CN116822164A - Method for calculating maximum value of impact sinking rate of aircraft landing on ship - Google Patents
Method for calculating maximum value of impact sinking rate of aircraft landing on ship Download PDFInfo
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Abstract
The application belongs to the field of aircraft design, and particularly relates to a method for calculating the maximum value of the impact sinking rate of an aircraft during the process of landing, and a plurality of random event models are established during the process of landing; performing a simulation experiment for simulating the movement process of the aircraft landing by using a simulation model of the aircraft landing, and adding random parameters to the simulation experiment by using a random event model; acquiring the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing as the sinking rate; and carrying out normal distribution fitting on a plurality of sinking rates to obtain a sinking rate average value Vm and a mean square error sigma, taking the sinking rate corresponding to vm+3Be as the maximum sinking rate, wherein the application simulation result comprises the influence of a plurality of factors such as the closed-loop time delay of a large system of the locomotive, the relative navigation positioning precision, the deck motion prediction algorithm precision, the on-board sensor precision and the like, and the simulation result and the conclusion are more accurate.
Description
Technical Field
The application belongs to the field of aircraft design, and particularly relates to a method for calculating the maximum value of the impact sinking rate of an aircraft on a ship.
Background
Because the use environment of the aircraft requires taking off and landing on a ship moving longitudinally and transversely in stormy waves, the landing process threatens the safety of the aircraft. In order to enable safe take-off and landing of the aircraft on board the vessel and handling and storage on board the vessel, the aircraft has to be designed to be heavier than a land-based aircraft. Wherein, the weight gain is mainly generated by the lifting device and the machine body structure thereof. The large difference in mass between the landing gear of a ship-borne aircraft and a land-based aircraft is mainly caused by large difference in landing impact and sinking rates of the aircraft, and the maximum sinking rate is a main parameter affecting the landing gear. Therefore, when designing an aircraft, it is necessary to study the maximum sinking rate, which is the instantaneous speed of the aircraft relative to the ship at the moment the aircraft is on the ship.
The factors influencing the landing rate of the aircraft are many, the landing speed of the aircraft, the deck wind speed, the landing glide angle of the aircraft, the airflow disturbance at the tail end, the attitude of the aircraft when the aircraft touches the ship, the sinking and floating movement of the ship, the sea condition conditions and the like, the landing rate of the aircraft under different conditions is greatly different, randomness exists, and the determination of the maximum landing rate of the aircraft as the design condition of the landing gear device can ensure that the aircraft can safely land under various complex conditions, and the situation that the landing gear is damaged due to insufficient structural strength of the landing gear and the danger on the ship surface is caused by the fault of the aircraft does not occur.
Since there is no maximum sinking rate index in China, there is an unacceptable risk of damage to the landing gear of the ship for uncertain situations, and determining the maximum sinking rate by an empirical formula generally leaves a sufficient margin. The use of a larger sinking rate index as a condition for designing landing gear and related structures results in over-design of landing gear and airframe structural strength at the cost of heavier aircraft landing gear and related structures, which results in less fuel and weapon loads being added to the aircraft and significant losses for aircraft, particularly on-board aircraft.
Disclosure of Invention
In order to solve the above problems, the present application provides a method for calculating the maximum value of the impact sinking rate of an aircraft on a ship, comprising:
establishing a simulation model of aircraft boarding, and establishing a plurality of random event models in the aircraft boarding process;
performing a simulation experiment for simulating the movement process of the aircraft landing by using a simulation model of the aircraft landing, and adding random parameters to the simulation experiment by using a random event model;
acquiring the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing as the sinking rate;
and carrying out normal distribution fitting on the sinking rates through a least square method to obtain a sinking rate average value Vm and a mean square error sigma, and taking the sinking rate corresponding to vm+3Be as the maximum sinking rate.
