CN113536625B - Analysis method for blocking hook bouncing and hook rope meshing in carrier aircraft carrier landing process - Google Patents
Analysis method for blocking hook bouncing and hook rope meshing in carrier aircraft carrier landing process Download PDFInfo
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Abstract
The invention discloses a method for analyzing the bouncing of a blocking hook and the engagement of a hook rope in the carrier landing process of a carrier-based aircraft. Compared with the existing calculation and analysis method, the finite element modeling method provided by the invention considers more influencing factors, and the result is more accurate; meanwhile, the simulation of the impact of the arresting hook on the deck is realized, the problem that the transient response of the impact of the arresting hook on the deck is difficult to obtain in the aircraft landing process is solved, the cost can be saved, and the design efficiency is improved.
Description
Technical Field
The invention belongs to the technical field of dynamic response load simulation of a carrier-based aircraft arresting hook impacting a deck, and particularly relates to an arresting hook bouncing and hook rope meshing analysis method in a carrier-based aircraft landing process.
Background
The arresting hook is a remarkable difference between a carrier-based aircraft and a land-based aircraft, and has the main function of hooking an aircraft carrier arresting rope after the aircraft enters the ground smoothly to generate arresting force so as to realize short-distance braking of the aircraft moving at a high speed. Before the carrier-based aircraft hangs the rope, the arresting hook collides with the deck first and bounces with limited height under the action of the longitudinal arresting device. Because the carrier-based aircraft sinking speed is high, the blocking hook still has high rebound even under the action of the longitudinal damper after colliding with the deck, if the blocking hook is not controlled, the blocking hook can even rebound beyond the blocking rope, so that the carrier-based aircraft hanging rope fails, and therefore, the consideration of the blocking hook bouncing process in the carrier-based aircraft landing process is very important.
The method for researching the process is divided into theoretical analysis and finite element modeling analysis, wherein the theoretical analysis mainly calculates and solves the rebound height of the hook rope by constructing a rebound dynamics model, the method has the advantages of high calculation speed and capability of obtaining an analytic solution, and the defect that the model is too ideal, often has larger error with the actual situation and cannot meet the requirement of hook rope meshing judgment; the finite element modeling analysis method is to carry out numerical calculation solution by establishing a finite element analysis model of the carrier-based aircraft, the method can consider various factors into the model, and the result is close to the actual situation, but most of the prior finite element modeling methods are insufficient for the consideration of the arresting hooks, and the arresting hooks are generally regarded as a whole for modeling in the modeling process, so that the dynamic response result of the arresting hook model is inaccurate, the bouncing response of the arresting hooks during carrier landing is inaccurate, and reliable hook engagement judgment cannot be carried out.
Disclosure of Invention
Aiming at the current situation that the theoretical analysis and actual condition errors of the arresting hook bounce are larger and the finite element modeling is inaccurate in the process of researching the carrier aircraft carrier landing, the invention provides an arresting hook bounce and hook rope engagement analysis method in the process of carrier aircraft carrier landing, and provides a basis for the dynamic performance design and landing safety evaluation of the aircraft arresting hook and the arresting rope. The specific technical scheme of the invention is as follows:
a method for analyzing the jump of a blocking hook and engagement of a hook rope in the carrier aircraft carrier landing process comprises the following steps:
s1: establishing a blocking hook model;
s2: establishing a force transmission fuselage model, modeling by adopting a shell unit, and defining the model as a rigid body;
s3: establishing a deck model, modeling a contact area between the arresting hooks and the deck by adopting a body grid, modeling the rest deck parts by adopting shell units, and defining materials as steel;
s4: establishing a blocking cable model, establishing an elastic cable model through discrete spring beam units, simulating the appearance of a cable through a shell unit surrounding the beam units, and judging the contact of a blocking hook cable;
s5: the method comprises the steps of establishing a nose landing gear finite element model, wherein the nose landing gear finite element model is divided into four parts of a tire, a torque arm, a strut and a supporting rod, the torque arm, the strut and the supporting rod are modeled by adopting shell units, and the material is defined as steel; the tire carcass is modeled by adopting a body grid, the material is defined as Ogde rubber, a closed air chamber is defined in the carcass, and the rigidity of the tire air pressure is calibrated, namely, the tire air pressure is checked according to the relation between the tire compression amount and the tire supporting force; modeling the main landing gear by using the same modeling method;
s6: setting an initial dropping speed for a constructed landing gear finite element model in the landing gear earthquake checking process, simulating to obtain a displacement curve of a buffer strut, vertical stress condition of a tire and compression quantity change condition of the tire, comparing the obtained simulation curve with a curve obtained in an actual earthquake testing process, checking that a result obtained by simulation meets the requirement of error accuracy, and determining a landing gear buffering characteristic parameter;
s7: defining a contact relation between the arresting hook and the body and between the arresting hook and the landing gear;
s8: and carrying out finite element calculation and solving on the obtained carrier-borne aircraft carrier landing finite element model, extracting the hook engagement judgment condition, the blocking hook bouncing span and the bouncing height in the calculation result, and carrying out result processing analysis by combining the calculation working condition.
