X-15 FLIGHT REQUEST

Flight No.: 3-10-19 (Revised) Scheduled Date: October 3, 1962

Pilot: Major R. A. Rushworth

Subject of test: Pilot checkout and investigation of "ventral off" stability.

Launch: Delamar on a magnetic heading of 205°.

MH-96 FCS on Adaptive Damper.
 
 
 No. Time  Alt  V   a q            Event
             
1. 0 45 790 1.5 145 Launch - light engine, advance to 100%T. Rotate to a = 10°.
             
2. 20 45 1620 10 625 Maintain 10° a until q = 20°.
             
3. 48 60 2900 3 900 Reduce power to 50%T (Pc » 345) and extend speed brakes.
             
4. 65 75 3300 4 575 Push over to a » 2° (g » .2).
             
5. 104 98 4800 2 360 Pullup to a » 5°.
             
6. 108 100 5000 6 365 Shutdown, pushover to a = 2°, perform dv pulse.
             
7. 118 103 4900 2 340 Retract speed brakes, perform dv pulse.
             
8. 133 102 4820 2 330 Yaw damper off, roll to fixed gain. Perform dv pulse.
             
9. 142 98 4800 2 365 Pullup to a = 10°, perform dv pulse.
             
10. 158 93 4600 10 460 Pullup to a = 15°, perform dv pulse.
             
11. 174 93 4150 15 365 At pilot's discretion, pullup to a = 18°, perform dv pulse.
             
12. 184 97 3700 - - Perform dv pulses (a = 10° to 15°). Do not exceed dh(avg) = 28° during deceleration.
             
13. 270 97 3000 - 160 Vector to High Key, speed brakes as required. Perform dv pulses.
             
14. 365 62 2000 - 340 Retract speed brakes, (speed brakes not recommended 2 > M > 1). Reengage dampers. Engage f hold, turn 10° left (y » 195°) and release stick forces.
             
15.           Engage a hold, pushover to a = 0° and release stick forces. Jettison, (H2O2 "OFF").
             
16.           High Key, pressurize tanks below 20,000 ft., push to test ball nose.
             
17.           After touchdown, disengage MH-96 FCS.
             
18.           Before APU shutdown, cycle controls, retract flaps, trim stabilizer zero, data off.

Notes:

1. q vernier will be set at 20°, a cross-pointer null at 15°.

2. Duration of flight approximately 11 minutes.

3. Emergency lakes: Hidden Hills and Cuddeback.

 Ground Rules for No Launch: 1. MH-96 FCS malfunction as indicated on original flight request.

2. Inertial platform malfunction in attitudes.

3. Ball nose malfunction.

4. Radio or radar failure.

 Alternate Situations Before Launch: 1. MH-96 FCS malfunction in auto-pilot on reaction controls - proceed but do not operate affected FCS modes. Alternate Situations After Launch: 1. If engine does not light within 30 sec. after launch, jettison propellants and land at Delamar.

2. For delayed engine light, proceed as planned, maintain less than 3 g during rotation.

3. For radio, radar, or microwave failure, proceed as planned.

4. For adaptive damper failure to fixed gain in any axis, proceed as planned but do not use hold modes in affected axis.

5. For total yaw damper failure, proceed as planned.

6. For total roll damper failure, disengage yaw damper, return to Edwards, make da pulses at pilot's discretion.

7. For total pitch damper failure, proceed as planned, fly 1 g after burnout, perform pulses at pilot's discretion.

8. For inadvertent engine shutdown:

 0 - 48 sec Delamar.

48 - 88 sec Hidden Hills.

88 - 95 sec Cuddeback.

95 - Up sec Edwards.
 
 
 
 

X-15 FLIGHT REQUEST

Flight No.: 3-10-19 Scheduled Date: October 2, 1962

Pilot: Major R. A. Rushworth

Subject of test: Pilot checkout and investigation of "ventral off" stability.

Launch: Mud Lake on a magnetic heading of 177°.

MH-96 FCS on Adaptive Damper.
 
 
 No. Time  Alt  V   a q            Event
             
1. 0 45 790 1.5 145 Launch - light engine at 75%T, decrease power to 50%T. Rotate to a = 7°.
             
2. 53 45 1750 7 650 Maintain 7° a until q = 25°.
             
3. 95 75 2600 6 360 Push over to a » 2° (g » .25).
             
4. 136 100 4700 2 360 Burnout. Yaw damper off, roll to fixed gain. Perform dv pulse.
             
5. 158 102 4620 2 290 Pullup to a = 10°, perform dv pulse.
             
6. 173 103 4570 10 265 Pullup to a = 15°, perform dv pulse.
             
7. 188 102 4250 15 225 Pushover to a = 13°, perform dv pulse.
             
8. 200 104 3950 13 180 At pilot's discretion, pullup to a = 18°, perform dv pulse.
             
9. 210 105 3700 - 150 Perform dv pulses (a = 10° to 15°). Do not exceed dh(avg) = 28°.
             
10. 270 104 3000 - 120 Vector to High Key, speed brakes as required. Reengage dampers.
             
11. 370 67 2000 - 350 Retract speed brakes (speed brakes not recommended 2 > M > 1). Engage f hold, turn 10° left (y » 167°) and release stick forces.
             
12.           Engage a hold, pushover to a = 0° and release stick forces. Jettison, (H2O2 "OFF").
             
13.           High Key, pressurize tanks below 20,000 ft., push to test ball nose.
             
14.           After touchdown, disengage MH-96 FCS.
             
15.           Before APU shutdown, cycle controls, retract flaps, trim stabilizer zero, data off.

Notes:

1. q vernier will be set at 25°, a cross-pointer null at 15°.

2. Duration of flight approximately 11 minutes.

3. Emergency lakes: Grapevine and Ballarat.

 Ground Rules for No Launch: 1. MH-96 FCS malfunction as indicated in attached sheets.

2. Inertial platform malfunction in attitudes.

3. Ball nose malfunction.

4. Radio or radar failure.
 

 Alternate Situations Before Launch:  
1. MH-96 FCS malfunction in auto-pilot on reaction controls - proceed but do not operate affected FCS modes. Alternate Situations After Launch:   1. If engine does not light within 30 sec. after launch, jettison propellants and land at Mud Lake.

2. For delayed engine light, proceed as planned, maintain less than 3 g during rotation.

3. For radio, radar, or microwave failure, proceed as planned.

4. For adaptive damper failure to fixed gain in any axis, proceed as planned but do not use hold modes in affected axis.

5. For total yaw damper failure, proceed as planned.

6. For total roll damper failure, disengage yaw damper, return to Edwards, make da pulses at pilot's discretion.

7. For total pitch damper failure, proceed as planned, fly 1 g after burnout, perform pulses at pilot's discretion.

8. For inadvertent engine shutdown:
 

 0 - 65 sec Mud.

65 - 95 sec Grapevine.

95 - 120 sec Ballarat.

120 - Up sec Edwards.
 

Two engine starts may be attempted in all cases.