『每日軍武』- P-3 獵戶座式(Orion)長程反潛巡邏機

克里斯Chris

P-3 Orion
P-3 獵戶座式長程反潛巡邏機



原文:
The P-3C is a land-based, long range anti-submarine warfare (ASW) patrol aircraft. It has advanced submarine detection sensors such as directional frequency and ranging (DIFAR) sonobuoys and magnetic anomaly detection (MAD) equipment. The avionics system is integrated by a general purpose digital computer that supports all of the tactical displays, monitors and automatically launches ordnance and provides flight information to the pilots. In addition, the system coordinates navigation information and accepts sensor data inputs for tactical display and storage.

The P-3C can either operate alone or supporting many different customers including the carrier battlegroup and amphibious readiness group. The aircraft can carry a variety of weapons internally and on wing pylons, such as the Harpoon anti-surfacemissile, the MK-50 torpedo and the MK-60 mine. Each Maritime Patrol Aviation (MPA) squadron has nine aircraft and is manned by approximately 60 officers and 250 enlisted personnel. Each 11-person crew includes both officer and enlisted personnel.

The MPA squadrons deploys to sites outside the United States for approximately six months, and generally spends one year training at home between deployments. In February 1959, the Navy awarded Lockheed a contract to develop a replacement for the aging P-2 Neptune. The P-3V Orion entered the inventory in July 1962, and over 30 years later it remains the Navy's sole land-based antisubmarine warfare aircraft.

It has gone through one designation change (P-3V to P-3) and three major models: P-3A, P-3B, and P-3C, the latter being the only one now in active service.


The last Navy P-3 came off the production line at the Lockheed plant in April 1990. Since its introduction in 1969, the P-3C has undergone a series of configuration changes to implement improvements in various mission and aircraft systems through updates to the aircraft.

These changes have usually been implemented in blocks referred to as "Updates."Update I, introduced in 1975, incorporated new data processing avionics and software, whileUpdate II in 1977 featured an infrared detection system, a sonobuoy reference system, the Harpoon antiship missile and a 28-channel magnetic tape recorder/reproducer.

Technical Evaluation (TECHEVAL) forP-3C Update III Aircraft began in March 1981, and was completed in second quarter 1982. Force Warfare Test Directorate, Naval Air Warfare Center Aircraft Division (NAVAIRWARCENACDIV), at Patuxent River, Maryland, conducted the TECHEVAL.

Air Test and Evaluation Squadron One (VX-1) began Operational Test and Evaluation (OT&E) of the P-3C Update III Aircraft at NAVAIRWARCENACDIV Patuxent River in September 1981, and completed this phase of testing in January 1982. Provisional approval for service use was granted in July 1982. Approval for full production was received in January 1986 following Follow-on Operational Test and Evaluation (FOT&E). The Update III Program was enhanced by a Channel Expansion (CHEX) Program.

CHEX doubled the number of sonobuoy channels that can be processed and has been installed in all P-3C Update III Aircraft. The CHEX Program began in 1983 and the tested aircraft was delivered in April 1986. CHEX TECHEVAL was accomplished from March through June 1988. The P-3C Update III Aircraft is manned by an 11-man crew composed of five officers and six enlisted.

Enlisted crewmembers are selected from the following aviation ratings: Aviation Machinist's Mate (AD), Aviation Electrician's Mate (AE), Master Chief Aircraft Maintenanceman (AF), Senior Chief Aviation Structural Mechanic (AM), Aviation Structural Mechanic (Safety Equipment) (AME), Aviation Structural Mechanic (Hydraulics) (AMH), Aviation Structural Mechanic (Structures) (AMS), Aviation Electronics Technician (AT), and Aviation Warfare Systems Operator (AW).

The operational concept for the P-3C Update III and P-3C Update III AIP Aircraft remains the same as previous updates to the P-3C Aircraft, to provide tactical surveillance, reconnaissance, strike support, fleet support and warning, and monitoring of electromagnetic signals of interest for intelligence analysis. Patrol squadrons operate with nine aircraft from established Naval Air Stations (NASs) world wide.

