Maintenance script: ParaNet BBS Archive

2023-09-12T01:05:46Z

ParaNet BBS Archive

New page

[[Category:ParaNet]]

{{Infobox BBS
| image = Archived-En.png
| file = srfrm.txt
| author = Unknown
| date = Unknown
| subject =
| orig_bbs = Unknown
| bbs_main_page = [[ParaNet Main Page]]
| key_words = ParaNet, UFO, Ufology
}}

<pre>

(503) Thu 4 Jun 92 10:16p Rcvd: Fri 5 Jun 12:04a
By: Uucp, ParaNet(sm) Information Servi (104/422)
To: Michael Corbin
Re: SR.FRM
St: Pvt Kill Rcvd
------------------------------------------------------------------------------
* Original: TO ... Michael Corbin of 1:104/422
* ReDirected Using ReDirect Version 1.00 (C)1989 David Nugent

From scicom!csn.org!mcorbin
From: mcorbin@csn.org (Michael Corbin)
To: scicom!mcorbin
Date: Thu, 4 Jun 1992 21:12:54 -0600
Cc: Mike.Keithly@f605.n104.z1.fidonet.org

Cover

Lockheed SR-71
Supersonic / Hypersonic Research Facility

<previously published picture of SR-71 with tiger tails>

Researcher's Handbook

Volume I Executive Summary

Picture Page

<previously published picture of SR-71 taken from above>

Pg. 1

Contents

Purpose 2

Key Characteristics 4

Extended Capabilities 14

Current And Potential Payloads 16

Internal Payloads 22

External Payloads 27

Summary 40

Pg. 2

Purpose

- This handbook provides information on use of the SR-71
for basic and applied research, theoretical or applied
development, testing and evaluation of material or
equipment, in any field of user interest in the
supersonic/hypersonic arena

- The purpose of this handbook is to provide an overview
of the capabilities and limitations of the SR-71 as a high
altitude, high Mach, research, development, and test
and evaluation (RDT&E) platform

Pg. 3.

Introduction

- This summary depicts capabilities and operating
limitations of the SR-71 as a high altitude, high Mach,
research, development, test and evaluation (RDT&E)
platform

- Two Volumes
Vol I - Executive Summary
Vol II - Technical Description

- SR-71 Aircraft are operational and ready for
experimental development flight test applications

- Experimental design, modification/integration
services, and operations support are provided by
Lockheed Advanced Development Company, The
"SKUNK WORKS."

Pg. 4

Lockheed SR-71 Blackbird

<Line drawing of front, top and side view of SR-71>

Primary Function .................High Speed Test Platform
Speed ............................More Than 2,000 Miles Per Hour (Mach 3.2)
Altitude .........................Above 80,000 Feet
Number of Engines ................Two J-58 Turbojets with Afterburners
Range ............................More Than 2,000 Miles
Crew .............................Two: Pilot and Test Engineer

Dimensions:
Span ...........................55.6 Feet
Length .........................107.4 Feet
Height (Parked) ................18.5 Feet
Weight .........................143,000 Pounds

Pg. 5

- Vehicle: Two-Place, Delta Wing Built By Lockheed
- Powerplant: Two, Pratt & Whitney J-58, Axial-Flow
Turbojet
- "Routinely" Sustains Cruise At Mach 3.2 and 85,000 feet
- Total flight time: Over 53,000 hours
- Total time at Mach 3 or Above - Over 11,000 Hours
- Airframe Good Beyond The Year 2020
- Proven/Mature Supersonic Aircraft

Pg. 6

Status

- Six Flyable Aircraft
Two Vehicles Are Flight Ready At NASA Dryden
Flight Research Facility

Third Vehicle Flight Ready - July 1991

Three Additional Vehicles In Storage Under USAF

- SR-71 Simulator
Operational

Pg. 7

<Previously Published overhead shot of 3 SR-71's 2 - A's and a B in the middle>

Pg. 8

Spare Engines

<Interesting shot of the nozzle end of 8 J-58's lined up in a row>

Pg. 9

Warehoused Assets

<Warehouse shot of lots of long
<Shot of a warehouse interior with spare skinny, rectangular, and square
SR-71 noses wrapped up in protective covers wood containers piled neatly>
and these roughly boat-chaped containers
on wheels> <Warehouse shot of lots of
skinny and rectangular wood
boxes and deeper wood boxes,
piled high>
Sufficient Spares And Equipment
To Support Flying Operations
For Years

Pg. 10

Flight Envelope (Standard Conditions)

< A graph showing Altitude in thousands of ft. on the vertical axis,
and Mach No. on the horizontal axis.

