X-15 FLIGHT REQUEST

Flight No.: 3-19-30 Scheduled Date: June 12, 1963

Pilot: Major R. Rushworth

Subject of test: Altitude Buildup, U.V. experiment and vertical tail pressure distribution investigation.
Launch: Delamar Lake on a magnetic heading of 212°, MH-96 Adaptive, R.C. "AUTO," BCS "ON," ·y switch "STANDBY." Ventral OFF..
 
 
 No. Time  Alt  V   a q            Event
             
1. 0 45 790 2 145 Launch, light engine, increase to 100%T, rotate to 2g.
             
2. 14 45 1400 11 420 2g - Maintain 2g until q = 33°.
             
3. 22 48 1600 10 510 q = 33° - Maintain q = 33°.
             
4. 78 130 5200 6 120 Shutdown. Maintain » 5°a.
             
5. 105 180 4950 5 16 ·y switch to "·y."
             
6. 154 220 4600 5 6 Peak altitude. Extend speed brakes to 20°. Maintain q = 0° until a = 20°. Maintain a = 20°.
             
7. 201 180 4900 20 16 ·y switch to "STANDBY."
             
8. 250 87 4500 20 550 4g - Maintain 4g until H-dot » -500 ft/sec. (Max reentry q = 630).
             
9. 253 84 4300 18 600 H-dot = -500 ft/sec, pushover to a » 3°, extend speed brakes to 35°, vector to high key. Reaction control switch "OFF." Engine master "OFF."
             
10. 304 58 2600 5 840 Perform steady sideslip (bmax = 4°). Speed brakes in when necessary.
             
11. 347 48 1300 5 320 Perform steady sideslip (bmax = 5°).
             
12. 400 35 900 5 300 Perform steady sideslip (bmax = 5°).
             
13.           High Key - speed brakes as required. Check flap and "Squat" circuit breakers in.
             
14.           Before APU shutdown, cycle flaps, set stabilizer trim to zero, turn all data "Off."

 

Notes:

1. q vernier will be set at 33°, a cross-pointer null at 20°.

2. Emergency lakes: Hidden Hills, Cuddeback.

3. Flight duration: Approximately 10 minutes.

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

Total burn time at 100% = 81 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 attitudes.

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 Delamar Lake.

3. For delayed engine light, proceed, shutdown at 5200 ft/sec.

4. For total FCS failure or failure to fixed gain in any axis prior to 40 sec., pushover to .2g at 40 sec. and reduce to 40% Thrust at 50 sec., proceed to Edwards, shutdown at 5000 ft/sec. (Hmax » 120,000).

5. For attitude failure, use 5° a at 22 sec., pushover to .2g at 40 sec., reduce to 40% Thrust at 50 sec., proceed to Edwards, shutdown at 5000 ft/sec.

6. For ball nose failure, pushover to .2g at 40 sec., and reduce to 40% Thrust at 50 sec., proceed to Edwards. For ball nose failure after burnout, maintain a = 0° during reentry until H-dot = -500 ft/sec..

7. For FCS failure, attitude failure, or ball nose failure from 40 sec., to shutdown, pushover to .2g at time of failure, and reduce to 40% Thrust at 50 sec., proceed to Edwards, shutdown at 5000 ft/sec.

8. For total failure or failure to fixed gain in pitch or yaw after shutdown, reaction controls to "ON," proceed as planned.

9. For total failure or failure to fixed gain in roll after shutdown, switch yaw damper to correspond to the roll damper, reaction controls to "ON," proceed as planned.

10. For inadvertent engine shutdown:
 

 0 - 45 sec Delamar

45 - 63 sec Hidden Hills (2700 ft/sec)

63 - 68 sec Cuddeback (3900 ft/sec)

68 - Up sec Edwards (4300 ft/sec)