Cansat Competition

1. CanSat 2021 CDR: Team ### (Team Number and Name) 1
Electrical Power Subsystem Design
La hawla wala quwwata illa billah

2. CanSat 2021 CDR: Team ### (Team Number and Name)
EPS Overview (1/2)
Presenter: Name goes here
Container EPS Diagram
MCU
DC Step-Up
5V
Switch
Power
Air Pressure
sensor
Adafruit
GPS
LED
Buzzer
Camera
Module
RTC
Coin
Battery
18650 Li-Ion
3.6 Battery
XBEE
(Payload)
XBEE
(GCS)
Voltage
Sensor
Servo Motor
MCU 3.3V
Regulator
Science
Payload
1 & 2
GCS
Umbilical
Power
Component Purpose
MCU
All components in the container will be driven by MCU
and powered by single series 18650 Lithium-Ion battery
Power
1. Single 18650 Li-Ion 3.6V Battery used for supply
2. A 3V coin battery used for RTC external supply
3. External power switch will be used to ON/OFF the
power and also used to reset the container.
4. DC step-up used to step up voltage from battery
level 3.6V to ±5V for supply needed.
5. Voltage regulator from MCU used to reduce the
power to 3.3V
Sensors
and Other
1. RTC will be used for time storage when the power
off and also used for mission time.
2. The camera used to record Payload’s release as it
descent.
3. Air Pressure sensor is used to measure altitude.
4. A servo motor used to release the payload.
5. GPS used to estimate the current position of the
container.
6. 92 dB buzzer and LED will be used for container
indicator and interface.
Communication
Two XBEE module will be used for container
communication with payload and GCS.
USB

3. CanSat 2021 CDR: Team ### (Team Number and Name) 3
EPS Overview (2/2)
Presenter: Name goes here
Payload EPS Diagram
MCU
Switch
Power
Air
Temperature
Sensor
6-DOF IMU
Li-Ion
Battery
XBEE
(Payload’s)
Indicator
LED
Container
Voltage
divider
Air Pressure
Sensor
Umbilical
Power
Component Purpose
MCU
All components in the container will be driven by MCU
and powered by single series 14500 Lithium-Ion battery
Power
1. Single 14500 3.7 V used for external supply.
2. A power switch (external on/off switch) will be used
to connect or disconnect the power and also used to
reset the payload.
3. The voltage regulator from MCU is used to arrange
voltage from MCU
Sensors
and Other
1. The LED power are integrated with MCU
2. The battery voltage will be measured by the voltage
divider by 50%.
3. We will be used 6-DOF IMU to measure rotation
rate of payload after released.
4. We will used Air pressure sensor to measure
altitude.
5. The air temperature sensor used to measured air
temperature.
Communication
XBEE module will be used for communication with
container.
USB
MCU
3.3V
Regulator

4. EPS Changes Since PDR
CanSat 2021 CDR: Team ### (Team Number and Name) 4
CanSat 2021 CDR: Team ### (Team Number and Name) 4
Presenter: Name goes here
PDR CDR Rationale
Payload Battery (Series
Toshiba ER3V 3.7 V)
Payload Battery (Soshine
LS1450 3.6V)
Toshiba ER3V battery has Lower discharge
current (only 1mA) and Soshine 14500 have 1.5 A
discharge current.
Container Battery (Parallel
Shaft LS 14500)
Container Battery (SONY
VTC6)
Our fault at PDR, we don't read datasheet well.
The Shaft LS14500' are not rechargeable, so we
use SONY VTC6, because better capacity, better
discharge then Shaft LS 14500, and
rechargeable.
Container Electrical Block
Diagram : Servo,camera,
and LED in container are
powered by 5V from
StepUp.
Container Electrical Block
Diagram : Servo,camera,
and LED in container are
power direct by 3.7V from
battery.
The output PWM from Step up doesn't match for
Servo supply. So we use 3.7V supply from battery
directly.
Payload Electrical Block
Diagram : The voltage from
battery will be step up to 5v
and regulate to 3.3 volt to
supply MCU and all
sensors.
Payload Electrical Block
Diagram : The voltage from
3.7 V battery will be supply
to MCU directly at 5V pin,
and the sensor drive by
3.3V from MCU.
It will save space from PCB and base on test the
CDR Payload Block Diagram is work well.

