JPH0470534A - Aircraft-testing wind tunnel - Google Patents
Aircraft-testing wind tunnelInfo
- Publication number
- JPH0470534A JPH0470534A JP18448990A JP18448990A JPH0470534A JP H0470534 A JPH0470534 A JP H0470534A JP 18448990 A JP18448990 A JP 18448990A JP 18448990 A JP18448990 A JP 18448990A JP H0470534 A JPH0470534 A JP H0470534A
- Authority
- JP
- Japan
- Prior art keywords
- aircraft
- ground
- simulated
- building
- model
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims description 25
- 238000001556 precipitation Methods 0.000 claims abstract 2
- 238000007664 blowing Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 11
- 238000010586 diagram Methods 0.000 description 10
- 238000007796 conventional method Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 229920003002 synthetic resin Polymers 0.000 description 1
- 239000000057 synthetic resin Substances 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、航空機の模型を使用して、航空機の離陸２着
陸状態の空力特性等を試験するために使用する航空機試
験風洞に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an aircraft test wind tunnel used to test the aerodynamic characteristics of an aircraft during takeoff and landing conditions using an aircraft model.
従来は、第８〜１１図に示すように、風洞１９と地面板
２２．ランニングベルト２５を使用し、更には地面上を
台車３０．３６に航空ｌ！模型３２．３８を支持して、
レール２９．３４上を走行させて試験を行っている。Conventionally, as shown in FIGS. 8 to 11, a wind tunnel 19 and a ground plate 22. Use the running belt 25 and even move it on the ground to the trolley 30.36! Supporting model 32.38,
Tests are being conducted by running on rails 29.34.
すなわち、第８１は従来の方法の第１法を示すもので、
模型支持装置２０に模型２１を風洞１９内に支持し、地
面１１を模擬する地面板２２を使用して空気の流れ２４
を作って地面１１近くの航空機模型２１ （以下模型と
いう）に作用する空力特性を調べる。この方法では地面
板２２、模型２１はともに固定されているので実際の航
空機３９．（第１２．１３図参照）が地面１１近くを飛
行している状態と＠密には異なり試験の結果を悪化して
いる。風洞１９を使用するので、模型２１の大きさが大
きく制限され、この点からも試験の精度を悪化している
。That is, No. 81 shows the first method of the conventional method,
A model 21 is supported in a wind tunnel 19 by a model support device 20, and a ground plate 22 that simulates the ground 11 is used to control air flow 24.
to examine the aerodynamic characteristics acting on an aircraft model 21 (hereinafter referred to as the model) near the ground 11. In this method, the ground plate 22 and the model 21 are both fixed, so the actual aircraft 39. (See Figure 12.13) is different from the state in which the aircraft is flying close to the ground 11, which worsens the test results. Since the wind tunnel 19 is used, the size of the model 21 is greatly limited, which also deteriorates the accuracy of the test.
第９図は従来の方法の第２法を示すもので、模型支持袋
Ｗ２０にて模型２１を風洞１９内に支持し、地面を模擬
するランニングヘルド２５を使用して、空気の流れ２４
を作って、地面近くの模型２１に作用する空力特性を調
べる。この方法では、地面を模擬するランニングベルト
２５は動いているので実際の航空４ｉＳ！３９が地面近
くを飛行している状態に第１法よりもより近くなる。し
かし、ランニングヘルド２５の動かし方がむずかしく、
特に高速で一様に動かすことが困難となり、空気の流れ
２４が低速度に限定される。また、第１法と同様、風洞
１９を使用するので、模型２１の大きさが大きく制限さ
れ、この点から試験の精度を悪化している。FIG. 9 shows the second method of the conventional method, in which the model 21 is supported in the wind tunnel 19 with a model support bag W20, and the air flow 24 is
, and investigate the aerodynamic characteristics that act on the model 21 near the ground. In this method, the running belt 25 that simulates the ground is moving, so it looks like an actual aviation 4iS! 39 is flying closer to the ground than in the first method. However, it is difficult to move the Running Held 25.
