Flight No.: 3-38-61 Scheduled Date: December 17, 1964
Pilot: Major Robert Rushworth
Purpose: To obtain
data for the following programs:
1. Skin Friction - (Darwin Garringer)2. Test of General Electric Ablative Material - (Joe Watts)
3. Non-uniform, 3-dimensional Flow Field Measurements - (Bob Quinn & Murray Palitz)
4. Landing Gear Door Modification Checkout - (Dick Rosecrans)
5. Boundary layer noise - (Tom Lewis)
Instrumentation
Engineer: Febo Bartoli
Launch: Hidden Hills on a magnetic heading of 230°, MH-96 Adaptive, R.C. "OFF," BCS "OFF," heading vernier to "Standby," ventral off.
Launch point coordinates:
35° 57' N, 115° 40' W.
No. | Time | Alt | V | a | q | Event |
1. | 0 | 45 | 790 | 2 | 145 | Launch, light engine, increase to 100%T. Rotate at 10° a until q = 20°. |
2. | 18 | 46 | 1550 | 10 | 620 | q = 20° - Maintain q = 20°. |
3. | 44 | 60 | 2750 | 4 | 850 | Pushover to 0 "g." |
4. | 70 | 77 | 4500 | 0 | 1020 | Reduce to minimum thrust. |
5. | 74 | 78 | 4700 | 0 | 1050 | Modulate speed brakes (» 35°) to maintain slow longitudinal acceleration. |
6. | 77 | 78 | 4800 | 0 | 1100 | H dot » +100 fps - increase a to » 3° to maintain H dot » 50 fps (q constant at » 1100 psf). |
7. | 101 | 81 | 5180 | 3 | 1100 | Burnout - Retract speed brakes, pushover to » 0° a, set up rate of descent of » 200 fps to maintain q constant at » 1050 psf. |
8. | 150 | 74 | 4200 | 3 | 1050 | Extend speed brakes to 35°, increase rate of descent to » 400 fps, maintain q constant at » 1050 psf. |
9. | 160 | 70 | 3800 | 3 | 1050 | Cuddeback - maintain q constant at » 1050 psf. |
10. | 175 | 59 | 3000 | 3 | 1050 | Vector to High Key (y » 190°). Speed brakes as required. Engine Master "OFF." |
11. | High Key - check flap and "Squat" circuit breakers in. Exp. Switch "OFF." | |||||
12. | Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "Off." |
Notes:
2. Emergency lakes: Cuddeback.
3. Flight duration: Approximately 7 minutes.
4. Flight plan based on 58,800lb thrust - Engine #106.
Minimum thrust = 29,000lb
Total burn time at 100% = 86 sec.
Launch Wt. = 33,750lb
Burnout Wt. = 15,550lb
2. FCS malfunctions as indicated on Analyzer check list.
3. Malfunction of Ball Nose.
4. Malfunction of
inertial platform.
Failure | Action | ||
1. | Radio or Radar | Proceed as planned. | |
2. | Total Pitch/Roll Damper | Turn Yaw OFF, maintain a > 0. Shutdown at 4500 fps, vector to High Key. | |
3. | Total
Yaw Damper
Fixed Gain in any axis |
Proceed as planned. | |
4. | Attitude | Proceed as planned except use 4.5° a in place of 20° q at 20 seconds. | |
5. | Ball Nose | Heading vernier to ·y, proceed, use 1.6 g for rotation. | |
6. | Delayed engine light | Pushover to 0 "g" at H = 58,000 ft. |
7. Inadvertent engine shutdown:
0 - 47 sec Hidden Hills
47 - 53 sec Cuddeback (2900 fps)
53 - Up sec Edwards (3300 fps)