DE102022105101B3 - SENSOR PLATFORM AND RELATED SENSOR PLATFORM RELEASE MECHANISM AND RELATED SENSOR PLATFORM RELEASE PROCEDURE - Google Patents

Abstract

The invention relates to a sensor platform (1) and associated sensor platform release mechanism (2) comprising at least one sensor platform (1) and a sensor platform release mechanism (2), the sensor platform (1) having at least one sensor system (4), radio-supported data transmission and a Isolation of the sensor system (5) includes, wherein the sensor system (4) is modular and has devices for recording location data, the radio-supported data transmission stores measurement data and transmits it by radio technology and the isolation of the sensor system (5) has one or more covers, the sensor platform - Dropping mechanism (2) is designed to be modularly mountable on an aircraft (3) and is arranged on the aircraft (3) according to use, and has devices for detachably receiving at least one sensor platform (1). The invention also relates to a sensor platform dropping method with a sensor platform (1) and associated sensor platform release mechanism (2).

Description

The invention relates to a sensor platform and an associated sensor platform release mechanism and an associated sensor platform release method.

The invention describes a sensor platform protected against environmental influences for transport by aircraft, the release mechanism required for placement on the ground, and the release method.

Technically, the invention can be classified in the field of robotics, autonomous aircraft, autonomous sensors, radio-based data transmission, ballistics and materials technology. An example application is the field of in-situ measurement of physical parameters of high-energy turbulent mass flows, which is achieved by the precise dropping of sensors with suitable protection against environmental influences from a safe distance by drones.

Unmanned flight systems, in particular drones, are known from the prior art, both for mapping with permanently installed sensor systems and for transporting payloads, which can be (semi-)automatically or manually separated or picked up from the aircraft. Also known are autonomous sensor systems including data storage, as well as radio or cable-based data transmission (e.g. Vaisala weather balloon probes). These are not only light, but also have limited insulation against environmental influences. Various mechanisms for the precise dropping of explosive devices are known from military technology, even if they are only partially accessible to the civilian sector. Various materials for mechanical and thermal insulation are known from the field of space travel. Also known are stationary sensor systems for the manual installation and measurement of environmental parameters in the field.

The pamphlet DE102015013547 A1 discloses a new method for exploring and inspecting subsurfaces by combining the applications of drones, control and analysis software as well as sensors and high-frequency electromagnetic waves (Ground Penetrating Radar (GPR)).

In the pamphlet DE102009017676 B3 a high-temperature sensor with a conductor track structure on a substrate for temperatures between 800° C. and 900° C. is disclosed.

The pamphlet EP 2 019 810 B1 shows a chip housing for accommodating a chip structure, in particular a micromechanical sensor, which is characterized by reduced coupling of vibrations into the chip structure.

From the pamphlet U.S. 2018/0 203 158 A1 is a portable weather station with a lower housing part; an upper housing disposed on the lower housing in spaced relationship thereby forming an open channel between the upper housing and the lower housing; and a plurality of weather condition sensors, wherein a first set of one or more of the plurality of weather condition sensors is mounted on the upper housing portion of the portable weather station and a second set of one or more of the plurality of weather condition sensors is mounted on the lower housing portion of the portable weather station.

In addition, the document discloses U.S. 2017/0 205 536 A1 a platform configured to capture images and/or radio signals and carried by light aircraft, characterized in that it comprises a housing means accommodating one or more detection sensors selected from the group comprising or consisting of cameras configured to capture still and/or moving images and radio signal receivers configured to capture radio signals, the housing means being configured to be coupled to a light aircraft, the one or more detection s sensors are connected to a processing means configured to receive detection data from a position and motion detection unit coupled to the one or more detection sensors, the processing means being configured to control and/or program each detection sensor based on the received detection data so that it can capture images and/or radio signals when such a detection sensor is in a specific position and is subjected to vibrations at a speed no greater in absolute value than a maximum vibration velocity value, whereby a rate of variation of an actual alignment of such a detection sensor is not greater in absolute value than a respective maximum value of the rate of variation of the offset with respect to an ideal alignment to a target to ensure focusing of such a detection sensor to a target area.

