Sukhoi Su-30MK

Sukhoi Su-30 (kode NATO: Flanker-C) adalah pesawat tempur yang dikembangkan oleh Sukhoi Rusia pada tahun 1996. Pesawat ini adalah pesawat tempur multi-peran, yang efektif dipakai sebagai pesawat serang darat. Pesawat ini bisa dibandingan dengan F/A-18E/F Super Hornet and F-15E Strike Eagle Amerika Serikat.

Pesawat ini adalah pengembangan dari Su-27UB, dan memiliki beberapa varian. Seri Su-30K dan Su-30MK telah sukses secara komersial. Varian-varian ini diproduksi oleh KNAAPO dan Irkut, yang merupakan anak perusahaan dari grup Sukhoi. KNAAPO memproduksi Su-30MKK dan Su-30MK2, yang dirancang dan dijual kepada Tiongkok. Su-30 paling mutakhir adalah seri Su-30MK buatan Irkut. Antara lain Su-30MKI, yang merupakan pesawat yang dikembangkan khusus untuk Angkatan Udara India, serta MKM untuk Malaysia dan MKA untuk Algeria.
Negosiasi dengan India untuk menyuplai pesawat jenis Su-27 fighters dimulai pada tahun 1994. Biro desain mulai bekerja untuk mengembangkan Su-30-berbasis pesawat untuk Angkatan Udara India pada tahun 1995. AF Barkovsky ditunjuk sebagai ketua perancang proyek. Pada tanggal 30 November 1996 sebuah perjanjian dibuat untuk pembangunan bertahap dan pengiriman ke India dari 8 Su-30K fighters dengan dua kursi dan 32 Su-30MKI multi-peran dengan dua kursi fighters. Pesawat yang telah dijadwalkan untuk pengiriman di beberapa consignments, dengan bertahap akan meningkatkan avionics, powerplant dan senjata. Pengembang umum menurut resolusi yang dikeluarkan pemerintah Rusia adalah:

- Untuk pembangunan pesawat: Sukhoi Design Bureau OJSC (sekarang JSC),
- Untuk produksi pesawat: Irkutsk Aircraft Production Association (IAPA, sekarang Irkut Corporation).

Dua prototip dibangun oleh Biro Desain pada 1995-1998. Prototipe yang pertama, Su-30I-1, berdasarkan pada produk versi Su-30, prototipe atau model pesawat selesai dibuat di musim semi tahun 1997. Penerbangan pertama dilakukan oleh pilot uji V.Yu. Averyanov pada 1 Juli 1997. Pada bulan Juli 1997, Design Biro meluncurkan program untuk menguji pesawat bersama SPFC dari Angkatan Udara.

Pesawat terbang telah diproduksi di Irkutsk sejak tahun 2000. Pada saat Pra Produksi untuk pertama kalinya penerbangan pesawat telah diuji oleh V.Yu. Averyanov pada 26 November 2000. Pra produksi ketiga Su-30MKIs telah diserahkan ke Biro Desain dan telah digunakan bersama dengan prototip dalam joint-program dengan pengujian SPFC dari Angkatan Udara.

Sesuai dengan ketentuan kontrak, maka pesawat Su-30MKI akan diuji dan dikirimkan dalam 3 tahap. Pertama pengiriman 10 Su-30MKI ke pengguna terjadi pada tahun 2002; kedua dari 12 aeroplanes, pada tahun 2003. Pada 2004, pesawat Su-30K dan Su-30MKI telah dimasukkan ke dalam armada satuan Angkatan Udara dengan dua squadron.

Keistimewaan dari Su-30MKI ini adalah:

- Untuk pertama kalinya di dunia, produksi pesawat terbang yang memiliki mesin dengan tthrust vector kontrol (AL 31FP, dikembangkan oleh RDC setelah bernama A.Lyulka), dan sistem remote control terpadu dalam satu kontrol loop. Diambil bersama-sama, ini renders the Su-30MKI sangat lincah bermanuver;
- Untuk pertama kalinya dalam sejarah Biro Desain, pesawat yang dilengkapi dengan avionics skala besar yang terintegrasi dengan sistem luar negeri dan dalam negeri asalnya. The Su-30MKI memiliki “internasional” avionics portofolio, karena tidak termasuk sistem dan 14 unit yang dibuat oleh perusahaan asing dari 6 negara di dunia.
- Untuk pertama kalinya di dunia, sebuah pesawat produksi memiliki radar dengan PAA ( “Bar” dikembangkan oleh Scientific Instrumentation Research Institute of Technology). Selain itu, pesawat memilki new ejection seat yang baru, K-36D-3.5, dan inovasi lainnya dari sistem domestik asal.
- ADO line-up telah ditingkatkan secara signifikan dengan penambahan RVV-AYe air-to-air guided missile, Kh-29L/T/TYe, Kh-31A/P, Kh-59M air-to-ground missiles, dan KAB-500 dan KAB-1500 guided bombs.

