Mission concept for a satellite mission totest special relativity
Başlık çevirisi mevcut değil.
- Tez No: 645625
- Danışmanlar: DR. THİLO SCHULDT, DR. NORMAN GÜRLEBECK
- Tez Türü: Yüksek Lisans
- Konular: Astronomi ve Uzay Bilimleri, Hava ve Uzay Hekimliği, Havacılık ve Uzay Mühendisliği, Astronomy and Space Sciences, Air and Space Medicine, Aeronautical Engineering
- Anahtar Kelimeler: Belirtilmemiş.
- Yıl: 2016
- Dil: İngilizce
- Üniversite: Luleå Unıversıty Of Technology
- Enstitü: Yurtdışı Enstitü
- Ana Bilim Dalı: Belirtilmemiş.
- Bilim Dalı: Belirtilmemiş.
- Sayfa Sayısı: Belirtilmemiş.
Özet
Özet yok.
Özet (Çeviri)
In 1905 Albert Einstein developed the theory of Special Relativity. This theory describes the relation between space and time and revolutionized the understanding of the universe. While the concept is generally accepted new experimental setups are constantly being developed to challenge the theory, but so far no contradictions have been found. One of the postulates Einsteins theory of Relativity is based on states that the speed of light in vacuum is the highest possible velocity. Furthermore, it is demanded that the speed of light is independent of any chosen frame of reference. If an experiment would find a contradiction of these demands, the theory as such would have to be revised. To challenge the constancy of the speed of light the socalled Kennedy Thorndike experiment has been developed. A possible setup to conduct a Kennedy Thorndike experiment consists of comparing two independent clocks. Likewise experiments have been executed in laboratory environments. Within the scope of this work, the orbital requirements for the first space-based Kennedy Thorndike experiment called BOOST will be investigated. BOOST consists of an iodine clock, which serves as a time reference, and an optical cavity, which serves as a length reference. The mechanisms of the two clocks are different and can therefore be employed to investigate possible deviations in the speed of light. While similar experiments have been performed on Earth, space offers many advantages for the setup. First, one orbit takes roughly 90 min for a satellite based experiment. In comparison with the 24 h duration on Earth it is obvious that a space-based experiment offers higher statistics. Additionally the optical clock stability has to be kept for shorter periods, increasing the sensitivity. Third, the velocity of the experimental setup is larger. This results in an increased experiment accuracy since any deviation in the speed of light would increase with increasing orbital velocity. A satellite planted in a Low Earth Orbit (LEO) travels with a velocity of roughly 7 km/s. Establishing an Earth-bound experiment that travels with a constant velocity of that order is impossible. Finally, space offers a very quiet environment where no disturbances, such as vibrations, act upon the experiment, which is practically unavoidable in a laboratory environment. This thesis includes two main chapters. The chapter titled“Mission Level”exploits orbital candidates. Here, possible orbits are explained in detail and the associated advantages and problems are investigated. It also contains a discussion about ground visibility and downlink feasibility for each option. Finally, a nominal mission scenario is sketched. The other chapter is called“Sub-Systems”. Within this chapter the subsystems of the spacecraft are examined. To examine the possible orbits it is necessary to define criteria according to which the quality of the orbits can be determined. The first criterion reflects upon the scientific outcome of the mission. This is mainly governed by the achievable velocity and the orbital geometry. The second criterion discriminates according to the mission costs. These include the launch, orbital injection, de-orbiting, satellite development, and orbital maintenance. The final criteria defines the requirements in terms of mission feasibility and risks, e.g. radiation. The criteria definition is followed by explaining the mission objectives and requirements. Each requirement is then discussed in terms of feasibility.
Benzer Tezler
- Küp uydular için tümleşik uçuş bilgisayarı ve haberleşme sistemi
A combined OBC and communication subsystem for cubesats
MUSTAFA ERDEM BAŞ
Yüksek Lisans
Türkçe
2017
Astronomi ve Uzay Bilimleriİstanbul Teknik ÜniversitesiUçak ve Uzay Mühendisliği Ana Bilim Dalı
PROF. DR. ALİM RÜSTEM ASLAN
- Atto–femto scale planarsats: A power‑first design and feasibility framework for planar, surface‑limited spacecraft
Atto–femto ölçeğinde planarsat'lar (düzlemsel uydular): düzlemsel ve yüzey-kısıtlı uzay araçları için güç-öncelikli bir tasarım ve fizibilite çerçevesi
MEHMET ŞEVKET ULUDAĞ
Doktora
İngilizce
2026
Havacılık ve Uzay Mühendisliğiİstanbul Teknik ÜniversitesiUçak ve Uzay Mühendisliği Ana Bilim Dalı
PROF. DR. ALİM RÜSTEM ASLAN
- Integration and testing of ITÜpSAT1
İTÜpSAT1 uydusunun entegrasyonu ve testleri
ÖZGÜN SARI
Yüksek Lisans
İngilizce
2010
Havacılık ve Uzay Mühendisliğiİstanbul Teknik ÜniversitesiHavacılık ve Uzay Mühendisliği Ana Bilim Dalı
YRD. DOÇ. DR. GÖKHAN İNALHAN
- An investigation of drag for low earth orbit satellites
Alçak yörünge uydularında sürüklemenin incelenmesi
MUSTAFA KORKUT ÖZARSLAN
Yüksek Lisans
İngilizce
2023
Havacılık ve Uzay Mühendisliğiİstanbul Teknik ÜniversitesiUçak ve Uzay Mühendisliği Ana Bilim Dalı
PROF. DR. MELİKE NİKBAY
- Numerical simulation of two-dimensional collisionless plasma flows under the effect of electrostatic forces via particle in cell method
İki boyutlu çarpışmasız elektrostatik kuvvetler etkisindeki plazma akımlarının hücre yöntemi kullanılarak sayısal simulasyonu
ÖZGÜR TÜMÜKLÜ
Yüksek Lisans
İngilizce
2013
Havacılık ve Uzay MühendisliğiOrta Doğu Teknik ÜniversitesiHavacılık ve Uzay Mühendisliği Ana Bilim Dalı
PROF. DR. MEHMET CEVDET ÇELENLİGİL
YRD. DOÇ. DR. NEVSAN ŞENGİL