Início
Dispositivo: 9C13-9ED2-5B3C
Voo ID: 1360Mostrar eventos
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Resumo do voo
Altitude
Apogeu
135.05 Metros
Tempo até apogeu
5.51 seconds
Altitude fim combustão
51.76 m
Altitude vel. máx.
41.83 m
Altitude ejeção
130.65 m
Altitude aterragem
-2.99 m
Estabilidade
Pontuação estabilidade
82.5 / 100 (Bom)
Detalhes de estabilidade
Inclinação no fim da queima (20%)93.8
Consistência de inclinação (15%)79.7
Taxa arfagem/guinada (30%)68.4
Amortecimento (20%)100
Retidão de empuxo (15%)74.9
Velocidade
Máx. subida
48.38 m/s
Máx. descida
-11.19 m/s
No fim combustão
46.230 m/s
Vel. aterragem
-5.222 m/s
Vel. descida
-5.141 m/s
Vel. ejeção
-8.41 m/s
Recovery
Single deploy (no dual deploy detected)
Aceleração
Máx. subida
6.63 G
Máx. descida
22.47 G
Máx. durante combustão
6.63 G
Média subida
-0.02 G
Média combustão
3.28 G
Tempos
Fim combustão (primeiro)
1.48 seconds
Apogeu
5.51 seconds
Possível ejeção
6.427 seconds
Aterragem
32.86 seconds
Saída #1 ON
0 seconds
Saída #1 OFF
0 seconds
Ângulos
Inclinação rampa
24.79°
Incl. máx. até fim comb.
27.36°
Rolagem no lançamento
2.68°
Arfagem no lançamento
-24.66°
Rotação máx. (comb.)
290.75 dps
Rotação média (comb.)
84.98 dps
Geral
Data envio
22-Mar at 11:02
Amostras de dados
2438
Tempo total gravação
39.500 s
Média amostras/s
61.7
Número de bloqueios
0
Altitude gravação
37.49 m
Lançamento após arranque
1m 38s
Eixo de referência
X
Bateria & temperatura
Bateria início
96%
Bateria fim
94%
Temperatura início
16.43°C
Temperatura fim
16.14°C
Temp. MT1 lançamento
0°C
Regras de saída
Sem regras configuradas
Animação dos dados
FLIGHT 1360
135.05 Meters
ALTITUDE
0.00m
VELOCITY
0.00m/s
ACCEL
0.00G
TILT
0.00°
PITCH
0.00°
ROLL
0.00°
YAW
0.00°
TIME
0.00s
AWAITING LAUNCH
ALT
altimetercloud.com
LAUNCH
T+0.00s
LANDING
BURNOUT
Motor burn complete
Nota: A animação de voo requer que o altímetro esteja montado numa orientação fixa. Calibre os sensores para melhores resultados.
Notas do utilizador
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Vídeo Youtube
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Imagens do voo (0)
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Foguete associado
Nenhum foguete associado a este voo
Informações do dispositivo
Mercury V1
Este voo foi realizado num Mercury V1.
Versão hardware
Rev 3
Versão software
2.3
Última ligação
25-Mar at 03:51
Acelerómetro
32G 3-axis
Giroscópio
2000 dgps 3-axis
Sensor pressão
Bosch BMP 581
Magnetómetro
N/A
Motores do voo
1st Stage
1x
Klima
C6-5
Burn time
1.60 seconds
Diameter
18.00 mm
Average thrust
6.00 N
Max thrust
15.00 N
Impulse
10.00 Ns
Impulse class
C
Total weight
20.50 g
Propellant weight
9.60 g
Propellant type
composite
Links
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Local de lançamento, data e hora
Clique no mapa para marcar o local de lançamento. Alterne entre vista de mapa e satélite.
No results found — try a different search.
Clique no mapa · Arraste para ajustar
Lat—
Lng—
✓ Launch location saved successfully.
✗ Could not save location — please try again.
Regras de saída
As regras permitem ao Mercury executar ações com base nas condições de voo. Cada regra tem até 4 condições (A-D).
