CN110473445B - Aircraft flight attitude simulation equipment - Google Patents
Aircraft flight attitude simulation equipment Download PDFInfo
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- CN110473445B CN110473445B CN201910789208.9A CN201910789208A CN110473445B CN 110473445 B CN110473445 B CN 110473445B CN 201910789208 A CN201910789208 A CN 201910789208A CN 110473445 B CN110473445 B CN 110473445B
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
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- G—PHYSICS
- G09—EDUCATION; CRYPTOGRAPHY; DISPLAY; ADVERTISING; SEALS
- G09B—EDUCATIONAL OR DEMONSTRATION APPLIANCES; APPLIANCES FOR TEACHING, OR COMMUNICATING WITH, THE BLIND, DEAF OR MUTE; MODELS; PLANETARIA; GLOBES; MAPS; DIAGRAMS
- G09B9/00—Simulators for teaching or training purposes
- G09B9/02—Simulators for teaching or training purposes for teaching control of vehicles or other craft
- G09B9/08—Simulators for teaching or training purposes for teaching control of vehicles or other craft for teaching control of aircraft, e.g. Link trainer
- G09B9/16—Ambient or aircraft conditions simulated or indicated by instrument or alarm
- G09B9/20—Simulation or indication of aircraft attitude
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Abstract
The invention relates to aircraft flight attitude simulation equipment which comprises a display stand, a fairing, a support, a fan assembly, a first model assembly, a second model assembly and a third model assembly, wherein the fairing is arranged on the display stand; the exhibition stand is arranged on the ground; the fairing is of a transparent tubular structure and is transversely arranged, and the air inlet end of the fairing is connected with the fan assembly; the foot part of the bracket is connected to the exhibition stand, and the upper part of the bracket is connected with the fairing; the first model assembly comprises a first support rod, a first cross rod, a first baffle, a first rotary drum and a horizontal tail wing airplane model; the second model component comprises a second support rod, a second rotary cylinder and a vertical tail plane model; the third model component comprises a third support rod, a third cross rod, a third baffle, a third rotary drum and an aileron aircraft model; the first model assembly, the second model assembly and the third model assembly are arranged at intervals along the length direction of the fairing. The invention can simulate the flight postures of the airplane of pitching upwards, inclining leftwards and turning rightwards.
Description
Technical Field
The invention relates to an airplane model, in particular to airplane flight attitude simulation equipment.
Background
The aircraft flight attitude simulation device is demonstration equipment for simulating various flight attitudes of an aircraft, and particularly can simulate three actions of pitching, tilting left and right and steering when the aircraft flies, and the device enables people to know the attitude of the aircraft under the condition that wings of each part are in different states by observation. At present, an exhibit capable of simulating the flight attitude of an airplane does not appear in the market; therefore, the problem that people need to solve is to manufacture the device for demonstrating the flight attitude of the simulated airplane, which can realize three actions of pitching, left-right tilting and steering and enables people to know the attitude of the airplane under the condition that the wings of each part are in different states through observation and experience.
Disclosure of Invention
The invention aims to provide aircraft flight attitude simulation equipment which can simulate the flight attitude of an aircraft for bending upwards, inclining left and turning right.
