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Início
Dispositivo: B43A-459B-5EA4
Voo ID: 1218Mostrar eventos
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Conjuntos de dados
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⚠️
Voo de teste detetado
Isto parece ser um voo de teste ou não-foguete (ex. lanço à mão, teste de vácuo/pressão). Os dados podem não representar um voo real.
●No motor burnout detected
●Gyroscope not responding (all zero readings)
●Accelerometer frozen/saturated (constant readings)
Resumo do voo
Altitude
Apogeu
36.36 Metros
Tempo até apogeu
5.51 seconds
Altitude fim combustão
-1.21 m
Altitude vel. máx.
-76.83 m
Altitude ejeção
-1.21 m
Altitude aterragem
36.36 m
Estabilidade
Pontuação estabilidade
0.1 / 100 (Fraco)
Detalhes de estabilidade
Inclinação no fim da queima (20%)0
Consistência de inclinação (15%)0
Taxa arfagem/guinada (30%)0
Amortecimento (20%)0
Retidão de empuxo (15%)0
Velocidade
Máx. subida
135.96 m/s
Máx. descida
-509.44 m/s
No fim combustão
0.000 m/s
Vel. aterragem
0.000 m/s
Vel. descida
0.000 m/s
Vel. ejeção
54.84 m/s
Recovery
Single deploy (no dual deploy detected)
Aceleração
Máx. subida
14 G
Máx. descida
14 G
Máx. durante combustão
14 G
Média subida
14 G
Média combustão
14 G
Tempos
Fim combustão (primeiro)
0 seconds
Apogeu
5.51 seconds
Possível ejeção
0 seconds
Aterragem
5.51 seconds
Saída #1 ON
0 seconds
Saída #1 OFF
0 seconds
Ângulos
Inclinação rampa
89.94°
Incl. máx. até fim comb.
90.07°
Rolagem no lançamento
89.94°
Arfagem no lançamento
3.60°
Rotação máx. (comb.)
0 dps
Rotação média (comb.)
0 dps
Geral
Data envio
08-Mar at 15:15
Amostras de dados
1099
Tempo total gravação
22.000 s
Média amostras/s
49.9
Número de bloqueios
0
Altitude gravação
120.21 m
Lançamento após arranque
10m 45s
Eixo de referência
Y
Bateria & temperatura
Bateria início
27%
Bateria fim
27%
Temperatura início
18.25°C
Temperatura fim
18.17°C
Temp. MT1 lançamento
0°C
⚠ Bateria fraca — carregar antes do próximo voo
Regras de saída
Sem regras configuradas
Animação dos dados
FLIGHT 1218
36.36 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)
Sem imagens
Foguete associado
✅ Active
1
My Lil Nuke #1
LOC Precision — Lil' Nuke
✈️ 3 flights linked
Type
Kit build
Diameter
57.4mm
Length
749.3mm
Dry weight
368.5g
Mod
Modified
Stages
1
Fins
3
Recovery
Parachute
Chute
61cm
Body
Loc paper tube
Sim data from sim files
| Motor | Alt | Vel | Accel | Apogee | Source |
|---|---|---|---|---|---|
| Estes A8-3 | 135.3 m | 64.8 m/s | 29.6 G | 4.5 s | RockSim (estes_viking.rkt) |
| Estes B4-4 | 282.9 m | 105.3 m/s | 30.0 G | 6.1 s | RockSim (estes_viking.rkt) |
| Estes B6-4 | 288.1 m | 116.9 m/s | 31.0 G | 5.9 s | RockSim (estes_viking.rkt) |
| Estes C6-5 | 475.1 m | 171.4 m/s | 34.4 G | 7.5 s | RockSim (estes_viking.rkt) |
| Estes C6-7 | 483.1 m | 171.4 m/s | 34.4 G | 8.1 s | RockSim (estes_viking.rkt) |
Informações do dispositivo
Mercury V1
Este voo foi realizado num Mercury V1.
Versão hardware
Rev 2
Versão software
2.2
Última ligação
22-Mar at 16:10
Acelerómetro
32G 3-axis
Giroscópio
2000 dgps 3-axis
Sensor pressão
Bosch BMP 390
Magnetómetro
N/A
Motores do voo
1st Stage
1x
Estes
1/2A3-4
Burn time
0.36 seconds
Diameter
13.00 mm
Average thrust
3.03 N
Max thrust
7.62 N
Impulse
1.09 Ns
Impulse class
A
Total weight
6.60 g
Propellant weight
2.00 g
Propellant type
black powder
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.
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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).
Sem regras configuradas
Correspondência motor (BETA)
No motor matches, try refreshing the page.
Comparação de voo
Nenhum voo encontrado com a mesma configuração de motor.
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.
1:1 (50Hz)
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.
12000
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.
8x 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
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
⚠ O giroscópio não foi calibrado
X
0.000°
Y
0.000°
Z
0.000°
Acelerómetro
⚠ O acelerómetro não foi calibrado
X
0.000 mG
Y
0.000 mG
Z
0.000 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.
Merc8349
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.
5 dBm (default)
Modo suspensão
i
Controls whether the device enters low-power sleep when idle.
Normal (sleep when idle)
Monitor bateria
i
Monitors battery voltage during the flight.
DISABLED
Cloud group
i
The cloud group / category this flight is assigned to.
General use
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)
1000
Ch6 max pulse (µs)
2000
Ch6 frequency
50 Hz
Ch6 angle ON
170.00°
Ch6 angle OFF
10.00°
Ch6 on time
2.00s
Channel 7 mode
ON = HIGH
Ch7 min pulse (µs)
1000
Ch7 max pulse (µs)
2000
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.
No I2C servo board was connected for this flight.
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.
0.1500 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.
0.750
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.
0.00100 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.
287.05 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.
OFF (default)
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.
Medium (default)
Target altitude
i
The target apogee altitude in meters. The air brake system will try to slow the rocket so it reaches this altitude.
300.00 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.
5.00%
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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