CN219979001U - Aircraft pitching stability demonstration teaching aid - Google Patents
Aircraft pitching stability demonstration teaching aid Download PDFInfo
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- CN219979001U CN219979001U CN202321271166.8U CN202321271166U CN219979001U CN 219979001 U CN219979001 U CN 219979001U CN 202321271166 U CN202321271166 U CN 202321271166U CN 219979001 U CN219979001 U CN 219979001U
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Abstract
The utility model discloses an aircraft pitching stability demonstration teaching aid, which comprises: the device comprises an airplane model, a support frame, a balancing weight, a force measuring balance, a base and an air speed generating device, wherein the airplane model is connected with the support frame, the balancing weight is fixed in a fuselage of the airplane model, the support frame is connected with the force measuring balance, the force measuring balance is fixed on the base, and the air speed generating device is arranged in front of the airplane model. Force and moment generated by pitching of an aircraft model can be intuitively observed through a force measuring balance in the device, and the aircraft loses pitching stability and recovers pitching stability by continuously adjusting and detaching the vertical tail and the horizontal tail, so that influence factors and characteristics of the pitching stability are demonstrated, theory and practice are combined, and teaching effect is improved. The device also has the advantages of convenient observation, good demonstration effect, low cost, simple operation, good portability and the like.
Description
Technical Field
The utility model belongs to the field of aerodynamics and flight mechanics teaching of an airplane, relates to an important means of aerodynamics and flight mechanics teaching research of the airplane, namely simulation demonstration, and particularly relates to an airplane pitching stability demonstration teaching aid.
Background
The simulation demonstration is an important teaching means for enhancing the visual perception of students. The simulation demonstration is to realize reality of some objects and phenomena. For objective reasons, the teaching of aircrew class can not describe the image of some important phenomena occurring when the aircraft actually flies, watching the video lacks substitution feeling, and independent experimental teaching or visiting is difficult to ensure in time or effect, and the simulation demonstration can be used for teaching some important flying phenomena, concepts and definitions in combination with class teaching. Each theoretical breakthrough in the development of fluid mechanics and its application in engineering are almost always started from the demonstration of flow phenomena. For example, reynolds transition experiment in 1880, mach shock phenomenon experiment in 1888, prandial in 1904 put forward the concept of boundary layer, von karman's analysis of cylindrical vortex street by 1912, and none of them is based on demonstration.
For a fixed wing aircraft, the aircraft has pitch stability as long as the aircraft's focal point is behind the aircraft's center of gravity. At present, a normal layout (with the wings in front and the horizontal tails in back) generally has pitching stability, namely, the pitching attitude changes due to disturbance in the flight process of an aircraft, and the aircraft can recover to the original attitude without pilot operation. Of course, individual fighters may design the aircraft to be pitch static unstable (e.g., fighter-10, fighter-20) in order to increase lift as much as possible. Pitch stability is a relatively abstract concept of how to embody this characteristic when an aircraft with pitch stability actually flies, what is the influencing factor, and it is very important for flight students. While flight students lack actual flight training during school, knowledge of many flight phenomena remains mainly at the theoretical level, and although experience flight training is provided later, the training time is increased intangibly. The traditional classroom teaching is that a student sees or hears video animation or theoretical explanation, and the pitching stability of the airplane is difficult to be intuitively known and perceived. The on-site teaching is high in cost and the teaching effect is not ideal.
In view of the above, how to design an airplane pitching stability demonstration teaching aid which is practical, feasible, simple, convenient and easy to use and has good effect and method has important significance.
Disclosure of Invention
In order to solve the contradiction and problems existing in the traditional classroom teaching and the field teaching, better grasp the teaching for war and shorten talent training time, the utility model provides the plane pitching stability demonstration teaching aid which is not only suitable for the classroom demonstration teaching, but also has reference and reference practical values for science popularization teaching and the like.