The above object of the present invention is achieved by the following technical solutions: an aircraft flight attitude simulation device comprises a display stand, a fairing, a support, a fan assembly, a first model assembly, a second model assembly and a third model assembly; the exhibition stand is arranged on the ground; the fairing is of a transparent tubular structure and is transversely arranged, and the air inlet end of the fairing is connected with the fan assembly; the foot part of the bracket is connected to the exhibition stand, and the upper part of the bracket is connected with the fairing;
the first model assembly comprises a first support rod, a first cross rod, a first baffle, a first rotary drum and a horizontal tail wing airplane model; the first supporting rod penetrates through the side wall of the fairing, the lower end of the first supporting rod is fixedly connected to the table top of the exhibition stand, and the upper end of the first supporting rod extends into the fairing; the first cross rod is perpendicular to the length direction of the fairing, one end of the first cross rod is fixedly connected with the upper end of the first supporting rod, and the other end of the first cross rod is connected with the first blocking piece; the first rotary drum is sleeved on the first cross rod, and the first blocking piece limits the first rotary drum on the first cross rod; the horizontal tail wing airplane model is fixedly connected to the first rotary drum, the machine head faces the direction of the fan assembly, and the horizontal tail wing of the horizontal tail wing airplane model inclines downwards;
the second model component comprises a second support rod, a second rotary cylinder and a vertical tail plane model; the second supporting rod penetrates through the lower side wall of the fairing, the lower end of the second supporting rod is fixedly connected to the table top of the exhibition stand, and the upper end of the second supporting rod extends into the fairing; the second rotary drum is sleeved at the upper end of the second supporting rod; the vertical tail wing aircraft model is arranged at the top end of the second rotary drum, the machine head faces the direction of the fan assembly, and the vertical tail wing of the vertical tail wing aircraft model inclines rightwards;
the third model component comprises a third support rod, a third cross rod, a third baffle, a third rotary drum and an aileron aircraft model; the third supporting rod penetrates through the side wall of the fairing, the lower end of the third supporting rod is fixedly connected to the table top of the exhibition stand, and the upper end of the third supporting rod extends into the fairing; the third cross rod is parallel to the length direction of the fairing, one end of the third cross rod is fixedly connected with the upper end of the third supporting rod, and the other end of the third cross rod is connected with the third baffle; the aileron aircraft model is fixedly connected to the third rotary drum, the machine head faces to the direction of the fan assembly, and the right aileron of the aileron aircraft model inclines upwards;
the first model assembly, the second model assembly and the third model assembly are arranged at intervals along the length direction of the fairing.
By adopting the technical scheme, because the horizontal tail, the vertical tail and the ailerons of the horizontal tail airplane model, the vertical tail airplane model and the aileron airplane model are respectively arranged in an inclined manner, when the fan assembly transmits wind power into the fairing, the horizontal tail airplane model, the vertical tail airplane model and the aileron airplane model can drive the rotating cylinders to rotate respectively, and the attitude of the airplane models can change correspondingly, so that people can observe the influence of the horizontal tail, the vertical tail and the ailerons on the flight attitude of the airplane models.
The invention is further configured to: a first lug is arranged at one end of the first rotary drum, which is far away from the first baffle plate; the first cross rod is provided with a first fixed block and a first stop block, and the first convex block is positioned between the first fixed block and the first stop block; the center of gravity of the horizontal tail wing airplane model is positioned at the head part, when no wind exists, the gravity has the tendency of enabling the first rotary drum to rotate on the first cross rod, and the first fixed block blocks the first bump to enable the horizontal tail wing airplane model to be kept at the upper end of the first rotary drum; when wind exists, the wind power overcomes the gravity of the horizontal tail wing airplane model to enable the horizontal tail wing airplane model to have a pitching trend, the first rotary drum is driven to rotate on the first cross rod, when the horizontal tail wing airplane model rotates to a certain angle, the first convex block is blocked by the first stop block to stop the rotation, and at the moment, the gravity center of the horizontal tail wing airplane model is positioned at the head part; after the windbreak, the horizontal tail plane model can be restored to the original position due to the self gravity.
By adopting the technical scheme, people can restore the horizontal tail plane model to the original position due to dead weight after observing that the posture of the horizontal tail plane model changes completely and the wind stops, and the horizontal tail plane model does not need to be adjusted manually.
The invention is further configured to: the second rotary drum is sleeved with the second support rod and connected with the second support rod through a torsion spring.
By adopting the technical scheme, after people observe the attitude change of the vertical tail plane model and stop the wind, the vertical tail plane model can be restored to the original position under the action of the torsion spring without manual adjustment.
The invention is further configured to: a third lug is arranged at one end of the third rotary drum far away from the third baffle; a third fixed block and a third stop block are arranged on the third cross rod, and a third bump is positioned between the third fixed block and the third stop block; the gravity center of the aileron aircraft model is positioned on the right side of the fuselage, when no wind exists, the gravity has the tendency of enabling the third rotary drum to rotate on the third cross rod, and the third fixed block blocks the third bump to enable the aileron aircraft model to be kept at the upper end of the third rotary drum; when wind exists, the gravity of the aileron airplane model is overcome by the wind power, so that the aileron airplane model has a left-leaning trend, the third rotary drum is driven to rotate on the third cross rod, when the aileron airplane model rotates to a certain angle, the third bump is blocked by the third stop block, so that the rotation is stopped, and the gravity center of the aileron airplane model is positioned on the right side of the airplane body; after the windbreak, the aileron airplane model can be restored to the original position due to the self gravity.
