TWI282402B - Projectile for radially deploying sub-projectiles - Google Patents

Projectile for radially deploying sub-projectiles Download PDF

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TWI282402B
TWI282402B TW092100119A TW92100119A TWI282402B TW I282402 B TWI282402 B TW I282402B TW 092100119 A TW092100119 A TW 092100119A TW 92100119 A TW92100119 A TW 92100119A TW I282402 B TWI282402 B TW I282402B
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Taiwan
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projectile
bobbin
sub
projectiles
defense system
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TW092100119A
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Chinese (zh)
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TW200412418A (en
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James Michael O'dwyer
Sean Patrick O'dwyer
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Metal Storm Ltd
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Priority claimed from PCT/AU2002/000909 external-priority patent/WO2003006915A1/en
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Abstract

A projectile (10) for firing from a barrel, said projectile including a multiplicity of barrel assemblies (12, 13, 14) radially disposed from the centre of mass of the projectile, wherein each of said multiplicity of barrel assemblies includes a plurality of sub-projectiles (16) axially disposed within a barrel; each of said sub-projectiles associated with a discrete propellent charge (17) for propelling a respective sub-projectile from the barrel, wherein said projectile is capable of selectively firing sub-projectiles (16), suitably with the aid of primers (18) each coupled to an electronic controller (15), to provide a predetermined pattern of deployed sub-projectiles. A defence system employing projectiles of the type described is also disclosed, together with a method for disguising the launch location of a projectile utilising divert propulsion.

Description

1282402 玖、發明說明 月說月應欽明·發明所屬之技術領域、先前技術、内容、實施方式及圖式簡單說明) 【發明所屬之技術領域】 發明領域 本發明有關於具有彈射體本質的物件之散開,尤其為 5但不限於有關藉由一主彈射體來形成預定型式的散開次彈 射體,以及一種用於掩藏彈射體的發射位置之彈射體發射 方法。 【先前】 發明背景 10 已經使用含有炸藥的彈射體作為分裂裝置來散開複數 個裂片,在一種簡單形式中,此彈射體裂片的外殼係在炸 藥引爆時產生碎裂,使得外殼的個別裂片放射性散開而形 成一略呈球面形的分裂型式。 其他組態中,亦可改變藥劑的形狀及外殼的組態來控 15制分裂型式,但此分裂彈射體產生較薄殼狀的裂片外殼型 式,故需要能夠增加或控制分裂深度。 此等彈射體可能特別適合防禦一指定區域,避免此區 域在威脅情i兄解除之後變得危險(諸如習知雷區發生的情 形)。 20 對於外來攻擊的既有防禦方式係包括用於獲取及監測 包括諸如飛彈與火箭等飛行物的物體執跡之系統,軌跡獲 取及It測糸統之範例係描述於玻克(B〇eck)等人的美國專 利4,622,458號及費佛(Pfeiffer)等人的美國專利5,96〇,〇97號 6 1282402 坎、發明說明 近來對於包括以較高發射角度拋投或擲射目標的發 彈(諸如迫擊砲的特徵)威脅之精密防禦裝置係能夠從彈射 -軌跡求出彈射體發射裝置的位置藉以計算出攻擊來源 0 【發明内容】 發明概要 本發明的彈射體在第一Μ態中係適於從一冑管射出藉 以攔截及摧毀入侵飛彈,特別是高空彈道型飛彈。第二型 恶中,本發明提供-種用於攔截飛彈之方法,此方法包括 以下步驟·決定飛彈的路徑;將一此處描述類型的彈射體 射入該飛彈的路徑;及射出選定的次彈射體以在該決定出 的飛彈路徑中及鄰近處形成一預定型式的次彈射體。 本發明的彈射體可用來防禦載具本身,一受到攻擊特 別是近程攻擊的載具可能將此處描述類型的一彈射體射向 攻擊者並在攻擊者中間以一預定型式散開次彈射體。第三 型悲t,本發明提供一種載具對於攻擊武力之自身防紫方 法,此方法包括以下步驟··決定攻擊武力的位置,·將此處 描述類型的一彈射體射向攻擊武力的預定位置,·及射出選 定的次彈射體以在攻擊武力的預定位置中及鄰近處形成一 預定型式的次彈射體。 本發明的彈射體可用來驅退步兵的前進,第四型態中 ,本發明提供一種驅退步兵之方法,此方法包括以下步驟 :決定步兵的位置;將此處描述類型的至少一彈射體射向 所決定的步兵位置;及射出選定的次彈射體以在所決定的 1282402 玖、發明說明 步兵位置中及鄰近處形成一預定型式的次彈射體。 本發明的彈射體可用來形成空運式影像,諸如煙火, 第五型恕中’本發明提供一種用於形成空運式影像之方法 ’此方法包括以下步驟··將此處描述類型的一彈射體射入 5 空中,及射出包括影像形成物之選定的次彈射體以在空中 形成一預定型式的影像形成物。 本發明的彈射體可用來救火,第六型態中,本發明提 供一種救火之方法,此方法包括以下步驟:決定火場位置 ’將此處描述類型的至少一彈射體射向所決定的火場位置 1〇 ;射出選定的次彈射體以在火場預定位置中及鄰近處形成 預疋型式的次彈射體;及從所射出的次彈射體散開一滅 火劑。 本發明的彈射體可用來產生一燃料·空氣爆炸,第七 型悲中,本發明提供一種產生一燃料-空氣爆炸之方法, 15此方法包括以下步驟:選擇所需要的燃料-空氣爆炸位置 ,·將此處描述類型的至少一彈射體射向燃料_空氣爆炸位 置;射出包括一燃料之選定的次彈射體以形成一預定型式 的次彈射體,·使燃料從所射出的次彈射體散開;射出包括 引爆器之選定的次彈射體以形成一預定型式的次彈射體; 2〇引爆該等引爆器以產生一燃料-空氣爆炸。 本發明的彈射體可用來散開各種不同的酬載物,第八 !心中本發明提供一種散開酬載物之方法,此方法包括 以下步驟:選擇一酬載物之理想輸送位置;將此處描述類 型的至少一彈射體射向酬載物鄰近處;射出包括該酬載物 1282402 玖、發明說明 之遠定的次彈射體以形成-預定型式的次彈射體;及從所 射出的次彈射體散開該酬載物。 本發明的彈射體可用來防禦一指定區域,第九型態中 ▲本發明廣泛地有關於用於防禦―指定區域之防禦系統, 5該防禦系統包括: 至少-監測器’其用於監測指定區域以偵測任何出現 有新物體之區; 防禦褒置’其能夠削弱出現在一遠方指定區域中任何 10處之人員,其中該防禦裝置包括一能夠射出彈射體的武器 ,其中彈射體包括從彈射體的質心呈放射性配置之一陣列 的筒官總成,各筒管總成係具有軸向配置於一筒管内之複 數個次級或次彈射體’次彈射體係與用於從筒管推進該等 次彈射體之分離的推進藥劑相聯結,其中該陣列的筒管總 成能夠從選定的筒管選擇性射出次彈射體,藉此該彈射體 可散開一預定型式的次彈射體;及 通信裝置,其在該監測器與防紫裝置之間提供通信藉 以觸發防禦裝置的選擇性啟動將一削弱用攻擊輸送至戶二 測的區。 、 制11係包括佈設在衫區財之-或多個㈣〇 20 11或佈設為遠離指定區域之遠端感應裝置,或者,監測; 置可包括現址感應器與遠端感應裝置兩者。 監測裝置亦可提供所監測的指定區之_視覺顯示,藉 以依需要致動人工強制控制裝置而能以人工方式控制所設 定的防禦裝置。 1282402 玫、發明說明 …數個筒管同時射出或由單一筒管快速連續射出 數:次級或次彈射體,此等配置中可將電訊號攜行至筒管 或攜打通過疊覆的次級彈射體,疊覆的次級彈射體係 夾扣在彼此頂上以繼續穿過筒管的電路、或者抵靠住彼此 產生電性接觸。次彈龍可攜財控制電路或可與筒管形 成一電路。 —筒㈣成的陣列可配置為與彈射體前導端或尾端相鄰 ,糟以實行彈射體姿態的改變、或在中間使彈射體產生侧 向位移。或者,方向控制系統可包括與彈射體的前導端及 10尾端兩者相鄰之一陣列的筒管總成。 該陣列或各陣列的筒管總成可在具有一縱向分量的方 向中射出-次彈射體藉此增加彈射體的動能、或在與飛彈 縱軸線呈現切線的一方向具有一分量之方向中射出一次彈 射體藉此傳遞或改變彈射體繞其縱軸線之旋轉。筒管總成 15可跨過飛行表面射出次級彈射體(諸如—翼部),以對於彈 射體引發進-步的操舱效果。或者,筒管總成可延伸通過 翼型表面以在兩方向射出,如此可能對於空氣動力學設計 增添了結構性強度。 可視需要提供一分離陣列或相對陣列之筒管總成,來 2〇控制彈射體繞著彈射體縱軸線之旋轉。陣列的級態可包含 相對成對的筒管總成,相對成對的筒管總成係同時射出藉 以只改變繞著彈射體縱軸線之旋轉。可在方向性控制系統 射出次級彈射體之前及/或之後選擇性致動次彈射體,藉 以取消或利用此等彈射體繞其縱軸線旋轉對於彈射體之效 10 1282402 玫、發明說明 本發明的特定實施例令 管總成射出次彈射體來提供 行方向所需要之能量。 ’可能藉由從一或多個選定筒 改變主彈射體的姿態及/或飛 ㈣不赞明的弟二形式,提供一種用於掩藏一彈射體 發射裝置的發射位置之方法,此方法包括以下步n 10 15 筒管總成排放至少一彈射體,該筒管總成係具有一筒管, 複數個彈射體軸向配置於筒管内以操作性密封式接合筒管 的孔徑’及用於將各別彈射體順序性推進通過筒管的管口 之分離的推進藥劑,同時該至少一彈射體處於飛行狀態, 從所包含之一陣列的轉向推進總成發射至少—次彈射體, 各轉向推進總成具有軸向配置於一轉向推進筒管内之複數 個次彈射體’該等次彈射體係與用於從轉向推進筒管順序 性推進該等次彈射體之次級分離推進藥劑相聯結,其中該 陣列的轉向推進筒管總成能夠從選定的轉向推進筒管選擇 性射出次彈射體,藉此利用次彈射體的該種發射作用所產 生之反作用力來加速該彈射體。 由於次彈射體係為可供次級推進劑作用抵住的一質量 塊並在轉向推進筒管的尾膛上施加一反作用力,次彈射體 2〇的整體形狀並不太重要。本發明的目前形式中,可藉由使 留在筒管中的後續次彈射體密封式接合轉向推進筒管的孔 徑來形成尾膛,反作用力係從次級或轉向推進筒管的尾膛 轉移至彈射體並導致彈射體加速。 此陣列的筒管總成可從彈射體的質心呈現放射性配置 11 1282402 玖、發明說明 ’筒管總成的此等組態特別適用於不包含飛行途中推進系 統之物體,亦即火箭及飛彈。射出次彈射料只需使彈射 體位移且彈射體將繼續其軌跡,除了位移之外的部份即為 其視執跡(apparent trajectory)。 5 本發明可特別應用於區域阻絕系統,其中此區域受到 從諸如迫擊砲箱等砲座發射的彈射體所轟擊。當然可瞭解 本發明亦可應用於偽裝其他彈射體發射或射出系統之射出 位置。 -較佳實施财’可選擇視軌跡以將火力從發射裝置 10 轉移至其他空曠位置。 本發明的彈射體最好採用國際專利申請案 PCT/AU94/00124及PCT/AU96/〇〇459號所描述類型之筒管 總成,此等筒管總成包括一筒管;複數個:欠彈射體,其軸 向配置於筒管内以操作性密封式接合筒管的孔徑,以及用 15於順序性推進各別次彈射體通過筒管的筒口之分離的推進 藥劑。 次彈射體可能為圓形、傳統形狀或録狀且其㈣可能 偏置以在鏢從-可能身為平滑孔徑筒管的筒管推進時產生 穩定的旋動。攜載次彈射體之彈射體可能視需要而大致呈 20 圓柱形、卵形或球形。 推進藥劑可能形成為用於操作性隔離筒管中的次彈射 體之實心體塊’或者推進藥劑可能包封在金屬或其他剛性 殼套中’此殼套可能包括一嵌入的雷管,此雷管具有外邙 接觸裝置藉以適可接觸-與筒管相聯結之預先放入的電接 12 1282402 玖、發明說明 觸部。譬如’雷管可設有一簧式接觸部,此簧式接觸部可 縮回而能夠將所裝藥劑插入筒管内並在與該開孔對準時彈 出進入一筒管開孔内以操作性接觸其對接的筒管接觸部。 外殼套視需要可為消耗性或可化學性輔助推進劑的焚燒。 5並且,可提供一堆積及結合或分裝的藥劑及次彈射體之總 成藉以重新裝填一筒管。 各個次彈射體可包括-頭部及用於至少部份地界定一 推進劑空間之延伸裝置,延伸裝置可包括一間隔總成,此 〗IWi、心成從頭^往後延伸並抵靠住_相鄰的次彈射體總成 10 〇 15 20 間隔總成可延伸通過推進劑空間及頭部藉以將壓縮性 負載直接傳遞通過抵靠的相鄰間隔總成,㈣組態中,間 隔總成可對於可能身為頭部的薄圓柱形後部之—延伸裝置 添加了支撐作用。並且,延伸裝置可能與筒管孔徑構成一 操作〖生也封接觸,以防止焚燒漏過次彈射體。 間隔〜、成可i包括—剛性軸環,此剛性軸環往外延伸 、接。L展|±頭部的—薄圓柱形後部且此後部與筒管孔 y見不可操作禮封式接觸,藉以將轴向壓縮性負載直 接傳遞於間隔總成之間來避免延展性頭部變形。、 互補性楔固表面可分別配置於間隔總成及頭部上,因 而回應於間隔t置與頭部之間的相對軸向壓縮將頭部驅入 ”筒:孔位之接合作用。此配置中,可將頭部及間隔總成 裝入筒管内且在造成一軸向位移之後確保次彈射體與筒管 之間具有良好的密封。並適於將延伸裝置驅人與筒管孔徑 13 1282402 玖、發明說明 之接合作用。 頭部可能在其後端界定一推拔狀開孔,此開孔内收納 有位於間隔總成的前導端處之互補性推拔狀插口,其中 頭σ卩與互補性推拔狀插口之間的相對軸向移動將造成一徑 向膨脹力施加至次彈射體。 筒管可能為非金屬性且筒管的孔徑可能包括可用來完 10 15 20 全或部份地容納點火裝置之凹部,此組態中,筒管係容置 有利於電性導通控制裝置與點火裝置之間之電導體,此組 悲可使用在具有有限射出壽命之可棄式筒管總成中,因此 點火裝置及一或多條控制線可以與筒管一體製成。 一筒f總成可另外包括筒管中的點火開孔,且點火裝 置配置於筒管外而與開孔相鄰,一可能含有適可容納點火 裝置的凹部之非金屬性外筒管係可能圍繞住筒管,外筒管 可能亦容置有利於電性導通控制裝置與點火裝置之間之電 導體’外筒管可能形成為—疊層狀塑膠筒管且其可能包括 用於點火裝置之印刷電路疊層。 筒管總成可具有相鄰的次彈射體,次彈射體彼此分離 、五,小可刀朐的關你,各次彈 射體可包括一可膨脹的密封裝置藉以與筒管孔徑形成一操 作性密封,^位裝置可為相鄰的次彈射體之間的推進藥劑 ,且密封裳置適合包括一位於各次彈射體上之裙部,此裙 部在受到筒管中㈣載時則往外膨脹。可能在安裝次彈射 體的期間或在諸如搗實使次彈射體及推進藥劑的圓柱部固 貫的裝载工作之後施加此位於筒部中的負載,或者此負載 14 1282402 玖、發明說明 可能來自於一外次彈射體特別是相鄰的外次彈射體之射出 作用。 次彈射體的後端可能包括位於一往内縮小的凹部周圍 之一裙,此凹部諸如為一圓錐形凹部或一部份球形凹部或 類似物,推進藥劑延伸入此凹部内且在此凹部周圍處次彈 射體的在後移動將導致次彈射體裙的徑向膨服,此往後移 動可能由於次彈射體沿著推進藥劑的前導部份之一往後模 固移動的壓縮而發生,亦可能因為金屬從次彈射體的相對 廣大則導部份流動至其較小裙部而發生。 10 15 20 、或者’次彈射體可能係設有—往後發散的周邊密封凸 緣或軸%且其在次彈射體往後移動時往外撓曲成為與孔徑 j生密封式接合。並且,可能將次彈射體插人-加熱的筒 &内且此筒官收縮在次彈射體的各別密封部份上,藉以實 订讀。久彈射體可能包含一較硬心轴部,心轴部係由推 進藥^加以疋位且與一可能模製在心軸周圍的可變形環狀 卩口作以形成-早讀次彈射體,此次彈射體係仰賴次彈 射體鼻頭與其尾部之間的金屬流動以相對於心轴部往外膨 脹而與筒管孔徑產生密封性接合。 次彈㈣總成可能包括一往後膨脹的鈷表面且在其周 ^鎖㈣,此密封軸環射在切射體經過筒管 =移動·向膨脹而與筒管孔裡產生密封性接合。此組 柱形前導部。車成、有一抵罪住次彈射體的平端面之圓 圓周溝槽内或 次彈射體係可㈣於域及/或定位在 15 1282402 玖、發明說明 藉由孔i中的%狀肋或孔徑中的斷裂溝槽加以定位,並且 可此包括-包住次彈射體的至少外端部之金屬覆套。次彈 射體可能設有可收縮的周邊定位環,可收縮的周邊定位環 係往外延伸入筒管中的環狀溝槽内並在射出時縮回到次彈 5射體内藉以自由地通過筒管。 用於將-筒官總成的推進藥劑順序性點火之電氣點火 可月匕幸乂佳係包括以下步驟:使一點火訊號傳送通過堆積的 次彈射體藉以將前導推進藥劑點火,使前導的推進藥劑產 生點火以打開保險令下個推進藥劑可由下個點火訊號加以 10致動適於藉由將位於正常關閉的電接觸部之間的各別絕 緣引信插入來將-經裝載的筒管端點内的所有推進藥劑加 上保險。 可以電氣方式達成推進劑的點火,或可利用習知撞針 式方法來點火,諸如利用一中心射出雷管將最外部的次彈 射體加以點火且經控制所產生的點火將造成後續回合推進 藥劑順序性點火。可利用燃燒氣體經過控制的往後_或 者利用延伸通過次彈射體之引信柱經過控制的焚燒來達成 此作用。 /、他貫加例中,以電氣方式控制點火,其中各別的推 20進藥劑係與由不同點火訊號所觸發之雷管相聯結。譬如, 可將堆積式推進藥劑中的雷管定序為增加脈寬點火條件, 藉此電子控制器可選擇性傳送增加脈寬的點火脈衝以一種 選定的時序將推進藥劑加以順序性點火。但是,較佳,推 進藥劑係由一設定的脈寬訊號加以點火,且前導的推進藥 16 1282402 玫、發明說明 劑之焚燒將使下個推進藥劑打開保險以供下個發出的脈衝 加以致動。 此等實施例中,適於藉由使位於正常關閉的電接觸部 之間的各別絕緣引信插入來將一經裝載的筒管端點内的所 5有推進藥劑加上保險,將引信設為焚燒而能夠在傳送一適 當觸發訊號時將接觸部閉合,且使各絕緣引信對於一各別 前導推進藥劑呈現開啟以供點火用。 特定實施例中,筒管總成可能係屬於用以射出榴彈狀 次彈射體之低壓型,各別的筒管總成可能裝載有不同的次 10彈射體且筒管總成可能具有不同尺寸的孔徑以容納不同尺 寸的次彈射體。 