JPS62139799A - Thunderbolt test apparatus for missile - Google Patents
Thunderbolt test apparatus for missileInfo
- Publication number
- JPS62139799A JPS62139799A JP60278884A JP27888485A JPS62139799A JP S62139799 A JPS62139799 A JP S62139799A JP 60278884 A JP60278884 A JP 60278884A JP 27888485 A JP27888485 A JP 27888485A JP S62139799 A JPS62139799 A JP S62139799A
- Authority
- JP
- Japan
- Prior art keywords
- test
- lightning current
- flying object
- magnetic field
- lightning
- 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.)
- Granted
Links
- 238000012360 testing method Methods 0.000 title claims description 44
- APTZNLHMIGJTEW-UHFFFAOYSA-N pyraflufen-ethyl Chemical compound C1=C(Cl)C(OCC(=O)OCC)=CC(C=2C(=C(OC(F)F)N(C)N=2)Cl)=C1F APTZNLHMIGJTEW-UHFFFAOYSA-N 0.000 title 1
- 230000000694 effects Effects 0.000 description 4
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 239000012212 insulator Substances 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000003416 augmentation Effects 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 230000001939 inductive effect Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 239000000696 magnetic material Substances 0.000 description 1
Landscapes
- Testing Electric Properties And Detecting Electric Faults (AREA)
Abstract
(57)【要約】本公報は電子出願前の出願データであるた
め要約のデータは記録されません。(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は電気式操縦方式（ＦＢＷ＞を採用しＩ；航空機
、操縦性増大装置（ＣＡＳ）を採用した航空機を初めと
する各団航空機、ロケット、ミサイル等の飛翔体の雷試
験装置に係り、特に、地上試験であ、てら飛行時と同等
の状態で被電を模擬できるようにした飛翔体の雷試験賃
函に関する。[Detailed Description of the Invention] [Field of Industrial Application] The present invention is applicable to aircrafts employing an electric flight control system (FBW), aircrafts of various fleets including aircrafts employing a maneuverability augmentation system (CAS), This invention relates to a lightning testing device for flying objects such as rockets and missiles, and in particular to a lightning testing box for flying objects that can simulate electrification during ground testing in conditions equivalent to those during flight.
飛翔体が被電した場合の影響としては、搭載電気１器へ
の影響１機器損傷等があり、特に、飛行中に被電した場
合にあっては正常飛行が著しく阻害される恐れがある。When a flying object is electrified, the effects include damage to onboard electrical equipment, etc. In particular, when electrification occurs during flight, normal flight may be significantly impaired.
そこで、予め地上にて模擬的に被電状態を飛翔体に生じ
させて、被電に伴う不具合対策を採る手立てがなされて
いる。Therefore, measures have been taken to prevent problems caused by energization by causing the flying object to be energized in a simulated manner on the ground in advance.
従来、この種飛翔体の雷試験装置は第４図の如く構成さ
れていた。すなわち、供試飛翔体ＴＰは地上に設置され
ており、雷電流発生装置１により発生させたＮ擬雷電流
を給電＄１２により地上（大地）に設置された状態の供
試飛翔体ＴＰの機首に導き、供試飛翔体ＴＰを通過した
模擬雷電流を、リターンラインとして１本のケーブル３
により機体後部から雷電流発生装置１に導くようにして
いた。Conventionally, a lightning testing device for this type of flying object has been constructed as shown in FIG. That is, the test projectile TP is installed on the ground, and the N simulated lightning current generated by the lightning current generator 1 is applied to the aircraft of the test projectile TP installed on the ground (earth) by the power supply $12. A single cable 3 is used as a return line to conduct the simulated lightning current that has passed through the test flying object TP.
The lightning current was led to the lightning current generator 1 from the rear of the fuselage.
上記従来の構成では、供試飛翔体ＴＰを通過した模擬雷
電流のリターンラインとして・１本のケーブル３だけで
あるので、機体囲りの磁界分布は第３図（ｂ）に示すよ
うに大地の影響により不均一になり、飛１１中での磁界
分布と等価にならないものであり、従って、飛゛行中で
の正確な被電状態を模擬しているものではなく、飛１１
中の雷電流による誘導障害等の正確な評価がなされなか
った。In the above conventional configuration, there is only one cable 3 as a return line for the simulated lightning current passing through the test flying object TP, so the magnetic field distribution around the aircraft is as shown in Figure 3(b). It is not equivalent to the magnetic field distribution in flight 11 due to the influence of
An accurate assessment of inductive disturbances caused by lightning current inside the building was not made.