Rule 1
After launch onlyALL conditions (AND)Active during lockout
ACTION:OUTPUT #1
Conditions
AAltitude above pad (m)>0
❌Não ativou
Rule 2
After launch onlyALL conditions (AND)Active during lockout
ACTION:OUTPUT #1
Conditions
AAltitude above pad (m)>0
❌Não ativou
Rule 3
After launch onlyALL conditions (AND)Active during lockout
ACTION:OUTPUT #1
Conditions
AAltitude above pad (m)>0
❌Não ativou
Rule 4
After launch onlyALL conditions (AND)Active during lockout
ACTION:OUTPUT #1
Conditions
AAltitude above pad (m)>0
❌Não ativou
Rule 5
After launch onlyALL conditions (AND)Active during lockout
ACTION:OUTPUT #1
Conditions
AAltitude above pad (m)>0
❌Não ativou
Rule 6
After launch onlyALL conditions (AND)Active during lockout
ACTION:OUTPUT #1
Conditions
AAltitude above pad (m)>0
❌Não ativou
Correspondência motor (BETA)
Ainda em modo de teste! Estamos a descobrir qual motor foi usado no voo.
Marca
Motor
Pontuação
Forma
Comb.
Loki
I377CT
109
81.7%
91%
AeroTech
H130W
97
83.3%
85.6%
AeroTech
J500G
94
73.6%
94.7%
Cesaroni
139-G107-WH_DT-12A
92
87.7%
88.5%
AeroTech
J520W
92
82.2%
88.3%
Contrail
J555
92
85.1%
81%
AeroTech
F35W
87
70.3%
87.5%
Cesaroni
H200-BS
86
64.4%
92.1%
Cesaroni
131-G84-GR-10A
84
76.6%
93.4%
AeroTech
F39T
84
73.8%
91.7%
Comparação de voo
Comparing against 11 other flights with the same motor configuration.
Highest apogee
The maximum altitude reached. Higher is better for altitude-focused flights.
135.05m|199.39 best8th
Best stability
Composite score from tilt, spin rate, and ascent efficiency. 100 is perfect.
82.5/100|82.5 best1st
Fastest velocity
Peak ascent velocity recorded during the flight.
48.38m/s|61.1 best5th
Best avg burn G
Average acceleration during motor burn, in G-force.
3.28G|3.56 best3rd
Longest flight
Total recording duration from launch to landing detection.
39.5s|52.3 best4th
Lowest spin
Average spin rate during burn. Lower means a straighter flight.
84.98dps|53.82 best6th
Coldest flight
Board temperature at launch. Cold conditions affect battery and sensors.
16.43C|0.16 best4th
Combustão do motor
Esta é a magnitude de saída do acelerómetro do lançamento até ao fim da combustão.
You can check this against your motors thrust data on thrustcurve.org.
Definições gerais do voo
Este é um registo das definições utilizadas para este voo. Visite a
Visite a página Meus dispositivos e configure as definições..
Pressão prevista
i
Set this to your local forecast pressure at sea level. This will offer you slightly improved accuracty for your flight, although it's not 100% essential every little helps!
Xcweather.co.uk is a decent place to grab pressures from for your location and time.
Xcweather.co.uk is a decent place to grab pressures from for your location and time.
1013.2 mbar
Deteção lançamento
i
This is the altitude above the launch pad altitude where the altimeter will trigger itself into recording / flight mode.
The altimeter keeps a constant average of the pressure while waiting for launch, it uses a simple algorithm and the pre-flight buffers to do this. The most recent 120 samples (~4 seconds) are ignored so your pre-trigger altitude won't effect the ground baseline.
For almost all uses we suggest keeping this on the 25 Meter (~82 feet) default settings. If you want to test your altimeter by throwing it in the air, or are planning a very low flight you may want to lower the setting.
The altimeter keeps a constant average of the pressure while waiting for launch, it uses a simple algorithm and the pre-flight buffers to do this. The most recent 120 samples (~4 seconds) are ignored so your pre-trigger altitude won't effect the ground baseline.
For almost all uses we suggest keeping this on the 25 Meter (~82 feet) default settings. If you want to test your altimeter by throwing it in the air, or are planning a very low flight you may want to lower the setting.
25
meters
Sample ratio
i
The altimeter runs at 50Hz however you can record every sample or every X samples in order to extend the log time. For example if you set the ratio to 1 it will save 1:1 samples, or if you set it to 3 it will save 1 in 3 samples.
