X-15 FLIGHT REQUEST

Flight No.: 3-15-25 (Revised)* Scheduled Date: April 17, 1963

Pilot: Joseph A. Walker

Subject of test: Heat Transfer and Local Flow at high Mach number and low angle of attack. I. R. Experiment

Launch: Hidden Hills on a magnetic heading of 230°, MH-96 FCS Adaptive, MH-96 RC "OFF," BCS "ON," 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. 15 47 1500 10 480 Maintain 2g until q = 20°.
             
3. 37 57 2400 3 750 Push over to 0g.
             
4. 61 70 4000 0 1090 Increase a to 2°.
             
5. 74 73 4900 2 1400 Throttle back to 40% T, modulate speed brakes to maintain slow longitudinal acceleration.
             
6. 86 75 5050 2 1400 Burnout. Retract speed brakes. Perform gradual left and right side slips from 5,000 ft/sec to 3,500 ft/sec. bmax = 3°. Perform pushover-pullup maneuvers (a » 2 - 0 - 2).
             
7. 155 65 3500 3 1100 Vector to high key, speed brakes as required. Engine master "OFF."
             
8.           High Key. Check flap and "Squat" circuit breakers in.
             
9.           Before APU shutdown, cycle flaps, set stabilizer trim to zero, turn all data "Off."

*Revision due to change in predicted thrust levels. Notes: 1. q vernier will be set at 20°, a cross-pointer null at 2°.

2. Emergency lake: Three Sisters

3. Flight duration: Approximately 10 minutes.

4. Flight plan based on 59,500# thrust engine (27,100# for 40%).

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 pressure system malfunction.
 

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

2. For FCS failure to fixed gain in Yaw, proceed as planned.

For FCS failure to fixed gain in Roll, set Yaw to fixed, proceed.

For FCS failure to fixed gain in Pitch, proceed.

3. For total yaw damper failure, proceed, maintain a > 0, extend speed brakes to 20° at 4,000 ft/sec. Do not perform side slip maneuvers. Shutdown at 5,000 ft/sec.

For total roll damper failure, set Yaw damper "OFF," proceed, maintain a > 0, extend speed brakes to 20° at 4,000 ft/sec. Do not perform side slip maneuvers. Shutdown at 5,000 ft/sec.

For total pitch damper failure, proceed as planned.

4. For ball nose failure, rotate at 2g, proceed as planned, maintain H-dot » 200 ft/sec (» .8g) at 63 seconds. Do not perform side slip maneuvers.

5. For attitude failure, use 4° a in place of 20° q, proceed as planned.

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

7. For delayed engine light, proceed, pushover to zero g at 55,000 feet.

8. For inadvertent engine shutdown:
 

 0 - 39 sec Hidden Hills

39 - 60 sec Three Sisters

60 - Up sec Edwards


X-15 FLIGHT REQUEST

Flight No.: 3-15-25 Scheduled Date: April 16, 1963

Pilot: Joseph A. Walker

Subject of test: Heat Transfer and Local Flow at high Mach number and low angle of attack. I. R. Experiment

Launch: Hidden Hills on a magnetic heading of 230°, MH-96 FCS Adaptive, MH-96 RC "OFF," BCS "ON," 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. 17 47 1500 10 480 Maintain 2g until q = 20°.
             
3. 39 57 2400 3 750 Push over to 0g.
             
4. 63 70 4000 0 1090 Increase a to 2°.
             
5. 74 73 4900 2 1400 Throttle back to 50% T, modulate speed brakes to maintain slow longitudinal acceleration.
             
6. 87 75 5050 2 1400 Burnout. Retract speed brakes. Perform gradual left and right side slips from 5,000 ft/sec to 3,500 ft/sec. 
             
7. 155 65 3500 3 1100 Vector to high key, speed brakes as required. Engine master "OFF."
             
8.           High Key. Check flap and "Squat" circuit breakers in.
             
9.           Before APU shutdown, cycle flaps, set stabilizer trim to zero, turn all data "Off."

 
 
 

Notes:

1. q vernier will be set at 20°, a cross-pointer null at 2°.

2. Emergency lake: Three Sisters, Cuddeback

3. Flight duration: Approximately 10 minutes.

4. Flight plan based on 58,500# thrust engine (33,500# for 50%).

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 pressure less than 5.6 psi.
 

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

2. For FCS failure to fixed gain in Yaw, proceed as planned.

For FCS failure to fixed gain in Roll, set Yaw to fixed, proceed.

For FCS failure to fixed gain in Pitch, proceed.

3. For total yaw damper failure, proceed, maintain a > 0, extend speed brakes to 20° at 4,000 ft/sec.

For total roll damper failure, set Yaw damper "OFF," proceed, maintain a > 0, extend speed brakes to 20° at 4,000 ft/sec.

For total pitch damper failure, proceed as planned.

4. For ball nose failure, rotate at 1.5g, proceed as planned, maintain H-dot » 200 ft/sec at 63 seconds.

5. For attitude failure, use 4° a in place of 20° q, proceed as planned.

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

7. For delayed engine light, proceed, pushover to zero g at 57,000 feet.

8. For inadvertent engine shutdown:
 

 0 - 39 sec Hidden Hills

39 - 50 sec Three Sisters

50 - 65 sec Cuddeback

65 - Up sec Edwards