X-15 FLIGHT REQUEST

Flight No.: 1-52-82 Scheduled Date : December 22, 1964

Pilot: John B. McKay

Purpose : To obtain data for the following programs:

1. Honeywell inertial system check - (Mel Burke)

2. MIT Horizon Photometer - (Al Covington)

3. Air Density - (Jack Ehrenberger)

4. Nortronics Sky Brightness - (Lovic Thomas)

5. RAS Modification checkout - (Wilt Lock)

6. Pilot Altitude Buildup

Instrumentation Engineer - (Don Yount)

Launch: Delamar Lake #1 on magnetic heading 214°, 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 2 145 Launch, light engine, increase to 100% T. Rotate at 10° a ( » 2g) until q = 28°.
             
2. 25 48 1700 10 570 q = 28°. Maintain q = 28°.
             
3. 83 121 5200 6 170 Shutdown. Pushover to a = 0°. RAS "ON," Auto Cutoff "ON."
             
4. 145 180 4760 0 16 Peak altitude. Extend speed brakes to 20°. Maintain q» 0° to 20° a.
             
5. 194 142 4950 20 65 a = 20° - Maintain a = 20° until Hdot = -600 fps.
             
6. 208 120 4850 20 150 RAS "OFF."
             
7. 230 90 4300 20 480 Hdot = -600 fps, pushover, maintain Hdot » -450 fps, extend speed brakes to 35°. (Max reentry g » 3.0).
             
8. 288 60 2700 3 825 Cuddeback. Vector to High Key, speed brakes as required. Engine Master "OFF."
             
9.           High Key - check flap and "Squat" circuit breakers in.
             
10.           Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "OFF."

 

NOTES:

1. q vernier will be set at 28°, a crosspointer will null at 20°.

2. Emergency Lakes: Hidden Hills, Cuddeback.

3. Flight Duration: Approximately 10 minutes.

4. Flight plan based on 57,000# thrust engine - Engine #107.

Total burn time at 100% = 87.5 sec.

Launch wt. = 33,450#, Burnout wt. = 15,250#.

 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 - 40 sec.

Pushover to 2° a and extend speed brakes to 35° at 40 sec., shutdown at 5000 fps. Retract speed brakes after shutdown. (Hmax » 110K).
       
    (b) 40 sec. - S.D.

Pushover to 2° a, and extend S.B. to 35° when failure occurs: shutdown at 5000 fps, RAS "ON." Reenter at 15° a and 20° speed brakes.
       
    (c) After S.D.

Proceed as planned, reenter at 15° a.
       
3. Attitude Failure (a) 0 - 40 sec.

Use 6° a at 25 sec. instead of 28° q, then proceed with 2 (a).
       
    (b) 40 sec. - S.D.

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

Proceed as planned.
       
4. Ball Nose (a) 0 - 40 sec.

Same as 2 (a) except use » 0.1 g instead of 2° a.
       
    (b) 40 sec. - S.D.

Same as 2 (b), except use » 0.1 g instead of 2° a. Use q = 0 for reentry.
       
    (c) After S.D.

Use q = 0 for reentry.
       
5. Delayed engine light   Proceed - shut down at 5200 fps.
       
6. Inadvertent engine shutdown:

00 - 46 sec. Delamar

46 - 69 sec. Hidden Hills (2700 fps)

69 - 73 sec. Cuddeback (4100 fps)

73 - Up Edwards (4400 fps)