Su-30MKI dalam sejarah rusia untuk pertama kalinya memiliki program dalam sejarah showcased sebuah model baru bagi kerjasama militer-teknis termasuk semua jenis kerjasama jangka panjang yang saat ini dilakukan di dunia seperti:

- Pengiriman pertama konsinyasi produk dalam versi dasar (Su-30K),
- Kerjasama R & D untuk menghasilkan versi upgrade (Su-30MKI),
- Memberikan pengguna lisensi untuk manufaktur dengan setelah penggantian komponen rusia yang dibuat dengan orang-orang asing asal (pada bulan Desember 2000, telah menandatangani kontrak untuk menjual ke India lisensi untuk pembuatan 140 pesawat Su-30MKI pada akhir pengiriman),
- Mengupgrade pesawat dari pengiriman pertama untuk status teknik pengiriman akhir,
- Menyiapkan kerjasama teknis untuk pusat layanan pasca penjualan dengan disertakan pemeliharaan peralatan,
- Menggunakan «ekspor tempat» untuk memperluas ke pasar regional (di tahun 2003, kontrak dibuat untuk suplai Su-30MKM ke Malaysia).

Su-30MKK

Biro desain mulai bekerja untuk menghasilkan Su-30-berbasis dua kursi penerbang yang dirancang untuk Su -30MKK angkatan udara China pada 1997, AI Knyshev yang telah ditunjuk sebagai ketua perancang proyek. Di bawah kontrak, direncanakan Komsomolsk-on-Amur production(KnAAPO) dinamakan dengan kontraktor umum. Biro desain menghasilkan desain rinci pada 1997-98; prototipe pesawat yang dibuat di Komsomolsk-on-Amur di 1998-99. Versi baru dua penumpang berdasarkan pada desain solusi diadopsi untuk Su-27SK dan satu kursi fighter Su-27M. Akibatnya, Su-30MKK dimasukkan, untuk semua intents dan tujuan tanpa desain ulang, Su-27M’s centre wing section, wing panels, air intakes, tail beams, fins and landing gear and the Su-27SK’s tail-end fuselage dirangkai. Dengan cara ini, desain ruang lingkup dikurangi secara dramatis, tanpa ada komponen baru yang diperlukan untuk membangun pesawat terbang kecuali untuk hidung pesawat. Selain itu, rencana produksi telah ikut serta dalam menyiapkan produksi dua kursi pelatih pada awal’80 an.

Prototipe pertama dibangun di musim semi 1999, Su-30MKK-1 yang diterbangan pada 20 Mei 1999 oleh Pilot I.Ye. Solovyov (Biro Desain) dan A.V. Pulenko (KnAAPO). Pertama empat pesawat pra-produksi yang diserahkan ke Desain Biro untuk pengujian. Pengujian yang dilakukan bersama-sama dengan SPFC dari Angkatan Udara di 1999-2001, dengan produksi pertama 10 Su-30MKK pesawat dikirimkan ke pelanggan pada bulan Desember 2000.

Su-30MKK desain highlights:

- Pesawat ini memiliki peralatan upgrade dari mnufaktur Rusia, yang meliputi versi radar baru dengan tujuan dan sasaran pemetaan kemampuan; OSTS dengan target penyinaran menggunakan laser beam; sistem GPS, dan LCD multi fungi berwarna di kokpit, dll
- ADO line-up telah ditingkatkan dengan penambahan RVV-AYe air-to-air guided missile; Kh-29L/T/TYe, Kh-31P, Kh-59M air-to-ground missiles; dan KAB-500 dan KAB-1500 guided bombs. Su-30MKK telah digunakan sebagai dasar untuk menghasilkan suatu versi upgrade, maka Su-30MK2, yang berbeda dari versi terdahulu dalam sistem senjata dan peralatan konfigurasi; pesawat dari jenis ini telah diberikan kepada Cina pada tahun 2003. Selain itu, Su-30MK adalah jenis aeroplanes dikirim ke Indonesia pada tahun 2003.

Berikut ini adalah data tentang Su-30MK:

Aircraft performance:

a. Takeoff weight:
- normal (including rockets 2xR-27R1 + 2xR-73E, 5270 kg fuel), kg 24,900*
- maximum, kg 34,500
- max, kg 38,800
b. Maximum landing weight, kg 23,600
c. Max landing weight, kg 30,000
d. Maximum internal fuel, kg 9,640
e. Normal internal fuel, kg 5,270
f. Maximum ordnance, kg 8,000
g. Service ceiling (without external ordnance and stores), km 17.3
h. Maximum flight speed at sea level (without external ordnance and stores), km/h 1,350
i. Max Mach (without external ordnance and stores) 2.00 (1.9**)
j. G-limit (operational) 9
k. Maximum flight range (with rockets 2xR-27R1, 2xR-73E launched at half distance):
- at sea level, km 1,270
- at height, km 3,000
- with one refuelling (at 1.500 kg fuel remaining), km 5,200
- with two refuellings in flight, km 8,000
l. Maximum airborne time (pilot-dependent), hours 10
m. Takeoff run at normal takeoff weight, m 550
n. Landing run at normal landing weight (with braking parachute), m 750
m. Aeroplane dimensions:
- length, m 21.9
- wingspan, m 14.7
- height, m 6.4
n. Crew 2

In-flight refuelling system

a. Maximum flow rate (at entry pressure of 3.5 kg/cm 2), l/min 1,100
b. Powerplant
Number and type of engines 2 x AL-31F (2 x AL-31FP***)
Thrust in afterburner, kgf 12,500 -2 %

Avionics:

