CN111368427A - Simulation verification platform for airplane model - Google Patents
Simulation verification platform for airplane model Download PDFInfo
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- CN111368427A CN111368427A CN202010140732.6A CN202010140732A CN111368427A CN 111368427 A CN111368427 A CN 111368427A CN 202010140732 A CN202010140732 A CN 202010140732A CN 111368427 A CN111368427 A CN 111368427A
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Abstract
The invention relates to the technical field of simulation experiments, in particular to an aircraft model simulation verification platform which comprises a base station, a bearing block, a mandril, a motor and a controller, wherein the base station is provided with a bearing block; a bearing block is arranged above the base station, the bearing block moves in the vertical direction and is used for bearing the airplane model, and a corresponding ejector rod is arranged at the tail position of an engine of the airplane model; the support structure fixed on the airplane model interferes with the pneumatic layout of the joint, the measured pneumatic performance is influenced, and meanwhile, the airplane model is in a relatively static state, so that the data of simulation verification is limited; therefore, the ejector rod arranged at the tail part of the airplane model engine is used for performing simulation verification on the pneumatic performance of the acting force generated by the airplane model through the airflow in the wind tunnel, so that the airplane model can be adaptively adjusted in simulation, more perfect pneumatic performance data can be obtained, and the richness and the authenticity of the simulation verification data of the airplane model can be improved.
Description
Technical Field
The invention relates to the technical field of simulation experiments, in particular to an aircraft model simulation verification platform.
Background
With the continuous opening of the aviation field, more and more novel airplanes begin to emerge in succession, and during the airplane design, the needed method is to perform simulation verification on the airplane model, and to use the platform to perform data simulation on the influence of various conditions on the airplane model, so as to verify the airplane model and the design feasibility; the simulation verification is assisted by a computer to establish a virtual flow field model for fluid mechanics simulation, but the precision of the calculation result is usually determined by whether the definitions of boundary conditions, physical property parameters and the like during the preprocessing of the complex flow field simulation are consistent with the reality or not, and whether the calculation method and the postprocessing are accurate or not, and the verification is usually required in a real physical flow field wind tunnel.
Wind tunnels are derived from English "Wind tunnels", Wind Tunnel laboratories simulate the flow of air around aircraft with artificially generated air flows, and make an optimal design by collecting analytical data; the aircraft can be put into use only after repeated tests in a wind tunnel laboratory before test flight, and is an indispensable important part in aircraft development work; for a description of aircraft simulation verification wind tunnels, see Argy Wormwood, NASA wind tunnel laboratory list [ J ]. astronauts 2013 (3): 56-59.
Some technical solutions of an airplane model simulation verification platform also appear in the prior art, for example, a chinese patent with application number 2018115954716 discloses an airplane model simulation verification platform: the simulation device comprises a simulation excitation module and a simulation display module; a simulation model unit in the simulation excitation module is connected with a simulation excitation unit, the simulation excitation unit is connected with a first data management unit, and the first data management unit is respectively connected with a first database and a first data interface management unit; the simulation display unit in the simulation display module is connected with the second data management unit, and the second data management unit is respectively connected with the second database and the second data interface management unit; the first data interface management unit is connected with the second data interface management unit; the first database is connected with the second database; the technical scheme can realize low-cost, quick and extensible verification so as to meet the simulation verification requirements of various airplanes and various devices; the parallel development of system modules is realized, and the development efficiency of the platform is improved; however, the simulation result in the technical scheme can ensure the reliability only by obtaining the verification of a wind tunnel experiment or an actual physical flow field, so that the quality of the simulation verification data of the airplane model in the technical scheme is difficult to ensure.
In view of this, in order to overcome the above technical problems, the present company has designed and developed an aircraft model simulation verification platform, and a special simulation verification platform structure is adopted to solve the above technical problems.
Disclosure of Invention
In order to make up for the defects of the prior art, the invention provides an aircraft model simulation verification platform, which is characterized in that an ejector rod arranged at the tail part of an engine of an aircraft model is used, acting force generated by airflow generated in a wind tunnel on the aircraft model is used, so that the aircraft model only acts with the ejector rod to perform simulation verification on aerodynamic performance, and the aircraft model performs slight adaptive attitude adjustment in the simulation verification by matching with slight change of wind parameters in the wind tunnel, thereby obtaining more perfect aerodynamic performance data and improving the richness and the authenticity of the simulation verification data of the aircraft model.