そこで、本発明は、機体間りの磁界分布を均一に出来、
飛行中での正確な被占状態を模擬することが可能な飛翔
体の雷試験装置を提供することにある。Therefore, the present invention can make the magnetic field distribution between the bodies uniform,
An object of the present invention is to provide a lightning test device for a flying object capable of simulating an accurate occupied state in flight.
本発明は上記問題点を解決し、目的を達成するために、
次ぎのような手段を講じたことを特徴としている。すな
わち、雷電流発生装置により発生させた模擬雷電流を給
電線により地上（大地）に設置された状態の供試飛翔体
に導き、供試飛翔体を通過した模擬雷電流を雷電流発生
装置に導くリターンラインを、上記供試Ｒ翔体に対して
同心円状に配置したことを特徴とするものである。The present invention solves the above problems and achieves the objectives by:
It is characterized by the following measures: That is, a simulated lightning current generated by a lightning current generator is guided to a test flying object installed on the ground (earth) through a power supply line, and the simulated lightning current that has passed through the test flying object is transferred to the lightning current generator. It is characterized in that the guiding return line is arranged concentrically with respect to the test R flying body.
このような手段を講じたことにより、供試飛翔体を同心
円状に囲むリター ンライン上を１ａ凝雷電流が流れ、
これにより践体四りの磁界分布は大地により影ｐを受け
ず、飛行中での磁界分布と等価な均一磁界が１ηられる
。By taking such measures, a 1a condensing current flows on the return line concentrically surrounding the test projectile,
As a result, the magnetic field distribution around the body is not affected by the earth, and a uniform magnetic field equivalent to the magnetic field distribution during flight is reduced by 1η.
第１図（ａ）は本発明の一実施例の外観構成を示す斜視
図、第１図（ｂ）は第１図（ａ ）−−ｆｆけるＡ−Ａ
方向に見た断面図である。第１図（ａ）（ｂ）において
供試飛翔体ＴＰは地上に設置されており、雷Ｎ流発生装
置１により発生させた模擬雷電流を給電！！！２により
地上（大地）に設置された状態の供試飛翔体ＴＰの機首
に導き、供試飛翔体ＴＰを通過した模擬雷電流を、供試
飛翔体ＴＰに対して同心円状に配置したリターンライン
４に導き、この通過模ｗ１雷電流をリタンーンライン４
及びケーブル５を介して雷電流発生装置１に導くように
構成している。ここで、リターンライン４と供試飛翔体
ＴＰの機体後部とは図示しないケーブルで電気的に接続
されている。FIG. 1(a) is a perspective view showing the external configuration of an embodiment of the present invention, and FIG. 1(b) is a perspective view showing the external configuration of an embodiment of the present invention.
FIG. In Figures 1(a) and 1(b), the test flying object TP is installed on the ground, and is fed with a simulated lightning current generated by the lightning N current generator 1! ! ! 2, the simulated lightning current that was guided to the nose of the test projectile TP installed on the ground (earth) and passed through the test projectile TP was placed concentrically with respect to the test projectile TP. This passing wave w1 lightning current is returned to line 4.
and a cable 5 to lead to the lightning current generator 1. Here, the return line 4 and the rear part of the test flying object TP are electrically connected by a cable (not shown).
リターンライン４は、鉄等の磁性体を除く幅広の？Ｉａ
（図示では機体上下左右対称に２本）の導電体よりなり
、これら導電体を順次接続し且つ適宜の位置に配ｒａさ
れた絶縁体よりなるテストスタンド６により支持されて
供試飛翔体ＴＰを同心円状に包囲するように構成されて
いる。尚、供試飛翔体ＴＰは接地ｉＩ９により大地に接
地されている。Is the return line 4 wide, excluding magnetic materials such as iron? Ia
The test aircraft TP is supported by a test stand 6 made of insulators connected in sequence and arranged at appropriate positions. It is configured to surround concentrically. Incidentally, the test flying object TP is grounded to the earth by a ground iI9.
