands and feedback signals to operate the rotating machinery inside, thereby generating a negative pressure air source. The required static pressure source is obtained by adjusting the negative pressure air source based on the static pressure source command output.
[0016] In an optional implementation, the actual umbrella opening process is simulated based on a static pressure source, specifically including: The parachute deployment process is broken down into three stages: free fall, canopy inflation, and stable descent. In each stage, changes in the static pressure source simulate the altitude and rate of altitude change during actual deployment. During the free fall phase, the rate of change of height increases linearly, and the acceleration is close to the acceleration due to gravity. The parachute canopy inflation section uses an exponential function to simulate the inflection point of the rate of change of altitude caused by a sudden increase in drag. The rate of change of altitude during the steady descent phase remains constant.
[0017] Thirdly, a computer-readable storage medium is provided, wherein instructions are stored therein, which, when executed on a computer, cause the computer to perform the methods described in the above aspects.
[0018] The beneficial effects of this invention are that the calibration method, system, and medium for the aircraft parachute deployer tester provided by this invention, in the preparation stage, the control module acquires the calibration task, scenario requirements, and time synchronization instructions; the multi-source redundant clock module achieves time synchronization; the programmable altitude simulation module collects data based on instructions and generates a static pressure source to simulate the real parachute deployment process; the data measurement module measures the static pressure value and converts it into the theoretical altitude or altitude change rate value; the control module acquires the tester's displayed value and calculates the measurement error; and then adjusts the tester's internal algorithm parameters or calibration curve based on the error, which can effectively calibrate the aircraft parachute deployer tester and improve its measurement accuracy.
[0019] Furthermore, the design principle of this invention is reliable, the structure is simple, and it has a very wide range of application prospects. Attached Figure Description
[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0021] Figure 1 This is a schematic block diagram of an aviation parachute deployer tester calibration system according to an embodiment of the present invention.
[0022] Figure 2 This is a schematic diagram of the cable connection of an aviation parachute tester calibration system according to an embodiment of the present invention.
[0023] Figure 3 This is a schematic flowchart of a calibration method for an aircraft parachute deployer tester according to an embodiment of the present invention.
[0024] Figure 4This is a schematic diagram of the structure of a terminal provided in an embodiment of the present invention. Detailed Implementation
[0025] To enable those skilled in the art to better understand the technical solutions of this invention, the technical solutions of the embodiments of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this invention, and not all embodiments. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of this invention.
[0026] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention.
[0027] The aircraft parachute deployer calibration system may include multiple functional modules composed of computer program segments. The computer programs of each program segment in the aircraft parachute deployer calibration system may be stored in the memory of a computer device and executed by at least one processor to perform the function of calibrating the aircraft parachute deployer.
[0028] In this embodiment, the aircraft parachute deployer calibration system can be divided into multiple functional modules according to its functions, such as... Figure 1 As shown. The system's functional modules may include: a programmable high-simulation module, a multi-source redundant clock module, a data measurement module, and a control module. The module referred to in this invention is a series of computer program segments that can be executed by at least one processor and perform a fixed function, stored in memory. In this embodiment, the functions of each module will be detailed in subsequent embodiments.
[0029] The control module is configured to, during the pre-calibration preparation phase, acquire the requirements of the calibration task and the simulation of the actual parachute opening scenario, generate calibration altitude control instruction information, and acquire calibration time synchronization instructions. The multi-source redundant clock module is configured to achieve time synchronization of all modules during the calibration process based on time synchronization instructions; The programmable altitude simulation module is configured to connect to the control module, adjust the dual-flow proportional flow meter to generate a static pressure source based on the calibration altitude control command information, simulate the real parachute opening process based on the static pressure source, collect the air pressure value changes during the simulated real parachute opening process, and adjust the static pressure source in conjunction with the dual-flow proportional flow meter based on the air pressure value changes. The data measurement module is configured to measure the static pressure value output by the programmable altitude simulation module in simulating the actual parachute opening process, and control the module to convert the static pressure value into a theoretical altitude value or a theoretical altitude change rate value. The aircraft parachute deployer tester is connected to the control module and the programmable altitude simulation module respectively. The aircraft parachute deployer tester works under static pressure source, and the control module obtains the current altitude value or altitude change rate value displayed by the aircraft parachute deployer tester. The control module calculates the measurement difference between the height value and the theoretical height value, or the height change rate value and the theoretical height change rate value, and adjusts the internal algorithm parameters or calibration curve of the tester based on the measurement difference.