The P-3C Update III and P-3C Update III AIP Aircraft continue the P-3C's capability of operating one or more aircraft from remote airfields with no organizational or intermediate support for short periods of time. The P-3C Update III was introduced into the fleet during early 1985, and Aircraft Initial Operating Capability (IOC) was achieved in 1986. The P-3C Update III Aircraft is in the Production, Fielding, Deployment, and Operational Support Phase of the Weapon System Acquisition Process.

The noteworthy additions and changes which comprised Update III, enhanced acoustic data processing capabilities and improved the sonobuoy communications suite. These changes included the Single Advanced Signal Processor System, Advanced Sonobuoy Communications Link Receiver, Adaptive Controlled Phased Array System, Electronic Support Measure (ESM) Set, Acoustic Test Signal Generator, CP-2044 Digital Data Computer, and changes to the Environmental Control System.

[ 本文最後由 jacklf2004 於 07-10-7 02:45 PM 編輯 ]

克里斯Chris

續:

The Harpoon Stand-Off Land Attack Missile (SLAM) launched from the P-3C Orion aircraft provides commanders with the ability to immediately deploy a long range responsive platform that can remain on-station for extended periods of time, retask targets in flight, and deliver up to four over-the-horizon precision weapons in minutes. The same aircraft can then remain on station and continue to target other platforms' missiles by the use of its Electro-Optical, Rapid Targeting System (RTS) and real time data link capabilities.


The AN/ALQ-158(V) Adaptive Controlled Phased Array System [ACPA] VHF sonobuoy receiving antenna system amplifies reception of sonobuoy signals.

The ACPA now consists of: Two AS-3153/ALQ-158(V) Blade Antennas are installed; only omni-directional reception is provided; AM-6878/ALQ-158(V) Radio Frequency Amplifier equipment receives and amplifies the signals sent from the blade antennas and passes these amplified signals on to the AN/ARR-78 ASCL receiver.


AN/ARR-78(V)1 Advanced Sonobuoy Communications Link [ASCL] Receiver contains 20 receiver modules, each capable of accepting RF operating channels 1-99 (those sonobuoy channels now in use and those being developed for future use). All 20 receiver modules may be tuned to any one of the sonobuoy operating frequencies. The ASCL consists of a Radio Receiver, Receiver Control/On-Top Position Indicator (OTPI), Control Indicator, and Receiver Indicator.


Two R-2033/ARR-78(V)1 Radio Receiver units receive acoustic data for the SASP. Each has four auxiliary function channels which allow the TACCO to monitor the sonobuoy audio channels, BT light off detection, and OTPI reception. The C-10127/ARR-78(V)1 Receiver Control unit provides manual control of the OTPI receiver only, permitting the pilot to select the OTPI receiver and tune it to any one of the 99 channels. The C-10126/ARR-78(V) Control Indicator is the primary manual control for the ASCL Set is the control indicator.


Each of the two units installed allows the operator to select and program any of the 20 receiver modules. Each of the two ID-2086/ARR-78(V)1 Receiver Indicator units simultaneously displays the status of all 20 receiver modules on a continuous basis. The AN/UYS-1(V) Single Advanced Signal Processor System [SASP] is a digital processor designed for the conditioning, analysis, processing, and display of acoustic signals.


The SASP System is comprised of two basic elements. The TS-4271/UYS-1(V)10 Analyzer Detecting Set, also called the AU, is installed with a primary function of processing acoustic signals through the use of a Spectrum Analyzer TS-4271/UYS-1(V). It is protected from power transients by a PP-7467/UYS-1(V) Power Interrupt Unit (PIU). The CP-1808/USQ-78(V) SASP Display Control Unit (DCU), contains a programmable, modularity expandable system containing two independent computer subsystems, a System Controller, and a Display Generator (DG) and is also protected by a PIU.


