Key Terrestrial and Space Environment Sources

Johnson, Dale L.; Vaughan, William W.

doi:10.5028/jatm.v12.1089

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ORIGINAL PAPER • J. Aerosp. Technol. Manag. 12 • 2020 • https://doi.org/10.5028/jatm.v12.1089 copy

Key Terrestrial and Space Environment Sources

Authorship SCIMAGO INSTITUTIONS RANKINGS

ABSTRACT

Natural (Terrestrial & Space) Environment (NE) phenomena play a significant role in the design and flight of aerospace vehicles and in the integrity of the associated aerospace systems and structures. Both the terrestrial environment (0-90 km altitude) and the space environment (Earth orbital altitudes) parameters and their engineering application philosophy are given with emphasis on launch vehicle-affected terrestrial environment elements. This paper will describe the key terrestrial and space environment sources: wind; atmospheric; and orbital models used in the design and development of launch/space vehicles.

KEYWORDS:
Natural Environment; Terrestrial; Space; Design; Launch Vehicles

Category	Application	Source
Thermodynamic atmospheres	Used in design scenarios for aerodynamic pressure and aerodynamic heating during launch and, most critical, in return from space or in suborbital missions, or for preliminary flight test series.	• GRAM-07 (Leslie-Justus 2008Leslie FW, Justus CG (2008) The NASA MSFC Earth global reference atmospheric model - 2007 Version. (TM-2008-215581). NASA Technical Memorandum.) • Range Commander's Council (1983)Range Commander’s Council (1983) Cape Canaveral Florida - range reference atmosphere 0 to 70-km Altitude. (361-83). RCC Document. • NASA (1976)[NASA] National Aeronautics and Space Administration (1976) US standard atmosphere, 1976. (TM-X-74335). NASA Technical Report. • Johnson (2008)Johnson DL (2008) Terrestrial environment (climatic) criteria guidelines for use in aerospace vehicle development, 2008 Revision. (TM-2008-215633). NASA Technical Memorandum.
Vector wind profile (VWP) model	Used in design scenario baselines for dispersion of aero- dynamic loads attributable to wind profile dispersion (the persistence of winds over time as a function of the wind load calculations on the vehicle over that same time). Note: The VWP replaces preliminary design wind profiles constructed from selected percentiles of wind speed (scalar wind model) or wind components. It contains vertical wind shear percentile information.	• Adelfang et al. (1994)Adelfang SI, Smith OE, Batts GW (1994) Ascent wind model for launch vehicle design. J Spacecraft and Rockets 31(3):502-508. https://doi.org/10.2514/3.26467 https://doi.org/10.2514/3.26467... • Smith (1976)Smith OE (1976) Vector wind and vector wind shear models 0 to 27km altitude for Cape Kennedy, Florida and at Vandenberg AFB, California. (TM-X-73319). NASA Technical Report. • Adelfang (1999)Adelfang SI (1999) User’s guide for monthly vector wind profile model. (CR-1999-209759). NASA Technical Report.
Synthetic wind profiles	Used in preliminary design.	• Johnson (2008)Johnson DL (2008) Terrestrial environment (climatic) criteria guidelines for use in aerospace vehicle development, 2008 Revision. (TM-2008-215633). NASA Technical Memorandum.
Discrete gust models	Used to establish structural response to wind gusts. Both are used in the Shuttle program.	Classic 9 m/s (30 ft/s) gust model (see Fig. 6) (Johnson 2008Johnson DL (2008) Terrestrial environment (climatic) criteria guidelines for use in aerospace vehicle development, 2008 Revision. (TM-2008-215633). NASA Technical Memorandum.; Adelfang and Smith 1998Adelfang SI, Smith OE (1998) Gust models for launch vehicle ascent. Presented at: 36th AIAA Aerospace Sciences Meeting; Reno, USA. https://doi.org/10.2514/6.1998-747 https://doi.org/10.2514/6.1998-747... ) • New NASA gust model (Adelfang and Smith 1998Adelfang SI, Smith OE (1998) Gust models for launch vehicle ascent. Presented at: 36th AIAA Aerospace Sciences Meeting; Reno, USA. https://doi.org/10.2514/6.1998-747 https://doi.org/10.2514/6.1998-747... )
Turbulence models	Used in developing vehicle structures and systems for G&C. Also used with applications to fuel-budgeting studies.	• GRAM-07 Power spectrum density/continuous turbulence models (Johnson 2008Johnson DL (2008) Terrestrial environment (climatic) criteria guidelines for use in aerospace vehicle development, 2008 Revision. (TM-2008-215633). NASA Technical Memorandum.)
APRA	Used in mission planning studies to analyze vehicle design, mission scenario operability for specified weather constraints.	• Smith et al. (1982)Smith OE, Batts GW, Willett JA (1982) Atmospheric constraint statistics for the space shuttle mission planning. (TP-2069). NASA Technical Paper.
Launch site specific meteorological databases (for KSC and other sites, for prelaunch, launch, and landing from the surface to 27 km (15 nmi)	Used as an input to APRA above. Used to construct the VWP model. Used in design verification analyses (surface to 18 km (10 nmi).	• Surface weather data (30+ yr, hourly) • Monthly Rawinsonde wind profiles (surface to 27 km [15 nmi], 19 yr of data, serially complete, two profiles/day) • Jimsphere detailed wind profiles, 150 profiles/month for KSC and VAFB