各次彈射體適於包括一尾軸環,此尾軸環係困留式安 裝至次彈射體體部並在儲存於筒管中時往後延伸以楔固抵 住一尾端次彈射體體部的鼻頭部。一淺的楔固部係適於提 15供此楔固作用,因此在使用時,軸環的尾端膨脹而與筒管 產生操作性密封式接合。 可將尾端軸環安裝為相對於次彈射體體部具有有限的 軸向移動,且軸環的前導端設有一環狀密封面,此環狀密 封面係可接合在次彈射體體部上所形成之一互補面,因此 2〇由於推進氣體在其上的反作用力所導致之次彈射體體部的 在後移動將迫使其互補面在輛環前導端處與環狀密封面產 生密封性接合。 互補面及環狀密封面可大致為徑向延伸且在其上形成 有互補/·生的在封特性。但這些面較佳為互補性部份圓錐形 17 1282402 玖、發明說明 密封面且彼此楔固成為緊宓 冢⑴的袷封式接合,前導端部份亦 可膨脹而與筒管產生操作性贫 F 在封式接合。但部份圓錐形面 之間的楔固作用係適合為較陡哨的面,因此楔固作用並未 使軸環的前導端膨脹而與筒管產生操作性接合。 在低£型應用中’較佳各次彈射體可與一高壓推進劑 室相聯結,此高壓推進劑室係排氣至相鄰次彈射體之間所 形成的低壓推進室而產生有效率的低管口速度操作。高壓 推進劑室可與次彈射體體部或尾端轴環一體成型、或可設 置於筒管外部以經由穿過筒管壁的蜂呈現導通。 10 _可使點火的推進劑傳播進人之空間組態以及推進 劑性質係適於在使用時只發生低的筒管壓力,諸如测至 5000psi左右的壓力。—般而言,轴環在其放鬆姿態中並不 會在裝填用途或在射出期間防止彈射體自由地移動通過筒 管。 15 #-壓力墊在開放的尾端内部安裝於殼體上,軸環在 推進劑點火時係從接合狀況重新定位並由魔力塾扣持在放 鬆狀況以通過筒管及離開筒管管口。 彈射體可為習知類型並以習知方式射出、且較佳適可 從一筒官總成射出,此筒管總成包括軸向配置於一筒管内 20的複數個彈射體,其申各該等彈射體係與用於從筒管推進 該等彈射體之一分離的推進藥劑相聯結。 一較佳形式t,彈射體可概呈球形且具有自球型的質 心呈放射性配置之多數個筒管總成。筒管總成可為相同或 為不同,譬如,大直徑的筒管可從球型彈射體的中心配置 18 1282402 玖、發明說明 中散射一彈射體的裂片,但諸如令彈射體爆炸之此類系統 一般會產生散佈形成—膨脹球殼之—連串裂片,彈射體可 能在預定型式佔用的整體空間中以更均質的方式散開本發 明的次彈射體。藉由控制次彈射體的射出定時,可以建立 5 種一有大致均質性次彈射體分佈之立體“標旗,,形式。或 者可將次彈射體集中在更可能搁戴到飛彈之區域中,以 增向所散開的次彈射體之效力。 次彈射體可包含用於形成空運式影像之材料,影像形 成材料可能譬如包括外爆物、可燃物、白熾物或發光物或 10其他用於提供高度可見的暫時影像之物質。或者,影像形 成物可忐包括諸如具有金屬箔本質之煙霧、氣體、顆粒或 片或條、或者能夠散佈而形成影像之其他材料。因此,可 旎有利地使用本發明的彈射體從軍機發射反制措施,影像 $成物亦可包括諸如降落傘及類似物等用於減慢自散佈位 15置下降的速度之裝置。 次彈射體可配置於筒管總成中所以一旦射出及影像形 成物散開之後,即形成所需要的暫時空運式影像。可將包 a不同影像形成物(具有不同顏色或形式)之次彈射體順序 生衣載入各筒管總成内。 2 0 I _ιββ_ 言如可由外爆裝置、儲存的能量或次彈射體的可分離 70件之分離作用來散開影像形成物以暴露出影像形成物, 或者利用任何其他適當的散佈裝置。 景’像形成物可包含在一殼體内,此殼體可具有任何適 田、、且悲、以圍堵住影像形成物並有適當組態以接合先前彈射 20 1282402 玖、發明說明 此殼體較佳係為榴彈狀彈射體 體之可膨脹軸環的尾端。此殼 但亦可採用具有長形殼體 採用的類型而有較低矮的形狀 的彈射體。 殼體可適於由可生物分解性材料及/或可燃性材料形 成’此材料可基於-諸如木屬等天然產物或—諸如可生物 分解性聚合物等合成材料。 本發明的彈射體最好可散開選定的次彈射體1282402 玖 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明 发明Dispersion, especially 5, but not limited to, a diffuse projectile that forms a predetermined pattern by a primary projectile, and a projectile launching method for hiding the launch position of the projectile. [Previously] Background of the Invention 10 A projectile containing an explosive has been used as a splitting device to spread a plurality of splits. In a simple form, the outer shell of the projectile split is broken when the explosive is detonated, so that the individual splits of the outer shell are radioactively dispersed. And form a slightly spherical split pattern. In other configurations, the shape of the medicament and the configuration of the shell can be changed to control the split pattern, but the split projectile produces a thin shell-like split shell type, so it is necessary to be able to increase or control the split depth. These projectiles may be particularly well suited to defend against a designated area, avoiding the danger of this area becoming dangerous after the threat has been lifted (such as the situation in which the minefield occurs). 20 The existing defenses for external attacks include systems for acquiring and monitoring objects including objects such as missiles and rockets. The examples of trajectory acquisition and It measurement are described in Becker. U.S. Patent No. 4,622,458 to U.S. Patent No. 4,622,458, to U.S. Patent No. 5,96,,,,,,,,,,,,,,,,,,,,,,,,,,,, A sophisticated defense device, such as a feature of a mortar, is capable of determining the position of the projectile launching device from the ejection-trajectory to calculate the source of the attack. [SUMMARY OF THE INVENTION Summary of the Invention The projectile of the present invention is in the first state. Suitable for shooting from a single tube to intercept and destroy invading missiles, especially high-altitude ballistic missiles. In a second type of evil, the present invention provides a method for intercepting a missile, the method comprising the steps of: determining a path of the missile; injecting a projectile of the type described herein into the path of the missile; and ejecting the selected number of times The projectile forms a predetermined type of sub-projectile in and adjacent to the determined missile path. The projectile of the present invention can be used to defend against the vehicle itself, and a vehicle that is attacked, particularly a short-range attack, can fire a projectile of the type described herein toward the attacker and spread the sub-projectile in a predetermined pattern among the attackers. . The third type of sorrow, the present invention provides a self-anti-purple method for the attacking force of the vehicle, the method comprising the following steps: determining the position of the attacking force, and shooting a projectile of the type described herein to the attacking force. The position, and the selected secondary projectile are formed to form a predetermined type of sub-projectile in and adjacent to the predetermined location of the attacking force. The projectile of the present invention can be used to repel the advancement of the infantry. In a fourth form, the present invention provides a method of repelling infantry, the method comprising the steps of: determining the position of the infantry; at least one projectile of the type described herein. Shooting at the determined infantry position; and projecting the selected sub-projectile to form a predetermined type of sub-projectile in and around the determined 1242402 发明, invention instructor position. The projectile of the present invention can be used to form an airborne image, such as a pyrotechnic article, and the present invention provides a method for forming an airborne image. This method includes the following steps: a projectile of the type described herein. The shot is launched into the air and the selected sub-projectile including the image formation is formed to form a predetermined pattern of image formation in the air. The projectile of the present invention can be used for fire fighting. In a sixth aspect, the present invention provides a method of fire fighting, the method comprising the steps of: determining a fire location "at least one projectile of the type described herein is directed at the determined fire The field position is 1 〇; the selected sub-projectile is fired to form a pre-type sub-projectile in and adjacent to the predetermined position of the fire field; and an extinguishing agent is dispersed from the sub-projectile that is ejected. The projectile of the present invention can be used to generate a fuel/air explosion. In a seventh type of sorrow, the present invention provides a method of generating a fuel-air explosion, 15 the method comprising the steps of: selecting a desired fuel-air explosion location, • directing at least one projectile of the type described herein to the fuel_air explosion position; projecting a selected sub-projectile including a fuel to form a predetermined type of sub-projectile, dispersing fuel from the ejected projectile Shooting a selected sub-projectile including a detonator to form a predetermined type of sub-projectile; 2 detonating the detonators to produce a fuel-air explosion. The projectile of the present invention can be used to spread a variety of different payloads. The eighth aspect of the present invention provides a method for dispersing a payload, the method comprising the steps of: selecting an ideal delivery position of a payload; At least one type of projectile is directed toward the vicinity of the payload; the second projectile including the remote projectile of the invented description of the invention is formed to form a predetermined type of projectile; and the secondary projectile is ejected from the projection Spread the rewards. The projectile of the present invention can be used to defend against a designated area. In the ninth type, the present invention broadly relates to a defense system for defending a designated area, and the defense system includes: at least a monitor for monitoring the designation An area to detect any area where a new object appears; a defense device 'which can weaken anyone appearing at any 10 locations in a remote designated area, wherein the defense device includes a weapon capable of projecting a projectile, wherein the projectile includes The center of mass of the projectile is a cylinder assembly of an array of radioactive configurations, each bobbin assembly having a plurality of secondary or secondary projectiles in an axial arrangement in a bobbin, and a sub-ejector system for use from the bobbin Advancing the propellant for advancing the separation of the sub-projectiles, wherein the array of bobbin assemblies is capable of selectively ejecting the sub-projectile from the selected bobbin, whereby the projectile can disperse a predetermined type of sub-projectile; And a communication device that provides communication between the monitor and the anti-purple device to trigger selective activation of the defense device to deliver a weakening attack to the area of the household. The system 11 includes a remote sensing device that is disposed in the shirt area or a plurality of (four) 〇 20 11 or the cloth is set to be away from the designated area, or the monitoring; the device may include both the current location sensor and the remote sensing device. The monitoring device can also provide a visual display of the monitored designated area to manually control the set of defense devices as needed to activate the manual control device. 