Vol 1246
Flight 1246
Mercury V1 Rev 2 · firmware 2.2
Apogée
199.39m
7.09 s after launch
Max. montée
0m/s
peak ascent
Max. pendant combustion
6.64G
during the burn
Atterrissage
17.18s
touchdown 0 m/s
ZOOM TO
s
s
Résumé du vol
The flight, moment by moment
Liftoff
0 s
Inclinaison rampe11.22°
Thrust calc pad tilt7.4°
Launch detected
1.059 s
Altitude25.29 m
Vitesse0 m/s
Fin combustion (premier)
1.75 s
Altitude55.05 m
Vitesse0.000 m/s
Éjection possible
6.874 s
Altitude194.71 m
Vitesse0 m/s
Apogée
7.09 s
Altitude199.39 Mètres
Incl. max. jusqu’à fin comb.15.44°
Atterrissage
17.17 s
Altitude5.73 m
Max. descente0 m/s
Stabilité89.1%Excellent
Inclinaison à la fin de combustion (20%)81.4
20% · Launch tilt 7.4°
Tangage/lacet (30%)93.4
25% · Coning 26.4/39.5°/s
Coning · boost (25%)86.4
25% · Spin 25°/s
Rectitude de poussée (15%)92.8
30% · Thrust 98.6%
Rocket information
Calculated from the flight data alone
Apogee lost to tilt1.66 m
flown vertical ≈ 201 m · from the thrust-calculated tilt
Chute opening peak2.3 G
largest deceleration after ejection
Average descent rate18.35 m/s
ejection to landing · 10.30 s
Batterie & température 45% → 43% · Température début 13.89 → 14.02 °C · Lancement après démarrage 4m 24s
Altitude
Apogée199.39 Mètres
Temps jusqu’apogée7.09 s
Altitude fin combustion55.05 m
Altitude vitesse max.2.34 m
Altitude éjection194.71 m
Altitude atterrissage5.73 m
Altitude enregistrement294.43 m
Vitesse
Max. montée0 m/s
Max. descente0 m/s
À fin combustion0.000 m/s
Vitesse descente0.000 m/s
Vitesse éjection0 m/s
Vitesse atterrissage0.000 m/s
Accélération
Max. pendant combustion6.64 G
Max. montée6.64 G
Max. descente2.3 G
Moy. montée0.29 G
Moy. combustion3.49 G
Temps
Fin combustion (premier)1.75 s
Apogée7.09 s
Éjection possible6.874 s
Atterrissage17.17 s
Sortie #1 ON0 s
Sortie #1 OFF0 s
Angles
Inclinaison rampe11.22°
Thrust calc pad tilt7.4°
Incl. max. jusqu’à fin comb.15.44°
Roulis au lancement4.95°
Tangage au lancement-10.08°
Rotation max. (comb.)162.69 dps
Rotation moy. (comb.)53.97 dps
Recovery
Single deploy
No dual deploy detected on this flight.
Général
Date envoi17-Mar at 17:29
Échantillons1548
Durée totale enregistrement30.300 s
Moy. échantillons/s51
Nombre de verrouillages10
Lancement après démarrage4m 24s
Axe de référenceX
Batterie & température
Batterie début45%
Batterie fin43%
Température début13.89°C
Température fin14.02°C
Temp. MT1 lancement0°C
Règles de sortie
Aucune règle configurée
Notes utilisateur
Aucune note
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Vidéo Youtube
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Images du vol 0
Aucune image
Moteurs du vol
1st stage · 5s delay
Durée combustion
1.6 s
Diameter
18.00 mm
Poussée moyenne
6 N
Poussée max.
15 N
Poids total
20.50 g
Poids propergol
9.60 g
Type propergol
composite
Liens
Impulsion10Ns
Poussée max.15N
Durée combustion1.6s
Classe impulsionC
1st stage thrustloading curve…
Motor data by ThrustCurve.org
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Fusée associée
Aucune fusée associée à ce vol
Flight mass
Liftoff mass123.7gestimated
Mass at burnout114.1gestimated
No mass is set for this flight, so Motor thrust (N) uses a mass estimated from the measured burn and the motors’ rated impulse. Set the rocket’s mass for the measured impulse and specific impulse.