By adopting the technical scheme, after people observe the attitude change of the aileron aircraft model and stop the aircraft, the aileron aircraft model can be restored to the original position due to dead weight without manual adjustment.
The invention is further configured to: an air outlet is arranged on the table surface of the exhibition stand, and the air outlet end of the fairing is bent downwards and extends into the air outlet.
By adopting the technical scheme, the air outlet end of the fairing is bent downwards, so that air can flow out only after turning around the bend in the fairing, and the stability of air flow in the fairing is improved
The invention is further configured to: the fairing is of a circular tubular structure.
By adopting the technical scheme, the fairing is of a circular tubular structure, so that the wind power of each direction borne by the airplane is more uniform, and the airflow in the fairing is more uniform and stable.
The invention is further configured to: the three display boards are arranged on the exhibition stand and respectively correspond to the three groups of models.
By adopting the technical scheme, the display board makes basic introduction to each model component, so that people can quickly understand the effect of the model.
The invention is further configured to: the fan assembly comprises a mounting frame and a fan; the foot part of the mounting rack is connected to the table surface of the exhibition stand, the upper part of the mounting rack is provided with a tubular inner cavity, and an opening at one end of the inner cavity is communicated with the air inlet end of the fairing in a sealing way; the fan is arranged in the mounting frame inner cavity.
By adopting the technical scheme, the fan is arranged in the mounting frame, the mounting frame is communicated with the air inlet end of the fairing in a closed manner, and the wind energy of the fan can be ensured to blow into the fairing more and be utilized
The invention is further configured to: the fan is a speed-regulating fan.
By adopting the technical scheme, the wind power of the fan can be adjusted, and when the wind power is not small and different, the change speed of the flight attitude of the airplane model is different, so that people can quickly observe the attitude change of the airplane model and can carefully observe the change process slowly
In conclusion, the invention has the following beneficial effects:
1. the horizontal tail, the vertical tail and the ailerons of the horizontal tail airplane model, the vertical tail airplane model and the aileron airplane model are respectively arranged in an inclined manner, when the fan assembly transmits wind power into the fairing, the horizontal tail airplane model, the vertical tail airplane model and the aileron airplane model can drive respective rotating cylinders to rotate, and the attitude of the airplane model can be correspondingly changed, so that people can observe the influence of the horizontal tail, the vertical tail and the ailerons on the flight attitude of the airplane model;
2. the arrangement of the lug, the fixed block, the stop block and the torsion spring on the rotary drum and the support rod enables the three airplane models to automatically restore to the original positions after demonstration, so that the subsequent use is convenient, and manual adjustment is not needed;
3. the fairing is a circular tube structure, and the air outlet end of the fairing is bent downwards, so that the uniformity and stability of air flow in the fairing are guaranteed.
Drawings
FIG. 1 is a schematic diagram of an aircraft flight attitude simulation apparatus;
FIG. 2 is a schematic structural diagram of a first model component;
FIG. 3 is a partial cross-sectional view of a second mold assembly;
fig. 4 is a schematic structural view of a third model component.
In the figure, 1, a display stand; 10. an air outlet; 2. a cowling; 3. a support; 4. a fan assembly; 40. a mounting frame; 41. a fan; 5. a first model component; 50. a first support bar; 51. a first cross bar; 510. a first fixed block; 511. a first stopper; 52. a first baffle plate; 53. a first rotating drum; 530. a first bump; 54. a horizontal tail model of the aircraft; 6. a second model component; 60. a second support bar; 61. a second rotating drum; 62. a torsion spring; 63. a vertical tail model; 7. a third model component; 70. a third support bar; 71. a third cross bar; 710. a third fixed block; 711. a third stopper; 72. a third baffle plate; 73. a third drum; 730. a third bump; 74. an aileron aircraft model; 8. a display board.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Examples
Referring to fig. 1, an aircraft flight attitude simulation device comprises a display stand 1, a fairing 2, a bracket 3, a fan assembly 4, a first model assembly 5, a second model assembly 6, a third model assembly 7 and a display board 8; the exhibition stand 1 is arranged on the ground, and an air outlet 10 is formed in the exhibition surface of the exhibition stand 1; the fairing 2 is a round tubular structure, is made of transparent materials, is horizontally arranged, takes the bracket 3 as a support, the air inlet end of the fairing 2 is connected with the fan assembly 4, and the air outlet end is bent downwards and extends into the air outlet 10; the plurality of brackets 3 are arranged at intervals, the foot parts of the brackets are connected to the exhibition stand 1, and the upper ends of the brackets are matched with the outer side wall of the fairing 2; the fan assembly 4 includes a mounting bracket 40 and a fan 41; the foot part of the mounting rack 40 is connected to the exhibition surface of the exhibition stand 1, the upper part of the mounting rack 40 is provided with a tubular inner cavity along the length direction of the fairing 2, and an opening at one end of the tubular inner cavity is communicated with the air inlet end of the fairing 2 in a sealing way; the fan 41 is arranged in the tubular inner cavity of the mounting frame 40, and the wind power of the fan 41 has three gears, namely a large gear, a middle gear and a small gear.