Vertical axis marked in 20,000 ft. increments starting at SL up to
100,000 ft. Horizontal axis marked in .5 Mach increments from 0
up to Mach 3.5.

Key numbers:
Minimum Airspeeds (Approx. Hope I read them right)
0 Mach to .5 Mach AND SL to 22,000 ft. = 145 KIAS
.5 Mach to Mach 1 AND 22,000 to 41,000 ft. = 350 KEAS
Mach 1 to Mach 3.2 AND 32,000 to 85,000 ft. = 310 KEAS

REDUCE KEAS TO 400 at M = 3.2

500 KEAS DESIGN LIMIT

<KEAS is Knots Equivalent Air Speed.
Any help explaining this would be appreciated.
Buck Adams told me it meant air speed over the wing.

So does this take into account being downstream of shocks
and air density, and out of BL. I thought dynamic pressure
was always what high Mach guys flew.

Buck also said something to the effect, you fly KEAS on
climb (sounds similar to how dynamic pressure is used on
high acceleration flights to high Mach) and Mach at cruise.
Or do I have that reversed. HELP!>

Pg. 11

Flight Envelope

- Maximum Performance
Mach 3.2+

Altitude: Above 85,000 Feet

- Airspeeds
310 - 450 KEAS (Normal)

500 KEAS (Extended)

- Dynamic Pressure Range: 325 - 847 lbs/ft

- Heat Soak: Over 600 F for 60 minutes

- Remain at Mach 3.00: Over 60 Minutes Per Sortie

Pg. 12

Flight Profile-Maximum Range

<A diagram/chart that shows takeoff, climb to 71,500 ft
a distance of 2373 N. Mi being covered during cruise starting
at 71,500 ft, and the cruise portion of the flight ending at
80,000 ft. Descent to landing follows the 2373 miles covered
in cruise. So ascent and descent are not covered in the
2373 mile distance>

- Total Time: ~ 100 Mins

- Mach 3.0 Time: ~ 64 Mins

- T/O Gross Wt: 140,000 lbs

- T/O Fuel: 80,000 lbs

Pg. 13

Flight Profile - Maximum A/B Cruise

<A diagram/chart that shows takeoff, climb to 84,000 ft
a distance of 2008 N. Mi being covered during cruise starting
at 84,000 ft, and the cruise portion of the flight ending at
85,000 ft. Descent to landing follows the 2008 miles covered
in cruise. So ascent and descent are not covered in the
2008 mile distance>

- Total Time: ~ 83 Mins

- Mach 3.0 Time: ~ 48 Mins

- T/O Gross Wt: 140,000 lbs

- T/O Fuel: 80,000 lbs

Pg. 14

Extended Flight Envelope - Development

- Beyond 3.2
Thrust/Drag: Not An Immediate Limit

Inlet Temperature, Aerostability, and Hot
Structure Considerations

Engineering/Flight Qualification Required

- Equivalent Airspeed Beyond 500 KEAS
Engineering/Flight Qualification Required

Pg. 15

Demonstrated Flight Development Capability

<Picture of SR-71 climbing with tiger tails - like cover sheet>

Pg. 16

Demonstrated Integration

- Lockheed Skunk Works Has Demonstrated Highly
Successful Systems Engineering/Integration On
The SR-71

Optical Film Cameras (Visual and IR)

Imaging Radar Systems

ELINT

Air-to-Ground Data Linking

Analog and Digital Recording Devices

Design of Real-Time Satellite Data Link

Design of a Global Position System (GPS)