The invention relates to an aircraft model simulation verification platform which comprises a base station, a bearing block, a mandril, a motor and a controller, wherein the base station is provided with a bearing block; be provided with the pit on the base station, install the expansion bracket in the pit, the top of expansion bracket is equipped with the carrier block: the telescopic frame is driven by a hydraulic rod and controls the movement of the bearing block in the vertical direction; the bearing block is used for bearing the airplane model; an upright post is arranged behind the airplane model, and a mandril is arranged at the tail part of an engine of the airplane model; the head of the ejector rod is in contact with the tail of an engine of the airplane model, and the tail of the ejector rod is fixed on the upright post; the ejector rods correspond to the engine positions of the airplane model one by one, and are fixedly arranged on the base station through the upright posts; the motor drives a fan of the simulation platform to operate, and a wind power source is provided for simulation verification of the airplane model; the controller adjusts the wind power in the simulation verification process by controlling the power of the motor, and drives the bearing block to lift by controlling the action of the hydraulic rod on the telescopic frame; when the airplane model lifting device works, the controller is started, the telescopic frame extends out to enable the bearing block to lift, the airplane model is placed on the bearing block, the position of the adjusting upright post is installed on the base station, the head of the ejector rod is correspondingly attached to the tail position of an engine of the airplane model, the fan is started to operate by controlling the motor, wind blows from the head direction of the airplane model, the interaction between the airplane and the wind during flight is simulated, meanwhile, the telescopic frame retracts gradually to lower the bearing block, the bearing block falls into a pit of the base station, the airplane model is supported by the lifting force of the wind in the vertical direction, and the airplane model is positioned by the ejector rod at the tail position of the engine in the horizontal direction; the method is characterized in that the method comprises the following steps that a support structure is fixedly connected to the middle or the tail of an airplane model in a simulation process to fully measure the pneumatic performance of the airplane model, the support structure fixedly connected to the airplane model interferes with the pneumatic layout of a connection part to influence the pneumatic performance of local measurement, and meanwhile, the airplane model in a wind tunnel is in a relatively static state in simulation verification and cannot acquire dynamic pneumatic performance data of the airplane model, so that the data of the simulation verification is limited; the ejector rod arranged at the tail part of the engine of the airplane model is utilized, the acting force of airflow generated in the wind tunnel on the airplane model is utilized, the airplane model only acts on the ejector rod to perform simulation verification on the pneumatic performance, the ejector rod is selected to act on the tail part of the engine of the airplane model, the power source in the airplane flight is simulated more truly, the simulation interference of a supporting structure on the local pneumatic modeling on the airplane model is avoided, the ejector rod is contacted with the tail part of the engine of the airplane model, and the micro-change of the wind parameter in the wind tunnel is matched, so that the airplane model performs micro-adaptive posture adjustment in the simulation verification, more complete pneumatic performance data is obtained, and the richness and the authenticity of the simulation verification data of the airplane model are improved.
Preferably, the head of the ejector rod is provided with an air bag in a circular truncated cone shape, the small end face of the circular truncated cone-shaped air bag is fixedly connected to the head of the ejector rod, and the large end face of the circular truncated cone-shaped air bag faces the tail of an engine of the airplane model; the middle part of the large end surface of the air bag is sunken and is used for being attached to the tail part of an engine of the airplane model; when the airplane model simulation test device works, the ejector rods are aligned to the positions of the tail parts of the engines of the airplane models, the wind tunnel is started for simulation verification, and due to the difference of the engine models of the airplane models, the corresponding ejector rod heads need different models to be matched and contacted with the positions of the tail parts of the engines of the airplane models, so that the influence of the position deviation of the ejector rod positioning on the simulation verification data is prevented; through setting up the gasbag at ejector pin head round platform form, the middle part of gasbag is sunken to make the ejector pin can be accurate location on aircraft model's engine afterbody position, and simultaneously under wind-tunnel wind-force effect, aircraft model's engine afterbody molding makes the shape of contact surface of gasbag take place to correspond the change to avoid the ejector pin to fix a position the deviation on aircraft model engine afterbody position, promoted aircraft model simulation verification data's richness and authenticity.
