X-15 FLIGHT REQUEST

Flight No.: 1-45-72 Scheduled Date : March 17, 1964

Pilot: Major R. Rushworth

Purpose of Flight: Phase II Optical Degradation Experiment.

Launch: Delamar Lake on magnetic heading 214°, SAS Hi-Lo-Hi (8-4-8), ASAS "ARMED", both BCS "OFF", RAS "OFF". Heading vernier to "·y," Ventral OFF.

Launch Point Coordinates: 37° 18' N, 114° 36' W
 
 
 No. Time Alt Vel a q  Event
             
1. 0 45 790 2 145 Launch, light engine, increase to 100% T, rotate at 11° a until q = 30°.
             
2. 20 48 1600 11 500 q = 30°, maintain q = 30°.
             
3. 37 60 2300 5 600 Pushover to 0 g. (Hdot » 1000 fps).
             
4. 68 88 4500 0 580 Extend speed brakes to 20°.
             
5. 81 98 5700 0 580 Shutdown at 5700 fps.
             
6. 91 102 5550 0 450 Increase a to » 4°. (q» 4°). Maintain a» 4° to peak altitude.
             
7. 103 103 5450 4 410 Nellis - Peak altitude - (Maintain q and f within ±8°). Descend at 200 ft/sec to 70,000 ft.
             
8. 145 97 5050 4 470 Pahrump - (Maintain q and f within ±8°).
             
9. 148 96 5000 4 480 Retract speed brakes.
             
10. 258 72 3450 4 760 Pilot Knob - (Maintain q and f within ±8°).
             
11 270 70 3300 4 770 70,000 ft - maintain 70,000'.
             
12. 293 70 2950 4 620 Cuddeback - (Maintain q and f within ±8°). Test mode to "Landing" (q > 0°). Pushover to a» 2°, vector to High Key. Speed brakes as required. Engine Master "OFF."
             
13.           High key - Check flap and "Squat" circuit breakers in.
             
14.           Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "OFF."

 

NOTES:

1. q vernier will be set at 30°, a crosspointer will null at 0°.

2. Emergency Lakes: Hidden Hills and Cuddeback.

3. Flight Duration: Approximately 11 minutes.

4. Flight plan based on 59,300# thrust engine.

Total burn time at 100% = 84 sec.

Launch wt. = 32,800#, Burnout wt. = 15,000#.

 GROUND RULES FOR NO LAUNCH: 1. Radio, Radar or TM malfunction.

2. Malfunction of any SAS channel.

3. Malfunction of inertial platform.

4. Total Ball Nose failure.

5. APU gearbox pressurization malfunction.

6. "Test" malfunction.

 ALTERNATE SITUATIONS AFTER LAUNCH:
 
 
Failure
  
Action
       
1. Radio or Radar   Proceed as planned.
       
2. Total Pitch Damper   Maintain a > 0°, proceed as planned.
       
3. Total Yaw Damper   Proceed as planned except pushover to 2° a at 52,000 ft instead of zero g. Heading vernier to "Standby."
       
4. Total Roll Damper   Same as 3 except turn Yaw Damper off.
       
5. Attitude Failure   Use 5° a in place of 30° q. 
       
6. Ball Nose   Proceed as planned.
       
6. Delayed engine light   Pushover to zero g at H = 55,000 ft (Hdot » 1,000 fps).
       
7. Inadvertent engine shutdown:

00 - 45 sec. Delamar Lake

45 - 65 sec. Hidden Hills (2700 fps)

65 - 70 sec. Cuddeback (4200 fps)

70 - Up Edwards (4600 fps)