An aircraft pitch stability demonstration teaching aid comprising: the device comprises an aircraft model, a support frame, a balancing weight, a force measuring balance, a base and a wind speed generating device, wherein the aircraft model is arranged on the support frame, the support frame supports the aircraft model and enables the aircraft model to generate pitching and yawing motions, the balancing weight is fixed in an aircraft model body, the bottom of the support frame is connected with the force measuring balance, the force measuring balance is fixed on the base, the wind speed generating device is arranged in front of the aircraft model to simulate forward incoming flow of an aircraft, the vertical tail and the horizontal tail of the aircraft model are detached so as to respectively demonstrate the influence of different factors on pitching stability, the support frame is provided with a pitching and yawing motion mechanism, so that the pitching stability of the aircraft is better displayed to students, the force measuring balance is connected with the aircraft model and the base, the force applied to the aircraft model is measured, and the moment of the aircraft model is measured.
Preferably, the aircraft model body is hollow and is internally provided with a baffle plate which plays a limiting role on the balancing weight. The aircraft model is hollow, can alleviate model weight, portable also does benefit to the realization modularization equipment, and the inside baffle that has of model fuselage not only is favorable to placing of balancing weight, can prevent more that the aircraft model from at every single move in-process, the demonstration error phenomenon that the balancing weight probably slides back and forth and lead to.
Preferably, the vertical tail of the aircraft model is detachable, and the pitching stability influence factor of the aircraft is mainly a horizontal tail wing, but the students are cognized differently, and the vertical tail wing is detachable, so that the effect of different factors on pitching stability can be respectively demonstrated in the teaching aid demonstration process, and the students can understand and master the different factors more deeply.
Preferably, the horizontal tail of the airplane model is detachable, so that the horizontal tail plays an important role in balancing the lifting force and keeping the pitching of the airplane stable for an actual airplane, the horizontal tail is detachable and rotatable, the pitching state of the airplane model can be clearly demonstrated and compared when the horizontal tail exists or not, the important role of a student on the horizontal tail is realized, and the situation that the pitching of the airplane is stable is kept is more comprehensively perceived and experienced.
Preferably, the balancing weight is placed inside the aircraft model, and the balancing weight is placed inside the aircraft model, so that the pneumatic appearance of the assembled whole set of model accords with the actual pneumatic layout of the aircraft, the demonstration effect is more practical, the interference caused by the external balancing weight to the air flow can be eliminated, and the demonstration effect is more scientific and reasonable.
Preferably, the support frame is a device with a two-axis rotating mechanism, and comprises a U-shaped support, a pitching plate for realizing pitching motion is hinged on the U-shaped support, a vertical rotating shaft for realizing yawing motion is arranged at the bottom of the U-shaped support, and the bottom of the vertical rotating shaft is screwed on the base. Whether the aircraft pitching has stability or not can be shown only in the movement process, after the two-axis rotating mechanism is connected with the aircraft model, the aircraft has pitching motion (the freedom degree rotating around the transverse axis) capability, the pitching characteristics of the aircraft under different conditions can be well demonstrated, students can understand related theories more thoroughly, and a foundation is laid for better and faster entering the aircraft in the follow-up process.
Preferably, the force measuring balance is used for measuring force and moment, when the aircraft flies, various pneumatic forces and moments under the pneumatic forces are generated, the aircraft generates pitching motion, the root cause is that the aircraft receives the moment around the transverse axis, the moment influences the pitching balance of the aircraft, and the change of the moment during pitching motion is shown through the data of the force measuring balance, so that students are helped to deepen understanding of knowledge.
Preferably, the wind speed generator is a speed-adjustable wind speed generator. The wind speed generating device is specifically a small miniature axial flow fan or a small miniature centrifugal fan, and the small miniature axial flow fan or the small miniature centrifugal fan is adopted, so that on one hand, the cost can be effectively reduced, and in addition, the portability of the wind speed generating device used as a teaching aid is also considered. Of course, a wind speed generator such as an electric fan may be used.
According to the aircraft pitching stability demonstration teaching aid, force and moment generated by pitching of an aircraft model can be intuitively observed through the force balance in the device, and through continuously adjusting and detaching the vertical tail and the horizontal tail, the aircraft loses pitching stability and recovers pitching stability, the influence factors and characteristics of the pitching stability are demonstrated, the theory and practice are combined, and the teaching effect is improved. The device also has the advantages of convenient observation, good demonstration effect, low cost, simple operation, good portability and the like.
