From f8949b29a4644ac5343238554536d537e540eb7b Mon Sep 17 00:00:00 2001 From: Anson Biggs Date: Tue, 7 Dec 2021 19:13:08 -0700 Subject: [PATCH] content --- css/custom.css | 4 +-- index.html | 78 ++++++++++++++++++++++++++------------------------ 2 files changed, 43 insertions(+), 39 deletions(-) diff --git a/css/custom.css b/css/custom.css index 5a2cbff..73148b9 100644 --- a/css/custom.css +++ b/css/custom.css @@ -20,7 +20,7 @@ header div img { margin-top: 5vh; } -@media (max-width: 992px) { +/* @media (max-width: 992px) { .p-5 { padding: 3rem; padding-bottom: 1rem; @@ -29,7 +29,7 @@ header div img { div.col-lg-6 { text-align: center; } -} +} */ a { word-break: break-all; diff --git a/index.html b/index.html index db59cb9..38a37c5 100644 --- a/index.html +++ b/index.html @@ -80,7 +80,7 @@
- LANDER Logo + LANDER Team Logo
As interest in colonizing the Moon increases, developing a sustainable method of transporting equipment and resources to - and from the lunar surface will be necessary. LANDER's + and from the lunar surface will be necessary. LANDER’s approach to this problem is a system that uses one thruster capable of vectoring thrust to control vehicle attitude and - perform propulsive landings with minimal fuel use. However, - key to the design challenge is creating a suitable test - environment for such a system that can simulate variables, - such as lunar gravity and a lack of atmosphere. Project LANDER + perform propulsive landings with minimal fuel use. The key to + the design challenge is creating a suitable test environment + for a system that can simulate variables such as lunar gravity + and a lack of atmosphere while on Earth. Project LANDER endeavored to provide a potential solution by designing a - complex simulation utilizing live data. Due to an abbreviated - timetable and low-quality components, LANDER did not meet all - of its requirements for the Thrust Vector Control Test and - Operational Demonstration. However, while LANDER was a - proof–of-concept system, the team hopes to lay the foundation - for future development in this area. + complex simulation utilizing live data from a + hardware-in-the-loop system. Unfortunately, due to an + abbreviated timetable and low-quality components, LANDER did + not meet all its requirements for a successful Operational + Demonstration. However, LANDER was a proof-of-concept system, + and the team hopes to lay the foundation for future + development in this area.

@@ -137,13 +138,13 @@

Test Stand Setup

- The fully assembled system and the CAD of the system can be - seen on the figure to the right. LANDER consists of 5 - subsystems, Control Software, Avionics, Control Mechanisms, - Structure, and Test Stand. These subsysems all come together - to produce a test stand capable of simulating a vehicle - landing on the lunar surface. The test stand involves a - complex hardware in the loop computer simulation running on a + The fully assembled system and the system's CAD can be seen in + the following figure. LANDER consists of 5 subsystems, Control + Software, Avionics, Control Mechanisms, Structure, and Test + Stand. These subsystems all come together to produce a test + stand capable of simulating a vehicle landing on the lunar + surface. The test stand involves a complex + hardware-in-the-loop computer simulation running on a microcontroller.

@@ -153,7 +154,7 @@ Picture of people gathered at an SAE International Event @@ -175,12 +176,11 @@ title="proportional–integral–derivative controller is a control loop mechanism for driving an error in state (vehicle deflection) to zero." >PID - which gives commands to the simulated vehicle; the commands - are then translated back into hardware as TVC commands. The - physical vehicle encompasses the avionics, TVC, and load - cells. The physical vehicle receives commands from the - simulated vehicle and returns, calculated thrust data back to - the control software. + that gives the simulated vehicle commands; the commands are + then rendered into hardware as TVC commands. The physical + vehicle encompasses the avionics, TVC, and load cells. The + physical vehicle receives commands from the simulated vehicle + and returns calculated thrust data to the control software.

@@ -189,7 +189,7 @@ Picture of people gathered at an SAE International Event @@ -205,18 +205,21 @@

Operational Demonstration Results

The experimental thrust curve shows that the four load cells - managed to match the thrust curve for the + matched the thrust curve for the Estes F15 - within 6.2 Newton Seconds or 13.2% of expected. Due to - multiple changes in project and scope LANDER initially chose - very cheap load cells since the test stand demonstration was - originally mean't to be a verification for much larger goals. - Acquiring usable data from the load cells ended up taking much - more time and resources than the team initially expected, but - thanks to proper risk mitigation the team was able to overcome - the challenge and find a real solution. + within 6.2 Newton Seconds or 13.2% of expected. Unfortunately, + due to multiple changes in project and scope, LANDER initially + chose very cheap load cells since the test stand demonstration + originally only served as verification for much more extensive + goals, such as an actual propulsive landing. Therefore, + acquiring usable data from the load cells took much more time + and resources than the team initially expected. This time sink + could have easily been mitigated if the team had spent more + money on load cells to handle the new mission profile. + However, the team overcame the challenge thanks to proper risk + mitigation.

@@ -291,9 +294,10 @@

Final Report

At the conclusion and verification of the Operational - Demonstration LANDER has compiled a Final Report for the project. + Demonstration, LANDER has compiled a Final Report for the project. The Final Report compiles two semesters of work into one succinct document that highlights all of the findings from the project. + Open FinalReport.pdf