CN111681492B - Centrifugal flight load and illusion analogue means - Google Patents
Centrifugal flight load and illusion analogue means Download PDFInfo
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- CN111681492B CN111681492B CN202010718304.7A CN202010718304A CN111681492B CN 111681492 B CN111681492 B CN 111681492B CN 202010718304 A CN202010718304 A CN 202010718304A CN 111681492 B CN111681492 B CN 111681492B
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- 206010021143 Hypoxia Diseases 0.000 description 1
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- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
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Abstract
The invention relates to the technical field of simulated flight, and particularly discloses a centrifugal flight load and illusion simulation device which comprises a transmission supporting system, a rotating arm system, a yaw frame system, a pitching frame system and a cabin system, wherein the transmission supporting system supports the rotating arm system, the pitching frame system is arranged on the rotating arm system and drives the pitching frame system to rotate around a connection point with the rotating arm system, the yaw frame system is arranged on the pitching frame system, the pitching frame system drives the yaw frame system to rotate around a connection point with the yaw frame system, the cabin system is arranged on the yaw frame system, and the yaw frame system drives the cabin system to rotate around a connection point with the yaw frame system. The invention has the advantages that the main shaft rotates to generate overload acceleration, three degrees of freedom of yaw, pitch and roll relative to a human body coordinate system are generated at the tail end of the rotating arm, and a trained pilot sits in a seat cabin system and bears centrifugal overload acceleration and three spatial attitude angle motions, so that the simulation training of the space orientation disorder is realized.
Description
Technical Field
The invention relates to the technical field of simulated flight, in particular to a centrifugal flight load and illusion simulation device.
Background
A centrifugal flight load and space orientation obstacle simulator is based on a centrifugal platform, continuous overload acceleration is generated by rotation of a centrifugal machine, a three-degree-of-freedom rotating frame system is arranged at the tail end of the centrifugal machine, accurate simulation of load values and directions can be achieved, and meanwhile gesture simulation under an overload environment can be conducted.
Flight load simulation can train pilots' anti-overload capabilities. In the process of maneuver flight of a high-performance fighter, when overlarge head-foot overload occurs, brain tissue hypoxia caused by reduced brain blood supply is caused, and then gray vision, blackness and even loss of consciousness of a pilot are caused, so that flight accidents are extremely easy to cause. The improvement of overload resistance requires that the pilot has to grasp certain overload resistance actions, which are performed on special equipment, in addition to equipment guarantees.
Space orientation disorders are yet another significant aviation medical problem that currently severely threatens flight safety, with a high probability of occurrence, and can be encountered by both skilled pilots and novice pilots, whatever model may occur. And is particularly likely to occur in environments where vision is limited, such as in the night, haze, etc. The space orientation obstacle easily induces the pilot to judge the position and the posture of the pilot to be incorrect, thereby causing the flight accident. The training of the spatial orientation disorder is carried out, namely, the simulator is used for generating an environment which is easy to generate the spatial orientation disorder, so that a pilot is helped to correctly recognize the spatial orientation disorder, take measures for preventing the spatial orientation disorder and actively overcome the spatial orientation disorder.
The prior art comprises the following steps:
at present, patent number CN201821463335.7 discloses a "four-degree-of-freedom helicopter dynamic flight simulator", which describes a four-degree-of-freedom platform based on a centrifuge platform, and the functions of the platform are similar to those of the technical scheme of the present invention.
However, the four-degree-of-freedom helicopter dynamic flight simulator in the patent adopts a double-layer layout structure, namely, a main driving motor and a speed reducer are positioned at the next layer, and special basements are needed for arrangement, so that the defects of complex civil construction, high cost and high equipment installation and debugging difficulty are caused.
The cabin centroid position and the main shaft bearing point of the patent are positioned on two planes, so that the yaw frame bears overlarge overturning moment, meanwhile, the rotating arm is greatly stressed by bending moment, the rotating arm deforms when the motion is intensified, and meanwhile, the yaw frame is required to have enough strength and rigidity, so that the weight of the yaw frame is increased.
The counterweight and the mass center of the cabin system of the patent are not in a line parallel to the ground, so that a couple imbalance is formed, vibration is easily caused, and the bearing is severely stressed.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a centrifugal flying load and illusion simulation device.
The aim of the invention is achieved by the following technical scheme: the utility model provides a centrifugal flight load and illusion analogue means, includes transmission supporting system, rocking arm system, yaw frame system, every single move frame system and cabin system, transmission supporting system supports and drives its rotation to produce overload acceleration to the rocking arm system, set up every single move frame system on the rocking arm system and drive every single move frame system and rotate around the tie point with the rocking arm system, every single move frame system's rotation center perpendicular to transmission supporting system rotation center realizes the every single move motion of system, yaw frame system sets up on every single move frame system, and every single move frame system drives yaw frame system and rotates around the tie point with yaw frame system, and the rotation center of yaw frame system perpendicular to pitch frame system realizes the yaw motion of system, the cabin system sets up on yaw frame system, and yaw frame system drives the cabin system and rotate around the tie point with yaw frame system, and the rotation center of cabin system perpendicular to yaw frame system realizes the roll motion of system.
Specifically, the transmission supporting system comprises a base and a main motor, wherein the main motor is arranged at the bottom of the base, a main shaft mounting hole is formed in the base, the output end of the main motor is connected with a main shaft, the main shaft is arranged in the main shaft mounting hole, a bearing system is arranged in the main shaft mounting hole, and the main shaft is rotationally connected with the base through the bearing system.
