CN110803301A - Novel ejection speed measuring method for ejection of ejection seat out of cabin - Google Patents
Novel ejection speed measuring method for ejection of ejection seat out of cabin Download PDFInfo
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- 238000004088 simulation Methods 0.000 claims description 12
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- 238000003062 neural network model Methods 0.000 claims description 4
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D25/00—Emergency apparatus or devices, not otherwise provided for
- B64D25/08—Ejecting or escaping means
- B64D25/10—Ejector seats
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Abstract
The invention discloses a novel ejection speed measuring method for an ejection seat, and belongs to the technical field of aviation ejection lifesaving. According to the motion characteristics of the ejection seat, a mapping relation model of the acceleration value of the ejection seat in the x-direction of the body axis and the ejection speed based on a BP neural network is established in advance based on a computer simulation means. And (3) installing an acceleration sensor in the x direction of the body axis at a proper position of the ejection seat, and measuring the acceleration value in the x direction of the body axis at the moment that the ejection seat is ejected out of the cabin. And calculating the corresponding ejection cabin-out speed according to the pre-established mapping relation model and the acceleration value. The method avoids the possibility of inaccurate measurement caused by blockage of the airspeed head and the influence of an external flow field, has small error, and meets the engineering application requirements.
Description
Technical Field
The invention relates to the technical field of aviation ejection lifesaving, in particular to a novel ejection speed measuring method for an ejection seat.
Background
The ejection seat is a main lifesaving device for providing emergency departure for pilots. With the expansion of the flight envelope of the fighter, the ejection seat must meet the lifesaving requirement under the conditions of large-range ejection speed and ejection height. Therefore, dividing the ejection mode according to different ejection conditions becomes a key technology of the third generation ejection seat. The principle is that the ejection speed and height when the ejection is started are measured through a sensor, and the parachute opening time of the lifesaving parachute is determined according to a preset program control mode. The ejection seats of the main models in service are all installed with airspeed tubes, and the speed value at the moment of ejection out of the cabin is measured and used as the input of a program controller.
As a result of a large number of ejection tests of the ejection seat, the lifesaving parachute is often ejected prematurely. Through investigation and analysis, the measurement is caused by inaccuracy of the measurement of the airspeed head, and the main reasons are as follows: firstly, when the canopy is penetrated and ejected, fragments of the canopy can block the airspeed head; secondly, the mounting position of the airspeed head is easily influenced by the surrounding flow field of the ejection seat, and particularly, when the ejection seat of certain types is ejected at a high speed, the guide plate can be ejected out for protecting a pilot from being blown by high-speed airflow, and the measurement accuracy of the airspeed head can be directly influenced due to the influence of the flow field of the guide plate. The two reasons can cause the great error of airspeed head measurement, and the safety life-saving performance of the ejection seat is seriously influenced.
With the advancement of inertial measurement technology, high-precision, low-mass, high-frequency, low-cost inertial measurement units have become very popular. Although the inertial measurement unit can directly obtain the movement velocity by integrating the measured acceleration value, it is necessary to know the initial velocity value and perform corresponding initial calibration. In consideration of the independence of measurement, namely, relevant data is not obtained from an aircraft data bus, an initial value is not known, and therefore, the integral operation cannot be carried out.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a novel method for measuring the ejection speed of the ejection seat out of the cabin.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows: a novel ejection speed measuring method for an ejection seat is disclosed, the flow of which is shown in figure 1, and the method comprises the following steps:
step 1: dividing the process of taking the ejection seat out of the cabin into two stages, establishing a mathematical model according to the specific conditions of each stage, and compiling a computer simulation calculation program;
the ejection seat is in a complex motion process in the cabin-out stage, and the ejection seat slides on a guide rail fixed on the airplane by a pulley and is connected with the ejection barrel by an upper joint of the ejection barrel. The mathematical model is established in two stages:
the first stage is as follows: the ejection seat is clamped in the guide rail groove by two pairs of pulleys, the ejection seat system can only move along the direction of the guide rail and can not rotate, and the ejection seat system is under the action of the thrust and gravity of the rocket package at the moment;
and a second stage: the ejection seat is only provided with a pair of pulleys in the ejection groove, the ejection seat system rotates around the axis of the pulleys and moves linearly along the guide rail with two degrees of freedom, and the ejection seat system is under the action of pneumatic power, rocket package thrust and gravity.