1282402 Rose, invention description... several bobbins are fired simultaneously or by a single bobbin to quickly and continuously fire the number: secondary or secondary projectiles, in which the electrical signal can be carried to the bobbin or carried through the overlapping times The stage projectiles, the stacked secondary ejection systems are clamped on top of one another to continue through the circuitry of the bobbin or to make electrical contact against each other. The sub-elastic can carry a control circuit or can form a circuit with the bobbin. - The array of cartridges can be configured to be adjacent to the leading or trailing end of the projectile to effect a change in the attitude of the projectile or lateral displacement of the projectile in the middle. Alternatively, the directional control system can include a bobbin assembly in an array adjacent one of the leading end and the trailing end of the projectile. The array or array of bobbin assemblies may eject a sub-projectile in a direction having a longitudinal component thereby increasing the kinetic energy of the projectile or ejecting in a direction having a component in a direction in which the longitudinal axis of the missile exhibits a tangent A projectile thereby transmits or changes the rotation of the projectile about its longitudinal axis. The bobbin assembly 15 can project a secondary projectile (such as a wing) across the flight surface to induce an in-flight maneuvering effect on the projectile. Alternatively, the bobbin assembly can extend through the airfoil surface to exit in both directions, which may add structural strength to the aerodynamic design. A separate array or opposing array of bobbin assemblies can be provided as needed to control the rotation of the projectile about the longitudinal axis of the projectile. The stages of the array may include opposing pairs of bobbin assemblies that are simultaneously ejected relative to each other to change only the rotation about the longitudinal axis of the projectile. The secondary projectile can be selectively actuated before and/or after the directional control system emits the secondary projectile, thereby canceling or utilizing the ejection of the projectile about its longitudinal axis for the projectile 10 1282402, the invention is illustrated The particular embodiment causes the tube assembly to emit a secondary projectile to provide the energy required for the row direction. 'Probably by changing the attitude of the main projectile from one or more selected cylinders and/or flying the (four) undisputed second form, providing a method for hiding the emission position of an ejection device, the method comprising the following Step n 10 15 The bobbin assembly discharges at least one projectile having a bobbin, the plurality of projectiles being axially disposed within the bobbin for operatively sealingly engaging the bore of the bobbin and for The respective projectiles sequentially propel the separated propellant through the nozzle of the bobbin while the at least one projectile is in flight, launching at least one projectile from the steering propulsion assembly of one of the arrays, each steering propulsion The assembly has a plurality of sub-projectiles axially disposed within a steering propeller bobbin. The sub-ejector system is coupled to a secondary separation propellant for sequentially advancing the sub-projectiles from the steering propulsion bobbin, wherein The array of steering propulsion bobbin assemblies is capable of selectively ejecting a sub-projectile from a selected steering propulsion bobbin, thereby utilizing the reaction force generated by the sub-projectile's launching action Speed the projectile. Since the secondary ejection system is a mass that can be resisted by the secondary propellant and exerts a reaction force on the tail of the steering propeller, the overall shape of the secondary projectile 2 is less important. In the present form of the invention, the tail boom can be formed by sealing the subsequent sub-projectiles retained in the bobbin into the bore of the steering bobbin, the reaction force being transferred from the tail of the secondary or steering propeller To the projectile and cause the projectile to accelerate. The bobbin assembly of this array can exhibit a radioactive configuration from the center of mass of the projectile. 11 1282402 玖Inventive Note This configuration of the bobbin assembly is particularly suitable for objects that do not contain the propulsion system in flight, ie rockets and missiles. . Shooting the projectile only requires the projectile to be displaced and the projectile will continue its trajectory, except for the displacement, which is the apparent trajectory. 5 The invention is particularly applicable to regional containment systems in which the area is bombarded by projectiles fired from a base such as a mortar box. It will of course be appreciated that the invention may also be applied to camouflage the ejection locations of other projectile launch or ejection systems. - Preferred implementations may select a viewing trajectory to transfer fire power from the launching device 10 to other open positions. Preferably, the projectile of the present invention employs a bobbin assembly of the type described in the International Patent Application No. PCT/AU94/00124 and PCT/AU96/〇〇459, which includes a bobbin; The projectile is axially disposed within the bobbin to operatively seal the aperture of the bobbin, and 15 is used to sequentially advance the separation of the respective projectile through the barrel of the bobbin. The secondary projectile may be circular, conventional or recorded and its (4) may be biased to produce a stable swirl when the dart is advanced from a bobbin that may be a smooth aperture bobbin. The projectile carrying the sub-projectile may be substantially cylindrical, oval or spherical as desired. The propellant may be formed as a solid block for the secondary projectile in the operationally isolated bobbin 'or the propellant may be encased in a metal or other rigid casing'. The casing may include an embedded detonator having The external contact device is adapted to be in contact with the pre-assembled electrical connection 12 1282402, which is connected to the bobbin. For example, a 'detonator can be provided with a spring-shaped contact portion that can be retracted to insert the loaded medicament into the bobbin and eject into a bobbin opening when aligning with the opening to operatively contact the docking Bobbin contact. The casing may be consumable or chemically assisted in the incineration of the propellant. 