X-15 FLIGHT REQUEST

Flight No.: 1-61-101 Scheduled Date : October 8, 1965

Pilot: Capt. Joe Engle

Purpose : 1. MIT Horizon Photometer - (P. Chenoweth)

2. Pace Transducer - (Dean Webb)


Instrumentation Engineer - (Don Yount)

Launch: Delamar Lake #1 on magnetic heading 215°, SAS Hi-Lo-Hi (8-4-8), ASAS Armed, both BCS "ON," RAS "OFF," Auto Cutoff "OFF." Ventral off.

Launch Point Coordinates: 37° 18' N, 114° 36' W
 
 
 No. Time Alt Vel a q  Event
             
1. 0 45 790 0 145 Launch, light engine, increase to 100% T. Rotate at 11° a ( » 2g) until q = 38°.
             
2. 29 51 1850 11 620 q = 38°. Maintain q = 38°.
             
3. 83 144 5150 8 350 Shutdown. Pushover to a = 0°.
             
4. 95 170 4950 0 280 RAS "ON," Auto Cutoff "ON."
             
5. 106 200 4750 0 6 Comp b "ON."
             
6. 169 250 4430 0 0.6 Peak altitude. Extend speed brakes to 20°. Pitch RAS "OFF." Perform pitch oscillation at q» 2°/sec.
             
7. 220 200 4760 21 6 Terminate pitch oscillation at a = 21° (q» -5°). Set b switch to "b," dh = -25°. Pitch RAS "ON."
             
8. 240 170 4950 21 20 RAS "OFF," a = 21°. Maintain a = 21° until g = 4.0. Maintain g = 4.0 until Hdot = -600 fps.
             
9. 292 70 3850 12 1010 Hdot = -600 fps, pushover, maintain Hdot » -400 fps, extend speed brakes to 35°.
             
10. 300 65 3500 4 680 Abeam Cuddeback. Vector to High Key. Speed Brakes as required. Engine Master "OFF."
             
11.           High Key - check flap and "Squat" circuit breakers in.
             
12.           Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "OFF."

NOTES:

1. q vernier will be set at 38°, a crosspointer will null at 21°.

2. Emergency Lakes: Hidden Hills, Cuddeback.

3. Flight Duration: Approximately 10 minutes.

4. Flight plan based on 57,250# thrust engine - Engine #108.

Total burn time at 100% = 86 sec.

Launch wt. = 33,150#, Burnout wt. = 15,250#, 300# allowed for in-flight jettison.

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

2. Malfunction of any SAS channel.

3. Malfunction of inertial platform.

4. Malfunction of Ball Nose.

 ALTERNATE SITUATIONS AFTER LAUNCH:
 
 
Failure
  
Action
       
1. Radio or Radar   Proceed as planned.
       
2. Total Pitch Damper

Total Roll Damper

(Turn Yaw Damper OFF)

Total Yaw Damper

Failure to ASAS

 (a) 0 - 35 sec.

Pushover to 2° a at 35 sec., shutdown at 5150 fps. (Hmax » 150).
       
    (b) 35 sec. - S.D.

Pushover to 2° a when failure occurs. Shutdown at 5150 fps. RAS "ON." Reenter at -25° dh and 20° speed brakes.
       
    (c) After S.D.

Proceed as planned, reenter at 21° a.
       
3. Attitude Failure (a) 0 - 35 sec.

Use 6° a at 29 sec. instead of 38° q, then proceed with 2(a).
       
    (b) 35 sec. - S.D.

Same as 2(b).
       
    (c) After S.D.

Proceed as planned.
       
4. Ball Nose (a) 0 - 35 sec.

Same as 2(a) except use » 0.1g instead of 2° a.
       
    (b) 35 sec. - S.D.

Same as 2(b), except use » 0.1g instead of 2° a. Use q = -5 for reentry.
       
    (c) After S.D.

Use q = -5 for reentry.
       
      Pushover to zero g at H = 65,000 ft. (Hdot » 600 fps).
       
5. Delayed engine light   Proceed - shutdown at 5150 fps.
       
6. Inadvertent engine shutdown:

00 - 42 sec. Delamar

42 - 48 sec. (2300 fps)

48 - 68 sec. Hidden Hills (2400 fps)

68 - 72 sec. Cuddeback (3900 fps)

72 - Up Edwards (4200 fps)