CN100343884C - Plane fleight principle comprehensive demonstration instrument - Google Patents
Plane fleight principle comprehensive demonstration instrument Download PDFInfo
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- CN100343884C CN100343884C CNB2005100426096A CN200510042609A CN100343884C CN 100343884 C CN100343884 C CN 100343884C CN B2005100426096 A CNB2005100426096 A CN B2005100426096A CN 200510042609 A CN200510042609 A CN 200510042609A CN 100343884 C CN100343884 C CN 100343884C
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Abstract
The present invention relates to a comprehensive demonstrator for flying principle of airplanes. In order to overcome the defect that demonstration equipment in the prior art has single function and can not simulate various flying postures of an airplane under air dynamic action, the present invention is characterized in that a small-scale wind tunnel is formed on the box body of the demonstrator to simulate a flow field around the airplane, and a joint bearing arranged on the back of the gravitational center of an airplane model (6) is hung in the box body of the demonstrator through a hanging device. The hanging device is in a balance lever structure, and a hanging rod (3) and a balance weight rod (10) are respectively positioned on both ends of a balance rod (2), wherein a support rod (4)positioned in the middle of the balance rod (2) is movably connected with the balance rod (2) so as to ensure that the balance rod (2) and the hanging rod (3) rotate freely in a vertical plane and realize various flying postures. The present invention can simulate deviation, roll, pitching and various other flying postures of an airplane, and visibly shows the flying principle of the airplane. With the characteristics of convenient operation, low cost and high generalization, the present invention can be widely used for aviation teaching and aviation popular science.
Description
(1) technical field under:
The present invention relates to the instrument of Demonstrator aircraft flight theory, is the plane fleight principle comprehensive demonstration instrument that is used for aviation science popularization teaching.
(2) background technology:
Technology related to the present invention is a smoke wind tunnel.
The aerodynamic teaching aid of smoke wind tunnel Chang Zuowei, stream condition that can be when popular simulated aircraft moves in air, the smog that passes through to be discharged can clearly be demonstrated trend and the variation that air flow stream is crossed model.Model in the smoke wind tunnel generally all is static, and the various flight attitudes that can not the simulated aircraft model produce under the effect of air-flow are as driftage, lift-over and pitching.The limitation of smoke wind tunnel mainly is that function ratio is more single, can only realize the stream condition of the single movement formation of certain model, and popular the shortage undergoes.
In 91108908 patented claims of Patent Office of the People's Republic of China, a kind of dependence Electromagnetic Drive is disclosed, realize taking off, fly and landing of model aircraft.Though this technology can be showed the flight course of aircraft, can not go to explain flight theory with aerodynamic principle.
(3) summary of the invention:
For overcoming the function singleness that exists in the prior art, deficiency that can't the various motions of simulated flight device under aerodynamic effect the present invention proposes a kind of plane fleight principle comprehensive demonstration instrument.
The present invention includes casing, Demonstrator aircraft model and telechiric device, erecting by overhang, used the wind-tunnel technology, utilize the casing of demonstrator to form small-sized wind tunnel simulation aircraft flow field on every side, produce air-flow by blower fan, under this flow field effect, by each rudder face of telechiric device operating aircraft model, thereby make the model aircraft that is installed in the casing produce lift, and realize various flight attitudes.Technical characterictic of the present invention is that casing is two-layer: the upper strata is for installing the control box of erecting by overhang, and lower floor is a demonstration box, and model aircraft hangs in the demonstration box by the suspension rod on the erecting by overhang; The upper end of suspension rod is connected on the balance stem, and the lower end is connected with the oscillating bearing that is positioned at model aircraft center of gravity place, makes the model of an airplane to rotate around suspension rod, to realize the various flight attitudes of aircraft.
Erecting by overhang comprises balance stem, suspension rod, weight linear meter and support bar, and be the balanced lever structure: suspension rod and weight linear meter lay respectively at the two ends of balance stem, and support bar is positioned at the middle part of balance stem, makes total system reach mobile equilibrium.
Realize flexibly connecting by passing through U type bearing between removable pin and the support bar between balance stem and suspension rod, the weight linear meter.
The present invention can show plane fleight principle visually, the attitude of various motions such as simulated aircraft driftage, lift-over, pitching, have characteristics easy to operate, visual in image, that cost is low, popularization is strong, spectators are experienced in person and experience the mechanism that aircraft flight attitude changes, simultaneously the popular science knowledge of decorrelation, improve the interest of popular learning science knowledge, thereby improve the whole nation's quality of science.