Preferably, the simulation model of aircraft landing comprises: an aircraft model for simulating an aircraft, an atmospheric disturbance model for simulating disturbance of atmospheric air flow to the aircraft and to the air flow of the ship, a ship motion model for simulating navigation in water and for the aircraft to land on the ship, and a deck motion prediction model for calculating preset ship deck motions; a sensor model for measuring the relative ship speed of an aircraft, a landing guidance control algorithm model for guiding the landing of the aircraft model on the deck of the ship motion model.
Preferably, in the simulation experiment, the motion parameters of the ship motion model are randomly intercepted in the ship motion database.
Preferably, the random event model comprises a model for randomly generating random parametric variations of turbulence in the wind disturbance, a model for randomly generating random parametric variations of wake components of the vessel in the wind disturbance; the method comprises the steps of generating a model of deck motion prediction error values meeting an error probability distribution, generating a model of positioning measurement error values meeting the error probability distribution, and generating a model of ship inertial navigation measurement errors meeting the error probability distribution.
Preferably, the method for obtaining the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing on the ship comprises the following steps:
acquiring the position coordinates of the aircraft relative to the ship and the speed of the aircraft relative to the ship;
establishing a relation curve between the speeds of the aircraft relative to the ship corresponding to the position coordinates of the aircraft relative to the ship;
and acquiring the position coordinates of the aircraft relative to the ship when the aircraft is in contact with the ship, and finding out the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing the ship on the relation curve through the position coordinates of the aircraft relative to the ship when the aircraft is in contact with the ship.
Preferably, the method for obtaining the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing on the ship comprises the following steps:
acquiring the position coordinates of the aircraft relative to the ship;
calculating the relative distance between the aircraft and the ship according to the position coordinates of the aircraft relative to the ship;
establishing a relation curve of the relative distance between the aircraft and the ship and time;
and calculating a derivative value of the relation curve when the relative distance between the aircraft and the ship is 0, and taking the derivative value as the instantaneous speed of the aircraft relative to the ship at the moment when the aircraft lands on the ship.
Preferably, the number of experiments of the simulation experiment is at least 1000.
The advantages of the application include: the simulation result of the application comprises the influence of a plurality of factors such as the closed-loop time delay of a large system of the locomotive and the ship, the relative navigation positioning precision, the deck motion prediction algorithm precision, the on-board sensor precision and the like, the simulation result and the conclusion are more accurate, the reliability is higher, and the risk of landing the ship can be further lightened according to the index determined by the method;
the maximum sinking rates of different airplanes corresponding to different offshore platforms and different sea conditions are different, and the method can strictly take the corresponding conditions as simulation conditions according to the requirements, so that the calculation results meeting the requirements but not oversupplied are obtained, the weight reduction of the undercarriage and the airframe structure is facilitated, and huge benefits in terms of war efficiency can be brought. .
Drawings
FIG. 1 is a flowchart of a method for calculating the maximum value of the impact sinking rate of an aircraft on a ship according to a preferred embodiment of the application.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only the part related to the present application is shown in the drawings, and other related parts may refer to the general design, and the embodiments of the present application and the technical features of the embodiments may be combined with each other to obtain new embodiments without conflict.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in the description of the present application are merely used for indicating relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and that the relative positional relationships may be changed when the absolute position of the object to be described is changed, thus not being construed as limiting the application. The terms "first," "second," "third," and the like, as used in the description of the present application, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the application are not to be construed as limiting the amount absolutely, but rather as existence of at least one. As used in this description of the application, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term as such, but does not exclude other elements or articles from the list of elements or articles that appear after the term.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description of the present application are used in a broad sense, and for example, the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The principle of the method of the application is as follows: taking factors related to ship landing, such as atmospheric disturbance, sea conditions, ship motion, deck motion prediction errors, sensor error characteristics, data chain time delay, aircraft control strategies, aircraft pneumatic data errors and the like into consideration, establishing a probability model for random events in the ship landing process, performing mass simulation (repeated closed loop simulation for more than 1000 times) on the ship landing process by adopting a Monte Carlo simulation method, recording sinking speed of the aircraft relative to a deck at the moment of ship landing, analyzing and sorting sinking rate simulation data, performing normal distribution fitting through a least square method, obtaining a sinking rate average value Vm and a mean square error, and taking the sinking rate corresponding to vm+3Sigma as the maximum sinking rate.