The DG also provides hardware interface to two Commandable Manual Entry Panels (CMEPs) C-11808/USQ-78(V), and two Multi-Purpose Displays (MPDs) IP-1423/ USQ-78(V).


The two manual entry panels provide the operator an interface to control system operating modes and MPD visual presentations. With the AN/ALQ-78A Countermeasures Set the existing Countermeasures Set (AN/ALQ-78) is modified by an ECP which improved both maintainability and performance. This ECP was first introduced in the P-3C Update II (ECP-955 for production aircraft and ECP-966 for retrofit aircraft).


The AN/ARS-5 Receiver-Converter Sonobuoy Reference System, a 99 Channel SRS, permits the continuous monitoring of a sonobuoy location from a stand-off position. The SRS provides "fly to" reference data to the CP-2044. It was fit into Lockheed I-9 aircraft serial 5812 Bureau Number 163005 and subsequent production aircraft and was retrofit into production P-3C Update III Aircraft.


The AN/ARC-187 Ultra High Frequency Radio Set provides for a satellite communications capability. The two installed AN/ARC-143 UHF Radios were replaced by two AN/ARC-187 UHF Radios with the incorporation of ECP-988. This ECP is applicable to all P-3C Update III Aircraft. The AN/ARC-187 was installed in the P-3C Update III production aircraft delivered in May 1988 and subsequent. Retrofit installation by Lockheed Martin field teams has been completed.

The CP-2044 Digital Data Computeris a single cabinet airborne computer equipped with high-throughput microprocessors, increased memory capacity, a dual bus system, and built-in diagnostics. Improvements to the CP-901 have resulted in a design which dramatically increases performance while maintaining the CP-901 footprint and significantly reduces weight and power requirements.


Main shared memory is increased to one megaword, with an additional one megaword available for memory growth. In addition, each of the processor modules contain one megaword of local memory. These design improvements and the use of Ada language will accommodate future processing requirements and keep the system viable throughout the 1990s. Performance improvements are made possible by 15 new six by nine inch printed circuit cards.


The CP-2044 features three Motorola 68030 microprocessors and card slots for four additional processors. Functions of the previously external AN/AYA-8 or OL-337(V)/AY Logic Units and the CV-2461A/A are incorporated in the CP-2044. The AN/ARN-151(V)1 Global Positioning System [GPS] provides highly accurate navigation information. The five-channel receiver processor unit continuously tracks and monitors four satellites simultaneously, while the fifth channel tracks another satellite for changeover to maintain an acceptable geometry between satellites.


The AN/ALR-66A/B(V)3 Electronic Support Measures [ESM] Set provides concurrent radar warning receiver data (threat data) along with ESM data (fine measurement of classical parametric data). The AN/ALR-66B(V)3 Set provides increased sensitivity and processing improvements over its predecessor, the AN/ALR-66A(V)3. Further refinements to the operational flight program and the library will provide an operator tailorable library. The AN/ALR-66B(V)3 provides inputs to the EP-2060 Pulse Analyzer to detect, direction find, quantify, process, and display electromagnetic signals emitted by land, ship, and airborne radar systems

[ 本文最後由 jacklf2004 於 07-10-7 02:46 PM 編輯 ]

克里斯Chris

TheCounter Drug Update Equipment update is a Chief of Naval Operations (CNO) identified urgent requirement to equip a limited number of active and reserve P-3C Update III Aircraft with a RORO capability to install all or selected systems to counter narcotic trafficking operations.

Counter Drug Update systems include:Air-to-Air Radar System AN/APG-66EOSS AN/AVX-1(V)1Project Rigel Communications EquipmentECP-315 addresses the design, manufacture, and installation of aircraft wiring provisions for AFC-563 kits in 32 aircraft (18 active and 14 reserve).

