X-15 FLIGHT REQUEST

Flight No.: 3-64-95 Scheduled Date: October 17, 1967

Pilot: Major Wm. J. Knight

Purpose: 1. Ames Boost Guidance (14) - Burke

2. Solar Spectrum Measurement (29) - Bryant
3. Ultraviolet Plume (3c) - Bryant
4. Micrometeorite Collector (13) - Bryant
5. Tip Pod Camera (42a) - Bryant

Launch: Smith Ranch #1 on a magnetic heading of 170°

MH-96 "Adaptive," Reaction Controls "Auto," BCS "ON," BG/b engaged, acom = 11°, PAI switch to "Heading," Ventral OFF.

Launch point coordinates: 39° 29.5' N, 117° 11.5' W.

Instrumentation Engineer: R. Borek

No. Time Alt V a q Event

1. 0 45 790 2 145 Launch, light engine at 100%T. Rotate at a = 11° until q = 37°. Fly BG null until burnout. (q = 37° will be flown if BG malfunctions.) Engage "roll-hold" after establishing 0° heading error.

2. 25 52 1650 11 450 q = 37°. Maintain q = 37° until burnout.

3. 84.4 150 5595 8 56 Burnout. (If burnout has not occurred, shutdown at 5700 fps.) Switch to PAI. Pushover to, and maintain a = 0°. Roll A/C ±10° at less than 5°/sec. Switch to PAI. Engine Master OFF.

4. 91 170 5500 0 26 Micrometeorite switch to EXTEND. JPL experiment switch to ON.

5. 121 230 5150 0 3 Switch to comp. a.

6. 176 273 4890 0 .2 Peak altitude. Maintain q, F, & Y within ±2° until a = 22°.

7. 231 230 5150 18 3 Switch to Ball Nose a.

8. 241 210 5200 22 6 a = 22°. Maintain a = 22° until An = 5g. Switch to a/b. Roll-hold OFF. (Qmax » 850 psf). Micrometeorite to "RETRACT." JPL switch to OFF. Pod camera switch to ON.

9. 292 95 5050 22 525 An = 5.0g. Maintain 5g until H dot = -400 fps.

10. 304 82 4350 17 710 H dot = -400 fps. Pushover to maintain H = 80K ft until 50 N. M.

11. 320 80 4000 4 695 50 N.M. Extend speed brakes to 20°. Start right turn to » 180°. Pushover to obtain H dot = -300 fps.

12. 365 70 3000 4 600 Cuddeback. Increase H dot to -400 fps. Vector to Hi-Key. Speed brakes as required.

13. High Key - Check flap and "squat" circuit breakers in. Arm stick kicker and third skid. Engine Master "OFF." (2) Radiometer switches OFF. Window Shade Down.

NOTES:

1. q vernier will be set at 37°, a cross-pointer null at 22°.

2. Emergency lakes: Mud, Ballarat, Cuddeback.

3. Flight duration: Approximately 12 minutes.

4. Flight plan based on 60,000lb thrust at 100%. Engine #103.

Total burn time at 100% T. (60,000lb) = 84.4 seconds.

Launch wt = 33,818lb Burnout wt = 15,341lb

c.g = c.g. =

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 = 170°

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

2. FCS malfunction as indicated on analyzer check list.

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 or failure to fixed gain	2a.	0 - 35 seconds Switch to a/b. Fly q = 30° in place of q = 37°. Pushover to a = 2° at 35 sec. Proceed to burnout. (Hmax = 135K, V = 5910.) Fly a = 15° to H dot = -200 fps. Then fly H dot = -200 fps to 50 N.M. (H = 85K, V = 3900)

		2b.	35 sec. - Burnout Switch to a/b. Pushover to a = 2° when failure occurs. Proceed to burnout. If reentry is required, use a = 15° to H = 250K. Above 250K, use a = 17°.

		2c.	After Burnout Use a = 17° for reentry.

3.	Ball Nose Failure	3a.	0 - 35 seconds Switch to comp. a. Pushover to 0g at 35 seconds. Proceed to burnout. (Hmax = 125K, V=5865). Fly H dot = -250 fps to 50 N.M. (H = 81K, V = 3700 fps.)

		3b.	35 sec. - Burnout Switch to comp. a. Pushover to 0g when failure occurs. Proceed to burnout. If reentry is required, use q = 0° to 220K, q = -5° to 250K, and q = -10° above 250K. (dHmax = -25°.)

		3c.	After Burnout Switch to comp. a. Use q = -10° for reentry. (dHmax = -25°.)

4.	Attitude Failure	4.	Use a = 5° in place of q = 37° at 25 sec. Switch to a/b. Proceed with 3a, b, or c as applicable. (Use a for reentry, if a reentry is required.)

5.	Inertial Failure	5.	Switch to a/b. Proceed as planned.

6.	Delayed Light	6.	Rotate to 2.5g. Proceed as planned.

7.	Boost Guidance	7.	Fly q = 37° in place of BG null at 25 sec. Proceed as planned.

INADVERTENT ENGINE SHUTDOWN:

0 - 43 sec Smith Ranch

43 - 68 sec Mud Lake (2500 fps)

68 - 73.5 sec Ballarat (4100 fps)

73.5 - 76 sec Cuddeback (4600 fps)

76 - Up sec Edwards (4800 fps)

Approved

E. J. Adkins, Head X-15 Project Office


1.	0	45	790	2	145	Launch, light engine at 100%T. Rotate at a = 11° until q = 37°. Fly BG null until burnout. (q = 37° will be flown if BG malfunctions.) Engage "roll-hold" after establishing 0° heading error.

2.	25	52	1650	11	450	q = 37°. Maintain q = 37° until burnout.

3.	84.4	150	5595	8	56	Burnout. (If burnout has not occurred, shutdown at 5700 fps.) Switch to PAI. Pushover to, and maintain a = 0°. Roll A/C ±10° at less than 5°/sec. Switch to PAI. Engine Master OFF.

4.	91	170	5500	0	26	Micrometeorite switch to EXTEND. JPL experiment switch to ON.

5.	121	230	5150	0	3	Switch to comp. a.

6.	176	273	4890	0	.2	Peak altitude. Maintain q, F, & Y within ±2° until a = 22°.

7.	231	230	5150	18	3	Switch to Ball Nose a.

8.	241	210	5200	22	6	a = 22°. Maintain a = 22° until An = 5g. Switch to a/b. Roll-hold OFF. (Qmax » 850 psf). Micrometeorite to "RETRACT." JPL switch to OFF. Pod camera switch to ON.

9.	292	95	5050	22	525	An = 5.0g. Maintain 5g until H dot = -400 fps.

10.	304	82	4350	17	710	H dot = -400 fps. Pushover to maintain H = 80K ft until 50 N. M.

11.	320	80	4000	4	695	50 N.M. Extend speed brakes to 20°. Start right turn to » 180°. Pushover to obtain H dot = -300 fps.

12.	365	70	3000	4	600	Cuddeback. Increase H dot to -400 fps. Vector to Hi-Key. Speed brakes as required.

13.						High Key - Check flap and "squat" circuit breakers in. Arm stick kicker and third skid. Engine Master "OFF." (2) Radiometer switches OFF. Window Shade Down.