5 Also, a stacked and combined or dispensed medicament and sub-projectile assembly can be provided to refill a bobbin. Each of the sub-projectiles may include a head and an extension device for at least partially defining a propellant space, and the extension device may include a spacer assembly, and the IWi, the core extends from the head to the rear and abuts against the _ Adjacent sub-projectile assemblies 10 〇 15 20 The spacer assembly can extend through the propellant space and the head to directly transfer the compressive load through the adjacent spacer assembly. (4) In the configuration, the interval assembly can be Support is added to the extension device, which may be the thin cylindrical back of the head. Also, the extension means may form an operation with the bore diameter of the bobbin to prevent the incineration from leaking through the sub-projectile. The spacing ~, the forming i includes a rigid collar, and the rigid collar extends outward and connects. L Exhibition|±Head-thin cylindrical rear part and this rear part is inoperable and sealed with the tube hole y, so that the axial compressive load is directly transmitted between the spacer assemblies to avoid the deformation of the head deformation . The complementary wedge surfaces may be respectively disposed on the spacer assembly and the head, so that the relative axial compression between the head and the head is driven into the "cylinder: hole joint" in response to the relative axial compression between the head and the head. The head and the spacer assembly can be loaded into the bobbin and ensure a good seal between the sub-projectile and the bobbin after causing an axial displacement, and is suitable for driving the extension device with the bobbin aperture 13 1282402接合, the invention of the joint effect. The head may define a push-out opening at the rear end thereof, the opening contains a complementary push-out socket at the leading end of the spacer assembly, wherein the head σ卩The relative axial movement between the complementary push-out sockets will cause a radial expansion force to be applied to the secondary projectile. The bobbin may be non-metallic and the bore of the bobbin may include all of the 10 15 20 full or partial The recess of the ignition device is accommodated. In this configuration, the bobbin is accommodated to facilitate the electrical conductor between the electrical conduction control device and the ignition device. This group can be used in a disposable bobbin with a limited injection life. Into the middle, therefore the ignition device And one or more control wires may be integrally formed with the bobbin. The one cylinder f assembly may additionally include an ignition opening in the bobbin, and the ignition device is disposed outside the bobbin adjacent to the opening, and one may contain suitable accommodation The non-metallic outer bobbin of the recess of the ignition device may surround the bobbin, and the outer bobbin may also accommodate an electrical conductor that facilitates electrical conduction between the control device and the ignition device. The outer bobbin may be formed as a stack. Plastic tube and it may include a printed circuit stack for the ignition device. The bobbin assembly may have adjacent sub-projectiles, the sub-projectiles are separated from each other, five, the small knife can close you, each ejection The body may include an expandable sealing device to form an operative seal with the bore aperture, the position device may be a propellant medicament between adjacent subprojectiles, and the sealing skirt is adapted to include a plurality of projectiles a skirt that expands outward when loaded by the bobbin (four). It may be applied during the installation of the subprojectile or after a loading operation such as tamping to force the subprojectile and the cylindrical portion of the propellant This is located in the tube The load in the section, or the load 14 1282402 玖, the description of the invention may come from the injection of an outer projectile, especially an adjacent outer projectile. The rear end of the secondary projectile may include a recess that is located in a narrowing direction. a skirt around the recess, such as a conical recess or a portion of a spherical recess or the like, into which the propellant extends into the recess and the subsequent movement of the sub-projectile around the recess will result in a sub-ejector skirt Radial expansion, this backward movement may occur due to the compression of the secondary projectile along one of the leading portions of the propellant, and may also flow due to the relatively large amount of metal from the secondary projectile. 10-15 20 or 'sub-projectiles may be provided with a peripheral seal flange or shaft % diverging backwards and deflected outwardly as the sub-projectile moves backwards j raw sealed joint. Also, it is possible to insert the secondary projectile into the heated cylinder & and the cylinder is contracted onto the respective sealed portions of the secondary projectile for actual reading. The long-term projectile may include a harder mandrel portion that is clamped by the propellant and formed with a deformable annular mouth that may be molded around the mandrel to form an early read-out projectile. The secondary ejection system relies on the metal flow between the secondary projectile and its tail to expand outwardly relative to the mandrel portion to create a sealing engagement with the bore aperture. The secondary (four) assembly may include a cobalt surface that expands rearward and is locked (4) in its circumference. The sealing shaft is fired in the cutting body through the bobbin = moving and expanding to form a sealing engagement with the bore of the bobbin. This group of cylindrical guides. In a circular circumferential groove or a secondary ejection system that has a flat end face that is in violation of the projectile, it can be (4) in the domain and/or positioned at 15 1282402. The invention is illustrated by the % rib or aperture in the hole i. The fracture groove is positioned and may include a metal cover that encases at least the outer end of the secondary projectile. The secondary projectile may be provided with a retractable peripheral positioning ring, the retractable peripheral positioning ring extending outwardly into the annular groove in the bobbin and retracting into the sub-bomb 5 when projecting, thereby freely passing through the barrel tube. The electric ignition for sequentially igniting the propellant of the cylinder assembly may include the following steps: transmitting an ignition signal through the stacked sub-projectiles to ignite the pilot propellant to advance the precession The medicament is ignited to open the fuse so that the next propellant can be actuated by the next firing signal. 10 is adapted to insert the end of the loaded bobbin by inserting individual insulation fuzes between the normally closed electrical contacts. All the propellants in the insurance plus insurance. The propellant ignition can be achieved electrically, or can be ignited using conventional pin-type methods, such as igniting the outermost sub-projectile with a centrally-shot detonator and the resulting ignition will cause subsequent rounds to advance the drug sequence. ignition. This effect can be achieved by controlled combustion of the combustion gases later or by controlled incineration using a futible column extending through the secondary projectile. / In his case, the ignition is controlled electrically, and each of the push-in units is connected to a detonator triggered by a different ignition signal. For example, the detonators in the stacked propellant can be sequenced to increase the pulse width ignition condition whereby the electronic controller can selectively transmit an ignition pulse that increases the pulse width to sequentially ignite the propellant at a selected timing. Preferably, however, the propellant system is ignited by a set pulse width signal, and the inducing drug of the lead propellant 16 1282402, the inventing agent will cause the next propellant to be opened for insurance to be actuated by the next pulse. . In these embodiments, it is adapted to inflate the 5 propellant medicaments within the end of a loaded bobbin by inserting individual insulation fuzes between the normally closed electrical contacts, and setting the fuze to Incineration enables the contacts to be closed when an appropriate trigger signal is transmitted, and each insulation fuse is opened for ignition of a respective pilot propellant. In a particular embodiment, the bobbin assembly may be of a low pressure type for projecting a grenade-like sub-projectile, and each bobbin assembly may be loaded with a different sub-10 projectile and the bobbin assembly may have different sizes. The aperture is adapted to accommodate sub-projectiles of different sizes. Each of the projectiles is adapted to include a tail collar that is trapped to the body of the secondary projectile and extends rearwardly when stored in the bobbin to wedge against a tail end projectile body The nose of the department. A shallow wedge is adapted to provide this wedging action so that in use, the trailing end of the collar expands to create an operative sealing engagement with the barrel. The tail collar can be mounted for limited axial movement relative to the secondary projectile body, and the leading end of the collar is provided with an annular sealing surface that engages the secondary projectile body Forming a complementary surface, so that the subsequent movement of the secondary projectile body