[0030] Optionally, as an embodiment of the present invention, refer to Figure 2 The programmable height simulation module uses a programmable height simulation device, the multi-source redundant clock module uses a multi-source redundant clock system, the data measurement module uses a data measuring instrument, and the control module uses a control terminal. The time synchronization cable connects the multi-source redundant clock system to the programmable high-precision analog device, data measuring instrument, and control terminal; The communication bus connects the programmable altitude simulation device with a multi-source redundant clock system, data measuring instruments, control terminals, and an aircraft parachute tester. The static pressure hose connects the programmable altitude simulation device, data measuring instrument, and aircraft parachute tester.
[0031] Optionally, as an embodiment of the present invention, the programmable height simulation module includes: a sensor unit, an embedded system unit, and a dual-flow-control proportional flow meter; The sensor unit collects air pressure values and air pressure changes during the simulated real parachute opening process. These values are then converted into altitude parameters and altitude change rate parameters by the built-in pressure / altitude conversion module and pressure change value / altitude change rate module. Feedback signals are generated based on these altitude parameters and altitude change rate parameters, with the error range controlled within ±0.1%. The embedded system unit calculates the static pressure source command to be output based on the calibration control command and the feedback signal from the sensor unit. The air generator is equipped with a servo motor, a negative pressure generator, and a pressure vessel. The servo motor drives the rotating machinery inside the negative pressure generator to work through calibration control commands and feedback signals from the sensor unit, generating a negative pressure air source. The air source is output to or stopped by the programmable solenoid valve, with a response time of ≤10ms. The dual-flow-control proportional flow meter is connected to the volume generator and adjusts the negative pressure gas source to obtain the required static pressure source based on the static pressure source command output.
[0032] Optionally, as an embodiment of the present invention, the key technologies employed in the programmable height simulation module include: (1) Dynamic height closed-loop control a) Feedback adjustment mechanism The actuator output is dynamically adjusted by comparing the preset height with the actual measured value in real time using a PID controller. A feedforward compensation algorithm is introduced to cope with sudden load changes and improve the system's immunity to disturbances.
[0033] b) Multimodal switching logic Based on the characteristics of the parachute opening phase (such as free fall, canopy inflation, and stable descent), different control parameter groups are set to achieve a smooth transition.
[0034] (2) Dynamic testing function Dynamic testing is achieved through programmable parameter configuration, supporting a customizable height change rate range (0-100m / s); and providing various dynamic test templates such as continuous mode, pulse mode, and step mode.
[0035] (3) Pre-set mathematical model of height curve a) Dynamic modeling of conventional parachute opening process Establish a differential equation based on Newton's second law:
[0036] in: For height, For quality, The drag coefficient, For parachute tension.
[0037] b) The programmable high-resolution simulation module employs a piecewise curve generation algorithm based on the conventional model. The parachute opening process is broken down into three stages: Free fall phase: The rate of change of height increases linearly, and the acceleration is close to the acceleration due to gravity; Parachute inflation section: An exponential function is used to simulate the inflection point of the rate of change of altitude caused by a sudden increase in drag; Stable descent phase: The rate of change in altitude remains constant.
[0038] Optionally, as an embodiment of the present invention, the multi-source redundant clock module has time synchronization and redundancy switching functions. The system provides a master clock signal through a GPS / BeiDou receiver (positioning accuracy ±10ns) and a rubidium atomic clock (frequency stability ≤1E-12 / day) as a backup clock, providing a synchronized time reference for the programmable altitude simulation device, the aircraft parachute tester, and the control terminal, achieving time synchronization and accuracy during the test. The master-backup clock switching delay is ≤1μs, ensuring the continuity of the time signal under extreme environments.