The pamphlet U.S. 6,082,675 A describes a range delivery system responsive to GPS coordinate signals and GPS in-flight signals to locate a sonobuoy at a remote location to deliver and place that would otherwise be dangerous to full-size aircraft deploying the sonar buoy in the conventional manner. A flying platform, e.g. B. a drone or a guided paraglider, carries the sonobuoy to a distant location. A GPS receiver on the platform inputs GPS coordinate signals representative of the remote location and receives GPS signals representative of the location of the platform. A control signal generator generates control signals in response to the two GPS signals and forwards the control signals to servos that move the control surfaces to control the platform. The sonobuoy is triggered by the platform in response to GPS signals indicating at least the proximity of the remote location. This system enables the secret deployment and activation of the sonobuoy.

From the pamphlet U.S. 6,056,237 A an unmanned aerial vehicle compatible with Sonotubes, hereinafter referred to as a UAV, and systems for launching and controlling the UAV. The UAV generally consists of modular sections including a nose section, a payload section, a wing and fuel tank section, and an engine section. The modular sections are attached to adjacent sections by unitary gaskets and associated components. The present invention comprises an apparatus that makes it possible to deploy very small, portable, ballistic-launched, autonomously or semi-autonomously guided vehicles with pre-programmed, communicated or telemetric mission programming. A wide range of payload packages, including backup supplies, sensors and antenna assemblies, can be carried, used or deployed in flight. Portable operation is made possible through the use of a launch canister. The launch canister includes retractable launch stabilization legs, turbine engine exhaust ports, and various antennas. The launch container can also be a modified type “A”, “B” or “C” sonotube. The system according to the invention also comprises a portable console for the command, control, communication, computer and intelligence (C41) and for the analysis of the sensors. The console is preferably rugged, waterproof, and shockproof, and includes the necessary control and analysis computers, input/output devices, antennas, and associated hardware and software for vehicle and mission control. The C4I console and/or launch canisters may be transported in a backpack suitable for human transport.

Furthermore, in the pamphlet U.S. 2003/0 192 992 A1 describes a radial sonobuoy launch system with a clam shell launch tube and a method for launching a sonobuoy. The clamshell launcher tube emits a sonobuoy radially and the clamshell launcher tube is reloaded in flight. The sonobuoys are ejected pneumatically approximately parallel to the air flow. A pressure control structure with a door and gate maintains cabin pressure during reload and launch. Support arms and drive arms evenly distribute the launch mechanism's ejection accelerations and direct the trajectory of the sonobuoy during launch. A shell-shaped launch tube is capable of launching a variety of sonobuoys of different sizes.

The pamphlet U.S. 2014/0 048 654 A1 discloses a deployment system for aircraft devices comprising a spring-driven linkage for deploying one or more kicker feet to push a device to be deployed away from the deployment system. The kicker feet may include front and rear kicker feet that push the deployed device to obtain a desired pitch at launch, such as minimal or substantially zero pitch. The release of the kicker feet can be controlled by a pair of actuators, such as. B. electric magnet actuators, both of which must be actuated to trigger the device.

An electrical connection may allow for position compensation to account for tolerances in positioning the device relative to the initiation system.

In addition, the document discloses U.S. 2018/0 251 221 A1 a system and method for releasing an object comprising a passageway connected to the object, the passageway having a first end and a second end, at least one hinged door connected to the second end of the passageway, and at least one pusher to close the at least one hinged door and selectively open the at least one hinged door when the object contacts the at least one hinged door.

The problems in the prior art are essentially that known thermal and mechanical insulation materials from space travel tend to be too expensive for mass production and at the same time too heavy for drone transport. However, isolation of the sensors is necessary for use in many natural phenomena, such as the heat development in volcanic phenomena.

Furthermore, for a targeted drop in the civilian area, mostly copter threats have been used so far used with short range. However, for a safe approach to high-energy, large-scale natural phenomena, long-range drones are necessary.

Sensors for measurements in moving mass flows also require absolute or relative localization.

When measuring in the field with stationary sensor systems, there is a lack of safety for personnel and equipment. In addition, stationary sensor systems are not sufficiently flexible with regard to the locality of a spontaneously occurring natural phenomenon.

Data storage is particularly risky in terms of salvage during high-energy natural phenomena. Data transmission via radio is often complicated by environmental parameters such as the density of the medium and the required range.

So far, there has been no suitable combination of protected sensor system, release mechanism and carrier vehicle.

The object of the present invention is to eliminate the known deficiencies of the prior art and to provide a suitable combination of protected sensor system, release mechanism and aircraft. A further object is to provide a simple and safe release method for this.

It is the object of the present invention to provide a thermally, mechanically and chemically insulated sensor system and a release mechanism for attachment to an aircraft, which makes it possible to transport the sensor system to a measurement location by an aircraft, to release the sensor system from the air to a measurement location using the release mechanism on the aircraft and to transmit the data obtained by radio.