Further, the specific method in the step S1 is as follows:
s1-1: dividing a arresting hook model into a hook head, a hook arm, a stabilizer, a universal joint and a longitudinal damper, wherein the hook head and the hook arm are used for building a finite element model by using body grids, and shells of the stabilizer, the universal joint and the longitudinal damper are modeled by adopting shell units and endow the shells with material properties of corresponding materials to form an integral appearance;
s1-2: establishing an inner rod unit of the longitudinal damper, establishing a shell by adopting a shell unit, establishing the longitudinal rod unit in the damper, defining the rod unit material as an elastic beam rod, setting corresponding displacement-external force curve data for the rod unit according to the characteristic requirement of the longitudinal damper, obtaining relevant damping force data through displacement deformation of the rod, and simulating the function of the longitudinal damper;
s1-3: and establishing a rod unit in the stabilizer, wherein the rod unit is defined as an elastic beam, response displacement-external force curve data are set for the rod unit according to the transverse swing reduction requirement of the stabilizer, relevant damping force data are obtained through displacement deformation of the rod, and the function of the stabilizer is simulated.
Further, in the step S7, the hook head is fixedly connected with the hook arm, the hook arm slides with the stabilizer, the hook arm rotates with the universal joint, the universal joint rotates with the longitudinal damper, the blocking hook rotates with the machine body, and the machine body is fixedly connected with the landing gear.
The invention has the beneficial effects that:
1. according to the invention, through careful modeling of the arresting hooks and checking of the tires and the landing gear, the bouncing problem of the arresting hooks in the carrier-based aircraft landing process can be accurately simulated. Compared with the existing calculation and analysis method, the finite element modeling method provided by the invention considers more influencing factors, and the obtained result is more accurate;
2. the invention can realize the simulation of the impact of the arresting hook on the deck, solves the problem that the dynamic response of the arresting hook on the deck is difficult to obtain in the carrier-based aircraft landing process, and provides an important reference basis for the overall design of the arresting hook and the arresting rope and the landing safety;
3. the simulation method provided by the invention can realize simulation of various complex environments on the ship, including sinking speed, heading speed and dragging movement of the aircraft, and obtain blocking hooking response data which is relatively consistent with the actual ship landing condition through checking, so that the experimental cost is saved, and the design efficiency is improved;
4. the simulation method provided by the invention can be suitable for carrier-borne aircrafts with different landing speeds, and is also suitable for blocking hooks with different forms.
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For a clearer description of an embodiment of the invention or of the solutions of the prior art, reference will be made to the accompanying drawings, which are used in the embodiments and which are intended to illustrate, but not to limit the invention in any way, the features and advantages of which can be obtained according to these drawings without inventive labour for a person skilled in the art. Wherein:
FIG. 1 is a flow chart of the method of the present invention;
FIG. 2 is a graph of longitudinal bouncing displacement of the arresting hook;
FIG. 3 is a graph of transverse bouncing displacement time of the arresting hook;
FIG. 4 is a model of a barrier hook;
FIG. 5 is a nose landing gear model;
FIG. 6 is a main landing gear model;
FIG. 7 is a force transfer fuselage model;
figure 8 is a model of a stopper rope.
Detailed Description
In order that the above-recited objects, features and advantages of the present invention will be more clearly understood, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description. It should be noted that, without conflict, the embodiments of the present invention and features in the embodiments may be combined with each other.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than those described herein, and therefore the scope of the present invention is not limited to the specific embodiments disclosed below.
As shown in fig. 1, the invention provides a method for analyzing the meshing of a arresting hook and a rope during carrier landing, which is characterized in that the arresting hook is subjected to component modeling, tire rigidity check and landing gear earthquake check, so that the problem of the arresting hook bouncing during carrier landing is researched, and particularly, by establishing an arresting dynamics model comprising a deck, a landing gear, an arresting hook, a force transmission machine body and the arresting rope, the meshing dynamics response of the arresting rope at the carrier landing time of the carrier aircraft is more accurate.