[0039] Optionally, as an embodiment of the present invention, the multi-source redundant clock module employs a Kalman filter algorithm to fuse multi-source signals from GPS / BeiDou receivers and rubidium atomic clocks, and the FPGA implements real-time processing and seamless switching between primary and backup clocks, specifically including: 1. System Modeling and Initialization 1.1 Definition of State Vector The definition includes clock skew (Δt) and drift rate (Δt). Two-dimensional state vector:
[0040] 1.2 State transition matrix design Based on the dynamic characteristics of clock skew, construct a short state transition matrix:
[0041] Where T is the synchronization period (e.g., 1ms), which reflects the linear relationship between state changes at adjacent moments.
[0042] 1.3 Initial Parameter Settings Initial state: (Assuming no initial bias) Initial covariance:
[0043] Process noise matrix:
[0044] in, Calibration was performed using the Allen variance test of the crystal oscillator.
[0045] 2. Forecasting Phase 2.1 State Prediction Calculate the current predicted value based on the state estimate from the previous time step:
[0046] For example, when T=1ms, the predicted clock skew value is:
[0047] This step enables dynamic extrapolation.
[0048] 2.2 Covariance Prediction Update the error covariance matrix:
[0049] This formula quantifies the impact of process noise on estimation uncertainty.
[0050] 3. Observation Phase 3.1 Observation Generation The timestamp difference is obtained using the round-trip time (RTT) measurement method:
[0051] Where and TOArx are the transmission / reception timestamps, respectively, and Vk is the observation noise.
[0052] 3.2 Definition of Observation Matrix The observation matrix H measures only clock deviation:
[0053] The observation equation simplifies to:
[0054] The noise variance R is determined by the signal propagation delay jitter and the noise error.
[0055] 4. Update Phase 4.1 Kalman Gain Calculation The gain is calculated based on the predicted covariance and observation noise:
[0056] The gain matrix has a dimension of 2x1 and determines the confidence weights of the observations.
[0057] 4.2 Status Update Corrected forecast:
[0058] For example, clock difference correction:
[0059] in, This is the first element of the gain matrix.
[0060] 4.3 Covariance Update Update error covariance:
[0061] This step reduces estimation uncertainty.
[0062] 5. Dynamic parameter calibration 5.1 Adaptive Adjustment of Process Noise Q is dynamically updated based on crystal oscillator stability:
[0063] in, This is a window for historical drift rate data.
[0064] 5.2 Online estimation of observation noise R is calculated using the sliding window method:
[0065] β is the forgetting factor (usually taken as 0.95).
[0066] 6. Termination condition: The covariance matrix converges. .
[0067] Optionally, as an embodiment of the present invention, the data measuring instrument is equipped with a multi-channel high-precision ADC acquisition module to complete the synchronous acquisition and data preprocessing of parameters such as static pressure, temperature and time, with a sampling rate ≥1kHz, and generates calibration curves and error results in real time, and transmits them to the control terminal through the data bus.
[0068] Optionally, as an embodiment of the present invention, the control terminal is built by an embedded system and can run detection software to perform error analysis: generate calibration curves by least squares method, calculate indication error and repeatability; and has a built-in storage module to support data management functions such as historical data query and automatic generation of calibration reports.
[0069] Optionally, as an embodiment of the present invention, the specific calibration process is as follows: 1. Time synchronization 1.1.1 Turn on the power to the programmable altitude simulation device, multi-source redundant clock system, data measuring instrument, control terminal, and aircraft parachute tester in sequence, and preheat for more than 1 hour; 1.1.2 On the main interface of the control terminal's programmable control software, select and enter the "Time Synchronization" interface to begin the time synchronization operation. The GPS / BeiDou time synchronization multi-source redundant clock system compares and calibrates the time reference chip of the programmable altitude simulation device, the multi-source redundant clock system, the data measuring instrument, and the control terminal to complete the time reference synchronization operation; 1.1.3 After the above steps are completed, the software will automatically return to the main interface and indicate that the time base synchronization is complete.