Specifically, the rocking arm system includes cantilever crane, driving motor, rotation axis, reduction gear, the one end of cantilever crane with main shaft fixed connection, the other end of cantilever crane is provided with the rotation axis mounting hole, the rotation axis mounting hole level sets up, driving motor's output is connected the input of reduction gear, the rotation axis is connected to the output of reduction gear, the rotation axis is arranged in the rotation axis mounting hole and is connected with the cantilever crane rotation.
Specifically, every single move frame system includes every single move frame, yaw driving motor, yaw drive shaft, yaw driven shaft, every single move frame and rotation axis fixed connection, be provided with yaw drive shaft mounting hole and yaw driven shaft mounting hole on the every single move frame with one heart, and yaw drive shaft mounting hole and yaw driven shaft mounting hole's axial lead perpendicular to rotation axis, yaw driving motor fixes on every single move frame, and its output is connected yaw drive shaft, yaw drive shaft is arranged in yaw drive shaft mounting hole and rather than rotating connection, yaw driven shaft is arranged in yaw driven shaft mounting hole and rather than rotating connection.
Specifically, yaw frame system include yaw frame, cabin driving motor, cabin driven shaft, cabin drive shaft, yaw frame is annular symmetrical structure, yaw frame's outside respectively with yaw drive shaft and yaw driven shaft fixed connection, yaw frame is last to wearing to be provided with cabin driven shaft mounting hole and cabin drive shaft mounting hole along the center of symmetry, cabin driving motor fixes on yaw frame, cabin driving motor's output connection cabin drive shaft, the cabin drive shaft is arranged in the cabin drive shaft mounting hole to rotate rather than being connected, the cabin driven shaft is arranged in the cabin driven shaft mounting hole to rotate rather than being connected.
Specifically, cabin system includes cabin body, screen, instrument desk, seat, the outside of cabin body respectively with cabin drive shaft and cabin driven shaft fixed connection, screen, camera, seat all set up in the cabin body.
Specifically, the bearing system comprises a bearing sleeve, a first ball bearing, a first thrust ball bearing and a first angular contact bearing, wherein the bearing sleeve is fixed in a main shaft mounting hole, and the bearing sleeve, the ball bearing, the first thrust ball bearing and the first angular contact bearing are all arranged in the bearing sleeve, so that a rotating pair is formed between the main shaft and the base.
Specifically, the cantilever crane on be provided with the connecting hole, the connecting hole in be provided with and connect the cover that expands, connect the cover that expands and establish on the main shaft, the cantilever crane is through connecting cover and main shaft fixed connection, the tip of cantilever crane and main shaft fixed connection's one end still is provided with the counter weight, be provided with second angular contact bearing, second thrust bearing, second ball bearing in the rotation axis mounting hole, the rotation axis passes through second angular contact bearing, second thrust bearing, second ball bearing and cantilever crane rotation connection.
Specifically, the pitching frame is of a U-shaped structure, two sides of the pitching frame are symmetrically provided with connecting lugs, the yaw driving shaft mounting hole and the yaw driven shaft mounting hole are respectively arranged on one connecting lug, the pitching frame is also provided with a fixed mounting hole, the rotating shaft is arranged in the fixed mounting hole and is fixedly connected with the pitching frame through a fixed expansion sleeve, and one end of the rotating shaft is also provided with a clamp for positioning the pitching frame; the yaw driving shaft installation hole in be provided with third angular contact bearing, yaw driving shaft is connected with every single move frame rotation through third angular contact bearing, yaw driven shaft installation hole in be provided with fourth angular contact bearing, yaw driven shaft is connected with every single move frame rotation through fourth angular contact bearing.
Specifically, be provided with the axle sleeve in the cabin drive shaft mounting hole, be provided with fifth angular contact bearing in the axle sleeve, the cabin drive shaft passes through fifth angular contact bearing and is connected with the axle sleeve rotation, forms the revolute pair with yaw frame, the cabin driven shaft mounting hole in be provided with the bearing housing, be provided with sixth angular contact bearing in the bearing housing, the cabin driven shaft passes through sixth angular contact bearing and is connected with the bearing housing rotation, forms the revolute pair with yaw frame.
The invention has the following advantages:
1. The cabin system, the yaw frame system, the pitch frame system and the jib system are designed to be in axisymmetric structures or approximate axisymmetric structures, and balance weights are carried out, so that force balance and couple balance are achieved. The huge bending moment caused by the excessive centrifugal force generated by the motion is reduced to aggravate the vertical deformation of the rotating arm.
2. The arm support in the rotating arm system is connected with the pitching frame system through the rotating shaft, and a shafting consisting of the second angular contact bearing, the second thrust bearing and the second ball bearing can bear the composite load of axial force, radial force and bending moment, and the shafting bears the bending moment effect generated by the axial force and gravity generated by the cabin system, the yawing frame system and the pitching frame system in a centrifugal field. The axial force is more than 6 times of gravity, so that the bearing capacity of the thrust bearing can be fully exerted, the span between the bearings is reduced, the compact arrangement of the shafting is realized, the defect of severe bearing stress caused by a single-point supporting structure can be overcome, the cost is reduced by replacing a more special bearing with a plurality of conventional bearing groups, the main stress in the prior art is changed from bending moment to main stress to axial force, and the bearing stress is reasonably matched.