It becomes difficult to move uniformly, especially at high speeds, and the air flow 24 is limited to low speeds. Further, as in the first method, since the wind tunnel 19 is used, the size of the model 21 is greatly limited, which deteriorates the accuracy of the test.
第１０図は従来の方法の第３法を示すもので屋外の地面
１１にレール２９を敷き、模型３２を模型支持装置３１
に支持して台車３０にとりつけ、台車３０を走行させて
移動方向３３に移動させる。FIG. 10 shows the third conventional method, in which a rail 29 is laid on the outdoor ground 11, and a model 32 is placed on a model support device 31.
It is supported on the carriage 30 and moved in the moving direction 33 by running the carriage 30.
第１，２法に比して模型３２は大きくでき、実際の航空
機３９が地面１１近くを飛行している状態をより厳密に
模擬することができる。使用する模型支持装置３１の長
さの状態でしか試験できないので、第１２図に示すよう
な航空機３９の降下の状態を調べるためには、多数回、
模型支持装置３１の長さを変えて試験をする必要がある
。またレール２９の存在が実際の飛行場の状態とは異な
り、模擬の厳密さを阻害している。Compared to the first and second methods, the model 32 can be made larger, and the state in which the actual aircraft 39 is flying close to the ground 11 can be simulated more closely. Since it is possible to test only the length of the model support device 31 used, in order to examine the descending state of the aircraft 39 as shown in FIG.
It is necessary to perform tests by changing the length of the model support device 31. Furthermore, the presence of the rail 29 differs from the actual airfield conditions and impedes the rigor of the simulation.
第１１図は従来の方法の第４法を示すもので、屋外の地
面１１の上にレール３４をレール支持装置３５にとりつ
け、模型３８を模型支持装置３７に支持して台車３６に
とりつけ台車３６を走行させて移動方向３３に移動させ
る。第１２法に比して模型３８は大きくでき、実際の航
空機３９が地面１１近くを飛行している状態をより厳密
に模擬することができる。使用する模型支持装置３７の
長さの状態でしか試験できないので、第１２図に示すよ
うな航空機３９の陳下の状態を調べるためには、多数回
、模型支持装置３７の長さを変えて試験をする必要があ
る。FIG. 11 shows a fourth conventional method, in which a rail 34 is attached to a rail support device 35 on the outdoor ground 11, a model 38 is supported by a model support device 37, and a model 38 is attached to a trolley 36. is run and moved in the moving direction 33. Compared to the twelfth method, the model 38 can be made larger, and the state in which the actual aircraft 39 is flying close to the ground 11 can be simulated more closely. Since the test can only be performed with the length of the model support device 37 used, in order to check the hanging state of the aircraft 39 as shown in FIG. 12, the length of the model support device 37 must be changed many times. I need to do a test.
第１３閲は、地面高さに対する地面による揚力増加を示
す線図、第１４図はマイクロバーストに遭遇した航空機
の経路を示す説明図であり、航空機３９が地面１１近く
を飛行すると、第１３図に示すように、地面に航空機３
９が近づ（はど地面による揚力４３が増加する。したが
って同様に航空機３９の安定性、操縦性、性能等に及ぼ
す影響が大きく、地面近くにおける航空機３９の空力特
性を厳密に把握する必要がある。Figure 13 is a diagram showing the increase in lift caused by the ground relative to the ground height, and Figure 14 is an explanatory diagram showing the path of the aircraft that encountered the microburst. Aircraft 3 on the ground as shown in
9 approaches (the lift force 43 due to the ground increases. Therefore, it similarly has a large effect on the stability, maneuverability, performance, etc. of the aircraft 39, and it is necessary to strictly understand the aerodynamic characteristics of the aircraft 39 near the ground. be.
