X-15 FLIGHT REQUEST

Flight No.: 3-29-48 Scheduled Date: May 21, 1964

Pilot: Milton O. Thompson

Purpose: Heat Transfer and skin friction experiments with the sharp upper vertical fin and boundary layer noise experiment.

Launch: Silver Lake #2 on a magnetic heading of 260°, MH-96 Adaptive, R.C. "OFF," BCS "OFF," heading vernier to "Standby," ventral off.

Launch point coordinates: 35° 07' N, 115° 15' W.

No. Time Alt V a q Event

1. 0 45 790 2 145 Launch, light engine, increase to 100%T. Rotate at 10° a until q = 20°.

2. 17 46 1500 10 495 q = 20° - Maintain q = 20°.

3. 27 49 2100 4 820 Pushover to 0 "g." (H-dot = 500 fps)

4. 42 55 2800 0 1170 Reduce to minimum thrust (» 40%). Modulate speed brakes to maintain slow longitudinal acceleration.

5. 46 56 2900 0 1180 Increase a to maintain H-dot » 50 ft/sec.

6. 95 58 3200 3 1250 Perform moderate rudder pulse.

7. 98 58 3220 3 1250 Roll to 60° left bank, increase a to » 7°. Turn to a heading of 240°.

8. 109 59 3300 7 1250 Heading = 240°, perform moderate rudder pulse, then roll wings level.

9. 120 61 3350 7 1200 Burnout (H-dot » +400 fps). Retract speed brakes, pushover to 0° a.

10. 139 66 2700 0 640 Peak altitude. Descend at » 200 ft/sec to maintain q constant at » 600 psf. Vector to High Key.

11. High Key. Check flap and "Squat" circuit breakers in.

12. Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "Off."

Notes:

1. q vernier will be set at 20°, a cross-pointer null at 7°.

2. Emergency lakes: Cuddeback.

3. Flight duration: Approximately 8 minutes.

4. Flight plan based on 59,200lb thrust engine.

Minimum thrust = 30,500lb.

Total burn time at 100% = 82 sec.

Launch Wt. = 33,000lb Burnout Wt. = 15,000lb

Ground Rules For No Launch:
1. Radio, Radar, or TM malfunction.

2. FCS malfunctions as indicated on Analyzer check list.

3. Malfunction of Ball Nose.

4. Malfunction of inertial platform attitudes.

5. APU gear box malfunction.

Alternate Situations After Launch:

	Failure	Action

1.	Radio or Radar	Proceed as planned.

2.	Total Pitch/Roll Damper	Turn Yaw OFF, maintain a > 0. Proceed as planned. Do not perform rudder pulse or Roll maneuver, vector to High Key after burnout.

3.	Total Yaw Damper Fixed Gain in any axis	Proceed as planned. Do not perform rudder pulse.

4.	Attitude	Proceed as planned except use 5.5° a in place of 20° q at 17 seconds. Do not perform Roll maneuver. Vector to High Key after burnout.

5.	Ball Nose	Heading vernier to "^·y," proceed, use 1.8g for rotation. Do not perform rudder pulse.

6.	Delayed engine light	Pushover to 0 g at H = 47,000 ft. (H-dot = 600 fps).

7. Inadvertent engine shutdown:

0 - 42 sec Silver

42 - 70 sec Cuddeback (2800 fps)

70 - Up sec Edwards (3000 fps)


1.	0	45	790	2	145	Launch, light engine, increase to 100%T. Rotate at 10° a until q = 20°.

2.	17	46	1500	10	495	q = 20° - Maintain q = 20°.

3.	27	49	2100	4	820	Pushover to 0 "g." (H-dot = 500 fps)

4.	42	55	2800	0	1170	Reduce to minimum thrust (» 40%). Modulate speed brakes to maintain slow longitudinal acceleration.

5.	46	56	2900	0	1180	Increase a to maintain H-dot » 50 ft/sec.

6.	95	58	3200	3	1250	Perform moderate rudder pulse.

7.	98	58	3220	3	1250	Roll to 60° left bank, increase a to » 7°. Turn to a heading of 240°.

8.	109	59	3300	7	1250	Heading = 240°, perform moderate rudder pulse, then roll wings level.

9.	120	61	3350	7	1200	Burnout (H-dot » +400 fps). Retract speed brakes, pushover to 0° a.

10.	139	66	2700	0	640	Peak altitude. Descend at » 200 ft/sec to maintain q constant at » 600 psf. Vector to High Key.

11.						High Key. Check flap and "Squat" circuit breakers in.

12.						Before APU shutdown, cycle flaps, set stabilizer trim to zero, data "Off."