X-15 FLIGHT PLAN

December 18, 1968

Flight No.: 1-82-143 (Rev B.) Scheduled Date : December 20, 1968

Pilot: Major William J. Knight

Purpose : 1. High Altitude IR Background (24) - J. Kolf

2. High Altitude Sky Brightness (19) - J. Kolf

3. Fluidic Probe - R. Bogue

4. Fixed-Alpha Ball (31) - R. Bogue

Flight Planning Engineer: J. Kolf

Operations Engineer: V. Capasso

Instrumentation Engineer: D. Yount

 Launch: Hidden Hills #1 on a magnetic heading of 230°.

SAS Hi-Lo-Hi (8-4-8), YAR "OFF," Pitch-Roll and Yaw ASAS "OFF,"

Both BCS "ON," RAS "OFF," AUTO-CUTOFF "OFF," Ventral "OFF."

Launch Point Coordinates: 35° 56.5' N, 115° 39.4' W
 
 
 No. Time Alt Vel a q  Event
             
1. 0 45 790 2 145 Launch, light engine at 100% T. Rotate at a = 11° until q = 35°.
             
2. 28 50 1800 11 590 q = 35°. Maintain q = 35° until V = 3900 fps.
             
3. 68 98 3900 7 270 V = 3900 fps. Shutdown. Pushover to a = 0°. Maintain a = 0° to peak altitude. Turn RAS "ON," AUTO CUTOFF "ON." Engine Master "OFF."
             
4. 98 150 3550 0 22 Scanner "ON."
             
5. 130 162 3380 0 13 Peak altitude. Maintain q = 0° until dh = max. trim. (a» 15-17°). Maintain dh = max. trim until Hdot = -300 fps.
             
6. 158 150 3500 14 22 Scanner "OFF." RAS "OFF." AUTO CUTOFF "OFF."
             
7. 204 85 3650 17 450 Over Cuddeback.
             
8. 221 68 3200 13 790 Hdot = -300 fps. Begin left turn to » 165°. Vector to High-Key. Speed brakes as required.
             
9.           High Key - Check flap and "squat" circuit breakers in. Arm stick kicker and third skid. Engine Master Off. Window shade DOWN. WTR Master Switch "OFF."

NOTES:

1. q vernier will be set at 35°, a crosspointer will null at 15°.

2. Emergency Lakes: Silver, Cuddeback (3 Sisters - alternate)

3. Flight Duration: Approximately 9 minutes.

4. Flight plan based on 59,000# thrust at 100%. Engine #106.

Total burn time at 100% T (59,000#) = 85.5 sec.

 Launch wt = 34,900 Burnout Wt = 16,100#

CG = 19.7 CG = 14.6

5. In-flight jettison check. (Accounted for in wts. and burn time.)

6. Precision attitudes pre-set: Pitch = 0° (90.0)

Roll = 0° (90.0)

Heading = 230°

7. Timer set for 88-91 seconds.

 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.

5. Malfunction of both BCS.
 
 

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

(except Yaw ASAS)

 2a. 0 - 35 sec.

Engage ASAS. Pushover to a = 2° at 35 secs. Shutdown at V = 3900 fps. (h = 120K).
       
    2b. 35 sec. to shutdown

Engage ASAS. Pushover to a = 2°. Shutdown at V = 3900 fps.
       
    2c. After shutdown

Engage ASAS. Proceed as planned.
       
3. Ball Nose Failure  3. Same as 2. (Use An = 0.2g in place of a = 2°.)
       
4. Attitude Failure 4. Same as 2.
       
5. Inertial Failure 5. Same as 2. Shutdown at t = 66 sec.
       
6. Delayed Light 6. Rotate at a = 11° to An = 2.5g. Proceed as planned.
       
  INADVERTENT ENGINE SHUTDOWN:

00 - 42 sec. Hidden Hills

42 - 47 sec. Silver 

(or 3 Sisters)(2400 fps)

47 - 54 sec. Cuddeback (2650 fps)

54 - Up Edwards (3000 fps)

    

  J. L. Kolf, Head X-15 Research Projects Office
 
 

X-15 FLIGHT PLAN

November 20, 1968

Flight No.: 1-82-143 (Revised) Scheduled Date : November 26, 1968

Pilot: Major William J. Knight

Purpose : 1. WTR Experiment (20) - J. Kolf

2. High-Altitude IR Background (24) - J. Kolf

3. High Altitude Sky Brightness (19) - J. Kolf

4. Fluidic Probe - R. Bogue

5. Fixed-Alpha Ball (31) - R. Bogue

Flight Planning Engineer: J. Kolf

Operations Engineer: V. Capasso

Instrumentation Engineer: D. Yount

 Launch: Railroad Valley #2 on a magnetic heading of 183°.

SAS Hi-Lo-Hi (8-4-8), YAR "OFF," Pitch-Roll and Yaw ASAS "OFF,"

Both BCS "ON," RAS "OFF," Auto-Cutoff "OFF," Ventral "OFF."