1. Fire control system
1.1. Air-to-air fire control system
1.1.1. Search and track radar
1.1.2. IRST and laser rangefinder
1.1.2.1. Optical search and track station
1.1.2.2. Helmet-mounted target designator
1.1.3. Wide-angle HUD
1.1.4. IFF system interrogator
1.2. Air-to-surface fire control system
1.2.1. Coloured multi-purpose LCD indicators
1.2.2. Onboard digital computer
1.2.3. GPS satellite-based navigation system
1.2.4. Weapons control system
2. Aeroplane remote control system
3. IFF system transponder
4. Antenna feed system
5. Flight navigation system
5.1. Digital computer
5.2. Attitude and heading reference system
5.3. Short-range radiotechnical navigation system
5.4. GPS system
5.5. Autopilot system
5.6. Altitude and speed data processing and display system
5.7. Air data system
6. Electronic countermeasure equipment
6.1. Radar warning receiver with an expansion block
6.2. Chaff and heat flare dispenser
6.3. Radio jamming transmitter (in pod)
7. Communications system
7.1. VHF and UHF band communications transceiver
7.2. VHF and UHF band communications transceiver
7.3. SW band radio communications transceiver
8. Onboard automatic control system
8.1. Integrated onboard control and crew warning system
8.2. Flight information recording equipment
8.3. Onboard emergency situation warning equipment
9. Video recording system
9.1. Onboard video recorder
9.2. Forward vision video camera
9.3. Video controller
10. Aircraft responder
11. Telecommand homing system
12. Pod-type IRST and laser rangefinder

Limits

Aircraft limit:
- SLL, hours 3,000
- to first overhaul, hours 1,500
- service life, years 25
Engine and outboard accessory-gearbox life:
- to first overhaul, hours 500
- service life limit, hours 1,500

*May vary depending on the equipment configuration installed upon customer’s request
**With canard surfaces installed
***With thrust vector control engine installed

Armaments/persenjataan:

1. Guns Onboard 30mm gun with 150 rds
2. Guided air-to-air missiles R-27R1(ER1) R-27T1(ET1) R-27P(EP) R-73E RVV-AYe
3. Guided air-to-surface missiles Kh-59ME Kh-31A, Kh-31P Kh-29T(TYe), Kh-29L
4. Guided bomb units KAB-500KR, KAB-500OD KAB-1500KR, KAB-1500L
5. Air bombs FAB-500T BETAB-500ShP ODAB-500PM OFAB-250-270 OFAB-100-120 P-50T Incendiary bombs
6. Cluster bombs RBK-500 SPBE-D
7. Unguided missiles S-8KOM, S-8OM, S-8BM S-13T, S-13OF S-25OFM-PU
8. External fuel tanks N/a
9. Suspension points 12

F-16 Fighting Falcon

F-16 Fighting Falcon adalah jet tempur multi-peran yang dikembangkan oleh General Dynamics, di Amerika Serikat. Pesawat ini awalnya dirancang sebagai pesawat tempur ringan, dan akhirnya berevolusi menjadi pesawat tempur multi-peran yang sangat populer. Kemampuan F-16 untuk bisa dipakai untuk segala macam misi inilah yang membuatnya sangat sukses di pasar ekspor, dan dipakai oleh 24 negara selain Amerika Serikat.

Pesawat ini sangat popular di mata international dan telah digunakan oleh 25 angkatan udara. F-16 merupakan proyek pesawat tempur Barat yang paling besar dan signifikan, dengan sekitar 4000 F-16 sudah di produksi sejak 1976. Pesawat ini sudah tidak diproduksi untuk Angkatan Udara Amerika Serikat, tapi masih diproduksi untuk ekspor.
F-16 dikenal memiliki kemampuan tempur di udara yang sangat baik, dengan inovasi seperti tutup kokpit tanpa bingkai yang memperjelas penglihatan, gagang pengendali samping untuk memudahkan kontrol pada kecepatan tinggi, dan kursi kokpit yang dirancang untuk mengurangi efek g-force pada pilot. Pesawat ini juga merupakan pesawat tempur pertama yang dibuat untu menahan belokan pada percepatan 9g.

Pada tahun 1993, General Dynamics menjual bisnis produksi pesawat mereka kepada Lockheed Corporation, yang kemudian menjadi bagian dari Lockheed Martin setelah merger dengan Martin Marietta pada tahun 1995.

Sejarah

Pada tahun 1960-an, Angkatan Udara dan Angkatan Laut Amerika Serikat menyimpulkan bahwa masa depan pertempuran udara akan ditentukan oleh peluru kendali yang semakin modern. Dan bahwa pesawat tempur masa depan akan digunakan untuk pengejaran jarak jauh, berkecepatan tinggi, dan menggunakan sistem radar yang sangat kuat untuk mendeteksi musuh dari kejauhan. Ini membuat desain pesawat tempur masa ini lebih seperti interseptor daripada pesawat tempur klasik. Pada saat itu, Amerika Serikat menganggap pesawat F-111 (yang pada saat itu masih dalam tahap pengembangan) dan F-4 Phantom akan cukup untuk kebutuhan pesawat tempur jarak jauh dan menengah, dan didukung oleh pesawat jarak dekat bermesin tunggal seperti F-100 Super Sabre, F-104 Starfighter, dan F-8 Crusader.

Pada Perang Vietnam, Amerika Serikat menyadari bahwa masih banyak kelemahan pada pesawat-pesawat mereka. Peluru kendali udara ke udara pada masa itu masih memiliki banyak masalah, dan pemakaiannya juga dibatasi oleh aturan-aturan tertentu. Selain itu, pertempuran di udara lebih banyak berbentuk pertempuran jarak dekat dimana kelincahan di udara dan senjata jarak dekat sangat diperlukan.

