1268891 玖、發明說明： 【發日月所屬之技術領域】 發明領域 本發明係有關於載運式武器平台及其製造方法。本發 5明係特別有關於，但非專指為飛行载具的構造。 【先前技術】 背景技術之說明 武器系統典型係以分開且獨立的構件來被裝配於既有 的載運平台上，雖然在許多情況下會與該載具的其它機械 10和電子系統功能性地整合。該等武器系統的質量通常在移 動平台的没什以及發射的動力作用之容許度等皆為重要的 考量因素，例如當消耗彈藥時其後座力與質量分佈的變化 等。武器質量之分佈及其發射動力作用會直接影響到該載 具的功能特性。 b 在小型載具的情況下，可用武器系統的選擇可能會想 當艾限或甚至被排除。但是，在許多情況下若能有效地武 裝一載具而不致太大地損及其性能將會是很有利的。許多 現有的載具，特別是那些小型的健發行器或調查機器人 等，一般皆移動杈，在較低高度操作，且通常並無武裝， 20因此易遭小型武器攻擊而損壞。 在少數個別的例子中，曾見有將飛彈發射管整合於大 型飛行器的結構者’如Ν〇·4040334美國專利（Smethers，Jr) 係設於廣體重型喷射機中，及如在英國專利ν〇·212〇991 (kjolseth&Mowill)係裝在地面效應及水陸兩用機艇中。但 1268891 是，其顯然不能針對例如本發明所屬之該類小型載具來提 供飛彈發射能力。 【發明内容】 本發明之目的 5 因此，乃有需提供一種載運式武器平台及武器平台的 構建方法，來解決新載具設計的缺失及/或具有傳統武器系 統之既存載具的缺失，特別是供使用於敵對環境中的小型 遙控載具者。 本發明之揭露 10 廣義而言，本發明係為一種小型武器平台而包含有多 數的鎗管總成，其中該等鎗管總成會形成該武器平台的武 器和結構部件。較好是，該等鎗管總成之各鎗管係由輕質 的筒管所製成，最好是由複合材料例如工程塑膠或碳纖維 複合物等所構成。若有需要，該等筒管亦可組成一共同外 15 壁的多孔結構。較好是，該等鎗管總成係被設成能同時由 該鎗管的兩端來發射投射物，而得儘量減少不良的後座力 作用。 在一較佳實施例中，該武器平台包含一載具’其中該 等鎗管總成會形成該載具的結構骨架，或至少其結構骨架 20 的一部份。若為一飛行載具，例如固定翼或旋轉翼的飛行 器，則該等鎗管總成乃可形成該發行器之機身及/或機翼的 骨架及/或翼樑。 本發明的另一形式係為一種構建一武器平台的方法， 該方法包含以一武器之多數的鎗管總成來形成該武器平台 1268891 之一或多數結構物的步驟。較好是，該等鎗管總成係使其 各鎗管能以相反方向來設置，而在開火時能儘量減少不良 的後座力作用。 本發明具有發明人前在No. PCT/AU94/00124及No· 5 PCT/AU96/00459等國際專利申請案中所述之該類鎗管總 成的特定用途。該等鎗管總成包含一鎗管，多數的投射物 軸向地列設在該餘管中，而與該鎗管之膛孔可操作地密封 塞裝，且用來推送各投射物之個別的發射藥劑會依序地佈 滿該鎗管的内膛。 1〇 該投射物的整體造型，包括投射核心及可擴張的套筒 係可呈習知的矢狀造型，或呈球狀，或任何其它合宜的形 狀。該投射物亦可包含鰭片等且最好岔開而在矢狀物由一 光滑膛孔的鎗管射出時得能產生穩定的自旋。 该等投射藥劑係裝在推進物空間内，並可形成固塊而 is有助於該等餘管總成的裝填。《者該發射藥劑亦可被封 裝，並可包含一埋入的雷管具有外部接觸裝置，而可接觸 ^知f所附又之一預定的電觸點。例如該雷管可具有一彈 C觸點’其可回而使封裝的藥包缺人麟管中，並在 與該鎗管之-孔隙對準時即會彈入該孔隙内，而來與所對 20應的鎗管觸點操作地接觸。若有需要其外殼亦可被消耗， 或化學性地協助該藥劑燃燒。而且堆疊連接或分開封裝的 藥包與投㈣之組合總《可被提供以便讀管的再裝 填。 該鎗管可為非金屬製品，且其膛孔可含有凹槽等以完 1268891 全或部份地容裝點火裝置。在此構造中，該鎗管可裝有電 導體俾便於該等控制裝置與點火裝置之間的電導通。此構 造係能供使用於可拋棄式鎗管總成，其具有有限的發射使 用時間，因此該等點火裝置及控制導線等乃可與該餘管一 5 體地製成。 一艙管總成或亦可在其4倉管中包含點火孔隙，且其點 火裝置係設在該鎗管外部而鄰近該等孔隙。其鎗管亦可被 一非金屬外筒所包圍，該外筒可含有凹槽來容納點火裝 置。該外筒亦可容裝電導體以便於控制裝置與點火裝置之 10間的電導通。該外筒可被製成疊層的塑膠筒其内含有該點 火裝置的印刷電路層。 用來連績點火一餘管總成之發射藥劑的電發火操作最 好包含以下步驟：將一點火信號送經該等串疊的投射物來 將前頭發射藥劑點火’並令該前頭發射藥劑的點火可使下 15 一發射藥劑備妥以供下個點火信號來啟動。較好是所有的 發射藥劑皆朝一膛管的内端裝填，而藉設在正常關閉的電 觸點之間的各絕緣保險片之插入來避免發火。 該投射物的發火係可藉電來達成，或其點火亦可利用 傳統的發射銷式方法，例如利用一中央發射雷管來點火最 20外側的投射物，及控制順序地點火來造成各輪發射藥劑的 連續發火。此係可藉受控的朝後宣洩之燃燒氣體，或延伸 貫穿該等投射物或該膛管的引線柱之受控的燃燒而來達 成。 該點火的另-種方式係電子式控制，即將各發射藥劑 1268891 配a又雷官而藉個別的點火信號來擊發。例如在該等事疊之 發射藥劑中的雷管乃可續接來增加點火所需的脈衝寬度， 且電子&制器施選擇性地送出增加脈衝寬度的點火脈衝， 而以所擇的時間順序來連續地點火該等發射藥劑。但最 5好該等發射藥劑係以一設定脈衝寬度的信號來點火，且前 一發射藥劑的燃燒將會使下一發射藥劑備妥以供下一脈衝 來啟動。 較好在該等實施例中所有的發射藥劑皆由一膛管的内 端開始裝填，且藉設在正常關閉的電觸點間之各絕緣保險 10片的插入而來避免發火；該等保險片係被設成可在一適當 的擊發信號送入時能夠點燃而使該等觸點關閉，遂令該等 絕緣保險片開放而使一對應的前頭發射藥劑被點火。 舉例而言，有多數的投射物可被同時發射，或以很快 的順序來連接發射，或者回應遙控的電點火信號而來發 15 射。在該等設計中，該電信號係可該鎗管外部來傳送，或 亦可經由串疊的投射物來傳送，其可互相串接並透過該鍮 管來延續該電路，或互相以電觸點抵接而來傳送。該等投 射物係可帶有控制電路，或其亦能與該鎗管來形成一電路。 圖式簡單說明 20 為使本發明能更容易瞭解並付諸實施，現將參照示出 本發明之較佳實施例的各所附各圖式來說明，其中·· 第1圖為本發明一實施例鎗管總成的截面側視圖； 第2圖為用來形成一載運式武器平台之結構骨架的多 數鎗管總成之立體圖； 1268891 第3圖為—使用第2圖之結構骨架的飛行器之立體圖； 第4圖為—侧視圖示出第3圖之飛行器之4倉管總成之列 設方式； 第5圖為第4圖之飛行器的前視圖； 5 第6圖為第4圖之飛行器的另一侧視圖，示出該等縱向 餘管總成的操作用途； 第7圖為第4圖之飛行器的又一側視圖，示出與_較大 的習知飛機之比例；及 第8圖示出第4圖之飛行器利用橫向鎗管總成來對付一 10目標的操作示意圖。 【實施方式】 本發明之實施例的說明 第1圖示出一鎗管總成10包含一鎗管U具有相反的鎗 口端12、13 ’而該鎗管中裝有多數的投射物14及配設的發 15射藥劑15等。本實施例的鎗管係由一輕質的碳纖維複合材 料所製成。該鎗管11係被裝填成使各投射物14由一共用的 後膛壁16開始軸向地堆疊在該鎗管内，故若有需要該等設 射物將可由任-或兩個餘口端來發射。該等發射劑15係被 α又成可藉電|置(未不出）來選擇性地點火，而使各投射物能 Μ由該餘^中以預定的發射速率來連續地發射。最好用來 H亥等彳又射物的裝置係依據本發明之發明人在先前專利 申請案中所述的内容來實施者。 武器平面的結構骨架20係示於第2圖中，乃由第讀 所示之多個餘管總成1〇所形成。該骨架2〇包含一組兩支橫 10 1268891 向延伸的鎗營總成21，及一組四支縱向延伸的鎗管總成22 等。