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PRO/BMDO (продолжение)
milstar: Radar performance degrades in environments disturbed by nuclear explosions. ################################################### Hit- to-kill GBIs eliminate the nuclear weapon in the interceptor, but not that in the incoming RV, which could detonate on contact or command. ####################################### Neskolko yglow attaki ,na kazdom formazija/gruppirowka po 100 -1000 boegolowok W ochen' xoroschim/xoroschim chansom chast' iz nix budet podorwanna po prodwizeniju k rajonu attaki dlja degradazii/polnoj newozmoznosti funkzionirowanija rls PRO/BMD That would produce widespread ionospheric disturbances that could interrupt radar or infrared sensors for times longer than the attack. ################################# The US has no relevant data on nuclear phenomenology at relevant intercept altitudes. ####################################################### While x-band radars are less susceptible to nuclear blackout, the Achilles heel of Sentinel and Safeguard was random refraction from multiple bursts, for which there is no experimental evidence. ##################### Wopros s 35 ghz i 94 ghz RLS ,budut oni lutsche w dannoj situazii ? s ychetom wozmoznix plusow - ochen' yzkij luch ,dlja cassegran antenni 13.7 metra diametorom 0.014 grad dlja 94 ghz i 0.042 grad dlja 35 ghz i minusow - pri nizkix yglax bolschoe zatuxanie ot atmosferi ,w dozd' rsche xuze Megawatnnie lampi est' na oba diapazona pri depressed traektori wisota poleta mozet bit' 50-60 km pri elevazii 0 grad eto 800 km Y Warlok pri antenne 1.8 metra 94 ghz i impulsnoj moschnosti 100 kwt pri yglax elevazii 30 grad- 700 km pri 0 grad -70 km W 7 raz bolsche antenna = 49 po moschnosti i 10 po moschnsoti = 490.Koren' chetwertoj stepeni daet ywelichenie dalnosti w 4.7 raza Na 35 ghz werojatno lutsche(zatuxanie w atmosfere i ot dozdja mensche ) , no za schet ywelichanija lucha s 0.014 grad w 0.042 grad For attacks greater than a few weapons, this introduces a fundamental uncertainty into ######################################################## NMD. ### Gregory H. Canavan Los Alamos National Laboratory gcanavan@lanl.gov http://www.aps.org/units/fps/newsletters/1999/july/canavan-paper.html
milstar: The second phase, Full Rate Production, will begin in 2007, with the construction of a 20,600-square-foot, $5 million addition to the Assembly and Test building, and 18,500 additional square feet for administration and storage. See Lockheed Martin MFC release. June 28/2000: Lockheed Martin Space Systems Missiles & Space Operations in Sunnyvale, CA received a $77.5 million increment as part of a $3.97 billion (cumulative total includes options) cost-plus-award-fee contract for the Engineering and Manufacturing Development (EMD) of the initial Theater High Altitude Area Defense (THAAD) tactical ballistic missile defense system. “During the EMD program, the system design will evolve to satisfy the Army’s key operational requirements while developing weapon system components that are not only effective but are affordable, ready for production, and available to the U.S. Army soldiers for a first unit equipped in FY 2007.” Work will be performed in Sunnyvale, CA (68%); Huntsville, AL (30%), and Courtland, AL (2%), and is expected to be complete by May 3, 2008. This is a sole source contract initiated on Oct. 29, 1999 by the U.S. Army Space and Strategic Defense Command in Huntsville, AL (DASG60-00-C-0072). Jan 30/98: Small business qualifier Tec-Masters Inc. in Huntsville, AL received a $2.2 million increment as part of a $27.8 million cost-plus-award-fee/ level-of-effort contract for Theater High Altitude Area Defense (THAAD) Simulation and Hardware-in-the-Loop development. The estimated cumulative total value of this contract will be $43 million if all options are exercised. Work will be performed in Huntsville, AL and is expected to be complete by Sept. 30, 2002. This is a sole source contract initiated on Aug. 22, 1997 by the U.S. Army Space and Missile Defense Command in Huntsville, AL (DASG60-98-C-0044). Nov 21/96: Silverton Construction in El Paso, TX received a $10.4 million firm-fixed-price contract for construction of 2 standard design tactical equipment shops, an organizational maintenance shop and direct support maintenance shop, a fuel dispensing facility, oil storage building, sentry station, pavement, site improvements, utilities, physical security, and information systems for the Theater High Altitude Area Defense (THAAD) system. Work will be performed at Fort Bliss, TX and is expected to be