پروژه پایتون یا نرم افزار مشابه(42253)*
چهار سال پیش منتشر شده
تعداد بازدید: 137
کد پروژه: 344800
شرح پروژه
سلام و وقت بخیر
در خصوص انجام یک پروژه الکترواپتیک مزاحمتون میشم. ممنون میشم اگه راهنمایی بفرمایید
1) A low-Earth orbit imaging system capable of providing images on-demand from an Earth control station.
OR
2) A geostationary hyperspectral imaging system capable of providing calibrated imagery from 400 nm to 12 μm.
Objectives
• Identify key system requirements that will define the performance of your system.
• Identify the components necessary for your system to operate — the full system component list.
• Develop a block diagram showing the relationships between the individual system elements.
• Perform the analyses necessary to develop the detailed specifications for the elements/subsystems in your overall system.
• Develop the system budgets necessary for your system; at a minimum a system pointing budget should be developed.
• Develop a system design document that describes your detailed system design and the expected system performance.
• Present your analysis.
عموما از پایتون استفاده میشه اما لزومی از استفاده از پایتون نیست.
تا هفته ی بعد یک گزارش اولیه از شروع پروژه نیاز دارم. و چهار هفته بعد از هفته ی اول باید پروژه رو تحویل بدم.
Option One: Mission: Commercial Imaging Satellite
Mission objective: The goals of the imaging mission are to provide a capability similar to, and if possible better than, that provided by the Worldsat-3 satellite. The end-user of the imagery would be the commercial market. The end-user will have the ability to request up-to-date imagery of any point of the Earth, within the limits of the re-visit time of a low earth orbiting satellite. In summary perform a system level design of a low-Earth orbit imaging system capable of providing images on-demand from an Earth control station.
It is not expected that this design will provide fine level details on the bus, but will establish requirements such as pointing stability and power requirements for the bus provider. The electro-optic design must be detailed enough to provide details necessary for optical/electrical/mechanical/aerospace engineers to do detailed design of subsystems.
Requirements:
• System shall operate in near-Earth orbit. Notional orbit is 300 miles above MSL
• System shall be solar powered
• System shall provide imagery from 400 nm to 1.5 micro meter
• System shall provide snap-shot images as well as along linear swaths along the orbital path
• System shall provide a minimum 80 cm resolution across the entire specified optical band
• System shall be launchable on a Falcon-X class or larger launch vehicle
• Collected imagery shall be downloaded to an Earth station within 15 minutes of collection – assume there is always a high bandwidth ground station within site of the space system
• System shall be remotely pointed. Pointing of the aperture can be done either through pointing the satellite body, using a pointing mirror, or a combination of the two. Novel methods may be proposed.
• System shall have an on-orbit lifetime of 5 years
💢Kian💢, [9/15/2022 10:08 AM]
Option 2: Mission: Hyperspectral Imaging Satellite
Mission objective: The goals of the hyperspectral mission are to provide a capability similar to, and if possible better than, that provided by the Landsat 8 satellite. The end-user of the data would be the commercial market. The end-user will have the ability to request up-to-date data of any point of the hemisphere covered by the system. In summary perform a system level design of a geostationary hyperspectral imaging system capable of providing calibrated imagery from 400 nm to 12 micro meter.
It is not expected that this design will provide fine level details on the bus, but will establish requirements such as pointing stability and power requirements for the bus provider. The electro-optic design must be detailed enough to provide details necessary for optical/electrical/mechanical/aerospace engineers to do detailed design of subsystems.
Requirements:
همیارپروژه, [9/15/2022 10:55 AM]
• System shall operate in a geostationary orbit
• System shall be solar powered
• System shall provide a calibrated imaging capability from 400 nm to 12 micro meter.
• System shall be calibrated using multiple (minimum two) methods
• System spatial resolution shall be a minimum of 1 km
• System shall provide a continuous scan
• System shall be launchable on a Falcon BFR or similar
• System shall have on on-orbit lifetime of 10 years
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