PROJECT HAZEL AIRCRAFT DESIGN REPORT NO. ZP-253 OCTOBER 1958

• Document Type: CREST
• Collection: General CIA Records
• Document Number (FOIA) /ESDN (CREST): CIA-RDP89B00709R000400830001-3
• Release Decision: RIFPUB
• Original Classification: S
• Document Page Count: 123
• Document Creation Date: December 27, 2016
• Document Release Date: December 13, 2010
• Sequence Number: 1
• Publication Date: October 1, 1958
• Content Type: MEMO

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SAN DIEGO
SECRET
TITLE.
PROJECT
HAZEL
AIRCRAFT DESIGN
CONTRACT NO. NO(as)58-812(SS-100)
OCTOBER 1958
REPORT ZP-253
PRrF'A,RFF1 ti-{ 60, ..,
Hans H.
REPORT ZP-P53
DATE .Qctaber 1958
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_P. -ktan
C. R. Tuttle
r J
gFC. RFT
AP1=fOVEL)[1.,,?a,r '
A. R. Lambert
Chief of Pre Design
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ANALYSIS CO N VA I R PAGE i
PREPARED BY A DIVISION OF GENERAL DYNAMICS CORPORATION REPORT NO. ZP-253
CHECKED BY mvv~...
REVISED BY DATE October 1958
SECRET
This document contains information affecting the national
defense of the United States within the meaning of the
Espionage Laws, Title 18, U. S. C. Sections 793 and 791e.
The transmission or the revelation of its contents in any
manner to an unauthorized person is prohibited by law.
SECRET
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ANALYSIS CO N VA I R PAGE ii
PREPARED BY A DIVISION OF GENERAL DYNAMICS CORPORATION REPORT NO. Z P-253
CHECKED BY ISAN DIEGO) MODEL
REVISED BY DATE October 1958
SECRET
TABLE OF CONE=
Summery
PAGE
1
2
Introduction 10
Section I - Configuration Study . . . . . . . . . . . . . . 17
A. General . 18
1. Configurations . . . . . . . . . . . . . . . 18
2. Mission Profile . . . . . . . . . . . . . . . 18
3- Engines . . . . . . . . . . . . . . . . . . . 21
40 v wing . . . . . . . . . . . . . . . . . . . . 24
5. Center of Gravity Location and Stability . . . 26
6. Hydrodynamic Considerations . . . . . . . . . 26
Be Configurations . . . . . . . . . . . . . . . . . . 30
1. Single Engine Configurations . . . . . . . . . 30
at Marquardt Engine . . . . . . . . . . . . 30
2. Twin Engine Configurations.. . . . . . . . . . 36
a. Marquardt Engines . . . . . . . . . . . . 36
be Pratt & Whitney Engines . . . . . . . . . 41
C. Weights . . . . . . . . . . . . . . . . . . . . . . 46
D. Launching Methods . . . . . . . . . . . . . . . . . 49
SECRET
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ANALYSIS CO N VA I R PAGE iii.
PREPARED BY A DIVISION of GENERAL DYNAMICS CORPORATION REPORT NO. ZP-253
CHECKED BY (SAN DIEGO) MODEL 1958
REVISED BY DATE October 1958
SECRET
TABLE OF CONTENTS (CONT' D)
PAGE
Section II - Systems . . . . . . . . . . . . . . . . . . . . %
1. Auxiliary Power System. . . . . . . . . . . . . 55
2. Thrust Vector Control System. . . . . . . . . . 55
3. Control Activation System . . . . . . . . . . . 57
4+. Boost Rocket Separation System. . . . . . . . . 57
5. Structure Pressurization System . . . . . . . . 57
6. Air Conditioning System . . . . . . . . . . . . 58
7. Electrical Power Generator System . . . . . . . 58
8. Fuel System . . . . . . . . . . . . . . . . . . 58
Section III - Crew Capsule and Escape Methods. . . . . . . . 60
Section IV - Structural Consideration. . . . . . . . . . . . 7 0
A. Structural Design Criteria . . . . . . . . . . . . 71
B. Structural Configurations. . . . . . . . . . . . . 82
C. Materials and Fabrication . . . . . . . . . . . . 84
D. Structural Feasibility . . . . . . . . . . . . . . . 96
E. Structural Weight Estimates . . . . . . . . . . . . 104
SECRET
TORN 1812I
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ANALYSIS
PREPARED BY
CHECKED BY
REVISED BY
CONVAIR
A DI\ISIUN CF GENERA, DFNAMIcS C:1 )
,BOOST 5YS7 E/=1
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SECRET.
FORM Isla-A-1
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ANALYSIS
PREPARED BY
CHECKED BY
REVISED BY
CONVAIR
A DIVISION OF GENERAL DYNAMICS CORPORATION
(SAN DIEGO)
SECRET
SECRET
PAG`.' 54
REPORT NO. ZP-253
MODEL
DATE October 1958
FORM IS-n?Declassified and Approved For Release 2012/05/31: CIA-RDP89B00709R000400830001-3
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ANALYSIS
PREPARED BY
CHECKED BY
REVISED BY
C O N VA I R PAC... .55
A DIVISION OF GENERAL DYNAMICS CORPORATION REPORT NO. ZP-253
(SAN DIEGO) MODEL
DATE October 1958
SECRET
The Hazel Systems are shown schematically in Figure 30. The following
subsystems are summarized in this section:
1. Auxiliary Power
2. Thrust Vector Control
3. Control Actuation
4. Boost Rocket Separation
5. Structure Pressurization
6. Air Conditioning
7. Electrical Power Generation
8. Fuel System
1. Auxiliary Power
Estimated auxiliary power requirements can be satisfied with the follow-
ing two (2) auxiliary power systems:
a) Vehicle Liquid Monopropellant Auxiliary Power System
b) Boost Rocket Pneumatic Servo System
a) Vehicle Liquid bbnopropellant Auxiliary Power System
This system consists of a liquid monopropellant, such as
hydrozine, decomposed in a catalyst gas generator. The propellant is
supplied to the gas generator by pressure secured from the pressurized
structure helium supply. Flow is varied on demand by sensing gas generator
pressure. Systems receiving energy are:
1) Structural Pressurization
2 Aerodynamic Surface Control
3 Electrical Power
b) Boost Rocket Pneumatic Servo System
This system consists of a gas source which supplies energy to an
actuator through a pneumatic servo. A more detailed analysis relative to
state-of-art at time of detail design will select either a hot gas, bottled
gas or other energy source. The system receiving energy is the Boost Rocket
Vector Control.
2. Thrust Vector Control
Thrust vector control is required on the Boost Rocket to correct devia-
tions from the proposed flight path. The choice of method to obtain jet
deflection cannot be made without further study. Present indications are
that the final choice will be between swivel (gimbaled) nozzles and jetevators.
SECRET
FORM IIA-A-1
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ANALYSIS C O N VA I R PAGE 96
PREPARED BY A DIVISION OF GENERAL DYNAMICS CORPORATION REPORT NO. ZP-253
CHECKED BY (SAN DIEGO) MODEL
REVISED BY DATE October 1958
SECRET
D. Structural ,Feasibility
On the following pages approximate formulae have been developed for the
determination of structural pressure and minimum gages or areas of material
for the non-rigid wing. Assumptions made and detailed in the calculations
are:
1. Uniform airload distribution.
2. No wing inertia relief.
3. Root at f is typical critical section.
4. 2/3 of chord is uniformly loaded by the
design bending moment of the wing outboard of section.
5. Section requirements are constant from root to tip.
The rigid structure would be analyzed by well established methods and
are not detailed here.
SECRET
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