CN105651123B - 一种可旋转电磁轨道炮炮弹 - Google Patents

一种可旋转电磁轨道炮炮弹 Download PDF

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CN105651123B
CN105651123B CN201610055049.6A CN201610055049A CN105651123B CN 105651123 B CN105651123 B CN 105651123B CN 201610055049 A CN201610055049 A CN 201610055049A CN 105651123 B CN105651123 B CN 105651123B
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shell
screw
rotary power
hole
shell body
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CN105651123A (zh
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袁晓明
陈晓阳
关继红
张立杰
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Yanshan University
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B6/00—Projectiles or missiles specially adapted for projection without use of explosive or combustible propellant charge, e.g. for blow guns, bows or crossbows, hand-held spring or air guns
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
    • F42B10/02—Stabilising arrangements
    • F42B10/26—Stabilising arrangements using spin
    • F42B10/28—Stabilising arrangements using spin induced by gas action

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

一种可旋转电磁轨道炮炮弹，引信后部外表面设螺纹，弹体前端设凹槽，凹槽内设内螺纹，引信和弹体通过螺纹相连，弹体外壁上设T型槽，弹体外壁T型槽内插接T型板，T型板固定在旋转动力壳的内板内壁上，旋转动力壳套接在弹体的外部，旋转动力壳内板和外板为两端开口的圆柱形壳体，内板置于外板的内部，内板和外板之间设叶片，弹体后端设螺纹孔，弹体后端与绝缘层一侧相邻，绝缘层中部设通孔，绝缘层另一侧与电枢一端相邻，螺钉从右依次穿过电枢中部的通孔和绝缘层中部的通孔，螺钉的一端设螺纹，螺钉一端插接在弹体后端的螺纹孔内，螺钉与弹体螺纹连接。本发明炮弹运动方向稳定，射击准确率高，射程较远，适用于电磁轨道炮的远距离和精确作战。

Description

一种可旋转电磁轨道炮炮弹
技术领域
本发明涉及电磁发射领域。
背景技术
电磁轨道炮是一种利用电磁发射技术将电磁能转化为炮弹动能的杀伤性武器。与传统火炮相比，电磁力比火药燃气压力作用力更大，作用时间更长，大大提高了炮弹的出口动能和射程。若电磁轨道炮炮弹出膛后处于平行飞行状态，在空气阻力和自身重力的作用下产生较大的转矩，从而极易改变炮弹的飞行状态，使其出现摇摆或翻转等问题，降低了炮弹的飞行稳定性和射击准确性。此外，由于空气阻力的大小一般与速度的平方成正比，在较高的出膛速度条件下，电磁炮炮弹受到的空气阻力较大，严重影响其射程。若采取措施使炮弹高速自转，则炮弹在重力和空气阻力的作用下不容易改变其运行轨迹，并且在一定程度上抑制空气阻力的影响，能够有效地提高炮弹的飞行稳定性、射程和发射精度。
发明内容
本发明的目的是提供一种飞行稳定、射击准确率高、射程较远的可旋转电磁轨道炮炮弹。
本发明主要包括有引信、弹体、T型槽、T型板、旋转动力壳、内板、外板、叶片、绝缘层、电枢和螺钉。
其中，引信后部的外表面设有螺纹，弹体前端设有凹槽，在凹槽内设有内螺纹，引信和弹体通过螺纹相连。为了有效减少空气阻力，最好引信和弹体的外部均为流线型。在弹体的外壁上设有T型槽，在弹体外壁的T型槽内插接T型板。T型板固定在旋转动力壳的内板内壁上。旋转动力壳套接在弹体的外部，旋转动力壳包括内板、外板和叶片，旋转动力壳的内板和外板均为两端开口的圆柱形壳体，内板置于外板的内部，内板和外板之间设有叶片，叶片呈螺旋状。弹体后端设有螺纹孔，弹体后端与绝缘层一侧相邻，绝缘层中部设有通孔，绝缘层的另一侧与电枢的一端相邻，螺钉从右依次穿过电枢中部的通孔和绝缘层中部的通孔，螺钉的一端设有螺纹，螺钉的一端插接在弹体后端的螺纹孔内，螺钉与弹体螺纹连接。
本发明在使用时，电磁轨道炮炮弹在炮膛内加速过程中处于真空环境，在电磁推进力的作用下，炮弹做加速运动并得到较高的出口速度，在炮膛内加速过程中炮弹不旋转；炮弹出膛后，在叶片所受空气阻力的作用下产生切向加速度，使炮弹转速不断增加，当其转速达到某一临界值时，离心力使旋转动力壳上的T型板逐渐脱离弹体上的T型槽，直至旋转动力壳与弹体完全脱离，炮弹以一定的前进速度和自转速度击中指定目标。
本发明与现有技术相比具有如下优点：炮弹运动方向稳定，射击准确率高，射程较远，适用于电磁轨道炮的远距离和精确作战。
附图说明
图1为旋转电磁轨道炮炮弹的整体示意图；
图2为旋转电磁轨道炮炮弹旋转动力壳脱离后的示意图；
图3为图1中间截面A-A的剖面示意图；
图4、图5为旋转电磁轨道炮炮弹的旋转动力壳的示意图；
图6为旋转电磁轨道炮炮弹弹体与旋转动力壳的连接示意图；
具体实施方式
在图1、图2、图3、图4、图5和图6所示的本发明的示意简图中，引信1后部的外表面设有螺纹，弹体2前端设有凹槽，在凹槽内设有内螺纹，引信和弹体通过螺纹相连。引信和弹体的外部均为流线型。在弹体的外壁上设有T型槽3，在弹体外壁的T型槽内插接T型板4。T型板固定在旋转动力壳5的内板6内壁上。旋转动力壳套接在弹体的外部，旋转动力壳包括内板6、外板7和叶片8，旋转动力壳的内板和外板均为两端开口的圆柱形壳体，内板置于外板的内部，内板和外板之间设有叶片，叶片呈螺旋状。弹体后端设有螺纹孔，弹体后端与绝缘层9一侧相邻，绝缘层中部设有通孔，绝缘层的另一侧与电枢10的一端相邻，螺钉11从右依次穿过电枢中部的通孔和绝缘层中部的通孔，螺钉的一端设有螺纹，螺钉的一端插接在弹体后端的螺纹孔内，螺钉与弹体螺纹连接。