(4) description of drawings:
Accompanying drawing 1 is the structural representation of plane fleight principle comprehensive demonstration instrument;
Accompanying drawing 2 is structural representations of erecting by overhang.
Wherein:
1. control box 2. balance stems 3. suspension rods 4. support bars 5. screen packs
6. model aircraft 7. demonstration boxs 8. supports 9. blower fans 10. weight linear meters
11.U type bearing 12,13,14. removable pins
(5) embodiment:
Present embodiment is by erecting by overhang, and model aircraft 6 is placed air, and by the flow field around the small-sized wind tunnel simulation aircraft.Under this flow field effect, make aircraft produce lift; Each rudder face by the control aircraft makes model aircraft realize various flight attitudes.
Present embodiment comprises Demonstrator aircraft model 6, casing 1, erecting by overhang.Specific implementation process is:
Casing is made with the hard iron sheet, is divided into two-layer: the upper strata is for installing the control box 1 of erecting by overhang, and lower floor is a demonstration box 7.The cross section of demonstration box 7 is a square structure, is equivalent to an easy wind-tunnel, and an end is air inlet place, and the screen pack 5 that is used for rectification is installed, and the other end is equipped with blower fan 9; Side, demonstration box 7 middle part is equipped with sight glass.Threaded hole that support bar 4 is installed and the through hole that suspension rod 3 is installed are arranged on the dividing plate between control box 1 and the demonstration box 7, and model aircraft 6 passes dividing plate by the suspension rod on the erecting by overhang 3 and hangs in the demonstration box 7.Support 8 is arranged under the casing.
Erecting by overhang (accompanying drawing 2) comprises balance stem 2, suspension rod 3, support bar 4 and weight linear meter 9, is the balanced lever structure:
At balance stem 2 one ends connecting hole is arranged, be connected by the connecting hole of removable pin 12 with suspension rod 3 upper ends, the diameter of removable pin 12 should be less than the connecting hole aperture, and enough gaps are arranged between the connecting hole, to guarantee can to produce relative motion between suspension rod 3 and the balance stem 2 in vertical plane.Model aircraft 6 is positioned at suspension rod 3 lower ends, and the oscillating bearing by back, center of gravity of airplane place is connected with suspension rod 3, makes model aircraft to rotate around suspension rod, to realize various flight attitudes.
The other end of balance stem 2 has connecting hole, and also there is respective connecting weight linear meter 10 upper ends made from thin circle aluminium bar, flexibly connects by removable pin 14 and balance stem 2, and balances each other with the model aircraft 6 that is positioned at balance stem 2 one ends.The diameter of removable pin 14 should be less than the connecting hole aperture, and making has enough gaps between removable pin and the connecting hole, to guarantee can to produce relative motion between balance stem 2 and the weight linear meter 10 in vertical plane.
The upper end of support bar 4 is " T " font by U type bearing 11 and balance stem 2 and is connected: the middle part of balance stem 2 is useful on the connecting hole that connects U type bearing 11, on two end faces of U type bearing 11 connecting hole is also arranged respectively; Balance stem 2 is placed in the U type bearing 11, and the connecting hole with removable pin 13 connects on U type bearing and the balance stem flexibly connects both; The diameter of removable pin 13 should be less than the connecting hole aperture, and making has enough gaps between removable pin and the connecting hole, to guarantee that balance stem 2 can produce relative motion in vertical plane.There is screw thread the lower end of support bar 4, is connected with threaded hole on the dividing plate, thereby erecting by overhang is fixed on the dividing plate between demonstration box and the control box 1.
Claims (4)
1. plane fleight principle comprehensive demonstration instrument, comprise casing, blower fan (9), model aircraft (6), erecting by overhang and telechiric device, the casing of demonstrator forms the flow field around the small-sized wind tunnel simulation aircraft, model aircraft (6) is installed in the casing, produce air-flow by blower fan (9), be used for the aloft air flow field of simulated aircraft, realize various flight attitudes, it is characterized in that by each rudder face of telechiric device operating aircraft model:
A. casing is two-layer: the upper strata is for installing the control box (1) of erecting by overhang, and lower floor is demonstration box (7), and model aircraft (6) hangs in the demonstration box (7) by the suspension rod on the erecting by overhang (3);
B. erecting by overhang adopts the balanced lever structure, and suspension rod (3) and weight linear meter (10) lay respectively at the two ends of balance stem (2), and support bar (4) is positioned at the middle part of balance stem;
C. use respectively between balance stem (2) and suspension rod (3), the weight linear meter (10) removable pin (12,14), and support bar (4) between flexibly connect with U type bearing (11).