This object is achieved with a sensor platform and associated sensor platform ejection mechanism according to the main claim and an associated sensor platform ejection method according to the independent claim.

• - die Sensorplattform mindestens ein Sensorsystem, eine funkgestützte Datenübertragung und eine thermische und mechanische und chemische Isolation des

Sensorsystems umfasst,
wobei

• - das Sensorsystem modular aufgebaut ist und Vorrichtungen zur Aufzeichnung von Ortungsdaten aufweist,
• - die funkgestützte Datenübertragung Messdaten speichert und per Funktechnik überträgt und
• - die Isolation des Sensorsystems eine oder mehrere Hüllen aufweist;
• - der Sensorplattform-Abwurfmechanismus
  • - modular an einem Fluggerät montierbar ausgebildet ist und am Fluggerät verwendungsgemäß angeordnet ist, wobei das Fluggerät (3) zum Transport und zur Positionierung der in dem Sensorplattform-Abwehrmechanismus (2) angebrachten mindestens einen Sensorplattform (1) an einen zuvor festgelegten Ort ausgebildet ist; ; und
  • - über Vorrichtungen zur lösbaren Aufnahme von mindestens einer Sensorplattform verfügt, wobei durch Auslösung der Vorrichtungen zur lösbaren Aufnahme ein zielgenaues Abwerfen der mindestens einen Sensorplattform (1) aus der Luft gelingt. Als Schutz vor thermischen, mechanischen und chemischen Umwelteinflüssen wie Druck, Beschleunigung, Hitze, Korrosion wird das Sensorsystem mit einer oder auch mehreren Hüllen isoliert.

A sensor platform and an associated sensor platform ejection mechanism comprise at least one sensor platform and one sensor platform ejection mechanism, which is/are characterized in that

• - the sensor platform has at least one sensor system, radio-based data transmission and thermal, mechanical and chemical insulation of the

sensor system includes,
whereby

• - the sensor system is modular and has devices for recording location data,
• - the radio-supported data transmission stores measurement data and transmits them by radio technology and
• - the insulation of the sensor system has one or more covers;
• - the sensor platform ejection mechanism
  • - is designed to be modularly mountable on an aircraft and is arranged on the aircraft according to use, the aircraft (3) being designed to transport and position the at least one sensor platform (1) attached to the sensor platform defense mechanism (2) at a previously specified location; ; and
  • - Has devices for the detachable mounting of at least one sensor platform, wherein by triggering the devices for the detachable mounting a targeted dropping of the at least one sensor platform (1) from the air is possible. To protect against thermal, mechanical and chemical environmental influences such as pressure, acceleration, heat and corrosion, the sensor system is insulated with one or more covers.

Preferably, a sleeve for insulating the sensor system can be made of polyetheretherketone (PEEK) in the sensor platform. Polyetheretherketone is temperature resistant up to 300 °C. In addition, PEEK is very tough, which results in a very high impact resistance, which is required if the sensor platform hits rocks, for example.

When using multiple shells, it becomes possible to stagger the properties of multiple materials.

In a particularly preferred embodiment, a sleeve for insulating the sensor system in the sensor platform can be made of polyetheretherketone (PEEK) and additionally surrounded by a further sleeve made of a cork layer.

The additional cork layer serves as a shock absorber and for temperature insulation. In addition to the low thermal conductivity of cork, another protective effect is provided by ablation. The cork granules will move from the outside in ignite and burn up. When these glowing pieces of cork detach from the shell, heat is dissipated, which has been proven in space travel for decades. The protective cork shells are made of granules with polyurethane glue and/or silicone.

The sensor system can have various sensors for recording selected parameters. Possible selected parameters are, for example, temperature, pressure, humidity, flow rate, acceleration, viscosity, density, pH value, electrochemical potential, ionic strength, sound value sizes, approximation, light.

In particular, the device for recording location data can be designed as an accelerometer. Using the data from an accelerometer, it is possible to calculate the location relative to the drop location.

In addition, radio-assisted data transmission can store measurement data and transmit them redundantly via radio technology. For this purpose, the frequency is adapted to the surrounding medium and the necessary range. Redundancy can be achieved, for example, by transmitting sliding windows over the series of measurements.