The application provides a method for calculating the maximum value of the impact sinking rate of an aircraft on a ship, which comprises the following steps:
step 1: establishing a simulation model of aircraft boarding, and establishing a plurality of random event models in the aircraft boarding process; the simulation model for aircraft landing comprises: an aircraft model for simulating an aircraft, an atmospheric disturbance model for simulating disturbance of atmospheric air flow to the aircraft and to the air flow of the ship, a ship motion model for simulating navigation in water and for the aircraft to land on the ship, and a deck motion prediction model for calculating preset ship deck motions; a sensor model for measuring the relative ship speed of an aircraft, a landing guidance control algorithm model for guiding the landing of the aircraft model on the deck of the ship motion model.
Step 2: performing a simulation experiment for simulating the movement process of the aircraft landing by using a simulation model of the aircraft landing, and adding random parameters to the simulation experiment by using a random event model; and during the simulation experiment, the motion parameters of the ship motion model are randomly intercepted in a ship motion database.
The random event model comprises a model for randomly generating random parameter variables of turbulence in wind disturbance and a model for randomly generating random parameter variables of random components of wake flow of a ship in wind disturbance; a model for generating deck motion prediction error values satisfying an error probability distribution, a model for generating positioning measurement error values satisfying an error probability distribution, a model for generating ship inertial navigation measurement errors satisfying an error probability distribution
Step 3: acquiring the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing as the sinking rate;
step 4: and performing normal distribution fitting on the sinking rates, performing normal distribution fitting through a least square method to obtain a sinking rate average value Vm and a mean square error sigma, and taking the sinking rate corresponding to vm+3sigma as the maximum sinking rate.
The random event modeling principle is as follows:
a) Randomly intercepting ship motion parameters in a ship motion database in a simulation environment;
b) Random parameter variables of turbulence in wind disturbance are generated by random numbers;
c) Random parameter variables of random components of stern flow in wind disturbance are generated by random numbers;
d) The deck motion prediction error is generated by random numbers meeting the error probability distribution, and all variables are independent;
e) The positioning measurement error is generated by random numbers meeting the error probability distribution, and each variable is independent;
f) The ship inertial navigation measurement error is generated by random numbers meeting the error probability distribution, and each variable is independent; .
Preferably, the method for obtaining the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing on the ship comprises the following steps:
acquiring the position coordinates of the aircraft relative to the ship and the speed of the aircraft relative to the ship;
establishing a relation curve between the speeds of the aircraft relative to the ship corresponding to the position coordinates of the aircraft relative to the ship;
and acquiring the position coordinates of the aircraft relative to the ship when the aircraft is in contact with the ship, and finding out the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing the ship on the relation curve through the position coordinates of the aircraft relative to the ship when the aircraft is in contact with the ship.
Preferably, the method for obtaining the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing on the ship comprises the following steps:
acquiring the position coordinates of the aircraft relative to the ship;
calculating the relative distance between the aircraft and the ship according to the position coordinates of the aircraft relative to the ship;
establishing a relation curve of the relative distance between the aircraft and the ship and time;
and calculating a derivative value of the relation curve when the relative distance between the aircraft and the ship is 0, and taking the derivative value as the instantaneous speed of the aircraft relative to the ship at the moment when the aircraft lands on the ship.
