194:) in two steel vessels. This pressure is released through an electrically-fired cartridge that opens a valve with a blow-out disc. This is the full extent of the electrical control system. Once fired, the valve does not close again. A pressure regulator delivers air at 33 bar (480 psi), through a shuttle valve that pressurised first the catalyst tanks and then the propellant tank. This delay ensures reliable ignition in the combustion chamber. A non-return valve ensures that no catalyst can flow backwards into the air or propellant plumbing, with an explosive result. A rubber diaphragm, broken as propellant pressure builds, ensures that there is no backflow through the combustion chamber either. Z-stoff was known for problems of clogging injectors and so an inline filter was used.
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casing, fitted with wings, engine and radio control. Control equipment was housed in a rearward extension of the bomb casing but the motor was mounted in a separate housing beneath. It had originally been developed as an unpowered glide bomb, "Gustav
Schwartz Propellerwerke", and the engine was added
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casting, cooled by the propellant flow. The combustion chamber is single-walled mild steel, with no provision for cooling. A steel mixing cup is downstream of the injector, with the radial Z-Stoff 6mm pipe leading into it. One 3 mm diameter injector nozzle points into the cup, thirty smaller
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The 109-507 was developed from the 109-500. As a missile engine, it was only required to work once, and for a short duration. It was thus simplified in both its features and in its construction materials. Rather than the complex centrifugal
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radial 2 mm nozzles deliver most of the propellant along the walls of the chamber. Helical swirl baffles in the chamber promote good mixing and decomposition of the peroxide.
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used for most Walter engines, a simple gas pressurisation system was used to feed the propellants. A wartime
British report expressed surprise that the engine's
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The engine had a burning time of around 10 seconds. After this the missile glided to the target, taking up to 100 seconds for a range of 8.5 km.
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fuel in combination with the evolved oxygen. These were more powerful and fuel efficient, but also more complex and required
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Thrust varied through the boost phase, as air pressure and propellant flow fell, dropping from 600 kgf to 400 kgf.
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The unreliability of Z-stoff and its clogging meant that it was largely replaced with other fuel cycles for manned aircraft.
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and was decomposed by a catalyst into superheated steam and oxygen. The catalyst used was a consumable liquid solution of
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As it was intended for attacking lightly- or unarmoured targets, it did not require an armour-piercing high impact speed.
123:) engine. The 109-500 was pod-mounted and parachuted back to earth after takeoff. Engine pods were serviced and re-used.
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missiles. As these larger missiles weighed twice the Hs 293, they used a pair of the engines, one under each wing root.
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As the engine was mounted below the missile fuselage, the exhaust nozzle pointed downwards at 30°, so as to align the
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and so was unpowered, free-falling steeply and reaching a high speed, at the cost of a range half that of the Hs 293
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later. After flight tests, a visible tracking flare was also added, in a further rearward extension.
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Propellants are forced into the combustion chamber by compressed air, stored at 200
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The Hs293 has been variously described as a missile or as a boosted
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developed by
Germany during World War II. It was used to propel the
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of 517 kg, carrying 68 kg of propellants when full.
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The propellant injector in the combustion chamber is a simple
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Rocket engines using cold cycle hydrogen peroxide propellant
167:'. This was a 'cold cycle' engine; the peroxide acted as a
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92:The same engine was also used for the planned
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245:The more complex 'hot cycle' then burned a
83:with the centre of gravity of the missile.
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288:. Arms and Armour Press. pp. 23–25.
55:(HWK). Like other Walter engines it used
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327:Department of the Army (March 1953).
159:The engine's fuel chemistry used 80%
112:This engine was a development of the
53:Hellmuth Walter Kommanditgesellschaft
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286:German Secret Weapons of World War 2
387:"Rocket Engine, Walter HWK 109-507"
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338:. pp. 200–203. TM 9-1985-2.
232:was intended to attack armoured
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253:with precision moving parts.
155:Rocket motor, casing removed
139:, rather than anything more
446:RI-201 "Cold" Take Off Pack
329:"German Explosive Ordnance"
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451:RI-203 "Hot" Take Off Pack
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121:rocket-assisted take-off
552:Aircraft rocket engines
369:"The HWK 109-507 Motor"
163:hydrogen peroxide or '
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24:
521:Me.109 Climb Assister
208:The engine pod had a
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71:. It consisted of an
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173:calcium permanganate
51:It was produced by
542:HWK rocket engines
284:(1970). "Hs-293".
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133:combustion chamber
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516:HeimatschĂĽtzer IV
351:, pp. 25–26.
135:was made of mere
59:as a propellant.
57:hydrogen peroxide
33:liquid-propellant
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511:HeimatschĂĽtzer I
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336:Technical Manual
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81:line of thrust
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46:guided missile
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36:rocket engine
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373:Walter Werke
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314:Walter Werke
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295:085368-053-1
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282:Hogg, Ian V.
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190:(2,900
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181:bipropellant
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506:HWK 109-739
501:HWK 109-729
496:HWK 109-719
491:HWK 109-559
486:HWK 109-509
481:HWK 109-507
476:HWK 109-502
471:HWK 109-501
466:HWK 109-500
391:Smithsonian
349:Hogg (1970)
199:light alloy
114:HWK 109-500
108:Development
29:HWK 109-507
536:Categories
251:turbopumps
216:References
210:dry weight
141:refractory
137:mild steel
129:turbopumps
117:Starthilfe
73:SC500 bomb
69:glide bomb
161:high test
43:anti-ship
310:"Hs 293"
247:kerosene
183:engine.
461:RII-211
456:RII-203
230:Fritz-X
177:Z-Stoff
165:T-Stoff
63:Missile
23:missile
292:
147:Engine
102:Hs 296
98:Hs 295
94:Hs 294
40:Hs 293
31:was a
21:Hs 293
332:(PDF)
290:ISBN
228:The
175:or '
100:and
27:The
432:HWK
192:psi
188:bar
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424:e
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119:(
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