due to the reaction force of the propellant gas on it will force its complementary surface to seal with the annular sealing surface at the leading end of the ring. Engage. The complementary face and the annular sealing face may extend substantially radially and have complementary properties on the seal. However, these faces are preferably complementary partial conical 17 1282402 玖, the invention describes the sealing faces and is wedged to each other to form a 袷-sealing joint of (1), and the leading end portion can also expand and operate poorly with the bobbin. F is joined in the seal. However, the wedging action between the partial conical faces is suitable for the steeper horn face, so that the wedging action does not expand the leading end of the collar to create an operative engagement with the bobbin. In low-profile applications, it is preferred that each of the projectiles be coupled to a high-pressure propellant chamber that is vented to a low-pressure propulsion chamber formed between adjacent sub-projectiles to produce an efficient Low nozzle speed operation. The high pressure propellant chamber may be integrally formed with the secondary projectile body or the trailing end collar, or may be placed outside of the barrel to conduct conduction via a bee passing through the wall of the barrel. 10 _ The space configuration that allows the propellant to be ignited into the human space and the propellant properties are suitable for use with only low bobbin pressures, such as pressures up to about 5,000 psi. In general, the collar does not prevent the projectile from moving freely through the barrel during loading or during ejection. The 15 #-pressure pad is mounted to the housing inside the open tail end. The collar is repositioned from the engaged condition when the propellant is ignited and held in a loose condition by the magic force to pass the bobbin and exit the bobbin nozzle. The projectile can be of a conventional type and fired in a conventional manner and preferably adapted to be ejected from a tubular assembly comprising a plurality of projectiles axially disposed within a bobbin 20, The ejection systems are coupled to a propellant for separating the one of the projectiles from the bobbin. In a preferred form t, the projectile can be substantially spherical and have a plurality of bobbin assemblies in which the centroid of the self-spherical shape is radioactively disposed. The bobbin assemblies may be the same or different, for example, a large diameter bobbin may be configured from the center of the spherical projectile 18 1282402 玖, in the description of the invention, a lob of a projectile is scattered, but such as to explode the projectile The system generally produces a series of lobes that are scatter-formed to expand the spherical shell, and the projectile may spread the secondary projectile of the present invention in a more homogeneous manner in the overall space occupied by the predetermined pattern. By controlling the timing of the ejection of the sub-projectile, it is possible to establish three kinds of three-dimensional "flags, a form with a substantially homogeneous sub-projectile distribution. Alternatively, the sub-projectiles can be concentrated in an area more likely to be placed in the missile. The effectiveness of the secondary projectile that is spread out. The secondary projectile may include materials used to form an airborne image, and the image forming material may include, for example, a blowout, a combustible, an incandescent or a illuminant or other a substance of a highly visible temporary image. Alternatively, the image forming material may include such materials as smoke, gas, particles or sheets or strips having the essence of a metal foil, or other materials capable of being dispersed to form an image. The invented projectile launches counter-measures from the military aircraft, and the image artifacts may also include devices such as parachutes and the like for slowing down the speed at which the self-dispersing position 15 is lowered. The sub-projectiles may be disposed in the bobbin assembly. Therefore, once the shot and the image formation are scattered, the desired temporary airborne image is formed. The package a different image formation (with different colors) Or the form of the projectile of the projectile is loaded into each of the bobbin assemblies. 2 0 I _ιββ_ Words can be separated by the separation of the blasting device, the stored energy or the separable 70 pieces of the sub-projectile To expose the image former, or to utilize any other suitable dispensing device. The image formation can be contained within a housing that can have any field, and sorrow, to block the image formation and It is suitably configured to engage the previous ejection 20 1282402. The invention is preferably a tail end of an expandable collar of a grenade-like projectile body. The casing may also be of the type having a long casing. a projectile having a lower profile. The casing may be adapted to be formed from a biodegradable material and/or a flammable material. This material may be based on - a natural product such as a wood or a biodegradable polymer, etc. Synthetic material. The projectile of the present invention preferably disperses the selected sub-projectile

10形式散開其餘的次彈射體。 本务月的彈射體可適合使用在本申請人的國際專利申 請案PCT/AUG_ 13 5 1號巾賴述類型之m统中。 圖式簡單說明 為了更瞭解及實際施行本發明,現在參照用於顯示本 15發明的較佳實施例之附圖,其中·· 第1圖為根據本發明的一較佳實施例之一彈射體的剖 第2圖為在具有複數個軸向配置的軟殼彈射體之一筒 吕〜、成中所使用之一軟殼彈射體的剖視圖; 第3圖為第2圖所示之軟殼彈射體的發射方式之剖視圖; 第4圖為根據本發明另 第5圖為另一貫施例之防禦系統的立體圖。 21 1282402 玖、發明說明 第3圖顯示從一主筒管總成3〇射出之一系列的彈射體 10 ’主缚管總成3 0具有複數個主筒管3 1、3 2及3 3。彈射I# 10A已從筒管33射出並拋棄其軟殼(未圖示),彈射體1〇B已 從琦管32射出且軟殼20在圖中處於拋棄過程,可膨脹套筒 5 23已脫離後軟殼22且後軟殼22亦已脫離彈射體1〇β,前軟 殼21已同樣地脫離彈射體10B,彈射體1〇c已更晚地從筒 管31射出且軟殼20已開始脫離彈射體i〇c。 參照第4及5圖,已看出藉由分佈於整個指定區域之一 陣列的現場感應器41來監測一接受防禦的指定區域4〇,此 10等感應器可能為諸如壓力型、聲音型或震動型感應器等任 何適當的類型。 所顯示的防禦系統42採用的武器係為一對榴彈箱43的 形式,權彈箱43各使用筒管總成3〇且麵合至一遠端感應裝 置44及一與現場感應器41相聯結的接收器單元,依照入 15侵物的本質來選擇所需要之次彈射體的型式。 進入指定區域40内之入侵物可能為任意數種形式其中 入侵物可能為步兵或徒 入侵物可能為諸如裝甲 之一種且可能包括複數個入侵物, 步士兵等形式的軍事人員。或者, 20發砲執跡並計算發射裝置的位置之精密 之精密防禦系統,藉以攻The 10 form spreads the remaining subprojectiles. The projectile of this month may be suitable for use in the applicant's international patent application PCT/AUG_13 5 1 towel type. BRIEF DESCRIPTION OF THE DRAWINGS For a better understanding and practical implementation of the present invention, reference is now made to the accompanying drawings in FIG Figure 2 is a cross-sectional view of a soft shell projectile used in one of a plurality of soft shell projectiles having a plurality of axial configurations; and Fig. 3 is a soft shell ejection shown in Fig. 2. A cross-sectional view of a mode of emission of a body; Fig. 4 is a perspective view of a defense system of another embodiment according to another fifth embodiment of the present invention. 21 1282402 发明, DESCRIPTION OF THE INVENTION Figure 3 shows a series of projectiles ejected from a main bobbin assembly 3 10 10' main bib tube assembly 30 has a plurality of main bobbins 3 1 , 3 2 and 3 3 . The ejection I# 10A has been ejected from the bobbin 33 and discarded its soft shell (not shown), the projectile 1〇B has been ejected from the pass tube 32 and the soft shell 20 is in the process of abandonment, the expandable sleeve 5 23 has After the detachment of the soft shell 22 and the rear soft shell 22 has also detached from the projectile 1 〇 β, the front soft shell 21 has likewise detached from the projectile 10B, the projectile 1 〇 c has been ejected from the bobbin 31 later and the soft shell 20 has Start to break away from the projectile i〇c. Referring to Figures 4 and 5, it has been seen that by monitoring a designated area 4 接受 that is protected by an on-site sensor 41 distributed throughout an array of designated areas, such a 10 may be of a pressure type, a sound type or Any suitable type such as a vibrating sensor. The weapon system 42 is shown in the form of a pair of grenade boxes 43 each having a bobbin assembly 3 that is coupled to a distal sensing device 44 and coupled to the field sensor 41. The receiver unit selects the type of sub-projectile required according to the nature of the intrusion. The invasive objects entering the designated area 40 may be in any of several forms. The intruder may be an infantry or an invader. The intruder may be a military personnel such as a type of armor and may include a plurality of invaders, step soldiers, and the like. Or, 20 precision guns and the precise precision defense system that calculates the position of the launcher.