次Δ゛に上記の姐く構成された本実施例の作用について
説明する。すなわち、雷電流発生装置１により発生させ
た模擬雷電流は、給電線２により供試飛翔体ＴＰの１首
に導きかれ、供試飛翔体ＴＰを通過した模擬雷電流は、
リタ −ンライン４及びケーブル５を介して雷電流発生
装置１に導かれる。ここで、リター ンライン４は供試
飛翔体ＴＰに対して同心円状に配置し且つ態体上下左右
対称に２本の導電体よりなるので、リタンーンライン４
に流入した模擬雷電流は供試飛翔体ＴＰに対して同心円
状に流れることになり、大地による影響を受けないで供
試Ｒ用体ＴＰに対して均一な磁界分布を示すことになる
。Next, the operation of this embodiment having the second structure described above will be explained. That is, the simulated lightning current generated by the lightning current generator 1 is guided to one neck of the test projectile TP by the power supply line 2, and the simulated lightning current that has passed through the test projectile TP is
It is guided to the lightning current generator 1 via a return line 4 and a cable 5. Here, since the return line 4 is arranged concentrically with respect to the test flying object TP and is made of two conductors symmetrically above and below the object, the return line 4
The simulated lightning current flowing into the test object TP flows concentrically with respect to the test object TP, and exhibits a uniform magnetic field distribution with respect to the test object TP without being affected by the ground.
第２図は、第１図においてリタ −ンライン４の包囲内
に磁界センサ７を設け、磁界分布をストレージオシロス
コープ８．で観察した時の特性図であり、機首の電子機
器室の外周部における特性を示している。第２図及び第
３図（ａ）より明らかなように、大地の影響が無視でき
る程に、供試飛翔体ＴＰを中心に均一な磁界分布がなさ
れている。In FIG. 2, a magnetic field sensor 7 is provided within the envelope of the return line 4 in FIG. 1, and the magnetic field distribution is measured by a storage oscilloscope 8. This is a characteristic diagram when observed at , and shows the characteristics at the outer periphery of the electronic equipment room in the nose. As is clear from FIGS. 2 and 3(a), the magnetic field is uniformly distributed around the test flying object TP to the extent that the influence of the ground can be ignored.
以上の如くの本実施例によれば以下列挙する作用効果を
奉する。According to this embodiment as described above, the following effects are provided.
■ 機体間りの磁界分布は大地の影響を受けないで均一
になり、飛行中での磁界分布と等価となり、従って、飛
行中での正確な被電状態を模擬でき、飛行中の雷電流に
よる誘Ｓ障害等の正確な評価がなされる。■ The magnetic field distribution between the aircraft bodies is uniform without being affected by the ground, and is equivalent to the magnetic field distribution during flight. Therefore, it is possible to accurately simulate the energized state during flight, and it is possible to simulate lightning current during flight. Accurate evaluation of S-induced disorders, etc. will be made.
■ 機体間りの磁界分布は均一であることから、供試飛
翔体ＴＰを含めたインピーダンスが小さく（特にインダ
クタンス成分）でき、よって雷電流 ・発生装置１の能
力の増大化が図られる。- Since the magnetic field distribution between the aircraft bodies is uniform, the impedance including the test flying object TP can be reduced (particularly the inductance component), thereby increasing the capability of the lightning current generator 1.
■ リターンライン４は、適宜の位置に配置された絶縁
体よりなるテストスタンド６により支持されるものであ
るので、このテストスタンド６の配冒位での変更により
各種形状の異なる供試飛翔体工Ｐに適用が可能であり、
試験効率の上で有利となる。■ Since the return line 4 is supported by a test stand 6 made of an insulator placed at an appropriate position, by changing the deployment position of this test stand 6, various shapes of test flying objects can be produced. It is applicable to P,
This is advantageous in terms of test efficiency.
以上詳述したように本発明は、雷電流発生装置により発
生させた模擬雷電流を給電線により地上（大地）に股謬
された状態の供試飛翔体に導ぎ１供試飛翔体を通過した
模擬雷電流を雷電流発生装置に導くリター ンラインを
、上記供試飛翔体に対して同心円状に配置したものであ
る。As described in detail above, the present invention is capable of guiding a simulated lightning current generated by a lightning current generator to a test flying object that is suspended on the ground (earth) through a power supply line, and passing through one test flying object. A return line that guides the simulated lightning current to the lightning current generator is arranged concentrically with the test projectile.
したがって本発明によれば、供試飛翔体を同心円状に囲
むリター シライン上を模ｒＫ！雷電流が流れ、これに
より機体間りの磁界分布は大地により影旨を受けず、飛
行中での磁界分布と等価名均−Ｕ４ｉ界が得られるので
、飛行中での正確な？Ｉ！雷状前状態擬ことを可能とし
た飛翔体の宙試験装置が提供できるものである。Therefore, according to the present invention, the rK! A lightning current flows, and as a result, the magnetic field distribution between the aircraft bodies is not affected by the earth, and the equivalent mean -U4i field is obtained as the magnetic field distribution during flight, so it is possible to obtain accurate magnetic field distribution during flight. I! It is possible to provide an in-air test device for a flying object that can simulate a pre-lightning state.