Referring to fig. 1 and 2, the first model assembly 5 comprises a first strut 50, a first cross bar 51, a first flap 52, a first drum 53 and a horizontal tail model airplane 54; the first supporting rod 50 penetrates through the lower side wall of the fairing 2, the lower end of the first supporting rod 50 is fixedly connected to the table top of the exhibition stand 1, and the upper end of the first supporting rod extends into the fairing 2; the first cross bar 51 is perpendicular to the length direction of the fairing 2, one end of the first cross bar 51 is fixedly connected with the upper end of the first supporting bar 50, and the other end of the first cross bar 51 is provided with threads and is in threaded connection with the first blocking piece 52; the first rotary drum 53 is sleeved on the first cross rod 51, and one end of the first rotary drum 53 close to the first supporting rod 50 is provided with a first convex block 530; the first cross bar 51 is provided with a first fixed block 510 and a first stop block 511, and the first bump 530 is positioned between the first fixed block 510 and the first stop block 511; the horizontal tail airplane model 54 is fixedly connected to the first rotary drum 53, the center of gravity of the horizontal tail airplane model 54 is positioned at the nose part, the nose faces the direction of the fan assembly 4, and the horizontal tail of the horizontal tail airplane model 54 inclines downwards; in the absence of wind, the gravity of the horizontal tail airplane model 54 tends to rotate the first rotary drum 53 on the first cross bar 51 toward the nose, and the first fixing block 510 blocks the first projection 530 to keep the horizontal tail airplane model 54 at the upper end of the side wall of the first rotary drum 53; when wind exists, the wind power overcomes the gravity of the horizontal tail wing airplane model 54 to enable the horizontal tail wing airplane model to have a tendency of bending upwards, and the first rotary drum 53 is driven to rotate on the first cross rod 51, so that the upward bending flight attitude of the airplane model is shown; when the first rotary drum 53 rotates to a certain angle, the first bump 530 is blocked by the first stopper 510 to stop the rotation, and at this time, the horizontal tail airplane model 54 rotates to the maximum elevation angle, and the center of gravity is still located at the nose part; after the wind stops, the horizontal tail model 54 returns to its original position due to its own weight.
Referring to fig. 1 and 3, the second model assembly 6 comprises a second strut 60, a second drum 61, a torsion spring 62 and a vertical tail model airplane 63; the second supporting rod 60 penetrates through the lower side wall of the fairing 2, the lower end of the second supporting rod 60 is fixedly connected to the table top of the exhibition stand 1, and the upper end of the second supporting rod extends into the fairing 2; the second drum 61 is sleeved at the upper end of the second support rod 60, and the second drum and the second support rod are connected through a torsion spring 62; the vertical tail model 63 is disposed on the top end of the second rotary drum 61 with the nose facing the fan assembly 4, and the vertical tail of the vertical tail model 63 is inclined to the right side of the body.