Launch Point Coordinates: 38° 13.4' N, 116° 10.7' W

 Item Time Alt Vel. a q Event
 
             
1. 0 45 790 2 145 Launch, light engine at 100% T. Rotate at a = 11° until q = 40°.
             
2. 31 53 1900 11 570 q = 40°. Maintain q = 40° until shutdown.
             
3. 82 145 4950 9 54 Shutdown. Pushover to a = 0° and maintain a = 0° until peak altitude. (q = 0°). Turn RAS "ON," Auto Cutoff "ON." Engine Master "OFF."
             
4. 135 235 4300 0 1.5 WTR experiment switch to "UP." Maintain f and y» 0é.
             
5. 168 250 4180 0 .7 Peak altitude. Maintain q = 0° until a = 22°.
             
6. 194 240 4300 »11 1 WTR experiment switch to "DOWN."
             
7. 222 210 4500 22 4 a = 22°. Maintain a = 22° until An = 5g. Maintain An = 5g until Hdot » -300 fps. Turn scanner "OFF."
             
8.           1"g." Turn RAS "OFF."
             
9. 289 76 3700 16 720 Hdot = -300 fps. Pushover to maintain Hdot = -400 fps. Begin turn to » 200°. Open speed brakes to 35°.
             
10. 315 70 3000 9 630 Cuddeback. Vector to High-Key. Speed brakes as required.
             
11.           High Key - Check flap and "squat" circuit breakers in. Arm stick kicker and third skid. Engine Master Off. Window shade DOWN. 

NOTES:

1. q vernier will be set at 40°, a crosspointer will null at 22°.

2. Emergency Lakes: Mud, Grapevine, Racetrack, Cuddeback.

3. Flight Duration: Approximately 10 minutes.

4. Flight plan based on 59,000# thrust at 100%. Engine #106.

Total burn time at 100% T = 85.5 sec.

 Launch wt = 34,900 Burnout Wt = 16,100#

CG = 19.7 CG = 14.6

5. In-flight jettison check. (Accounted for in wts. and burn time.)

6. Precision attitudes pre-set: Pitch = 0° (90.0)

Roll = 0° (90.0)

Heading = 183°

7. Controlled launch time.

8. Timer set for 88-91 seconds.

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

2. Malfunction of any SAS channel or P-R ASAS.

3. Malfunction of inertial platform.

4. Malfunction of Ball Nose.

5. Malfunction of either BCS.

6. Malfunction of Precision Heading.
 
 

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

(except Yaw ASAS)

 2a. 0 - 35 sec.

Engage ASAS. Pushover to a = 2° at 35 secs. S.D. at 4950 fps. (Hmax = 150K). Fly a = 15° until Hdot = -100 fps., then maintain Hdot = -100 fps to 50 N.M. (M = 3.5, H = 80K).
       
    2b. 35 sec. to shutdown

Engage ASAS. Pushover to a = 2° and shutdown at V = 4950 fps. Use a = 15° if reentry is required. (Do not extend experiment)
       
    2c. After shutdown

Engage ASAS. Reenter at a = 15°. (Do not extend experiment.)
       
3. Ball Nose Failure  3a. 0 - 35 seconds

Pushover to 0g at 35 sec. and shutdown at V = 5000 fps. (Hmax = 130K). Fly a = 15° until Hdot = -200 fps, then maintain Hdot = -200 fps to 50 N.M. (M = 3.3, H = 80K).
       
    3b. 35 sec - shutdown

Pushover to 0g and shutdown at V = 4950 fps. Use q = 0 to -5° for reentry. (dhmax = -25°). Do not extend experiment.
       
    3c. After shutdown

Use q = 0 to -5° for reentry (dhmax = -25°). Do not extend experiment.
       
4. Attitude Failure 4. Perform gradual pushover at 32 sec. and proceed with 3a, b, or c as applicable. (Use a in place of q for reentry, use q = 400 psf in place of Hdot = -200 fps).
       
5. Inertial Failure 5. Proceed as planned. Shutdown at 82 seconds.
       
6. Delayed Light 6. Rotate to ANmax = 2.5g. Proceed as planned.
       
  INADVERTENT ENGINE SHUTDOWN:

00 - 37 sec. Railroad Valley

37 - 50 sec. Mud (2100 fps)

50 - 59 sec. Grapevine (2700 fps)

59 - 68 sec. Racetrack (3200 fps)

68 - 72 sec. Cuddeback (3800 fps)

72 - Up Edwards (4100 fps)

    

  Jack L. Kolf X-15 Research Projects Office
 
 

X-15 FLIGHT PLAN

November 12, 1968

Flight No.: 1-82-142 Scheduled Date : November 21, 1968

Pilot: Major William J. Knight

Purpose : 1. WTR Experiment (20) - J. Kolf

2. High-Altitude IR Background (24) - J. Kolf

3. High Altitude Sky Brightness (19) - J. Kolf

4. Fluidic Probe - R. Bogue

5. Fixed-Alpha Ball (31) - R. Bogue

Flight Planning Engineer: J. Kolf

Operations Engineer: V. Capasso

Instrumentation Engineer: D. Yount

 Launch: Smith Ranch #1 on a magnetic heading of 169°.