complete by Jan. 20, 1998. There were 31 bids solicited on Sep. 22, 1996, and 7 bids received by the U.S. Army Corps of Engineers in Fort Worth, TX (DACA63-96-C-0004). Sept 24/96: Small business qualifier Dynetics, Incorporated in Huntsville, AL received a $3.4 million increment as part of a $35 million cost-plus-award-fee/ level-of-effort contract for systems engineering and technical assistance (SETA) for the Theater High Altitude Area Defense (THAAD). Work will be performed in Huntsville, AL and is expected to be complete by September 23, 2001. There were 39 bids solicited on March 29, 1996, and 3 bids were received by the U.S. Army Strategic Defense Command in Huntsville, AL (DASG60-96-C-0193). Additional Readings & Sources US Missile Defense Agency – Terminal High Altitude Area Defense Fact Sheet [PDF] Pentagon DefenseLINK, Missile Defense – Theater High Altitude Area Defense (THAAD) System GlobalSecurity.org – THAAD TMD Designation Systems – Lockheed Martin THAAD Army Technology – THAAD Theatre High Altitude Area Defense Missile System, USA Lockheed Martin Missiles & Fire Control – THAAD Raytheon – Terminal High-Altitude Area Defense (THAAD) Radar System Center for Defense Information – Missile Defense Tests: Theater High Altitude Area Defense (THAAD) Flight Test History. The left-wing CDI think-tank has a complete table of the first 12 tests to August 1999. See “Contracts and Key Events” section above for subsequent tests. DID FOCUS Article – Raytheon’s Standard Missile Naval Defense Family. Includes information and links related to the SM-3. US GAO (March 24/11, #GAO-11-372) – Missile Defense: Actions Needed to Improve Transparency and Accountability DID (Dec 18/07) – US Missile Defense Shifting Toward More Realistic Testing? DID (Dec 5/05) – Israel Successfully Tests Arrow Theater Missile Defense. Adds a very comprehensive set of facts and resources re: Israel’s Arrow/Hetz theater defense system. Designation Systems – Coleman Hera IMINT & Analysis – S-300P tag items. Articles give a very detailed overview of S-300/S-400 versions and deployment, backed by imagery intelligence of Russian sites. Also adds some S-500 related information. This article is a free sample taken from our database of 300+ detailed analyses of defense programs and contracting trends. To see what we are already covering, check our list of Focus and Spotlight articles. For full access to the complete Defense Industry Insider knowledge base, subscribe today for less than $50 a month. Content updated daily!
milstar: THAAD Weapon System Achieves Intercept of Two Targets at Pacific Missile Range Facility Kauai, Hawaii, October 5th, 2011 -- THAAD Photo 1 THAAD Photo 2 The U.S. Army Test and Evaluation Command, The Missile Defense Agency and the U.S. Army conducted a flight test of the Terminal High Altitude Area Defense (THAAD) weapon system today, challenging the system to track, detect and intercept two different targets utilizing two THAAD interceptors – a first for the system. ----------------------------------------------------------------------------------------------------------------------------------------------------------- The flight test, known as FTT-12, was designated an Initial Operational Test and Evaluation test by the Director, Operational Test and Evaluation, Office of the Secretary of Defense. The Director, Operational Test and Evaluation and the Army Test and Evaluation Command will also independently evaluate the operational effectiveness of the system. It was conducted at the Pacific Missile Range Facility (PMRF) on Kauai, Hawaii. ---------------------------------------------------------------------- During the mission, the first THAAD missile intercepted an air-launched short-range ballistic missile target. The second THAAD missile intercepted a sea-launched short-range ballistic missile target a short time later. Since 2005, the program has completed 12 flight tests, with nine-for-nine intercepts. ------------------------------------------------------------------------------------------------------------------------------------------ W oboix sluschajax short range ########################## “Today’s outcome is a credit to the soldiers who executed this mission from start to finish,” said Tom McGrath, THAAD vice president and program manager at Lockheed Martin. “It was, by far, THAAD’s most challenging flight test to date and demonstrates the system’s advanced capabilities.” Soldiers from Alpha Battery, 4th Air Defense Artillery Regiment, 11th Air Defense Artillery Brigade, the first THAAD battery activated in 2008, transported the