2. plane fleight principle comprehensive demonstration instrument according to claim 1 is characterized in that suspension rod (3) is connected by the oscillating bearing that is positioned at model aircraft center of gravity place with model aircraft (6).
3. plane fleight principle comprehensive demonstration instrument according to claim 1 is characterized in that being used for the aperture of the diameter of the removable pin (12,14) that balance stem (2) and support bar (4) be connected with weight linear meter (10) less than connecting hole.
4. plane fleight principle comprehensive demonstration instrument according to claim 1 is characterized in that erecting by overhang passes through support bar (4) and is fixed on the dividing plate between demonstration box (7) and the control box (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005100426096A CN100343884C (en) | 2005-04-28 | 2005-04-28 | Plane fleight principle comprehensive demonstration instrument |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2005100426096A CN100343884C (en) | 2005-04-28 | 2005-04-28 | Plane fleight principle comprehensive demonstration instrument |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1707563A CN1707563A (en) | 2005-12-14 |
| CN100343884C true CN100343884C (en) | 2007-10-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB2005100426096A Expired - Fee Related CN100343884C (en) | 2005-04-28 | 2005-04-28 | Plane fleight principle comprehensive demonstration instrument |
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| CN (1) | CN100343884C (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109100111A (en) * | 2018-07-06 | 2018-12-28 | 江西洪都航空工业集团有限责任公司 | A kind of vertical wind tunnel model free flight test delivery device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101499220B (en) * | 2009-01-24 | 2010-09-29 | 哈尔滨工业大学 | Method and apparatus for simulating large thruster on spacecraft |
| CN102024358A (en) * | 2010-12-16 | 2011-04-20 | 西北工业大学 | Airplane lift demonstration instrument for physics teaching |
| CN102059556B (en) * | 2010-12-18 | 2013-05-22 | 广州机床厂有限公司 | Installation structure of machine tool control cabinet |
| CN104485034B (en) * | 2014-12-28 | 2017-03-08 | 上海电机学院 | The wing fills aircraft simulation device |
| CN105222960B (en) * | 2015-11-13 | 2018-04-06 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of wind-tunnel support system bascule |
| CN105910791A (en) * | 2016-05-31 | 2016-08-31 | 中国航空工业集团公司西安飞机设计研究所 | Airplane wind tunnel test model installation device |
| CN107115678A (en) * | 2017-06-16 | 2017-09-01 | 中电科芜湖通用航空产业技术研究院有限公司 | Model aircraft support meanss |
| CN111613124A (en) * | 2019-02-26 | 2020-09-01 | 长春中国光学科学技术馆 | Science popularization device for demonstrating image stabilization technology |
| CN112700694A (en) * | 2019-10-22 | 2021-04-23 | 海鹰航空通用装备有限责任公司 | Three-dimensional display system of aircraft |
| CN111307396B (en) * | 2019-11-29 | 2021-03-05 | 厦门大学 | Model supporting structure, device and system for wind tunnel virtual flight test |
| CN114187804B (en) * | 2021-12-23 | 2024-03-26 | 中国人民解放军海军航空大学 | Aerodynamic force-based special flight training teaching aid and control method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09170962A (en) * | 1995-12-19 | 1997-06-30 | Fujita Corp | Wind environment evaluation system |
| JPH09203685A (en) * | 1996-01-26 | 1997-08-05 | Nkk Corp | Model support method in wind tunnel test and apparatus for the method |
| WO1999001854A1 (en) * | 1997-07-04 | 1999-01-14 | Anthonie Arie De Lange | A method and a device for producing three-dimensional physical reproductions |
-
2005
- 2005-04-28 CN CNB2005100426096A patent/CN100343884C/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09170962A (en) * | 1995-12-19 | 1997-06-30 | Fujita Corp | Wind environment evaluation system |
| JPH09203685A (en) * | 1996-01-26 | 1997-08-05 | Nkk Corp | Model support method in wind tunnel test and apparatus for the method |
| WO1999001854A1 (en) * | 1997-07-04 | 1999-01-14 | Anthonie Arie De Lange | A method and a device for producing three-dimensional physical reproductions |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109100111A (en) * | 2018-07-06 | 2018-12-28 | 江西洪都航空工业集团有限责任公司 | A kind of vertical wind tunnel model free flight test delivery device |
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| Publication number | Publication date |
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| CN1707563A (en) | 2005-12-14 |
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