5. CanSat 2021 CDR: Team ### (Team Number and Name) 5
EPS Requirements
Presenter: Name goes here
RN Requirement Rationale Priority
Verification
A I T D
RN#25
The science payload shall measure altitude using an
air pressure sensor.
CReq HIGH ✅ ✅ ✅
RN#26 The science payload shall measure air temperature. CReq HIGH ✅ ✅
RN#27
The science payload shall measure rotation rate as it
descends.
CReq HIGH ✅ ✅ ✅
RN#28
The science payload shall transmit all sensor data
once per second.
CReq HIGH ✅ ✅ ✅ ✅
RN#31
The container shall include electronics to receive
sensor payload telemetry.
CReq HIGH ✅ ✅
RN#35 The container shall measure its battery voltage. CReq HIGH ✅ ✅
RN#38
The container and science payloads must include an
easily accessible power switch that can be accessed
without disassembling the CanSat and science
payloads and in the stowed configuration.
CReq HIGH ✅ ✅
RN#39
The container must include a power indicator such as
an LED or sound generating device that can be easily
seen or heard without disassembling the CanSat and
in the stowed state.
CReq HIGH ✅

6. 6
RN Requirement Rationale Priority
Verification
A I T D
RN#41
The audio beacon must have a minimum sound
pressure level of 92 dB, unobstructed.
CReq HIGH ✅ ✅
RN#42
Battery source may be alkaline, Ni-Cad, Ni-MH or
Lithium. Lithium polymer batteries are not allowed.
Lithium cells must be manufactured with a metal
package similar to 18650 cells. Coin cells are allowed.
CReq HIGH ✅
RN#44
An easily accessible battery compartment must be
included allowing batteries to be installed or removed
in less than a minute and not require a total
disassembly of the CanSat.
CReq HIGH ✅ ✅
RN#45
Spring contacts shall not be used for making electrical
connections to batteries. Shock forces can cause
momentary disconnects.
CReq HIGH ✅ ✅
RN#47
The CanSat shall operate for a minimum of two hours
when integrated into the rocket.
CReq HIGH ✅ ✅ ✅ ✅
RN#62
The ground station shall include one laptop computer
with a minimum of two hours of battery operation,
XBEE radio and a hand-held antenna.
CReq HIGH ✅ ✅
EPS Requirements

7. CanSat 2021 CDR: Team ### (Team Number and Name) 7
Container Electrical Block Diagram
Presenter: Name goes here
Voltage
Sensor
Teensy 3.6
BME280
BUZZER
Motor Servo
LED Indicator
Adafruit
GPS
VIN Digital~
Digital~
Serial4
Camera
SQ111
XBEE2
XBEE1
Digital~
Serial5
Li-Ion
Battery
3.6V
GND
3.6V
GND
3.3V
GND
3.3V
GND
3.3V
Antenna
Antenna
±3.6V
Serial1
Digital
GND
GND
3.3V
3.3V
3.6V
5V
3.6V
GND
I2C2
RTC
GND
Coin Battery
3V
3V
± 3V
I2C0
UART
UART
UART
I2C0
PWM
PWM
GND
I2C2
I2C0
Digital
+
-
5V Boost
GND
Switch
NO
C NC
Vin Vout 3.3V
+
-
I2C0
GND
GND
MCU
Power
Sensor And Other
Communication
Umbilical
Power
USB
3.6V
5V
3.3V
Measured
Voltage

8. CanSat 2021 CDR: Team ### (Team Number and Name) 8
Container Electrical Block Diagram
Presenter: Name goes here
1. The logic voltage of system has two , there are 3.3 volt and 5 volt.
2. Power switch, LED and Buzzer are jumpered with to external of system, so it is easily to show
the indicator, and easily on/off the CanSat.
3. The battery will be accessed jumper by wired to the PCB. So if we want to replace the battery,
we shouldn’t disassembling major of CanSat.
4. There are two type power source on system, from batteries and umbilical power source. The
Umbilical power source is the power from 5 Volt USB cable to USB Port in microcontroller. The
Umbilical power source is use for testing and safety inspections. So that, it don’t reduce the
power of battery voltage which is used for demonstration time.