[0070] 2. Altitude parameter calibration 2.1 Altitude parameter measurement calibration 2.1.1 On the main interface of the control terminal's programmable control software, select and enter the "Altitude Parameter Measurement Calibration" interface; 2.1.2 The aircraft parachute deployer tester is in the "Altitude 1" display interface and is in measurement mode; 2.1.3 Enter the target value "25000m" and click the "Confirm" button; 2.1.4 The control terminal acquires the ambient temperature through a data measuring instrument and inputs the real-time temperature and the "2500m" command to the programmable altitude simulation device; 2.1.5 The programmable altitude simulation device generates a static pressure air source corresponding to an altitude of 2500m based on the input command, and sends a message to the control terminal after the air source pressure stabilizes; 2.1.6 The control terminal sequentially records the static pressure value of the data measuring instrument via the data bus and converts it into an altitude value, compares it with the altitude value displayed by the aircraft parachute tester, and calculates its measurement error; 2.1.7 Repeat steps “2.1.3” to “2.1.6” to complete the 20000m section sequentially. Measurement calibration at 15000m, 10000m, 8000m, 7000m, 6000m, 5000m, 4000m, 3000m, 2000m, 1000m, 500m, and 0m; 2.1.8 Repeat steps “2.1.3” to “2.1.7” to complete the measurement calibration at 0m, 500m, 1000m, 2000m, 3000m, 4000m, 5000m, 6000m, 7000m, 8000m, 9000m, 10000m, 15000m, 20000m, and 25000m. 2.1.9 After calibration, the control terminal returns to the main software interface.
[0071] 2.2 Altitude parameter control calibration 2.2.1 On the main interface of the control terminal's programmable control software, select and enter the "Altitude Parameter Control Calibration" interface; 2.2.2 The aircraft parachute deployer test device is displayed on the "Altitude 1" screen and is in control mode; 2.2.3 Start the vacuum pressure pump of the aircraft parachute tester and adjust the static pressure input regulating valve to keep the "Altitude 1" display showing "25000m" stable. 2.2.4 The control terminal sequentially records the real-time temperature and static pressure values of the data measuring instrument via the data bus, converts them into actual altitude values and the altitude values displayed by the aircraft parachute tester after temperature compensation, and calculates the measurement error. 2.2.5 Repeat steps “2.2.3” to “2.2.4” to complete the 20000m section sequentially. Measurement calibration at 15000m, 10000m, 8000m, 7000m, 6000m, 5000m, 4000m, 3000m, 2000m, 1000m, 500m, and 0m; 2.2.6 Repeat steps “2.2.3” to “2.2.5” to complete the measurement calibration at 0m, 500m, 1000m, 2000m, 3000m, 4000m, 5000m, 6000m, 7000m, 8000m, 9000m, 10000m, 15000m, 20000m, and 25000m. 2.2.7 After calibration, the control terminal returns to the main software interface.
[0072] 3. Height Change Rate Parameter Calibration 3.1 Measurement Calibration of Height Change Rate 3.1.1 On the main interface of the control terminal programmable software, select and enter the "Height Change Rate Parameter Measurement Calibration" interface; 3.1.2 The aircraft parachute deployer tester is in the "Speed 1" display interface and is in measurement mode; 3.1.3 Enter the target value "-100m / s" and click the "Confirm" button; 3.1.4 The control terminal acquires the ambient temperature through a data measuring instrument and inputs the real-time temperature and the "-100m / s" command to the programmable altitude simulation device; 3.1.5 The programmable altitude simulation device generates a static pressure change value corresponding to an altitude change rate of "-100m / s" according to the input command, and sends a message to the control terminal after the static pressure change value of the air source stabilizes. 3.1.6 The control terminal sequentially records the static pressure change value of the data measuring instrument via the data bus and converts it into the altitude change rate and the altitude change rate displayed by the aircraft parachute tester, and calculates its measurement error; 3.1.7 Repeat steps “3.1.3” to “3.1.6” to complete the measurement calibration for -80m / s, -60m / s, -40m / s, -35m / s, -25m / s and -20m / s in sequence; 3.1.8 Repeat steps “3.1.3” to “3.1.7” to complete the measurement calibration in sequence at -20m / s, -25m / s, -35m / s, -40m / s, -60m / s, -80m / s, and -100m / s. 3.1.9 After calibration, the control terminal returns to the main software interface.
