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Mitsubishi Ki-2 “Louise” — Twin-Engine Light Bomber
Japanese: 三菱 九三式双軽爆撃機 | Allied reporting name: “Louise”
The Mitsubishi Ki-2 was a 1930s twin-engine light bomber developed for the Imperial Japanese Army Air Service (IJAAS), derived directly from the German Junkers K-37 twin-engine fighter-bomber design purchased by Mitsubishi. It represented a pivotal transitional airframe in Japanese military aviation — forcing Mitsubishi factories to abandon wood-and-fabric construction methods in favour of all-metal stressed-skin production lines.
Because the IJAAS systematically destroyed its military archives at the end of World War II, primary technical literature for the Ki-2 is exceptionally scarce. This collection brings together the surviving primary-source documentation preserved in Japanese archival repositories.
📋 Performance Data Sheet (Ki-2-I / Ki-2-II)
| Parameter | Ki-2-I (Model 1) | Ki-2-II (Model 2) |
|---|---|---|
| Powerplant | 2 × Nakajima Jupiter 9-cyl air-cooled radials | 2 × Nakajima Ha-8 (Type 94) 9-cyl radials |
| Power Output | 450–570 hp per engine | 750 hp per engine |
| Propeller | Two-blade fixed-pitch wooden | Two-blade variable/fixed-pitch metal |
| Cowling | Townend ring / open cylinder fairings | Streamlined low-drag NACA cowlings |
| Maximum Speed | 225 km/h (140 mph) at 3,000 m | 283 km/h (176 mph) |
| Cruising Speed | 150 km/h (93 mph) | |
| Service Ceiling | 7,000 m (22,966 ft) | |
| Operational Range | 900 km (559 miles); ferry range 1,630 km | |
| Climb Rate | 10.5 min to 3,000 m (9,843 ft) | |
| Empty Weight | 2,800 kg (6,173 lb) | |
| Max Takeoff Weight | 4,550 kg (10,031 lb) | |
| Bomb Load | 500 kg (1,102 lb) internal/external racks | |
📐 Aerodynamic Profile & Design Origin
- Wing Structure: Junkers-style low-wing monoplane layout. The Ki-2-I used corrugated duralumin skin panels for structural rigidity — effective but generating significant parasitic drag.
- Ki-2-II Upgrades: Smooth metal wing skin panels replaced corrugated surfaces; enclosed pilot canopy added; glazed enclosed nose turret incorporated; semi-retractable landing gear folding forward into engine nacelles replaced the Ki-2-I’s fixed spat-faired undercarriage.
- Tail Configuration: Twin fins and rudders for directional stability while providing clear arcs of fire for the dorsal gunner.
🚀 Engine Technical Notes
- Ki-2-I: Nakajima Jupiter radials with Townend ring cowlings — adequate for the corrugated-skin airframe but limiting top speed.
- Ki-2-II: Nakajima Ha-8 (Type 94) radials producing 750 hp each, paired with streamlined NACA low-drag cowlings — delivering a 58 km/h speed increase over the Model I.
🕹️ Handling & Stability Studies
- Single-Engine Control: Unlike the larger Ki-1, the Ki-2 demonstrated excellent asymmetric power handling and could safely sustain altitude and maintain control on a single operating engine.
- Maneuverability: Highly praised by crews for agility relative to its classification — far more maneuverable than contemporary biplane bombers such as the Kawasaki Ki-3.
- Stall Vulnerability: Early flight testing suffered severe structural and aerodynamic stalls during landing configurations. One early prototype stalled on approach, resulting in a fatal fuselage snap. Production models corrected this by drastically strengthening the rear fuselage framework.
🏆 Engineering Legacy
- Manufacturing Milestone: The Ki-2 forced Mitsubishi factories to abandon wood-and-fabric methods in favour of all-metal stressed-skin production lines — a foundational shift for all subsequent Mitsubishi military aircraft.
- Civilian Record-Breaker: A highly modified aerodynamic variant named Ohtori (鳳, “Phoenix”) was built for long-range civil aviation. Engineering adjustments to fuel capacity enabled a historic 9,300 km flight around China and a record 21-hour Tokyo-to-Bangkok flight in 1936.