3. The pitching frame in the pitching frame system is provided with a fork-shaped structure or a half-frame structure, two ends of a connecting fork lug in the pitching frame are provided with shafting composed of paired angular contact bearings and paired angular contact bearings, so that two-point support of the yawing frame system is realized, and the yawing frame is prevented from bearing overlarge overturning moment in the moving process.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic diagram of the drive support system and swivel arm system of the present invention;
FIG. 3 is a schematic view of a pitch frame system according to the present invention;
FIG. 4 is a schematic diagram of the yaw frame system and the cabin system of the present invention;
FIG. 5 is a schematic view of a clip structure of the present invention;
In the figure: 1-cabin system, 11-cabin body, 12-cabin door, 13-instrument desk, 14-screen, 15-seat, 2-yaw frame system, 21-yaw frame, 22-cabin drive motor, 23-cabin drive shaft, 24-cabin driven shaft, 25-bushing, 26-fifth angle contact bearing, 27-sixth angle contact bearing, 28-cabin driven shaft slip ring, 29-bearing bushing, 3-pitch frame system, 31-pitch frame, 32-yaw drive motor, 33-yaw drive shaft, 34-yaw driven shaft, 35-yaw driven shaft slip ring, 36-connection lug, 37-fourth angle contact bearing, 38-third angle contact bearing, 4-boom system, 41-boom system, 42-drive motor, 43-decelerator, 44-rotation shaft, 45-second angle contact bearing, 46-second thrust bearing, 47-second ball bearing, 48-clip, 5-drive support system, 51-base, 52-main motor, 53-spindle, 54-bearing bushing, 55-first ball bearing, 56-first angle contact bearing, 57-first angle contact bearing, 58-third angle contact bearing, 4-second thrust bearing, 46-second angle contact bearing, 7-brake, 7-cabin brake system.
Detailed Description
For the purpose of making the technical solution and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings and examples. It should be understood that the particular embodiments described herein are illustrative only and are not intended to limit the invention, i.e., the embodiments described are merely some, but not all, of the embodiments of the invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by a person skilled in the art without making any inventive effort, are intended to be within the scope of the present invention.
It is noted that relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article or apparatus that comprises the element.
The present invention will be further described with reference to the accompanying drawings, but the scope of the present invention is not limited to the following.
As shown in fig. 1 to 5, the centrifugal flying load and illusion simulation device comprises a transmission supporting system 5, a swinging arm system 4, a yaw frame system 2, a pitching frame system 3 and a cabin system 1, wherein the transmission supporting system 5 supports and drives the swinging arm system 4 to rotate to generate overload acceleration, the swinging arm system 4 is provided with the pitching frame system 3 and drives the pitching frame system 3 to rotate around a connection point with the swinging arm system 4, the rotation center of the pitching frame system 3 is perpendicular to the rotation center of the transmission supporting system 5, pitching movement of the system is realized, the yaw frame system 2 is arranged on the pitching frame system 3, the pitching frame system 3 drives the yaw frame system 2 to rotate around a connection point with the yaw frame system 2, the rotation center of the yaw frame system 2 is perpendicular to the rotation center of the pitch frame system 3, yaw movement of the system is realized, the cabin system 1 is arranged on the yaw frame system 2, and the yaw frame system 2 drives the cabin system to rotate around the connection point with the yaw frame system 2, and the rotation center of the cabin system 1 is perpendicular to the rotation center of the yaw frame system 2, so that rolling movement of the system is realized. The yaw frame system 2, the pitch frame system 3 and the cabin system 1 are arranged at one end, far away from the connection with the transmission supporting system 5, of the boom system 4, three degrees of freedom of yaw, pitch and roll relative to a human body coordinate system are generated, all rotating shafts 44 can continuously rotate, a trained pilot sits in the cabin system 1 and bears centrifugal overload acceleration and three angular motions in space, and simulation training of space orientation disorder is realized; the centrifugal flying load and illusion simulation device in the scheme adopts a single-layer layout, all elements are positioned on one floor, a transmission bearing system 5 supports a rotating arm system 4 and provides rotating power to drive the rotating arm system 4 to do rotating motion in a horizontal plane, the rotation center of the transmission bearing system 5 is in a vertical direction, a pitching frame system 3 is arranged at one end of the rotating arm system 4 far away from the transmission bearing system 5, the pitching frame system 4 is driven to do pitching motion while rotating horizontally, and the rotation center of the pitching frame system 3 is in a horizontal direction; simultaneously every single move frame system 3 can drive yaw frame system 2 rotation, yaw frame system 2's rotation center is vertical direction, yaw frame system 2 drives cabin system 1 pivoted rotation center is the horizontal direction, cabin system 1 in this scheme, yaw frame system 2, every single move frame system 3, rocking arm system 4 all design into axisymmetric structure, and carry out counter weight 7 and balance, make each free fulcrum of movement all be located approximately in being on a parallel with the coplanar on ground simultaneously, accomplish force balance and couple balance simultaneously, reduce the too big centrifugal force that the motion produced and lead to huge moment of flexure aggravate rocking arm vertical deformation, can reduce the overturning moment and the rocking arm moment of flexure that yaw frame system 2 bore, reduce rocking arm vertical deformation, simultaneously reduce the vibration of system.
