X-15 FLIGHT PLAN

August 29, 1968

Flight No.: 1-80-140 Scheduled Date: Sept. 12, 1968

Pilot: Maj. Wm. J. Knight

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

2. Horizon Scanner (17) - J. Welsh
3. Fixed Alpha Cone - R. Bogue
4. Fluidic Probe - R. Bogue

Flight Planning Engr: J. Kolf
Res. Project Engr: J. Welsh
Operations Engr: V. Capasso
Instrumentation Engr: 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.

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 = 36°.

2. 28 52 1850 11 566 q = 36°. Maintain q = 36° until burnout.

3. 88 148 5470 8 58 Burnout. (Shutdown at 5600 fps if burnout has not occurred.) Turn RAS "ON", auto cutoff "ON". Pushover to a = 0°.

4. 162 »247 4850 0 1 Extend experiment. Maintain q, f & ^·y» 0°.

5. 172 250 4810 0 .9 Peak altitude. Maintain q = 0° until a = 22°.

6. 205 240 4950 »12 1.5 Retract experiment.

7. 235 195 5200 22 10 a = 22 °. Maintain a = 22° until AN = 5.0g. Turn RAS "OFF" and auto-cutoff "OFF" at lg.

8. 281 95 4800 22 450 AN =5g. Maintain AN = 5g until = -400 fps.

Flight No.: 1-80-140 Scheduled Date: Sept. 12, 1968

Item Time Alt Vel a q Event

9. 290 82 4150 18 680 = -400 fps. Pushover to maintain » -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 = -400 fps. Vector to Hi-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 59,000# thrust at 100%. Engine #103. Total burn time at 100% T (59,000#) = 88.0 seconds.
Launch Wt. = 35,308# Burnout Wt = 16,110#
c.g. = 20.0 c.g. = 14.9

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

6. Precision attitudes preset: Pitch = 0.0° (90.0)

Roll = 0.0° (90.0)
Heading = 169°

GROUND RULES FOR NO LAUNCH:

1. Radio, radar, or TM malfunction.

2. Malfunction or any SAS channel.

3. Malfunction of inertial platform.

4. Malfunction of Ball Nose.

5. Malfunction of either BCS.

6. Malfunction of Precision Heading.

Flight No.: 1-80-140 Scheduled Date: Sept.. 12, 1968

ALTERNATE SITUATIONS AFTER LAUNCH:

Failure Action

1. Radio or radar 1. Proceed as planned.

2. Any Damper Failure 2a. 0 - 35 seconds
Engage ASAS. Pushover to a = 2° at 35 secs. Proceed to burnoutt. (Vmax = 5750, hmax » 142K). Maintain = -200 fps to 50 N.M. (M = 3.5, h = 75K).

2b. 35 secs - 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. Proceed to burnout. (Vmax = 5800, hmax = 105K). Fly level to M = 5, then = -200 fps to 50 N.M. (M = 3.0, h = 75K).

3b. 35 secs - 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.)

Flight No.: 1-80-140 Scheduled Date: Sept.. 12, 1968

ALTERNATE SITUATIONS AFTER LAUNCH:

Failure Action

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

0 - 46 sec. Smith Ranch

(2500 fps)

46 - 67.5 sec. Mud

(3800 fps)

67.5 - 79 sec. Grapevine

(4600 fps)

79 - 82 sec. Cuddeback

(4900 fps)

82 - Up Edwards

Approved by

J. R. Welsh, Chief, X-15

Research Projects Office


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.	88	148	5470	8	58	Burnout. (Shutdown at 5600 fps if burnout has not occurred.) Turn RAS "ON", auto cutoff "ON". Pushover to a = 0°.

4.	162	»247	4850	0	1	Extend experiment. Maintain q, f & ^·y» 0°.

5.	172	250	4810	0	.9	Peak altitude. Maintain q = 0° until a = 22°.

6.	205	240	4950	»12	1.5	Retract experiment.

7.	235	195	5200	22	10	a = 22 °. Maintain a = 22° until AN = 5.0g. Turn RAS "OFF" and auto-cutoff "OFF" at lg.

8.	281	95	4800	22	450	AN =5g. Maintain AN = 5g until = -400 fps.

9.	290	82	4150	18	680	= -400 fps. Pushover to maintain » -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 = -400 fps. Vector to Hi-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.

1.	Radio or radar	1.	Proceed as planned.

2.	Any Damper Failure	2a.	0 - 35 seconds Engage ASAS. Pushover to a = 2° at 35 secs. Proceed to burnoutt. (Vmax = 5750, hmax » 142K). Maintain = -200 fps to 50 N.M. (M = 3.5, h = 75K).

		2b.	35 secs - 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. Proceed to burnout. (Vmax = 5800, hmax = 105K). Fly level to M = 5, then = -200 fps to 50 N.M. (M = 3.0, h = 75K).

		3b.	35 secs - 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.