CN114120792A - Special teaching aid based on aircraft attitude control - Google Patents
Special teaching aid based on aircraft attitude control Download PDFInfo
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- CN114120792A CN114120792A CN202111440772.3A CN202111440772A CN114120792A CN 114120792 A CN114120792 A CN 114120792A CN 202111440772 A CN202111440772 A CN 202111440772A CN 114120792 A CN114120792 A CN 114120792A
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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
- G09B25/00—Models for purposes not provided for in G09B23/00, e.g. full-sized devices for demonstration purposes
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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
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Abstract
The invention relates to a special teaching aid based on airplane attitude control, and belongs to the technical field of aviation teaching aids. The aircraft comprises a driving seat, wherein a posture and centering indicating mechanism used for simulating the posture of an aircraft and a track indicating mechanism used for simulating the flying height of the aircraft are arranged in front of the driving seat, a posture control mechanism used for driving the posture and centering indicating mechanism to pitch, roll and center is arranged below the posture and centering indicating mechanism, the track indicating mechanism comprises a plurality of aiming lamps which are vertically arranged, a track control mechanism used for driving the aiming lamps to light and extinguish is arranged below the track indicating mechanism, an operating rod used for operating the posture control mechanism is arranged at the front end of the driving seat, and an accelerator rod used for operating the track control mechanism is arranged at the right side of the driving seat. The invention can reproduce the stress state of the landing aircraft, visually sense the landing principle of the aircraft, realize the convergence and communication of the landing aircraft knowledge and finish knowledge internalization.
Description
Technical Field
The invention relates to a special teaching aid based on airplane attitude control, and belongs to the technical field of aviation teaching aids.
Background
The control of the state of the airplane is the premise of safe landing, the control of the attack angle and the attitude of the airplane is particularly important under the condition that the airplane does not have flight path (speed) stability, students have difficulty in understanding and mastering related knowledge and methods, and the expected effect cannot be achieved by teaching only in theory. At present, a special teaching aid aiming at the requirements is not seen in the navigation teaching.
Disclosure of Invention
The invention aims to solve the problems that teaching in class is not vivid enough, students are limited to participate in teaching activities, and theories are difficult to understand and master, and provides a special teaching aid which can reproduce the stress state of a carrier landing aircraft, visually sense the carrier landing principle of the aircraft, realize the fusion of carrier landing flight knowledge and complete knowledge internalization.
In order to achieve the purpose, the invention provides the following technical scheme:
a special teaching aid based on airplane attitude control is characterized by comprising a driving seat 1, wherein the front of the driving seat 1 is provided with an attitude and centering indicating mechanism 4 for simulating the attitude of an airplane and a track indicating mechanism 12 for simulating the flying height of the airplane, an attitude control mechanism for driving the attitude and centering indicating mechanism 4 to pitch, roll and center is arranged below the attitude and centering indicating mechanism 4, the track indicating mechanism 12 comprises a plurality of aiming lamps 16 which are vertically arranged, a track control mechanism for driving the aiming lamps 16 to turn on and off is arranged below the track indicating mechanism 12, the front end of the driving seat 1 is provided with an operating rod 2 for operating the attitude control mechanism, and the right side of the driving seat is provided with an accelerator rod 3 for operating the track control mechanism;