Claims (2)

1.一种可旋转电磁轨道炮炮弹，主要包括引信、弹体、T型槽、T型板、旋转动力壳、绝缘层、电枢和螺钉，其特征在于：引信后部的外表面设有螺纹，弹体前端设有凹槽，在凹槽内设有内螺纹，引信和弹体通过螺纹相连，在弹体的外壁上设有T型槽，在弹体外壁的T型槽内插接T型板，T型板固定在旋转动力壳的内板内壁上，旋转动力壳套接在弹体的外部，旋转动力壳包括内板、外板和叶片，旋转动力壳的内板和外板均为两端开口的圆柱形壳体，内板置于外板的内部，内板和外板之间设有叶片，叶片呈螺旋状，弹体后端设有螺纹孔，弹体后端与绝缘层一侧相邻，绝缘层中部设有通孔，绝缘层的另一侧与电枢的一端相邻，螺钉从右依次穿过电枢中部的通孔和绝缘层中部的通孔，螺钉的一端设有螺纹，螺钉的一端插接在弹体后端的螺纹孔内，螺钉与弹体螺纹连接。
2.根据权利要求1所述的一种可旋转电磁轨道炮炮弹，其特征在于：引信和弹体的外部均为流线型。
CN201610055049.6A 2016-01-27 2016-01-27 一种可旋转电磁轨道炮炮弹 Expired - Fee Related CN105651123B (zh)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11867487B1 (en) 2021-03-03 2024-01-09 Wach Llc System and method for aeronautical stabilization

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1037744A (en) * 1962-06-28 1966-08-03 Tampella Oy Ab Method and means for stabilizing the trajectory of projectiles
US4796534A (en) * 1988-01-22 1989-01-10 The United States Of America As Represented By The Secretary Of The Army Spinning ramjet vehicle with a non-spinning combustor
GB2244687B (en) * 1990-06-06 1993-10-27 British Aerospace Stabilisation systems for aerodynamic bodies.
RU2219478C1 (ru) * 2002-12-24 2003-12-20 Закрытое акционерное общество "Энергетика" Снаряд
CN102636078A (zh) * 2011-02-10 2012-08-15 吴德滨 旋转炮弹电磁炮
CN102914212A (zh) * 2012-11-21 2013-02-06 魏伯卿 电磁炮回旋加速磁托弹射弹
CN104964600A (zh) * 2015-05-28 2015-10-07 燕山大学 一种多导轨旋转电磁轨道炮

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1037744A (en) * 1962-06-28 1966-08-03 Tampella Oy Ab Method and means for stabilizing the trajectory of projectiles
US4796534A (en) * 1988-01-22 1989-01-10 The United States Of America As Represented By The Secretary Of The Army Spinning ramjet vehicle with a non-spinning combustor
GB2244687B (en) * 1990-06-06 1993-10-27 British Aerospace Stabilisation systems for aerodynamic bodies.
RU2219478C1 (ru) * 2002-12-24 2003-12-20 Закрытое акционерное общество "Энергетика" Снаряд
CN102636078A (zh) * 2011-02-10 2012-08-15 吴德滨 旋转炮弹电磁炮
CN102914212A (zh) * 2012-11-21 2013-02-06 魏伯卿 电磁炮回旋加速磁托弹射弹
CN104964600A (zh) * 2015-05-28 2015-10-07 燕山大学 一种多导轨旋转电磁轨道炮

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11867487B1 (en) 2021-03-03 2024-01-09 Wach Llc System and method for aeronautical stabilization

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