Further, the transmission supporting system 5 includes a base 51 and a main motor 52, the main motor 52 is disposed at the bottom of the base 51, a main shaft mounting hole is disposed on the base 51, an output end of the main motor 52 is connected with a main shaft 53, the main shaft 53 is disposed in the main shaft mounting hole, a bearing system is disposed in the main shaft mounting hole, and the main shaft 53 is rotatably connected with the base 51 through the bearing system. In the scheme, the main motor 52 adopts a direct-drive motor, the base 51 is of a conical structure, the edge of the bottom of the base is fixed on a civil engineering foundation through foundation bolts, the main motor 52 is arranged in the bottom of the base 51, single-layer layout of the system is achieved, the civil engineering construction difficulty and cost can be reduced, products can be conveniently installed and debugged, a stator of the main motor 52 is fixed on the base 51 through screws, a rotor of the main motor 52 is connected with the main shaft 53 through a coupler, the coupler is connected with the main shaft 53 through an expansion sleeve, one end of the main shaft 53 is further connected with a slip ring rotor of a slip ring of the main motor through a structure with bolts at a spigot, a slip ring stator of the slip ring of the main motor is fixed on the motor stator through ropes, chains and steel sticks, a brake 58 is further arranged on the base 51, the brake 58 passes through the spigot to be fixed on the base 51 through screws, the main shaft 53 passes through the brake 58, and the brake 58 is braked through the clasping main shaft 53.
Further, the boom system 4 includes a boom 41, a driving motor 42, a rotation shaft 44, and a decelerator 43, one end of the boom 41 is fixedly connected with the main shaft 53, the other end of the boom 41 is provided with a rotation shaft mounting hole, the rotation shaft mounting hole is horizontally arranged, an output end of the driving motor 42 is connected with an input end of the decelerator 43, an output end of the decelerator 43 is connected with the rotation shaft 44, and the rotation shaft 44 is disposed in the rotation shaft mounting hole and is rotatably connected with the boom 41. In the scheme, the top of the arm support 41 is provided with a structure with protruding two ends and a concave middle, wherein a rotating shaft mounting hole is formed in a protrusion at one end of the arm support 41, a driving motor 42 and a speed reducer 43 are mounted at a concave part of the arm support 41 through bolts, an output shaft of the driving motor 42 is connected with an output shaft of the speed reducer 43 through a coupler, the scheme further comprises a speed reducer slip ring, a rotor of the speed reducer slip ring is fixed at one end of the output shaft of the speed reducer 43 through a screw, a speed reducer slip ring stator is fixed on a shell of the speed reducer 43 through a rope or rod structure, and the other end of the output shaft of the speed reducer 43 is provided with a flange structure and is connected with one end of a rotating shaft 44 through a screw; a second angular contact bearing 45, a second thrust bearing 46 and a second ball bearing 47 are arranged in the rotating shaft mounting hole, so that the rotating shaft 44 and the arm support 41 form a revolute pair, the inner rings of the second angular contact bearings 45 arranged in pairs are respectively positioned through shaft shoulders and shaft sleeves, and the outer rings are free; the second thrust bearing 46 realizes positioning and force transmission through the hole shoulder and the shaft sleeve; the second ball bearing 47 realizes the positioning of the inner ring and the outer ring through the shaft shoulder, the hole shoulder, the bearing retainer ring and the round nut, the shaft system can realize the compound bearing of unidirectional axial force and radial force, the outer ring of the second angular contact bearing 45 is free and has a certain slight displacement, the second angular contact bearing 45 can ensure that the axial load is not born and only bears radial load, the axial load is born by the second thrust bearing 46 completely, and the positioning can be realized through the bearing retainer ring on the outer ring of the second angular contact bearing 45 close to the end of the speed reducer 43, the bidirectional axial force bearing mainly bearing of centrifugal load can be realized, wherein the axial force is more than 6 times of gravity, thus the bearing capacity of the thrust bearing can be fully exerted, the span between the bearings is reduced, the compact layout of the shaft system is realized, and the main bearing is changed from bending moment to axial force. The rotating arm system 4 structure adopting the scheme reduces a frame structure, can reduce the rotational inertia of the system, can realize higher overload change rate under the same driving power and torque, can meet the requirement of high overload change rate under the premise of four-degree-of-freedom driving, and can simultaneously meet the requirements of space orientation disorder and overload resistance training.