Furthermore, a changed surface structure and/or shape of the one or more shells of the insulation of the sensor system can be formed by partial damage, deformation or melting. This changed surface structure and/or shape of the sensor system can in turn produce a protective effect for the sensor system in the sensor platform. For example, the melting of a layer of plastic when thrown into a volcanic cloud can lead to the accumulation of a layer of stone, which in turn provides renewed protection.

A mechanical safeguard for the at least one sensor platform can also be present in the sensor platform release mechanism in order to prevent unintentional release in the event of a power failure, for example.

In a preferred embodiment, the sensor platform release mechanism can have an aerodynamic shape in order to be able to be optimally transported, particularly in the case of long-distance drones.

A camera can also preferably be integrated into the sensor platform ejection mechanism, the integrated camera being designed as a means for positioning the sensor platform ejection mechanism and the at least one sensor platform being ejected precisely by triggering the devices for releasable reception.

The camera integrated in the sensor platform release mechanism can also be attached via a gimbal mount in order to achieve the best possible image stabilization.

• - Herstellung den Einsatzanforderungen entsprechender spezifischer Sensorplattform(en);
• - Anbringen von mindestens einer Sensorplattform an den hierfür vorgesehenen Vorrichtungen eines Sensorplattform-Abwurfmechanismus;
• - Montage des Sensorplattform-Abwurfmechanismus an einem Fluggerät;
• - autonome oder manuelle Positionierung des Fluggeräts an einem zuvor festgelegten Ort;
• - autonomer oder manueller zielgenauer Abwurf der mindestens einen Sensorplattform an dem zuvor festgelegten Ort;
• - Messung, Speicherung und Übertragung der Daten per Funk an den Anwender über die Sensorplattform.

The sensor platform dropping method with a sensor platform and associated sensor platform dropping mechanism has the following steps:

• - Production of specific sensor platform(s) corresponding to the application requirements;
• - Attaching at least one sensor platform to the devices provided for this purpose of a sensor platform release mechanism;
• - Mounting the sensor platform release mechanism on an aircraft;
• - Autonomous or manual positioning of the aircraft at a predetermined location;
• - Autonomous or manual precise dropping of the at least one sensor platform at the predetermined location;
• - Measurement, storage and transmission of the data wirelessly to the user via the sensor platform.

• - Einsatz des Fluggerätes als Zwischenverstärker für das Funksignal und / oder
• - Bergung der mindestens einen Sensorplattform.

The sensor platform dropping method with a sensor platform and associated sensor platform dropping mechanism can also include the following steps:

• - Use of the aircraft as a repeater for the radio signal and / or
• - Recovery of the at least one sensor platform.

The sensor platform dropping method according to the invention ensures a high level of safety for the user. In particular, the possibility of using long-range drones as aircraft, for example, creates a large distance to the phenomenon to be examined.

The combination of thermal/mechanical/chemical insulation of a sensor, its targeted release from the air to the measuring location (far away from the user) and transmission of the data obtained by radio is to be seen as new and inventive in the sense of the invention.

• So sind die Herstellungskosten für erfindungsgemäße Sensorplattformen niedrig, was wiederum die Produktion von hohen Stückzahlen ermöglicht, wodurch wiederum das gleichzeitige Einbringen mehrerer Sensorplattformen eine hohe Anzahl und Redundanz an Messungen erlaubt. Da davon ausgegangen werden kann, dass die Sensorplattformen nur teilweise bergbar sein werden, sind niedrige Herstellungskosten ebenfalls von deutlichem Vorteil. Die Kosten wirken sich ebenfalls auf die wissenschaftliche Anwendbarkeit positiv aus.

In particular, various advantages result from the invention:

• Thus, the production costs for sensor platforms according to the invention are low, which in turn enables the production of large quantities, which in turn allows a large number and redundancy of measurements to be introduced at the same time. Since it can be assumed that the sensor platforms will only be partially recoverable, low production costs are also a clear advantage. The costs also have a positive effect on the scientific applicability.

The at least one sensor platform and the associated sensor platform removal mechanism also have such a low weight that commercial aircraft can be used for transport and the simultaneous carrying of several sensor platforms both in flight and in the field to the departure point is not a problem.

The novel sensor platform dropping method enables measurements in previously inaccessible environments, for example due to the lack of security of the user and / or the sensor or the accessibility of the measurement location.

Since this is a temporally and spatially flexible method, it can be adapted to natural phenomena that occur spontaneously, are locally limited and are difficult to predict.

In particular, it is a modular system that can be transported by different aircraft and is easily adaptable.