各組鎗管總成21、22之個別的餘管^係可依用途所需 而永久或可釋卸地固接在一起。在變化的設計中，應可瞭 解一武器平台的結構骨架亦可包含另種僅具有單一鎗口端 5的鎗管總成。又，該等鎗管總成亦可為不同的尺寸，以容 裝不同類型的彈藥及/或配合結構需要。 第2圖的結構骨架20係特別為一第3圖所示的飛行器30 所設計者。詳言之，該發行器3〇係為一種無人式遙控小型 戰鬥飛行載具(SCAV)。在該發行器的結構設計中，橫向延 10 伸的鎗管組21會形成該飛行器之機翼31的翼樑，而縱向延 伸的鎗管組22則形成支撐機身32的骨架。該飛行器3〇亦包 含一機尾33及一對水平穩定翼34,皆係被該機身骨架所支 撐。此結構設計能有效地將一多管鎗系統整合於該載具 中，而僅增加有限的載具重量。 15 該飛行器30的進一步細節，在一實施例中具有大約9 呎(2.75米）的長度，及大約10呎(3.0米）的翼幅，而被示於第 4、5圖中。構成其翼樑和機身骨架的餘管總成10總共裝有 780發0.32(8mm)(|)的子彈，其皆可被個別地發射。該等子彈 的總重量估計約在12.5磅(5.675公斤）左右，而該等發射藥劑 20 約1.1磅(0.5公斤），且該等鎗管僅增加2磅(0·9公斤），當由第 4圖視之，有些子彈會向前41發射，而有些會向後42發射’ 而其它的子彈可由該飛行器之右般及左般翼端43、44的艙 管出口端來側向地發射，如第5圖所示。 在/操作模式中，該飛行器30能以無後座力作用之每 1268891 分鐘180000發(rpm)的速率來發射270發子彈至一目標。其 後座力可藉由該鎗管總成10的向前及向後鎗口端41和42同 時地發射投射物65、64等而來有效地消除，如第6圖所示。 此模式能僅在0.01秒内將4·3磅（1·9公斤）的投射物送至一目 5 標處。一偵察照相機61，於本實施例中係被裝設在該飛行 器30的機尾33上，而可用檢測被攻擊的目標。若有需要， 則由後鎗口端42發射的彈頭64等亦可為非毀滅性的，而來 提供另外的載物例如誘餌或暫時性的刺激物等。 在另一操作模式中，該等縱向搶管總成亦可僅由其後 10 鎗口端62、63來發射，而使後座力作用形成對其空速的正 向推力。 所推薦的SCAV 30係被示於第7圖中來對比於一習知 的商用飛機，即波音737客機70的尺寸比例。 又另一種操作模式係被示於第8圖中，其中該飛行器30 15 係以一執道飛行路徑81來迴繞在一目標80上方。週期性 地，或最好是可隨意地，子彈能由具有翼端鎗口 67的橫向 餘管組來射向該目標80。此模式可造成不確定性及/或騷擾 而來消減敵軍的士氣。或者，若有狀況時，將能以60000rpm 的高速率來發射120發子彈。此等較高的速率能將19磅 2〇 (0.836公斤）的投射物在〇·ΐ秒内投射於一目標上。 本發明之上述實施例的優點係可解決移動較慢、飛行 較低的飛行器易受輕武器系統攻擊的問題，而能增加操作 使用時的可存活率，亦可經由任意的多方向開火來提供騷 擾或消減敵軍士氣的能力。 12 1268891 在使用時，該SCAV可由一母飛行器在任何所需高度， 包括一非常高的高度來投射。在一用來攔截敵人飛彈的高 空佈署中，例如其可由一母機在70000呎(21350米）的高空來 投射，該飛行器30能由一緩慢燃燒的固體燃料火箭66(見第 6圖）來推進。該飛行器起先可藉該母機上之一目標獲取及 追踪系統來引導，嗣快速降低至較低高度再以一内部的終 端搜尋器來捕捉該特定目標，例如一巡戈飛彈等。 應可瞭解本實施例的飛行器係能發射相對於其尺寸不 成比例的高動力衝擊物，並且具有沿相反方向以可變發射 10 速率（慢或極快）來同時發射的能力，而得平衡後座力，否則 該等後座力可能會損及該飛行器，並可能會擾亂該飛行器 的飛行路徑、高度或空速。 應可瞭解以上所述僅為本發明的舉例說明，而所有專 業人士顯而易知的修正變化，應視為含括於如以下申請專 15利範圍所界定之本發明的廣義範疇内。 【圖式簡單説明】 第1圖為本發明一實施例鎗管總成的截面側視圖； 第2圖為用來形成一載運式武器平台之結構骨架的多 數餘營總成之立體圖； 20 第3圖為一使用第2圖之結構骨架的飛行器之立體圖； 第4圖為一側視圖示出第3圖之飛行器之鎗管總成之列 設方式； 第5圖為第4圖之飛行器的前視圖； 第6圖為第4圖之飛行器的另一側視圖，示出該等縱向 13 1268891 鎗管總成的操作用途； 第7圖為第4圖之飛行器的又一側視圖，示出與一較大 的習知飛機之比例；及 第8圖示出第4圖之飛行器利用橫向鎗管總成來對付一 5 目標的操作示意圖。 【圖式之主要元件代表符號表】 10,21，22…鎗管總成 41…前射子彈 11…鎗管 42···後射子彈 12，13…鎗口端 43…右舷翼端 14,64,65…投射物 44···左舷翼端 15…發射藥劑 61…偵察照相機 16…後腫壁 62,63…後鎗口端 20…結構骨架 66…火箭 30…飛行器 67···翼端4倉口 31…機翼 70···波音737客機 32…機身 80···目標 33…機尾 81…繞行路徑 34…水平穩定翼1268891 发明, INSTRUCTION DESCRIPTION: TECHNICAL FIELD OF THE INVENTION The present invention relates to a carrier weapon platform and a method of manufacturing the same. This section is particularly relevant, but does not specifically refer to the construction of a flying vehicle. BACKGROUND OF THE INVENTION A weapon system is typically assembled on a separate carrier platform with separate and independent components, although in many cases it will be functionally integrated with other mechanical 10 and electronic systems of the carrier. . The quality of these weapon systems is often an important consideration in the absence of the mobile platform and the tolerance of the dynamics of the launch, such as changes in the recoil and mass distribution when the ammunition is consumed. The distribution of the quality of the weapon and its launching dynamics directly affect the functional characteristics of the vehicle. b In the case of small vehicles, the choice of available weapon systems may be desirable or even excluded. However, in many cases it would be advantageous to be able to effectively mount a carrier without causing too much damage to its performance. Many of the existing vehicles, especially those with small health distributors or survey robots, are generally mobile, operate at lower altitudes, and are usually unarmed, so they are vulnerable to small weapon attacks. In a few individual cases, there have been structural structures that integrate missile launch tubes into large aircraft. 