1:
Max samples
i
This is the maximum samples the altimeter will log per flight. When it reaches this amount it will stop and save the recording.
0
Recording stop
i
This setting is how the altimeter decides to stop recording. You can choose either 300 or 600 samples stable or it will record until it's 10000 sample limit unless you press the BUTTON in Manual stop mode.
The samples stable method waits for the devices altitude not to change for the set number of samples. This is defined by not changing by more than +/- 1.0 meters for 98% of the samples, it's a reliable method to stop the recording after landing within 8-10 seconds (300 sample) or 16-20 seconds (600 sample).
The samples stable method waits for the devices altitude not to change for the set number of samples. This is defined by not changing by more than +/- 1.0 meters for 98% of the samples, it's a reliable method to stop the recording after landing within 8-10 seconds (300 sample) or 16-20 seconds (600 sample).
Auto: 300 samples stable
Oversampling
i
Oversampling is a internal setting of the BMP 390 pressure sensor. It is how many samples are taken for each reading. By taking multiple samples for each pressure reading the altimeter reduces noise and increases the resolution of the output.
The sensor can run at 50 samples per second in 4X mode, so we suggest leaving it in this mode as it will offer the highest accuracy.
The sensor can run at 50 samples per second in 4X mode, so we suggest leaving it in this mode as it will offer the highest accuracy.
16x Oversampling
IIR filter
i
The IIR filter is another internal sensor for the BMP390 pressure sensor. It is a Infinite impulse response filter used to enhance pressure measurement accuracy by reducing noise. It's primarily for smoothing out rapid pressure changes.
We suggest not setting this too high as it will cause delay to changes in altitude if set very high.
We suggest not setting this too high as it will cause delay to changes in altitude if set very high.
COEFF 7
Pressure filter
i
This filter is a software Kalman filter that runs on the altimeters processor.
The Kalman filter uses a prediction step based on a system model and then a correction step using new measurements to refine its estimate, it creates accurate most certain results from data with noise in it.
The Kalman filter uses a prediction step based on a system model and then a correction step using new measurements to refine its estimate, it creates accurate most certain results from data with noise in it.
Kalman 2 (default)
Lockout time
i
The Lockout time is how long the altimeter should stop making decisions and taking actions if it detects unusual high speed altitude changes that are unexpected.
These false readings can be caused by ejection charges (if the altimeter is in the same compartment as the motor ejection gases) or even when you transition to Mach speeds and can give false readings of altitude changes.
When these events are detected the system enters Lockout for the specified time while it stabalises. This effects things like triggering the output, or calculating other data.
These false readings can be caused by ejection charges (if the altimeter is in the same compartment as the motor ejection gases) or even when you transition to Mach speeds and can give false readings of altitude changes.
When these events are detected the system enters Lockout for the specified time while it stabalises. This effects things like triggering the output, or calculating other data.
750ms
Lockout change
i
This is how we detect a lockout. If the pressure changes by this much in a single sample downwards (pressure increase, lower altitude) then it's likely to be a false reading. Multiply the setting by 32 to get the speed in meters per second that it will trigger at.
1.5 meters
Sync sensors
i
The filters on the pressure sensor can cause it to lag very slightly behind the Accelerometer and Gyroscope data.
The Sync sensors option detects how far out of sync these sensors are. It then corrects the Acceleration and Gyroscope readings to match the pressure sensor.
ATIVADO (25 samples / 430.00ms)
Orientation
i
This is the orientation you intend to install the Altimeter in your rocket. It's needed to ensure completly accurate angles and orientation charts and reports. Check out the Manual for more information on this.
Upwards (text up)
IMU filter
i
The IMU filter, or fusion filter takes the data from each axis of the Gyroscope and Accelerometer to calculate the Pitch, Roll, Yaw and tilt angle from vertical.
These filters can build up some discrepency over time so it's important to calibrate your sensors to minimise this.
Madgwick 6-Axis
Launch ALP
i
This is prevention against accidental launch detection.
With this disabled the launch is based only on pressure and something that creates a low pressure can trigger the flight by accident. For example pulling your nose cone off can even trigger it.
With this enabled the rocket also needs to have seen 8 samples (0.25 seconds) of acceleration above this setting in the last 3 seconds as well as the pressure drop to trigger. There is a backup trigger of 1.05 seconds of altitude being above the launch detect setting too.