[0073] 3.2 High-rate-of-change control calibration 3.2.1 On the main interface of the control terminal programmable software, select and enter the "Height Change Rate Parameter Control Calibration" interface; 3.2.2 The aircraft parachute deployer tester is in the "Speed 1" display interface and in control mode; 3.2.3 Start the vacuum pressure pump of the aircraft parachute deployer test apparatus, and adjust the static pressure input regulating valve to ensure that the "Speed 1" display shows "-100m / s" and remains stable. 3.2.4 The control terminal sequentially records the real-time temperature and static pressure values of the data measuring instrument via the data bus, converts them into actual altitude change values and speed values displayed by the aircraft parachute tester after temperature compensation, and calculates the measurement error. 3.2.5 Repeat steps “2.2.3” to “2.2.4” to complete the control calibration for -80m / s, -60m / s, -40m / s, -35m / s, -25m / s and -20m / s in sequence; 3.2.6 Repeat steps “2.2.3” to “2.2.5” to complete the control calibration for -20m / s, -25m / s, -35m / s, -40m / s, -60m / s, -80m / s, and -100m / s; 3.2.7 After calibration, the control terminal returns to the main software interface.
[0074] The calibration method for the aircraft parachute deployer tester provided in this embodiment of the invention is executed by computer equipment, and correspondingly, the aircraft parachute deployer tester calibration system runs on the computer equipment.
[0075] Figure 3 This is a schematic flowchart of a calibration method for an aircraft parachute deployer tester according to an embodiment of the present invention. Figure 3 The execution entity is the aforementioned aircraft parachute deployer tester calibration system. Depending on different requirements, the order of the steps in this flowchart can be changed, and some steps can be omitted.
[0076] like Figure 3 As shown, the method includes: Step S1: In the pre-calibration preparation stage, obtain the requirements of the calibration task and the simulation of the actual parachute opening scenario, generate calibration altitude control instruction information, and obtain the calibration time synchronization instruction. Before the calibration officially begins, operators interact with the calibration task management system via the control module to obtain detailed calibration task information, such as the specific calibration items and accuracy requirements. Simultaneously, based on different actual parachute deployment scenarios, such as varying flight altitudes and speeds, the system analyzes the requirements for simulating real-world parachute deployment. The control module then processes this information to generate calibration instructions. Furthermore, the control module establishes a communication connection with the multi-source redundant clock module to obtain time synchronization instructions for calibration. Upon receiving these instructions, the multi-source redundant clock module adjusts the clocks of all modules in the calibration system using its internal high-precision clock source and time synchronization algorithm to ensure time consistency across all modules.
[0077] By accurately acquiring calibration tasks and scenario requirements to generate instructions, and achieving time synchronization, a foundation is laid for subsequent calibration work, ensuring that the calibration process is carried out in accordance with predetermined requirements and at a unified time, thereby improving the accuracy and reliability of calibration.
[0078] Step S2: Based on the calibration height control command information, adjust the dual-flow proportional flow meter to generate a static pressure source, simulate the actual umbrella opening process based on the static pressure source, collect the air pressure value changes during the simulated actual umbrella opening process, and adjust the static pressure source in combination with the dual-flow proportional flow meter based on the air pressure value changes. After receiving calibration control commands from the control module, the programmable altitude simulation module uses its internal high-precision barometric pressure sensor to collect ambient air pressure and pressure changes at specific time intervals. Then, based on the collected pressure data, it calculates the parameters of the dual-flow-controlled proportional flowmeter that need adjustment using an algorithm, and precisely adjusts it to allow the flowmeter to output gas at a specific pressure and flow rate, thereby generating a static pressure source that meets the requirements of simulating a real umbrella opening process.
[0079] By collecting air pressure data and adjusting the dual-flow proportional flowmeter to generate a static pressure source, the air pressure environment during the parachute opening process can be realistically simulated, providing test conditions close to actual conditions for subsequent accurate calibration of the aircraft parachute opener test apparatus.
