 |
|||
|
|
|||
| ||||||||||
|
|  MIL-L-23822C(AS)
Ablation. The chamber or throat linings of the pro-
3.4.4
pulsion unit shall not ablate so as to emit solid particles exceeding
those defined in WS-4613.
Smoke emission. The rocket engine shall not emit
3.4.5
smoke or flame from any part of the engine other than from the nozzle
exits.
Thrust build-up. The time required to increase the
3.4.6
rocket engine thrust from activation of the propellant feed line cart-
ridge operated valves to 90 per cent (%) of rated boost thrust shall
be in accordance with Figure 1.
The thrust decay time interval from
3.4.7
Thrust tail-off.
cut-off of the rocket engine booster chamber thrust to 5% of the
rated booster chamber thrust shall be not greater than one and one-
half (1-1/2) seconds when operating to the requirements of Table I.
Thrust variation. The rocket engine thrust variation
3.4.8
from any source at either booster or sustainer thrust level shall be
as specified in Table I when measured in accordance with Figure 2.
Operating range.
3.4.9
Temperature range. The. rocket engine shall start,
3.4.9.1
operate and stop over the temperature range from minus (-) 65 F.
to plus (+) 140 F.
The rocket engine shall start,
Altitude range.
3.4.9.2
operate and stop over the altitude range from sea level to 100,000
feet.
The rocket engine shall be started and
Cartridges.
3.4.10
the booster chamber thrust shall be stopped by the activation of im-
pulse cartridges Mk 45 Mod 0 conforming to MIL-C-23661 which
will be Government-furnished equipment.
The rocket engine shall not leak pro-
Leakage.
3.4.11
pellants when tested at a static pressure of 620 psig minimum.
Environmental requirements.
3.5
11
|
|
Privacy Statement - Press Release - Copyright Information. - Contact Us |
Click
here for thousands of PDF manuals