Further, the pitching frame system 3 comprises a pitching frame 31, a yaw driving motor 32, a yaw driving shaft 33 and a yaw driven shaft 34, the pitching frame 31 is fixedly connected with a rotating shaft 44, yaw driving shaft mounting holes and yaw driven shaft mounting holes are concentrically arranged on the pitching frame 31, the axial lines of the yaw driving shaft mounting holes and the yaw driven shaft mounting holes are perpendicular to the axial line of the rotating shaft 44, the yaw driving motor 32 is fixed on the pitching frame 31, the output end of the yaw driving motor 32 is connected with the yaw driving shaft 33, the yaw driving shaft 33 is arranged in the yaw driving shaft mounting holes and is rotationally connected with the yaw driving shaft mounting holes, the yaw driven shaft 34 is arranged in the yaw driven shaft mounting holes and is rotationally connected with the yaw driven shaft mounting holes, the pitching frame 31 is of a U-shaped structure, connecting lugs 36 are symmetrically arranged on two sides of the pitching frame 31, the yaw driving shaft mounting holes and the yaw driven shaft mounting holes are respectively arranged on one connecting lug 36, the pitching frame 31 is also provided with a fixed mounting hole, the rotating shaft 44 is arranged in the fixed mounting hole and is fixedly connected with the pitching frame 31 through a fixed expansion sleeve, and one end of the rotating shaft 44 is also provided with a pitching clamp 48 for positioning the pitching frame 31; the yaw drive shaft installation hole in be provided with third angular contact bearing 38, yaw drive shaft 33 is connected with pitch frame 31 rotation through third angular contact bearing 38, yaw driven shaft installation hole in be provided with fourth angular contact bearing 37, yaw driven shaft 34 is connected with pitch frame 31 rotation through fourth angular contact bearing 37. The fixed mounting holes of the pitching frame 31 are arranged in the middle of the symmetrically arranged connecting lugs 36, one end of the rotating shaft 44 is matched with the pitching frame 31 through a cylindrical surface to realize positioning, and the structural combination of the arm support 41 and the U-shaped pitching frame 31 is adopted, so that one frame structure is reduced, and the rotational inertia of the system can be reduced; the fixed expansion sleeves are arranged in two, the fixed mounting holes are stepped holes, the two fixed expansion sleeves are arranged in the stepped holes, a clamp 48 is arranged at one end of the rotating shaft 44, the fixed expansion sleeves are positioned in the stepped holes, the clamp 48 is of a structure of two semi-rings, connecting parts are arranged at two ends of the semi-rings, the two semi-rings are fixedly connected through bolts, a groove structure is arranged on the rotating shaft 44, the clamp 48 is clamped in the groove structure to realize positioning and bear centrifugal load, meanwhile, the rotating shaft 44 and the pitching frame 31 are further subjected to axial positioning and bearing of the pitching frame system 3 through a spigot structure, the pitching frame system 3 further comprises a yaw driven shaft slip ring 35, a stator of the yaw driven shaft slip ring 35 is fixed on the pitching frame 31 through bolts, and a rotor of the yaw driven shaft slip ring 35 is installed on the yaw driven shaft 34 through an intersection structure and rotates together with the yaw driven shaft 34.
Further, the yaw frame system 2 includes a yaw frame 21, a cabin driving motor 22, a cabin driven shaft 24, and a cabin driving shaft 23, the yaw frame 21 is in an annular symmetrical structure, the outer side of the yaw frame 21 is fixedly connected with a yaw driving shaft 33 and a yaw driven shaft 34, a cabin driven shaft mounting hole and a cabin driving shaft mounting hole are formed in the yaw frame 21 in a penetrating manner along the symmetry center, the cabin driving motor 22 is fixed on the yaw frame 21, the output end of the cabin driving motor 22 is connected with the cabin driving shaft 23, the cabin driving shaft 23 is arranged in the cabin driving shaft mounting hole and is in rotational connection with the cabin driving shaft mounting hole, and the cabin driven shaft 24 is arranged in the cabin driven shaft mounting hole and is in rotational connection with the cabin driven shaft mounting hole; the cabin driving shaft installation hole in be provided with axle sleeve 25, be provided with fifth angular contact bearing 26 in the axle sleeve 25, cabin driving shaft 23 is connected through fifth angular contact bearing 26 and axle sleeve 25 rotation, forms the revolute pair with yaw frame 21, cabin driven shaft installation hole in be provided with bearing housing 29, be provided with sixth angular contact bearing 27 in the bearing housing 29, cabin driven shaft 24 is connected through sixth angular contact bearing 27 and bearing housing 29 rotation, forms the revolute pair with yaw frame 21. In the scheme, a rotor of a cabin driving motor 22 is connected with a cabin driving shaft 23 through an expansion sleeve, a motor stator is fixed on a yaw frame 21 through bolts, the cabin driving shaft 23 is rotationally connected with a shaft sleeve 25 through a fifth angular contact bearing 26, a matching hole of the shaft sleeve 25 and the yaw frame 21 is in tight clearance fit, the fifth angular contact bearing 26 realizes the positioning of an inner ring and an outer ring through a round nut, a shaft shoulder, a hole shoulder and a bearing retainer ring structure, realizes the bidirectional axial and radial combined bearing, further comprises a cabin driven shaft slip ring 28, a stator of the cabin driven shaft slip ring 28 is fixedly arranged on the yaw frame 21 through a screw and a bearing sleeve 29, a rotor of the cabin driven shaft slip ring 28 is fixedly connected with the cabin driven shaft 24 through a fork structure,
Further, the cabin system 1 includes a cabin 11, a screen 14, an instrument desk 13, and a seat 15, wherein the outer side of the cabin 11 is fixedly connected with a cabin driving shaft 23 and a cabin driven shaft 24, and the screen 14, the camera, and the seat 15 are all disposed in the cabin 11. In the scheme, the cabin body 11 is fixedly connected with the cabin driving shaft 23 and the cabin driven shaft 24 respectively through the expansion sleeve, the cabin system 1 is driven to rotate, the cabin driven shaft 24 and the cabin body 11 adopt cylindrical surface matched spigot structures, and the positions of the cabin system 1 are adjusted through the gaskets, so that the conical surface positioning matched structure of the cabin driving shaft 23 and the cylindrical surface matched spigot structure of the cabin driven shaft 24 are simultaneously contacted, and the axial force brought by different poses of the cabin system 1 can be borne; the video rendering scene displayed by the screen 14 provides a simulated visual environment, sensory transfer compensation is carried out or visual illusion training is carried out, the pilot is trained to carry out aircraft state and gesture cognition through the instrument desk 13, the space orientation obstacle state is judged and changed by means of the instrument desk 13, the seat 15 is arranged at the bottom of the cabin body 11, the instrument desk 13 is positioned in front of and on two sides of the seat 15, meanwhile, the cabin door 12 is arranged on the side face of the cabin body 11, the pilot enters and exits through a movable ladder, the movable ladder is provided with a platform structure, the boarding height is controlled within a certain range, the screen 14 is positioned in front of the instrument desk 13, and the comfortable visual distance is provided.