The invention is described below with reference to the accompanying illustrations in the description of the illustrations, which are intended to explain the invention and are not necessarily to be viewed as restrictive.

• eine beispielhafte Darstellung einer Ausführungsvariante eines erfindungsgemäßen Sensorplattform-Abwurfmechanismus für zwei Sensorplattformen in der Seitenansicht;
• eine beispielhafte Darstellung einer Ausführungsvariante einer erfindungsgemäßen Sensorplattform und
• eine beispielhafte Darstellung einer Ausführungsvariante eines erfindungsgemäßen Sensorplattform-Abwurfmechanismus befestigt an einer Long-Range-Drohne (Wingcopter).

Show it:

• an exemplary representation of an embodiment variant of a sensor platform release mechanism according to the invention for two sensor platforms in the side view;
• an exemplary representation of an embodiment variant of a sensor platform according to the invention and
• an exemplary representation of an embodiment variant of a sensor platform release mechanism according to the invention attached to a long-range drone (wingcopter).

In an exemplary representation of an embodiment variant of a sensor platform release mechanism 2 according to the invention for two sensor platforms 1 is shown in a side view. A sensor platform release mechanism 2 and a connected and a non-connected sensor platform 1 are shown. The camera integrated in the front area is not visible in the figure and transmits a video signal to the user via radio for precise release. shows the representation as a line drawing. In the same representation is presented as a halftone image for better illustration.

The and show photos of an exemplary embodiment variant of the subject invention.

shows an exemplary representation of an embodiment variant of a sensor platform 1 according to the invention with a sensor system 4 and an inner and outer shell 5a, 5b as insulation of the sensor system 4. The sensor system 4 shown is designed in this figure for temperature measurements in volcanic glow clouds and consists of a temperature probe, an accelerometer and an antenna, which transmits the data to the user by radio. The sensor system 4 is surrounded by an inner shell 5a made of polyetheretherketone (PEEK) and an outer shell 5b made of cork. Cork absorbs shock, is heat-resistant and insulating, and is lightweight. PEEK is also heat-resistant with a melting temperature >330°C, is inelastic and has a high resistance to deformation.

In an exemplary representation of an embodiment variant of a sensor platform release mechanism 2 according to the invention attached to an aircraft 3, in this example to a VTOL (Vertical Take Off and Landing) long-range drone, or a wingcopter, is shown.

Another example:

• Für Temperaturmessungen in vulkanischen Glutwolken wird ein Sensorsystem 4 aufweisend einen PT-100-Temperatursensor und ein integriertes, digitales 3-Achsen-Accelerometer mitsamt Gyroskop gemäß genutzt.

The invention is described below using a specific exemplary embodiment, with the addition of the illustrations explained above:

• A sensor system 4 comprising a PT-100 temperature sensor and an integrated, digital 3-axis accelerometer together with a gyroscope is used for temperature measurements in volcanic glow clouds according to FIG used.

An armored shell made of the plastic PEEK surrounds the sensor system 4, i.e. the battery and electronics of the sensor. Plastics generally have low thermal conductivity, which protects the interior from overheating for a certain period of time. PEEK is temperature resistant up to 300°C. Since this plastic is also very tough, it results a very high impact resistance, which is necessary when the sensor hits rocks.

The PEEK armor shell consists of two hemispheres that are threaded on the equatorial plane. An O-ring is used to counteract loosening of the thread and for additional sealing. This prevents the armored shell from being opened unintentionally.

The sensor is additionally protected by a layer of cork around the armored shell. This cork shell serves as a shock absorber and as temperature insulation. In addition to the low thermal conductivity of cork, another protective effect through ablation is used. The cork granules will ignite and burn up from the outside in. When these glowing pieces of cork detach from the shell, heat is dissipated, which has been proven in space travel for decades. The protective cork shells are made of granules with polyurethane glue and/or silicone.

The sensitive area of the temperature sensor is led out of the insulating sleeves (inner sleeve: PEEK, outer sleeve: cork) 5a, 5b and is not covered by the insulating cork layer. The sensor electronics include a module for digitizing the temperature data, a transceiver module for sending the processed data and a microcontroller for controlling the entire electronics and pre-processing the data.