[0080] Step S3: Measure the static pressure value output during the simulated actual parachute opening process, and convert the static pressure value into a theoretical altitude value or a theoretical altitude change rate value; the aircraft parachute opener tester operates under static pressure and displays the current altitude value or altitude change rate value; The data measurement module uses a high-precision pressure sensor to measure the static pressure value output by the programmable altitude simulation module during the simulated actual parachute opening process. Then, according to a pre-set formula or algorithm for converting air pressure to altitude, the measured static pressure value is converted into a theoretical altitude value or a theoretical altitude change rate value. Simultaneously, the aircraft parachute opener test apparatus is placed in the generated static pressure source environment. Sensors inside the test apparatus detect static pressure changes in real time and convert them into altitude values or altitude change rate values, which are then displayed on the test apparatus's screen.
[0081] It enables the measurement and conversion of static pressure values during simulated umbrella opening, as well as the acquisition of values displayed by the testing instrument, providing data support for subsequent calculation of measurement errors and helping to evaluate the measurement accuracy of the testing instrument.
[0082] Step S4: Calculate the measurement difference between the height value and the theoretical height value or the height change rate value and the theoretical height change rate value, and adjust the internal algorithm parameters or calibration curve of the tester based on the measurement difference.
[0083] The control module compares the current altitude or altitude change rate displayed by the aircraft parachute deployer tester with the theoretical altitude or theoretical altitude change rate calculated by the data measurement module, and calculates the measurement error between the two through mathematical operations. Then, based on a pre-set error adjustment strategy and algorithm, the module adjusts the algorithm parameters or calibration curves within the tester, enabling it to more accurately reflect the actual altitude or altitude change in subsequent measurements.
[0084] By calculating the measurement error and adjusting the internal parameters or calibration curve of the tester, the measurement accuracy of the aircraft parachute tester can be effectively improved, ensuring that it provides reliable measurement data in actual use.
[0085] Optionally, as an embodiment of the present invention, the air pressure value and air pressure change value during the simulated real parachute opening process are collected, and converted into height parameters and height change rate parameters through the built-in pressure / altitude conversion module and pressure change value / altitude change rate module, and a feedback signal is generated based on the height parameters and height change rate parameters. Based on the calibration control command and the feedback signal from the sensor unit, the static pressure source command to be output is calculated. The negative pressure generator is driven by calibration control commands and feedback signals to operate the rotating machinery inside, thereby generating a negative pressure air source. The required static pressure source is obtained by adjusting the negative pressure air source based on the static pressure source command output.
[0086] Optionally, as an embodiment of the present invention, simulating the actual umbrella opening process based on a static pressure source specifically includes: The parachute deployment process is broken down into three stages: free fall, canopy inflation, and stable descent. In each stage, changes in the static pressure source simulate the altitude and rate of altitude change during actual deployment. During the free fall phase, the rate of change of height increases linearly, and the acceleration is close to the acceleration due to gravity. The parachute canopy inflation section uses an exponential function to simulate the inflection point of the rate of change of altitude caused by a sudden increase in drag. The rate of change of altitude during the steady descent phase remains constant.
[0087] Figure 4 This is a schematic diagram of a terminal provided in an embodiment of the present invention. The terminal can be used to execute the method for calibrating an aviation parachute tester provided in an embodiment of the present invention.
[0088] The terminal may include a processor, a memory, and a communication unit. These components communicate via one or more buses. Those skilled in the art will understand that the server structure shown in the figure does not constitute a limitation of the present invention. It may be a bus topology or a star topology, and may include more or fewer components than shown, or combine certain components, or have different component arrangements.
[0089] The memory can be used to store the processor's execution instructions. The memory can be implemented using any type of volatile or non-volatile storage terminal or a combination thereof, such as static random access memory (SRAM), electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic storage, flash memory, magnetic disk, or optical disk. When the execution instructions in the memory are executed by the processor, the terminal is able to perform some or all of the steps in the above method embodiments.
[0090] The processor is the control center of the storage terminal, connecting various parts of the electronic terminal via various interfaces and lines. It executes software programs and / or modules stored in the memory, and calls data stored in the memory to perform various functions and / or process data. The processor can be composed of integrated circuits (ICs), such as a single packaged IC or multiple packaged ICs with the same or different functions connected together. For example, the processor may consist only of a central processing unit (CPU). In this embodiment of the invention, the CPU may have a single processing core or include multiple processing cores.