📚 Document Manifest
This collection brings together three primary archival volumes for the Mitsubishi Ki-2 “Louise”, recovered and preserved by Online Aviation Library.
Archival source: Asia Historical Documents Center (アジア歴史資料センター / JACAR), Imperial Japanese Army Air Service wartime production archive. Original language: Japanese.
Volume 1 — Ki-2 Technical Drawings
三菱 九三式双軽爆撃機 技術図面 | Mitsubishi Heavy Industries / IJAAS wartime production archive | Original language: Japanese
| Sheet | Appendix No. | Content |
|---|---|---|
| 01 | Cover | Collection title page and document register |
| 02 | 附図第九 (Fig. 9) | 中央翼 (共二) — centre section plan view: front spar (前縁框), ribs 1–4, front/rear attachment frames, 2,800mm span; cross-sections: centre rib (中央框), front/rear movable frame (前後別動框), outer rib (外方框), G-profile airfoil section |
| 03 | 附図第二 (Fig. 2) | 外翼 (共二) — auxiliary wing attachment bracket (補助翼取付筋帯): isometric exploded view of No. 4 rib, attachment bracket, auxiliary wing bearing, bolt assembly, circular tube spar |
| 04 | 附図第三 (Fig. 3) | 外翼翼框 (共二) — circular tube spar joint: connecting fittings (結接金具), attachment parts (都取付件), C-profile spar section; I-beam spar side elevation with bolt flange plates |
| 05 | 附図第五 (Fig. 5) | 外翼翼框 (共四) — circular tube spar with Z-section and diagonal bracing; compression rib (押抑結筋); 30×28 tube and 100×1–00×0.8 Z-material callouts |
| 06 | 附図第七 (Fig. 7) | 主翼球面節接手 — spherical ball joint cross-section (A, B, C); outer wing attachment rib cross-section with numbered positions 1–7; full material specification table |
| 07 | 附図第九 (Fig. 9) | 補助翼 — full-span plan view (4,801mm): spar positions, rib station spacings, front/rear spar centrelines; cross-sections A-B (円管框), C-D (60×41 corrugated), E-F (60×18 corrugated), H-G (streamlined tip fairing), I (circular tube end cap) |
| 08–50+ | Various | Supplementary structural and systems drawings from the IJAAS/JACAR wartime production archive — airframe, undercarriage, control surfaces, systems installations |
Volume 2 — Ki-2-II Operating and Maintenance Manual
九三式双軽爆撃機(二型)説明書 | 陸軍航空本部 (Imperial Japanese Army Air Headquarters) | Original language: Japanese
| Page | Appendix No. | Content |
|---|---|---|
| Cover | — | 九三式双軽爆撃機(二型)説明書 — official IJAAS title page with 陸軍航空本部 stamp |
| 0960 | — | 一面図 — Ki-2-II full two-view drawing: top-down plan (wingspan 19,740mm, fuselage width 2,481mm, wheel track 4,115mm, engine centreline spacing 4,495mm) with twin NACA cowlings, corrugated wing skin, glazed nose turret, dorsal gunner position, ventral gondola, bomb racks; side elevation with 940×300mm main wheels, 400×100mm tail wheel |
| 0967 | — | 重量及重心一覧表 — Weight & Centre of Gravity table for 11 loading configurations: empty (4,465 kg) through special full load (6,003 kg) and 500 kg bomb load (6,311 kg); CG position X (mm) and % chord; fuselage CG reference diagram |
| 0973 | — | 備品名称員数量表 (sheet 1) — Equipment Parts Quantity Table: Ko/A airframe, Otsu/B engine, Hei/C systems, Tei/D instruments; part name, quantity, unit weight, total weight, remarks |
| 0974 | — | 備品名称員数量表 (sheet 2) — Equipment Parts Quantity Table continuation: Bo/E electrical, Ki/F armament, Ko/G survival/emergency; bomb suspension device, flare drop device, interphone, machine gun, filter, propeller components |
| 0978 | 附図第二 (Fig. 2) | 胴體 (共二) — Fuselage isometric cutaway section 2: oval fuselage cross-section with auxiliary frame, flat plate skin panels, angle bracket floor stringer attachments, corrugated duralumin exterior skin, internal frame ring with riveted flanges |
