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Appareil: 9C13-9ED5-E690
Vol ID: 2836Andromeda flight 6
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Résumé du vol
Altitude
Apogée
77.37 Mètres
Temps jusqu’apogée
3.94 seconds
Altitude fin combustion
60.23 m
Altitude vitesse max.
27.14 m
Altitude éjection
69.03 m
Altitude atterrissage
-0.94 m
Stabilité
Score de stabilité
89.3 / 100 (Excellent)
Inclinaison à la fin de combustion (20%)92.7
Tangage/lacet (30%)93.8
Coning · boost (25%)93.3
Rectitude de poussée (15%)79.9
Launch tilt 2.8° · Coning 25.6/26.7°/s · Spin 36.9°/s · Thrust 95.7%
About this score
Worked out from the flight log between liftoff and 80% of apogee, independent of the angle the altimeter was mounted at in the airframe.
Inclinaison à la fin de combustion (20%) – how close to vertical it left the rod.
Tangage/lacet (30%) and Coning · boost (25%) – how much the nose swung off the rocket's own axis. The main factor.
Rectitude de poussée (15%) – how cleanly the motor pushed along the body.
Spin about the rocket's own axis is not counted against it — a fast, straight spin is stable. The line under the bars shows the raw measurements.
Vitesse
Max. montée
153.16 m/s
Max. descente
-4.41 m/s
À fin combustion
11.040 m/s
Vitesse atterrissage
-2.879 m/s
Vitesse descente
-2.553 m/s
Vitesse éjection
-0.55 m/s
Recovery
Single deploy (no dual deploy detected)
Accélération
Max. montée
22.11 G
Max. descente
19.89 G
Max. pendant combustion
22.11 G
Moy. montée
1.07 G
Moy. combustion
3.59 G
Temps
Fin combustion (premier)
1.37 seconds
Apogée
3.94 seconds
Éjection possible
2.801 seconds
Atterrissage
34.93 seconds
Sortie #1 ON
0 seconds
Sortie #1 OFF
0 seconds
Angles
Inclinaison rampe
92.56°
Thrust calc pad tilt
2.8°
Incl. max. jusqu’à fin comb.
110.50°
Roulis au lancement
-92.56°
Tangage au lancement
-2.17°
Rotation max. (comb.)
2602.51 dps
Rotation moy. (comb.)
58.5 dps
Général
Date envoi
24-Aug at 07:56
Échantillons
6914
Durée totale enregistrement
56.600 s
Moy. échantillons/s
122.1
Nombre de verrouillages
1
Altitude enregistrement
-24.19 m
Lancement après démarrage
5m 56s
Axe de référence
Y
Batterie & température
Batterie début
43%
Batterie fin
35%
Température début
36.14°C
Température fin
33.63°C
Temp. MT1 lancement
0°C
Règles de sortie
Aucune règle configurée
Animation des données
FLIGHT 2836
77.37 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.
Notes utilisateur
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Vidéo Youtube
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Images du vol (0)
Aucune image
Fusée associée
Informations appareil
Mercury V1
Revision 3
Revision 3
Mercury V1
Ce vol a été effectué sur un Mercury V1.
Version matériel
Rev 3
Version logiciel
2.40
Dernière connexion
24-Aug at 16:07
Accéléromètre
32G 3-axis
Gyroscope
2000 dgps 3-axis
Capteur pression
Bosch BMP 581
Magnétomètre
N/A
Moteurs du vol
Aucun moteur ajouté à ce vol
Ajoutez cet appareil à votre compte pour modifier
Combustion moteur
To overlay a thrustcurve here, add your motors to this flight using the “Flight motors” box above. The combined thrust curve is then scaled to match the recorded acceleration peak.
Site de lancement, date & heure
Cliquez sur la carte pour marquer votre site de lancement. Basculez entre vue carte et satellite.
No results found — try a different search.
Cliquez sur la carte · Glissez pour ajuster
Lat—
Lng—
✓ Launch location saved successfully.
✗ Could not save location — please try again.
Rule events
No output rules fired during this flight.
Correspondance moteur (BETA)
Encore en phase de test ! Nous cherchons à deviner quel moteur a été utilisé.
Marque
Moteur
Score
Forme
Comb.
Cesaroni
H410-VM
108
92.6%
96.3%
Quest
B14T
100
93.9%
95.7%
AeroTech
I1299N
80
87.4%
96.3%
Quest
A6Q
79
85.4%
94.7%
Cesaroni
68-F240-VM-15A
66
88.9%
92.6%
AeroTech
H999
54
83.1%
92.9%
Cesaroni
25-E75-VM-17A
50
77%
95.2%
AeroTech
H669N
49
71.8%
93.7%
Estes
1/2A6
48
88.9%
76.9%
AeroTech
G339N
31
66.8%
92.8%
Paramètres généraux
Ceci est un aperçu des paramètres utilisés pour ce vol. Rendez-vous sur la
Rendez-vous sur la page Mes appareils puis Configurer les paramètres..
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.
35
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.
1:5 (hybrid, reduces after apogee)
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.
18000
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.
16x 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)
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.
0.5 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 (24 samples / 132.00ms)
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
Ceci est un aperçu des paramètres utilisés pour ce vol.
Arm switch
i
When enabled, GP6 is a hardware arm switch — outputs and rules are held off until the switch is closed to ground.
DISABLED
Startup lockout
i
Outputs and rules are blocked for this many seconds after power-on while sensors settle. 0 = off.
None
Launch confirm delay
i
After launch is detected, outputs and rules won't fire until this many seconds have passed.
—
Altitude floor
i
Outputs and rules are blocked until the rocket is at least this height above the launch pad.
—
Custom dataset 1
i
User-defined expression evaluated per sample, available for charting.
—
Custom dataset 2
—
Étalonnage capteurs
Décalages de calibration utilisés pour ce vol.
Gyroscope
⚠ Le gyroscope n’a pas été calibré
X
0.000°
Y
0.000°
Z
0.000°
Accéléromètre
⚠ L’accéléromètre n’a pas été calibré
X
0.000 mG
Y
0.000 mG
Z
0.000 mG
Paramètres appareil
Ceci est un aperçu des paramètres utilisés pour ce vol.
Ceci est un aperçu des paramètres utilisés pour ce vol.
TAG appareil
i
A custom name or tag assigned to this device for easy identification.
Merc3792
Langue
i
The language setting configured on the device.
🇬🇧 English
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.
2 dBm (low)
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.
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
Ceci est un aperçu des paramètres utilisés pour ce vol.
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
Ceci est un aperçu des paramètres utilisés pour ce vol.
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.
$tc_not_configured
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.
$tc_not_configured
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.
$tc_not_configured
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.
$tc_not_configured
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.
$tc_not_configured
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.
$tc_not_configured
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)
Commentaires2
If you turn on the Truefuse 2C Velocity chart from the overlays this will show you the real velocity.
It is being added to the next firmware now we've tested it.