X-15 Flight Request

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X-15 FLIGHT REQUEST

Flight No.: 3-65-96 Scheduled Date: October 31, 1967

Pilot: Major M. Adams

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

2. Solar Spectrum Measurement (29) - Bryant
3. Ultraviolet Plume (3c) - Bryant
4. Micrometeorite Collector (13) - Bryant
5. Traversing Probe (32) - Saltzman
6. Saturn Ablatives - Bryant
7. Tip Pod Camera (42a) - Bryant
8. Nose Gear Loads - McKay

Launch: Delamar #1 on a magnetic heading of 216°

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

Launch point coordinates: 37° 17.5' N, 114° 35.7' 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 = 38°. Fly BG null until shutdown. (q = 38° will be flown if BG malfunctions.)

2. 26 52 1800 11 535 q = 38°. Maintain q = 38° until shutdown.

3. 78 140 5100 7 70 Shutdown. Switch to PAI. Pushover to, and maintain a = 0° until peak altitude. Roll A/C ±10° at less than 5°/sec. Engine master OFF.

4. 91 170 4950 0 20 Micrometeorite switch to EXTEND. JPL experiment switch to ON.

5. 128 230 4550 0 2 Switch to comp. a.

6. 165 250 4360 0 .7 Peak altitude. Maintain q, F, & Y within ±2° until a = 20°.

7. 204 230 4550 15 2 Switch to ball nose a.

8. 225 200 4750 20 7 a = 20°. Maintain a = 20° until An = 5.0g. Switch to a/b. Maintain 5g until H dot = -500 fps. Micrometeorite to RETRACT. JPL experiment switch to OFF. Tip-Pod camera switch to ON.

9. 286 77 4050 16 822 H dot = -500 fps. Pushover to maintain H dot = -400. Extend speed brakes to 35°. Begin » 3g left turn to » 195°.

10. 302 74 3400 6 668 Cuddeback. Vector to Hi-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. Two (2) radiometer switches OFF.

NOTES:

1. q vernier will be set at 38°, a cross-pointer null at 20°.

2. Emergency lakes: Hidden Hills, Cuddeback.

3. Flight duration: Approximately 10 minutes.

4. Flight plan based on 60,000lb thrust at 100%. Engine #109.

Total burn time at 100% T. (60,000lb) = 80.1 seconds.

Launch wt = 33,313lb Shutdown wt = 15,900lb Burnout wt = 15,450lb

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

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

Roll = 0.0° (90.0)

Heading = 216°

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.

ALTERNATE SITUATIONS AFTER LAUNCH:

	Failure		Action

1.	Radio or radar	1.	Proceed as planned.

2.	ANY Damper Failure	2a.	0 - 35 seconds Switch to a/b. Pushover to a = 2° at 35 sec. Shutdown at V = 5100 fps. (Hmax = 160K.) Use a = 15° for reentry.

		2b.	35 sec. - Shutdown Switch to a/b. Pushover to a = 2° when failure occurs. Shutdown at V = 5100 fps. Use a = 15° for reentry.

		2c.	After Shutdown Reenter at a = 15°.

3.	Ball Nose Failure	3a.	0 - 35 seconds Switch to comp. a and a/b. Pushover to An = 0g at 35 secs. Shutdown at V = 5100 fps. (Hmax = 130K). Fly dh = -20° until H dot = -250 fps., then fly H dot = -250 to 50 mi. (H = 82K, M = 3.6).

		3b.	35 sec. - Shutdown Switch to comp. a and a/b. Pushover to An = 0g when failure occurs. Shutdown at V = 5100 fps. Use q = 0° for reentry up to 200K ft., then use q = -5°. (dHmax = -25°.)

		3c.	After Shutdown Switch to comp. a. Use q = -5° for reentry. (dHmax = -25°.)

4.	Attitude Failure	4.	Use a = 5° in place of q = 38° at 26 sec. Switch to a/b. Proceed with 3a, b, or c as applicable. (Use a for reentry, if reentry is required.)

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

6.	Delayed Light	6.	Rotate at An = 2.5g. Proceed as planned.

7.	Boost Guidance	7.	Fly q = 38° in place of BG null. Switch to a/b. Proceed as planned.