Ten active and five reserve RORO kits are provided for AN/AVX-1 and 10 RORO kits for AN/APG-66 (active duty aircraft only). ECP-391, Project Rigel, addressed the design, manufacture, and installation of aircraft wiring provision kits in 18 active aircraft and eight RORO kits.


The Sustained Readiness Program (SRP) provides for the preemptive replacement of airframe components and systems identified as having potential for significant impact on future aircraft availability because of excessive time to repair, obsolescence, component manufacturing lead time, or cost impact.


The SRP kit is comprised of a set of core installations and repairs that must be performed on each aircraft and a set of conditional installations and repairs. The need for the conditional installations and repairs will be determined by inspections performed on each aircraft as it is inducted. In addition, the fuel quantity system will be replaced with a Digital Fuel Quantity System (DFQS).


The first SRP aircraft under went modification and was completed in first quarter FY97. The Electronic Flight Display System (EFDS) is an updated version of the Flight Display System (FDS). It is defined as the flight instrument, associated controls, and its interface to the aircraft, and is designed to provide the pilot, co-pilot, or Navigation/Communication (NAV/COMM) Officer with a comprehensive, unambiguous presentation of navigation information adequate for both worldwide tactical and non-tactical navigation.


The display unit uses a flat panel domestic Active Matrix Liquid Crystal Display (AMLCD). The FDS functionally replaces the P-3 electro-mechanical Horizontal Situation Indicator (ID-1540/A), electro-mechanical Flight Director Indicators (FDI) (ID-1556), selected functions of the Navigation Availability Advisory Lights, and integrates GPS navigation with the flight instruments.


Additional information such as navigational aid waypoint locations, GPS annunciation, and FDS status pages are also displayed. Due to the high operational expense of the Inertial Navigation Unit currently installed, a Replacement Inertial Navigation Unit (RINU) has become necessary.

The RINU will be installed coincidental with the EFDS and training will be developed to include both systems. The Navy periodically conducts service life assessment programs to reevaluate its fatigue damage accrual estimate, flight hour limits, and operational availability and reliability.


Based on these assessments, the P-3's service life limit hasincreased from 7,500 flight hours to 20,000. Over the years, the Navy found that P-3 flying patterns were not as severe as had been assumed.The original limit was based on conservative assumptions about in-flight stresses (e.g. maneuvers and payload), while the higher limit reflectedactual operating experience and more modern analysis of the original fatigue test data. The Navy periodically reevaluates flight hour limits, or, more accurately, the fatigue damage accrual rate from which it derives flight hour limits.


Preliminary analysis in the early 1990s indicated that the 20,000 hour limit for the P-3 could be extended to 24,000 hours or more, which represents an additional 6 years of service life atcurrent usage rates. The extension may be lessened if other factors such as corrosion or cost of operation and maintenancebecome unmanageable. Using the Navy's retirementprojection methodology and assuming a 24,000 Right hour limit, the fleet size would remain at 249 aircraft through the decade and drop to 239 by fiscal year 2005.


On 12 March 1999 Lockheed Martin Aeronautical Systems, Marietta GA, was awarded a $30,205,495 cost-plus-incentive-fee contract to conduct Phase II and III of the service life assessment program (SLAP) being conducted for the P-3C aircraft. The primary purpose of the SLAP is to assess the fatigue life and damage tolerance characteristics of the P-3C airframe, and to identify structural modifications required in an effort to attain the 2015 service life goal

Specifications(數據)
Primary Function	Antisubmarine warfare(ASW)/Antisurface warfare (ASUW)
Contractor	Lockheed
	P-3A	P-3B (L)	P-3B (H)	P-3C
Date Deployed	August 1962			August 1969
Power Plant	Four T56-A-10 Allison turbo prop 4,300 horsepower each	Four T56-A-14 Allison turbo prop 4,600 horsepower each
Maximum gross weight	127,500 lbs	127,500 lbs	139,760 lbs	139,760 lbs
Endurance	10-13 hr	10-13 hr	10-13 hr	10-13 hr
Crew composition	5 - minimum flight crew 11 - normal crew 21 - maximum accomodation
Cruise speed (average)	330 knots	330 knots	330 knots	330 knots
Fuel capacity (approximate)	60,000 lbs	60,000 lbs	60,000 lbs	60,000 lbs
Fuel consumption (lb/hr)	4000-5000	4000-5000	4000-5000	4000-5000
Unit Cost				$36 million (FY 1987)
Armament [td=4,1]up to around 20,000 pounds (9 metric tons) internal and external loads