There are very few situations where this option would cause issues, so we suggest leaving it on.
With this disabled the launch is based only on pressure and something that creates a low pressure can trigger the flight by accident. For example pulling your nose cone off can even trigger it.
With this enabled the rocket also needs to have seen 8 samples (0.25 seconds) of acceleration above this setting in the last 3 seconds as well as the pressure drop to trigger. There is a backup trigger of 1.05 seconds of altitude being above the launch detect setting too.
There are very few situations where this option would cause issues, so we suggest leaving it on.
1.4G
Launch lock
i
When enabled, the altimeter locks out recording for a set period after power on to prevent false triggering during setup.
DISABLED
Static temperature
i
A fixed temperature value used for altitude calculation when the external temperature sensor is disabled or not connected.
15.00 °C
Temp sensor
i
If an external MT1 temperature sensor is connected, this controls whether it is used for logging only or also for altitude calculations.
DISABLED
Definições de saída
Este é um registo das definições utilizadas para este voo.
Saída 1 ativada
i
Disable or enable the output from being able to turn on or off.
DESATIVADO
Saída 1 gatilho
i
After apogee (altitude)
This method triggers when the altitude drops below the set altitude after apogee is detected.After apogee (time)
This method triggers the defined seconds after apogee is detected.After launch (altitude)
This method is activated if/once the altimeter exceeds the set altitude after launch.After launch (time)
This option triggers the defined seconds after launch is detected.After burnout (time)
This method triggers the defined seconds after burnout is detected.
After apogee (altitude)
Saída 1 tempo ligado
i
This is how long the output should trigger ON state when the rules are met.
2000ms
Saída 1 altitude
i
This is the altitude to trigger at if using a trigger method that works on altitude.
For example if you set this to 75m and After apogee (altitude) for the trigger then the output will turn on at 75m on descent above the launch altitude.
For example if you set this to 75m and After apogee (altitude) for the trigger then the output will turn on at 75m on descent above the launch altitude.
0 meters
Saída 1 tempo
i
This is the time variable for output triggers that work on time.
For example if you set this to 3 seconds and After apogee (time) as the trigger then the output will turn on 3 seconds after apogee.
For example if you set this to 3 seconds and After apogee (time) as the trigger then the output will turn on 3 seconds after apogee.
0 seconds
Bloqueio altitude
i
Altitude lock is a safety feature that prevents the output from triggering if the altitude is below this level when the rules are met.
50.00 m
Bloqueio inclinação
i
This is another safety feature. It can be used to disable the output if the rocket has gone too far from vertical.
For example if you set the tilt angle lock to 40 degrees then the output will not fire if the rocket is more than 40 degrees from vertical. To disable set this to 0.
For example if you set the tilt angle lock to 40 degrees then the output will not fire if the rocket is more than 40 degrees from vertical. To disable set this to 0.
0.00 °
Calibração de sensores
Desvios de calibração utilizados neste voo.
Giroscópio
X
0.490°
Y
-0.370°
Z
-0.530°
Acelerómetro
X
-14.310 mG
Y
14.090 mG
Z
11.770 mG
Definições do dispositivo
Este é um registo das definições utilizadas para este voo.
Este é um registo das definições utilizadas para este voo.
TAG dispositivo
i
A custom name or tag assigned to this device for easy identification.
Merc8554
Idioma
i
The language setting configured on the device.
en
Modo encerramento
i
Controls what happens after recording. Standard shuts down normally, Delayed keeps WiFi on for 30 seconds after landing, Stay on keeps the device powered on.
Delayed 30s
Brilho LED
i
The brightness level of the LED indicators on the Mercury. Lower values save battery.
20%
WiFi TX power
i
WiFi transmit power level. Higher gives better range but uses more battery.
12000
Modo suspensão
i
Controls whether the device enters low-power sleep when idle.
Stay awake
Monitor bateria
i
Monitors battery voltage during the flight.
DISABLED
Cloud group
i
The cloud group / category this flight is assigned to.
1
Portas GP6 / GP7
Configuração das portas GP6 e GP7 para canais pirotécnicos, servos ou outros dispositivos.