'US Patent No. 4040334 (Smethers, Jr) is based on a wide-body type jet, and as in the UK patent ν 〇·212〇991 (kjolseth&Mowill) is installed in ground effect and amphibious boats. However, 1268891 is that it is obviously not possible to provide missile launch capability for such small vehicles as the present invention. SUMMARY OF THE INVENTION Object 5 of the present invention Accordingly, there is a need to provide a method for constructing a carrier weapon platform and a weapon platform to address the lack of new vehicle design and/or the absence of existing vehicles with conventional weapon systems, particularly It is a small remote control vehicle for use in hostile environments. SUMMARY OF THE INVENTION In a broad sense, the present invention is a small weapon platform that includes a plurality of barrel assemblies that form the weapons and structural components of the weapon platform. Preferably, the barrels of the barrel assemblies are made of a lightweight bobbin, preferably of a composite material such as an engineering plastic or a carbon fiber composite. If desired, the tubes can also form a common outer wall 15 porous structure. Preferably, the barrel assembly is configured to simultaneously emit projectiles from both ends of the barrel, thereby minimizing undesirable recoil forces. In a preferred embodiment, the weapon platform includes a carrier 'where the barrel assembly forms a structural skeleton of the carrier, or at least a portion of its structural skeleton 20. In the case of a flying vehicle, such as a fixed-wing or rotary-wing aircraft, the barrel assemblies may form the skeleton and/or spar of the fuselage and/or wing of the issuer. Another form of the invention is a method of constructing a weapon platform that includes the step of forming one or a plurality of structures of the weapon platform 1268891 with a majority of the barrel assembly of a weapon. Preferably, the barrel assembly allows each barrel to be placed in the opposite direction and minimizes undesirable recoil forces during firing. The present invention has the specific use of such a barrel assembly as described in the International Patent Application No. PCT/AU94/00124 and No. 5 PCT/AU96/00459. The barrel assembly includes a barrel, a plurality of projections are axially disposed in the remaining tube, and the bore of the barrel is operatively sealed and used to push each of the projections The firing agent will sequentially fill the inner tube of the barrel. 1〇 The overall shape of the projectile, including the projection core and the expandable sleeve, may be in the form of a conventional sagittal shape, or in the form of a sphere, or any other suitable shape. The projectile may also comprise fins or the like and is preferably split to produce a stable spin when the sagittal is ejected from a smooth bored barrel. The projection medicaments are housed in the propellant space and may form a solid block to facilitate the loading of the remaining tube assemblies. The propellant may