[ 本文最後由 jacklf2004 於 07-10-7 02:47 PM 編輯 ]

克里斯Chris

P-3C TECHNICAL DATA: External Dimensions Wing span 30.37 m Wing chord (at root) 5.77 m Wing chord (at tip) 2.31 m Wing aspect ratio 7:5 Length overall 35.61 m Height overall 10.27 m Fuselage diameter 3.45 m Tailplane span 13.06 m Wheel Track (c/l shock absorbers) 9.50 m Wheel base 9.07 m Propeller diameter 4.11 m Cabin door (height) 1.83 m Cabin door (width) 0.69 m	Internal Dimensions Cabin, excl flight deck and electrical load center: Length 21.06 m Maximum width 3.30 m Maximum height 2.29 m Floor area m2 Volume 120.6 m
	Areas Wings, gross 3120.77 m2 Ailerons (totals) 8.36 m2 Trailing-edge flaps (total) 19.32 m2 Fin, including dorsal fin 10.78 m2 Rudder, including tab 5.57 m2 Tailplane 22.39 m2 Elevators, including tabs 7.53 m2
Weights and Loadings Weight empty 27,890 kg Maximum fuel weight 28,350 kg Maximum expendable load 9,071 kg Maximum normal T-O weight 61,235 kg Design zero-fuel weight 35,017 kg Maximum landing weight 47,119 kg Maximum wing loading 507.0 kg/m Maximum power loading 4.18 kg/kW	Performance P-3B/C at maximum T-O weight (except where indicated otherwise): Maximum level speed at 4,575 meters at AUW of 47,625 kg 411 knots Econ cruising speed at 7,620 m at AUW of 48,895 kg 328 knots Patrol speed at 457 m at AUW of 49,895 kg Rate of climb at 457 m Time to 7,620 meters 594 min. Service ceiling 30 min. Service ceiling , OEI 8,625 meters T-O run 5,790 meters T-O to 15 miles 1,290 meters Landing from 15 meters at design landing weight 1,673 meters 1,673 meters Mission radius (3 h on station at 457 m; 1,500 ft) 845 nautical miles Maximum mission radius (no time on station) at 61,235 kg 1,345 nautical miles Ferry range 2,070 nautical miles Maximum endurance at 4,575 meters on two engines 17 h 12 min Maximum endurance at 4,575 meters on four engines 12 h 20 min

『文章來自：反潛巡邏機系列』

克里斯Chris

武器介紹：

P-3 Orion/獵戶座式長程反潛巡邏機




P-3C是一種為以陸地為基地設計的長程反潛(ASW,Anti-Submarine Warfare)巡邏機。它搭載了多種水下偵查傳感器,如:

定向高頻陣列(DIFAR)聲納浮標和磁異偵查(MAD,Magnetic Anomaly Detection)設備。

航空電子設備系統由通用電腦(美國海軍標準機用型電腦)作所有作戰顯示,螢幕和自動地的電腦發射軍用品和提供飛行資訊對飛行員。另外,系統協調航海資訊和接受傳感器資料輸入為作戰顯示和儲存。

P-3C可以單獨執行任務或支援運載許多不同的人員包括乘載戰鬥小組和兩棲快速反應小組。航空器可能內部攜帶各種各樣的武器並且在機翼固定武器發射架,譬如魚叉飛彈、MK-50魚雷、MK-60水雷。