Alt. (km)	1 (30º)		2 (60º)		3 (90º)		4 (120º)		5 (150º)		6 (180º)		7 (210º)		8 (240º)		9 (270º)		10 (300º)		11 (330º)		12 (360º)		Mean
Alt. (km)	IP	ºOP	IP	ºOP	IP	ºOP	IP	ºOP	IP	OP	IP	ºOP	IP	ºOP	IP	ºOP	IP	ºOP	IP	ºOP	IP	ºOP	IP	ºOP	IP	OP
0	4.5	-3.6	3.0	-6.6	1.6	-8.2	-1.2	-9.0	-5.1	-7.0	-6.8	-1.8	-5.9	3.2	-4.3	6.2	-2.9	7.8	-0.1	8.6	3.8	6.6	5.5	1.4	-0.65	-0.21
1	8.2	-6.2	3.3	-12.2	-2.5	-13.8	-8.8	-12.0	-14.2	-7.0	-17.0	0.8	-15.6	9.5	-10.7	15.4	-4.9	17.1	1.4	15.3	6.8	10.2	9.6	2.4	-3.70	1.62
2	0.4	-5.5	-5.1	-8.6	-9.6	-8.8	-13.8	-7.3	-17.5	-3.6	-18.9	2.3	-16.1	8.5	-10.7	11.6	-6.21	1.8	-1.9	10.3	1.7	6.6	3.1	0.7	-7.88	1.48
3	-8.5	-4.7	-13.2	-4.8	-15.2	-4.1	-17.5	-3.1	-19.5	-0.1	-19.1	4.5	-14.9	8.1	-10.2	8.2	-8.2	7.4	-5.9	6.5	-3.9	3.5	-4.3	-1.1	-11.70	1.68
4	-16.3	-3.7	-20.1	-1.7	-19.7	-0.2	-19.8	0.1	-20.7	2.1	-19.1	5.8	-14.1	7.9	-10.3	5.9	-10.7	4.4	-10.6	4.1	-9.8	2.1	-11.3	-1.6	-15.21	2.11
5	-24.2	-2.6	-26.9	1.6	-24.2	4.1	-22.4	4.0	-21.8	5.2	-19.2	7.6	-13.8	7.6	-11.0	3.3	-13.7	0.9	-15.5	1.0	-16.1	-0.2	-18.7	-2.6	-18.97	2.49
6	-32.8	-0.2	-34.1	6.1	-29.1	9.1	-25.1	8.7	-22.5	8.7	-18.6	8.8	-13.1	6.2	-11.8	-0.1	-16.8	-3.2	-20.8	-2.8	-23.4	-2.7	-27.3	-2.9	-22.95	2.98
7	-42.6	1.6	-42.7	10.7	-35.0	14.9	-28.0	14.4	-22.6	13.0	-16.8	10.7	-10.6	5.0	-10.5	-4.1	-18.2	-8.3	-25.2	-7.8	-30.5	-6.4	-36.3	-4.1	-26.58	3.31
8	-55.9	2.4	-54.8	16.7	-43.1	24.0	-31.3	24.0	-21.5	20.9	-12.4	15.1	-4.5	4.4	-5.7	-9.9	-17.4	-17.2	-29.2	-17.2	-38.9	-14.1	-48.1	-8.3	-30.24	3.40
9	-79.8	3.5	-76.0	27.6	-55.6	40.5	-34.3	40.9	-16.2	34.8	-0.3	23.1	11.3	3.5	7.5	-20.6	-12.9	-33.5	-34.3	-33.9	-52.3	-27.8	-68.3	-16.1	-34.26	3.50
10	-67.4	4.1	-65.7	20.4	-51.9	28.2	-38.2	27.1	-27.3	22.5	-17.4	15.2	-9.0	2.7	-10.7	-13.6	-24.4	-21.4	-38.2	-20.3	-49.1	-15.8	-59.0	-8.4	-38.18	3.39
11	-61.8	5.3	-60.5	16.6	-50.6	20.5	-42.0	18.6	-35.3	15.2	-28.7	10.3	-22.5	1.4	-23.8	-9.9	-33.6	-13.9	-42.3	-11.9	-48.9	-8.6	-55.6	-3.6	-42.13	3.32
12	-56.7	5.7	-55.5	12.4	-49.0	13.4	-44.4	11.3	-41.0	9.3	-37.1	6.6	-33.0	1.2	-34.2	-5.5	-40.7	-6.5	-45.3	-4.3	-48.6	-2.3	-52.6	0.4	-44.84	3.49