Preferably, the number of experiments in the simulation is at least 1000
The simulation result of the application comprises the influence of a plurality of factors such as the closed-loop time delay of a large system of the locomotive and the ship, the relative navigation positioning precision, the deck motion prediction algorithm precision, the on-board sensor precision and the like, the simulation result and the conclusion are more accurate, the reliability is higher, and the risk of landing the ship can be further lightened according to the index determined by the method;
the maximum sinking rates of different airplanes corresponding to different offshore platforms and different sea conditions are different, and the method can strictly take the corresponding conditions as simulation conditions according to the requirements, so that the calculation results meeting the requirements but not oversupplied are obtained, the weight reduction of the undercarriage and the airframe structure is facilitated, and huge benefits in terms of war efficiency can be brought.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The method for calculating the maximum value of the impact sinking rate of the aircraft on the ship is characterized by comprising the following steps of:
establishing a simulation model of aircraft boarding, and establishing a plurality of random event models in the aircraft boarding process;
performing a simulation experiment for simulating the movement process of the aircraft landing by using a simulation model of the aircraft landing, and adding random parameters to the simulation experiment by using a random event model;
acquiring the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing as the sinking rate;
and carrying out normal distribution fitting on the sinking rates to obtain a sinking rate average value Vm and a mean square error sigma, and taking the sinking rate corresponding to vm+3sigma as the maximum sinking rate.
2. The method for calculating the maximum value of the impact sinking rate of an aircraft landing as defined in claim 1, wherein the simulation model of the aircraft landing comprises: an aircraft model for simulating an aircraft, an atmospheric disturbance model for simulating disturbance of atmospheric air flow to the aircraft and to the air flow of the ship, a ship motion model for simulating navigation in water and for the aircraft to land on the ship, and a deck motion prediction model for calculating preset ship deck motions; a sensor model for measuring the relative ship speed of an aircraft, a landing guidance control algorithm model for guiding the landing of the aircraft model on the deck of the ship motion model.
3. The method for calculating the maximum value of the impact sinking rate of an aircraft on a ship according to claim 2, wherein the motion parameters of the ship motion model are randomly intercepted in a ship motion database during a simulation experiment.
4. The method for calculating the maximum value of the impact sinking rate of an aircraft on a ship according to claim 1, wherein the random event model comprises a model for randomly generating random parameter variables of turbulence in wind disturbance and a model for randomly generating random parameter variables of wake random components of a ship in wind disturbance; the method comprises the steps of generating a model of deck motion prediction error values meeting an error probability distribution, generating a model of positioning measurement error values meeting the error probability distribution, and generating a model of ship inertial navigation measurement errors meeting the error probability distribution.
5. The method for calculating the maximum value of the impact sinking rate of an aircraft on a ship according to claim 1, wherein the method for obtaining the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft on the ship is as follows:
acquiring the position coordinates of the aircraft relative to the ship and the speed of the aircraft relative to the ship;
establishing a relation curve between the speeds of the aircraft relative to the ship corresponding to the position coordinates of the aircraft relative to the ship;
and acquiring the position coordinates of the aircraft relative to the ship when the aircraft is in contact with the ship, and finding out the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft landing the ship on the relation curve through the position coordinates of the aircraft relative to the ship when the aircraft is in contact with the ship.
6. The method for calculating the maximum value of the impact sinking rate of an aircraft on a ship according to claim 1, wherein the method for obtaining the instantaneous speed of the aircraft relative to the ship at the moment of the aircraft on the ship is as follows:
acquiring the position coordinates of the aircraft relative to the ship;
calculating the relative distance between the aircraft and the ship according to the position coordinates of the aircraft relative to the ship;
establishing a relation curve of the relative distance between the aircraft and the ship and time;
and calculating a derivative value of the relation curve when the relative distance between the aircraft and the ship is 0, and taking the derivative value as the instantaneous speed of the aircraft relative to the ship at the moment when the aircraft lands on the ship.
7. The method for calculating the maximum value of the impact sinking rate of an aircraft on a ship according to claim 1, wherein the number of experiments of the simulation experiment is at least 1000.
8. The method for calculating the maximum value of the impact sinking rate of an aircraft on a ship according to claim 1, wherein the normal distribution fitting is performed by a least square method.
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| CN202310666790.6A CN116822164A (en) | 2023-06-06 | 2023-06-06 | Method for calculating maximum value of impact sinking rate of aircraft landing on ship |
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| CN202310666790.6A CN116822164A (en) | 2023-06-06 | 2023-06-06 | Method for calculating maximum value of impact sinking rate of aircraft landing on ship |
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