The ejection seat system can be acted by various external forces in the cabin-out stage, wherein the thrust of the ejection barrel adopts a test data curve, and the thrust of the rocket package can be generated when the movement distance is greater than the ignition stroke of the rocket package. For the aerodynamic force processing, the wind tunnel blowing test data of the ejection seat system is adopted, and the aerodynamic force characteristic of the ejection seat in the cabin-out stage is considered to be difficult to accurately determine, so that the system is not influenced by aerodynamic force in the first stage, and 80% of the ejection seat enters airflow in the second stage, so that the aerodynamic force and the aerodynamic moment are calculated by adopting the aerodynamic characteristic of the whole ejection seat.
Analysis shows that the acceleration of the ejection seat in the x direction of the body axis at the moment of taking out of the cabin is mainly caused by the components of aerodynamic force, rocket package thrust and gravity in the x direction of the body axis. Neglecting the influence of the intrinsic parameters of the ejection seat, such as the thrust of the ejection cylinder, the installation angle of the seat, etc., the factors influencing the acceleration value of the ejection seat in the x-direction of the body axis include: ejection height, ejection speed and ejection off-machine quality.
Step 2: changing state parameters of the ejection seat when the ejection is started, wherein the state parameters comprise ejection speed, ejection height and ejection departure mass, obtaining acceleration of the corresponding ejection seat in the x direction of the body axis at the moment of taking out of the cabin through simulation, and taking simulation result data as a sample;
step 2.1: selecting a group of ejection speed, ejection height and ejection off-machine quality as ejection starting state parameters;
step 2.2: simulating by a simulation calculation program to obtain an acceleration value of the corresponding ejection seat in the x direction of the body axis at the moment of taking out of the cabin;
step 2.3: and (3) taking the selected ejection height, ejection speed, ejection departure mass and the acceleration value of the ejection seat in the x direction of the body axis at the moment of departure from the cabin, which is obtained by corresponding simulation, as a group of samples, and simulating ejection starting parameters in different states to obtain a plurality of groups of samples.
The relationship between the parameters in the sample conforms to the formula: acceleration f (ejection height, ejection speed, ejection off-board mass). In this case, the ejection speed is present as a known quantity, and the acceleration value is unknown to be quantified. The relationship function is converted, and the converted relationship is as follows: the ejection speed f (ejection height, acceleration, ejection off-board mass). Therefore, the ejection speed is a ternary implicit function formed by 3 parameters of ejection height, acceleration and ejection off-plane mass, the mapping relation of the ejection speed and the ejection off-plane mass has the characteristic of high nonlinearity, and the common function fitting is difficult to meet the precision requirement.
And step 3: taking the acceleration, the ejection height and the ejection off-plane mass of the ejection seat in the sample in the x direction of the body axis at the moment of taking the ejection seat out of the cabin as input, taking the ejection speed as output, training a BP neural network model, and obtaining a highly nonlinear mapping relation model between the input and the output;
and 4, step 4: writing the mapping relation model into an ejection seat program controller module;
and 5: the acceleration, the ejection height and the ejection departure mass of the ejection seat in the x direction of the body axis at the instant of taking the ejection seat out of the cabin are collected and input into an ejection seat program controller module, and an ejection speed value is obtained through calculation.
The method for acquiring the acceleration of the ejection seat in the x direction of the body axis at the moment of cabin exit comprises the steps of installing an acceleration sensor on the ejection seat in the x direction of the body axis, and measuring the obtained acceleration value according to a pre-designed working mode, such as ejection time or ejection stroke, after the ejection is started.
Adopt the produced beneficial effect of above-mentioned technical scheme to lie in:
1. the ejection speed value is obtained by utilizing the acceleration value measured by the acceleration sensor, so that the blockage of the airspeed head is avoided, and the possibility of inaccurate measurement caused by the influence of an external flow field is eliminated;
2. the invention establishes a mathematical model and a simulation program, calculates and obtains a data set among the ejection speed, the ejection height, the acceleration and the ejection off-board mass, and the data set can accurately establish the corresponding relation among the parameters. In addition, due to the advantages of computer simulation, the number of samples of the data set is not limited, and compared with a physical test, the cost is low and the period is short;
3. the invention utilizes a BP neural network model to complete the nonlinear mapping process from 3 parameters such as acceleration and the like to the ejection speed, has small error and meets the requirements of engineering application;
4. the acceleration sensor only needs to consider the installation direction during installation, has no limitation on the installation position, and does not need initial calibration, and the traditional speed sensor has requirements on the installation position and needs to avoid the influence of a flow field as much as possible.