13	-49.2	7.7	-49.1	9.7	-46.8	8.6	-45.0	6.3	-43.6	4.2	-42.0	2.1	-40.3	-0.6	-40.5	-2.7	-42.7	-1.6	-44.5	0.7	-46.0	2.8-	47.5	5.0	-44.76	3.53
14	-39.3	7.4	-41.3	7.5	-42.2	6.5	-42.4	4.1	-42.9	1.8	-43.8	0.0	-44.0	-0.7	-42.0	-0.8	-41.1	0.2	-41.0	2.5	-40.4	4.9	-39.5	6.6	-41.65	3.33
15	-31.3	6.6	-33.7	5.0	-35.1	3.3	-36.0	0.6	-38.0	-1.6	-40.8	-2.3	-42.1	-0.8	-39.7	0.8	-38.4	2.5	-37.5	5.2	-35.5	7.4	-32.6	8.1	-36.73	2.90
16	-24.4	5.6	-26.6	3.2	-28.3	1.3	-30.0	-1.2	-32.9	-3.0	-36.8	-3.0	-38.8	-0.4	-36.6	2.0	-34.9	3.9	-33.2	6.4	-30.2	8.2	-26.4	8.2	-31.59	2.60
17	-16.0	3.6	-19.3	0.6	-22.5	-0.8	-24.9	-2.3	-28.1	-3.5	-32.3	-3.1	-34.8	0.2	-31.5	3.3	-28.2	4.7	-25.8	6.2	-22.7	7.4	-18.5	7.0	-25.36	1.94
18	-6.8	3.0	-11.1	-1.9	-16.7	-3.0	-19.7	-3.7	-22.5	-4.3	-26.6	-4.0	-30.7	-0.2	-26.5	4.7	-20.8	5.8	-17.8	6.5	-15.0	7.2	-11.0	6.8	-18.78	1.41
19	-0.5	1.7	-5.1	-3.9	-10.8	-4.7	-13.5	-4.8	-16.0	-5.0	-20.0	-4.2	-25.1	0.3	-20.5	5.9	-14.7	6.6	-12.0	6.8	-9.6	6.9	-5.6	6.2	-12.77	0.99
20	6.3	1.7	1.8	-5.2	-4.7	-6.3	-7.9	-6.5	-10.9	-6.4	-15.4	-5.4	-22.0	-0.4	-17.5	6.5	-11.0	7.5	-7.8	7.7	-4.8	7.7	-0.3	6.7	-7.85	0.63
21	12.1	0.2	8.4	-8.5	0.2	-10.6	-5.3	-10.3	-10.1	-9.3	-16.0	-6.7	-22.5	0.1	-18.8	8.9	-10.6	11.0	-5.1	10.7	-0.3	9.6	5.5	7.1	-5.21	0.18
22	14.9	-0.4	10.5	-9.9	1.8	-11.8	-3.8	-11.3	-8.7	-10.1	-15.1	-7.4	-23.0	0.1	-18.6	9.6	-9.9	11.5	-4.3	11.1	0.7	9.9	7.0	7.1	-4.04	-0.14
23	17.3	-0.1	12.6	-10.0	2.7	-11.7	-3.4	-11.2	-8.7	-10.0	-15.4	-7.4	-24.2	0.0	-19.5	9.9	-9.7	11.6	-3.5	11.1	1.8	10.0	8.5	7.4	-3.46	-0.02
24	16.5	0.9	11.1	-9.3	2.0	-11.1	-3.0	-11.0	-7.6	-10.3	-14.0	-8.2	-23.8	-0.7	-18.4	9.5	-9.3	11.3	-4.2	11.2	0.3	10.5	6.7	8.3	-3.65	0.09
25	18.2	-0.9	12.0	-11.4	1.9	-11.6	-3.1	-10.5	-7.4	-9.1	-13.9	-6.7	-25.9	0.9	-19.8	11.3	-9.6	11.5	-4.7	10.4	-0.3	9.1	6.1	6.7	-3.88	-0.02
26	19.9	-0.9	12.4	-11.9	1.6	-12.2	-3.8	-11.1	-8.6	-9.7	-15.8	-7.1	-28.9	1.2	-21.3	12.1	-10.6	12.4	-5.2	11.3	-0.4	9.9	6.8	7.4	-4.48	0.11
27	22.1	-0.5	11.7	-11.5	1.2	-12.1	-4.3	-11.3	-9.5	-10.2	-17.7	-7.8	-32.4	1.2	-22.0	12.2	-11.4	12.8	-6.0	12.0	-0.8	10.9	7.4	8.5	-5.14	0.35