weapon system from Fort Bliss, Texas, in mid-August. Soldiers emplaced the system at PMRF and operated the system under the control of the 94th Army Air and Missile Defense Command during the flight test. In order to make this a realistic tactical environment, the soldiers did not know what day or time the mission would occur. ---------------------------------------------------------------------------------------------------------------------------------------- THAAD is the only missile defense system with the operational flexibility to intercept in both the endo- and exo-atmospheres to provide versatile capability to the warfighter. ------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- A key element of the nation’s Ballistic Missile Defense System (BMDS), THAAD is a Missile Defense Agency program, with the program office located in Huntsville, AL. The agency is developing the BMDS to defend the United States, its deployed forces and allies against ballistic missiles at all ranges and in all phases of flight. Lockheed Martin is a world leader in systems integration and the development of air and missile defense systems and technologies, including the first operational hit-to-kill interceptor. It also has considerable experience in interceptor design and production, infrared seekers, command and control/battle management, and communications, precision pointing and tracking optics, as well as radar and signal processing. The company makes significant contributions to all major U.S. missile defense systems and participates in several global missile defense partnerships. Headquartered in Bethesda, Md., Lockheed Martin is a global security company that employs about 126,000 people worldwide and is principally engaged in the research, design, development, manufacture, integration and sustainment of advanced technology systems, products and services. The Corporation’s 2010 sales from continuing operations were $45.8 billion. 9 Cheryl Amerine, (240)271-2836 e-mail cheryl.amerine@lmco.com For additional information, visit our website: http://www.lockheedmartin.com/mfc
milstar: http://www.gps.caltech.edu/~hayes/Publications/Hayes_SPIE620809.pdf 1. OVERVIEW The Seeker Experimental System (SES), located at MIT Lincoln Laboratory (MIT LL), is a reconfigurable passive infrared sensor testing and emulation laboratory. Passive infrared sensors are crucial to ballistic missile and air defense technologies, providing detection, track, and phenomenology information from launch through reentry. SES was developed in the mid-1990s to provide midwave infrared (MWIR) focal plane array (FPA) and algorithm testing for Army and Navy interceptor programs.
milstar: http://srmsc.org/pdf/004431p0.pdf Sprint test ... 32 testa na KMR . Odin fizicheskij kontakt s celju ( Sprint boegolowka 1kt )
milstar: 1.Missile divert system operating phenomenonology http://www.dtic.mil/cgi-bin/GetTRDoc?Location=U2&doc=GetTRDoc.pdf&AD=ADA432835 2.Standard Missile-3 with Aegis BMD http://www.raytheon.com/capabilities/products/stellent/groups/public/documents/content/cms01_055769.pdf
milstar: Xarakteristiki interceptorow GBI 2 st ,3 st ,sm-3 i drugie http://cstsp.aaas.org/files/BriefOnEastEuropeMissileDefense.PDF profil poleta GBI -2,3 ,SS-25 posle burnout kazdoj stupeni wisota i rasstojanie Korrekzija mnenija MDA (interceptori ne mogut perexwatit russkie raketi ) - Perexwatchiki sposbni perexwatir rossijskie boegolowki
milstar: Nike Hercules.wmv http://www.youtube.com/watch?v=TBv8P31i3dE&feature=related
milstar: Poligon White Sands http://www.wsmr.army.mil/pdf/CompositeRCH2011.pdf
milstar: http://ria.ru/tv_defense_safety/20120504/641160640.html
milstar: BMDO interceptori na baze Trident -2 ########################## 0 =22.55 degrees ygol mesta V =7.177, 7.1935, and 7.21 km/s Altitudes Where Reentry Effects May Be Observable (60 to 90 seconds) pri dalnsoti 9000 km Sew. Koreja- objekn na CONUS http://www.carnegieendowment.org/pdf/npp/CarnegieDC_BriefingSummary061801-01(3).pdf Boost-Phase Kill Vehicle Capable of 10 G Maximum Divert Acceleration and 2 km/sec Total Divert Velocity Total Propellant Weight = 230 lbs Propellant Density = 72 lb/ft3 Total Propellant Volume = 3.2 ft3 Motor Weight = 80 lbs Thrust = 4610 lbs Weight of Tanks and Structure = 46 lbs Overall Vehicle Weight = 460 lbs Payload Weight = 100 lbs Propellant=N2O4/MMH Vacuum Steady State Real Engine Performance Specific Impulse (lbf-s/lbms) = 295 Throat Diameter = 5.2 inches (.13 meters) Exit Diameter = 23.2 inches (.59 meters) Area Ratio=20 Chamber Pressure = 125 psia Motor Length = 50 inches (1.27 meters) Chamber