preferably, the posture and centering indication mechanism 4 comprises a circular ferry plate 5, an airplane target table 33 is installed on the outer circumference of the ferry plate 5, a posture ball 11 is placed on the ferry plate 5, a circle center area 6, a middle ring area 7 and an outer ring area 8 are sequentially drawn on the upper surface of the ferry plate 5 from inside to outside by taking the circle center as the center, a centering line 9 is drawn along the diameter direction of the ferry plate 5, splayed indication lines 10 are symmetrically drawn by taking the centering line 9 as the center line, the splayed indication lines 10 are provided with two groups and symmetrically arranged in the outer ring area 8 by taking the middle ring area 7 as the center, and the narrow end of the splayed indication line 10 is close to the middle ring area 7;
preferably, the attitude control mechanism comprises an attitude cylinder group arranged below the ferry plate 5, the attitude cylinder group comprises two rolling cylinders 17 and one pitching cylinder 18, the movable ends of the three cylinders are mounted on the lower surface of the ferry plate 5 through universal bearings, the movable ends of the two rolling cylinders 17 are arranged at two ends of a diameter line 20 of the ferry plate 5, the diameter line 20 is perpendicular to the centering line 9, the movable ends of the pitching cylinders 18 are arranged at the rear end of the centering line 9, the three cylinders are respectively connected with three gas discharge pipelines, electromagnetic valves are respectively mounted on the three gas discharge pipelines, namely a first electromagnetic valve 21, a second electromagnetic valve 22 and a third electromagnetic valve 23, and the control lever 2 is used for controlling the three electromagnetic valves to work;
preferably, the track control mechanism comprises a master cylinder 24, the master cylinder 24 is arranged below the attitude cylinder group, the movable end of the master cylinder 24 is arranged on the lower surface of a transmission supporting plate 25, the bottom of the attitude cylinder group is arranged on the upper surface of the transmission supporting plate 25, five proximity sensors 26 are arranged on the side surface of the master cylinder 24 along the lifting direction of the movable end of the master cylinder, the five proximity sensors 26 are respectively connected with five aiming lamps 16, the master cylinder 24 is connected with an air source 27, a fourth electromagnetic valve 29 and a fifth electromagnetic valve 37 are arranged on a pipeline between the air source 27 and the master cylinder 24, and the fourth electromagnetic valve 29 and the fifth electromagnetic valve 37 are controlled by an accelerator rod 3;
preferably, the air inlet of the main cylinder 24 is communicated with the attitude cylinder group through a pipeline, the pipeline comprises two first air inlet pipes 34 communicated with the air inlets of the two rolling cylinders 17 and a second air inlet pipe 35 communicated with the air inlet of the pitching cylinder 18, and the first air inlet pipes 34 are provided with one-way flow limiting valves 36;
preferably, the posture and centering indicating mechanism 4 and the track indicating mechanism 12 are both arranged above the control box 31, and the posture control mechanism and the track control mechanism are arranged inside the control box 31;
preferably, an annular surrounding edge 13 is arranged at the circumference of the ferry plate 5, and a transparent cover 14 is arranged at the top of the surrounding edge 13;
preferably, the outer circumference of the central area 6 and the outer circumference of the middle ring area 7 are provided with upward convex ring lines 15, and the height of the ring lines 15 is 0.5-2 mm;
preferably, the diameter of the ferry plate 5 is 250-300mm, the diameter of the attitude ball 11 is 40-60mm, the diameter of the circle center area 6 is 40-60mm, and the diameter of the middle ring area 7 is 60-150 mm;
preferably, the posture ball 11 is white, the central area 6 is green, the middle ring area 7 is orange, and the outer ring area 8 is red;
preferably, two parallel lines 19 for simulating the course borders are provided in the outer annular zone 8.