Captive Test Of Radar For Reentry Vehicle

Laser Communication

Pg. 17

Successful Tests and Demonstrations

- Overland Sonic Boom Characterization

- Shuttle Re-Entry Flight Path Emulation

- Extended High-Heat Profile

- Digital Automatic Flight/Inlet Control Development

- Advanced Sensor/EW Interoperability

- High-Altitude Turbulence Characterization

- High-Temperature Structure And Thermal Protection
Materials

Pg. 18

Other RDT&E Testing Potential

- CFD Code Validation

- Laminar Flow Control Experiments

- Upper Atmosphere Characterization

- Inlet/Engine Compatibility

- Sonic Boom Evaluation/Propagation

- High-Speed Civil Transport (HSCT) Component Evaluation

- Sensor/Processor Experiments

- Endothermic Fuel Testing

Pg. 19

Experimental Payloads

Aircraft's Internal Payload (No Drag)
Capacity And Surplus Thrust (For
External Payloads - Additional Drag)
Define The Scale Of Experimental
Components/Equipment That Can be
Carried

Pg. 20

Payload Weight vs Time at Mach 3.2

< A graph showing Time At mach 3.2 (Minutes) on the vertical axis,
and Payload Weight - 1000 lbs, on the horizontal axis.

Vertical axis marked in 20 minute increments starting at 0 up to
80. Horizontal axis marked in 5000lb increments from 0
up to 25 (0 - to - 25,000 lbs).

The curve is very close to linear with a very gentle knee (reduction
in negative slope) at approx 12,000 lbs. So, lets call it linear.
It goes from a y-intercept of (0,80) to a (x,y) coordinate of
(25,24) (thats 25,000lbs,24minutes)
>

Pg. 21

Excess Thrust vs Altitude at Mach 3.2

< A graph showing Excess Thrust (LBS) on the vertical axis,
and Altitude (FT), on the horizontal axis.

Vertical axis marked in 2000 lb Thrust (Th) increments starting at 0 lb Th
up to 8000 lb Th. Horizontal axis marked in 5000 ft increments from 75,000 ft
up to 85,000 ft.

The curve has a gentle knee at (80,000 ft, ~5,000 lb Th). Other points
on the curve are ~ 7,500 lb of excess thrust at 75,000 ft
(75,000 ft, 7,500 lb Th), and ~ 3,000 lb excess thrust at 85,000 ft
(85,000 ft., 3,000 lb Th).

Ed. Note: As a class assignment, assume the relationship was perfectly linear,
compute the equation of the line and the value of the x-intercept
(altitude when excess thrust goes to 0). Or, assume linear to the
right of the knee of the curve.
Just for fun! Who knows if it's valid!
>

Pg. 22

Internal Payload Provisions

- Large Payload Compartments/Bays

Abundant Electrical Power: 60KVA, 115/220V, 400Hz

Abundant Cooling Air: More Than 30 Pounds Per Minute
35 Deg F Air

More than 150 Liters LN2 Available

Accessible Through Large Doors/Hatches

Existing Payload Upload/Download Provisions

Pg. 23

Payload Bay Capacities

<OK, here I really can't do it justice by words alone. There is a B+W line
drawing of all the bays running along the chine forward of the wing, on both
sides of the fuselage. There are a number of different size bays, including
inside the nose cone itself.

Personally, I think we have a hint here about how the RS-71
weapon storage bays may have been done. The interesting new issue is the
commonality between the YF-12A air-to-air missile technology that was
successfully demonstrated, and the possibility of using that technique on
a RS-71 where you replace the air-to-air missile with a air-to-ground
missile. I'm not saying that this was the plan but it is obviously suggested
by this foil and the next several foils! What do you all think?

There are some interesting YF-12A program results as well!>

<The bays are labeled on the left side, from the nose backward to the wing:
A-nose, K, M, P, S, and then on the right side from the nose back to the
wing: A-nose, D, L, N, Q, T. There is a centerline bay labeled C between
K & L>

Payload Vol (Cu ft) Typical payload Max Dims in Bay (inches)
Bay Each Bay Weight (Each Bay) - Typical Mounting