Kolonel John Boyd mengembangkan teori tentang perawatan energi pada pertempuran pesawat tempur, yang bergantung pada sayap yang besar untuk bisa melakukan manuver udara yang baik. Sayap yang lebih besar akan menghasilkan gesekan yang lebih besar saat terbang, dan biasanya menghasilkan jarak jangkau yang lebih sedikit dan kecepatan maksimum yang lebih kecil. Boyd menganggap pengorbanan jarak dan kecepatan perlu untuk menghasilkan pesawat yang bisa bermanuver dengan baik. Pada saat yang sama, pengembangan F-111 menemui banyak masalah, yang mengakibatkan pembatalannya, dan munculnya desain baru, yaitu F-14 Tomcat. Dorongan Boyd tentang pentingnya pesawat yang lincah, gagalnya program F-111, dan munculnya informasi tentang MiG-25 yang saat itu kemampuan dibesar-besarkan membuat Angkatan Udara Amerika Serikat memulai perancangan pesawat mereka sendiri, yang akhirnya menghasilkan F-15 Eagle.

Pada saat pengembangannya, F-15 berevolusi menjadi besar dan berat seperti F-111. Ini membuat Boyd frustrasi dan ia pun meyakinkan beberapa petinggi Angkatan Udara lain bahwa F-15 membutuhkan dukungan dari pesawat tempur yang lebih ringan. Grup petinggi Angkatan Udara ini menyebut diri mereka “fighter mafia”, dan mereka bersikeras akan dibutuhkannya program Pesawat Tempur Ringan (Light Weight Fighter, LWF).

Pada Mei 1971, Kongres Amerika Serikat mengeluarkan laporan yang mengkritik tajam program F-14 dan F-15. Kongres mengiyakan pendanaan untuk program LWF sebesar US$50 juta, dengan tambahan $12 juta pada tahun berikutnya. Beberapa perusahaan memberikan proposal, tetapi hanya General Dynamics dan Northrop yang sebelumnya sudah memulai perancangan dipilih untuk memproduksi prototip. Pesawat mereka mulai diuji pada tahun 1974. Program LWF awalnya merupakan program evaluasi tanpa direncanakan pembelian versi produksinya, tetapi akhirnya program ini dirubah namanya menjadi Air Combat Fighter, dan Angkatan Udara AS mengumumkan rencana untuk membeli 650 produk ACF. Pada tanggal 13 Januari 1975 diumumkan bahwa YF-16 General Dynamics mengalahkan saingannya, YF-17.

Varian

Varian F-16 ditandai oleh nomer blok yang menandakan pembaruan yang signifikan. Blok ini mencakup versi kursi tunggal dan kursi ganda.

F-16 A/B

F-16 A/B awalnya dilengkapi Westinghouse AN/APG-66 Pulse-doppler radar, Pratt & Whitney F100-PW-200 turbofan, dengan 14.670 lbf (64.9 kN), 23.830 lbf (106,0 kN) dengan afterburner. Angkatan Udara AS membeli 674 F-16A dan 121 F-16B, pengiriman selesai pada Maret 1985.

Blok 1
Blok awal (Blok 1/5/10) memiliki relatif sedikit perbedaan. Sebagian besar diperbarui menjadi Blok 10 pada awal 1980-an. Ada 94 Blok 1, 197 Blok 5, dan 312 Blok 10 yang diproduksi. Blok 1 model awal produksi dengan hidung dicat hitam.

Blok 5
Diketahui kemudian bahwa hidung hitam menjadi identifikasi visual jarak jauh untuk pesawat Blok 1, sehingga warnanya diubah menjadi abu-abu untuk Blok 5 ini. Pada F-16 Blok 1, ditemukan bahwa air hujan dapat berkumpul pada beberapa titik di badan pesawat, sehingga untuk Blok 5 dibuat lubang saluran air.

Blok 10
Pada akhir 1970-an, Uni Soviet secara signifikan mengurangi ekspor titanium, sehingga produsen F-16 mulai menggunakan alumunium. Metode baru pun dilakukan: aluminum disekrup ke permukaan pesawat Blok 10, menggantikan cara pengeleman pada pesawat sebelumnya.

Blok 15
Perubahan besar pertama F-16, pesawat Blok 15 ditambahkan stabiliser horizontal yang lebih besar, ditambah dua hardpoint di bagian dagu, radar AN/APG-66 yang lebih baru, dan menambah kapasitas hardpoint bawah sayap. F-16 diberikan radio UHF Have Quick II. Blok 15 adalah varian F-16 yang paling banyak diproduksi, yaitu 983 buah. Produksi terakhir dikirim pada tahun 1996 ke Thailand. Indonesia memiliki varian ini sebanyak 12 unit.

Blok 15 OCU
Mulai tahun 1987 pesawat Blok dikirim ke dengan memenuhi standar Operational Capability Upgrade (OCU), yang mencakup mesin F100-PW-220 turbofans dengan kontrol digital, kemamampuan menembakkan AGM-65, AMRAAM, dan AGM-119 Penguin, serta pembaruan pada kokpit, komputer, dan jalur data. Berat maksimum lepas landasnya bertambah menjadi 17.000 kg. 214 pesawat menerima pembaruan ini, ditambah dengan beberapa pesawat Blok 10.

