Flight No.: 2-47-84 Scheduled Date : July 29, 1966
Pilot: Maj. W. J.
Knight
Purpose : 1. Star
Tracker Experiment (Welsh)
2. Pilot Altitude BuildupLaunch: Delamar Lake on magnetic heading of 214°3. Alternate Pitot Static System (Webb)
4. Base Drag Study (Saltzman)
SAS Hi-Lo-Hi (8-4-8), ASAS Armed, Both BCS "ON," RAS "OFF"
Heading Vernier to Standby, Ventral "OFF."
Star Tracker Vernier y = 214°, q = +5 (95)°, f = +2 (92)°
Launch point coordinates: 37° 18' N; 114° 36' W.
Instrumentation
Engineer - Bob Brush
No. | Time | Alt | V | a | q | Event |
1. | 0 | 45 | 790 | 2 | 145 | Launch, light engine at 75% T. Increase to 100% T. Rotate at a = 11° until q = 37°. |
2. | 32 | 53 | 1950 | 11 | 600 | q = 37°. Maintain q = 37°. |
3. | 81.8 | 135 | 5020 | 8 | 83 | Shutdown (burnout may occur). Pushover to a = 0°, heading vernier to ·y. |
4. | 117 | 200 | 4600 | 0 | 6 | Extend speed brakes to 20°. RAS "ON." Auto cutoff "ON." |
5. | 134 | 220 | 4450 | - | 2.9 | Begin Star Tracker experiment. |
6. | 162 | 230 | 4420 | - | 2.4 | Peak altitude. |
7. | 191 | 220 | 4450 | - | 2.9 | Terminate Star Tracker task. Experiment "OFF," RAS "OFF." Maintain q = 0 until a = 17°. |
8. | 209 | 200 | 4600 | - | 6 | a = 17°, maintain a = 17°-18° during entry (dh = -25°) until H-dot » -800 fps. Heading vernier to "STANDBY." |
9. | 276 | 70 | 3900 | 14 | 1020 | H-dot » -800 fps. Pushover to a » 3°. Maintain H-dot » -300 fps (Qmax » 1100, NZmax » 4.6g). |
10. | 307 | 60 | 3000 | 3 | 1000 | Cuddeback, vector to High Key. Speed brakes as required. |
11. | High Key - check flap and "squat" circuit breakers in, engine master "Off." Extend alternate pitot static tube. | |||||
12. | Before APU shutdown, cycle flaps, set stabilizer trim to zero, data off. Star Tracker to "cage," then "standby." |
Notes:
2. Emergency Lakes: Hidden Hills and Cuddeback.
3. Flight duration: Approximately 10 min.
4. Flight plan based on 60,600# thrust at 100%. Engine #106
Total burn time at 100% T. = 81.8 sec.
Launch wt. = 35,326 Burnout wt. = 16,754
In-flight jettison check (accounted for in wts. and burn time).
2. Malfunction of any SAS channel.
3. Malfunction of inertial system.
4. Malfunction of ball nose.
5. Malfunction of BCS.
6. Malfunction of Star Tracker.
7. Malfunction of RAS.
Failure Action
1. | Radio or Radar | Proceed as planned. | |
2. | Total
Pitch Damper
Total Roll damper (turn Yaw off) Total Yaw damper Failure to ASAS |
(a)
(b)
(c) |
0
- 35 sec.
Pushover to 2° a at 35 sec. Shutdown at 5300 fps. (Hmax » 150). 35 sec. - Shutdown Pushover to 2° a and reduce to minimum thrust when failure occurs; shutdown at 5300 fps. After Shutdown Proceed as planned, reenter at 15° a. |
3. | Ball Nose | (a)
(b)
(c) |
0
- 35 sec.
Pushover to zero g at 35 sec. Shutdown at 5300 fps. 35 sec. - Shutdown Pushover to zero g and reduce to minimum thrust when failure occurs. Shutdown at 5300 fps. After Shutdown Use q = 0 and dh = -25° for reentry; heading vernier to "·y." |
4. | Attitude | (a)
(b)
(c) |
0
- 35 sec.
Use 9° a at 32 sec. in place of 37° q, then proceed with 3(a). 35 sec. - Shutdown Same as 3(b). After Shutdown Proceed as planned. Horizon reference to be used to maintain q and f. |
5. | Delayed engine light | Proceed as planned. |
6. Inadvertent engine shutdown
0 - 43 sec Delamar
43 - 49 sec _______ (2400 fps)
49 - 68 sec. Hidden Hills (2700 fps)
68 - 72 sec. Cuddeback (3900 fps)
72 - Up sec Edwards
(4200 fps)