Referring to fig. 1 and 4, the third model assembly 7 comprises a third strut 70, a third cross-bar 71, a third flap 72, a third drum 73 and an aileron aircraft model 74; the third supporting rod 70 penetrates through the lower side wall of the fairing 2, the lower end of the third supporting rod 70 is fixedly connected to the table top of the exhibition stand 1, and the upper end of the third supporting rod extends into the fairing 2; one end of the third cross bar 71 is parallel to the length direction of the fairing 2, and one end of the third cross bar 71 is fixedly connected with the upper end of the third support bar 70; the other end of the third cross bar 71 is provided with threads and is in threaded connection with a third baffle 72; the third drum 73 is sleeved on the third cross rod 71, and one end of the third drum 73 close to the third supporting rod 70 is provided with a third bump 730; a third fixing block 710 and a third block 711 are arranged on the third cross bar 71, and a third bump 730 is positioned between the third fixing block 710 and the third block 711; the aileron aircraft model 74 is fixedly connected to the third rotary drum 73, the gravity center of the aileron aircraft model 74 is positioned at the right side of the fuselage, the nose faces the direction of the fan assembly 4, and the right aileron of the aileron aircraft model 74 inclines upwards; in the absence of wind, the gravity of the aileron aircraft model 74 tends to rotate the third drum 73 to the right of the fuselage on the third cross bar 71, and the third fixed block 710 blocks the third projection 730 to hold the aileron aircraft model 74 on the upper end of the third drum 73; when wind exists, the wind force overcomes the gravity of the aileron airplane model 74 to enable the aileron airplane model to have a left-leaning trend, and drives the third rotary drum 73 to rotate on the third cross rod 71, so that the left-leaning flying attitude of the airplane model is shown; when the third rotating drum 73 rotates to a certain angle, the third bump 730 is blocked by the third block 711 to stop rotating, and at this time, the aileron aircraft model 74 inclines to the maximum angle, and the center of gravity of the aileron aircraft model is still positioned at the right side of the fuselage; after the wind stops, the aileron model 74 will return to its original position due to its own weight.
Referring to fig. 1, three display boards 8 are provided on the exhibition stand 1, respectively corresponding to the three model assemblies, and respectively showing basic descriptions of the three models.
When the above model is used, the horizontal tail model 54, the vertical tail model 63, and the aileron model 74 are in a balanced attitude when the fan 41 is not turned on; when observing the flight attitude of the aircraft, the fan 41 is turned on, and the fan 41 blows air into the cowling 2.
At this time, since the horizontal tail of the horizontal tail airplane model 54 is inclined downwards, the horizontal tail airplane model 54 tends to tilt up due to wind force, and the first rotary drum 53 is driven to rotate on the first cross bar 51, so that the upward-tilting flight attitude of the airplane model is shown; when the first rotary drum 53 rotates to a certain angle, the first protrusion 530 is stopped by the first stopper 510, and after the wind stops, the horizontal rear wing model 54 returns to the original position due to its own weight.
The vertical tail of the vertical tail airplane model 63 is in an inclined state, so that the vertical tail airplane model 63 deflects in the flight direction due to wind force and drives the second rotating cylinder 61 to rotate on the second supporting rod 60, and the process that the flight direction of the airplane model is changed is shown; when the second rotary drum 61 rotates on the second support rod 60, the torsion spring 62 is stressed to deform, and after the wind stops, the torsion spring 62 is deformed to restore, so that the vertical tail plane model 63 and the second rotary drum 61 are driven to restore to the original positions.
The ailerons of the aileron aircraft model 74 are in an inclined state, so that the aileron aircraft model 74 is inclined to the left by wind power to drive the third rotary drum 73 to rotate on the third cross rod 71, when the third rotary drum 73 rotates to a certain angle, the third bump 730 is blocked by the third block 710 to stop the rotation, and after the wind stops, the aileron aircraft model 74 can be restored to the original position due to the self gravity.
The fairing 2 greatly reduces the influence of external air flow and the like on the internal model; the fairing 2 is in a circular tube shape, so that the wind in the fairing is uniform and stable in the transmission process; and the air outlet end of the fairing 2 is bent downwards, so that the air can flow out only after turning around a curve in the fairing 2, and the stability of the air flow in the fairing 2 is further ensured.
The wind power of the fan 41 can be adjusted, and when the wind power is different, the change speed of the flight attitude of the airplane model is different, so that people can observe the attitude change more quickly and carefully observe the change process more slowly.
The fan 41 is arranged in the mounting frame 40, and the mounting frame 40 is closely communicated with the air inlet end of the fairing 2, so that more wind energy of the fan 41 can be blown into the fairing 2 and utilized.
The embodiments of the present invention are preferred embodiments of the present invention, and the scope of the present invention is not limited by these embodiments, so: all equivalent changes made according to the structure, shape and principle of the invention are covered by the protection scope of the invention.