第１図（ａ）は本発明の一実施例の外観構成を示す斜視
図、第１図（ｂ）は第１図（ａ）おけるＡ−Ａ方向に児
た断面図、第２図はリターンラインの包囲内の［ｎ界分
布特性図、第３図＜ ａ ）は同実施例による磁界分布
特性を示す図、第３図（ｂ）は従来例による磁界分布特
性を示す図、第４図は従来例を示す斜視図である。
１・・・雷電流発生装置、２・・・給電線、４・・・リ
ターンライン、５・・・ケーブル、６・・・テストスタ
ンド、７・・・磁界センサ、８・・・ストレージオシロ
スコープ、９・・・接地線。
１＋ｆ憎−出１５１１人 ｌ’、ｒｊ ｔ・’ｈ庁
１°′／術研′元（へｌ：ｊ： ｉ’：（１［ド
徹FIG. 1(a) is a perspective view showing the external configuration of an embodiment of the present invention, FIG. 1(b) is a sectional view taken along the A-A direction in FIG. 1(a), and FIG. 2 is a return view. Figure 3 (a) shows the magnetic field distribution characteristic of the same embodiment, Figure 3 (b) shows the magnetic field distribution characteristic of the conventional example, and Figure 4. FIG. 2 is a perspective view showing a conventional example. DESCRIPTION OF SYMBOLS 1... Lightning current generator, 2... Power supply line, 4... Return line, 5... Cable, 6... Test stand, 7... Magnetic field sensor, 8... Storage oscilloscope, 9...Grounding wire. 1+f hate-out 1511 people l', rj t・'h office 1°'/Jutsuken'moto (he l:j: i':(1[do
Tooru
Claims (1)
生装置により発生させた模擬雷電流を地上に設置された
状態の供試飛翔体に導く給電線と、該供試飛翔体を通過
した模擬雷電流を雷電流発生装置に導くリターンライン
とを具備してなる飛翔体の雷試験装置において、上記リ
ターンラインを、上記供試飛翔体に対して同心円状に配
置したことを特徴とする飛翔体の雷試験装置。A lightning current generator that generates a simulated lightning current, a power supply line that leads the simulated lightning current generated by the lightning current generator to a test flying object installed on the ground, and a power line that passes through the test flying object. A lightning testing device for a flying object, comprising a return line that guides a simulated lightning current to a lightning current generator, characterized in that the return line is arranged concentrically with respect to the test flying object. Body lightning test equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60278884A JPS62139799A (en) | 1985-12-13 | 1985-12-13 | Thunderbolt test apparatus for missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP60278884A JPS62139799A (en) | 1985-12-13 | 1985-12-13 | Thunderbolt test apparatus for missile |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS62139799A true JPS62139799A (en) | 1987-06-23 |
| JPH0331640B2 JPH0331640B2 (en) | 1991-05-07 |
Family
ID=17603444
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP60278884A Granted JPS62139799A (en) | 1985-12-13 | 1985-12-13 | Thunderbolt test apparatus for missile |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS62139799A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011145675A1 (en) * | 2010-05-20 | 2011-11-24 | 三菱重工業株式会社 | Current generation device |
| JP2012122839A (en) * | 2010-12-08 | 2012-06-28 | Mitsubishi Heavy Ind Ltd | Parameter selection device, lightning simulation system, parameter selection method, and lightning simulation method |
| JP2012242307A (en) * | 2011-05-23 | 2012-12-10 | Mitsubishi Aircraft Corp | Thunder stroke test device, thunder stroke test system, and thunder stroke test method |
-
1985
- 1985-12-13 JP JP60278884A patent/JPS62139799A/en active Granted
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011145675A1 (en) * | 2010-05-20 | 2011-11-24 | 三菱重工業株式会社 | Current generation device |
| JP2011244639A (en) * | 2010-05-20 | 2011-12-01 | Mitsubishi Heavy Ind Ltd | Current generator |
| US9071050B2 (en) | 2010-05-20 | 2015-06-30 | Mitsubishi Heavy Industries, Ltd. | Current generating device |
| JP2012122839A (en) * | 2010-12-08 | 2012-06-28 | Mitsubishi Heavy Ind Ltd | Parameter selection device, lightning simulation system, parameter selection method, and lightning simulation method |
| JP2012242307A (en) * | 2011-05-23 | 2012-12-10 | Mitsubishi Aircraft Corp | Thunder stroke test device, thunder stroke test system, and thunder stroke test method |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0331640B2 (en) | 1991-05-07 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EXPY | Cancellation because of completion of term |