| 0860 | 附図第四図 (Fig. 4) | 胴體 (共四) — Fuselage bomb bay structural detail: 胴體中部覆 6附近ノ構造ヲ示ス — upper/lower longerons, A/B stringers, bomb suspension rack, lateral bracing, welded box; A-detail: 波板 30×10×0.4, 40×40×1.6 angle; B-detail: 40×40×2 angle, 1.5mm plate |
| 0982 | 附図第六 (Fig. 6) | 胴體前端 — Glazed nose section structural drawing: isometric 3/4 view of complete glazed nose turret dome assembly with windward rotation centre, glass panel attachment holes, upper/lower rotation rail plates, rotation prevention fixing screw, flat cover; upper/lower rail cross-sections |
| 0984 | 附図第八 (Fig. 8) | 主翼 (共一) 翼肂及外皮 — Main wing rib and skin structure: isometric cutaway of outer wing leading edge showing leading edge, skin panels, aileron, trailing edge, front spar, ribs 1–4, Duralumin doubler joint; A-detail cross-section with paper former and circular tube spar end cap |
| 1014 | 附図第三八 (Fig. 38) | 陥著装置 (共十六) 切気圧縦 — Landing gear brake system plumbing diagram: full aircraft-wide pneumatic brake line routing with special connectors (Type Otsu), two-stage connector pipes, indicator, red lamp, pipe valves, isolator valves, upper/lower safety valves; pipe dimension callouts |
| 1016 | 附図第一 (Fig. 1) | 車輪制動装置 — Wheel brake master cylinder cross-section: front view (components 5–11) with upper/lower pressure adjustment screws, left/right wheel brake pressure connections, 50° and 3° angles; side view (components 1–4), 118mm height, 75° angle |
| 1018 | 附図第四一 (Fig. 41) | 尾輪 — Tail wheel assembly: side-elevation of complete 400×100mm tail wheel and oleo strut with spherical bearing, frames 14/15, axle strut (120° travel), stop fitting, maximum deflection/ground static/flight positions, rotation joint, fork fitting, rubber attachment fittings, rubber buffer posts (10mm diameter, 2 each side) |
| 1020 | 附図第三五 (Fig. 35) | 発動機架 (共二) C部詳細 — Engine mount section C detail: isometric exploded view of Nakajima Ha-8 radial engine mount tube joint assembly with 35×83, 35×8, and 45×18 aluminium alloy tubes, heat dissipation plate attachment, diameter 14 taper bolt |
| 1022 | 附図第五五 (Fig. 55) | 発動機覆 — NACA engine cowling exploded assembly: five components in isometric exploded view — forward cowl ring (9 cylinder cutout openings), oval mounting ring, three-petal rear cowl flap assembly, three-petal front cowl flap, axial spinner/propeller hub fairing; front attachment screws, front guard vertical plate |
| 1024 | 附図第七七 (Fig. 77) | 環状框 — Fuselage ring frame: large isometric view of complete oval riveted duralumin ring frame with rectangular lightening holes, corrugated skin attachment flanges, floor attachment brackets; A-B断面 cross-section (cord bolt, plate, metal fitting); bolt joint section detail; front head receiver fitting with felt gasket pad |
| 1052 | 附図第七五 (Fig. 75) | 八九式(特)眼倉取付金具 左部倉用ヲ示ス — Type 89 (Special) gun sight mounting bracket (left bay): exploded isometric of base plate D-ring, curved saddle bracket, handle, release catch lever, gun sight housing cradle, cover open/close section, eyepiece, eyepiece cord, steel rubber bead |
| 1054 | 附図第七七 (Fig. 77) | 旋回風よけ取付要領 — Rotating windscreen mounting instructions: large front-view of complete circular rotating windscreen ring assembly with rotating ring, joint cover plates, fixed ring, lower windscreen gap trim, ladder plate, horizontal ladder; forward attachment fitting detail; A and B cross-section profiles |
| 1056 | 附図第九一 (Fig. 91) | 爆弾配置要領 (共一) — Bomb arrangement layout sheet 1: four-view bomb load configuration diagram — 100kg bombs (3+3 positions, two rows) and 50kg bombs (3+3+3+3 positions, four rows); rear-view elevations of both configurations |
