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Startseite
Gerät: 9C13-9ED5-7708
Flug-ID: 1848Flight 1848
⚠️
Testflug erkannt
Dies scheint ein Test- oder Nicht-Raketenflug zu sein (z.B. Handwurf, Vakuum-/Drucktest). Die Daten stellen möglicherweise keinen echten Raketenflug dar.
●High altitude with minimal acceleration (vacuum/pressure test)
●No motor burnout detected
Flugzusammenfassung
Höhe
Apogäum
151.11 Meter
Zeit bis Apogäum
4.24 seconds
Brennschluss-Höhe
71.87 m
Max. Geschw.-Höhe
67.09 m
Auswurf-Höhe
71.87 m
Lande-Höhe
71.87 m
Stabilität
Stabilitätswert
0.1 / 100 (Schlecht)
Neigung bei Brennschluss (20%)0
Nick/Gier-Rate (30%)0
Coning · boost (25%)0
Schubgeradheit (15%)0
Launch tilt 0° · Coning 0/0°/s · Spin 0°/s · Thrust 0%
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.
Neigung bei Brennschluss (20%) – how close to vertical it left the rod.
Nick/Gier-Rate (30%) and Coning · boost (25%) – how much the nose swung off the rocket's own axis. The main factor.
Schubgeradheit (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.
Geschwindigkeit
Max. Aufstieg
34.53 m/s
Max. Abstieg
-7.65 m/s
Bei Brennschluss
0.000 m/s
Landegeschw.
-0.023 m/s
Abstiegsgeschw.
-4.213 m/s
Auswurfgeschw.
34.01 m/s
Recovery
Single deploy (no dual deploy detected)
Beschleunigung
Max. Aufstieg
0.39 G
Max. Abstieg
7.27 G
Max. während Brennen
0 G
Durchschn. Aufstieg
-0.03 G
Durchschn. Brennen
N/A
Zeiten
Brennschluss (erster)
0 seconds
Apogäum
4.24 seconds
Möglicher Auswurf
0 seconds
Landung
0 seconds
Ausgang #1 EIN
0 seconds
Ausgang #1 AUS
0 seconds
Winkel
Rampen-Neigung
0.00°
Thrust calc pad tilt
0°
Max. Neigung bis Brennschluss
47.65°
Start-Roll
0.00°
Start-Nick
0.00°
Max. Drehung (Brennen)
0 dps
Durchschn. Drehung (Brennen)
0 dps
Allgemein
Flight time (approx)
Upload-Datum
25-Jun at 10:46
Datenpunkte
11551
Gesamte Aufnahmezeit
53.700 s
Durchschn. Abtastrate/s
215.1
Anzahl Sperren
2
Aufnahme-Höhe
71.43 m
Start nach Einschalten
22m 44s
Referenzachse
0
Batterie & Temperatur
Batterie Start
84%
Batterie Ende
82%
Temperatur Start
34.23°C
Temperatur Ende
34.93°C
MT1 Starttemp.
0°C
Ausgangsregeln
Keine Regeln konfiguriert
Flugdaten-Animation
FLIGHT 1848
151.11 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
Hinweis: Die Fluganimation erfordert eine feste Ausrichtung Ihres Höhenmessers. Kalibrieren Sie Ihre Sensoren für beste Ergebnisse.
Benutzernotizen
Fügen Sie dieses Gerät Ihrem Konto hinzu, um zu bearbeiten
Youtube-Video
Kein Video
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Flugbilder (0)
Keine Bilder
Verknüpfte Rakete
Keine Rakete mit diesem Flug verknüpft
Geräteinformationen
Mercury V1
Revision 3
Revision 3
Mercury V1
Dieser Flug wurde mit einem geflogen: Mercury V1.
Hardwareversion
Rev 3
Softwareversion
2.40
Zuletzt online
25-Jun at 10:48
Beschleunigungssensor
32G 3-axis
Gyroskop
2000 dgps 3-axis
Drucksensor
Bosch BMP 581
Magnetometer
N/A
Flugmotoren
Keine Motoren zu diesem Flug hinzugefügt
Fügen Sie dieses Gerät Ihrem Konto hinzu, um zu bearbeiten
Motorbrenndauer
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.
