Difference between revisions of "MakerLaunch"
Spacefelix (Talk | contribs) (Added rocket specifications) |
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== Vehicle Sizing == | == Vehicle Sizing == | ||
| − | We are assuming the required delta V total will be 10,000 m/s (normal [http://en.wikipedia.org/wiki/Low_Earth_orbit#Human_use LEO orbital velocity] of around 7,800 m/s (17,448 mph) rounded to 8,000 m/s plus an added 2,000 m/s from atmospheric drag and gravitational losses) from sea-level to LEO altitude. Currently, we are looking at a three-stage solid propellant rocket that has the following specifications. | + | We are assuming the required delta V total will be 10,000 m/s (normal [http://en.wikipedia.org/wiki/Low_Earth_orbit#Human_use LEO orbital velocity] of around 7,800 m/s (17,448 mph) rounded to 8,000 m/s (17,895 mph) plus an added 2,000 m/s (4,474 mph) from atmospheric drag and gravitational losses) from sea-level to LEO altitude. Currently, we are looking at a three-stage solid propellant rocket that has the following specifications. |
{| class="wikitable" border="1" | {| class="wikitable" border="1" | ||
|- | |- | ||
| − | | 19-gram Payload Assumed | + | | 19-gram (0.04 lbm) Payload Assumed |
| ISP (seconds) | | ISP (seconds) | ||
| − | | Inert Mass (kg) | + | | Inert Mass (kg, lbm) |
| − | | Propellant Mass (kg) | + | | Propellant Mass (kg, lbm) |
| Mass Fraction | | Mass Fraction | ||
| − | | Delta V (m/s) | + | | Delta V (m/s, mph) |
| − | | Inital Mass (kg) | + | | Inital Mass (kg, lbm) |
|- | |- | ||
| First Stage | | First Stage | ||
| 210 | | 210 | ||
| − | | 7.07 | + | | 7.07, 15.59 |
| − | | 40.08 | + | | 40.08, 88.36 |
| 0.85 | | 0.85 | ||
| − | | | + | | 3,396.38, 7,597.48 |
| − | | 49.61 | + | | 49.61, 109.38 |
|- | |- | ||
| Second Stage | | Second Stage | ||
| 242.50 | | 242.50 | ||
| − | | 0.35 | + | | 0.35, 0.78 |
| − | | 2.01 | + | | 2.01, 4.42 |
| 0.85 | | 0.85 | ||
| − | | | + | | 4,009.90, 8,969.89 |
| − | | 2.46 | + | | 2.46, 5.43 |
|- | |- | ||
| Third Stage | | Third Stage | ||
| 275 | | 275 | ||
| − | | 0.02 | + | | 0.02, 0.04 |
| − | | 0.06 | + | | 0.06, 0.14 |
| 0.77 | | 0.77 | ||
| − | | 2652.11 | + | | 2652.11, 5,932.61 |
| − | | 0.10 | + | | 0.10, 0.22 |
|} | |} | ||
Revision as of 23:49, 18 September 2010
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Creator: |
Contents
[hide]Overview
This page is for the MakerLaunch project. Makers Local 256's spaceflight effort with HAL5's HALO Project to make a launcher that can win the N-Prize Competition. The N-Prize offers two cash Prizes, each of £9,999.99 (nine thousand, nine hundred and ninety-nine pounds and ninety-nine pence, sterling, $15,589.05). The prizes will be awarded to the first persons or groups to put into orbit around the Earth a satellite with a mass of between 9.99 and 19.99 grams, and to prove that it has completed at least 9 orbits with the 9th orbit occuring before 19:19:09 (GMT) on the 19th September 2011. One prize (the "single-spend-to-orbit", or "SSO" Prize) will be awarded to the first entrant to complete the challenge using a non-reusable launch system. The other prize (the "reusable vehicle" or "RV" Prize) will be awarded to the first entrant to complete the challenge using a partially or wholly reusable launch system. Both prizes carry equal status. The cost of the launch, but not ground facilities, must fall within a budget of £999.99 ($1,558.89). Entrants for the RV Prize may exceed this budget, but must demonstrate recovery of hardware such that the per-launch cost remains within £999.99 ($1,558.89). Imaginative use of string and chewing gum is encouraged. Entrants are responsible for everything, organisers are responsible for nothing. N-Prize Competition Rules In Full
Calendar
Status
- 6-8/10 - Have done some preliminary calculations on what kind of rocket would be required to put a various payload masses to Low Earth Orbit (LEO) velocity and altitude.
Concepts
Rocket Options
- Solid
- Hybrid
- Liquid
Satellite Options
- Have a Tx\Rx capability to leave small twitter like messages on the Satellite for hackerspaces to send to each other.
- Can this be done with a satellite this small?
Challenges
- Technical
- Financial
- High Cost of Spaceflight - Achieving orbit on a 1g planet with an atmosphere is a wonder in of itself given the energy required. Getting to orbit on a barely-controlled explosion is always expensive and risky. Therefore, partnerships with people who work with rocketry on the amateur level and sponsorships are a must.
Vehicle Sizing
We are assuming the required delta V total will be 10,000 m/s (normal LEO orbital velocity of around 7,800 m/s (17,448 mph) rounded to 8,000 m/s (17,895 mph) plus an added 2,000 m/s (4,474 mph) from atmospheric drag and gravitational losses) from sea-level to LEO altitude. Currently, we are looking at a three-stage solid propellant rocket that has the following specifications.
| 19-gram (0.04 lbm) Payload Assumed | ISP (seconds) | Inert Mass (kg, lbm) | Propellant Mass (kg, lbm) | Mass Fraction | Delta V (m/s, mph) | Inital Mass (kg, lbm) |
| First Stage | 210 | 7.07, 15.59 | 40.08, 88.36 | 0.85 | 3,396.38, 7,597.48 | 49.61, 109.38 |
| Second Stage | 242.50 | 0.35, 0.78 | 2.01, 4.42 | 0.85 | 4,009.90, 8,969.89 | 2.46, 5.43 |
| Third Stage | 275 | 0.02, 0.04 | 0.06, 0.14 | 0.77 | 2652.11, 5,932.61 | 0.10, 0.22 |
People
- Bendersgame
- Brokentrace
- Spacefelix
- Your Name Here