| 1058 | 附図第八一 (Fig. 81) | 一五璤爆弾懸吊装置 — 15kg bomb suspension assembly: large isometric cutaway of complete bomb bay interior showing full suspension rack system in situ — bomb bays 6 and 7, rotation handle, side panels, bomb suspension rack fittings, bomb ejection tube, bomb tube, compression tube |
| 1059 | 附図第八二 (Fig. 82) | 一五璤爆弾懸吊装置 (共二) — 15kg bomb suspension rack side elevation: bomb bay door, open/close latch, equipment box, safety pin device bracket, flight direction arrow |
| 1060 | 附図第八三 (Fig. 83) | 一五璤爆弾吊装置蓋開閉操作概要 — 15kg bomb bay door open/close operation overview: three-view — side elevation (operating lever 515mm), front elevation (packing/gasket, plates, bolt piece), isometric 3/4 view of door mechanism |
| 1061 | 附図第九 (Fig. 9) | 一五璤爆弾倉蓋開閉器集造装置 — Bomb bay door open/close mechanism: four-view of door actuator with pilot seat safety device, electrical circuit connection diagram, dimension callouts |
| 1062 | 附図第八三 (Fig. 83) | 一五璤爆弾吊装置蓋開操作把手 — 15kg bomb bay door opening operation handle: side elevation of ratchet lever handle (45mm, 18mm, gear teeth); front view of circular ratchet plate (106mm diameter, 4 bolt holes at 90°, 3 ratchet positions 甲/乙/丙, 8.60° angle) |
| 1063 | 附図第八六 (Fig. 86) | 一五璤爆弾横吊装置 — 15kg bomb horizontal suspension: isometric view showing attachment fittings, Type Otsu electromagnetic lock (Model 2), bomb bay door, electromagnetic lock seat, vertical hook/bombing panel, Type 19 electromagnetic connector, flight direction |
| 1065 | 附図第八八 (Fig. 88) | 中央翼左下五〇璤爆弾懸吊架構造要領 — 50kg bomb suspension rack structural overview: isometric view of centre wing left lower 50kg bomb rack with Type Ko electromagnetic lock, electromagnetic lock seat, flight direction |
| 1069 | 附図第九 (Fig. 9) | 爆撃電気接続装置図 — Bombing electrical connection system diagram: full wiring schematic — port/starboard Type 15 electromagnetic connectors, Type 2 electromagnetic locks, bombing panel, release electromagnetic lock, safety device |
| 1090 | 附図第一一一 (Fig. 111) | 主間開部構造及装著配置要領 — Main hatch structure & installation layout: front elevation of main hatch panel (rectangular with oval cutout, 42×46mm, bolt pattern); isometric 3/4 view of hatch locking lever mechanism (325mm, 45mm); top-down plan of oval hatch opening; side elevation cross-section; tail fin/rudder outline plan |
| 1092 | 附図第一一〇 (Fig. 110) | 著陸燈・視認燈・警燈・信號燈及機除遥蔽装著要領 — Complete aircraft lighting installation layout: full aircraft 3/4 isometric perspective view of Ki-2-II showing all external lighting positions with candlepower ratings — landing light 10CP (port wing), rotating lights 10CP (both engine nacelles), position light 10CP (nose), rotating light 10CP (starboard wing), tail rotating light 10CP, signal light 240CP (ventral), emergency light 240CP |
| 1094 | 附図第一一四 (Fig. 114) | 尾部制除燈及尾燈応燈近装置配置要領 — Tail navigation light & tail light installation layout: B-B cross-section of tail light bar assembly (Type 1 aluminium alloy plate, Type 1/2 lamp bulbs No. 171, front shield 113, 87mm); top-down plan of tail light housing (large oval, two circular lamp positions); side elevation showing front/rear plates, lamp centre, shield plates |
| 1095 | 附図第三六 (Fig. 36) | 警戒構造及装着配置要領 — Glazed nose turret structural layout: top-down plan of oval eye-shaped glazed turret panel with rivet pattern and fuselage centreline; A-A cross-section (10-type 2-bulb lamp in dome); B-B cross-section (hollow glass, spruce frame, aluminium alloy plate, flight direction); outer wing rib station profile |
