Flight No.: 3-59-88 Scheduled Date: May 8, 1967
Pilot: William Dana
Purpose: 1. PCM System Checkout - B. Borek
Launch: Silver Lake #2 on a magnetic heading of 238°2. Coldwall Heat Transfer - J. Watts3. Step Panel Heat Transfer - J. Watts
4. Boost Guidance Checkout - M. Burke
5. Energy Management Checkout - M. Burke
6. Tip Pod Accelerometer - E. Kordes
7. Sonic Boom Study - N. McLeod
8. Horizontal Tail Loads - R. Meneely
MH-96 "Adaptive," Reaction Controls "OFF," BCS "OFF," BG engaged, acommand = 10°, PAI switch to "Heading," Ventral OFF.
Launch point coordinates: 35° 35' N, 115° 57' W.
Instrumentation
Engineer: Bob Borek
No. | Time | Alt | V | a | q | Event |
1. | 0 | 45 | 790 | 2 | 145 | Launch, light engine at 100%T. Rotate at a = 10° to q = 20°. |
2. | 19 | 46 | 1650 | 10 | 600 | q = 20°. Maintain q = 20° until h = 55K. (H dot » 670 fps). |
3. | 37 | 55 | 2450 | 4 | 900 | h = 55K. Pushover to "0" g. Maintain "0" g until H dot » 100 fps. |
4. | 65 | 67 | 4100 | 0 | 1350 | At q » 1350 psf, reduce to Tmin (» 50%T). Increase a to maintain H dot » 50-100 fps. (a » 3°). |
5. | 68 | 68 | 4350 | 3 | 1450 | Open speed brakes to maintain small (» 0.2g) positive acceleration. Push panel ejection button. (q and M » stable). |
6. | 103 | 71 | 4650 | 2 | 1500 | Burnout. Reduce speed brakes to » 20° and maintain H dot = -100 to -150 fps. Switch to a/b and roll rate. Begin gradual turn towards Edwards. |
7. | 141 | 70 | 3250 | 3 | 740 | Cuddeback. Push over until H dot = -600 fps and perform 10° pullup for tail loads. Vector to Hi-Key. Speed brakes as required. |
8. | High Key. Check flap and "squat" circuit breakers in. Arm stick kicker and third skid. Engine Master "OFF." Window shade down. |
NOTES:
2. Emergency lake: Cuddeback.
3. Flight duration: Approximately 9 minutes.
4. Flight plan based on 59,000lb thrust at 100%. Engine #103.
Flight plan based on 33,500lb thrust at 49.5%.
Total burn time at 100% T. (59,000#) = 86.2 seconds.
Launch wt = 33,664lb Burnout wt = 14,973lb
c.g = 22.3 c.g. = 22.4
5. Ground jettison check (Accounted for in wts. and burn time).
6. Precision attitudes preset: Pitch = 20° (110.0)
Roll = 0° (90.0)
Heading = 238°
2. FCS malfunction as indicated on analyzer check list.
3. Malfunction of inertial platform.
4. Malfunction of
ball nose.
Failure | Action | ||
1. | Radio or radar | Proceed as planned. | |
2. | Total Pitch Damper | Pushover to a = 2° at 40 secs. Shutdown at 4000 fps. Eject blow-off panel. Vector to Hi-Key. | |
3. | Total Roll Damper | Same as 2. (Turn Yaw Damper OFF). | |
4. | Total Yaw Damper | Same as 2. | |
5. | Failure to Fixed Gain | Proceed as planned. | |
6. | Ball Nose Failure | Switch to comp. a. Rotate at 2g. Pushover to An » 0.4g at 40 sec. Shutdown at 4000 fps. Eject blow-off panel. Vector to Hi-Key. | |
7. | Attitude Failure | Use a = 5° in place of q = 20° at 19 sec. Same as 2. (If only q vernier, switch to PAI and proceed as planned.) | |
8. | Inertial Failure | Without
radio contact:
Same as 2. (Shutdown at 64 sec.) With radio contact: Proceed as planned. |
|
9. | Delayed Light | Rotate at 2g. Pushover at h = 50K. Proceed as planned. |
INADVERTENT ENGINE SHUTDOWN:
0 - 44 sec Silver
44 - 47 sec Cuddeback (2800 fps)
47 - Up sec Edwards
(3000 fps)
Approved (J. G. Armstrong, for)
E. J. Adkins, Head X-15 Project Office