Further, the bearing system includes a bearing sleeve 54, a first ball bearing 55, a first thrust ball bearing 56, and a first angular contact bearing 57, wherein the bearing sleeve 54 is fixed in the spindle mounting hole, and the bearing sleeve 54, the ball bearing, the first thrust ball bearing 56, and the first angular contact bearing 57 are all disposed in the bearing sleeve 54, so that the spindle 53 and the base 51 form a revolute pair. In the scheme, the bearing sleeve 54 passes through the spigot to be positioned and is fixed in the main shaft mounting hole of the base 51 through a screw, the main shaft 53 passes through a first thrust bearing, a first ball bearing 55, a first angular contact bearing 57 is rotationally connected with the bearing sleeve 54, the outer ring of the first angular contact bearing 57 is free, the inner ring is respectively positioned by a shaft shoulder and a shaft sleeve, the third angular contact bearing 38 is ensured not to bear axial force, the axial force is only borne by the first thrust bearing, the bearing system can bear the axial force, the radial force and the bending moment, and the bearing mounting difficulty can be reduced through the bearing sleeve 54
Further, the arm support 41 on be provided with the connecting hole, the connecting hole in be provided with and connect the cover that expands, connect the cover that expands and establish on the main shaft 53, arm support 41 through connect the cover that expands and main shaft 53 fixed connection, the tip of the one end of arm support 41 and main shaft 53 fixed connection still is provided with the counter weight 7, be provided with second angular contact bearing 45, second thrust bearing 46, second ball bearing 47 in the rotation axis mounting hole, rotation axis 44 is connected with the rotation of arm support 41 through second angular contact bearing 45, second thrust bearing 46, second ball bearing 47.
Furthermore, the pitching frame 31 has a U-shaped structure, two sides of the pitching frame are symmetrically provided with connecting lugs 36, the yaw driving shaft mounting hole and the yaw driven shaft mounting hole are respectively arranged on one connecting lug 36, the pitching frame 31 is also provided with a fixed mounting hole, the rotating shaft 44 is arranged in the fixed mounting hole and is fixedly connected with the pitching frame 31 through a fixed expansion sleeve, and one end of the rotating shaft 44 is also provided with a clamp 48 for positioning the pitching frame 31; the yaw drive shaft installation hole in be provided with third angular contact bearing 38, yaw drive shaft 33 is connected with pitch frame 31 rotation through third angular contact bearing 38, yaw driven shaft installation hole in be provided with fourth angular contact bearing 37, yaw driven shaft 34 is connected with pitch frame 31 rotation through fourth angular contact bearing 37.
Further, a shaft sleeve 25 is arranged in the cabin driving shaft mounting hole, a fifth angular contact bearing 26 is arranged in the shaft sleeve 25, the cabin driving shaft 23 is rotationally connected with the shaft sleeve 25 through the fifth angular contact bearing 26 to form a revolute pair with the yaw frame 21, a bearing sleeve 29 is arranged in the cabin driven shaft mounting hole, a sixth angular contact bearing 27 is arranged in the bearing sleeve 29, and the cabin driven shaft 24 is rotationally connected with the bearing sleeve 29 through the sixth angular contact bearing 27 to form a revolute pair with the yaw frame 21.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way. Many possible variations and modifications of the disclosed technology can be made by anyone skilled in the art, or equivalent embodiments with equivalent variations can be made, without departing from the scope of the disclosed technology. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technology of the present invention fall within the protection scope of the present invention.
Claims (6)
1. A centrifugal flight load and illusion analogue means, its characterized in that: the system comprises a transmission supporting system (5), a swinging arm system (4), a pitching frame system (3), a yaw frame system (2) and a cabin system (1), wherein the transmission supporting system (5) supports and drives the swinging arm system (4) to rotate to generate overload acceleration, the swinging arm system (4) is provided with the pitching frame system (3) and drives the pitching frame system (3) to rotate around a connection point with the swinging arm system (4), the rotation center of the pitching frame system (3) is perpendicular to the rotation center of the transmission supporting system (5) to realize pitching movement of the system, the yaw frame system (2) is arranged on the pitching frame system (3), the pitching frame system (3) drives the yaw frame system (2) to rotate around a connection point with the yaw frame system (2), the rotation center of the yaw frame system (2) is perpendicular to the rotation center of the pitching frame system (3) to realize yawing movement of the system, and the cabin system (2) drives the system to rotate around the connection point with the yaw frame system (2) to realize yawing movement of the cabin system (1);
The transmission supporting system (5) comprises a base (51) and a main motor (52), wherein the main motor (52) is arranged at the bottom of the base (51), a main shaft mounting hole is formed in the base (51), the output end of the main motor (52) is connected with a main shaft (53), the main shaft (53) is arranged in the main shaft mounting hole, a bearing system is arranged in the main shaft mounting hole, and the main shaft (53) is rotationally connected with the base (51) through the bearing system;
the rotating arm system (4) comprises a cantilever crane (41), a driving motor (42), a rotating shaft (44) and a speed reducer (43), one end of the cantilever crane (41) is fixedly connected with the main shaft (53), the other end of the cantilever crane (41) is provided with a rotating shaft mounting hole, the rotating shaft mounting hole is horizontally arranged, the output end of the driving motor (42) is connected with the input end of the speed reducer (43), the output end of the speed reducer (43) is connected with the rotating shaft (44), and the rotating shaft (44) is arranged in the rotating shaft mounting hole and is rotationally connected with the cantilever crane (41);
The bearing system comprises a bearing sleeve (54), a first ball bearing (55), a first thrust ball bearing (56) and a first angular contact bearing (57), wherein the bearing sleeve (54) is fixed in a main shaft mounting hole, and the bearing sleeve (54), the ball bearing, the first thrust ball bearing (56) and the first angular contact bearing (57) are all arranged in the bearing sleeve (54) so that a rotating pair is formed by the main shaft (53) and the base (51);
The cantilever crane (41) on be provided with the connecting hole, the connecting hole in be provided with and connect the cover that expands, connect the cover that expands and establish on main shaft (53), cantilever crane (41) are through connecting the cover that expands and main shaft (53) fixed connection, the tip of cantilever crane (41) and main shaft (53) fixed connection's one end still is provided with counter weight (7), be provided with second angular contact bearing (45), second thrust bearing (46), second ball bearing (47) in the rotation axis mounting hole, rotation axis (44) are through second angular contact bearing (45), second thrust bearing (46), second ball bearing (47) and cantilever crane (41) rotation connection.