Motor thrust (N) is on the chart, under Acceleration.
Other flights on this motor
11 · highest first
Règles de sortie
Les règles permettent au Mercury d’effectuer des actions selon les conditions de vol. Chaque règle a jusqu’à 4 conditions (A-D).
Aucune règle configurée
Correspondance moteur (BETA)
Encore en phase de test ! Nous cherchons à deviner quel moteur a été utilisé.
Marque
Moteur
Score
Forme
Comb.
AeroTech
G67R
103
90.1%
95.4%
AeroTech
I215R
95
90.8%
94%
Klima
C6
92
86.8%
89.5%
Estes
D12
87
81.2%
87.8%
Loki
G70CT
76
80.8%
85.4%
Estes
E16
63
85.5%
91.2%
AeroTech
F37
62
70.5%
89.5%
AeroTech
F32
56
82.8%
84.1%
AeroTech
K750ST
53
72.1%
95%
AeroTech
E24C
51
79.2%
87.1%
Linked flights
No linked flights yet.
Site de lancement, date & heure
Imagery © Esri, Maxar, Earthstar Geographics
Cliquez sur la carte · Glissez pour ajuster
Canopy height from the Meta and WRI High Resolution Canopy Height Maps v2 (Meta and World Resources Institute, 2026; source imagery © 2016 Vantor), used under CC BY 4.0. Ground elevation built from Terrain Tiles (Mapzen and AWS Open Data), derived from 3DEP and GMTED courtesy of the U.S. Geological Survey, SRTM courtesy of NASA, and ETOPO1 courtesy of NOAA. Map and imagery credited on the view above.
Site nameUnnamed siteLat47.524776Lng7.551312Ground level342.8 m · 1125 ftDate de lancement—Heure de lancement—
No conditions have been recorded for this flight.
About sea-level pressure and QNH
Sea-level pressure is kept as given: the model’s own, or the figure entered from a forecast or report. QNH is that pressure the way an altimeter setting means it, through the standard atmosphere, and is what the adjusted apogee and the adjusted CSV use.
Model values, not observations. NOAA GFS: weather data by Open-Meteo.com (CC BY 4.0). Ensemble: NOAA GEFS.
Animation des données
FLIGHT 1246
199.39 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
Note : L’animation de vol nécessite que votre altimètre soit monté dans une orientation fixe. Calibrez vos capteurs pour de meilleurs résultats.
Mercury V1
Ce vol a été effectué sur un Mercury V1.
The hardware
Version matérielRev 2
Version logiciel2.2
Dernière connexion21-Mar at 11:05
Capteur pressionBosch BMP 390
Accéléromètre32G 3-axis
Gyroscope2000 dgps 3-axis
MagnétomètreN/A
Flights from this altimeter
8 of 8
Flight #1335
126.4m
Flight #1334
161.2m
Flight #1333
154.5m
Flight #1332
40.2m
Flight #1299
148m
Flight #1298
147.1m
Flight #1246 this flight
199.4m
Flight #1243
71.2m
Flight #1298
91/100
Flight #1246 this flight
89/100
Flight #1333
88/100
Flight #1332
87/100
Flight #1335
87/100
Flight #1299
82/100
Flight #1334
80/100
Flight #1243
79/100
Flight #1246 this flight
199.4m
Flight #1334
161.2m
Flight #1333
154.5m
Flight #1299
148m
Flight #1298
147.1m
Flight #1335
126.4m
Flight #1243
71.2m
Flight #1332
40.2m
Flight #1243
52.8s
Flight #1333
52.3s
Flight #1334
33.8s
Flight #1298
32.4s
Flight #1246 this flight
30.3s
Flight #1335
28.8s
Flight #1332
25.2s
Flight #1299
24.9s
Settings, as they were for this flight
Paramètres généraux
Pression prévue
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
Détection lancement
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
Ratio échantillonnage
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. échantillons
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
Arrêt enregistrement
i
This setting is how the altimeter decides to stop recording. You can choose either 450 (~9s) or 900 (~18s) samples stable or it will record until the max samples 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: 450 samples stable (~9s)
Suréchantillonnage
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
Filtre IIR
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
Filtre pression
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)
Temps verrouillage
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
Changement verrouillage
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
Synchro capteurs
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.