第１４図に示すように、航空機３９が滑走路４７に着陸
しようとして、予定した経路４５で飛行している時に、
航空機３９がマイクロバースト４４に遭遇すると、第１
４図の破線に示すような経路４６を取り、滑走路４７の
手前に墜落するようなこともあり、マイクロバースト４
４は飛行安全上極めて重大な項目である。As shown in FIG. 14, when an aircraft 39 is flying on a scheduled route 45 to land on a runway 47,
When the aircraft 39 encounters the microburst 44, the first
Microburst 4 may take route 46 as shown in the broken line in Figure 4 and crash short of runway 47.
Item 4 is extremely important for flight safety.
以上の従来の方法では第１〜４法いずれにおいても、第
１４図に示すようなマイクロバースト４４の模擬は不可
能であった。In any of the above conventional methods, it is impossible to simulate the microburst 44 shown in FIG. 14 in any of the first to fourth methods.
本発明は、この様な事情に鑑みて提案されたもので、以
上のような問題点を解消させ、より厳密に実際の航空機
が地面近くを飛行することを模擬でき、マイクロバース
トの模擬が可能で、地面の高さの変化の模擬も可能で容
易にそれらを変更できる航空機試験風洞を提供すること
を目的とする。The present invention has been proposed in view of the above circumstances, and it solves the above-mentioned problems, makes it possible to more closely simulate an actual aircraft flying close to the ground, and makes it possible to simulate microbursts. The purpose of the present invention is to provide an aircraft test wind tunnel in which changes in ground height can be simulated and can be easily changed.
（課題を解決するための手段）
そのため、本発明は風洞の建屋上屋及び底面に航空機模
型を走行させるレール、建屋上部より建屋内に送風する
送風機 Ｈ水流膜、ヒンジによる一部を上下動できる模
擬地面を設け、航空機と地表との高度差による飛行への
影響、マイクロバーストの発生に対する試験、航空機の
降下角に関する試験等を臨場的に行う航空機試験風洞を
特徴とする。(Means for Solving the Problems) Therefore, the present invention provides a rail for running an aircraft model on the roof and bottom of a wind tunnel building, a blower for blowing air into the building from the top of the building, a water flow membrane, and a hinge that allows a portion to be moved up and down. It features an aircraft test wind tunnel with a simulated ground surface where tests can be conducted realistically, including tests on the influence of altitude differences between the aircraft and the ground on flight, tests on the occurrence of microbursts, and tests on the angle of descent of the aircraft.
Ｃ作用］
上述の構成により以上のような問題点を解消させ、より
厳密に実際の航空機が地面近くを飛行することを模擬で
き、マイクロバーストの模擬が可能で、地面の高さの変
化の模擬も可能で容易にそれらを変更できる航空ｉ試験
風洞を得ることかできる。C effect] The above-mentioned configuration solves the above problems, and can more accurately simulate an actual aircraft flying close to the ground, simulate microbursts, and simulate changes in ground height. It is also possible to obtain aeronautical I test wind tunnels that can easily modify them.
本発明を実施例について説明すると、第１図は、その第
１実施例を示す縦断面図、第２図は第１図の■−■断面
図、第３図は、第２実施例を示す縦断面図、第４図は第
３図のｒＶ−ＴＶ断面図、第５図、第６図はそれぞれ模
擬地面の上下移動、傾き変化の第１法、第２法ブロツク
線図、第７図は模擬マイクロバースト発生のブロック線
図である。To explain the present invention in terms of embodiments, FIG. 1 is a vertical sectional view showing the first embodiment, FIG. 2 is a sectional view taken along the line ■-■ in FIG. 4 is a cross-sectional view of the rV-TV in FIG. 3, FIGS. 5 and 6 are block diagrams of the first and second methods of vertical movement and inclination change of the simulated ground, respectively, and FIG. is a block diagram of simulated microburst generation.
第１実施例を第１〜２図を参照しつつ説明すると、建屋
ｌ内の上部にレール支持装置３を介して、レール２を設
ける。模型６は模型支持装置５を介して台車４にとりつ
けられ、台車４はレール２上を走行して移動方向７に移
動できる。The first embodiment will be described with reference to FIGS. 1 and 2. A rail 2 is provided at the upper part of a building 1 via a rail support device 3. The model 6 is attached to a truck 4 via a model support device 5, and the truck 4 can run on the rails 2 and move in a moving direction 7.
