Lot 1431
Flight 1431
Mercury V1 Rev 1 · firmware 2.3
Apogeum
195.28m
6.16 s after launch
Maks. wznoszenie
159.37m/s
peak ascent
Maks. podczas spalania
13.57G
during the burn
Lądowanie
37.1s
touchdown 5.73 m/s
ZOOM TO
s
s
Podsumowanie lotu
The flight, moment by moment
Liftoff
0 s
Nachylenie rampy13.53°
Thrust calc pad tilt4.4°
Launch detected
0.18 s
Wysokość10.47 m
Prędkość118.44 m/s
Wypalenie (pierwszy)
0.68 s
Wysokość62.36 m
Prędkość3.500 m/s
Možliwy wyrzut
5.984 s
Wysokość194.86 m
Prędkość5.59 m/s
Apogeum
6.16 s
Wysokość195.28 Metry
Maks. nachylenie do wypalenia26.24°
Lądowanie
37.09 s
Wysokość-11.6 m
Maks. opadanie-9.07 m/s
Stabilność51.3%Umiarkowany
Nachylenie przy wypaleniu (20%)88.9
20% · Launch tilt 4.4°
Prędkość pochylania/odchylania (30%)77.1
25% · Coning 54.4/111.1°/s
Coning · boost (25%)44.7
25% · Spin 649.2°/s
Prostoliniowość ciągu (15%)10.4
30% · Thrust 80.3%
Rocket information
Calculated from the flight data alone
Boost acceleration5.1 m/s²
average over the burn · 0.5 g
Coast deceleration0.6 m/s²
average · gravity plus drag
Apogee lost to tilt0.57 m
flown vertical ≈ 195.8 m · from the thrust-calculated tilt
Chute opening peak10.58 G
largest deceleration after ejection
Average descent rate6.63 m/s
ejection to landing · 31.11 s
Bateria & temperatura 0% → 0% · Temperatura początek 18.02 → 18.36 °C · Start po włączeniu 12m 32s
Wysokość
Apogeum195.28 Metry
Czas do apogeum6.16 s
Wysokość wypalenia62.36 m
Wys. maks. prędkości36.81 m
Wys. wyrzutu194.86 m
Wys. lądowania-11.6 m
Wysokość nagrywania-2.37 m
Prędkość
Maks. wznoszenie159.37 m/s
Maks. opadanie-9.07 m/s
Przy wypaleniu3.500 m/s
Prędk. opadania-6.502 m/s
Prędk. wyrzutu5.59 m/s
Prędk. lądowania-5.726 m/s
Przyspieszenie
Maks. podczas spalania13.57 G
Maks. wznoszenie15.54 G
Maks. opadanie10.58 G
Śr. wznoszenie0.83 G
Śr. spalanie11.38 G
Czasy
Wypalenie (pierwszy)0.68 s
Apogeum6.16 s
Možliwy wyrzut5.984 s
Lądowanie37.09 s
Wyjście #1 WŁ0 s
Wyjście #1 WYŁ0 s
Kąty
Nachylenie rampy13.53°
Thrust calc pad tilt4.4°
Maks. nachylenie do wypalenia26.24°
Przechylenie startowe-13.35°
Pochylenie startowe-2.19°
Maks. obrót (spal.)1673.23 dps
Śr. obrót (spal.)415.47 dps
Recovery
Single deploy
No dual deploy detected on this flight.
Ogólne
Data przesłania05-Apr at 17:44
Próbki danych2876
Całkowity czas nagrania50.900 s
Śr. próbki/s56.5
Liczba blokad0
Start po włączeniu12m 32s
Oś referencyjnaX
Bateria & temperatura
Bateria początek0%
Bateria koniec0%
Temperatura początek18.02°C
Temperatura koniec18.36°C
Temp. MT1 startowa0°C
Reguły wyjścia
Brak skonfigurowanych reguł
Notatki užytkownika
Brak notatek
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Film Youtube
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Zdjęcia lotu 0
Brak zdjęć
Flown as
Rocket
None
not linked
Motor configuration
None
no motor recorded
Loaded weight
None
not entered
Silniki lotu
Nie dodano silników do tego lotu
Dodaj to urządzenie do swojego konta, aby edytować
Powiązana rakieta
Žadna rakieta nie jest powiązana z tym lotem
Reguły wyjścia
Reguły pozwalają Mercury wykonywać akcje na podstawie warunków lotu. Každa reguła ma do 4 warunków (A-D).