SAS Hi-Lo-Hi (8-4-8), Pitch-Roll and Yaw ASAS "OFF,"

Both BCS "ON," RAS "OFF," Ventral "OFF."

Launch Point Coordinates: 39° 30' N, 117° 11' W

Item Time Alt Vel. a q Event
 
             
1. 0 45 790 2 145 Launch, light engine at 100% T. Rotate at a = 11° until q = 36°.
             
2. 28 52 1850 11 566 q = 36°. Maintain q = 36° until burnout.
             
3. 84 148 5450 8 57 Burnout. (Shutdown at 5600 fps if burnout has not occurred.) Turn RAS "ON," auto cutoff "ON." Pushover to a = 0°. Eng. Master "OFF." Scanner "ON."
             
4. 133 235 4950 0 2 Extend experiment. Maintain f and ·y» 0°.
             
5. 172 250 4810 0 0.9 Peak altitude. Maintain q = 0° until a = 22°.
             
6. 199 240 4950 »11 1.5 Retract experiment.
             
7. 235 195 5200 22 10 Scanner "OFF." Maintain a = 22° until An = 5.0g. Turn RAS "OFF" and auto cutoff "OFF" at 1g.
             
8. 281 85 4750 22 765 An = 5g. Maintain An = 5g until Hdot = -400 fps.
             
9. 290 82 4150 18 680 Hdot = -400 fps. Pushover to maintain Hdot = -100 fps.
             
10. 338 75 3450 4 656 50 N.M. Begin gradual turn to Edwards.
             
11. 387 70 2700 4 510 Cuddeback. Pushover to Hdot = -400 fps. Vector to High-Key. Speed brakes as required.
             
12.           High Key - Check flap and "squat" circuit breakers in. Arm stick kicker and third skid. Engine Master Off. Window shade DOWN. 

NOTES:

1. q vernier will be set at 36°, a crosspointer will null at 22°.

2. Emergency Lakes: Mud, Grapevine, Cuddeback.

3. Flight Duration: Approximately 11 minutes.

4. Flight plan based on 60,500lb thrust at 100%. Engine #103.

Total burn time at 100% T (60,500lb) = 84.0 sec.
Launch wt = 34,700 Burnout Wt = 16,110lb
CG = 20.0 CG = 14.9

 5. Ground jettison check. (Accounted for in wts. and burn time.)

6. Precision attitudes pre-set: Pitch = 0° (90.0)
Roll = 0° (90.0)
Heading = 169°

7. Timer set for 88-91 seconds.

 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.

5. Malfunction of either BCS.

6. Malfunction of Precision Heading.
 
 

 ALTERNATE SITUATIONS AFTER LAUNCH:
 
 
Failure
  
Action
       
1. Radio or Radar 1. Proceed as planned.
       
2. Any Damper failure 2a. 0 - 35 sec.

Engage ASAS. Pushover to a = 2° at 35 secs. Proceed to burnout. (Vmax = 5750, Hmax = 142K). Maintain Hdot = -200 fps to 50 N.M. (M = 3.5, H = 75K).
       
    2b. 35 sec. to Burnout

Engage ASAS. Pushover to a = 2° at failure. Proceed to burnout. Use a = 15° if reentry is required. (Do not extend experiment)
       
    2c. After Burnout

Engage ASAS. Use a = 15° for reentry. Do not extend experiment.
       
3. Ball Nose Failure  3a. 0 - 35 seconds

Pushover to 0g at 35 sec. and proceed to burnout. (Vmax = 5800, Hmax = 105K). Fly level to M = 5, then Hdot = -200 fps to 50 N.M. (M = 3.0, H = 75K).
       
    3b. 35 sec - Burnout

Pushover to 0g when failure occurs. Proceed to burnout. Use q = 0° (dhmax = -25°) if reentry is required. Do not extend experiment.
       
    3c. After Burnout

Use q = 0 (dhmax = -25°) for reentry. Do not extend experiment.
       
4. Attitude Failure 4. Use a = 5° in place of q = 36° at 28 sec. Proceed with 3a, b, or c as applicable. (Use a = 22° for reentry).
       
5. Inertial Failure 5. Proceed as planned. After reentry, pushover when q has peaked and fly 650 q to Edwards.
       
6. Delayed Light 6. Use ANmax = 2.5g for rotation. Proceed as planned.
       
  INADVERTENT ENGINE SHUTDOWN:

00 - 43 sec. Smith Ranch

43 - 64.5 sec. Mud (2500 fps)

64.5 - 74.5 sec. Grapevine (3800 fps)

74.5 - 78 sec. Cuddeback (4600 fps)

78 - Up Edwards (4900 fps)

    

  Jack L. Kolf X-15 Research Projects Office