Drawings
Fig. 1 is a flow chart of a novel ejection speed measuring method for ejecting an ejection seat out of a cabin.
Detailed Description
The following detailed description of embodiments of the present invention is provided in connection with the accompanying drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
As shown in fig. 1, the method of the present embodiment is as follows.
Step 1: dividing the process of taking the ejection seat out of the cabin into two stages, establishing a mathematical model according to the specific conditions of each stage, and compiling a computer simulation calculation program;
the first stage is as follows: the ejection seat is clamped in the guide rail groove by two pairs of pulleys, the ejection seat system can only move along the direction of the guide rail and can not rotate, and the ejection seat system is under the action of the thrust and gravity of the rocket package at the moment;
and a second stage: the ejection seat is only provided with a pair of pulleys in the ejection groove, the ejection seat system rotates around the axis of the pulleys and moves linearly along the guide rail with two degrees of freedom, and the ejection seat system is under the action of pneumatic power, rocket package thrust and gravity.
Step 2: changing state parameters of the ejection seat when the ejection is started, wherein the state parameters comprise ejection speed, ejection height and ejection departure mass, obtaining acceleration of the corresponding ejection seat in the x direction of the body axis at the moment of taking out of the cabin through simulation, and taking simulation result data as a sample;
step 2.1: selecting a group of ejection speed, ejection height and ejection off-machine quality as ejection starting state parameters;
step 2.2: simulating by a simulation calculation program to obtain an acceleration value of the corresponding ejection seat in the x direction of the body axis at the moment of taking out of the cabin;
step 2.3: and (3) taking the selected ejection height, ejection speed, ejection departure mass and the acceleration value of the ejection seat in the x direction of the body axis at the moment of departure from the cabin, which is obtained by corresponding simulation, as a group of samples, and simulating ejection starting parameters in different states to obtain a plurality of groups of samples.
The relationship between the parameters in the sample conforms to the formula: acceleration f (ejection height, ejection speed, ejection off-board mass). In this case, the ejection speed is present as a known quantity, and the acceleration value is unknown to be quantified. The relationship function is converted, and the converted relationship is as follows: the ejection speed f (ejection height, acceleration, ejection off-board mass). Therefore, the ejection speed is a ternary implicit function formed by 3 parameters of ejection height, acceleration and ejection off-plane mass, the mapping relation of the ejection speed and the ejection off-plane mass has the characteristic of high nonlinearity, and the common function fitting is difficult to meet the precision requirement.
And step 3: taking the acceleration, the ejection height and the ejection off-plane mass of the ejection seat in the sample in the x direction of the body axis at the moment of taking the ejection seat out of the cabin as input, taking the ejection speed as output, training a BP neural network model, and obtaining a highly nonlinear mapping relation model between the input and the output;
and 4, step 4: writing the mapping relation model into an ejection seat program controller module;
and 5: the acceleration, the ejection height and the ejection departure mass of the ejection seat in the x direction of the body axis at the instant of taking the ejection seat out of the cabin are collected and input into an ejection seat program controller module, and an ejection speed value is obtained through calculation.
The method for acquiring the acceleration of the ejection seat in the x direction of the body axis at the moment of cabin exit comprises the steps of installing an acceleration sensor on the ejection seat in the x direction of the body axis, and measuring the obtained acceleration value according to a pre-designed working mode, such as ejection time or ejection stroke, after the ejection is started.