Channel 6 mode
ON = HIGH
Ch6 min pulse (µs)
0
Ch6 max pulse (µs)
1000
Ch6 frequency
0 Hz
Ch6 angle ON
50°
Ch6 angle OFF
170.00°
Ch6 on time
10.00s
Channel 7 mode
ON = HIGH
Ch7 min pulse (µs)
2000
Ch7 max pulse (µs)
1000
Ch7 frequency
50 Hz
Ch7 angle ON
170.00°
Ch7 angle OFF
10.00°
Ch7 on time
2.00s
Placa servo I2C PCA9685
Este é um registo das definições utilizadas para este voo.
Configuration for the external I2C PCA9685 servo expansion board. This board provides up to 6 additional servo channels.
Servo board
i
Enable or disable the external I2C PCA9685 servo expansion board.
ENABLED
Oscillator freq
i
The oscillator frequency of the PCA9685 chip. Default is 25000000 (25 MHz). Adjust only if your board has a different crystal.
2.00 Hz
Min pulse width
i
The minimum pulse width in microseconds for the servo range. Standard servos typically use 500-600 µs as minimum.
25000000 µs
Max pulse width
i
The maximum pulse width in microseconds for the servo range. Standard servos typically use 2400-2500 µs as maximum.
600 µs
PWM frequency
i
The PWM frequency for all servos on the board. Standard servos use 50 Hz.
2400 Hz
Servo 1
OFF: iservo_freq:50°
ON: iservo1_off10°
Time: iservo1_on170s
Servo 2
OFF: iservo1_time2.00°
ON: iservo2_off10°
Time: iservo2_on170s
Servo 3
OFF: iservo2_time2.00°
ON: iservo3_off10°
Time: iservo3_on170s
Servo 4
OFF: iservo3_time2.00°
ON: iservo4_off10°
Time: iservo4_on170s
Servo 5
OFF: iservo4_time2.00°
ON: iservo5_off10°
Time: iservo5_on170s
Servo 6
OFF: iservo5_time2.00°
ON: iservo6_off10°
Time: iservo6_on170s
Previsão e freios aéreos
Este é um registo das definições utilizadas para este voo.
The Mercury can predict apogee while coasting after burnout. These settings control the prediction calculation and optional air brake system.
Dry mass
i
The total mass of the rocket after motor burnout (dry mass). This is used for the ballistic prediction of apogee altitude. Enter the mass without the motor propellant, or the mass at burnout.
99/0/0.00 kg
Drag Cd
i
The aerodynamic drag coefficient (Cd) of the rocket. This is used with the rocket area to calculate aerodynamic drag during coast. A typical model rocket has a Cd of 0.4 to 0.8. You can find this value from OpenRocket or RockSim simulations.
0.1500
Reference area
i
The cross-sectional reference area of the rocket in square meters. This is typically the area of a circle with the body tube diameter. For example a 38mm tube has an area of approximately 0.00113 m².
0.750 m²
Gas constant
i
The specific gas constant for dry air, used in the atmospheric model for altitude and density calculations. The standard value is 287.05 J/(kg·K). You shouldn't need to change this unless you know what you're doing.
0.00100 J/(kg·K)
The following settings configure the air brake system.
Air brake enabled
i
Enables or disables the active air braking system. When enabled, the Mercury will deploy air brakes via the configured servo channel to try and reach the target altitude. Firmware 2.1+ required.
ON
Servo channel
i
Which servo output channel the air brake mechanism is connected to. GP6 and GP7 are the two onboard servo headers, I2C channels are for an external servo expander board.
GP6
Deploy speed
i
The speed at which the air brakes deploy. The Mercury gradually increases the servo angle until the predicted apogee matches the target rather than going full on/off. This setting controls how quickly it ramps up to full braking.
5.00
Target altitude
i
The target apogee altitude in meters. The air brake system will try to slow the rocket so it reaches this altitude.
0 m
Over shoot %
i
The percentage over the target altitude to aim for until within 15% of the target. This helps prevent undershooting if the prediction is slightly off early in the coast. For example, with a 1000m target and 5% early adjustment, the Mercury will aim for 1050m until it passes 850m.
300.00%
Activation altitude
i
The air brake system activates after burnout, but won't engage until the rocket has reached this percentage of the target altitude. This prevents the brakes from deploying too early when predictions may be less accurate.
20% (default)
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