X-15 FLIGHT REQUEST

Flight No.: 3-41-64 A Scheduled Date: April 23, 1965

Pilot: Capt. Joe Engle

Purpose: To obtain data for the following programs:

1. Heat transfer experiment with surface distortion panels, and ablative tests - (Joe Watts)
2. Handling qualities evaluation - (Larry Taylor)
3. Boundary layer noise - (Tom Lewis)

Instrumentation Engineer: Febo Bartoli

Launch: Hidden Hills on a magnetic heading of 230°, MH-96 Adaptive, R.C. "OFF," BCS "OFF," heading vernier to "Standby," ventral off.

Launch point coordinates: 35° 58' N, 115° 40' 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. 19 46 1600 10 560 q = 20° - Maintain q = 20°.

3. 42 58 2600 4 840 Pushover to 0 "g."

4. 68 74 4400 0 1120 Reduce to minimum thrust.

5. 72 76 4600 0 1130 Extend speed brakes to 35° to maintain slow longitudinal acceleration. Increase a to maintain peak H = 78,000.

6. 93 78 5200 3 1270 Burnout. Maintain H = 78,000 ft.

7. 120 78 4000 6 760 Retract speed brakes, pushover to a = 0. Turn roll and yaw dampers to "OFF" and perform roll pulses.

8. 158 74 3400 0 675 Increase a to 6° and perform roll pulses.

9. 170 70 3200 6 720 Abeam Cuddeback, dampers to adaptive, speed brakes as required. Vector to High Key. Engine Master "OFF."

10. High Key - check flap and "Squat" circuit breakers in. Roll and yaw dampers to "OFF" and perform roll pulses at a = 0°, 6°, 12° at pilot's discretion. Calibrate pulse. Reengage dampers.

11. 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 0°.

2. Emergency lakes: Cuddeback.

3. Flight duration: Approximately 9 minutes.

4. Flight plan based on 58,750lb thrust engine.

Minimum thrust = 36,500lb.

Total burn time at 100% = 83.3 sec.

Launch Wt. = 33,750lb Burnout Wt. = 15,500lb

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.

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. Shutdown at 4500 fps, vector to High Key.

3.	Total Yaw Damper Fixed Gain in any axis	Proceed as planned.

4.	Attitude	Proceed as planned except use 4.5° a in place of 20° q at 19 seconds. Do not perform roll maneuvers.

5.	Ball Nose	Heading vernier to ^·y, proceed, use 1.6 g for rotation. After burnout, vector to High Key.

6.	Delayed engine light	Pushover to 0 g at H = 56,000 ft.

7. Inadvertent engine shutdown:

0 - 48 sec Hidden Hills

48 - 54 sec Cuddeback (3000 fps)

54 - Up sec Edwards (3400 fps)


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

2.	19	46	1600	10	560	q = 20° - Maintain q = 20°.

3.	42	58	2600	4	840	Pushover to 0 "g."

4.	68	74	4400	0	1120	Reduce to minimum thrust.

5.	72	76	4600	0	1130	Extend speed brakes to 35° to maintain slow longitudinal acceleration. Increase a to maintain peak H = 78,000.

6.	93	78	5200	3	1270	Burnout. Maintain H = 78,000 ft.

7.	120	78	4000	6	760	Retract speed brakes, pushover to a = 0. Turn roll and yaw dampers to "OFF" and perform roll pulses.

8.	158	74	3400	0	675	Increase a to 6° and perform roll pulses.

9.	170	70	3200	6	720	Abeam Cuddeback, dampers to adaptive, speed brakes as required. Vector to High Key. Engine Master "OFF."

10.						High Key - check flap and "Squat" circuit breakers in. Roll and yaw dampers to "OFF" and perform roll pulses at a = 0°, 6°, 12° at pilot's discretion. Calibrate pulse. Reengage dampers.

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