Blok 20
150 Blok 15 OCU untuk Taiwan dengan tambahan kemampuan yang serupa dengan F-16 C/D Blok 50/52: menembakkan AGM-45 Shrike, AGM-84 Harpoon, AGM-88 HARM, dan bisa membawa LANTIRN. Komputer pada Blok 20 diperbarui secara signifikan, dengan kecepatan proses 740 kali lipat, dan memori 180 kali lipat dari Blok 15 OCU.

Spesifikasi (F-16C Blok 30)

Karakteristik umum

* Kru: 1
* Panjang: 49 ft 5 in (14.8 m)
* Lebar sayap: 32 ft 8 in (9.8 m)
* Tinggi: 16 ft (4.8 m)
* Area sayap: 300 ft² (27.87 m²)
* Airfoil: NACA 64A204 root and tip
* Berat kosong: 18,238 lb (8,272 kg)
* Berat terisi: 26,463 lb (12,003 kg)
* Berat maksimum lepas landas: 42,300 lb (16,875 kg)
* Mesin: 1× Pratt & Whitney F100-PW-220 afterburning turbofan
o Dorongan kering: 14,590 lbf (64.9 kN)
o Dorongan dengan afterburner: 23,770 lbf (105.7 kN)
* Alternate powerplant: 1× General Electric F110-GE-100 afterburning turbofan
o Dry thrust: 17,155 lbf (76.3 kN)
o Thrust with afterburner: 28,985 lbf (128.9 kN)

Performa

* Kecepatan maksimum: >Mach 2 (1,320 mph, 2,124 km/h) at altitude
* Radius tempur: 340 mi (295 nm, 550 km) on a hi-lo-hi mission with six 1,000 lb (450 kg) bombs
* Jarak jangkau ferri: >3,200 mi (2,800 nm, 4,800 km)
* Atap servis: >55,000 ft (15,000 m)
* Tingkat panjat: 50,000 ft/min (260 m/s)
* Beban sayap: 88.2 lb/ft² (431 kg/m²)
* Dorongan/berat: F100 0.898; F110 1.095

Persenjataan

* Senjata api: 1× 20 mm (0.787 in) M61 Vulcan gatling gun, 511 rounds
* Roket: 2¾ in (70 mm) CRV7
* Rudal:
o Air-to-air missiles:
+ 6× AIM-9 Sidewinder or
+ 6× AIM-120 AMRAAM or
+ 6× Python-4
o Air-to-ground missiles:
+ 6× AGM-65 Maverick or
+ 4× AGM-88 HARM
o Anti-ship missiles: 4× AGM-119 Penguin
* Bom:
o 2× CBU-87 cluster
o 2× CBU-89 gator mine
o 2× CBU-97
o 4× GBU-10 Paveway
o 6× GBU-12 Paveway II
o 6× Paveway-series laser-guided bombs
o 4× JDAM
o 4× Mk 80 series
o B61 nuclear bomb

Pesawat sebanding

* Chengdu J-10
* Dassault Mirage 2000
* F/A-18 Hornet
* F-20 Tigershark
* HAL Tejas
* IAI Lavi
* Mikoyan MiG-29

Lockheed Martin F-35 Lighting

Lockheed Martin F-35 Lighting II (Joint Strike Fighter) Cutway
Click image for the full size image




F-35B: What Makes it Fly
From Popular Science

Lift Fan
Whereas conventional jet fighters need up to 3,000 feet of runway to take off, the F-35B pilot simply pushes the throttle forward and is airborne in less than 500 feet. A computer controls the lift fan, which pushes cold air down, causing the jet to float up. The air also prevents hot exhaust from entering the lift fan and stalling the engine. As the F-35B approaches 288 mph, the wings produce enough lift to let the fan disengage.

Engine
Behind the jet’s supersonic speed is the Pratt & Whitney F135 turbofan. During liftoff, the rear exhaust nozzle rotates to direct the engine’s thrust downward, while a drive shaft in front of the engine turns the lift fan.

Roll Nozzles
On the underside of each wing, two computer-controlled roll nozzles channel a small amount of thrust from the engine to stabilize the airplane and keep it from rolling out of control.

Stealth
A precisely shaped body deflects enemy radar signals away from the aircraft instead of back toward the source. An internal weapons bay further minimizes the jet’s radar “signature.”

Sukhoi Su-27

Su-27 - answer of Russia to creation in USA of a fighter F-15 intended for a gain of domination in an air and having unique battle(dashing) possibilities. The journal “Interavia” has named Su-27 “ as the most capable fighter in the world ”. The beginning of the biography Su-27, machine of the fourth generation, is dramatic. Creating an equivalent F-15, the designer collective led by M. Simonov did not possess all completeness of datas about American F-15. When in the summer of a 1977 the

flight tests of a new plane(airplane) designated N-10 have begun was clarified: the tactical-characteristics of F-15 are higher, than it was supposed. And is significant.

Under the insisting the designers N-10 have sent in a museum of aircraft. The realization of the project of a new plane(airplane) - smaller began, than N-10, in sizes more accomplished on aerodynamics, arrangement, is valid capable to argue with F-15 for domination in an air. Later, by the way, the prototype SU-27 just at F-15 has selected a number of the important world(global) records. Su-27 (for stages N-10) was developed as the first domestic “unstablis” plane(airplane) with an electroremote control system. To pilot the machine to the pilot the electrocommand system with “ by brain centre ”, always by ready rational image helps to correct operations of the person, to correct an own error.

