Daşıyıcı raket

Daşıyıcı raket (ing. carrier rocket) - Yer səthindən kosmosa, adətən, Yerin orbitinə və ondan uzağa yük daşıması üçün istifadə olunan raket.

Rusiyanın Soyuz TMA-5 kosmik daşıyıcısı Qazaxıstandan uçuşa başlayır.

Yükünə görə

NASA daşıyıcı raketləri Dünya orbitindən daşıdığı yük qabiliyyətinə görə aşağıdakı kimi təsnifatlandırmışdır:^[1]

• Kiçik daşıyıcı raket: < 2,000 kiloqram (4,400 funt) - misal üçün Vega^[2]
• Orta daşıyıcı raket: 2,000 to 20,000 kiloqram (4,400 to 44,100 funt) - misal üçün Soyuz ST^[3]
• Ağır daşıyıcı raket: > 20,000 to 50,000 kiloqram (44,000 to 110,000 funt) - misal üçün Ariane 5^[3]
• Çox ağır daşıyıcı raket: > 50,000 kiloqram (110,000 funt) - misal üçün Saturn V ^[4]

İstinadlar

1. NASA Space Technology Roadmaps - Launch Propulsion Systems, p.11 Arxivləşdirilib 2016-03-24 at the Wayback Machine: "Small: 0-2t payloads, Medium: 2-20t payloads, Heavy: 20-50t payloads, Super Heavy: >50t payloads"
2. "Launch services—milestones". Arianespace. 24 November 2015 tarixində arxivləşdirilib. İstifadə tarixi: 19 August 2014.
3. "Welcome to French Guiana" (PDF). arianespace.com. Arianespace. 23 September 2015 tarixində orijinalından (PDF) arxivləşdirilib. İstifadə tarixi: 19 August 2014.
4. HSF Final Report: Seeking a Human Spaceflight Program Worthy of a Great Nation Arxivləşdirilib 2019-02-16 at the Wayback Machine, October 2009, Review of U.S. Human Spaceflight Plans Committee, p. 64-66: "5.2.1 The Need for Heavy Lift ... require a “super heavy-lift” launch vehicle ... range of 25 to 40 mt, setting a notional lower limit on the size of the super heavy-lift launch vehicle if refueling is available ... this strongly favors a minimum heavy-lift capacity of roughly 50 mt ..."

Xarici keçidlər

• S. A. Kamal, A. Mirza: The Multi-Stage-Q System and the Inverse-Q System for Possible application in SLV, Proc. IBCAST 2005, Volume 3, Control and Simulation, Edited by Hussain SI, Munir A, Kiyani J, Samar R, Khan MA, National Center for Physics, Bhurban, KP, Pakistan, 2006, pp 27–33 Free Full Text
• S. A. Kamal: Incorporating Cross-Range Error in the Lambert Scheme, Proc. 10th National Aeronautical Conf., Edited by Sheikh SR, Khan AM, Pakistan Air Force Academy, Risalpur, KP, Pakistan, 2006, pp 255–263 Free Full Text
• S. A. Kamal: The Multi-Stage-Lambert Scheme for Steering a Satellite-Launch Vehicle, Proc. 12th IEEE INMIC, Edited by Anis MK, Khan MK, Zaidi SJH, Bahria Univ., Karachi, Pakistan, 2008, pp 294–300 (invited paper) Free Full Text
• S. A. Kamal: Incompleteness of Cross-Product Steering and a Mathematical Formulation of Extended-Cross-Product Steering, Proc. IBCAST 2002, Volume 1, Advanced Materials, Computational Fluid Dynamics and Control Engineering, Edited by Hoorani HR, Munir A, Samar R, Zahir S, National Center for Physics, Bhurban, KP, Pakistan, 2003, pp 167–177 Free Full Text
• S. A. Kamal: Dot-Product Steering: A New Control Law for Satellites and Spacecrafts [sic], Proc. IBCAST 2002, Volume 1, Advanced Materials, Computational Fluid Dynamics and Control Engineering, Edited by Hoorani HR, Munir A, Samar R, Zahir S, National Center for Physics, Bhurban, KP, Pakistan, 2003, pp 178–184 Free Full Text
• S. A. Kamal: Ellipse-Orientation Steering: A Control Law for Spacecrafts [sic] and Satellite-Launch Vehicles, Space Science and the Challenges of the twenty-First Century, ISPA-SUPARCO Collaborative Seminar, Univ. of Karachi, 2005 (invited paper)
• Time lapse captured from a satellite of a rocket carrying 35 satellites