Brak skonfigurowanych reguł
Dopasowanie silnika (BETA)
Wciąż w trybie testowym! Pracujemy nad ustaleniem, jaki silnik był użyty.
Marka
Silnik
Wynik
Kształt
Spalanie
AeroTech
I599N
162
95.3%
97.7%
AeroTech
J1299N
124
90.9%
96.4%
Cesaroni
H565
111
92.1%
97.7%
Cesaroni
K2045Vmax
95
84.5%
96.2%
AeroTech
H283ST
94
85%
93.7%
AeroTech
J1799N
91
86.9%
92.6%
Cesaroni
H399-WT
89
89.2%
93.7%
AeroTech
F115SN
87
83.7%
88.9%
Cesaroni
F59-WT
85
93.2%
96.6%
AeroTech
J1265ST
80
92.3%
96.7%
Linked flights
No linked flights yet.
Miejsce startu, data i godzina
Imagery © Esri, Maxar, Earthstar Geographics
Kliknij na mapę · Przeciągnij, aby dostosować
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.
No launch site has been set for this flight.
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.
Animacja danych lotu
FLIGHT 1431
195.28 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
Uwaga: Animacja lotu wymaga montażu wysokościomierza w stałej orientacji. Skalibruj czujniki dla najlepszych wyników.
Mercury V1
Ten lot został wykonany na Mercury V1.
The hardware
Wersja sprzętuRev 1
Wersja oprogramowania2.3
Ostatnio online28-Apr at 12:19
Czujnik ciśnieniaBosch BMP 390
Akcelerometr32G 3-axis
Gyroskop2000 dgps 3-axis
MagnetometrN/A
Flights from this altimeter
2 of 2
Settings, as they were for this flight
Ogólne ustawienia lotu
Ciśnienie prognozowane
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
Detekcja startu
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.
10
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.
1:0 (hybrid, reduces after apogee)
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 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.
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 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.
0.5 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.
WŁĄCZONY (14 samples / 150.00ms)
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
Ustawienia wyjścia
Wyjście 1 aktywne
i
Disable or enable the output from being able to turn on or off.
WYŁĄCZONY
Wyjście 1 wyzwalacz
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)
Wyjście 1 czas włączenia
i
This is how long the output should trigger ON state when the rules are met.
2000ms
Wyjście 1 wysokość
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
Wyjście 1 czas
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
Blokada wysokości
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
Blokada kąta nachylenia
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 °
Kalibracja czujników
Przesunięcia kalibracji użyte w tym locie.
Gyroskop
X-7.690°
Y-6.700°
Z-9.790°
Akcelerometr
X15.410 mG
Y-4.810 mG
Z6.570 mG
Ustawienia urządzenia
TAG urządzenia
i
A custom name or tag assigned to this device for easy identification.
Merc3210
Język
i
The language setting configured on the device.
en
Tryb wyłączania
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
Jasność 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)
Tryb uśpienia
i
Controls whether the device enters low-power sleep when idle.
Normal (sleep when idle)
Monitor baterii
i
Monitors battery voltage during the flight.
DISABLED
Cloud group
i
The cloud group / category this flight is assigned to.
1
Porty GP6 / GP7
Konfiguracja portów GP6 i GP7 dla kanałów pirotechnicznych, serw lub innych urządzeń.
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
Płytka servo I2C PCA9685
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.
Prognoza i hamulce powietrzne
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.
0.5000 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)
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
1431.csv
The log as columns of text. Opens in a spreadsheet, and in every simulator that reads flight data.
260 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.
In the file
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.
QR code
Links to this flight page. Useful on a range card or a club display.
Komentarze
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