A (Nose) 23 550 lbs 30 X 30 X 75
C 7.2 150 lbs 24 X 24 X 16
D 12 230 lbs 11 X 17 X 80
K & L 29.2/Bay 900 lbs 16 X 17 X 92
M & N 21.7/Bay 200 lbs 18 X 18 X 49
P & Q 32.0/Bay 340 lbs 18 X 18 X 90
S & T 22.7/Bay 400 lbs 18 X 18 X 62

<I Changed order of last 2 lines so bays on the same side of the A/C
line up vertically in the above chart>

Pg. 24

Internal Payload Deployment

- High Altitude, High Mach Missile Launch

Demonstrated GAR-9 (Phoenix Type) Launches

Altitudes from 65,000 to 76,000 feet

Target Aircraft Was From 500 To 40,000 Feet

Internal Carriage

Piston Eject

All But One Of 7 Launches Successful
(Failure Caused By Missile Gyro Failure)

Pg. 25

GAR-9 Loading Into SR-71 Variant

< A nice previously published large head-on picture of a YF-12A in black
with a GAR-9 missile positioned on a cart under the missile bay.>

Pg. 26

Modification Potential

- Aircraft Can Be Modified To Accomplish:

Internal Carriage: Free Flight Deployment

External Carriage: Captive Experiments

External Carriage: Free Flight Deployment

Pg. 27

External Carriage - Captive

- Experiments Designed For SR-71 Integration
Suggest Potential Of Aircraft For Future
Experimental Payloads

Reentry Vehicle Sensor On Half Body

High-Altitude/High-Mach Air Particulate
Sampler

Full Scale Supersonic Nacelle

Pg. 28

AXIS ** Installation in P and S Bays

<A B+W line drawing of a side view of the front half of a SR-71 and how
the X-band Intercept Sensor (AXIS) was to be installed (remember
the SWERVE articles?)

There's also a frontal view that shows the AXIS as a small radome under the
left side chine under where the P and S Bays are.>

<Note 2 contiguous bays on the same side of the aircraft are used
for AXIS>

** Active X-Band Intercept System <acronym explanation>

Clutter Rejection Validation Experiment

Pg. 29

Air Particulate Sampler

W1 W2 Filter Approach
Flow Rate Inlet Exit Velocity - Maximum
SCFM Width Width FPS

708 5.43 1.00 177
1000 7.68 1.71 258

(Sized for double thickness PBI filter media.

<A B+W line drawing/schematic 4-view of the Air Particluate Sampler>

Pg. 30

Supersonic Nacelle Wind Tunnell Test

<A neat left front end shot of a YF-12A wind tunnell model
with a NASA emblem on the nose, and a very large supersonic
nacelle with an inlet spike, ON TOP of the YF-12 fuselage.

The nacelle seems to be on a pylon and there are 4 support
wires that attach to the fuselage and the nacelle (?)

The nacelle is being carried forward of where the M-12's carried
the D-21A's.>

Pg. 31

Upper Surface Flow Field

<A color picture of M-12 #940 with a drone on its back from 3 O'clock.

Probably the same shot or very similar to the one M-12 shot that
was originally published back in the late 70's.>

Local Flow Conditions Are Uniform
Within A Large Region In The Expansion
Dominated Flow Above The Aircraft

Pg. 32

Upper Surface Flow Field Survey - Mach No.

< A graph showing Local Mach. No on the vertical axis,
and Mach Number - Freestream, on the horizontal axis.

Vertical axis marked in .2 Mach increments starting at Mach 2.2
up to Mach 3.4. Horizontal axis marked in .2 Mach increments from
Mach 2.2 to Mach 3.4.

The curve goes from left to right and is very gently concave down
(almost linear). Ordered pairs indicate:
(Freestream Mach No., Local Mach No On Upper Surface).

End points on the curve are: (Mach 2.5, Mach 2.6) and (Mach 3.2, Mach 3.3).
A approx. center point is: (Mach 2.8, Mach 2.94).
>

Note: Data Measurement At 20-80 Inches
Above Fuselage

Pg. 33

Upper Surface Flow Field Survey - Reynolds Number

75,000 Ft Altitude

< A graph showing Local Reynolds No. on the vertical axis (1/Ft X 10**6),
and Mach Number - Freestream, on the horizontal axis.