2. A centrifugal flight load and illusion simulation device according to claim 1, wherein: the pitching frame system (3) comprises a pitching frame (31), a yaw driving motor (32), a yaw driving shaft (33) and a yaw driven shaft (34), wherein the pitching frame (31) is fixedly connected with a rotating shaft (44), a yaw driving shaft mounting hole and a yaw driven shaft mounting hole are concentrically arranged on the pitching frame (31), the axial lead of the yaw driving shaft mounting hole and the axial lead of the yaw driven shaft mounting hole are perpendicular to the axial lead of the rotating shaft (44), the yaw driving motor (32) is fixed on the pitching frame (31), the output end of the yaw driving motor is connected with the yaw driving shaft (33), the yaw driving shaft (33) is arranged in the yaw driving shaft mounting hole and is rotationally connected with the yaw driving shaft mounting hole, and the yaw driven shaft (34) is arranged in the yaw driven shaft mounting hole and is rotationally connected with the yaw driven shaft mounting hole.
3. A centrifugal flight load and illusion simulation device according to claim 2, characterized in that: yaw frame system (2) include yaw frame (21), cabin driving motor (22), cabin driven shaft (24), cabin drive shaft (23), yaw frame (21) are annular symmetrical structure, the outside of yaw frame (21) respectively with yaw drive shaft (33) and yaw driven shaft (34) fixed connection, be provided with cabin driven shaft mounting hole and cabin drive shaft mounting hole along the centre of symmetry to wearing on yaw frame (21), cabin driving motor (22) are fixed on yaw frame (21), cabin drive shaft (23) are connected to the output of cabin driving motor (22), cabin drive shaft (23) are arranged in the cabin drive shaft mounting hole to rotate rather than being connected, cabin driven shaft (24) are arranged in the cabin driven shaft mounting hole, and rotate rather than being connected.
4. A centrifugal flight load and illusion simulation device according to claim 3, wherein: the cabin system (1) comprises a cabin body (11), a screen (14), an instrument desk (13) and a seat (15), wherein the outer side of the cabin body (11) is fixedly connected with a cabin driving shaft (23) and a cabin driven shaft (24) respectively, and the screen (14), the camera and the seat (15) are arranged in the cabin body (11).
5. A centrifugal flight load and illusion simulation device according to claim 2, characterized in that: the pitching frame (31) is of a U-shaped structure, two sides of the pitching frame are symmetrically provided with connecting lugs (36), a yaw driving shaft mounting hole and a yaw driven shaft mounting hole are respectively formed in one connecting lug (36), a fixed mounting hole is further formed in the pitching frame (31), a rotating shaft (44) is arranged in the fixed mounting hole and is fixedly connected with the pitching frame (31) through a fixed expansion sleeve, and a clamp (48) is further arranged at one end of the rotating shaft (44) and used for positioning the pitching frame (31); the yaw driving shaft installation hole in be provided with third angular contact bearing (38), yaw driving shaft (33) are connected with pitch frame (31) rotation through third angular contact bearing (38), yaw driven shaft installation hole in be provided with fourth angular contact bearing (37), yaw driven shaft (34) are connected with pitch frame (31) rotation through fourth angular contact bearing (37).
6. A centrifugal flight load and illusion simulation device according to claim 3, wherein: be provided with axle sleeve (25) in cockpit drive shaft mounting hole, be provided with fifth angle contact bearing (26) in axle sleeve (25), cockpit drive shaft (23) are connected with axle sleeve (25) rotation through fifth angle contact bearing (26), form the revolute pair with yaw frame (21), cockpit driven shaft mounting hole in be provided with bearing housing (29), be provided with sixth angle contact bearing (27) in bearing housing (29), cockpit driven shaft (24) are connected with bearing housing (29) rotation through sixth angle contact bearing (27), form the revolute pair with yaw frame (21).