This system, expressing by language of the founders of the machine, is spreaded on volume of a plane(airplane) by the channels and extremely is hardy. Su-27 is excellent armed, far sees by locator. The machine is equipped with drives created in NPO “Saturn” of the name A. Lulka. AL-31F - first in country a two-contour drive of such class appropriate on parameters to maximum world(global) reachings. It(he) of a modular construction, with interchangeablis blocks, that simplifies and makes cheaper repair. The resource(safe life) of a drive is lifted up to resource(safe life) of a plane(airplane). The interest in West calls also two-place training-battle Su-27UB, as on “pair” a system of the weapon and management by him(it) completely is saved. Signifies, the battle(dashing) use of a fighter is possible and in such variant.

Control system of arms: coherent the system of target destination is impulse - Doppler radar, optic-electronic helmet locator.

Su-27SK FIGHTER: HIGH POWER GUARANTEED

Formally, the development program of the Su-27SK fighter, a version of the Su-27 aircraft, was launched in 1969, though the conceptual studies and work substantiating its higher performance at Air Force research institutes and in industry date back to a much earlier period. Since then 30 years have elapsed and it would be interesting now to rate the machine from the viewpoint of the present-day standards, analyze the prospects for ideas which originated in the late 1960s and realized in the creation of the baseline aircraft and its version, the Su-27SK.