In the present embodiment, considering various ejection states, two end limit values are respectively selected for the off-plane mass, a low altitude, a hollow altitude and a high altitude are respectively selected for the ejection height, and a low speed, a medium speed and a high speed are respectively selected for the ejection speed, and three sets of data are collected as examples, as shown in table 1:
TABLE 1 three sets of data collected
| Serial number | Ejection height (m) | Acceleration (m/s) in x-direction of body axis2) | Off-machine quality (percentile) |
| 1 | 432 | 49.64896 | 5％ |
| 2 | 3589 | 4.8678 | 5％ |
| 3 | 6983 | -34.5116 | 95％ |
The 3 sets of collected data are respectively input into a mapping relation model in an ejection seat program controller module, and the comparison between the predicted speed and the actual ejection speed of the BP neural network is obtained as shown in the table 2:
TABLE 2 comparison of predicted speed to actual speed
The speed prediction errors under the 3 groups of ejection state parameters are smaller, the precision of the speed measurement of the ejection seat in the cabin-out process is higher, and the actual measurement requirements of engineering are met.
Claims (4)
1. A novel ejection speed measuring method for ejecting an ejection seat out of a cabin is characterized by comprising the following steps:
step 1: dividing the process of taking the ejection seat out of the cabin into two stages, establishing a mathematical model according to the specific conditions of each stage, and compiling a computer simulation calculation program;
step 2: changing the state parameters when the ejection of the ejection seat is started comprises the following steps: the ejection speed, the ejection height and the ejection departure mass are obtained through simulation, the acceleration of the corresponding ejection seat in the x direction of the body axis at the moment of getting out of the cabin is obtained, and the simulation result data is used as a sample;
and step 3: taking the acceleration, the ejection height and the ejection off-plane mass of the ejection seat in the sample in the x direction of the body axis at the moment of taking the ejection seat out of the cabin as input, taking the ejection speed as output, training a BP neural network model, and obtaining a highly nonlinear mapping relation model between the input and the output;
and 4, step 4: writing the mapping relation model into an ejection seat program controller module;
and 5: the acceleration, the ejection height and the ejection departure mass of the ejection seat in the x direction of the body axis at the instant of taking the ejection seat out of the cabin are collected and input into an ejection seat program controller module, and an ejection speed value is obtained through calculation.
2. The method for measuring the ejection and cabin-out speed of the ejection seat according to claim 1, wherein the two stages in step 1 are respectively:
the first stage is as follows: the ejection seat is clamped in the guide rail groove by two pairs of pulleys, the ejection seat system can only move along the direction of the guide rail and can not rotate, and the ejection seat system is under the action of the thrust and gravity of the rocket package at the moment;
and a second stage: the ejection seat is only provided with a pair of pulleys in the ejection groove, the ejection seat system rotates around the axis of the pulleys and moves linearly along the guide rail with two degrees of freedom, and the ejection seat system is under the action of pneumatic power, rocket package thrust and gravity.
3. The method for measuring the ejection and cabin-exiting speed of the ejection seat as claimed in claim 1, wherein the process of the step 2 is as follows:
step 2.1: selecting a group of ejection speed, ejection height and ejection off-machine quality as ejection starting state parameters;
step 2.2: simulating by a simulation calculation program to obtain an acceleration value of the corresponding ejection seat in the x direction of the body axis at the moment of taking out of the cabin;
step 2.3: and (3) taking the selected ejection height, ejection speed, ejection departure mass and the acceleration value of the ejection seat in the x direction of the body axis at the moment of departure from the cabin, which is obtained by corresponding simulation, as a group of samples, and simulating ejection starting parameters in different states to obtain a plurality of groups of samples.
4. The method for measuring the ejection and cabin-out speed of the ejection seat as claimed in claim 1, wherein the step 5 is to install an acceleration sensor on the ejection seat in the x direction of the body axis at the moment of cabin-out of the ejection seat, and after the ejection is started, measure the magnitude of the obtained acceleration value according to a pre-designed working mode, such as the ejection time or the ejection stroke.
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Cited By (3)
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| CN111625764A (en) * | 2020-05-21 | 2020-09-04 | 北京嘀嘀无限科技发展有限公司 | Calibration method and device for mobile data, electronic equipment and storage medium |
| CN114136676A (en) * | 2021-11-26 | 2022-03-04 | 航宇救生装备有限公司 | Ejection integration simulation method for human chair system |
| WO2022082416A1 (en) * | 2020-10-20 | 2022-04-28 | 航宇救生装备有限公司 | Deflation device for ejection overload control of rocket ejection seat |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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Application publication date: 20200218 |