The special teaching aid based on the airplane attitude control is ingenious in structural design, the stress state of a carrier landing airplane in flight can be visually shown through the cooperation of the attitude, the centering indicating mechanism 4 and the flight path indicating mechanism 12, the control lever 2 is independently controlled, the designated cylinder in the attitude cylinder group is deflated, the height of the movable end of the deflated cylinder is reduced, the attitude of the ferry plate 5 is changed, the attitude ball 11 rolls to one side of the deflated cylinder, meanwhile, the main cylinder 24 is deflated, the movable end of the main cylinder 24 is lowered, and the flight path can descend when the attitude of the simulated airplane is adjusted. When the throttle lever 3 is controlled independently, the pressure in the main cylinder 24 changes, the attitude cylinder group acts therewith, when the fuel is added, the active end of the main cylinder 24 rises, the two roll cylinders 17 have less air input than the pitch cylinder 18 due to the action of the one-way flow limiting valve 36, and the ferry plate 5 is downward-inclined (front-low and rear-high), so that the aircraft attack angle is reduced when the fuel is added. When oil is reduced, the movable end of the main cylinder 24 descends, the two rolling cylinders 17 do not act under the action of the one-way flow limiting valve 36, air in the pitching cylinder 18 flows to the main cylinder 24, the movable end of the pitching cylinder descends, and the ferry plate 5 tilts upwards (high in the front and low in the back), so that the aircraft attack angle is increased when oil reduction is simulated. When the control rod 2 and the throttle rod 3 are subjected to compound control, the state response of the carrier aircraft is comprehensively simulated. In conclusion, the landing aircraft stress state can be reproduced, the landing flight principle can be intuitively sensed, and the landing driving key can be experienced. Meanwhile, each cylinder, pipeline and valve can be disassembled and assembled, and students need to memorize and analyze and flexibly apply learned knowledge in the manual assembly process, so that the ship landing flight knowledge fusion is communicated, and the knowledge internalization is completed.
Drawings
FIG. 1 is a schematic structural diagram of a special teaching aid based on airplane attitude control according to the invention;
FIG. 2 is a schematic view of a driver seat configuration;
FIG. 3 is a schematic structural diagram of a control box, a posture and centering indicating mechanism and a track indicating mechanism;
FIG. 4 is a side view of the attitude and centering indicator mechanism;
FIG. 5 is a schematic structural view of a ferry plate;
FIG. 6 is a schematic view of the structure of the ferry plate with the skirt and transparent cover removed;
FIG. 7 is a top view of the ferry plate;
fig. 8 is a schematic structural diagram of the attitude control mechanism and the track control mechanism.
In the figure: 1. a driving seat; 2. a joystick; 3. a throttle lever; 4. a posture and centering indication mechanism; 5. a ferry plate; 6. a circle center area; 7. a middle loop region; 8. an outer ring area; 9. centering a line; 10. a splayed indicator line; 11. a posture ball; 12. a track indicating mechanism; 13. a surrounding edge; 14. a transparent cover; 15. looping; 16. an aiming lamp; 17. a rolling cylinder; 18. a pitching cylinder; 19. parallel lines; 20. a diametric line; 21. a first solenoid valve; 22. a second solenoid valve; 23. a third electromagnetic valve; 24. a master cylinder; 25. a transmission supporting plate; 26. a proximity sensor; 27. a gas source; 28. a tee joint; 29. a fourth solenoid valve; 31. A control box; 32. a reference light strip; 33. an airplane target platform; 34. a first intake pipe; 35. a second intake pipe; 36. a one-way flow-limiting valve; 37. and a fifth solenoid valve.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
The special teaching aid based on the airplane attitude control in the embodiment refers to fig. 1-8, and comprises a driving seat 1, wherein an attitude and centering indicating mechanism 4 for simulating the attitude of the airplane and a track indicating mechanism 12 for simulating the flying height of the airplane are arranged in front of the driving seat 1, an attitude control mechanism for driving the attitude and centering indicating mechanism 4 to pitch, roll and center is arranged below the attitude and centering indicating mechanism 4, the track indicating mechanism 12 comprises a plurality of aiming lamps 16 which are vertically arranged, a track control mechanism for driving the aiming lamps 16 to turn on and off is arranged below the track indicating mechanism 12, an operating rod 2 for operating the attitude control mechanism is arranged at the front end of the driving seat 1, and an accelerator rod 3 for operating the track control mechanism is arranged at the right side. The posture and centering indicating mechanism 4 and the track indicating mechanism 12 are arranged above the control box 31, and the posture control mechanism and the track control mechanism are arranged inside the control box 31.
The cockpit 1, the joystick 2 and the throttle lever 3 together constitute a simulated steering device that provides simulated steering inputs for the throttle lever and the joystick of the aircraft for changing flight conditions or eliminating flight deviations. The driving seat 1, the operating rod 2 and the accelerator lever 3 are designed according to the actual installation size 1:1, so that better operation input experience is guaranteed.