The accelerometer and gyroscope data are numerically integrated directly in the probe by the microcontroller, which makes it possible to determine the position of the probe. This position data is written to a FIFO memory (“first in, first out”) at fixed times, together with the temperature and time stamp. The content of this FIFO memory is constantly transmitted to the integrated transceiver module, which sends the data to a receiver in the missile, here a drone, or located directly at the user. It is sufficient to measure the temperature only once per second. By using a baud rate in the thousands, it is possible to transmit each data item several times, i.e. with redundancy. Older entries that have already been transferred several times are continuously replaced by newer ones. As a result, short-term disturbances in radio transmission, which are to be expected in a harsh environment, hardly pose a problem. The time stamp in the data record later enables the measurement data to be assigned correctly.

Reference List

1

sensor platform

2

Sensor Platform Dropping Mechanism

3

aircraft

4

sensor system

5

Isolation / protective cover sensor system

5a

inner shell

5b

outer shell

Claims (12)

Sensor platform (1) and associated sensor platform release mechanism (2); comprising: - at least one sensor platform (1) and - a sensor platform release mechanism (2); characterized in that : - the sensor platform (1) comprises at least one sensor system (4), radio-based data transmission and thermal, mechanical and chemical insulation of the sensor system (5), wherein - the sensor system (4) has a modular structure and has devices for recording location data, - the radio-based data transmission stores measurement data and transmits them using radio technology, and - the insulation of the sensor system (5) has one or more covers; - the sensor platform release mechanism (2) - is designed to be modularly mountable on an aircraft (3) and is arranged on the aircraft (3) according to use, the aircraft (3) being designed for transporting and positioning the at least one sensor platform (1) attached to the sensor platform release mechanism (2) at a predetermined location; and - has devices for the detachable mounting of at least one sensor platform (1), wherein by triggering the devices for the detachable mounting a targeted dropping of the at least one sensor platform (1) from the air is possible. sensor platform (1) and sensor platform ejection mechanism (2). claim 1 , characterized in that a shell for insulating the sensor system (5) in the sensor platform (1) is made of polyetheretherketone (PEEK). Sensor platform (1) and sensor platform ejection mechanism (2) according to the preceding claim, characterized in that the cover for isolating the sensor system (5) in the sensor platform (1) is surrounded by a further cover made of a cork layer. Sensor platform (1) and sensor platform ejection mechanism (2) according to one of the preceding claims, characterized in that the sensor system (4) has at least one sensor for recording selected parameters selected from the following list: temperature, pressure, humidity, flow rate, acceleration, viscosity, density, pH value, electrochemical potential, ionic strength, sound values, proximity, light. Sensor platform (1) and sensor platform release mechanism (2) according to one of the preceding claims, characterized in that the device for recording location data is designed as an accelerometer. Sensor platform (1) and sensor platform release mechanism (2) according to one of the preceding claims, characterized in that the radio-assisted data transmission stores measurement data and transmits them redundantly using radio technology. Sensor platform (1) and sensor platform release mechanism (2) according to one of the preceding claims, characterized in that a modified surface structure and/or shape of the one or more shells of the insulation of the sensor system (5) is formed by partial damage, deformation or melting. Sensor platform (1) and sensor platform ejection mechanism (2) according to any one of the preceding claims, characterized in that the sensor platform ejection mechanism has an aerodynamic shape. Sensor platform (1) and sensor platform ejection mechanism (2) according to one of the preceding claims, characterized in that a camera is integrated in the sensor platform ejection mechanism (2), the integrated camera being designed as a means for positioning the sensor platform ejection mechanism (2) and enabling the at least one sensor platform (1) to be ejected with precision by triggering the devices for releasable reception. Sensor platform (1) and sensor platform release mechanism (2) according to one of the preceding claims, characterized in that the camera integrated in the sensor platform release mechanism (2) is attached via a gimbal suspension. Sensor platform dropping method with a sensor platform (1) and associated sensor platform dropping mechanism (2) according to one of the preceding claims, having the steps: - Production of specific sensor platform(s) (1) corresponding to the application requirements; - Attaching at least one sensor platform (1) to the devices provided for this purpose of a sensor platform release mechanism (2); - Mounting the sensor platform dropping mechanism (2) on an aircraft (3); - Autonomous or manual positioning of the aircraft (3) and the sensor platform dropping mechanism (2) at a predetermined location; - Autonomous or manual precise dropping of the at least one sensor platform (1) at the predetermined location; - Measurement, storage and transmission of data via radio technology to the user via the sensor platform (1). Sensor platform dropping method with a sensor platform (1) and associated sensor platform dropping mechanism (2) according to the preceding claim, comprising additional steps, namely: - Use of the aircraft (3) as a repeater for the radio signal and / or - Recovery of at least one sensor platform (1).