also be packaged and may include a buried detonator having an external contact means for contacting a predetermined electrical contact attached to the other. For example, the detonator can have a resilient C-contact 'which can be used to make the packaged drug pack lacking in the tube, and will blast into the aperture when aligned with the aperture of the barrel, and 20 should be in contact with the barrel contact. The outer casing can also be consumed if necessary, or chemically assisted in burning the agent. Moreover, the combination of the stacked or separately packaged drug pack and the cast (4) can be provided for refilling of the tube. The barrel may be a non-metallic article, and the bore may include a recess or the like to accommodate the ignition device in whole or in part. In this configuration, the barrel can be provided with an electrical conductor to facilitate electrical conduction between the control device and the ignition device. The construction system can be used in a disposable barrel assembly which has a limited launch time, so that the ignition device and control wires and the like can be made in one piece with the remaining tube. A tank assembly may also include an ignition aperture in its 4-bar tube and its igniter is external to the barrel adjacent to the aperture. The barrel may also be surrounded by a non-metallic outer cylinder that may contain recesses to accommodate the ignition device. The outer cylinder can also house electrical conductors to facilitate electrical conduction between the control unit and the ignition unit 10. The outer cylinder can be formed into a laminated plastic cylinder containing the printed circuit layer of the ignition device. Preferably, the electric ignition operation for igniting the firing agent of the remaining tube assembly includes the steps of: passing an ignition signal through the series of projectiles to ignite the front emitting agent and causing the front to emit the medicament Ignition allows the next 15 firing agent to be ready for the next ignition signal to start. Preferably, all of the propellant charges are loaded toward the inner end of a manifold, and the insertion of the insulating fuses between the normally closed electrical contacts avoids ignition. The firing of the projectile can be achieved by electricity, or its ignition can also use conventional launch pin methods, such as using a central launch detonator to ignite the projectile on the outermost 20, and controlling the sequential ignition to cause each launch. Continuous igniting of the medicament. This can be achieved by controlled controlled combustion of the gas, or by controlled combustion of the lead through the projectile or the manifold. Another way of igniting is electronic control, that is, each firing agent 1268891 is equipped with a separate officer and fired by an individual ignition signal. For example, the detonators in the stack of propellant charges can be continued to increase the pulse width required for ignition, and the electronic &s device selectively delivers an ignition pulse of increased pulse width in a selected chronological order. The ignition agents are ignited continuously. However, at best, the firing agents are ignited with a signal of a set pulse width, and the combustion of the previous firing agent will cause