The flight path indicating mechanism 12 gives a light-watching flight reference to finish light-watching flight training. The 16 height of aiming lamp through a plurality of vertical overall arrangement of throttle lever 3 control is bright to go out and is changed, when refueling, is located the 16 lamp balls of aiming lamp of eminence and lights, when subtracting oil, is located the aiming lamp 16 of eminence and goes out, and the aiming lamp 16 that is located the low department lights, and the bright removal that aims lamp 16 represents the height change of track. The track indicating mechanism 12 is arranged in front of the left side of the driver seat 1, is manufactured according to the dimension of actual-installed 1/5, and is a green standard lamp strip 32 in the horizontal direction, and is about 100 mm long and about 20 mm wide; the aiming lamp group formed by the aiming lamps 16 is vertical, the height is about 150mm, the width is about 50mm, the aiming lamps 16 are correspondingly lightened along with the up-and-down movement of the gravity center of the ferry plate 5 and are matched with the green standard lamp strip 32 to indicate the height and the variation trend of the eye positions of the trainees. The student judges the height of the eye position relative to the ideal glide slope, and adjusts the position of the throttle lever 3 by taking the height as an operation reference to control the glide angle (height), so that the aiming lamp at the central position is lighted.
The posture and centering indicating mechanism 4 comprises a circular ferry plate 5, an airplane target table 33 is installed on the outer circumference of the ferry plate 5, a posture ball 11 is placed on the ferry plate 5, a circle center area 6, a middle ring area 7 and an outer ring area 8 are sequentially drawn on the upper surface of the ferry plate 5 from inside to outside by taking the circle center as the center, a centering line 9 is drawn along the diameter direction of the ferry plate 5, splayed indicating lines 10 are symmetrically drawn by taking the centering line 9 as the center line, the splayed indicating lines 10 are provided with two groups and symmetrically arranged in the outer ring area 8 by taking the middle ring area 7 as the center, and the narrow end of each splayed indicating line 10 is close to the middle ring area 7; preferably, an annular surrounding edge 13 is arranged at the circumference of the ferry plate 5, and a transparent cover 14 is arranged at the top of the surrounding edge 13. The outer circumference of the central area 6 and the outer circumference of the middle ring area 7 are provided with upward convex ring lines 15, and the height of the ring lines 15 is 0.5-2 mm. The posture ball 11 is white, the central area 6 is green, the middle ring area 7 is orange, and the outer ring area 8 is red. Two parallel lines 19 are provided in the outer annular zone 8 for simulating the course borders. Wherein the diameter of the ferry plate 5 is 250-300mm, the diameter of the circle center area 6 is 40-60mm, and the diameter of the middle ring area 7 is 60-150 mm.
The attitude control mechanism comprises an attitude cylinder group arranged below the ferry plate 5, the attitude cylinder group comprises two rolling cylinders 17 and a pitching cylinder 18, the movable ends of the three cylinders are arranged on the lower surface of the ferry plate 5 through universal bearings, the movable ends of the two rolling cylinders 17 are arranged at two ends of a diameter line 20 of the ferry plate 5, the diameter line 20 is perpendicular to a centering line 9, the movable end of the pitching cylinder 18 is arranged at the rear end of the centering line 9, the three cylinders are respectively connected with three air discharging pipelines, the three air discharging pipelines are respectively provided with electromagnetic valves, namely a first electromagnetic valve 21, a second electromagnetic valve 22 and a third electromagnetic valve 23, and the control rod 2 is used for controlling the three electromagnetic valves to work.