Claims (6)
1. An aircraft flight attitude simulation device, characterized by: the device comprises a display stand (1), a fairing (2), a support (3), a fan assembly (4), a first model assembly (5), a second model assembly (6) and a third model assembly (7); the exhibition stand (1) is arranged on the ground; the fairing (2) is of a transparent tubular structure and is transversely arranged, and the air inlet end of the fairing (2) is connected with the fan assembly (4); the foot part of the bracket (3) is connected to the exhibition stand (1), and the upper part of the bracket (3) is connected with the fairing (2);
the first model component (5) comprises a first support rod (50), a first cross rod (51), a first baffle plate (52), a first rotary drum (53) and a horizontal tail plane model (54); the first supporting rod (50) penetrates through the side wall of the fairing (2), the lower end of the first supporting rod (50) is fixedly connected to the table top of the exhibition stand (1), and the upper end of the first supporting rod extends into the fairing (2); the first cross rod (51) is vertical to the length direction of the fairing (2), one end of the first cross rod (51) is fixedly connected with the upper end of the first support rod (50), and the other end of the first cross rod (51) is connected with the first blocking piece (52); the first drum (53) is sleeved on the first cross rod (51), and the first baffle (52) limits the first drum (53) on the first cross rod (51); the horizontal tail airplane model (54) is fixedly connected to the first rotary drum (53), the nose faces to the direction of the fan assembly (4), and the horizontal tail of the horizontal tail airplane model (54) inclines downwards;
one end of the first rotary drum (53) far away from the first baffle plate (52) is provided with a first lug (530); the first cross rod (51) is provided with a first fixed block (510) and a first stop block (511), and the first bump (530) is positioned between the first fixed block (510) and the first stop block (511); the center of gravity of the horizontal tail airplane model (54) is positioned at the head part, when no wind exists, gravity has the tendency of enabling the first rotary drum (53) to rotate on the first cross rod (51), and the first fixed block (510) blocks the first lug (530) so that the horizontal tail airplane model (54) is kept at the upper end of the first rotary drum (53); when wind exists, the wind power overcomes the gravity of the horizontal tail wing airplane model (54) to enable the horizontal tail wing airplane model to have a tendency of bending upward and drive the first rotary drum (53) to rotate on the first cross rod (51), when the horizontal tail wing airplane model rotates to a certain angle, the first bump (530) is blocked by the first stop block (511) to stop rotating, and the center of gravity of the horizontal tail wing airplane model (54) is located at the head part; after the windbreak, the horizontal tail plane model (54) can be restored to the original position due to the self gravity;
the second model assembly (6) comprises a second strut (60), a second drum (61) and a vertical tail model airplane (63); the second supporting rod (60) penetrates through the lower side wall of the fairing (2), the lower end of the second supporting rod (60) is fixedly connected to the table top of the exhibition stand (1), and the upper end of the second supporting rod extends into the fairing (2); the second rotary drum (61) is sleeved at the upper end of the second supporting rod (60); the vertical tail wing aircraft model (63) is arranged at the top end of the second rotary drum (61), the machine head faces the direction of the fan assembly (4), and the vertical tail wing of the vertical tail wing aircraft model (63) inclines to the right;
the second rotary drum (61) is sleeved with the second support rod (60) and is connected with the second support rod (60) through a torsion spring (62);
the third model component (7) comprises a third support rod (70), a third cross rod (71), a third baffle plate (72), a third rotary drum (73) and an aileron aircraft model (74); the third supporting rod (70) penetrates through the side wall of the fairing (2), the lower end of the third supporting rod (70) is fixedly connected to the table top of the exhibition stand (1), and the upper end of the third supporting rod extends into the fairing (2); the third cross bar (71) is parallel to the length direction of the fairing (2), one end of the third cross bar (71) is fixedly connected with the upper end of the third support rod (70), and the other end of the third cross bar (71) is connected with the third baffle (72); the aileron aircraft model (74) is fixedly connected to the third rotary drum (73), the nose faces to the direction of the fan assembly (4), and the right aileron of the aileron aircraft model (74) inclines upwards;
a third lug (730) is arranged at one end of the third rotary drum (73) far away from the third baffle plate (72); a third fixing block (710) and a third stop block (711) are arranged on the third cross rod (71), and a third bump (730) is positioned between the third fixing block (710) and the third stop block (711); the gravity center of the aileron airplane model (74) is positioned at the right side of the fuselage, when no wind exists, the gravity has the tendency of enabling the third rotary drum (73) to rotate on the third cross rod (71), and the third fixed block (710) blocks the third bump (730) so that the aileron airplane model (74) is kept at the upper end of the third rotary drum (73); when wind exists, the wind force overcomes the gravity of the aileron airplane model (74) to enable the aileron airplane model to have a left-leaning trend, the third rotary drum (73) is driven to rotate on the third cross rod (71), when the aileron airplane model rotates to a certain angle, the third bump (730) is blocked by the third block (711) to stop the rotation, and the gravity center of the aileron airplane model (74) is positioned on the right side of the airplane body; after the windbreak, the aileron airplane model (74) can be restored to the original position due to the self gravity;
the first model component (5), the second model component (6) and the third model component (7) are arranged at intervals along the length direction of the fairing (2).
