Problem Definition

Background

Entry into an atmosphere is a challenging engineering problem and holds significant risk for any planetary sample return or crewed space exploration mission. Validation of aerothermal analysis tools is needed to better understand the conditions an entry vehicle must endure for more efficient design of Thermal Protection Systems (TPS). The acquisition of flight data through TPS instrumentation is the best means by which this can be achieved. The embedding of sensors into a heat shield adds mission risk and flight systems complexity, and as a result, fully embedded sensor suites are rarely flown on entry vehicles. NASA is interested in wireless sensor systems that will reduce flight systems complexity and provide mass savings compared to conventional wired systems. This reduction of risk and complexity will allow TPS embedded sensors to easily be developed and employed on entry vehicles and, as a result, more efficient design of Thermal Protection Systems can be achieved.

Problem Statement

The goal of this project is to develop and demonstrate a wireless TPS sensor architecture that can log reliable data in the NASA Ames X-Jet facility and during a balloon launch with the University of Idaho RISE team. This year’s senior design team will improve upon the previous team’s design by incorporating multiple wireless nodes and more than one sensor type into the architecture.

Benefits of Project

Very few entry vehicles have fully embedded sensor suites to gather data about the re-entry environment because of the added risk and complexity involved in implementing such a system. A wireless sensor architecture would allow greater flexibility in the placement of sensors on a vehicle. Also, removing wires would reduce complexity and weight. This project will develop a system that will receive data from multiple wireless nodes and multiple sensor types. Integrating a wireless sensor suite on future missions will provide crucial data to characterize the re-entry environment.

Deliverables

  • Wireless sensor suite that incorporates multiple nodes and sensor types
  • Integration with U of I RISE team for high altitude balloon drop

Project Objectives

First Priority
Multi-Nodal Wireless Architecture
Multiple Sensors per Node
Multiple Sensor Types per Node
Integration into RISE Balloon Test
Testing with X-Jet

Second Priority
Increased Power Density
Implement Power Saving Mode
Built in Error Checking/Correction

Third Priority
Improved Signal to Noise Ratio
Miniaturization of System

Specifications

Need Specification Target Value Unit Related Specifications
Multi-Nodal Wireless Architecture 1) Number of Nodes Architecture can Support 10    
Multiple Sensors per Node 2) Number of Sensors per Node 5    
Multiple Sensor Types per Node 3) Minimum Number of Different Sensors Per Node >= 2    
Integration with Rise Balloon 4) Maximum Size 4 x 5 x 0.5 inches 5
  5) Maximum Weight 16 ounces 4
  6) Vibration Resistance Low Susceptibility    
  7) Minimum Sensor Temperature -60 °C 13
  8) Minimum Electronics Temperature -60 °C 14
  9) Sensor Sampling Rate 1 Hz 2,3
  10) Minimum System Power Life 6 months 2
  11) Minimum Sensor Pressure 0 psi  
  12) Maximum Sensor Pressure 14 psi  
X-Jet Testing 13) Wireless Signal Range 10 meters 1
  14) A to D Resolution 12 bits  
  15) Maximum Sensor Temperature 1000 °C 7
  16) Maximum Electronics Temperature 125 °C 8

 

NASA
NASA Homepage
NASA Ames Homepage

University of Idaho
Homepage
Senior Design
ME Department
ECE Department
Thermasense

 
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