Preferably, an air pipe is arranged inside the ejector rod; a miniature air pump is arranged on the upright post; one end of the air pipe is communicated with the air bag, the other end of the air pipe is communicated to the micro air pump through the tail part of the ejector rod, and the micro air pump is provided with a pressure sensor; the pressure sensor feeds back the pressure value of the air bag at the head part of the ejector rod through an air pipe; when the airplane model simulation test device works, the airplane model is positioned in the wind tunnel only through the ejector rod at the tail part of the engine, and airflow parameters in the wind tunnel need to be controlled to ensure that the airplane model simulation test is smoothly carried out; the air bag arranged at the head of the ejector rod can feed back the stress conditions of engines at different positions on the airplane model, the air pressure data of the air bag is fed back to the processing module of the controller through the pressure sensor, and then the size of wind power in the wind tunnel is adjusted through the controller to be within a reasonable range of simulation verification, so that the airplane model in the wind tunnel is prevented from being blown up or falling off in simulation to terminate the verification process, and the richness and the authenticity of simulation verification data of the airplane model are improved.
Preferably, the miniature air pump is provided with an air pressure regulator, and the air pressure regulator is controlled by a controller; the controller can respectively adjust the air pressure value in each air bag through the air pressure regulator; during working, the airplane model needs to simulate various actual conditions in airplane operation in simulation so as to obtain real and comprehensive verification data, and the change of the air flow parameters in the wind tunnel can only be used as the verification of the performance of the airplane model by the change of the external environment, but cannot verify the performance of the airplane model by changing the parameters of the airplane model; the controller controls the air pressure regulator on the miniature air pump, so that the air bags at the heads of the ejector rods have different air pressure values, the action conditions of the engines of the airplane under different working conditions are simulated, the influence on the overall aerodynamic performance of the airplane model is also simulated, and the richness and the authenticity of simulation verification data of the airplane model are improved.
Preferably, the tail section of the ejector rod is provided with threads, the ejector rod is rotatably installed on the upright post through the threads, and a positioning nut is arranged at the contact position of the ejector rod outside the upright post; when the airplane model simulation verification platform works, the extending length of the ejector rod on the stand column is adjusted through rotation so as to be suitable for engine positions of airplane models of different models, the positioned ejector rod is limited by the arranged positioning nut, the accurate control of the action position of the ejector rod in airplane model simulation is ensured, and the universality range of the airplane model simulation verification platform is expanded.
Preferably, a base is arranged below the upright column, supporting rods are arranged at three positions on the base, and the base is connected with the upright column through the supporting rods; the upper end of the supporting rod is provided with a fixed spherical joint which is rotatably arranged in a spherical hole at the bottom of the upright post; the lower end of the supporting rod is positioned in a hole groove in the base, and a servo motor is arranged at the bottom of the hole groove; a screw pair is arranged in the supporting rod, and the screw pair is driven by a servo motor to enable the supporting rod to lift on the base; during operation, the airplane model needs to be positioned in different postures in simulation to simulate the take-off, landing and rotation processes in the operation of the airplane, and the airplane model needs to be adjusted in the wind tunnel for multiple times until the required posture is reached to carry out flight simulation verification, so that the simulation verification efficiency of the airplane model is reduced, and the workload is increased; the servo motor is controlled to operate by the controller, so that the supporting rods are respectively lifted to different heights, the upright column is inclined, the ejector rod changes in posture, the airplane model can change in posture in different motion processes, and the richness and authenticity of the simulation verification data of the airplane model are improved.