Startplatz, Datum & Uhrzeit
Klicken Sie auf die Karte, um Ihren Startplatz zu markieren. Wechseln Sie zwischen Karten- und Satellitenansicht.
No results found — try a different search.
Klicken Sie auf die Karte · Ziehen zum Anpassen
Lat—
Lng—
✓ Launch location saved successfully.
✗ Could not save location — please try again.
Rule events
No output rules fired during this flight.
Motor-Zuordnung (BETA)
Noch im Testmodus! Wir arbeiten daran, den passenden Motor für einen Flug zu ermitteln.
Marke
Motor
Punkte
Form
Brennen
Contrail
G300
39
23.4%
53.3%
Estes
1/4A3T
14
28%
68.8%
Allgemeine Flugeinstellungen
Dies ist ein Schnappschuss der für diesen Flug verwendeten Einstellungen. Gehen Sie zur
Gehen Sie zur Meine Geräte Seite und konfigurieren Sie die Einstellungen..
Prognosedruck
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
Starterkennung
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
Abtastverhältnis
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. Abtastungen
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
Aufnahme-Stopp
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)
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
Druckfilter
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)
Sperränderung
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
Sensorsynchronisation
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.
AKTIVIERT
Ausrichtung
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
Start-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
Startsperre
i
When enabled, the altimeter locks out recording for a set period after power on to prevent false triggering during setup.
DISABLED
Statische Temperatur
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
Ausgangseinstellungen
Dies ist ein Schnappschuss der für diesen Flug verwendeten Einstellungen.
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
—
Sensorkalibrierung
Kalibrierungsversätze für diesen Flug.
Gyroskop
X
-0.490°
Y
0.100°
Z
1.080°
Beschleunigungssensor
X
-2.290 mG
Y
8.160 mG
Z
3.600 mG
Geräteeinstellungen
Dies ist ein Schnappschuss der für diesen Flug verwendeten Einstellungen.
Dies ist ein Schnappschuss der für diesen Flug verwendeten Einstellungen.
Geräte-TAG
i
A custom name or tag assigned to this device for easy identification.
LITTLERED
Sprache
i
The language setting configured on the device.
🇬🇧 English
Abschaltmodus
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
LED-Helligkeit
i
The brightness level of the LED indicators on the Mercury. Lower values save battery.
20%
WLAN-Sendeleistung
i
WiFi transmit power level. Higher gives better range but uses more battery.
2 dBm (low)
Schlafmodus
i
Controls whether the device enters low-power sleep when idle.
Normal (sleep when idle)
Batterieüberwachung
i
Monitors battery voltage during the flight.
DISABLED
Cloud-Gruppe
i
The cloud group / category this flight is assigned to.
GP6 / GP7 Anschlüsse
Konfiguration der GP6- und GP7-Ausgänge. Diese können Pyrokanäle, Servos oder andere Geräte ansteuern.
Kanal 6 Modus
ON = HIGH
Ch6 min pulse (µs)
0
Ch6 max pulse (µs)
0
Ch6 frequency
0 Hz
Ch6 angle ON
0.00°
Ch6 angle OFF
0.00°
Ch6 on time
0.00s
Kanal 7 Modus
ON = HIGH
Ch7 min pulse (µs)
0
Ch7 max pulse (µs)
0
Ch7 frequency
0 Hz
Ch7 angle ON
0.00°
Ch7 angle OFF
0.00°
Ch7 on time
0.00s
I2C PCA9685 Servoplatine
Dies ist ein Schnappschuss der für diesen Flug verwendeten Einstellungen.
Konfiguration der externen I2C PCA9685 Servo-Erweiterungsplatine mit bis zu 6 zusätzlichen Servokanälen.
Für diesen Flug war keine I2C-Servoplatine angeschlossen.
Vorhersage und Luftbremsen
Dies ist ein Schnappschuss der für diesen Flug verwendeten Einstellungen.
Der Mercury kann das Apogäum während der Freiflugphase vorhersagen. Diese Einstellungen steuern die Berechnung und das Luftbremsensystem.
Trockenmasse
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
Widerstandsbeiwert
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
Bezugsfläche
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
Die folgenden Einstellungen konfigurieren das Luftbremsensystem.
Luftbremse aktiviert
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)
Zielhöhe
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)
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