Diameter = 13.5 inches (.35 meters) Spherical Fuel/Oxidizer Tank Diameters = 18 inches Barrel Tank Barrel Diameter = 10 inches (.26 meters) Overall Length = 38.5 inches (.98 meters) Barrel Lenght = 28.5 inches (.73 meters) Characteristics of the Navy Theater-Wide Interceptor that Make It Unsuitable for Anti-ICBM Boost-Phase Interceptor Navy interceptor Needs: • To be much bigger and heavier to do the job • A Much Higher booster burnout speed for Adequate Area Coverage • Much more divert capability to deal with accelerating targets • Much higher resolution sensors for homing on the target These requirements lead to a much bigger and heavier booster to do the Job Such a Bigger and Heavier Booster is NOT compatible with storage and launch systems on standard Navy combat ships. Navy Upper Tier Interceptor Weight = 3,100 lbs GBI Interceptor Weight = 30,000 –40,000 lbs
milstar: ICBM must achieve burnout before ballistic trajectory can be projected and confirmed • Predicted ICBM trajectory must impact in defended area • SM-3 launch does not occur until after track developed and weapon system processes completed (assuming perfect sensor knowledge, approximately one minute after ICBM burnout, can be up to 2-3 minutes) • ICBM achieves burnout approximately 130 to 180 seconds after launch • Earliest SM-3 launch approximately 190 to 240 seconds after ICBM launch • ICBM too fast for an SM-3 to catch up to and intercept • ICBM speed and range well beyond SM-3 capability before launch possible from Aegis EPAA Missile Defense assets http://photos.state.gov/libraries/russia/231771/PDFs/EPAA%20Technical%20Overview%20ENG.pdf
milstar: Section 2 BOOSTER CHARACTERISTICS http://www.princeton.edu/~ota/disk3/1984/8410/841004.PDF From apogee, the slowest point in their free- fall trajectory, the RVs and empty bus gain speed as they fall back to earth. RVs are more resistant to damage from directed-energy weapons than boosters, and they might be accompanied by many decoys. When these objects enter the upper atmosphere at about 100 km altitude somewhat over 2 minutes before impact, they be- gin to heat up, and the lighter objects slow down. Still lower, below 50 km altitude and less than a minute before impact, the objects undergo vio- lent deceleration and the bus breaks up. The RVs, now glowing with heat, streak toward their targets at an angle of about 23 degrees to the horizontal. ..... Studies performed for the Defense Department showed that with a 25 percent reduction in pay- load, a booster about the same size as MX could be built which would burn out in less than 1 min- ute at only 80 to 90 km, well within the sensible atmosphere. At 90 km the atmosphere is still too dense for extremely accurate RV deployment or for deployment of lightweight RV decoys and other penetration aids aimed at later defensive layers: these functions require an additional 10 to 15 seconds of precision deployment betweer 90 and 110 km. If the offense needs precision ac curacy for some of its ICBMs but fears intercept during these additional few seconds of high-alti tude operation, mounting one or two RVs or each of several “microbuses” instead of all the RVs on a single bus affords some protection. Each microbus would contain a simple guidance sys tern only good enough to carry the RVs from up per stage burnout to 110 km. Instead of present ing one target above 90 km, therefore, such i booster would present several targets.
milstar: Capability tradeoffs for the IIB are open now, though there are a few boundaries that are surfacing. To make use of the MK 41 vertical launch systems on Aegis ships today, the missile’s diameter must fit. The weapon will also likely use solid fuel. Should liquid fuel be required, the Navy is unlikely to support the program because the service does not allow it on ships, and the program would crater without Navy support. And the weapon must be deployed by 2020. Industry sources suggest that O’Reilly i s in favor of a 27-in.-dia. booster, which is the largest size that can be accommodated by the MK 41. This has not been issued as a requirement, however. http://missiledefense.wordpress.com/2011/06/14/pentagon-mulls-hurdles-to-early-missile-intercept/ Raytheon acknowledges that the MDA is leaning toward a 27-in. booster. The MK 41 launcher can accommodate five 27-in. boosters versus eight of today’s SM-3 IAs. The SM-3 IA/Bs are 13.5 in. in diameter, with the IIA planned as an upgrade to a 21-in. frame. Raytheon is leaving the door open to a IIA upgrade for the IIB design because of what company officials say is a track record of SM-3s exceeding capability.