The attitude and centering indication mechanism 4 is used for simulating the attitude change and centering adjustment state and operation feedback of the carrier-based aircraft in the carrier landing process. The attitude and centering indicating device 4 comprises an attitude ball 11, a ferry plate 5 and an airplane target table 33. The attitude deviation and the centering deviation are judged according to the position of the attitude ball 11 relative to the central area 6 of the ferry plate 5, and the attitude deviation refers to the deviation between the front and back of the relative position of the attitude ball 11 and the ferry plate 5. If the attitude ball 11 is in front of the diameter line 20 of the ferry plate 5, namely the attitude (attack) angle is too small, the operating rod 2 needs to be pulled backwards, the operating rod 2 controls the third electromagnetic valve 23 to realize the conduction of the air discharge pipeline of the pitching cylinder 18, after the pull rod is pulled backwards, the movable end of the pitching cylinder 18 descends, and the rear end of the ferry plate 5 sinks. If the attitude ball 11 is behind the diameter line 20 of the ferry plate 5, that is, the attitude (attack) angle is too large, the operating lever 2 is pushed forward, the operating lever 2 controls the first electromagnetic valve 21 and the second electromagnetic valve 22 on the air discharging pipelines of the two rolling cylinders 17, the air discharging pipelines of the two rolling cylinders 17 are simultaneously conducted, the movable ends of the two rolling cylinders 17 descend, and after the operating lever 2 is pushed forward, the front end of the ferry plate 5 sinks.
The centering deviation is the deviation of the relative position of the attitude ball 11 and the circle center area of the ferry plate 5 from left to right, and the attitude ball 11 is deviated to the left on the left side of the centering line 9 of the ferry plate 5 and needs to be corrected to the right; the correction is to the left, i.e. to the right, on the right side of the centering line 9 of the ferry plate 5. The control rod 2 presses the left lever, the roll cylinder 17 positioned on the left side is deflated to enable the left side of the ferry plate 5 to sink, and as the roll cylinder 17 on the left side is communicated with the pitch cylinder 18 through the main cylinder 24, the pitch cylinder 18 is also deflated when the roll cylinder 17 on the left side is deflated, so that the left side of the ferry plate 5 sinks together. The control rod 2 presses the rod to the right, the rolling cylinder on the right side is deflated, and as the rolling cylinder 17 on the right side is communicated with the pitching cylinder 18 through the main cylinder 24, when the rolling cylinder 17 on the right side is deflated, the pitching cylinder 18 is also deflated, so that the right side of the ferry plate 5 is sunk together.
The kinematic response of the attitude ball 11 is determined by its structural weight, steering amplitude, and the shape of the upper surface of the ferry plate. The size of the attitude ball 11 is proportional to the wingspan of the real airplane, the diameter is 52.5 mm, the influence of air on the movement of the attitude ball can be ignored, and the size can meet the requirement of visual position judgment.
The attitude cylinder groups are arranged in an inverted triangle shape, the left and right two (two small and one large) are rolling cylinders 17, and the rear part is a pitching cylinder 18. The bottoms of the three attitude cylinders are communicated with a main cylinder 24 through pipelines, the air inlets of the main cylinder 24 are communicated with an attitude cylinder group through pipelines, the pipelines comprise two first air inlet pipes 34 communicated with the air inlets of the two rolling cylinders 17 and a second air inlet pipe 35 communicated with the air inlets of the pitching cylinders 18, and the first air inlet pipes 34 are provided with one-way flow limiting valves 36.
The track control mechanism comprises a main air cylinder 24, the main air cylinder 24 is arranged below the attitude air cylinder group, the movable end of the main air cylinder 24 is arranged on the lower surface of a transmission supporting plate 25, the bottom of the attitude air cylinder group is arranged on the upper surface of the transmission supporting plate 25, five proximity sensors 26 are arranged on the side surface of the main air cylinder 24 along the lifting direction of the movable end of the main air cylinder, the five proximity sensors 26 are respectively connected with five aiming lamps 16, the main air cylinder 24 is connected with an air source 27, a fourth electromagnetic valve 29 and a fifth electromagnetic valve 37 are arranged on a pipeline between the air source 27 and the main air cylinder 24, and the fourth electromagnetic valve 29 and the fifth electromagnetic valve 37 are controlled by an accelerator rod 3.