The invention has the following beneficial effects:
1. the invention uses the ejector rod arranged at the tail part of the engine of the airplane model and the acting force generated by the airflow generated in the wind tunnel on the airplane model to ensure that the airplane model only acts with the ejector rod to carry out simulation verification on the pneumatic performance, selects the ejector rod to act on the tail part of the engine of the airplane model, more truly simulates the power source in the airplane flight, avoids the simulation interference of a supporting structure on the local pneumatic modeling on the airplane model, ensures that the shape of the tail part of the engine of the airplane model and the shape of the contact surface of the air bag are correspondingly changed through the circular truncated cone-shaped air bag arranged at the head part of the ejector rod, avoids the deviation of the positioning position of the ejector rod, controls the air pressure regulator on the miniature air pump through the arranged controller, ensures that the air bag at the head part of each ejector rod has different air pressure values to simulate the action condition of each engine of the, the richness and the authenticity of the simulation verification data of the airplane model are improved.
2. The ejector rod after being adjusted and positioned is limited by the positioning nut so as to be suitable for engine positions on airplane models of different models, the precise control of the action position of the ejector rod in the airplane model simulation is ensured, the set controller controls the servo motor to operate, the supporting rods are respectively lifted to different heights, the upright post is further changed in an inclined angle, the ejector rod is changed in posture, the airplane model can conveniently change in posture in different motion processes, and the richness and the authenticity of simulation verification data of the airplane model are improved.
Drawings
The invention is further described with reference to the following figures and embodiments.
FIG. 1 is a perspective view of a simulation verification platform of the present invention;
FIG. 2 is a front view of the simulation verification platform of the present invention;
FIG. 3 is an enlarged view of a portion of FIG. 2 at A;
FIG. 4 is a schematic view of the structure of the base of the present invention;
in the figure: the device comprises a base platform 1, a pit 11, an expansion bracket 12, a bearing block 2, a mandril 3, an air bag 31, an air pipe 32, a positioning nut 33, a stand column 4, a micro air pump 5, an air pressure regulator 51, a base 6, a support rod 61, a spherical joint 611, a servo motor 62 and a screw pair 63.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
As shown in fig. 1 to 4, the aircraft model simulation verification platform of the present invention includes a base station 1, a bearing block 2, a lift pin 3, a motor and a controller; be provided with pit 11 on the base station 1, install expansion bracket 12 in the pit 11, the top of expansion bracket 12 is equipped with carrier block 2: the telescopic frame 12 is driven by a hydraulic rod and controls the bearing block 2 to move in the vertical direction; the bearing block 2 is used for bearing an airplane model; an upright post 4 is arranged at the rear part of the airplane model, and a mandril 3 is arranged at the tail part of an engine of the airplane model; the head of the ejector rod 3 is in contact with the tail of an engine of the airplane model, and the tail of the ejector rod 3 is fixed on the upright post 4; the ejector rods 3 correspond to the engine positions of the airplane model one by one, and the ejector rods 3 are fixedly arranged on the base platform 1 through the upright posts 4; the motor drives a fan of the simulation platform to operate, and a wind power source is provided for simulation verification of the airplane model; the controller adjusts the wind power in the simulation verification process by controlling the power of the motor, and drives the bearing block 2 to lift by controlling the action of the hydraulic rod on the telescopic frame 12; when the airplane model lifting device works, the controller is started, the telescopic frame 12 extends out to enable the bearing block 2 to lift, the airplane model is placed on the bearing block 2, the position of the adjusting upright post 4 is installed on the base platform 1, the head of the ejector rod 3 is correspondingly attached to the tail position of an engine of the airplane model, the fan is started to operate by controlling the motor, wind blows from the head direction of the airplane model, the interaction between the airplane and the wind during flying is simulated, meanwhile, the telescopic frame 12 is gradually retracted to descend the bearing block 2, the bearing block 2 falls into the pit 11 of the base platform 1, the airplane model is supported by the lifting force of the wind in the vertical direction, and the airplane model is positioned by the ejector rod 3 at the tail position of the engine in the horizontal direction; the method is characterized in that the method comprises the following steps that a support structure is fixedly connected to the middle or the tail of an airplane model in a simulation process to fully measure the pneumatic performance of the airplane model, the support structure fixedly connected to the airplane model interferes with the pneumatic layout of a connection part to influence the pneumatic performance of local measurement, and meanwhile, the airplane model in a wind tunnel is in a relatively static state in simulation verification and cannot acquire dynamic pneumatic performance data of the airplane model, so that the data of the simulation verification is limited; the ejector rod 3 arranged at the tail part of the engine of the airplane model is utilized, the acting force of airflow generated in the wind tunnel on the airplane model is utilized, the airplane model only acts on the ejector rod 3 to perform simulation verification on the pneumatic performance, the ejector rod 3 is selected to act on the tail part of the engine of the airplane model, the power source in the airplane flight is simulated more truly, the simulation interference of a support structure on the local pneumatic modeling on the airplane model is avoided, the ejector rod 3 is in contact with the tail part of the engine of the airplane model, and the micro-change of the wind parameter in the wind tunnel is matched, so that the airplane model performs micro-adaptive posture adjustment in the simulation verification, more complete pneumatic performance data is obtained, and the richness and the authenticity of the simulation verification data of the airplane model are improved.