A method for analyzing the jump of a blocking hook and engagement of a hook rope in the carrier aircraft carrier landing process comprises the following steps:
s1: establishing a blocking hook model;
s2: establishing a force transmission fuselage model, modeling by adopting a shell unit, and defining the model as a rigid body;
s3: establishing a deck model, modeling a contact area between the arresting hooks and the deck by adopting a body grid, modeling the rest deck parts by adopting shell units, and defining materials as steel;
s4: establishing a blocking cable model, establishing an elastic cable model through discrete spring beam units, simulating the appearance of a cable through a shell unit surrounding the beam units, and judging the contact of a blocking hook cable;
s5: the method comprises the steps of establishing a nose landing gear finite element model, wherein the nose landing gear finite element model is divided into four parts of a tire, a torque arm, a strut and a supporting rod, the torque arm, the strut and the supporting rod are modeled by adopting shell units, and the material is defined as steel; the tire carcass is modeled by adopting a body grid, the material is defined as Ogde rubber, a closed air chamber is defined in the carcass, and the rigidity of the tire air pressure is calibrated, namely, the tire air pressure is checked according to the relation between the tire compression amount and the tire supporting force; modeling the main landing gear by using the same modeling method;
s6: setting an initial dropping speed for a constructed landing gear finite element model in the landing gear earthquake checking process, simulating to obtain a displacement curve of a buffer strut, vertical stress condition of a tire and compression quantity change condition of the tire, comparing the obtained simulation curve with a curve obtained in an actual earthquake testing process, checking that a result obtained by simulation meets the requirement of error accuracy, and determining a landing gear buffering characteristic parameter;
s7: the method comprises the steps of defining a arresting hook and a contact relation between the arresting hook and a machine body as well as between the arresting hook and the machine body as well as between the arresting hook and a landing gear, wherein the fixedly connected part is arranged between a hook head and a hook arm, the sliding part is arranged between the hook arm and a stabilizer, the rotating part is arranged between the hook arm and a universal joint, the rotating part is arranged between the universal joint and a longitudinal damper, the rotating part is arranged between the arresting hook and the machine body, and the fixedly connected part is arranged between the machine body and the landing gear.
S8: and carrying out finite element calculation and solving on the obtained carrier-borne aircraft carrier landing finite element model, extracting the hook engagement judgment condition, the blocking hook bouncing span and the bouncing height in the calculation result, and carrying out result processing analysis by combining the calculation working conditions (the pitch angle, the roll angle and the sinking speed of the aircraft body).
The specific method of the step S1 is as follows:
s1-1: dividing a arresting hook model into a hook head, a hook arm, a stabilizer, a universal joint and a longitudinal damper, wherein the hook head and the hook arm are used for building a finite element model by using body grids, and shells of the stabilizer, the universal joint and the longitudinal damper are modeled by adopting shell units and endow the shells with material properties of corresponding materials to form an integral appearance;
s1-2: establishing an inner rod unit of the longitudinal damper, establishing a shell by adopting a shell unit, establishing the longitudinal rod unit in the damper, defining the rod unit material as an elastic beam rod, setting corresponding displacement-external force curve data for the rod unit according to the characteristic requirement of the longitudinal damper, obtaining relevant damping force data through displacement deformation of the rod, and simulating the function of the longitudinal damper;
s1-3: and establishing a rod unit in the stabilizer, wherein the rod unit is defined as an elastic beam, response displacement-external force curve data are set for the rod unit according to the transverse swing reduction requirement of the stabilizer, relevant damping force data are obtained through displacement deformation of the rod, and the function of the stabilizer is simulated.
Preferably, in step S7, the hook head is fixedly connected with the hook arm, the hook arm is slidably connected with the stabilizer, the hook arm is rotatably connected with the universal joint, the universal joint is rotatably connected with the longitudinal damper, the arresting hook is rotatably connected with the machine body, and the machine body is fixedly connected with the landing gear.
In order to facilitate understanding of the above technical solutions of the present invention, the following detailed description of the above technical solutions of the present invention is provided by specific embodiments.
Example 1
The finite element modeling of carrier-based aircraft landing and blocking is performed by considering the process of bouncing the blocking hook and meshing the hook rope for a certain type of carrier-based aircraft, as shown in fig. 4-8. In the analysis process of the simulation results of the bouncing of the arresting hook and the engagement of the hook rope, the longitudinal and transverse bouncing displacement curve change diagrams of the arresting hook in a certain time after the arresting hook collides with a deck in the carrier-based aircraft landing process are focused. In order to achieve the condition of engagement of the hook rope, successful carrier landing blocking of the carrier-based aircraft is generally required that the first longitudinal bouncing height of the blocking hook is not more than 1m and the transverse bouncing displacement is not more than 6.1m.
In this embodiment, as seen from the simulation result graph 2, the maximum longitudinal bouncing height of the arresting hook in the carrier landing process is 0.99m, and the moment occurs after the carrier aircraft lands on the carrier for 0.11 s.