the next firing agent to be ready for the next pulse to start. Preferably, in all of the embodiments, all of the propellant charges are loaded from the inner end of a manifold, and the insertion of the insulating sheets 10 between the normally closed electrical contacts is avoided to avoid ignition; The sheet is configured to ignite when a suitable firing signal is fed to close the contacts, and to cause the insulating sheets to open to cause a corresponding front emitting agent to be ignited. For example, a majority of the projectiles can be fired simultaneously, or connected in a quick sequence, or in response to a remotely controlled electrical ignition signal. In such designs, the electrical signal may be transmitted externally to the barrel or may be transmitted via a series of projectiles that may be connected in series and through the manifold to continue the circuit or to each other. The point is abutted and transmitted. The projections can be provided with control circuitry or they can also form a circuit with the barrel. BRIEF DESCRIPTION OF THE DRAWINGS In order to make the present invention easier to understand and implement, reference will now be made to the accompanying drawings in which A cross-sectional side view of a barrel assembly; Figure 2 is a perspective view of a majority of the barrel assembly used to form a structural skeleton of a carrier-type weapon platform; 1268891 Figure 3 is an illustration of an aircraft using the structural skeleton of Figure 2 Fig. 4 is a side view showing the arrangement of the 4 bin assembly of the aircraft of Fig. 3; Fig. 5 is a front view of the aircraft of Fig. 4; 5 Fig. 6 is the Fig. 4 Another side view of the aircraft showing the operational use of the longitudinal residual pipe assemblies; Figure 7 is a further side view of the aircraft of Figure 4, showing the ratio to the larger conventional aircraft; 8 is a schematic view showing the operation of the aircraft of FIG. 4 using a transverse barrel assembly to deal with a target of 10. [Embodiment] Description of Embodiments of the Invention FIG. 1 shows a barrel assembly 10 including a barrel U having opposite muzzle ends 12, 13' and a plurality of projections 14 contained in the barrel and The hair spray 15 and the like are provided. The barrel of this embodiment is made of a lightweight carbon fiber composite material. The barrel 11 is loaded such that each of the projectiles 14 is axially stacked within the barrel from a common rear sill wall 16, so that if necessary, the items will be available from either or both of the remaining ends. Come to launch. The propellants 15 are selectively ignited by the volts, so that each of the projectiles can be continuously emitted from the remainder at a predetermined emission rate. Preferably, the apparatus for the use of the apparatus and the like is based on the contents described in the prior patent application by the inventors of the present invention. The structural skeleton 20 of the weapon plane is shown in Fig. 2 and is formed by a plurality of remaining tube assemblies shown in the first reading. The skeleton 2〇 includes a set of two horizontally extending 1 2268891 gun-barrel assemblies 21, and a set of four longitudinally extending barrel assemblies 22 and the like. The individual remaining tubes of each of the