As an embodiment of the invention, the head of the ejector rod 3 is provided with an air bag 31, the air bag 31 is in a circular truncated cone shape, the small end face of the circular truncated cone-shaped air bag 31 is fixedly connected to the head of the ejector rod 3, and the large end face of the circular truncated cone-shaped air bag 31 faces to the tail of an engine of an airplane model; the middle part of the large end face of the air bag 31 is sunken and is used for being attached to the tail part of an engine of an airplane model; when the device works, the ejector rods 3 are aligned to the engine tail positions of the airplane models, the wind tunnel is started for simulation verification, and due to the engine modeling difference of the airplane models of various types, the heads of the corresponding ejector rods 3 need different modeling to be matched and contacted with the engine tail positions of the airplane models, so that the influence of the position deviation of the ejector rods 3 on the simulation verification data is prevented; through setting up the gasbag 31 at 3 head round platform forms of ejector pin, the middle part of gasbag 31 is sunken to make ejector pin 3 can be accurate location on aircraft model's engine afterbody position, and simultaneously under wind-tunnel wind-force effect, aircraft model's engine afterbody molding makes gasbag 31's shape of contact surface take place to correspond the change to avoid 3 deviations of ejector pin location on aircraft model engine afterbody position, promoted aircraft model simulation verification data's richness and authenticity.
As an embodiment of the present invention, an air pipe 32 is provided inside the top rod 3; a miniature air pump 5 is arranged on the upright post 4; one end of the air pipe 32 is communicated with the air bag 31, the other end of the air pipe 32 is communicated to the micro air pump 5 through the tail part of the ejector rod 3, and the micro air pump 5 is provided with a pressure sensor; the pressure sensor feeds back the pressure value of the air bag 31 at the head of the mandril 3 through an air pipe 32; when the airplane model simulation test device works, the airplane model is positioned in the wind tunnel only through the ejector rod 3 at the tail part of the engine, and airflow parameters in the wind tunnel need to be controlled to ensure that the airplane model simulation test is smoothly carried out; the air bag 31 arranged at the head of the ejector rod 3 can feed back the engine stress conditions of different positions on the airplane model, the air pressure data of the air bag 31 is fed back to the processing module of the controller through the pressure sensor, and then the wind power in the wind tunnel is adjusted through the controller to be within a reasonable range of simulation verification, so that the airplane model in the wind tunnel is prevented from being blown up or falling off in simulation to terminate the verification process, and the richness and the authenticity of the simulation verification data of the airplane model are improved.
As an embodiment of the present invention, an air pressure regulator 51 is disposed on the micro air pump 5, and the air pressure regulator 51 is controlled by a controller; the controller can respectively adjust the air pressure value in each air bag 31 through the air pressure regulator 51; during working, the airplane model needs to simulate various actual conditions in airplane operation in simulation so as to obtain real and comprehensive verification data, and the change of the air flow parameters in the wind tunnel can only be used as the verification of the performance of the airplane model by the change of the external environment, but cannot verify the performance of the airplane model by changing the parameters of the airplane model; the controller controls the air pressure regulator 51 on the miniature air pump 5, so that the air bags 31 at the heads of the ejector rods 3 have different air pressure values, the action conditions of the engines of the airplane under different working conditions are simulated, the influence on the overall aerodynamic performance of the airplane model is also simulated, and the richness and the authenticity of simulation verification data of the airplane model are improved.