milstar: . Первое приближенное к боевому испытание было проведено в Калифорнии 13 сентября 1985 г. Запущенная с истребителя F-15 ракета «СРЭМ-Альтаир» уничтожила американский спутник «Солуинд» па высоте 450 км. http://www.testpilot.ru/usa/vought/asat/asat.htm Считалось, что АРКП будет признан годным к выполнению боевых задач, если вероятность поражения десяти целей составит 0,5. В состав комплекса входит самолет-носитель (модернизированный истребитель F-15) и 2-ступеичатая ракета ASAT (Anti-Salellile). Вес ракеты около 1200 кг, длина 6,1 м, диаметр корпуса 0,5 м. Ракета подвешивается под фюзеляжем. В качестве двигательной установки первой ступени применен усовершенствованный ракетный твердотопливпый двигатель тягой 4500 кг (устанавливается на управляемой ракете Боинг СРЭМ), второй - твердотопливный двигатель тягой 2720 кг (в четвертой ступени ракеты-носителя «Скаут» - ускоритель Thiokol «Альтаир» III). Полезной нагрузкой является малогабаритный перехватчик MHIV (Miniature Homing Intercept Vehicle) фирмы Vought, имеющий вес 15,4 кг, длину 460 мм и диаметр около 300 мм. The ASM-135 was launched from an F-15A in a supersonic zoom climb. The F-15's mission computer and heads-up display were modified to provide steering directions for the pilot. http://www.designation-systems.net/dusrm/m-135.html
milstar: OPTIMUM SUPERSONIC CLIMB http://deepblue.lib.umich.edu/bitstream/2027.42/76507/1/AIAA-1994-3469-679.pdf http://www.airforce-magazine.com/MagazineArchive/Documents/2005/February%202005/0205zoom.pdf
milstar: With regard to the F-15 Streak Eagle climb records, a chapter in the book 'Air Superiority Blue - The F-15 Story' has a few facts about the record attempts. The book details the F-15 program as written by the design and engineering team. Quite a good read. The engines were spec P&W F100 engines, although the engineers made careful adjustments that increased allowable ITT by 50 deg F. This added about 3% to the engines thrust, though it didn't exceed the metallurgical limits of any of the components. After the eight records were set, both engines were inspected and returned to the wider fleet. Grand Forks Nth Dakota in January was chosen as the location for the attempts.."to pick a place where the air was as dense as possible for as much of the flightpath as possible". Any hardware that could be safely removed and still maintain the CoG limits was taken out.(incl. flap actuators & gun) The eight records set were (from a standing start): 3000m/9842ft - 27.6sec 6000m/19,685ft - 39.3sec 9000m/26,527ft - 48.9sec 12000m/39,370ft - 59.4sec 15000m/49,212ft - 77.05sec 20000m/65,617ft - 122.95sec 25000m/82,021ft - 160.95sec 30000m/98,425ft - 207.6sec The 6000, 9000 and 12000m records were set on the same flight. All records up to 12000m were set by accellerating level to 485KIAS after lift-off, then 5g rotate to 80 deg nose up. The aircraft was supersonic through about 6000'. The higher records were set using unique profiles designed for each attempt, but each involved a similar climb entry using 2.5g immelman from 485KIAS after liftoff, then level(ish) accelleration at about 32000' before entering climb so-mewhere above M2.0 at about 60 deg nose up. Take off run was about 400ft (seven aircraft lengths). http://www.pprune.org/dg-p-general-aviation-questions/429348-time-climb-records-3.html
milstar: Why More Acceleration Capability is Better A ballistic target will decelerate at it reenters the atmosphere. Depending on the engagement geometry, some or all of the deceleration could appear as a target maneuver to a pursuing interceptor. To first order, the deceleration experienced by the ballistic target is proportional to the square of its initial velocity and the sine of the reentry angle (see Chapter 17 of Reference 1). http://www.princeton.edu/sgs/publications/sgs/pdf/8_1Zarchan.pdf Typical maximum deceleration levels are shown in Figure 9. We can see that a target whose initial speed is 6000 ft/s with an atmospheric reentering angle of 45 degrees will experience a maximum deceleration of 6 g. If the initial speed increases to 8000 ft/s the maximum deceleration would increase to 12 g. An initial speed of 10,000 ft/s would give rise to a maximum deceleration of 18 g. If for practical reasons the minimum achievable