Design application	Exposure period	Risk (%)	C (m/s)^3/4
For on-pad exposure (unfueled)	180 days	1	1.60
For on-pad exposure (fueled)	1 day	1	1.60
For tower clearance (0-150m (500 ft))	1 hour	5	1.60
For ascent loads (0-150m (500 ft))	1 hour	5	1.21

Component	A	B	a	b	C ₂	C ₄
Longitudinal Lateral and vertical	0.807 0.154	29.035 9.059	-1.63 -0.93	1.972 2.134	1.000 0.580	0.845 0.781

Ai (m/s)	T (s)
Ai (m/s)	0.01	0.1	1	10	100	1,000
A1 longitudinal	2.7	5.1	9.1	10.7	10.9	10.9
A2 lateral	2.7	5.1	7.6	8.3	8.3	8.3
A3 vertical	2.0	3.7	5.5	6.2	6.2	6.2

Initial Altitude	Area/mass = 0.24 ft²/lbm (0.05 m²/kg)	Area/mass = 0.024 ft²/lbm (0.005 m²/kg)
300 km (162 nmi)	≈1 week	1 to 3 months
500 km (270 nmi)	3 months to 3 years	3 to 25 years
700 km (380 nmi)	»4 years	»35 years

	Averaging Time - Apply at Solar Noon	Extreme Albedo - Albedo: OLR, W/ft² (W/m²)	Extreme OLR - Albedo: OLR, W/ft² (W/m²)
Hot cases	128 s	0.51 : 16.7 (180)	0.26 : 30.7 (331)
β = 40º	896 s	0.40 : 17.8 (192)	0.26 : 27.6 (297)
Solar constant = 131.4 W/ft²	30 min	0.39 : 19.0 (205)	0.26 : 26.2 (282)
(1,414 W/m²)	90 min	0.38 : 19.0 (204)	0.29 : 25.5 (274)
Cold cases	128 s	0.07 : 25.4 (273)	0.39 : 14.4 (155)
β = 0º	896 s	0.10 : 24.3 (262)	0.36 : 15.1 (163)
Solar constant = 122.8 W/ft²	30 min	0.15 : 22.9 (246)	0.30 : 16.4 (176)
(1,322 W/m²)	90 min	0.20 : 22.2 (239)	0.34 : 18.6 (200)

Departamento de Ciência e Tecnologia Aeroespacial Instituto de Aeronáutica e Espaço. Praça Marechal do Ar Eduardo Gomes, 50. Vila das Acácias, CEP: 12 228-901, tel (55) 12 99162 5609 - São José dos Campos - SP - Brazil
E-mail: submission.jatm@gmail.com

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[1] Correspondence author: williamwvaughan@aol.com