FIRST STEPS TOWARD SPACE - Smithsonian Institution Libraries

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14 May 1940: Reviewed layout for rocket of 100,000 kg thrust!
22 July 1940: Smooth test run of first lox pump (6 radial
stages) discharging at 150 atm abs [see Figure 4].
I August 1940: First test at a thrust of 1000 kg during 120
sec, both propellants fed by high-pressure pumps.
II August 1940: Decided to operate 100,000-kg thrust engine
from the very beginning with mercury coolant and steam
turbine with system-contained waste heat.
19 September 1940: 1000-kg thrust under stable operation for
5 min! [see Figure 5]. Measured data: t = 304 sec, p' = 1000
kg, p„ = 40 atm, pfuei = 55 atm, pox = 100 atm.
24 October 1940: First long duration test at combustion pressure
of 75 atm!
28 October 1940: Water-coolant velocity for combustion
chamber 31.8 m/sec, for nozzle 30.5 m/sec.
(02 = side: 2x7 holes of 2.8 mm 0; fuel-side: 1 x 7 holes
of 1.5 mm 0; por = 100 abs atm, pfuel =90 atm abs, ratio
fuel/O„=l:10)
First test: 300 sec, p' = 500 kg, p0 = 38 atm abs.
Second test: 240 sec, p' = 800 kg, p0 = 93 atm abs.
29 October 1940: (02 = side: 2x7 holes of 2.8 mm 0; fuelside:
1x3 holes of 3 mm 0; p0 = 110 abs atm, p(uei =90
atm abs); t = 40 sec, p' = 1000 kg, p0 = 80 atm abs.
7 November 1940: Water-coolant velocity for combustion
chamber 25.5 m/sec (2 paths), for nozzle 33.5 m/sec (1 path)
(02 = side: 2x7 holes of 2.8 mm 0, fuel = side: 1x3 holes
of 3 mm 0; pox= 110 atm, pfue, = 95 atm, p' = 7.25 cm 2 ).
First test: 45 sec, p'= 900 kg, p0 = 80 atm.
Second test: 66 sec, p' = 1000 kg, p0 = 83 atm.
17 November 1940: Water-coolant velocity for combustion
chamber 24.5 m/sec, for nozzle 32 m/sec.
First test: 40 sec, p' = 800 kg, p0 = 77 atm.
SMITHSONIAN ANNALS OF FLIGHT
Second test: 45 sec, p' = 1100 kg, p„ = 89 atm.
20 November 1940: Third test: 40 sec, p' = 1100 kg, p0 =
89 atm.
30 November 1940: Long duration test of 510 sec at p' =
800 kg and p0 = 90 atm.
14 February 1941: First combustion chamber for 100-kg thrust
with cast outer wall successfully tested! Test data: t = 120
sec, p' = 750 kg, p0 = up to 65 atm.
18 February 1941: %-liter thruster with combustion pressure
of 1 atm abs (gauge) cooled for first time by steam at
100 atm and 400° C! Test duration 8 min (copper coolant
tubing).
19 February 1941: %-liter copper thruster cooled by steam
at 125 atm and up to 450° C for 15 min.
26 February 1941: Test runs of %-liter steel thruster with
steam at
130 atm and 250° C for 2 x 5 min at p0 = 1 atm abs;
120 atm and 450° C for 2x 5 min at p0 = 1 atm abs;
130 atm and 250° C for 2 x 5 min at p0 = 1 atm abs;
130 atm and 410° C for 2x 5 min at p0 = 1.5 atm abs;
5 March 1941:
130 atm and 410° C for 2x 10 min at p0 = 31 atm abs;
130 atm and 410° C for 2 x 10 min at p0 = 31 atm abs;
7 March 1941: %-liter steel thruster, wound tubing with
circular cross-section and 1-mm wall thickness, run with
steam at 100 atm and 410° C for 5 min at 1 atm abs; test
run completely stable and without trouble.
18 March 1941: Firing of 1000-kg-thrust rocket engine (nozzle:
Cu-tubes, 1 mm thick, 2 paths; water coolant velocity
~ 45 m/sec; combustion chamber: Cu-tubes, 3.5 mm thick,
2 paths; water coolant velocity ~ 30 m/sec).
FIGURE 6.—Instruments and propellent lines during a test on 20 March 1941: chamber pressure
100 atm, thrust 1100 kg, duration 3.5 min.