Transmission logic between the throttle lever 3 and the aiming light 16: the throttle lever 3 controls a fourth electromagnetic valve 29, when the throttle lever 3 is pushed forward, the fourth electromagnetic valve 29 is switched on, the air source 27 is filled in the main air cylinder 24, the movable end of the main air cylinder 24 is filled with air and ascends, the height of the gravity center of the ferry plate 5 is further changed, and the air source 27 is respectively transmitted to the corresponding aiming lamps 16 through the five proximity sensors 26. The ferry plate 5 is raised, the corresponding proximity switch 26 is turned on, and the sighting lamp 16 corresponding to the proximity switch 26 is turned on. When the oil is reduced (the throttle lever 3 is pushed backwards), the fifth electromagnetic valve 37 is switched on, the main cylinder 24 is deflated, the ferry plate 5 descends, and the air is transmitted to the corresponding aiming lamps 16 through the five proximity sensors 26.
Table 1: cylinder selection type example meter
TABLE 1 cylinder selection type example table
| Name (R) | Performance of | Model number | Number of | Remarks for note |
| Rolling cylinder | Low-friction cylinder | FCS-20-48-S1- |
2 | With spring |
| Pitching cylinder | Low-friction cylinder | FCS-20-48-S0- |
1 | With spring |
| Master cylinder | Thin cylinder | SC60×150 | 1 | With spring |
The throttle lever 3 is refueled: the fourth electromagnetic valve 29 is connected, the air source 27 supplies air to the main air cylinder 24, the main air cylinder 24 is communicated with the attitude cylinder group, the main air cylinder 24 is communicated with the two rollover air cylinders 17 through the one-way throttle valves 36 respectively, and air flow can only flow from the main air cylinder 24 to the rollover air cylinders 17 and cannot flow reversely; the master cylinder 24 is in direct communication with the pitch cylinder 18 and air flow is free to flow between the master cylinder 24 and the pitch cylinder 18. When the refuel aircraft is refueled, the main air cylinder 24 is filled with air, the pressure is increased, the piston of the main air cylinder 24 begins to rise upwards, the transmission supporting plate 25 begins to rise, the proximity sensor 26 corresponding to the position of the transmission supporting plate 25 controls the corresponding aiming lamp 16 to light up, and the mark refuel aircraft track rises. As the pressure of the main cylinder 24 increases, the airflow starts to flow to the attitude cylinder group, and as the airflow flowing to the tumble cylinder 17 passes through the one-way throttle valve 36, the flow rate becomes slow, and the action speed and the amplitude of the tumble cylinder 17 become slow; because the air flow flowing to the pitching air cylinder 18 is not limited by throttling, the air flow speed is high, and the pitching air cylinder 18 has high action speed and large amplitude. Thus, with the main cylinder 24 intake, the ferry plate 5 has a tendency to tip-down (low front and high rear), corresponding to a situation where the aircraft acceleration angle of attack becomes small.
Oil reduction of the throttle lever 3: the fifth solenoid valve 37 is switched on, the master cylinder 24 is deflated, the pressure is reduced, the piston of the master cylinder 24 begins to descend, the transmission supporting plate 25 begins to descend, and the proximity sensor 26 corresponding to the position of the transmission supporting plate 25 controls the corresponding aiming lamp 16 to light up to mark the track of the refueled aircraft to sink. As the pressure of the main cylinder 24 is reduced, the airflow starts to flow from the attitude cylinder group to the main cylinder 24, and because the main cylinder 24 is communicated with the tumble cylinder 17 in a one-way mode, the airflow cannot flow from the tumble cylinder 17 to the main cylinder 24, and the tumble cylinder 17 does not act; the pressure of the main cylinder 24 is reduced, the gas in the pitching cylinder 18 can smoothly flow to the main cylinder 24, the backflow speed is high, the pressure of the pitching cylinder 18 is reduced, the piston falls back, and the ferry plate 5 has a head-up trend (high in the front and low in the back) and conforms to the increase of the deceleration attack angle.