| 1096 | 附図第一七 (Fig. 17) | 信號燈構造及装著配置要領 — Signal light structure & installation layout: top-down plan of large oval ventral signal light housing (HP dimension, rivet pattern grid); A-A cross-section (Type 1 aluminium alloy plate, spruce frame, glass dome, Type 2 illumination lamp bulb No. 172); tail fin profile with aileron, ribs 1–4, leading edge light position |
| 1097 | 附図第三八 (Fig. 38) | 機銃設情高及装着配置要領 — Machine gun installation height & mounting layout: B-B and A-A cross-sections (spruce, glass, aluminium alloy plate, outer wing rib stations, inner bilateral electrical seat); plan view showing ventral window (large oval); outer wing rib station plan with ribs 1–5, front/rear wing |
| 1098 | 附図第一九 (Fig. 19) | 機上著陸燈構造及装著配置要領 — Airborne landing light structure & installation layout: A-A cross-section (164mm height, 153mm width, 16mm depth, 30-60-30mm base, 70mm total width); isometric 3/4 view of complete landing light assembly (parabolic reflector, 35° and 3° angles, rubber mount, illumination direction arrow); front view (170mm diameter ring); outer wing plan with aileron, ribs 1–4, leading edge light position |
| 1099 | 附図第一一〇 (Fig. 110) | 席房燈・移動燈及非常燈装着配置要領 — Cabin lights, portable lights & emergency lights installation: isometric cutaway of full fuselage interior showing all lighting positions — emergency light dry battery, cabin light dimmer, portable light storage; symbol legend for cabin light, portable light, emergency light |
| 1100 | 附図第一一一 (Fig. 111) | 非常燈構造要領 — Emergency light structure: isometric 3/4 view of portable dome-shaped emergency light (open/close handle, glass dome, circular base plate with 4 mounting holes); wiring diagram (dry battery, on/off switch, emergency light circuit); cross-section (shell, lamp bulb, 4/7/5/3mm dimensions); top-down plan (52mm and 26mm base) |
| 1101 | 附図第一一一 (Fig. 111) | 九〇式小圆照明弾投下装置 (共一) — Type 90 small round illumination flare drop device: isometric view of port wing showing flare chute from cockpit through wing structure — section 1 (cockpit end with operating handle), 6×1 flush coating, powder/flare, flight direction |
| 1103 | 附図第三三四 (Fig. 334) | 通話器装置要領 — Speaking tube interphone system layout: isometric cutaway of fuselage showing speaking tube routing — tube mouthpieces at stations 1, 3, 4; speaking tube running along fuselage floor; bottle/junction; numbered stations 1–4 |
| 1105 | 附図第三六 (Fig. 36) | 貨車積載及荷造要領 — Railway freight loading & packing instructions: side elevation of Type Chiki No. 19 military flatcar loaded with Ki-2 disassembled — fuselage, tail/aileron/parts, outer wings (×2); three crate cross-section dimension drawings: fuselage crate (2,900×2,250mm), tail/aileron crate (3,300×2,250mm), outer wing crate (2,300mm wide) |
Volume 3 — Ki-2 Photo Collections
Allied TAIU field documentation, IJAAS operational photography & post-war recovery records | English / Japanese
| Item | Content |
|---|---|
| Photographic Archive | Surviving photographic record of the Ki-2 airframe in operational service, ground handling, and Allied post-war inspection. Includes colourised period photographs of Ki-2 aircraft at Japanese airfields with ground crew. |
This is an archival, static-copy edition fixed at its original publication date. Intended for historical reference, flight simulation, museum restoration, and educational use only. Not approved for active airworthiness maintenance under FAA 14 CFR § 43.13, EASA Part-M, or equivalent international regulations. Operators of active aircraft must use current, revision-controlled publications from the Type Certificate holder or an authorized distributor.
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