ACTIVÉ (14 samples / 275.00ms)
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)
Filtre IMU
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
ALP lancement
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
Verrouillage lancement
i
When enabled, the altimeter locks out recording for a set period after power on to prevent false triggering during setup.
DISABLED
Température statique
i
A fixed temperature value used for altitude calculation when the external temperature sensor is disabled or not connected.
15.00 °C
Capteur temp.
i
If an external MT1 temperature sensor is connected, this controls whether it is used for logging only or also for altitude calculations.
DISABLED
Paramètres de sortie
Sortie 1 activée
i
Disable or enable the output from being able to turn on or off.
DÉSACTIVÉ
Sortie 1 déclencheur
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)
Sortie 1 durée
i
This is how long the output should trigger ON state when the rules are met.
2000ms
Sortie 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
Sortie 1 temps
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
Verrouillage 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
Verrouillage inclinaison
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 °
Étalonnage capteurs
Décalages de calibration utilisés pour ce vol.
Gyroscope⚠ Le gyroscope n’a pas été calibré
X0.000°
Y0.000°
Z0.000°
Accéléromètre⚠ L’accéléromètre n’a pas été calibré
X0.000 mG
Y0.000 mG
Z0.000 mG
Paramètres appareil
TAG appareil
i
A custom name or tag assigned to this device for easy identification.
Merc7408
Langue
i
The language setting configured on the device.
en
Mode arrêt
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
Luminosité LED
i
The brightness level of the LED indicators on the Mercury. Lower values save battery.
20%
Puissance WiFi TX
i
WiFi transmit power level. Higher gives better range but uses more battery.
5 dBm (default)
Mode veille
i
Controls whether the device enters low-power sleep when idle.
Normal (sleep when idle)
Surveillance batterie
i
Monitors battery voltage during the flight.
DISABLED
Groupe cloud
i
The cloud group / category this flight is assigned to.
1
Ports GP6 / GP7
Configuration des ports GP6 et GP7 pour canaux pyro, servos ou autres appareils.
Mode canal 6
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
Mode canal 7
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
Carte servo I2C PCA9685
Configuration de la carte servo externe I2C PCA9685 avec jusqu’à 6 canaux servo supplémentaires.
Aucune carte servo I2C n’était connectée pour ce vol.
Prédiction et aérofreins
Le Mercury peut prédire l’apogée pendant la phase de vol libre. Ces paramètres contrôlent le calcul et le système d’aérofrein.
Masse sèche
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
Coefficient Cx
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
Surface référence
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)
Les paramètres suivants configurent le système d’aérofrein.
Aérofrein activé
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)
Altitude cible
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)
Files
Where the altimeter signs its log, the file carries that signature and a tick beside it. A tick means the data is unchanged since the device wrote it, which is what a record claim needs.
CSV
1246.csv
The log as columns of text. Opens in a spreadsheet, and in every simulator that reads flight data.
132 KB
Adjusted CSV2904 recalculated in your browser
The log recomputed for your own sea-level pressure and temperature. Columns: time, altitude as recorded and adjusted, raw altitude as recorded and adjusted, pressure.
This file is built here from the signed log, so it carries no signature of its own. Anyone verifying a claim should be sent to the flight page and build their own from the original.
Custom CSVbuilt in your browser
Pick any of the chart’s data sets, the worked-out ones included, and the part of the flight to cover. Values come in the units the chart is set to.
Data sets
Time span
One row for every time any chosen data set has a sample. A data set with no sample at that time is left blank rather than filled in. Built from the chart’s data, so it carries no signature.
Share this flight
Anyone with the link can view this flight; nothing else on your account is shared.
Chart snapshot
A PNG of the chart exactly as you have it set right now: the series you have switched on, your zoom, your labels and any pressure correction applied.
Hotlink images
Stored images of the whole flight, altitude only, not your current chart view. Transparent, regenerated whenever the flight changes, and safe to hotlink on a forum.
Small340 × 255
Large1000 × 750
QR code
Links to this flight page. Useful on a range card or a club display.
Commentaires
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