Drawings
FIG. 1 is a schematic diagram of an aircraft pitch stability demonstration teaching aid;
fig. 2 is a schematic structural view of the support frame.
Description of the embodiments
The following describes specific embodiments of the present utility model with reference to the drawings.
Examples
An aircraft pitch stability demonstration teaching aid, as shown in fig. 1, specifically comprises: the device comprises an airplane model 1, a support frame 2, a balancing weight 3, a force measuring balance 4, a base 5 and a wind speed generating device 6, wherein the airplane model 1 is connected with the support frame 2, a horizontal tail 8 of the airplane model 1 can be detached, the support frame 2 can enable the airplane model 1 to generate pitching and yawing motions, the support frame 2 is a device with a two-axis rotating mechanism, a pitching plate 10 for realizing pitching motions is hinged to a U-shaped support 9,U type support 9, a vertical rotating shaft 11 for realizing yawing motions is arranged at the bottom of the U-shaped support 9, and the bottom of the vertical rotating shaft 11 is connected to the base 12 in a rotating mode. The balancing weight 3 is temporarily not used in the embodiment, the supporting frame 2 is connected with the force measuring balance 4, the force measuring balance 4 can measure the force and the moment born by the model, the force measuring balance 4 is fixed on the base 5, and the wind speed generating device 6 is arranged in front of the aircraft model 1. The wind speed generator 6 adopts a small centrifugal fan.
During simulation demonstration, the horizontal tail 8 of the airplane model is firstly installed and fixed. The wind speed generation device 6 is placed right in front of the aircraft model 1, so that the outlet axis of the wind speed generation device 6 is collinear with the longitudinal axis of the aircraft model 1, the rotation speed of the wind speed generation device 6 is continuously adjusted to simulate the incoming flow speed or the flying speed to change, and meanwhile, the aircraft model 1 is continuously stirred to enable the model to generate pitching motion, the pitching state of the aircraft model is observed, and relevant data of the force balance 4, particularly the change of pitching moment, is attended to. After repeated times, when the aircraft model 1 is stable, the horizontal tail 8 is removed, the aircraft model 1 is stirred again to generate pitching motion, a learner observes the recovery condition of the model and the data related to the force balance, and the learner intuitively and clearly understand the recovery condition of the pitching state of the aircraft model through repeated comparison of the recovery condition of the horizontal tail, so that the horizontal tail is a component for generating pitching balance for the aircraft with the focus behind the center of gravity in the actual flight process.
Examples
The aircraft pitching stability demonstration teaching aid in this embodiment has basically the same structure as that of embodiment 1, and the main difference is that: (1) The horizontal tail wing (horizontal tail 8) does not perform disassembly operation in the simulation demonstration process; (2) The vertical tail wing (vertical tail 7) is disassembled in the demonstration process; (3) The wind speed generating device 8 adopts a miniature axial flow fan, so that the size of the fan can be further reduced, and the maximum wind speed of the fan can be improved.
During simulation demonstration, the center line of the outlet of the wind speed generation device 6 is collinear with the longitudinal axis of the aircraft model 1, the rotation speed of the wind speed generation device 6 is continuously adjusted to simulate the incoming flow speed or the flying speed to change, and meanwhile the aircraft model 1 is continuously stirred to enable the model to generate pitching motion, the pitching state of the aircraft model 1 is observed, and relevant data of the force balance 4, particularly the change of pitching moment, is attended to. After repeated times, when the aircraft model is stable, the vertical tail wing (the vertical tail 7) is removed, the aircraft model 1 is stirred again to generate pitching motion, a learner observes the recovery condition of the model and the data related to the force balance, and under the condition of existence of the vertical tail 7, the pitching state of the aircraft model 1 cannot be recovered to be balanced, so that the learner can intuitively and clearly understand, and the vertical tail wing has no effect on pitching stability of the aircraft in the actual flight process.
