X-15 FLIGHT REQUEST

Flight No.: 3-56-83 Scheduled Date: October 6, 1966

Pilot: William H. Dana

Purpose: 1. Micrometeorite Collector (13) - C. Cangie

2. Dual Channel Radiometer (3c) - C. Cangie
3. Tip Pod Accelerometer - E. Kordes
4. Precision Attitude Checkout - J. Kolf
5. Alert Computer Checkout (14) - M. Burke
6. Sky Brightness (19) - C. Cangie
7. Cockpit Display - L. Lytton

Launch: Smith Ranch #1 on a magnetic heading of 168°

MH-96 adaptive, reaction controls "auto," BCS "ON," q/b Engaged, acommand = 11°, H dot command = 0 fps, ventral off. PAI heading switch to "heading."

Launch point coordinates: 39° 30' N, 117° 10' W.

Instrumentation Engineer: Bob Borek

No. Time Alt V a q Event

1. 0 45 790 2 145 Launch, light engine at 75%T. Increase to 100% T. Rotate at a = 11° to q = 39°. .

2. 30 51 1950 11 650 q = 39°. Maintain q = 39°.

3. 81 140 5270 7 80 Burnout. Pushover to a = 0°. Switch to a/b. Maintain a = 0° to peak. Roll aircraft ±10° at less than 5°/second. Engine master off.

4. 91 170 5100 0 22 Micrometeorite switch to EXTEND.

5. 116 220 4750 0 3 Switch to comp. a.

6. 171 267 4445 0 0 Peak altitude. Switch to precision attitude. Hold F and q within ±2° until a = 22°.

7. 222 220 4700 15 3 Switch to ball nose a.

8. 228 210 4800 22 5 a = 22°. Maintain a = 22° until An = 5.0 g. Switch to a/b. Maintain 5 g until H dot = 0.

9. 247 170 5000 22 21 Micrometeorite switch to RETRACT.

10. 296 74 3900 15 880 H dot = 0. Pushover to a = 5° until aircraft comes level at » 80K. Maintain H » 80K.

11. 356 80 3000 3 390 50 N.M. Begin descent at H dot = -400 fps. Turn to a heading of 180°.

12. 405 65 2500 5 570 Abeam Cuddeback. Vector to Hi-Key. Speed brakes as required.

13. High Key - check flap and "squat" circuit breakers in. Arm stick kicker and 3rd skid. Window shade down. Experiment off. Radiometer off. Camera on.

NOTES:

1. q vernier will be set at 39°, a cross-pointer null at 22°.

2. Emergency lake: Mud, Grapevine, Cuddeback.

3. Flight duration: Approximately 11 minutes.

4. Flight plan based on 60,600lb thrust at 100%. Engine #110.

Total burn time at 100% T. (60,600lb) = 81.1 seconds.

Launch weight = 34,235lb. Burnout weight = 15,741lb

Ground jettison check.

5. Precision attitude set: Pitch = 0.0

Roll = 0.0

Heading = 168°

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		Proceed as planned.

2.	Any damper failure or failure to fixed gain	(a)	0 - 35 seconds Use q = 30° in place of q = 39°. Pushover to a = 2° at 35 seconds. Proceed to burnout (5600 fps, Hmax = 140K).

		(b)	35 sec - burnout Pushover to a = 2° when failure occurs. Proceed to burnout. If reentry is required, use a = 15° up to 250K. Then use a = 17°.

		(c)	After burnout Reenter using a = 17° and speed brakes = 20°.

3.	Ball nose failure	(a)	0 - 35 seconds Switch to comp a. Pushover to 0 g at 35 seconds. Proceed to burnout. (5575 fps, Hmax = 138K).

		(b)	35 secs - burnout Switch to comp a. Pushover to 0 g when failure occurs. Proceed to burnout. If reentry is required, use q = 0 to 200K and q = -5 to 250K. (dHmax = -25°)

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

4.	Attitude failure		Use a = 6° at 30 secs in place of q = 39°. Switch to a/b mode, proceed with 3a, b, or c as applicable.

5.	Inertial failure		Proceed as planned.

6.	Delayed light		Proceed as planned. Rotate at 2g.

INADVERTENT ENGINE SHUTDOWN:

0 - 43 sec Smith Ranch

43 - 66 sec Mud Lake (2550 fps)

66 - 75 sec Grapevine (4000 fps)

75 - 77 sec Cuddeback (4700 fps)

77 - Up sec Edwards (4900 fps)

Flight Plan Approved by (Johnny G. Armstrong) for

E. J. Adkins, Chief

X-15 Research Project Office


1.	0	45	790	2	145	Launch, light engine at 75%T. Increase to 100% T. Rotate at a = 11° to q = 39°. .

2.	30	51	1950	11	650	q = 39°. Maintain q = 39°.

3.	81	140	5270	7	80	Burnout. Pushover to a = 0°. Switch to a/b. Maintain a = 0° to peak. Roll aircraft ±10° at less than 5°/second. Engine master off.

4.	91	170	5100	0	22	Micrometeorite switch to EXTEND.

5.	116	220	4750	0	3	Switch to comp. a.

6.	171	267	4445	0	0	Peak altitude. Switch to precision attitude. Hold F and q within ±2° until a = 22°.

7.	222	220	4700	15	3	Switch to ball nose a.

8.	228	210	4800	22	5	a = 22°. Maintain a = 22° until An = 5.0 g. Switch to a/b. Maintain 5 g until H dot = 0.

9.	247	170	5000	22	21	Micrometeorite switch to RETRACT.

10.	296	74	3900	15	880	H dot = 0. Pushover to a = 5° until aircraft comes level at » 80K. Maintain H » 80K.

11.	356	80	3000	3	390	50 N.M. Begin descent at H dot = -400 fps. Turn to a heading of 180°.

12.	405	65	2500	5	570	Abeam Cuddeback. Vector to Hi-Key. Speed brakes as required.

13.						High Key - check flap and "squat" circuit breakers in. Arm stick kicker and 3rd skid. Window shade down. Experiment off. Radiometer off. Camera on.