車或坦克車《人或無人載具,人侵者可能具有可以追縱 23 1282402 玖、發明說明 視軌跡。 雖Λ、、:上述防g系、统以陸地為基礎,本發明的另一型態 有關於可能稱為水雷之彈射體,這些水雷可從船艦發射並 5 10 保持漂浮水中而由遙控方式或則包括雷達、聲納或紅外 線感應器等機載感應“統的自發性操作加以啟動,可配 置一道含有諸如懸吊重碼等穩定或㈣裝置之水雷防線藉 以提i、依需要啟動或解除啟動的水用防禦周邊。 另佈°又模式中,本發明的彈射體可從諸如直昇機等 氣機落下可提供諸如矛部等穩定或錯固裝置來固定住將 彈射體扣持在地上的一位置,第一層的次彈射體可包括用 於發射則貞測是w魏方«錢具之感m统,且 可依需要由彈射體的各別筒管中之後續層的榴彈來接戰敵 方部隊或載具,可在其他層中提供其他感應器來調查接戰 結果。 另一佈设模式係提供一種具有便於手握及拋擲佈設的尺 寸之彈射體,類似於習知的手瘤彈。但是,若在手送式彈射 體的筒管中包含有次彈射體,將能夠利用一預設時間延遲 或-遙控设備由重覆模式加以使用,這可在諸如衔戰或洞 八地形等趙閉空間中發生接戰時提供特定的優點,次彈射 20體可包含非致命性彈藥及一警告用的音訊廣播系統,或許 在對峙情況中,若歹徒未立刻投降則能夠發出額外彈藥。 本發明的彈射體可依需要攜帶至太空中並送入一行星 或衛星周圍的軌道中,其實際包含一人造衛星。因為筒管 總成可在一概呈球型體部内呈放射性散佈,其可很有效地 24 1282402 玖、發明說明 運作以矯正人造衛星在軌道中之位置、保護一寶貴人造衛 星周圍的一區不受太空垃圾、隕石及類似物所侵襲、或與 一敵方太空載具或人造衛星接戰。因為發射一實心次彈射 體而非傳統人造衛星的氣體迸發所解放出之能量的緣故, 5 在低重力環境中可以遠為更快速地進行位置改變。適當地 建造人造衛星彈射體使其可藉由軌道衰退後再度進入大氣 時的燃燒加以消耗。 一種特定形式中’人造衛星可能包括一超彈射體,此 超彈射體可從其中放射性配置的筒管總成來散開本發明的 10彈射體,且這些散開的彈射體本身可配備有次彈射體,藉 以提供二階式防禦系統,此二階式防禦系統當然可使用於 具有適當規模的其他應用中。 當然暸解上文只是本發明的說明性範例,被熟悉此技 藝者視為位於本發明廣泛範圍及精神内之所有此等修改及 15變化係由申請專利範圍所界定。 【圖式簡單明】 第1圖為根據本發明的一較佳實施例之一彈射體的剖 視圖; 20 第2圖為在具有複數個軸向配置的軟殼彈射體之一筒 管總成中所使用之一軟殼彈射體的剖視圖; ° 第3圖為第2圖所示之軟殼彈射體的發射方式之剖視圖; 第4圖為根據本發明另—實施例之一防禦系統的側視 弟5圖為另_;丨上 貝方也例之防禦系統的立體圖 25 1282402 玖、發明說明 【圖弍之主要元件代表符號表】 10310A,i0EMi)C …彈射體 23...可膨脹套筒 1U2…大孔.徑筒管 24…去角後表面 13...中等孔徑筒管 30…主筒管總成 14...小孔徑筒管 31,32,33·..主筒管 15...電子控制器 40···指定區域 16…次彈射體 41...現場感應器 17...推進藥劑 42…防禦系統 18...點火裝置 43...榴彈箱 20...軟殼 44...遠端感應裝置 21...前軟殼部 49…接收器單元 22...後軟殼部 26Cars or tanks "People or unmanned vehicles, people invaders may have the ability to trace 23 1282402 玖, invention description track. Although the above-mentioned anti-g system is based on land, another form of the invention relates to a projectile that may be called a mine, which can be launched from a ship and 5 10 kept in floating water by remote control or Including the on-board sensing of radar, sonar or infrared sensors, etc., the spontaneous operation of the system is activated, and a mine defense line containing a stable or (four) device such as a suspended weight can be configured to provide i, start or deactivate as needed. In addition to the mode, the projectile of the present invention can be lowered from a gas engine such as a helicopter to provide a stabilizing or staggering device such as a lance to secure a position in which the projectile is held on the ground. The second projectile of the first layer may include a missile for the launch, and the speculation is the sense of the money, and the grenade of the subsequent layer in the respective bobbins of the projectile may be used to pick up the enemy troops as needed. Or vehicle, other sensors can be provided in other layers to investigate the outcome of the battle. Another layout mode provides a projectile with a size that is easy to handle and throw, similar to conventional handguns. If the bobbin in the hand-carrying projectile contains a secondary projectile, it will be able to use a preset time delay or - the remote control device is used by the repeat mode, which can be used in such as the title or the hole eight terrain. A particular advantage is provided in the event of a battle in a closed space. The secondary projectile 20 may contain non-fatal ammunition and a warning broadcast system. In the case of confrontation, if the gangster does not surrender immediately, additional ammunition can be issued. The projectile can be carried into space and sent to a orbit around a planet or satellite, which actually contains an artificial satellite. Because the bobbin assembly can be radioactively dispersed in a generally spherical body, it can be effective. 24 1282402 发明, invention instructions to operate to correct the position of the satellite in orbit, to protect a region around a valuable satellite from space debris, meteorites and the like, or with an enemy space vehicle or satellite Because of the energy liberated by the emission of a solid sub-projectile rather than the gas of a traditional satellite, 5 can be far in a low-gravity environment. Rapidly change position. Properly constructed satellite projectiles can be consumed by combustion when the orbit is degraded and then re-enter the atmosphere. In a particular form, the 'artificial satellite may include a super-projectile, which can be The radioactively configured bobbin assembly is used to spread the 10 projectiles of the present invention, and the diffused projectiles themselves can be equipped with sub-projectiles to provide a second-order defense system, which can of course be used for an appropriate scale. It is to be understood that the foregoing is only an illustrative example of the invention, and all such modifications and 15 variations are within the scope and spirit of the invention as defined by the appended claims. BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a cross-sectional view of an ejection body in accordance with a preferred embodiment of the present invention; 20 Figure 2 is used in a bobbin assembly of a soft shell projectile having a plurality of axial configurations A cross-sectional view of one of the soft shell projectiles; ° Fig. 3 is a cross-sectional view showing the mode of emission of the soft shell projectile shown in Fig. 2; The other side of the embodiment is a side view of the defense system. The figure is another _; the top view of the defensive system of the 贝 贝 25 25 25 128 128 128 128 128 128 128 128 128 128 128 128 128 128 128 128 103 103 103 103 103 103 103 103 103 103 103 103 103 103 103 103 103 103 103 C ... projectile 23... expandable sleeve 1U2... large hole. diameter bobbin 24... chamfered rear surface 13... medium aperture bobbin 30... main bobbin assembly 14... small aperture bobbin 31 , 32, 33 ·.. main bobbin 15 ... electronic controller 40 · · · designated area 16 ... sub-projectile 41 ... field sensor 17 ... propellant 42 ... defense system 18 ... ignition Device 43...grenade box 20...soft shell 44...distal sensing device 21...front soft shell portion 49...receiver unit 22...rear soft shell portion 26

Claims (1)