Pulling the operating lever 2: when the control rod 2 is pulled backwards, the third electromagnetic valve 23 of the pitching cylinder 18 is switched on, at the moment, the pitching cylinder 18 is deflated, the pressure is reduced, the height of the piston is reduced, the two rolling cylinders 17 do not act, the rear end of the ferry plate 5 is reduced, the head-up trend is achieved, and the head-up trend is consistent with the increase of the attack angle of the tie rod airplane. The pitching cylinder 18 is deflated, the air pressure is reduced, the air pressure of the main cylinder 24 is reduced due to the fact that the main cylinder 24 is communicated with the pitching cylinder 18, the piston height of the main cylinder 24 is reduced, the transmission supporting plate 25 begins to descend, and the mark is that the track of the trolley aircraft sinks.
Pushing the operating lever 2: when the control rod 2 is pushed forwards, the first electromagnetic valve 21 and the second electromagnetic valve 22 of the two rolling cylinders 17 are switched on, the two rolling cylinders 17 deflate, the pressure is reduced, the height of the piston is reduced, and the two rolling cylinders 17 are communicated with the main cylinder 24 through the one-way throttle valve 36. At this time, the two tumble cylinders 17 are simultaneously lowered in height. Because the pitching cylinder 18 is communicated with the main cylinder 24, the main cylinder 24 is communicated with the rolling cylinder 17 through the one-way flow limiting valve 36, the pressure of the pitching cylinder 18 is reduced and is slower than that of the rolling cylinder 17, so that the piston reduction speed of the pitching cylinder 18 is lower than that of the rolling cylinder 17, and the ferry plate 5 has a head-lowering tendency and is consistent with the reduction of the push rod attack angle. The rollover cylinder 17 is deflated, the air pressure is reduced, the main cylinder 24 is deflated, the air pressure is reduced, the piston descends, the transmission supporting plate 25 begins to descend, and the mark of the push rod aircraft track sinks.
Left-right pressing of the lever 2: the electromagnetic valve of the corresponding rolling cylinder 17 is switched on, the pressure of the rolling cylinder 17 at the same side is reduced, and the height of the piston is reduced; the rolling cylinder 17 is communicated with the main cylinder 24 through a one-way throttle valve 36, the air of the main cylinder 24 flows to the deflated rolling cylinder 17, the pressure of the main cylinder 24 is reduced, the pitching cylinder 18 is communicated with the main cylinder 24, the air of the pitching cylinder 18 flows to the main cylinder 24 and flows to the deflated rolling cylinder 17 through the main cylinder 24, the pressure of the cylinders is reduced, and the height of the piston of the pitching cylinder 18 is lowered appropriately; the other tumble cylinder 17 is restricted by the one-way throttle valve, so that gas cannot flow from the tumble cylinder 17 to the main cylinder 24, and the piston height is unchanged without operation. Thus, the ferry plate 5 will deflect to the side of the deflation tumble cylinder 17, and at the same time, the pressure in the main cylinder 24 is lost, the piston height drops, and the marker aircraft track sinks, which corresponds to the law of height lost by the crossbar-operated aircraft.
The special teaching aid based on aircraft attitude control of this embodiment possesses the teaching experiment function that accords with the law of landing a ship, structural principle is visual, the factor embodies abundant, and the student accomplishes the theoretical application of landing a ship flight in observation, analysis, discussion and assembling process, and the landing principle fuses to link up, promotes knowledge internalization. The student can be effectively supported to discover rules, clear logics, develop evaluation and think, distinguish and innovate.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (10)
1. The utility model provides a special teaching aid based on aircraft attitude control, a serial communication port includes the driving seat, driving seat the place ahead is equipped with gesture and centering indicating mechanism who is used for simulating the aircraft gesture, a flight path indicating mechanism for simulating aircraft flying height, gesture and centering indicating mechanism below is equipped with the gesture control mechanism who is used for driving gesture and centering indicating mechanism every single move, roll and centering motion, flight path indicating mechanism includes a plurality of aiming lamps of vertical arranging, flight path indicating mechanism below is equipped with the flight path control mechanism who is used for driving aiming lamp bright and go out, the driving seat front end is equipped with the control rod that is used for controlling gesture control mechanism work, the right side is used for controlling the throttle lever of flight path control mechanism work.