Examples
The aircraft pitching stability demonstration teaching aid in this embodiment has basically the same structure as that of embodiment 2, and the main difference is that: (1) The vertical tail wing (vertical tail 7) does not perform disassembly operation in the simulation demonstration process; (2) the counterweight 3 is fixed inside the aircraft model 1.
During simulation demonstration, the center line of the outlet of the wind speed generation device 6 is collinear with the longitudinal axis of the aircraft model 1, the rotation speed of the wind speed generation device 6 is continuously adjusted to simulate the incoming flow speed or the flying speed to change, and meanwhile the aircraft model 1 is continuously stirred, so that pitching motion is generated by the model, the pitching state of the aircraft model 1 is observed, and related data of a force measuring balance, particularly the change of pitching moment, is attended to. After repeated times, the balancing weight 3 is installed and fixed at the front cabin of the aircraft model 1, the aircraft model 1 is stirred, the pitching balance state recovery condition of the model is observed, after repeated times of demonstration, the balancing weight 3 is installed and fixed at the rear cabin of the aircraft model 1, and the aircraft model is stirred again, so that pitching motion is generated and the pitching balance state recovery condition is observed. The balancing weight 3 is arranged at different positions in the aircraft model 1, so that the front and back positions of the focus of the aircraft and the gravity center of the model are changed, and the aircraft with the focus at the gravity center position is intuitively demonstrated to have pitching stability.
Finally, it should be noted that the foregoing description is only a preferred embodiment of the present utility model, and is not intended to limit the present utility model, and although the present utility model has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present utility model should be included in the protection scope of the present utility model.
Claims (7)
1. An aircraft pitch stability demonstration teaching aid, comprising: aircraft model (1), support frame (2), balancing weight (3), dynamometry balance (4), first base (5), wind speed generating device (6), aircraft model (1) are installed on support frame (2), and support frame (2) support aircraft model (1) and enable aircraft model (1) to produce every single move and yaw motion, balancing weight (3) are fixed in aircraft model (1) fuselage, and support frame (2) bottom is connected with dynamometry balance (4), and dynamometry balance (4) are fixed on first base (5), wind speed generating device (6) are arranged in aircraft model (1) the place ahead.
2. An aircraft pitch stability demonstration teaching aid according to claim 1, characterized in that the aircraft model (1) is hollow and internally provided with a spacer which limits the counterweight (3).
3. An aircraft pitch stability demonstration teaching aid according to claim 1 or 2, characterised in that the vertical tail (7) of the aircraft model (1) is detachable.
4. An aircraft pitch stability demonstration teaching aid according to claim 1 or 2, characterized in that the horizontal tail (8) of the aircraft model (1) is detachable.
5. The aircraft pitching stability demonstration teaching aid according to claim 1, wherein the support frame (2) is a device with a two-axis rotating mechanism and comprises a U-shaped support (9), a pitching plate (10) for realizing pitching motion is hinged on the U-shaped support (9), a vertical rotating shaft (11) for realizing yawing motion is arranged at the bottom of the U-shaped support (9), and the bottom of the vertical rotating shaft (11) is screwed on the second base (12).
6. An aircraft pitch stability demonstration teaching aid according to claim 1, characterised in that the force balance (4) is a force balance capable of measuring forces and moments.
7. An aircraft pitch stability demonstration teaching aid according to claim 1, characterised in that the wind speed generating means (6) is an adjustable speed axial flow or centrifugal fan.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321271166.8U CN219979001U (en) | 2023-05-24 | 2023-05-24 | Aircraft pitching stability demonstration teaching aid |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321271166.8U CN219979001U (en) | 2023-05-24 | 2023-05-24 | Aircraft pitching stability demonstration teaching aid |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219979001U true CN219979001U (en) | 2023-11-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321271166.8U Active CN219979001U (en) | 2023-05-24 | 2023-05-24 | Aircraft pitching stability demonstration teaching aid |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219979001U (en) |
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2023
- 2023-05-24 CN CN202321271166.8U patent/CN219979001U/en active Active
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