time constant was 0.2 s, Figure 10 shows how the miss distance varies with flight time (or time to go at which the target maneuvers) for the case in which there is a 6 g target maneuver. We see that for the case of an interceptor with an infinite accelera- tion capability, the missile is vulnerable to miss distances in excess of 2 ft for flight times of less than 1 s (i.e., short seeker acquisition range) or for maneu- vers which occur with less than 1 s to go before intercept. The miss can be as large as 10 ft if the maneuver occurs at approximately 0.5 s before intercept even if the seeker had an infinite acquisition range. If the missile has a 30 g acceleration capability (i.e. five times the maneuverability of the target) the results remain unchanged. However, if the missile has an 18 g acceleration capability (i.e., three times the maneuverability of the target) then the vulner- ability of the missile can increase substantially. Therefore, from Figure 10 we see that more acceleration capability is bet- ter (i.e., miss gets smaller as acceleration capability increases). For endoat- mospheric missiles the maximum achievable angle of attack will determine how much of an acceleration capability the missile will have. For a given angle of attack the missile acceleration capability will decrease with increasing alti- tude. Against low-speed aircraft targets this phenomenon is not a problem since the aircraft maneuverability will also decrease with increasing altitude. However, against high-speed ballistic targets this presents a guidance system challenge since the target can easily out maneuver the missile for high alti- tude intercepts (i.e., see Figure 9). Decreasing the intercept altitude (i.e., where the ballistic target deceleration will be smaller) is often not possible for population safety reasons. In more conventional endoatmospheric missiles, the maximum angle of attack is chosen to avoid cross-coupling problems within the flight control sys- tem. However since needed missile acceleration is proportional to the square of the angle of attack (i.e., see Chapter 22 of Reference 1) there is a big advan- tage in pushing the limits of flight control technology in order to get more maneuverable interceptors. 
milstar: Все головные части ракеты оснащаются усовершенствованным комплексом средств преодоления ПРО, разработанным в ЦНИРТИ. . Для комплекса средств преодоления ПРО ракеты 15А14 впервые были созданы квазитяжелые ложные цели, позволяющие имитировать характеристики боевых блоков практически по всем селектирующим признакам на внеатмосферном участке траектории и значительной части атмосферного. На нисходящем АУТ движение ББ имитируется благодаря применению специального твердотопливного двигателя "разгона", не имеющего аналогов в мировой практике, прогрессивно (в 20 раз) возрастающая тяга которого компенсирует силу аэродинамического торможения ложной цели. http://rbase.new-factoria.ru/missile/wobb/15a14/15a14.shtml
milstar: Srawnenie konstrukzij boewix blokow i traektorij MARV str. 21-27 ########################################### 1. Pershing-2 2.Agni BGRV 4.2 metra dlinnoj ruli ,dwigatel ,yabch 3.Kitaj/Pakistan -M11 wes yabch okolo 35 % ot 1762 pounds 4. Topol-M http://www.scribd.com/doc/73116189/Ballistic-Glide-Re-Entry-Vehicle-BGRV-and-Indian-Missile-Program
milstar: There are multiple ways for the designer to provide maneuverable capability in a re-entry vehicle, 1. ...moveable flaps which can provide one, two, or three degrees of freedom 2. ...Control can also be effected by moving a mass laterally in the vehicle to offset the vehicle’s center of gravity.The resulting mass asymmetry is equivalent to an aerodynamic asymmetry. ################################## 3. ....Another aerodynamic approach is jet interaction, but this appears best suited to steering out navigational errors rather than defensive maneuvering. ############################################################ The common element is that the additional design variable of L/D lift to drag ratio is introduced. -------------------------------------------------------------------------------------------------------- http://exoaviation.webs.com/pdf_files/Atmospheric%20Re-Entry.pdf
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