As can be seen from fig. 3, the maximum lateral displacement distance of the arresting hooks during landing is 0.24m, which occurs 1.5s after landing of the carrier-based aircraft. From the simulation results of the embodiment, it can be seen that according to the conditions required to be met by the engagement of the hook ropes, the engagement of the hook ropes can be completed in the carrier landing process, and carrier landing blocking can be successfully realized.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. The method for analyzing the meshing of the blocking hook bouncing and the hook rope in the carrier aircraft carrier landing process is characterized by comprising the following steps of:
s1: establishing a blocking hook model;
s2: establishing a force transmission fuselage model, modeling by adopting a shell unit, and defining the model as a rigid body;
s3: establishing a deck model, modeling a contact area between the arresting hooks and the deck by adopting a body grid, modeling the rest deck parts by adopting shell units, and defining materials as steel;
s4: establishing a blocking cable model, establishing an elastic cable model through discrete spring beam units, simulating the appearance of a cable through a shell unit surrounding the beam units, and judging the contact of a blocking hook cable;
s5: the method comprises the steps of establishing a nose landing gear finite element model, wherein the nose landing gear finite element model is divided into four parts of a tire, a torque arm, a strut and a supporting rod, the torque arm, the strut and the supporting rod are modeled by adopting shell units, and the material is defined as steel; the tire carcass is modeled by adopting a body grid, the material is defined as Ogde rubber, a closed air chamber is defined in the carcass, and the rigidity of the tire air pressure is calibrated, namely, the tire air pressure is checked according to the relation between the tire compression amount and the tire supporting force; modeling the main landing gear by using the same modeling method;
s6: setting an initial dropping speed for a constructed landing gear finite element model in the landing gear earthquake checking process, simulating to obtain a displacement curve of a buffer strut, vertical stress condition of a tire and compression quantity change condition of the tire, comparing the obtained simulation curve with a curve obtained in an actual earthquake testing process, checking that a result obtained by simulation meets the requirement of error accuracy, and determining a landing gear buffering characteristic parameter;
s7: defining a contact relation between the arresting hook and the body and between the arresting hook and the landing gear;
s8: and carrying out finite element calculation and solving on the obtained carrier-borne aircraft carrier landing finite element model, extracting the hook engagement judgment condition, the blocking hook bouncing span and the bouncing height in the calculation result, and carrying out result processing analysis by combining the calculation working condition.
2. The analysis method for the engagement of the arresting hook and the hook rope in the carrier aircraft landing process according to claim 1, wherein the specific method in the step S1 is as follows:
s1-1: dividing a arresting hook model into a hook head, a hook arm, a stabilizer, a universal joint and a longitudinal damper, wherein the hook head and the hook arm are used for building a finite element model by using body grids, and shells of the stabilizer, the universal joint and the longitudinal damper are modeled by adopting shell units and endow the shells with material properties of corresponding materials to form an integral appearance;
s1-2: establishing an inner rod unit of the longitudinal damper, establishing a shell by adopting a shell unit, establishing the longitudinal rod unit in the damper, defining the rod unit material as an elastic beam rod, setting corresponding displacement-external force curve data for the rod unit according to the characteristic requirement of the longitudinal damper, obtaining relevant damping force data through displacement deformation of the rod, and simulating the function of the longitudinal damper;
s1-3: and establishing a rod unit in the stabilizer, wherein the rod unit is defined as an elastic beam, response displacement-external force curve data are set for the rod unit according to the transverse swing reduction requirement of the stabilizer, relevant damping force data are obtained through displacement deformation of the rod, and the function of the stabilizer is simulated.
3. The method for analyzing the jump of the arresting hook and the engagement of the hook rope in the carrier landing process according to claim 1, wherein in the step S7, the hook head is fixedly connected with the hook arm, the hook arm slides with the stabilizer, the hook arm rotates with the universal joint, the universal joint rotates with the longitudinal damper, the arresting hook rotates with the body, and the body is fixedly connected with the landing gear.
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| CN117073957B (en) * | 2023-10-13 | 2024-01-09 | 中国飞机强度研究所 | Ship-borne aircraft load measurement and ship surface characteristic simulation device and method |
| CN117087873B (en) * | 2023-10-20 | 2024-01-05 | 中国飞机强度研究所 | Device and method for measuring collision load of carrier-based aircraft blocking hook landing |
| CN117109505B (en) * | 2023-10-24 | 2024-01-30 | 中国飞机强度研究所 | Method for measuring blocking hook posture and determining space deformation data of carrier-based aircraft |
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| CN104156521A (en) * | 2014-07-31 | 2014-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for designing nose landing gear of aircraft on basis of free flight hooking condition |
| CN105136420A (en) * | 2015-09-07 | 2015-12-09 | 南京航空航天大学 | Comprehensive testing apparatus and testing method for simulating impact of arresting hook to deck and drop shock of undercarriage |
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| JP2003307073A (en) * | 2002-02-12 | 2003-10-31 | Hitoshi Nishitani | Device for preventing bounce of sliding door |
| CN104156521A (en) * | 2014-07-31 | 2014-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for designing nose landing gear of aircraft on basis of free flight hooking condition |
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