1282402 拾、申請專利箪姻 擎修(更》正替換頁 第921〇〇119#u專财請f φ請專利範时正* % η a 1. 種用於針對-目標發射之彈射體,該彈射體包括: 夕數個筒管總成,其從該彈射體的質心呈放射性 •'、中各"亥等多數個筒管總成係包括軸向配置於 一筒管内之複數個次彈射體; ⑽各該等次彈射體係與用於從該筒管推進一各別次 、/之力離的推進藥劑相聯結,其中該彈射體能 夠選擇性射出次彈射體以提供一預定型式之經散開的 次彈射體。 2. 如申請專利範圍第i項之彈射體,其中該彈射體適可從 一筒管射出。 3. 如申請專利範圍第2項之彈射體,其中該等複數個次彈 射體係軸向配置於該筒管内以操作性密封式接合該筒 管的孔徑。 如申清專利範圍第1至3項中任—項之彈射體,其概呈 東开少且具有從該球中心呈放射性配置之多數個筒管總 成。 5· ^申請專利範圍第4項之彈射體,其具有多種不同的筒 6 &直#係為了使多種不同口徑之次彈射體能被利用。 6·如申請專利範圍第4項之彈射體,其中較大直捏的筒管 係自該球形彈射體的中心配置且較小直捏的筒管定位 等車乂大直徑的筒管之間,以盡量加大該彈射體中 之次彈射體的密度。 7 •如申請專利範圍第!項中之彈射體,其中該彈射體包括 27 1282402 拾、申請專利範圍 一軟殼。 8.如申請專利範圍第1項中之彈射體,進一步包括一用於 控制該等推進藥劑的點火之電子控制器。 5 10 15 20 9·如申請專利範圍第8項之彈射體,其中可同時發射或快 速連續發射數個次彈射體。 1〇·如申請專利範圍第8項之彈射體,其中將該等多數個筒 管總成配置為可以使該彈射體上具有最小反作用合力 的方式來散開該等次彈射體,而該彈射體得以保持一 所需要的執跡。 U·如申請專利範圍第8項之彈射體,進一步包括用於追蹤 一威脅或入侵者之感應器。 12·如申請專利範圍第8項之彈射體,其中該電子控制器經 由一通信連結自一遠端追蹤站接收射出指令。 .如申凊專利範圍第丨項之彈射體,#中散開該等次彈射 體藉以變更或控制該彈射體的執跡。 •種用於攔截—飛彈之方法,該方法包括以下步驟: 決定該飛彈的路徑;射出-根據申請專利範圍第β13 項中任一項之彈射體進入該飛彈的路徑中,·及射出選 定的次彈射體以在該飛彈的預定路徑中及鄰近處形成 一預定型式的次彈射體。 種用於-載具自我”―攻料力之方法,包括以 :步驟:以該攻^力❹置;在該攻擊武力的經 决疋位置鄰近處射出—根據申請專利範圍第加項中 任一項之彈射體;及射ψ、煙6仏 、 射出選定的次彈射體以在該攻擊 28 15. 1282402 拾、申請專利範圍 武力的經決定位置中及鄰近處形成一預定型式的次彈 射體。 16. —種用於驅退步兵之方法,包括以下步驟:決定該步 兵的位置;在該步兵的經決定位置鄰近處射出至少一 個根據申請專利範圍第1至13項中任一項之彈射體;及 在該步兵的經決定位置中及鄰近處射出選定的次彈射 體以形成一預定型式的次彈射體。 10 15 20 17.—種用於形成空運式影像之方法,包括以下步驟:射 出一根據申請專利範圍第丨至13項中任一項之彈射體至 空中;及射出包括影像形成物之選定的次彈射體以在 空中形成一預定型式的影像形成物。 18·-種用於救火之方法,包括以下步驟:決㈣火場的 位置;在該火場的經決定位置鄰近處射出至少一根據 申請專利範㈣!至13财任—項之彈射體;射出選定 的次彈射體以在該火場的經決定位置中及鄰近處形成 預疋型式H彈射體;及從料射㈣次彈射體散 開一減火劑。 •一種用於產生一燃料'氣體外 •、 爆之方法,包括以下步驟 ••選擇該燃料-氣體外爆之所雲 所而要位置,·在該燃料-氣體 外爆的所需要位置鄰近處 根據申凊專利範 ㈤第1至13項中任一項之彈射 ㈣體,射出包含-燃料之選 疋的-人彈射體以形成一 私山 頂疋型式的次彈射體;從該等 射出的次彈射體散開該辦 认u 、抖’射出包含引爆器之選定 的—人彈射體以形成一預定型 生式的次彈射體;引爆該等 29 1282402 拾、申請專利範圍 引爆器以產生一燃料-空氣外爆。 •種用於散開一酬載物之方法,包括以下步驟:選擇 一酬載物輸送之一所需要位置;在該酬載物所需要位 · 置鄰近處射出至少一根據申請專利範圍第丨至13項中任 一項之彈射體;射出包含該酬載物之選定的次彈射體 - 以形成一預定型式的次彈射體;及從該等射出的次彈 射體散開該酬載物。 21· —種用於防禦一指定區域之防禦系統,該防禦系統包 馨 括: 至v監測器,其用於監測該指定區域以偵測其 _ 中出現有一新物體之任何區; — 防禦裝i,其能夠削弱出現在一冑方指定區域+ 任何處之入侵物,其中該防禦裝置包括-能夠射出彈 _ 射體的武器,其中該彈射體包括: —從該彈射體的質心呈放射性配置之一陣列的筒管 、、心成,各筒官總成係具有軸向配置於一筒管内之複數 眷 们人、、及或次彈射體,該等次彈射體係與用於從該筒管 )丨員序性推進料:欠彈射體之分離的推進藥劑相聯結, 及 - —"亥陣列的筒管總成能夠從選定的筒管選擇性射出 — °亥等—人彈射體’藉此該彈射體可散開-預定型式的次 彈射體;及 通t裝置,其在該監測器與該防禦裝置之間提供 U藉以觸.發該防禦裝置的選擇性啟動將一削弱攻擊 30 1282402 拾、申請專利範圍 輸送至所债測的區。 22.如申請專利範圍第21項之防禦系統,其中該等監測器 係包括佈設在該指定區域中之一或多個現址感應器或 佈没為遠離該指定區域之遠端感應裝置。 5 23·如申請專利範圍第21或22項之防禦系統,其中該等監 測裝置提供所監測的指定區之一視覺顯示,藉以可依 需要致動人工強制控制裝置而能以人工方式控制武器 〇 24. 如申請專利範圍第21項之防禦系統,其中可從複數個 1〇 筒管同時射出或由單一筒管快速連續射出數個次彈射 體。 25. 如申請專利範圍第24項之防禦系統,其中該筒管之一 外部電路上有一電性射出訊號被攜行通過。 26·如申請專利範圍第24項之防禦系統,其中疊覆之該次 15 彈射體上有一電性射出訊號被攜行通過。 27·如申請專利範圍第26項之防禦系統,其中該等次彈射 體係夾扣在彼此頂上以繼續一穿過該筒管的電路。 28·如申請專利範圍第26項之防禦系統,其中該等次彈射 體彼此抵靠產生電性接觸。 20 29·如申請專利範圍第24項之防禦系统,其中該等次彈射 體各攜載一控制電路。 30·如申請專利範圍第21項之防禦系統,其中該陣列的筒 管總成係包括配置於該彈射體的一端鄰近處之筒管籍 以實行該彈射體姿態的改變。 31 1282402 拾、申請專利範圍 31·如申請專利範圍第21項之防禦系統,其中該陣列的筒 管總成係包括配置於中間使該彈射體側向位移之筒管 〇 32. 如申請專利範圍第21項之防禦系統,其中各陣列的筒 5 管總成可在具有一縱向分量的方向中射出一次彈射體 以藉此增加該彈射體的動能。 33. 如申請專利範圍第21項之防禦系統,其中各陣列的筒 管總成可在與該彈射體縱軸線呈現切線的一方向中具 有-分量之方向中射出一次彈射體,藉以傳遞或改變 10 該彈射體繞其縱軸線之旋轉。 34·如申請專利範圍第21項之防㈣統,其中至少部份的 該等筒管總成可跨過飛行表面射出諸如一翼部等次級 彈射體,以對於該彈射體引發進一步的操舵效果。 35·如申請專利範圍第21項之防禦系統,其中至少部份的 15 1 亥等筒管總成係延伸通過翼型表面以在兩方向射出。 36·如申請專利範圍第21項之防禦系統,其中提供一分離 陣列或相對陣列之筒管總成來控制彈射體繞著該彈射 體縱轴線之旋轉。 37.如申請專利範圍第36項之防禦系統,其中該等陣列的 2〇 '组態係包含用於同時射出藉以只改變繞著該彈射體縱 軸線的旋轉之相對成對的筒管總成。 38·如申請專利範圍第21項之防禦系統,其中可能藉由從 選定的商官總成射出次彈射體來提供改變該等彈射體 的姿態及執跡所需要之能量。 32 1282402 拾、申請專利範圍 39 -種用於掩藏_彈射體發射裝置的發射位置之方法, 該方法包括以下步驟: 5 10 15 同管總成排出至少一彈射體,該筒管總成 係具有-筒管,複數個彈射體軸向配置於該筒管内以 操作4封式接合該筒管的孔徑,及用於將各別彈射 體I貝序f生推進通過該筒管的管口之分離的推進藥劑; (b)當该至少一彈射體處於飛行狀態時,從所包含 之一陣列的轉向推進總成射出至少一次彈射體,各轉 向推進總成具有軸向配置於—轉向推進筒管内之複數 個人彈射體,該等次彈射體係與用於從該轉向推進筒 笞順序性推進該等次彈射體之次級分離推進藥劑相聯 結;其中 (c)該陣列的轉向推進筒管總成能夠從選定的轉向 推進筒管選擇性射出該等次彈射體,藉此利用該等次 彈'射體的發射作用所產生之反作用力來加速該彈射體。 331282402 Pick up, apply for a patent, 擎 擎 擎 repair (more) is replacing page 921 〇〇 119 #u special wealth please f φ please patent Fan Shizheng * % η a 1. Kind of projectile for target-target launch, The projectile includes: a plurality of bobbin assemblies, which are radioactive from the center of mass of the projectile, and a plurality of bobbin assemblies including a plurality of tubes arranged axially in a bobbin. (10) each of the sub-ejector systems is coupled to a propellant for ejecting a different force from the bobbin, wherein the projectile is capable of selectively ejecting the sub-projectile to provide a predetermined pattern. 2. A projectile that is spread out. 2. In the case of the projectile of the scope of claim i, wherein the projectile is suitable to be ejected from a bobbin. 3. The projectile of claim 2, wherein the plurality of projectiles The secondary ejection system is axially disposed in the bobbin to operatively and sealingly engage the aperture of the bobbin. The projectile of any one of items 1 to 3 of the patent scope of the patent is substantially open and has The ball center is a radioactive configuration of most of the bobbin assemblies. Please refer to the projectile of item 4 of the patent scope, which has a plurality of different cylinders 6 & straight # in order to enable the use of a plurality of different caliber projectiles. 6. The projectile of claim 4, which is larger The straight pinched bobbin is disposed between the center of the spherical projectile and the small straight pinched bobbin is positioned between the large diameter bobbin to maximize the density of the sub-projectile in the projectile. • The projectile in the scope of the patent application, wherein the projectile includes 27 1282402, and the patent application scope is a soft shell. 8. The projectile of claim 1 further includes a control for An electronic controller for propelling the ignition of a medicament. 5 10 15 20 9 · If the projectile of the scope of claim 8 is capable of emitting a plurality of subprojectiles simultaneously or in rapid succession, 1 〇· The projectile of the item, wherein the plurality of bobbin assemblies are configured to disperse the sub-projectiles in a manner that has a minimum reaction force on the projectile, and the projectile maintains a desired U. The projectile of claim 8 further includes a sensor for tracking a threat or intruder. 12. The projectile of claim 8 wherein the electronic controller is via a The communication link receives an injection command from a remote tracking station. For example, in the projectile of the third paragraph of the patent application scope, the ejection of the sub-projectiles in # is used to change or control the execution of the projectile. a method of flying a missile, the method comprising the steps of: determining a path of the missile; projecting - entering a path of the projectile according to any one of the claims of claim 23, and projecting the selected sub-projectile to A predetermined type of sub-projectile is formed in and adjacent to the predetermined path of the missile. A method for - carrying a self-"grabbing force, comprising: a step: placing the attack force; shooting in the vicinity of the attacking position of the attacking force - according to the application for the patent scope a projectile; and a projectile, a smoker, and a selected sub-projectile to form a predetermined type of sub-projectile in and adjacent to the determined position of the attack, the application for the patent scope of force 16. A method for repelling an infantry, comprising the steps of: determining a position of the infantry; and ejecting at least one of the ejections according to any one of claims 1 to 13 in the vicinity of the determined position of the infantry And selecting a sub-projectile in a predetermined position in and adjacent to the determined position of the infantry to form a predetermined type of sub-projectile. 