模擬地面８は、木材１合成樹脂、？ｊ！合材料等で製造
され、模擬地面支持変更装置１０の変更により、上下移
動１２が可能となる。また、模擬地面８にはヒンジ９が
設けられ、その１部はヒンジ９まわりに上下動でき、模
擬地面８の傾き変化１３が可能となり、これらにより、
実際の航空１１３９の地面１１からの高さの変化による
飛行の変化を試験することができ、同時に実際の航空機
３９が降下する降下角４１を変化することができる。Simulated ground 8 is wood 1 synthetic resin, ? j! It is manufactured from a composite material or the like, and by modifying the simulated ground support modification device 10, vertical movement 12 is possible. Further, the simulated ground 8 is provided with a hinge 9, a part of which can move up and down around the hinge 9, making it possible to change the inclination 13 of the simulated ground 8.
Changes in flight due to changes in the height of the real aircraft 1139 above the ground 11 can be tested, and at the same time the descent angle 41 at which the real aircraft 39 descends can be varied.
模擬地面８の上下移動１２．傾き変化１３はスイッチ操
作により、配線を通って電気信号が伝達され、油圧装置
又は電動モーターを作動させ、アクチュエーターを作動
させて模擬地面支持装置１０を作動させ、模擬地面８の
上下移動１２、傾き変化１３が可能となる。油圧装置を
使用する場合の作動ブロック図を第５図に、電動モータ
ーを使用する場合の作動ブロフク図を第６図にそれぞれ
示す。Vertical movement of the simulated ground 812. The inclination change 13 is performed by operating a switch, and an electric signal is transmitted through the wiring to operate a hydraulic device or an electric motor, actuating an actuator to operate the simulated ground support device 10, and change the vertical movement 12 of the simulated ground 8 and the inclination. Change 13 becomes possible. An operational block diagram when a hydraulic system is used is shown in FIG. 5, and an operational block diagram when an electric motor is used is shown in FIG. 6.
第２実施例を第３〜４図を参照しつつ説明すると、この
実施例は航空機事故の原因となるマイクロバースト４４
（第１４図参照）を模擬するもので第１〜２図との共
通部分は第１〜２図と同一であるのでその説明は省略す
る。The second embodiment will be explained with reference to FIGS. 3 and 4. This embodiment will be described with reference to FIGS.
(See FIG. 14), and the common parts with FIGS. 1 and 2 are the same as those in FIGS. 1 and 2, so the explanation thereof will be omitted.
建屋１の上部に電動モーター１５の動力により駆動され
る送風機１６を設け、これで空気流を作り、吹出口１７
より下方へ吹出すことにより、模擬マイクロバースト１
８をつくり出すことができる。模擬マイクロバースト１
８は次のよう番こしてつくり出される。スイッチ操作に
より配ＭＩ４を遣って電気信号が伝達され、電動モータ
ー１５が作動し、送風機１６が回転して空気流を作り、
模擬マイクロバースト１８がっくり出される。これらの
作動プロ、り図を第７図に示す。A blower 16 that is driven by the power of an electric motor 15 is provided at the top of the building 1 to create an air flow and blow the air into the air outlet 17.
Simulated micro burst 1 by blowing more downward.
You can create 8. Simulated microburst 1
8 is produced by straining as follows. When the switch is operated, an electric signal is transmitted through the distribution MI 4, the electric motor 15 is activated, the blower 16 is rotated, and an air flow is created.
A simulated microburst 18 is revealed. A diagram of these operations is shown in Figure 7.
吹出口１７の位置を変えること及び模擬地面の上下移動
１２．傾き変化１３等によりマイクロバースト４４の位
置を任意に変えることができる。これにより、レール２
の上を動く台車に模型支持装置５により垂設される模型
を走行させマイクロバーストに関する各種の試験を行う
ことができる。Changing the position of the air outlet 17 and moving the simulated ground up and down12. The position of the microburst 44 can be arbitrarily changed by changing the inclination 13 or the like. This allows rail 2
Various tests regarding microbursts can be performed by running a model suspended by a model support device 5 on a trolley that moves above it.