As an embodiment of the invention, the tail section of the ejector rod 3 is provided with a thread, the ejector rod 3 is rotatably installed on the upright post 4 through the thread, and the contact part of the ejector rod 3 outside the upright post 4 is provided with a positioning nut 33; when the airplane model simulation verification platform works, the extending length of the ejector rod 3 on the upright post 4 is adjusted through rotation so as to be suitable for engine positions of airplane models of different models, the positioned ejector rod 3 is limited by the arranged positioning nut 33, the accurate control of the action position of the ejector rod 3 in airplane model simulation is ensured, and the universality range of the airplane model simulation verification platform is improved.
As an embodiment of the present invention, a base 6 is arranged below the upright 4, support rods 61 are arranged at three positions on the base 6, and the base 6 is connected with the upright 4 through the support rods 61; the upper end of the supporting rod 61 is provided with a fixed spherical joint 611, and the spherical joint 611 is rotatably arranged in a spherical hole at the bottom of the upright post 4; the lower end of the support rod 61 is positioned in a hole groove in the base 6, and the bottom of the hole groove is provided with a servo motor 62; a screw pair 63 is arranged in the supporting rod 61, and the screw pair 63 is driven by a servo motor 62 to enable the supporting rod 61 to lift on the base 6; during operation, the airplane model needs to be positioned in different postures in simulation to simulate the take-off, landing and rotation processes in the operation of the airplane, and the airplane model needs to be adjusted in the wind tunnel for multiple times until the required posture is reached to carry out flight simulation verification, so that the simulation verification efficiency of the airplane model is reduced, and the workload is increased; the servo motor 62 is controlled to operate through the controller that sets up for bracing piece 61 raises different heights respectively, and then makes stand 4 be the angle change of slope, and the gesture change also takes place thereupon for ejector pin 3, and the aircraft model of being convenient for is at the gesture change of different motion in-process self, has promoted the richness and the authenticity of aircraft model simulation verification data.
When the airplane model lifting device works, the controller is started, the telescopic frame 12 extends out to enable the bearing block 2 to lift, the airplane model is placed on the bearing block 2, the position of the adjusting upright post 4 is installed on the base platform 1, the head of the ejector rod 3 is correspondingly attached to the tail position of an engine of the airplane model, the fan is started to operate by controlling the motor, wind blows from the head direction of the airplane model, the interaction between the airplane and the wind during flying is simulated, meanwhile, the telescopic frame 12 is gradually retracted to descend the bearing block 2, the bearing block 2 falls into the pit 11 of the base platform 1, the airplane model is supported by the lifting force of the wind in the vertical direction, and the airplane model is positioned by the ejector rod 3 at the tail position of the engine in the horizontal direction; the ejector rod 3 is arranged at the tail part of the engine of the airplane model, the airplane model only acts with the ejector rod 3 to perform simulation verification on the pneumatic performance through the acting force of airflow generated in the wind tunnel on the airplane model, and the airplane model performs micro adaptive attitude adjustment in the simulation verification by contacting the ejector rod 3 with the tail part of the engine of the airplane model and matching with the micro change of the wind parameter in the wind tunnel, so that more complete pneumatic performance data is obtained; the air bag 31 is arranged at the head of the ejector rod 3 and is in a circular truncated cone shape, the middle part of the air bag 31 is sunken, so that the ejector rod 3 can be accurately positioned at the tail position of an engine of the airplane model, and meanwhile, under the action of wind force in a wind tunnel, the shape of the tail part of the engine of the airplane model is correspondingly changed, so that the deviation of the ejector rod 3 positioned at the tail position of the engine of the airplane model is avoided; the air bag 31 arranged at the head of the ejector rod 3 can feed back the stress conditions of engines at different positions on the airplane model, the air pressure data of the air bag 31 is fed back to the processing module of the controller through the pressure sensor, and then the controller adjusts the wind power in the wind tunnel to be within a reasonable range of simulation verification so as to prevent the airplane model in the wind tunnel from being blown up or falling off in simulation to terminate the verification process; a controller is arranged to control an air pressure regulator 51 on the miniature air pump 5, so that the air bags 31 at the heads of the ejector rods 3 have different air pressure values to simulate the action conditions of the engines of the airplane under different working conditions; the set positioning nut limits the mandril after the adjustment and the positioning, thereby ensuring the accurate control of the action position of the mandril 3 in the simulation of the airplane model; the controller control servo motor 62 that sets up moves for bracing piece 61 raises different heights respectively, and then makes stand 4 be the angle change of slope, and ejector pin 3 also takes place the gesture thereupon and changes, and the aircraft model of being convenient for is at the gesture change of different motion in-process self, has promoted the richness and the authenticity of aircraft model simulation verification data.