barrel assemblies 21, 22 can be permanently or releasably secured together as needed for the application. In a changing design, it should be understood that the structural skeleton of a weapon platform may also include another barrel assembly having only a single muzzle end 5. Moreover, the barrel assemblies can be of different sizes to accommodate different types of ammunition and/or mating structures. The structural skeleton 20 of Fig. 2 is specifically designed for the aircraft 30 shown in Fig. 3. In particular, the issuer 3 is an unmanned remote small combat flight vehicle (SCAV). In the structural design of the dispenser, the laterally extending barrel group 21 forms the spar of the wing 31 of the aircraft, and the longitudinally extending barrel group 22 forms the skeleton supporting the fuselage 32. The aircraft 3A also includes a tail 33 and a pair of horizontal stabilizers 34 supported by the fuselage frame. This structural design effectively integrates a multi-barrel gun system into the carrier, while adding only a limited carrier weight. 15 Further details of the aircraft 30, in one embodiment having a length of about 9 呎 (2.75 meters) and a wing width of about 10 inches (3.0 meters), are shown in Figures 4 and 5. The remaining tube assembly 10, which constitutes its spar and fuselage skeleton, is loaded with a total of 780 rounds of 0.32 (8 mm) (|) bullets, all of which can be individually fired. The total weight of the bullets is estimated to be around 12.5 pounds (5.675 kilograms), and the launching agent 20 is about 1.1 pounds (0.5 kilograms), and the barrels only add 2 pounds (0. 9 kilograms). As shown in Fig. 4, some bullets will be launched forward 41 and some will be launched backwards 42 while other bullets can be launched laterally by the right end of the aircraft and the outlet end of the left wing end 43, 44. Figure 5 shows. In the / mode of operation, the aircraft 30 is capable of transmitting 270 rounds of bullets to a target at a rate of 180,000 rpm per 1268891 minutes without recoil. The recoil can be effectively eliminated by simultaneously projecting the projectiles 65, 64, etc. from the forward and rearward muzzle ends 41 and 42 of the barrel assembly 10, as shown in Fig. 6. This mode delivers 4·3 lb (1·9 kg) of projectile to the 1st target in only 0.01 seconds. A reconnaissance camera 61, which in this embodiment is mounted on the tail 33 of the aircraft 30, can be used to detect the target being attacked. If desired, the bullets 64 and the like emitted by the rear muzzle end 42 may also be non-destructive to provide additional loads such as baits or temporary irritants. In another mode of operation, the longitudinal tube assemblies can also be fired only by the rear 10 muzzle ends 62, 63, and the recoil forces act to form a positive thrust for their airspeed. The recommended SCAV 30 series is shown in Figure 7 in comparison to a conventional commercial aircraft, i.e., the size ratio of the Boeing 737 aircraft 70. Yet another mode of operation is shown in Figure 8, in which the aircraft 30 15 is wound back and forth over a target 80 with an obedience flight path 81. Periodically, or preferably, optionally, the bullet can be directed toward the target 80 by a lateral residual tube set having a wing end muzzle 67. This mode can cause uncertainty