以上のように、本発明によれば、従来の技術の問題点を
解消して、従来の方法よりもより厳密に実際の航空機が
地面近くを飛行することを模擬でき、地面高さの変化も
容易にでき、マイクロバーストの模擬も可能となり、よ
り正確に、効率的に空力特性を調べることが可能な航空
機試験ができるようになる。As described above, according to the present invention, the problems of the conventional technology can be solved, and it is possible to more closely simulate the flight of an actual aircraft close to the ground than the conventional method, and it can also simulate changes in the ground height. It is easy to perform, it also makes it possible to simulate microbursts, and it becomes possible to conduct aircraft tests that allow for more accurate and efficient investigation of aerodynamic characteristics.
第１図は本発明の第１実施例を示す縦断面図、第２図は
第１図の■〜■断面図、第３図は第２実施例を示す縦断
面図、第４図は第３図の■−■断面図、第５図、第６図
はそれぞれ模擬地面の上下移動傾き変化の第１法、第２
法を示すフロック線図、第７図は模擬マイクロバースト
発止のブロック図である。
第８０．第９図はそれぞれ従来の第１法、第２法を示す
＠洞の縦断面図、第１０図、第１１図はそれぞれ従来法
の屋外試験を示す側面図、第１２図は航空機の降下を示
す側面図、第１３図は地面高さに対する地面による揚力
増加を示す線図、第１４図はマイクロバーストに遭遇し
た航空機の経路を示す説明図である。
１・・・建屋、２・・・レール、３・・・レール支持装
置、４・・・台車、５・・・模型支持装置、６・・・模
型、７・・・移動、８・・・模擬地面、９・・ヒンジ、
１０・・・模擬地面支持装置、１１・・・地面、１２・
・・上下移動、１３・・・傾き変化、１４・・・配線（
１５・・・電動モーター １６・・・送風機、１７・・
・吹出口、１日・・・模擬マイクロバースト、１９・・
・風洞、２０・・・模型支持装置、２１・・・模型、２
２・・・地面板、２３・・・地面板支持装置、２４・・
・空気の流れ、２５・・・ランニングヘルド、２６・・
・整形部、２７・・・回転装置、２８・・・ランニング
ヘルド装置支持装置、２９・・・レール、３０・・・台
車、３１・・・模型支持装置、３２・・・模型、３３・
・・移動、３４・・・レール、３５・・・レール支持装
置、３６・・・台車、３７・・・模型支持装置、３８・
・・模型、３９・・・航空機、４０・・・地面高さ、４
１・・・降下角、４２・・・揚力、４３・・・地面によ
る揚力増加、４４・・・マイクロバースト、４５・・・
予定した経路、４６・・・マイクロバーストに遭遇した
経路、４７・・・滑走路、代理人 弁理士 塚 本 正
文
第
図
Ｉ
ｔ６Ｌ凰４
（ｔｒ＠ｖｔ−一９−
ゝ ″ ｔ４に？４
！
一〇
第４
図
、−ｆｆ
２Ｌ−ル４降＃！
／ １７％
第
す
図
ｔＱＩＬ肩
第
図
゛ｚＢラン二ングヘルｌ−ψｌｆ手計１ｔｔｔ第
図
第
図
第
図
」９駁７橿
〔〕ダ
第 グミゴ
図
４で耐扁づ
第１４図
４４フイクロバースト
Ｉｌ遇＋ｒ；８１舎FIG. 1 is a longitudinal cross-sectional view showing the first embodiment of the present invention, FIG. 2 is a cross-sectional view from ■ to ■ of FIG. 1, FIG. 3 is a longitudinal cross-sectional view showing the second embodiment, and FIG. The ■-■ cross-sectional view in Figure 3, Figures 5 and 6 are the first and second methods of vertical movement and slope changes of the simulated ground, respectively.