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. An aircraft model simulation verification platform comprises a base station (1), a bearing block (2), a mandril (3), a motor and a controller; the method is characterized in that: be provided with pit (11) on base station (1), install expansion bracket (12) in pit (11), the top of expansion bracket (12) is equipped with carrier block (2): the telescopic frame (12) is driven by a hydraulic rod and controls the bearing block (2) to move in the vertical direction; the bearing block (2) is used for bearing an airplane model; an upright post (4) is arranged behind the airplane model, and a mandril (3) is arranged at the tail part of an engine of the airplane model; the head of the ejector rod (3) is in contact with the tail of an engine of the airplane model, and the tail of the ejector rod (3) is fixed on the upright post (4); the ejector rods (3) correspond to the engine positions of the airplane model one by one, and the ejector rods (3) are fixedly arranged on the base station (1) through the upright posts (4); the motor drives a fan of the simulation platform to operate, and a wind power source is provided for simulation verification of the airplane model; the controller adjusts the wind power in the simulation verification process by controlling the power of the motor, and drives the bearing block (2) to lift by controlling the action of the hydraulic rod on the telescopic frame (12).
2. An aircraft model simulation verification platform according to claim 1, wherein: the head of the ejector rod (3) is provided with an air bag (31), the air bag (31) is in a circular truncated cone shape, the small end face of the circular truncated cone-shaped air bag (31) is fixedly connected to the head of the ejector rod (3), and the large end face of the circular truncated cone-shaped air bag (31) faces the tail of an engine of the airplane model; the middle part of the large end face of the air bag (31) is sunken and is used for being attached to the tail part of an engine of the airplane model.
3. An aircraft model simulation verification platform according to claim 2, wherein: an air pipe (32) is arranged in the ejector rod (3); a miniature air pump (5) is arranged on the upright post (4); one end of the air pipe (32) is communicated with the air bag (31), the other end of the air pipe (32) is communicated to the micro air pump (5) through the tail part of the ejector rod (3), and the micro air pump (5) is provided with a pressure sensor; the pressure sensor feeds back the pressure value of the air bag (31) at the head of the mandril (3) through an air pipe (32).
4. An aircraft model simulation verification platform according to claim 3, wherein: an air pressure regulator (51) is arranged on the micro air pump (5), and the air pressure regulator (51) is controlled by a controller; the controller can respectively adjust the air pressure value in each air bag (31) through an air pressure regulator (51).
5. An aircraft model simulation verification platform according to claim 2, wherein: the tail section of the ejector rod (3) is provided with threads, the ejector rod (3) is rotatably installed on the upright post (4) through the threads, and the contact part of the ejector rod (3) outside the upright post (4) is provided with a positioning nut (33).
6. An aircraft model simulation verification platform according to claim 5, wherein: a base (6) is arranged below the upright post (4), supporting rods (61) are arranged at three positions on the base (6), and the base (6) is connected with the upright post (4) through the supporting rods (61); the upper end of the supporting rod (61) is provided with a fixed spherical joint (611), and the spherical joint (611) is rotatably arranged in a spherical hole at the bottom of the upright post (4); the lower end of the supporting rod (61) is positioned in a hole groove in the base (6), and a servo motor (62) is arranged at the bottom of the hole groove; a screw pair (63) is arranged in the supporting rod (61), and the screw pair (63) is driven by a servo motor (62) to enable the supporting rod (61) to lift on the base (6).
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| CN202010140732.6A CN111368427A (en) | 2020-03-03 | 2020-03-03 | Simulation verification platform for airplane model |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113978756A (en) * | 2021-10-09 | 2022-01-28 | 西北工业大学 | Large component barrel section butt joint experiment table and butt joint method based on trial assembly simulation |
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