9. Container Power Source
CanSat 2021 CDR: Team ### (Team Number and Name) 9
Presenter: Name goes here
Model
Battery
Chemistry
Voltage
(V)
Current
Capacity
(mAh)
Configuration
Number of
Cell
Current
Generates
Cost
SONY VTC6 ✅ Li-Ion 3.6 3000mAh Series 1s 15 A $ 9.30
65.2
mm
Weight: 45 g
18.5 mm
• A Sony VTC6 battery supply 3.7 volts. Single battery will be
connected to get 3.7V and 3000mAh capacity.
• The battery can generates until 15A ( 20A maximum)
• The battery supply the system until more than 2 hours

10. CanSat 2021 CDR: Team ### (Team Number and Name) 10
Container Power Budget (1/2)
Presenter: Name goes here
Component Voltage (V)
Power
Consumption (Wh)
Duty Cycles
(hr:min:sec)
Source
Adafruit Ultimate GPS V3 3.3 0.165 2:00:00 Datasheet
INA260 (Voltage Sensor) 3.3 0.0099 2:00:00 Datasheet
XBEE Pro S2C x 2 (Transmit) 3.3 0.1584 0:12:00 Datasheet
XBEE Pro S2C x 2 (Receive) 3.3 0.4092 4:00:00 Datasheet
BME 280 (Pressure + Temp) 3.3 0.00002376 2:00:00 Datasheet
SQ11-Camera 3.7 0.18 1:00:00 Estimated
Teensy 3.6 5 0.793 2:00:00 Datasheet
5V Buzzer 9dB 5 0.04 0:06:00 Datasheet
Servo SG90 3.7 0.18 0:06:00 Datasheet
LED 3.3 0.0495 0:30:00 Estimated
RTC : DS-3231 3.3 0.00099 0:30:00 Datasheet
Total 1.98601376

11. 11
Container Power Budget (2/2)
Selected Container Power: SONY VTC6 ✅
Available power = 7.72 Wh
Power consumption (Wh) = 1.986 Wh
Margins = Available power – Power consumption
= 7.72 – 1.986 = 5.714 Wh
💡For the reasons of the competition requirement, the container will be powered
by two hours of mission.

12. XBEE1
CanSat 2021 CDR: Team ### (Team Number and Name) 12
Payload Electrical Block Diagram
Presenter: Name goes here
STM32F1
Bluepill
Digital~
Serial1
Soshine 14500
3.7V
3.3V
3.3V I2C1
I2C2
5 V
GND
Switch
NO
C NC
MPU6050
3.3V
I2C2
Antenna
Vin
GND
Voltage
divider 50%
MCU
Power
Sensor And Other
Communication
3.3 V
USB Port
Umbilical Power
5v (USB’s PC
Power)
GND
3.3V
3.3V
LED Indicator
GND
UART
Analog
BME280
GND
I2C1
+
-
GND
• The 3.7V from battery will connected directly to STM32 in 5V pin, and regulated with internal 3.3V regulator from STM32.
• Switch ON/OFF will be placed to edge of pcb case.So its easily to acces switch.
• The battery will be accesed jumper by wired to the PCB and placed to external case. So if we want to replace the battery,
we shouldn’t disassembling major of CanSat.
• The Umbilical power source is use for testing and safety inspections. So that, they don’t reduce the power of battery
voltage which is used for demonstration time.

13. Payload Power Source
CanSat 2021 CDR: Team ### (Team Number and Name) 13
Presenter: Name goes here
Model
Battery
Chemistry
Voltage
(V)
Current
Capacity
(mAh)
Configuration
Number of
Cell
Current
Generates
Cost
Soshine 14500
3.7V✅
Li-Ion 3.7 900 Series 1s 2.7 A $ 3.82
Weight: 22 g
14 mm
(diameter)
50
mm
14 mm
• A Soshine 14500 battery supply 3.7 volts. Single battery will
be connected to get 3.7V and 900mAh capacity.
• The battery can generates until 2.7A The battery supply the
system until more than 2 hours

14. CanSat 2021 CDR: Team ### (Team Number and Name) 14
Payload Power Budget
Presenter: Name goes here
Component Voltage (V)
Power
Consumption (Wh)
Duty Cycles
(hr:min:sec)
Source
STM32F1 Bluepill 3.3 39.6 2:00:00 Datasheet
BME 280 (Pressure + Temp) 3.3 0.02376 2:00:00 Datasheet
MPU 6050 (6 - DOF IMU) 3.3 25.08 2:00:00 Datasheet
XBEE Pro S2C (Transmit) 3.3 39.6 0:06:00 Datasheet
XBEE Pro S2C (Receive) 3.3 204.6 2:00:00 Datasheet
LED 3.3 37.95 0:30:00 Datasheet
Voltage Divider 3.3 6.6 2:00:00 Datasheet
Total 0.35345376

15. 15
Payload Power Budget
Selected Container Power : Shosine 14500 900mAh ✅
Available power = 3.3 Wh
Power consumption (Wh) = 0.353 Wh
Margins = Available power – Power consumption
= 3. – 0.353 = 3.247 Wh
💡For the reasons of the competition requirement the payload will be powered by
two hours of mission.