2. The special teaching aid based on the airplane attitude control as claimed in claim 1, wherein the attitude and centering indicating mechanism comprises a circular ferry plate, an airplane target table is mounted on the outer circumference of the ferry plate, an attitude ball is placed on the ferry plate, a circle center area, a middle ring area and an outer ring area are sequentially drawn on the upper surface of the ferry plate from inside to outside by taking the circle center as the center, a centering line is drawn along the diameter direction of the ferry plate, splay indicating lines are symmetrically drawn by taking the centering line as the center line, two groups of splay indicating lines are arranged and are symmetrically arranged in the outer ring area by taking the middle ring area as the center, and the narrow end of each splay indicating line is close to the middle ring area.
3. The special teaching aid based on aircraft attitude control according to claim 2, wherein the attitude control mechanism comprises an attitude cylinder group arranged below the ferry plate, the attitude cylinder group comprises two rolling cylinders and one pitching cylinder, the movable ends of the three cylinders are arranged on the lower surface of the ferry plate through universal bearings, the movable ends of the two rolling cylinders are arranged at two ends of a diameter line of the ferry plate, the diameter line is perpendicular to the centering line, the movable end of the pitching cylinder is arranged at the rear end of the centering line, the three cylinders are respectively connected with three air discharging pipelines, electromagnetic valves are respectively arranged on the three air discharging pipelines, and the electromagnetic valves are respectively a first electromagnetic valve, a second electromagnetic valve and a third electromagnetic valve, and the operating rod is used for controlling the three electromagnetic valves to work.
4. The special teaching aid based on the airplane attitude control is characterized in that the track control mechanism comprises a master cylinder, the master cylinder is arranged below an attitude cylinder group, the movable end of the master cylinder is arranged on the lower surface of a transmission supporting plate, the bottom of the attitude cylinder group is arranged on the upper surface of the transmission supporting plate, five proximity sensors are arranged on the side surface of the master cylinder along the lifting direction of the movable end of the master cylinder, the five proximity sensors are respectively connected with five aiming lamps, the master cylinder is connected with an air source, a pipeline between the air source and the master cylinder is provided with a fourth electromagnetic valve and a fifth electromagnetic valve, and the fourth electromagnetic valve and the fifth electromagnetic valve are controlled by throttle levers.
5. The special teaching aid based on the airplane attitude control is characterized in that the air inlets of the main cylinders are communicated with the attitude cylinder group through pipelines, the pipelines comprise two first air inlet pipes communicated with the air inlets of the two rolling cylinders and a second air inlet pipe communicated with the air inlets of the pitching cylinders, and the first air inlet pipes are provided with one-way flow limiting valves.
6. The special teaching aid based on aircraft attitude control of claim 1, wherein the attitude and centering indicating mechanism and the track indicating mechanism are arranged above the control box, and the attitude control mechanism and the track control mechanism are arranged in the control box.
7. The special teaching aid based on the airplane attitude control is characterized in that an annular surrounding edge is arranged on the circumference of the ferry plate, and a transparent cover is arranged at the top of the surrounding edge.
8. A special teaching aid based on aircraft attitude control as claimed in claim 2, wherein the outer circumference of the central region and the outer circumference of the middle ring region are provided with upwardly convex ring lines, and the height of the ring lines is 0.5-2 mm.
9. The special teaching aid based on the airplane attitude control as claimed in claim 2, wherein the diameter of the ferry plate is 250-300mm, the diameter of the attitude ball is 40-60mm, the diameter of the circle center area is 40-60mm, and the diameter of the middle ring area is 60-150 mm; the color of the posture ball is white, the central area is green, the middle ring area is orange, and the outer ring area is red.
10. A specialized teaching aid for aircraft attitude control in accordance with claim 2 wherein two parallel lines are provided in the outer loop area for simulating the course sidelines.
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