X-15 FLIGHT REQUEST

Flight No.: 3-17-27 Scheduled Date: May 10, 1963

Pilot: Major R. Rushworth

Subject of test: Aerodynamic heating rates at high Mach number and high angle of attack, I.R. and U.V. experiments.

Launch: Hidden Hills on a magnetic heading of 180°, MH-96 Adaptive, Ventral off.

Launch point coordinates: 36° 20' N, 116° 11' W.

No. Time Alt V a q Event

1. 0 45 790 2 145 Launch, light engine, increase to 100%T, rotate to 2g.

2. 19 47 1600 11 410 2g - Maintain 2g until q = 30°.

3. 24 48 1800 10 530 q = 30° - Maintain q = 30°.

4. 32 55 2000 4 570 Pushover to 0 g.

5. 53 75 3400 0 625 Reduce thrust to » 80% (Pc » 500 psi).

6. 65 82 4000 0 630 Roll to 90° right bank.

7. 68 84 4300 0 660 Increase a to » 20°, (5 "g" maximum). Modulate throttle to maintain 4800 ft/sec.

8. 84 85 4800 20 720 Shutdown. Continue turn to »230°, pushover to » 8° a, roll wings level.

9. 115 90 3600 8 360 Pushover to » 5° a, switch yaw and roll dampers to fixed gain, perform dv pulses.

10. 154 87 3000 5 220 Switch roll and yaw dampers to Adaptive, vector to high key - speed brakes as required.

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

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

Notes:

1. q vernier will be set at 30°, a cross-pointer null at 20°.

2. Emergency lakes: Silver, Cuddeback.

3. Flight duration: Approximately 9 minutes.

4. Flight plan based on 59,000# thrust engine.

Total burn time at 100% = 80 sec.

Launch Wt. = 32,800lb Burnout Wt. = 15,000lb

Ground Rules For No Launch:
1. FCS malfunctions as indicated on Analyzer check list.

2. Malfunction of inertial platform.

3. Malfunction of ball nose.

4. APU gear box pressurization malfunction.

Alternate Situations After Launch:
1. For radio or radar failure, proceed as planned.

2. If engine light cannot be accomplished within 30 sec., jettison propellants and land at Hidden Hills.

3. For delayed engine light, proceed as planned except perform pushover to zero g at 52,000 ft.

4. For ball nose failure, vector to Edwards for landing.

5. For malfunction of inertial platform, proceed as planned at pilot's discretion.

6. For MH-96 failure:

Failure Action

(a) Total Pitch Extend speed brakes to 20°, proceed direct to Edwards, do not exceed 15° a, shutdown at 4500 ft/sec.

(b) Total Roll Same as (a) except turn yaw damper off.

Yaw to fixed gain

Pitch to fixed gain

(d) Roll to fixed gain Turn yaw damper to fixed gain, proceed as planned.

7. For inadvertent engine shutdown:

0 - 35 sec Hidden Hills

35 - 52 sec Silver (2200 ft/sec)

52 - 65 sec Cuddeback (3300 ft/sec)

65 - Up sec Edwards (4100 ft/sec)


1.	0	45	790	2	145	Launch, light engine, increase to 100%T, rotate to 2g.

2.	19	47	1600	11	410	2g - Maintain 2g until q = 30°.

3.	24	48	1800	10	530	q = 30° - Maintain q = 30°.

4.	32	55	2000	4	570	Pushover to 0 g.

5.	53	75	3400	0	625	Reduce thrust to » 80% (Pc » 500 psi).

6.	65	82	4000	0	630	Roll to 90° right bank.

7.	68	84	4300	0	660	Increase a to » 20°, (5 "g" maximum). Modulate throttle to maintain 4800 ft/sec.

8.	84	85	4800	20	720	Shutdown. Continue turn to »230°, pushover to » 8° a, roll wings level.

9.	115	90	3600	8	360	Pushover to » 5° a, switch yaw and roll dampers to fixed gain, perform dv pulses.

10.	154	87	3000	5	220	Switch roll and yaw dampers to Adaptive, vector to high key - speed brakes as required.

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

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