[0091] A communication unit is used to establish a communication channel, enabling the storage terminal to communicate with other terminals. It receives user data sent by other terminals or sends user data to other terminals.
[0092] The present invention also provides a computer storage medium, wherein the computer storage medium may store a program, which, when executed, may include some or all of the steps provided in the embodiments of the present invention. The storage medium may be a magnetic disk, an optical disk, read-only memory (ROM), or random access memory (RAM), etc.
[0093] Those skilled in the art will clearly understand that the techniques in the embodiments of the present invention can be implemented using software plus necessary general-purpose hardware platforms. Based on this understanding, the technical solutions in the embodiments of the present invention, or the parts that contribute to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium such as a USB flash drive, mobile hard drive, read-only memory (ROM), random access memory (RAM), magnetic disk, or optical disk, or other media capable of storing program code. It includes several instructions to cause a computer terminal (which may be a personal computer, server, or a second terminal, network terminal, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention.
[0094] The same or similar parts between the various embodiments in this specification can be referred to mutually. In particular, the terminal embodiments are basically similar to the method embodiments, so the description is relatively simple, and the relevant parts can be referred to the description in the method embodiments.
[0095] In the embodiments provided by this invention, it should be understood that the disclosed systems and methods can be implemented in other ways. For example, the system embodiments described above are merely illustrative. For instance, the division of modules is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple modules or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some interfaces; the indirect coupling or communication connection between systems or modules may be electrical, mechanical, or other forms.
[0096] The modules described as separate components may or may not be physically separate. The components shown as modules may or may not be physical modules; that is, they may be located in one place or distributed across multiple network modules. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs.
[0097] In addition, the functional modules in the various embodiments of the present invention can be integrated into one processing module, or each module can exist physically separately, or two or more modules can be integrated into one module.
[0098] Although the present invention has been described in detail with reference to the accompanying drawings and preferred embodiments, the present invention is not limited thereto. Various equivalent modifications or substitutions can be made to the embodiments of the present invention by those skilled in the art without departing from the spirit and essence of the invention, and such modifications or substitutions should all be within the scope of the present invention. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should also be covered within the protection scope of the present invention.
Claims
1. A calibration system for an aircraft parachute deployer tester, characterized in that, include: Programmable high-simulation module, multi-source redundant clock module, data measurement module and control module; The control module is configured to, during the pre-calibration preparation phase, acquire the requirements of the calibration task and the simulation of the actual parachute opening scenario, generate calibration altitude control instruction information, and acquire calibration time synchronization instructions. The multi-source redundant clock module is configured to achieve time synchronization of all modules during the calibration process based on time synchronization instructions; The programmable altitude simulation module is configured to connect to the control module, adjust the dual-flow proportional flow meter to generate a static pressure source based on the calibration altitude control command information, simulate the real parachute opening process based on the static pressure source, collect the air pressure value changes during the simulated real parachute opening process, and adjust the static pressure source in conjunction with the dual-flow proportional flow meter based on the air pressure value changes. The programmable height analog module includes: a sensor unit, an embedded system unit, and a dual-flow proportional flow meter; The sensor unit collects air pressure values and air pressure change values during the simulated real parachute opening process. These values are then converted into altitude parameters and altitude change rate parameters by the built-in pressure / altitude conversion module and pressure change value / altitude change rate module. Feedback signals are generated based on these altitude parameters and altitude change rate parameters. The embedded system unit calculates the static pressure source command to be output based on the calibration control command and the feedback signal from the sensor unit. The air generator is equipped with a servo motor, a negative pressure generator, and a pressure vessel. The servo motor drives the rotating machinery inside the negative pressure generator to work through calibration control commands and feedback signals from the sensor unit, generating a negative pressure air source. The air source is output to or stopped by the programmable solenoid valve. The dual-flow-control proportional flow meter is connected to the volume generator and adjusts the negative pressure gas source through it based on the static pressure source command to obtain the required static pressure source. The data measurement module is configured to measure the static pressure value output by the programmable altitude simulation module in simulating the actual parachute opening process, and control the module to convert the static pressure value into a theoretical altitude value or a theoretical altitude change rate value. The aircraft parachute deployer tester is connected to the control module and the programmable altitude simulation module respectively. The aircraft parachute deployer tester works under static pressure source, and the control module obtains the current altitude value or altitude change rate value displayed by the aircraft parachute deployer tester. The control module calculates the measurement difference between the height value and the theoretical height value, or the height change rate value and the theoretical height change rate value, and adjusts the internal algorithm parameters or calibration curve of the tester based on the measurement difference.