10 15 20 17. A method for forming an airborne image, comprising the steps of: Emitting a projectile according to any one of claims 1-3 to the air; and ejecting a selected sub-projectile including an image formation to form a predetermined type of image formation in the air 18·- A method for firefighting, comprising the following steps: (4) the position of the fire field; at least one of the determined positions in the fire field is shot according to the patent application (4)! a selected sub-projectile to form a pre-form H-type projectile in and adjacent to the determined position of the fire field; and a fire-reducing agent is dispersed from the shot (four) projectiles. 'External gas, explosion method, including the following steps•• Select the location of the fuel-gas explosion where the cloud is located, and in the vicinity of the required position of the fuel-gas explosion, according to the application patent (5) The ejection (four) body of any one of items 1 to 13 emits a human-projectile containing a fuel-selected raft to form a sub-projectile of a private mountain ridge type; the sub-projectiles ejected from the blasting Shake 'shooting selected human bombs containing detonators to form a sub-projectile of a predetermined type; detonating the 29 1282402 pick-up, patent-pending detonators to produce a fuel-air detonation. to The method of opening a payload includes the steps of: selecting a desired position for transporting one of the payloads; and launching at least one of the positions required by the payload in the vicinity of the patent application range from item 13 to item 13 a projectile; a sub-projectile containing the selected one of the payloads - to form a predetermined type of sub-projectile; and the sub-projectiles ejected from the objects to disperse the payload. Defending a defense system for a designated area, the defense system includes: a monitor to the v, which is used to monitor the designated area to detect any area in which a new object appears in the _; defensive installation i, which can be weakened Now the side specifies the area + any invaders, where the defensive device includes - a weapon capable of projecting the projectile, wherein the projectile comprises: - a barrel of an array of radioactive configurations from the centroid of the projectile a tube, a core assembly, each of which has a plurality of scorpions, and or sub-projectiles axially disposed in a bobbin, and the sub-ejector system is used for ordering from the bobbin Propellant: The propellant is coupled to the separation of the projectile, and the bobbin assembly of the array can be selectively ejected from the selected bobbin - a hobo-human projectile, whereby the projectile can be diffused - a predetermined pattern a sub-projectile; and a t-device, which provides a U between the monitor and the defense device to selectively activate the defensive device, and transmits a weakened attack 30 1282402 to the patented range. District. 22. The defense system of claim 21, wherein the monitor comprises one or more current sensors disposed in the designated area or a remote sensing device that is not remote from the designated area. 5 23. The defense system of claim 21 or 22, wherein the monitoring device provides a visual display of one of the designated zones monitored, whereby the manual control device can be activated as needed to manually control the weapon. 24. A defense system according to claim 21, wherein a plurality of subprojectiles are fired simultaneously from a plurality of one bobbin tubes or from a single bobbin. 25. The defensive system of claim 24, wherein an electrical outgoing signal on one of the external circuits of the bobbin is carried. 26. The defense system of claim 24, wherein an electrical ejection signal is carried over the 15th projectile. 27. The defense system of claim 26, wherein the secondary ejection systems are clamped on top of each other to continue an electrical circuit through the bobbin. 28. A defense system as claimed in claim 26, wherein the secondary projectiles abut each other to make electrical contact. 20 29. The defense system of claim 24, wherein each of the sub-projectiles carries a control circuit. 30. The defense system of claim 21, wherein the array of bobbin assemblies includes a bobbin disposed adjacent one end of the projectile to effect a change in attitude of the projectile. 31 1282402 pp., pp. 31. The defense system of claim 21, wherein the bobbin assembly of the array includes a bobbin 32 disposed laterally to displace the projectile in the middle. The defense system of clause 21, wherein the cartridge 5 tube assembly of each array is capable of ejecting the projectile once in a direction having a longitudinal component to thereby increase the kinetic energy of the projectile. 33. The defensive system of claim 21, wherein the array of bobbin assemblies can eject a projectile in a direction having a component in a direction that is tangent to the longitudinal axis of the projectile, thereby transmitting or changing 10 The projectile rotates about its longitudinal axis. 34. As claimed in claim 21, wherein at least a portion of the bobbin assemblies can eject a secondary projectile such as a wing across the surface of the flight to induce further steering effects on the projectile. . 35. The defensive system of claim 21, wherein at least a portion of the 15 1 hex tube assembly extends through the airfoil surface to exit in both directions. 36. The defense system of claim 21, wherein a separate array or opposing array of bobbin assemblies is provided to control rotation of the projectile about the longitudinal axis of the projectile. 37. The defense system of claim 36, wherein the array of the arrays comprises a pair of bobbin assemblies for simultaneous ejection to change only the rotation about the longitudinal axis of the projectile. . 38. The defense system of claim 21, wherein the sub-projectiles are fired from the selected business officer assembly to provide the energy needed to change the attitude and performance of the projectiles. 32 1282402 Pickup, Patent Application 39 - A method for hiding the launch position of a ejector launcher, the method comprising the steps of: 5 10 15 The same pipe assembly discharges at least one projectile having a bobbin assembly a bobbin, a plurality of projectiles axially disposed in the bobbin for operating a 4-block engagement of the bore of the bobbin, and a separation for advancing the respective projectiles through the nozzle of the bobbin (b) when the at least one projectile is in flight, ejecting at least one projectile from the steering propulsion assembly of one of the arrays, each steering propulsion assembly having an axial configuration in the steering propulsion bobbin a plurality of individual projectiles coupled to a secondary separation propellant for sequentially advancing the secondary projectiles from the steering propulsion cylinder; wherein (c) the array of steering propulsion bobbin assemblies The secondary projectiles can be selectively ejected from the selected steering propulsion bobbin, thereby utilizing the reaction forces generated by the firing of the sub-elastics to accelerate the projectile. 33
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