The worldwide practise of developing air combat complexes favors the correct formulation of the concept of an air complex (AC) as an essential precondition for its "longevity." Thirty years is clear proof that the correct choice was made for the conception of the
Su-27 fighter. The main purpose behind the development was to gain air supremacy. In formulating the operational/tactical concept of the air complex, emphasis was placed on making the best use of its fighter qualities, while limiting the attack potential to unguided weapon systems.
This concept has retained its relevance despite the stress made on the attack potential in the new versions of fourth-generation fighters. In the opinion of military specialists, air complexes must be multirole, that is, they should be effective against ground targets while fully satisfying "fighter requirements." This becomes obvious from analyzing the concepts of such aircraft as F-22A, Rafale and others, which use both guided and unguided weapons for their ground target attacks.
However, the mere availability of the guided weapons, enabling highly accurate selective engagement of ground targets, is far from being sufficient for effective execution of attack missions. To withstand a serious counteraction of hostile ground-based air defense systems, it is necessary to enhance the fighter survivability (i. e. its ability to evade or withstand enemy attacks) by reducing its radar signature, increasing the composition and mass of combat survivability enhancement means, extending the frequency range and increasing the energy potential of the electronic countermeasures (ECM) equipment, assuring the low-altitude flying capability, etc. Moreover, to successfully achieve these and related ends, it would be effectual to have another crewmember aboard the aircraft to operate the search-and-attack systems. The necessity of meeting this condition is confirmed by both foreign and domestic practises (F/A-18E, Su-30MK, etc.). There is also information concerning plans to develop two-seat versions of the Rafale and EF-2000 aircraft. Implementing these measures usually results in degrading the air complex's fighter capacity, reducing its effectiveness in both short- and long-range air combats and virtually changing the fighter concept, turning it into a strike aircraft with an increased fighter potential.
The analysis of employment of aircraft in military conflicts taking place in the world for the last three decades shows that the task of gaining air supremacy has not become obsolete, rather it has grown significantly. Hence the concept of the Su-27 aircraft, whose performance characteristics have been optimized on the basis of the priority solution of this very task, still remains up-to-date. The effectiveness of the solution will depend on how the aircraft performance fits current demands, which, in turn, will depend on the engineering efficiency of the air complex and its systems.
The engineering efficiency is characterized by a number of criteria describing the degree of correspondence of the air complex to the level of combat aircraft development of the period under consideration.
Aerodynamics. Some aircraft experts maintain that perfect aerodynamics of an aircraft are directly linked to the beauty of its outlines. Apart from determining the shape of the airframe delighting laymen and specialists alike, the integral aerodynamic configuration with a lifting fuselage and developed root extensions guarantees a high level of aerodynamics. It is usually evaluated in terms of the maximum aerodynamic quality characterizing the potential of the aerodynamic configuration chosen for the newly developed aircraft and the maximum lift ratio setting the limit for its load-carrying capacity. In these respects the Su-27SK has no rivals in the world among the fourth-generation fighters and is only second to 10 - 15% of advanced fighters currently under development.
The realization of the longitudinal static instability at subsonic speeds, deflection of the leading edges and trailing edge high-lift hardware of the wing adaptively to the flight regime (in angle of attack and Mach number) reduce the trimming losses, increase aerodynamic quality, enhance the load-carrying capacity and decrease the induced drag during evolutions.
Design. The airframe of the Su-27SK fighter is rated at a maximum operational overload of +9g, which is close to the value of the pilot's physiological g-tolerance, and is unlikely to be exceeded in the nearest future. The airframe structure makes extensive use of titanium alloys and strengthened grades of steel. The relative mass of the structure is an indication of the structural cleanness of any aircraft and is equal to about 0.29 for the Su-27SK, which is on a par with the best world standards.
The Su-27SK has been designed to achieve the maximum possible level of combat survivability, that is the capability of an aircraft to proceed with the assigned mission after being hit by the enemy. The two-engine powerplant with independent fuel supply lines for each engine, three-spar wing, redundant aircraft control and hydraulic systems, protection of the pilot's cockpit with equipment units, and explosion-proof design of fuel tanks are just a few items in a long list of measures aimed at solving this problem.
Powerplant. The powerpant comprises two AL-31F double-flow turbojet engines developing a maximum reheat thrust of 12,500 kgf. The engine's specific thrust is 10% higher than that of its American counterpart, the F-100-PW-100. The AL-31F is the world's only series-produced engine for combat aircraft with the active control of the gap between the blades and casing of the turbine; this characteristic markedly increases the efficiency of the latter and fuel efficiency of the engine.
The feature that sets the engine apart is the high level of gas flow stability, which allows it to operate reliably under extreme conditions ranging from irregular air flow at the inlet to the air intake surge and assures safe flight at high angles of attack as well as when the aircraft slips into a spin.
In its design the AL-31F employs many unique engineering innovations determining the potential for increasing the thrust and service life. The realization of these novel ideas will extend its life well into the next two to three decades. An example of these innovations is a vectorable thrust engine.
Control system. The Su-27SK is equipped with an analog-type fly-by-wire system with a quadruple redundancy, assuring control of the longitudinally unstable aircraft. In the last few generations of fighters these have been phased out by digital systems. However, along with the undisputable advantages, the fly-by-wire systems have some disadvantages that prompted the designers to resume employment of analog systems as a backup or combine these to enhance reliability and quality of aircraft control. The Su-27SK aircraft is controlled by an automatic flight control system (AFCS) integrated with the navigation system and command guidance equipment. The AFCS stabilizes the angular position and altitude of the aircraft, levels it off, allows a programmed climb and descent, controls the aircraft in altitude, speed and heading as it is being vectored to air targets, returning to the home airfield, and making the landing approach. The novel concepts and technological solutions involved in the Su-27 enabled it to achieve a high flight performance which today allows it, even without modernizing its major systems, to meet the most stringent requirements placed on modern aircraft.
The integrated configuration with large wing extensions provides, apart from the high aerodynamic efficiency, agreeable conditions for operation of the powerplant at high angles of attack, markedly increases the interior spaces for fuel, which, in turn, makes it possible to achieve the unique flight range without carrying the drop tanks (1,400 km near the ground and 3,900 km at a high altitude in cruising flight conditions). The unique aerodynamic characteristics combined with the optimal choice of such aircraft parameters as the specific wing loading and thrust-to-weight ratio, plus employment of the fly-by-wire system, allow the Su-27SK to outmaneuver its foreign counterparts, including the new generation of European fighters. A stunt like the "Pugachev cobra" could only be reproduced by the American F-16 fighter after significant modifications.
Implementing promising developments in the Su-27SK is the precondition for its "longevity" and expediency of continuous modernization. Among the factors for allowing continuous improvement of the air complex performance characteristics through its modernization is a high level of the structural cleanness, which provides a reserve for installation of more sophisticated equipment and armament. This has been confirmed by experience gained in developing the latest versions of the Su-27 fighter.
Avionics. The avionics of the Su-27SK comprises an airborne radar, optronic fire control system, flight-navigation complex, ECM and communications facilities allowing the aircraft to perform its missions both during the day and at night, in all weathers and in the face of enemy ECM background. Compared to its main foreign counterpart, the F-15C "heavy" tactical fighter, the Su-27SK is on a par with the latter in avionics and surpasses it in composition and capability of the optronic fire control system. The Russian fighter's avionics offers an equal and, in some cases, better performance than similar European new-generation fighters.
The high effectiveness of the Su-27SK is largely due to its advanced weapon control system (WCS) assuring automatic all-aspect detection and tracking of air targets in a free space and against the earth background, engagement of the targets by its air-to-air missiles and gun fire from short and long distances, and destruction of ground targets by its unguided weapons.
The powerful airborne pulse-Doppler radar enables the aircraft to detect and simultaneously track up to ten air targets of the "tactical fighter" type at ranges of up to 120 km. The fighter is also armed with a state-of-the-art optronic fire control system comprising an infrared direction finder with a high-altitude effective range compared to that of the airborne radar, laser range finder, head-up display and helmet-mounted target designator sending virtually instant inputs into the missile homing heads as the pilot turns his head within a wide range of angles. The airborne radar operates in conjunction with the optronic fire control system to exchange the target designation data, which markedly improves the target detection probability and target tracking reliability, especially in enemy ECM environment. The WCS software enables the crew to identify air threats, classify each threat, and select the right weapon to destroy the air target that is the most dangerous in a given tactical situation.
The integrated navigation and communications systems, forming part of the avionics equipment, allow the aircraft to be navigated in all phases of its flight and landing approach in both automatic and director modes and provide radio communications with the ground control stations and other aircraft at distances of up to 1,500 km. The communications equipment is used for exchange of coded information during air combat as well as command guidance from the ground for intercepting air targets.
Armament. To attack air targets, the Su-27SK can carry up to six
R-27E medium-range air-to-air missiles with semi-active radar and infrared homing heads, up to six R-73E short-range combat missiles or various combinations of the same, on its ten hardpoints.
The R-27E missile can attack all types of air targets from short and long distances and in all weathers, from all directions and against the earth background, with the enemy using his ECM and maneuver capabilities. The missile intercepts air targets flying at speeds up to
3,500 km/h and altitudes ranging from 0.02 to 27 km. It is equipped with an inertial radio-updated navigation system and semi-active radar or infrared homing heads. A significant advantage of the Su-27SK armament complex is that it can simultaneously carry the R-27E missiles fitted with different types of homing heads, which enhance the effectiveness of execution of combat missions in the enemy ECM environment.
The R-27E missile is a short-range weapon allowing highly accurate head-on and tail-on attacks against air targets in air combat from all directions. By its effectiveness which derives from the performance characteristics (maximum g-load, target designation angle, angular rate of air target autotracking, minimum launching range for a maneuverable target), the missile outperforms the world's best analogs.
The aircraft also carries aerial bombs of up to 500 kg, including concrete-piercing bombs, clusters, unguided airborne rockets. Such a complement of attack weapons has been accepted largely for gaining air supremacy, and among the several ways to achieve this would be pinning enemy aviation down to the ground (destroying airfield components, dropping mines on them, destroying aircraft and ground installations, disrupting communication and control).
Thus, the avionics and armament of the Su-27SK fighter are presently used as the effective means of accomplishment of its main combat mission - gaining air supermacy through destruction of the enemy aviation both in the air and on the ground.
Operation. The maintainability characteristics of the Su-27SK and its operating performance are crucial for development of and especially promotion of Russian fighters on the combat aircraft world market. According to available evidence, the characteristics of the Su-27SK are on a par with those of foreign fourth-generation tactical fighters. However, in term of the strategy of operation, they are inferior. During their lifetime, the Russian fighters require a considerable amount of scheduled maintenance service and repairs.
Naturally, if a fighter designer does not expect his aircraft to take part in future combat, the additional expenses associated with preventive maintenance and various repairs are simply a waste of money. But if you presume that your aircraft will take part in combat operations, notably large-scale ones, then the availability of a streamlined overhaul facility and well-trained maintenance personnel will not be regarded as a burden incurring additional expenses, but an advantage, since establishing an overhaul facility network usually takes considerable time which may be short during a war.
Effectiveness. Normally,what is meant by the combat effectiveness is the degree of fitness of an aircraft for successfully completing assigned missions. As stated above, the main mission of the Su-27SK is to gain air supremacy.
From the viewpoint of striking distance, the Su-27SK fighter, noted for its unique "load - range" performance, is on a par with the world's best. Interacting with ground and air control stations, the fighter can fly missions involving the interception of air targets to their full operational depth. The long flight range of the aircraft also enables rapid concentration of fighter aviation efforts in the most dangerous directions and its employment where airfields are rare and communications poor.
The conclusive phase of any fighter mission is the air combat, the results of which are used for appraising the effectiveness of the fighter. The equipment and armament of the Su-27SK, meeting the world's best standards or surpassing them, allow the aircraft to boast an appropriate effectiveness in long-range air combat. According to various estimates, the Su-27SK is in no way inferior to its foreign analog, the F-15C. Concerning short-range air combat, the Su-27SK with its unsurpassed agility, unique target designation system and armament, R-73E missiles, not only outperforms all current foreign counterparts, but will be second to none among the promising new-generation fighters.
The overall evaluation of combat effectiveness of the Su-27SK compared to its foreign counterparts, averaged over a great number of combat missions and conditions for their fulfillment, indicates that it outperforms the F-15C tactical fighter in combat potential factor by approx. 10 percent.
From a brief analysis one concludes that, by its concept, engineering perfection and combat effectiveness, the Russian Su-27SK fighter fully meets the requirements placed on the fighters of the early 21st century. The unique flight performance and significant reserves for further modernization of avionics and armament provide the obvious preconditions for operating the aircraft for decades to come.
Thus, a growing interest in the fighter may be anticipated in the countries planning to modernize or expand their aircraft fleet. Thanks to its design features, the Su-27SK can be customized by modernizing the armament systems (adding air-to-surface guided weapons), increasing the flight range through mid-air refueling as well as installing equipment at customer's request. This "flexibility" will make it possible to increase the export potential of the Su-27SK turning it into one of the best selling aircraft in the world.

