X-15 FLIGHT REQUEST
Flight No.: 1-67-112 Scheduled Date : August 25, 1966

Pilot: John B. McKay

Purpose : 1. Horizon Scanner (17) - J. Welsh

2. Micrometeorite Collection (13) - R. Bryant

3. Rarefied Gas (16) - D. Webb

4. Electrical Loads - K. Anderson

5. Wing Pod Flutter - E. Kordes

Launch: Delamar Lake #1 on magnetic heading 215°. SAS HI-LO-HI (8-4-8), ASAS Armed, both BCS "ON, RAS "OFF," Heading Vernier to "Standby," Ventral off.

Launch Point Coordinates: 37° 18' N, 114° 36' W

Instrumentation Engineer: (Don Yount)
 
 No. Time Alt Vel a q  Event
             
1. 0 45 790 0 145 Launch, light engine at 75% T. Increase to 100% T. Rotate at a = 11° ( » 2g) until q = 38°.
             
2. 30 52 1850 11 565 q = 38°. Maintain q = 38°.
             
3. 84.5 144 5150 8 60 Shutdown. Pushover to a = 0°. Establish b = 0 and switch heading vernier to "·Y." Turn RAS "ON."
             
4. 95 170 5000 0 21 Micrometeorite experiment to "extend."
             
5. 168 250 4460 0 0.7 Peak altitude. Maintain q= -5° until a = 20°.
             
6. 237 180 4950 20 14 Micrometeorite experiment to "retract." a = 20°. Maintain a = 20° until Nz = 5.0 g. Turn RAS "OFF" at 1g. Heading vernier to standby.
             
7. 279 83 4450 20 740 Nz = 5.0. Maintain 5.0 g until Hdot = -800 fps (i.e. until q has peaked).
             
8. 286 75 4050 16 850 Hdot = -800 fps. Pushover to a» 3° to maintain Hdot » -600 fps. Extend speed brakes to 35°.
             
9. 296 65 3600 3 1140 Abeam Cuddeback. Vector to High Key. Speed brakes as required. Engine master off.
             
10.           High Key - check flaps and "squat" circuit breakers in. Arm stick kicker.

NOTES:

1. q vernier will be set at 38°, a crosspointer will null at 20°.

2. Emergency Lakes: Hidden Hills, Cuddeback.

3. Flight Duration: Approximately 10 minutes.

4. Flight plan based on 58,300# thrust at 100%. Engine #110.

Total burn time - 85.3 seconds.

 Launch wt. = 34,600# Burnout wt = 15,500#

c.g. = 21.2 c.g. = 18.2

In-flight Jettison Check (accounted for in weights and burn time.)

 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. BCS Malfunction.

 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 seconds

Pushover to 2° a at 35 secs. Shutdown at 5150 fps. (Hmax = 150K).
       
    (b) 35 seconds - shutdown

Pushover to 2° a when failure occurs. Reduce to minimum thrust, shutdown at 5150 fps.
       
    (c) After shutdown

Proceed as planned. Use 15° a for reentry.
       
3. Ball nose failure (a) 0 - 35 seconds

Pushover to zero g at 35 seconds. Shutdown at 5150 fps. Heading vernier to "·y."
       
    (b) 35 seconds - shutdown

Pushover to zero g when failure occurs. Reduce minimum thrust if necessary to reduce maximum altitude. Shutdown at 5150 fps. Heading vernier to "·y."
       
    (c) After shutdown

Heading vernier to "·y." Use q = -5° for entry (dh = -25°).
       
4. Attitude (a) 0 - 35 seconds

Use 9° a at 32 seconds instead of 38° q, then proceed with 3a.
       
    (b) 35 seconds - shutdown

Same as 2b.
       
    (c) After shutdown

Proceed as planned (Heading vernier remains in standby).
       
5. Delayed engine light   Proceed as planned.
       
  INADVERTENT ENGINE SHUTDOWN:

00 - 43 sec. Delamar

43 - 49 sec. ------ (2400 fps)

49 - 69 sec. Hidden Hills (2700 fps)

69 - 73 sec. Cuddeback (3900 fps)

73 - Up Edwards (4200 fps)

    
Approved by

E. J. Adkins, Chief

X-15 Research Project Office