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Strona główna
Urządzenie: 9C13-9ED2-5B3C
Lot ID: 1837Flight 1837
Podsumowanie lotu
Wysokość
Apogeum
129.22 Metry
Czas do apogeum
5.31 seconds
Wysokość wypalenia
72.12 m
Wys. maks. prędkości
34.78 m
Wys. wyrzutu
127.47 m
Wys. lądowania
-3.48 m
Stabilność
Wskaźnik stabilności
52.6 / 100 (Umiarkowany)
Nachylenie przy wypaleniu (20%)86.3
Prędkość pochylania/odchylania (30%)33.6
Coning · boost (25%)24.3
Prostoliniowość ciągu (15%)69.4
Launch tilt 5.4° · Coning 140.2/176.2°/s · Spin 128.9°/s · Thrust 93.4%
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.
Nachylenie przy wypaleniu (20%) – how close to vertical it left the rod.
Prędkość pochylania/odchylania (30%) and Coning · boost (25%) – how much the nose swung off the rocket's own axis. The main factor.
Prostoliniowość ciągu (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.
Prędkość
Maks. wznoszenie
48.92 m/s
Maks. opadanie
-13.41 m/s
Przy wypaleniu
31.750 m/s
Prędk. lądowania
-5.216 m/s
Prędk. opadania
-4.898 m/s
Prędk. wyrzutu
-6.89 m/s
Recovery
Single deploy (no dual deploy detected)
Przyspieszenie
Maks. wznoszenie
11.87 G
Maks. opadanie
19.28 G
Maks. podczas spalania
11.87 G
Śr. wznoszenie
0.55 G
Śr. spalanie
3.04 G
Czasy
Wypalenie (pierwszy)
1.83 seconds
Apogeum
5.31 seconds
Možliwy wyrzut
5.898 seconds
Lądowanie
32.02 seconds
Wyjście #1 WŁ
0 seconds
Wyjście #1 WYŁ
0 seconds
Kąty
Nachylenie rampy
47.30°
Thrust calc pad tilt
5.4°
Maks. nachylenie do wypalenia
56.40°
Przechylenie startowe
47.16°
Pochylenie startowe
-2.84°
Maks. obrót (spal.)
951.3 dps
Śr. obrót (spal.)
223.59 dps
Ogólne
Flight time (approx)
Data przesłania
21-Jun at 16:45
Próbki danych
6458
Całkowity czas nagrania
50.200 s
Śr. próbki/s
128.6
Liczba blokad
0
Wysokość nagrywania
-47.76 m
Start po włączeniu
2m 29s
Oś referencyjna
X
Bateria & temperatura
Bateria początek
0%
Bateria koniec
0%
Temperatura początek
26.7°C
Temperatura koniec
27.17°C
Temp. MT1 startowa
0°C
⚠ Niski poziom baterii — naładuj przed następnym lotem
Reguły wyjścia
Brak skonfigurowanych reguł
Animacja danych lotu
FLIGHT 1837
129.22 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.
Notatki užytkownika
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Zdjęcia lotu (0)
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Powiązana rakieta
Žadna rakieta nie jest powiązana z tym lotem
Informacje o urządzeniu
Mercury V1
Revision 3
Revision 3
Mercury V1
Ten lot został wykonany na Mercury V1.
Wersja sprzętu
Rev 3
Wersja oprogramowania
2.40
Ostatnio online
24-Jun at 12:54
Akcelerometr
32G 3-axis
Gyroskop
2000 dgps 3-axis
Czujnik ciśnienia
Bosch BMP 581
Magnetometr
N/A
Silniki lotu
1st Stage
1x
Klima
C6-5
Burn time
1.60 seconds
Diameter
18.00 mm
Average thrust
6.00 N
Max thrust
15.00 N
Impulse
10.00 Ns
Impulse class
C
Total weight
20.50 g
Propellant weight
9.60 g
Propellant type
composite
Links
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Spalanie silnika
The dashed line is the combined thrust curve for your motors (data from thrustcurve.org), scaled so its peak matches the recorded acceleration maximum — the shape is meaningful, the absolute level is not (your rocket's weight is unknown).
Miejsce startu, data i godzina
Kliknij na mapę, aby oznaczyć miejsce startu. Przełączaj między widokiem mapy i satelity.
No results found — try a different search.
Kliknij na mapę · Przeciągnij, aby dostosować
Lat—
Lng—
✓ Launch location saved successfully.
✗ Could not save location — please try again.
Rule events
No output rules fired during this flight.
Dopasowanie silnika (BETA)
Wciąż w trybie testowym! Pracujemy nad ustaleniem, jaki silnik był użyty.
Marka
Silnik
Wynik
Kształt
Spalanie
Klima
B4
94
85%
91.5%
Quest
B6W
63
87.4%
86.6%
Quest
B4~2
48
75%
85%
Loki
G94IB
40
63%
85.8%
TSP
D20
38
76.2%
87.9%
Contrail
J800
35
28.9%
70.2%
Estes
F50
30
56.3%
85.5%
AeroTech
F52C
30
52.7%
87.5%
Cesaroni
G106-SK
30
29.7%
83.9%
AeroTech
G54
30
69.7%
88.4%
Porównanie lotów
Comparing against 14 other flights with the same motor configuration.
Highest apogee129.22 m 11th of 12
The maximum altitude reached above the launch point.
you
best
best 199.39 m · Flight #1246
Best stability52.6 /100 11th of 12
How straight it flew: launch, coning and thrust straightness combined. 100 is perfect.
you
best
best 93.5 /100 · Flight #1360
Fastest velocity48.92 m/s 6th of 12
Peak ascent velocity recorded during the flight.
you
best
best 61.1 m/s · Flight #1146
Best avg burn G3.04 G 6th of 12
Average acceleration during the motor burn, in G.
you
best
best 3.56 G · Flight #1246
Longest flight50.2 s 2nd of 12
Total recording time from launch to landing.
you
best
best 52.3 s · Flight #1333
Lowest spin223.59 dps 10th of 12
Average spin rate during the burn.
you
best
best 53.82 dps · Flight #1333
🌲 Is it in a tree?-47.76 m 4th of 12
Just for fun: whichever flight came down closest to 8 m above the launch point (roughly tree height) is the one most likely stuck up a tree.
8 m
you
best
closest to 8 m · 200Hz Nano test (2) (#1734) at 2.38 m
Ogólne ustawienia lotu
To jest migawka ustawień użytych dla tego lotu. Przejdź na
Przejdź na stronę Moje urządzenia i skonfiguruj ustawienia..
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.
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.
1:5 (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.
18000
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.
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
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 (88 samples / 351.00ms)
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
To jest migawka ustawień użytych dla tego lotu.
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
—
Kalibracja czujników
Przesunięcia kalibracji użyte w tym locie.
Gyroskop
⚠ Gyroskop nie został skalibrowany
X
0.000°
Y
0.000°
Z
0.000°
Akcelerometr
⚠ Akcelerometr nie został skalibrowany
X
0.000 mG
Y
0.000 mG
Z
0.000 mG
Ustawienia urządzenia
To jest migawka ustawień użytych dla tego lotu.
To jest migawka ustawień użytych dla tego lotu.
TAG urządzenia
i
A custom name or tag assigned to this device for easy identification.
Merc8360
Język
i
The language setting configured on the device.
🇬🇧 English
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.
2 dBm (low)
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.
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
To jest migawka ustawień użytych dla tego lotu.
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
To jest migawka ustawień użytych dla tego lotu.
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.
$tc_not_configured
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.
$tc_not_configured
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.
$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
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.
$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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