Vertical axis marked in .2 increments starting at 0.6
up to 1.4. Horizontal axis marked in .2 Mach increments from
Mach 2.2 to Mach 3.4.

The curve goes from left to right and is slightly concave down
but looks like it's composed of 3 segments.

Ordered pairs indicate:
(Freestream Mach No., Local Reynolds No.).

Points that make up the 3 segments are:
End points: (Mach 2.5, .91) and (Mach 3.2, 1.19).
Internal End Points Of Line Segs.: (Mach 2.7, 1.0) and (Mach 2.91, 1.09)>

<So Upper Surface Reynolds No. between Mach 2.5 and Mach 3.2 is .9 to
1.2 million/Ft >

Pg. 34

Upper Surface Flow Field Survey - Dynamic Pressure

75,000 Ft Altitude

< A graph showing Local Dynamic Pressure on the vertical axis (Lb/Ft**2),
and Mach Number - Freestream, on the horizontal axis.

Vertical axis marked in increments of 100 starting at 200
up to 600. Horizontal axis marked in .2 Mach increments from
Mach 2.2 to Mach 3.4.

The curve goes from left to right and is fairly linear.

Ordered pairs indicate:
(Freestream Mach No., Local Dynamic Pressure).

End points are: (Mach 2.5, 350) and (Mach 3.2, 560).

Note: Data Measurement At 20-80 Inches
Above Fuselage

Pg. 35

External payload Deployments

- D-21
Supersonic Drone

5 Successfully Launched At Mach 3

- Advanced Concepts - Hypersonic Research Vehicle
Studied But Not Developed

- Upper Or Lower Deployment Possible

Pg. 36

<Nice photo of M-12 #940 with drone, on the ground, with ladders and carts
pulled up. There are guys working on 940.

It was taken from the front (about 11 O'clock, and slightly above 940)
and it's a close shot. The pilots canopy is open.

It looks like the background terrain was airbrushed-out to look like blue
sky.>

Pg. 37

<Nice new photo of M-12 #940 with D-21A from 4:30 O'Clock and slightly above,
over mountain range (Sierras?). Beautiful Shot! >

Pg. 38

Hypersonic Test Vehicle

< Photo of a blackbird model with a Hypersonic Research Vehicle on the
back of it - D-21 style. Blackbird is in black with old FX-937 marking on
nacelle, and older pre-stealthy USAF markings>

<Blackbird model carries NASA tail stripe and tail no. 06937>

<06937 is really an A-12!!> <In latest blackbird list, it's in Palmdale
at Blackbird Airpark>

<Hypersonic Research Vehicle carries NASA stripe>

Pg. 39

Top Or Bottom Deployment Concept

<One picture with two head-on blackbird line-drawings, one above the other:

Top line drawing:
Blackbird head-on with D-21 in traditional position.
It says "D-21" under the drawing.

Bottom line drawing:
Blackbird head-on with a small lifting-body like vehicle under it.
The lifting body vehicle looks like it has a rocket booster attached to
the back-end of it. Ie: the Boost in Boost-Glide.
It says "Boost-Glide Vehicle" under the drawing.
>

Pg. 40

Summary

- No other platform is currently available, in design,
or forecast for the future that can provide the
flight envelope and test parameters the SR-71 can
provide - today.

- A highly reliable, mature, proven system

- Meets many current and projected RDT&E testing
requirements

- Experiment design/integration and support available
from Lockheed

- Overall program management available by Lockheed
Advanced Development Company (LADC)

Pg. 41

Missing

Pg. 42

"Look ahead where the Horizons are absolutely unlimited"
Robert E. Gross
Former CEO

@Redirected Via Node 1:104/422 : Thu, Jun 4, 1992 10:17pm

</pre>

d RDT&E testing
requirements

- Experiment design/integration and support available
from Lockheed

- Overall program management available by Lockheed
Advanced Development Company (LADC)

Pg. 41

Missing

Pg. 42

"Look ahead where the Horizons are absolutely unlimited"
Robert E. Gross
Former CEO

@Redirected Via Node 1:104/422 : Thu, Jun 4, 1992 10:17pm

ParaNet BBS/srfrm - Revision history

Maintenance script: ParaNet BBS Archive