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| CN112710459B (en) * | 2020-12-15 | 2023-05-09 | 南方科技大学 | Aeroengine rotor flight state simulation experiment platform |
| CN112857763B (en) * | 2020-12-31 | 2023-03-24 | 南方科技大学 | Structural dynamics experiment platform |
| CN117943337A (en) * | 2024-03-26 | 2024-04-30 | 内蒙古工业大学 | Intelligent airborne photovoltaic belt cleaning device suitable for super large scale photovoltaic power plant |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102013187A (en) * | 2010-10-29 | 2011-04-13 | 北京航空航天大学 | Flight simulator system with persistent overload simulation capability |
| CN103718226A (en) * | 2011-05-23 | 2014-04-09 | 阿姆斯特－系统科技有限责任公司 | Device for spatially moving persons |
| CN104160435A (en) * | 2012-01-18 | 2014-11-19 | 环境构造公司 | Centrifuge-based-flight simulator |
| CN104616563A (en) * | 2015-02-16 | 2015-05-13 | 清华大学 | Rocker arm type flight simulator having continuous overload simulation capability |
| CN204884273U (en) * | 2015-08-26 | 2015-12-16 | 重庆幻羽科技有限公司 | Virtual reality simulator with three degrees of freedom |
| CN108766101A (en) * | 2018-09-07 | 2018-11-06 | 中国工程物理研究院总体工程研究所 | Three Degree Of Freedom for helicopter Dynamic Flight Simulator turns frame system |
| CN108961915A (en) * | 2018-09-07 | 2018-12-07 | 中国工程物理研究院总体工程研究所 | Roll freedom for helicopter Dynamic Flight Simulator turns round stop mechanism |
| CN108961916A (en) * | 2018-09-07 | 2018-12-07 | 中国工程物理研究院总体工程研究所 | four-degree-of-freedom helicopter dynamic flight simulator |
| CN209000275U (en) * | 2018-09-07 | 2019-06-18 | 中国工程物理研究院总体工程研究所 | Roll freedom for helicopter Dynamic Flight Simulator turns round stop mechanism |
| CN209000276U (en) * | 2018-09-07 | 2019-06-18 | 中国工程物理研究院总体工程研究所 | Four-degree-of-freedom helicopter Dynamic Flight Simulator |
| CN209028882U (en) * | 2018-09-07 | 2019-06-25 | 中国工程物理研究院总体工程研究所 | Three Degree Of Freedom for helicopter Dynamic Flight Simulator turns frame system |
| CN110239732A (en) * | 2018-09-07 | 2019-09-17 | 中国工程物理研究院总体工程研究所 | Bolt retaining mechanism |
| CN209455023U (en) * | 2018-09-07 | 2019-10-01 | 中国工程物理研究院总体工程研究所 | Bolt retaining mechanism |
| CN212342086U (en) * | 2020-07-23 | 2021-01-12 | 中国工程物理研究院总体工程研究所 | Centrifugal flight load and illusion simulator |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI440499B (en) * | 2010-10-04 | 2014-06-11 | A space orientation mechanism |
-
2020
- 2020-07-23 CN CN202010718304.7A patent/CN111681492B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102013187A (en) * | 2010-10-29 | 2011-04-13 | 北京航空航天大学 | Flight simulator system with persistent overload simulation capability |
| CN103718226A (en) * | 2011-05-23 | 2014-04-09 | 阿姆斯特－系统科技有限责任公司 | Device for spatially moving persons |
| CN104160435A (en) * | 2012-01-18 | 2014-11-19 | 环境构造公司 | Centrifuge-based-flight simulator |
| CN104616563A (en) * | 2015-02-16 | 2015-05-13 | 清华大学 | Rocker arm type flight simulator having continuous overload simulation capability |
| CN204884273U (en) * | 2015-08-26 | 2015-12-16 | 重庆幻羽科技有限公司 | Virtual reality simulator with three degrees of freedom |
| CN108766101A (en) * | 2018-09-07 | 2018-11-06 | 中国工程物理研究院总体工程研究所 | Three Degree Of Freedom for helicopter Dynamic Flight Simulator turns frame system |
| CN108961915A (en) * | 2018-09-07 | 2018-12-07 | 中国工程物理研究院总体工程研究所 | Roll freedom for helicopter Dynamic Flight Simulator turns round stop mechanism |
| CN108961916A (en) * | 2018-09-07 | 2018-12-07 | 中国工程物理研究院总体工程研究所 | four-degree-of-freedom helicopter dynamic flight simulator |
| CN209000275U (en) * | 2018-09-07 | 2019-06-18 | 中国工程物理研究院总体工程研究所 | Roll freedom for helicopter Dynamic Flight Simulator turns round stop mechanism |
| CN209000276U (en) * | 2018-09-07 | 2019-06-18 | 中国工程物理研究院总体工程研究所 | Four-degree-of-freedom helicopter Dynamic Flight Simulator |
| CN209028882U (en) * | 2018-09-07 | 2019-06-25 | 中国工程物理研究院总体工程研究所 | Three Degree Of Freedom for helicopter Dynamic Flight Simulator turns frame system |
| CN110239732A (en) * | 2018-09-07 | 2019-09-17 | 中国工程物理研究院总体工程研究所 | Bolt retaining mechanism |
| CN209455023U (en) * | 2018-09-07 | 2019-10-01 | 中国工程物理研究院总体工程研究所 | Bolt retaining mechanism |
| CN212342086U (en) * | 2020-07-23 | 2021-01-12 | 中国工程物理研究院总体工程研究所 | Centrifugal flight load and illusion simulator |
Non-Patent Citations (2)
| Title |
|---|
| 离心式飞行模拟器发展概述;何阳;蒋春梅;宋琼;;机械设计;20171220(12);全文 * |
| 飞行错觉模拟器系统软件的设计和实现;王聪;曹征涛;赵显亮;杨明浩;郑媛憬;李玉亮;郭华;葛华;贾宏博;;医疗卫生装备;20190514(05);全文 * |
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