FIG. 7 is a block diagram of simulated microburst initiation. No. 80. Figure 9 is a vertical cross-sectional view of the tunnel showing the conventional method 1 and 2, respectively. Figures 10 and 11 are side views showing the outdoor test of the conventional method, and Figure 12 shows the descent of the aircraft. 13 is a diagram showing the increase in lift due to the ground relative to the ground height, and FIG. 14 is an explanatory diagram showing the path of the aircraft that encountered the microburst. DESCRIPTION OF SYMBOLS 1... Building, 2... Rail, 3... Rail support device, 4... Dolly, 5... Model support device, 6... Model, 7... Movement, 8... Simulated ground, 9...hinge,
10... Simulated ground support device, 11... Ground, 12.
・・Vertical movement, 13 ・Tilt change, 14 ・Wiring (
15...Electric motor 16...Blower, 17...
・Air outlet, 1 day...Simulated microburst, 19...
・Wind tunnel, 20... Model support device, 21... Model, 2
2... Ground plate, 23... Ground plate support device, 24...
・Air flow, 25...Running helmet, 26...
- Shaping section, 27... Rotating device, 28... Running heald device support device, 29... Rail, 30... Dolly, 31... Model supporting device, 32... Model, 33.
...Movement, 34...Rail, 35...Rail support device, 36...Dolly, 37...Model support device, 38.
...Model, 39...Aircraft, 40...Ground height, 4
1... Descent angle, 42... Lifting force, 43... Lifting force increase due to the ground, 44... Microburst, 45...
Planned route, 46...Route where the microburst was encountered, 47...Runway, Agent Patent Attorney Masaru Tsukamoto Figure I t6L凰4 (tr@vt-19- ゝ '' To t4?4 ! 10th figure, -ff 2L-le 4 descend #! / 17% 81 buildings
Claims (1)
ール、建屋上部より建屋内に送風する送風機、降水施設
、ヒンジによる一部を上下動できる模擬地面を設け、航
空機と地表との高度差による飛行への影響、マイクロバ
ーストの発生に対する試験、航空機の降下角に関する試
験等を臨場的に行う航空機試験風洞。A rail on which the aircraft model runs on the roof and bottom of the wind tunnel building, a blower that blows air into the building from the top of the building, a precipitation facility, and a simulated ground surface that can be partially moved up and down using hinges are installed to allow flight due to the difference in altitude between the aircraft and the ground. This is an aircraft test wind tunnel where tests are conducted on-site, such as tests on the impact on aircraft, the occurrence of microbursts, and tests on the angle of descent of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP18448990A JPH0470534A (en) | 1990-07-12 | 1990-07-12 | Aircraft-testing wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP18448990A JPH0470534A (en) | 1990-07-12 | 1990-07-12 | Aircraft-testing wind tunnel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0470534A true JPH0470534A (en) | 1992-03-05 |
Family
ID=16154072
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP18448990A Pending JPH0470534A (en) | 1990-07-12 | 1990-07-12 | Aircraft-testing wind tunnel |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0470534A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7131319B2 (en) | 2004-09-10 | 2006-11-07 | Chip Ganassi Racing Teams, Inc. | Method and apparatus for testing a moving vehicle |
| US8453964B2 (en) | 2009-10-29 | 2013-06-04 | Airbus Operations S.L. | Wind tunnel aircraft model with truncated wing |
| CN106813893A (en) * | 2017-03-14 | 2017-06-09 | 百安力钢结构应用科技有限公司 | Short-period high-voltage fluctuation test system for metal roof |
| CN109141803A (en) * | 2018-08-29 | 2019-01-04 | 杨雪锋 | A kind of transfer flight simulation wind-tunnel |
| CN106525375B (en) * | 2016-10-21 | 2020-05-12 | 国网山东省电力公司电力科学研究院 | An Adaptive System for Detection of UAV's Wind Resistance |
| CN112414667A (en) * | 2020-10-30 | 2021-02-26 | 中国航空工业集团公司西安飞机设计研究所 | Wind tunnel test method for aerodynamic noise of turboprop aircraft |