2. An aircraft flight attitude simulation apparatus according to claim 1, wherein: an air outlet (10) is formed in the table top of the exhibition stand (1), and the air outlet end of the fairing (2) is bent downwards and extends into the air outlet (10).
3. An aircraft flight attitude simulation apparatus according to claim 1, wherein: the fairing (2) is of a circular tubular structure.
4. An aircraft flight attitude simulation apparatus according to claim 1, wherein: the exhibition stand comprises three exhibition boards (8), wherein the three exhibition boards (8) are arranged on the exhibition stand (1) and respectively correspond to the three groups of models.
5. An aircraft flight attitude simulation apparatus according to claim 1, wherein: the fan assembly (4) comprises a mounting frame (40) and a fan (41); the foot part of the mounting rack (40) is connected to the table top of the exhibition table (1), the upper part of the mounting rack (40) is provided with a tubular inner cavity, and an opening at one end of the inner cavity is hermetically communicated with the air inlet end of the fairing (2); the fan (41) is arranged in the inner cavity of the mounting frame (40).
6. An aircraft flight attitude simulation apparatus according to claim 5, wherein: the fan (41) is a speed-adjustable fan (41).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910789208.9A CN110473445B (en) | 2019-08-26 | 2019-08-26 | Aircraft flight attitude simulation equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910789208.9A CN110473445B (en) | 2019-08-26 | 2019-08-26 | Aircraft flight attitude simulation equipment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110473445A CN110473445A (en) | 2019-11-19 |
| CN110473445B true CN110473445B (en) | 2021-06-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910789208.9A Active CN110473445B (en) | 2019-08-26 | 2019-08-26 | Aircraft flight attitude simulation equipment |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204102365U (en) * | 2014-07-21 | 2015-01-14 | 合肥磐石自动化科技有限公司 | A kind of simulated aircraft flight attitude controls demonstration equipment |
| CN204884326U (en) * | 2015-06-26 | 2015-12-16 | 上海工程技术大学 | Experimental device for be used for demonstrating pneumatic performance of wing |
| CN106781830A (en) * | 2016-12-28 | 2017-05-31 | 哈尔滨工业大学 | A kind of two degrees of freedom simulator of grid rudder aircraft |
| CN207197782U (en) * | 2017-09-09 | 2018-04-06 | 广州市南沙东涌中学 | A kind of wind tunnel test model wooden aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US9327202B2 (en) * | 2014-06-30 | 2016-05-03 | Airborne America, Inc. | Wind tunnel design with expanding corners |
| US9711059B2 (en) * | 2015-03-27 | 2017-07-18 | Somniacs Ag | Motion platform device for flight simulation |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204102365U (en) * | 2014-07-21 | 2015-01-14 | 合肥磐石自动化科技有限公司 | A kind of simulated aircraft flight attitude controls demonstration equipment |
| CN204884326U (en) * | 2015-06-26 | 2015-12-16 | 上海工程技术大学 | Experimental device for be used for demonstrating pneumatic performance of wing |
| CN106781830A (en) * | 2016-12-28 | 2017-05-31 | 哈尔滨工业大学 | A kind of two degrees of freedom simulator of grid rudder aircraft |
| CN207197782U (en) * | 2017-09-09 | 2018-04-06 | 广州市南沙东涌中学 | A kind of wind tunnel test model wooden aircraft |
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