W. (tons):	23- 33,0
Max. military load (kg):	6'200
Speed (km/h):	1400/2'35 mach min. indicated speed:  200
Acceleration time at H=1000 (sec):	from speed 600 to 1100:   14.1 from 1100 to 1300:   9.8
Dimensions (m):	14,7 x 21,9 x 5,9
Service seiling (m):	18'500
Range (km):	1370/3'700
M./Engine:	2 twin shaft DTRD- AL31-F2, 2 x 13'600 kgs
Man./Crew:	1
Armament:
Missiles:		4 AA R-27 (R-27R, R-27T, R-27TE) 6 AA R-73 AS total: 10
Artillery:		30 mm DP GSh-301
Other:		RBK cluster bombs (25, 500 kg) retarded aerial bombs (100, 250, 500 kg) unguided aerial missiles (C-8, C-25)
Controls:		countermeas.: pilot illum.radar warning receiver (bearing data host.radar emissions, chaff and infra red decoy dispensers, active multirole jammer) - optronic infra-red search and track sensor, laser range finder(40 -100 km range) - jam-proof coherent pulse Doppler radar, Phazatron N001 Zhuk, with track-while-scan and look-down/shoot-down capability (range: target 3sq.m - 40/100 km; search, detect and track up to 10 targets with automatic threat assesment and prioritization) fly-by-wire controls automatic flight controls