-
1990
- 1990-07-12 JP JP18448990A patent/JPH0470534A/en active Pending
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7131319B2 (en) | 2004-09-10 | 2006-11-07 | Chip Ganassi Racing Teams, Inc. | Method and apparatus for testing a moving vehicle |
| US7305870B2 (en) | 2004-09-10 | 2007-12-11 | Chip Ganassi Racing Teams, Inc. | Apparatus for testing a moving vehicle |
| US8453964B2 (en) | 2009-10-29 | 2013-06-04 | Airbus Operations S.L. | Wind tunnel aircraft model with truncated wing |
| CN106525375B (en) * | 2016-10-21 | 2020-05-12 | 国网山东省电力公司电力科学研究院 | An Adaptive System for Detection of UAV's Wind Resistance |
| CN106813893A (en) * | 2017-03-14 | 2017-06-09 | 百安力钢结构应用科技有限公司 | Short-period high-voltage fluctuation test system for metal roof |
| CN106813893B (en) * | 2017-03-14 | 2018-12-28 | 百安力钢结构应用科技有限公司 | Short-period high-voltage fluctuation test system for metal roof |
| CN109141803A (en) * | 2018-08-29 | 2019-01-04 | 杨雪锋 | A kind of transfer flight simulation wind-tunnel |
| CN109141803B (en) * | 2018-08-29 | 2020-07-31 | 江苏普旭软件信息技术有限公司 | Move and carry flight simulation wind-tunnel |
| CN112414667A (en) * | 2020-10-30 | 2021-02-26 | 中国航空工业集团公司西安飞机设计研究所 | Wind tunnel test method for aerodynamic noise of turboprop aircraft |
| CN112414667B (en) * | 2020-10-30 | 2023-03-14 | 中国航空工业集团公司西安飞机设计研究所 | Wind tunnel test method for aerodynamic noise of turboprop aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP2694263B2 (en) | Three-dimensional airflow generator, flight control system verification method for aircraft using the device, and flight motion simulator | |
| US8899986B2 (en) | Air rescue simulator | |
| JPH0470535A (en) | Aircraft-testing wind tunnel | |
| US20200249702A1 (en) | System and method for wind tunnel testing a uas in a fully autonomous operating mode | |
| CN104386250A (en) | Multi-rotor-wing patrolling aircraft and power transmission line patrolling system | |
| Luckner et al. | Hazard criteria for wake vortex encounters during approach | |
| JPH0470534A (en) | Aircraft-testing wind tunnel | |
| CN109506677A (en) | High precision measurement based on small rail car verifies system and method | |
| Cunningham et al. | Practical application of a subscale transport aircraft for flight research in control upset and failure conditions | |
| CN118882996B (en) | A device for testing airfoil jet lift enhancement based on real wind and wave environment | |
| JPH0439556Y2 (en) | ||
| CN114705390B (en) | Test device for simulating low-altitude wind shear in airplane lifting process | |
| CN220243547U (en) | Flight control testing arrangement | |
| Rowe et al. | A turbulence criterion for safe helicopter operations to offshore installations | |
| CN117566123A (en) | Ground virtual flight test device for fixed-wing UAV | |
| CN119803949B (en) | System and method for monitoring environmental health index in cabin of aerocar | |
| Chambers | Use of Dynamically Scaled Models for Studies of the High-Angle-of-Attack Behavior of Airplanes | |
| JP3678103B2 (en) | Control simulation apparatus and control simulation method | |
| CN121980743A (en) | Helicopter floating system air opening safety analysis and verification method | |
| CN119637107A (en) | An eVTOL aircraft take-off and landing performance test system | |
| Kuhn | Factors Influencing the Choice of Facilities and Techniques for Aeronautical Development | |
| Smith | All weather operations—present achievements | |
| Golovnev et al. | Technology for aerodynamic wake characteristics measurement behind an aircraft on a rail-guided track | |
| Command | Vertical wind tunnel | |
| Samaka | Design of a microprocessor-controlled shear warning device for general aviation aircraft |