2. The calibration system for an aircraft parachute deployer tester according to claim 1, characterized in that, The flow meter's inlet and outlet are each equipped with a proportional control valve that can automatically adjust its opening. The opening of the proportional valve is adjusted based on the static pressure source command to regulate the passing negative source air pressure and generate the required static pressure source.
3. The calibration system for an aircraft parachute deployer tester according to claim 1, characterized in that, The multi-source redundant clock module provides the master clock signal through a GPS / BeiDou receiver and uses a rubidium atomic clock as a backup clock to provide a synchronization time reference for the programmable altitude simulation module, the aircraft parachute tester, and the control module.
4. The calibration system for an aircraft parachute deployer tester according to claim 3, characterized in that, The multi-source redundant clock module uses a Kalman filter algorithm to fuse multi-source signals from GPS / BeiDou receivers and rubidium atomic clocks.
5. The calibration system for an aircraft parachute deployer tester according to claim 1, characterized in that, The data measurement module also measures the ambient temperature of the aircraft parachute tester in real time. The control module uses a temperature compensation algorithm to correct the static pressure value based on the real-time ambient temperature, and converts the corrected static pressure value into a theoretical altitude value or a theoretical altitude change rate value.
6. A calibration method for an aircraft parachute deployer tester, characterized in that, A method for calibrating an aviation parachute deployer tester based on the system according to any one of claims 1-5, the method comprising: During the pre-calibration preparation phase, the requirements for calibration tasks and simulated actual parachute opening scenarios are obtained, calibration altitude control instruction information is generated, and calibration time synchronization instructions are obtained. The static pressure source is generated by adjusting the dual-flow proportional flow meter based on the calibration height control command information. The static pressure source is used to simulate the real umbrella opening process. The air pressure value changes during the simulated real umbrella opening process are collected. The static pressure source is adjusted in combination with the dual-flow proportional flow meter based on the air pressure value changes. The static pressure value output during the simulated actual parachute opening process is measured and converted into a theoretical altitude value or a theoretical altitude change rate value. The aircraft parachute opener tester operates under a static pressure source and displays the current altitude value or altitude change rate value. Calculate the measurement difference between the height value and the theoretical height value, or the height change rate value and the theoretical height change rate value, and adjust the internal algorithm parameters or calibration curve of the tester based on the measurement difference.
7. The calibration method for the aircraft parachute deployer tester according to claim 6, characterized in that, The system collects air pressure values and air pressure change values during the simulated real parachute opening process. These values are then converted into altitude parameters and altitude change rate parameters by the built-in pressure / altitude conversion module and pressure change value / altitude change rate module. Feedback signals are then generated based on these altitude parameters and altitude change rate parameters. Based on the calibration control command and the feedback signal from the sensor unit, the static pressure source command to be output is calculated. The negative pressure generator is driven by calibration control commands and feedback signals to operate the rotating machinery inside, thereby generating a negative pressure air source. The required static pressure source is obtained by adjusting the negative pressure air source based on the static pressure source command output.
8. The calibration method for the aircraft parachute deployer tester according to claim 6, characterized in that, The actual umbrella opening process is simulated based on a static pressure source, specifically including: The parachute deployment process is broken down into three stages: free fall, canopy inflation, and stable descent. In each stage, changes in the static pressure source simulate the altitude and rate of altitude change during actual deployment. During the free fall, the rate of change of height increases linearly, and the acceleration is the acceleration due to gravity. The parachute canopy inflation section uses an exponential function to simulate the inflection point of the rate of change of altitude caused by a sudden increase in drag. The rate of change of altitude during the steady descent phase remains constant.
9. A computer-readable storage medium, characterized in that, The readable storage medium stores an aviation parachute tester calibration program, which, when executed by a processor, implements the steps of the aviation parachute tester calibration method as described in any one of claims 6-8.