and/or harassment to reduce enemy morale. Or, if there is a condition, it will be able to fire 120 rounds at a high rate of 60,000 rpm. These higher rates are capable of projecting 19 pounds (2,360 kilograms) of projectile onto a target in 〇·ΐ seconds. The above embodiments of the present invention have the advantages of solving the problem that a slow moving, low flying aircraft is vulnerable to attack by a light weapon system, and can increase the viability of the operation, and can also provide harassment through any multi-directional fire. Or the ability to reduce enemy morale. 12 1268891 In use, the SCAV can be projected by a parent aircraft at any desired height, including a very high altitude. In a high-altitude deployment used to intercept enemy missiles, for example, it can be projected by a parent aircraft at an altitude of 70,000 feet (21,350 meters), which can be powered by a slow-burning solid fuel rocket 66 (see Figure 6). Advance. The aircraft can be initially guided by a target acquisition and tracking system on the parent machine, quickly lowered to a lower altitude and then captured by an internal terminal searcher, such as a cruise missile. It will be appreciated that the aircraft system of the present embodiment is capable of emitting a high power impact that is disproportionate to its size and has the ability to simultaneously transmit at a variable emission rate of 10 (slow or very fast) in the opposite direction, and after balancing Seat force, otherwise the recoil may damage the aircraft and may disrupt the flight path, altitude or airspeed of the aircraft. It is to be understood that the above description is only illustrative of the invention, and that modifications and variations of the invention are intended to be included within the broad scope of the invention as defined by the following claims. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a cross-sectional side view of a barrel assembly of an embodiment of the present invention; FIG. 2 is a perspective view of a majority of the remaining assembly for forming a structural skeleton of a carrier-type weapon platform; 3 is a perspective view of an aircraft using the structural skeleton of FIG. 2; FIG. 4 is a side view showing the arrangement of the barrel assembly of the aircraft of FIG. 3; FIG. 5 is an aircraft of FIG. Figure 6 is another side view of the aircraft of Figure 4 showing the operational use of the longitudinal 13 1268891 barrel assembly; Figure 7 is a further side view of the aircraft of Figure 4, A ratio to a larger conventional aircraft; and Figure 8 shows a schematic diagram of the operation of the aircraft of Figure 4 using a transverse barrel assembly to deal with a 5 target. [The main components of the diagram represent the symbol table] 10,21,22...the barrel assembly 41...the front shot bullet 11...the barrel 42···the rear shot bullet 12,13...the muzzle end 43...the starboard wing end 14, 64, 65... Projectile 44···Port side wing end 15... Launching agent 61... Reconnaissance camera 16... After swollen wall 62, 63... Rear muzzle end 20... Structural skeleton 66... Rocket 30... Aircraft 67···wing end 4 silo 31...wing 70···Boeing 737 aircraft 32...body 80···target 33...tail 81...circle path 34...horizontal stabilizer
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