各個海上巡邏航空(MPA)分譴艦隊有九架P-3C和由大約60名軍官和250名士兵。每個11人機組員包括軍員和士兵。MPA分譴艦隊部署在美國境外大約六個月,和在本土花費一年訓練。


發展簡年表:
　　1959 年2月,海軍為了汰換老舊的P-2,下單給Lockheed公司開發替代機。

　　1962年7月一開始的P-3V構型1962年7月寫進了帳目紀錄,從此開始它超過30年的海軍陸基反潛機生涯。從開始發展的P-3V到定型的P-3,之後有三個主要構型: P-3A、P-3B和P-3C(1969年正式開始服役),P-3C是唯一一款目前仍活躍服務於多國海軍的機型。

　　1975年P-3C Update I(主要改良項目:航空電子系統)開始技術評估。
　　1977年P-3C Update II(主要改良項目:紅外線偵測系統、搭載魚叉飛彈作戰、聲納浮標系統...等等)開始技術評估。
　　1981年3月P-3C Update III(主要改良項目:通信系統、控管系統、GPS)開始技術評估。
　　1985年P-3C Update III正式進入美國海軍實際測試。
　　1986年P-3C Update III測試完成。
　　1990年4月最後的海軍P-3生產線(Lockheed工廠)結束生產。
　　1990年代初期開始進行機體延壽改良(機體壽命從原本的7500小時增加到20000小時,後來1996年經過分析部份狀元良好、較新者可進一步延長到24000小時,到2005年通過最後一筆預算)。

　　1996年以P-3C當發射載台,試射了魚叉反艦飛彈改成的SLAM(遠距攻陸飛彈)。
　　1998年P-3C Update III AIP升級計劃(主要改良項目:通信系統、控管系統、作戰系統、增加更強大的感測/電戰系統,改裝成電子偵察機)。

　　部份較接近淘汰年齡的P-3C在改裝後,移轉給海關、緝毒單位做偵察販毒者(使用海空交通運毒)使用。


　　重要成績:

P-3並無重要攻擊戰績,但從60年代後至今,多次發現蘇聯核動力潛艦於北太平洋、北大西洋等地出沒。

　　2001年4月1日,於南中國海南島外海,一架從沖繩嘉手納基地起飛的EP-3E電子偵察機與因其侵入領空而前往攔截的中共殲八戰機相撞。


　　

P-3B/C性能諸元(美國海軍使用的數據,美國售我中華民國的規格有無變動,尚未清楚):

規格:

全長21.06公尺,機體寬3.45公尺,翼展寬30.37公尺,機體高2.29公尺,停放全高(到垂尾翼頂)10.27公尺,內部全長21.06公尺,機體內部寬3.30公尺,機體內部高2.29公尺,內部最大容量120.6立方公尺。

重量:空重27890公斤,最大燃料重38350公斤,最多可拆裝載重(如:不影響飛行的電子設備)9071公斤,最大起飛重61235公斤,無燃料重(裝備基本設備)35017公斤,最大著陸重47119公斤。

速度:最大速度760公里/小時(飛行高4500公尺以上,飛行重47625公斤以下),一般巡航速607公里/小時(標準巡航高7620公尺,飛行重48895公斤以下),反潛巡航速(反潛巡航高457公尺,飛行重48895公斤以下)。

耐航:一般9小時54分鐘,使用兩個引擎(巡航高4575公尺,空中加油2次)17小時12分鐘,使用四個引擎(巡航高4575公尺,空中加油2次)12小時20分鐘

飛行距離:反潛任務最大巡航半徑1563公里(實際在任務空域總共約3小時),最大作戰半徑(需空中加油)3829公里。

飛行高:實用升限8625公尺(起飛至到達實用升限需30分鐘),從飛行高15公尺著陸須使用跑道長(最大著陸重)1673公尺。

[ 本文最後由 jacklf2004 於 07-10-7 02:49 PM 編輯 ]