Demonstration of a Compact Magneto-Optical Trap on an Unstaffed Aerial Vehicle

Abstract

The extraordinary performance offered by cold atom-based clocks and sensors has the opportunity to profoundly affect a range of applications, for example in gravity surveys, enabling long term monitoring applications through low drift measurements. While ground-based devices are already starting to enter the commercial market, significant improvements in robustness and reductions to size, weight, and power are required for such devices to be deployed by Unstaffed Aerial Vehicle systems (UAV). In this article, we realise the first step towards the deployment of cold atom based clocks and sensors on UAV’s by demonstrating an UAV portable magneto-optical trap system, the core package of cold atom based systems. This system is able to generate clouds of $2.1\pm 0.2\times {10}^7$ atoms, in a package of 370 mm × 350 mm × 100 mm, weighing 6.56 kg, consuming 80 W of power.

1. Introduction

Quantum technology based on cold atoms [1] has proven to be a powerful method for precision sensing [2,3] and time keeping [4]. For example, within laboratories, cold atom sensors have provided sensitive measurements of gravity [5], enabling investigations of the equivalence principle [6], the fine-structure constant [7], and Newton’s gravitational constant [8], as well as prompting the desire to transition these sensors into practical devices for use in real-world environments [2]. Currently, cold atom-based sensors have been demonstrated in urban [9] and mountainous environments [10,11], on road vehicles [12], aircraft [13,14], ships [15], the International Space Station [16], and on rockets [17].

There is significant interest in developing such systems for small and remote, or autonomous, platforms that require compact sensors. In particular, the deployment of sensors using Unstaffed Aerial Vehicles (UAVs) would enable applications that require access to inaccessible or hazardous locations—and future operation in flight on UAVs may enable autonomous surveillance and a wide range of applications. UAVs are used in a number of applications including archaeology [18], disaster recovery [19], forestry research [20], precision agriculture [21], and detection of rift basins [22]. Adding cold atom-based sensing to the array of sensors already deployed by and available on UAVs would not only enhance existing applications, but has the potential to open up new ones [2,23]. However, before wide adoption of cold atom based sensors and clocks can be realised, a number of challenges need to be overcome, including strict Size, Weight, and Power (SWaP) requirements and robustness against platform motion.

This article presents the first step towards a UAV portable cold atom device, by demonstrating a compact Magneto-Optical Trap (MOT) capable of being moved and deployed by a UAV, as well as demonstrating its operation during flight.

2. System Overview

The compact MOT system can be seen in Figure 1 and contains all the electronic, vacuum, and laser components required to generate a MOT.

The ultra-high vacuum environment is maintained within the science chamber by an active ion pump and passive getter pump when not in flight, and just the unpowered getter pump while in flight. When actively pumping, the chamber is maintained at an equilibrium pressure of $4\times {10}^{-9}$ mbar. The vacuum system houses rubidium dispensers which generate a background gas from which the MOT can load, in addition to four 10 mm prisms, a mirror, and a quarter wave plate arranged such that the beams required for laser cooling can be generated from a single input telescope [24,25]. The science chamber is shown in Figure 1B.

The quadrapole magnetic field environment required by the MOT was generated with permanent magnets arranged in a north–south cross configuration [24], with two 3 mm × 3 mm × 8 mm neodynium magnets at each cross point producing a magnetic field gradient of 17 G/cm. As an alternative, the system can be fitted with a pair of coils that can be used to generate a similar quadrupole field. If used, the coils require 6.4 W of power to operate.

The light used to cool and trap the atoms is generated with a frequency-doubled fibre laser system, a schematic of which can be seen in Figure 2. The use of fibre integrated components alleviates alignment issues, improving resilience against the effects of platform motion, such as mechanical shock and vibration [27]. The two frequencies needed for cooling ${}^{87}$ Rb atoms on the D2 transition are derived from the carrier and first-order frequency sideband created by phase modulation. The laser is linearly scanned over a region of 500 MHz to generate the cooling frequency. The laser frequency is scanned using an Arduino microcontroller generating a triangle wave, which scanned the piezo input of the seed laser, passing over half the cooling frequency on the cycling $|F^{\prime }=2⟩\to |F^{\prime }=3⟩$ transition roughly once every 40 s. The light from the seed laser is passed through an electro-optical modulator (EOM), which modulates the light at $6.5$ GHz to generate a sideband that acts as the repumping frequency on the $|F=1⟩\to |F^{\prime }=2⟩$ transition. After the EOM the light is then amplified with an erbium-doped fibre amplifier (EDFA) before being frequency doubled from 1560 nm to 780 nm in a periodically poled lithium niobate (PPLN) waveguide. The system can produce up to 450 mW of 780 nm laser light at the output into the fibre. The light out of the fibre then passes through a quarter waveplate to produce circularly polarised light and two beam expanders such that when the light reaches the prisms it has a beam diameter of 30 mm (1/e ${}^2$ ). When left to run autonomously, the system generates a cloud of atoms lasting roughly 1 s every 40 s. Alternatively, the system could be locked to the fluorescence of the MOT [24].

The laser system and control system are integrated around the vacuum system into a custom carbon fibre enclosure as shown in Figure 3.

The atom number produced in the system was characterised using a MOT loading curve [28]. An example loading curve can be seen in Figure 4. The MOT, when fully loaded, has an atom number of $2.1\pm 0.2\times {10}^7$ and has a loading time constant of $1.47\pm 0.12$ s. This is similar to what is achieved in existing cold atom based sensors [3,10,13,29].

The weight and power consumption when the MOT is running at peak power in flight is shown in Table 1. The majority of the power consumption is by the UAV itself; depending on the environmental factors, such as wind, and the amount of acceleration, the consumption may vary significantly. However, in a calm environment with moderate acceleration, the consumption would remain near the lower end of power range. The power consumption of the compact MOT is dominated by the laser system, in particular the EDFA, which accounts for $37\%$ of the power consumption. The batteries are the heaviest component in the system and account for $28\%$ of the total weight. The total weight of the UAV, compact MOT, and batteries, as well as the total power draw, will limit the total flight time possible with the system; we estimate this to be 18 min, compared to a maximum flight time of 32 min without the compact MOT system. Longer flight times will become possible with further SWaP reductions in cold atom systems; for example, halving the weight of the compact MOT would increase the max total flight time to 26 min. Examples of innovations which could be utilised to produce a SWaP optimised cold atom sensor include compact laser systems [30,31,32], optimised 3D printed components [33,34,35,36], high-flux compact cold-atom sources [37], and passively pumped vacuum cells [38,39,40].

In addition to implementing SWaP reductions to cold atom systems, implementing existing solutions to increase UAV flight times would enable longer flight times and include integration of a tether for power and data transmission [41], autonomous deployment and recovery from a charging station [42,43], solar-powered photovoltaic panels [44], larger UAVs, and use of batteries with high-power density such as high voltage lithium-ion polymer batteries [45].

3. Test Flight

The system was shut-down and transported via car for ∼45 min to a field in Birmingham, United Kingdom, on 7 March 2017 for a test flight. The compact MOT was mounted to a Vulcan UAV (from Raven UAV Ltd. Mitcheldean, Gloucestershire, UK) along with two Lithium Polymer (LiPo) batteries, which were able to supply 22.2 Volts with 22 Amp-hours of charge. These batteries were used to power both the compact MOT system and the UAV. The system can be seen in Figure 5A. The system was set to generate atom clouds periodically while on the ground and left to run autonomously throughout the whole of the test flight. The system was then flown to a height of ∼10 m, after which it hovered for 10 min before landing, during which time several atom clouds where generated. The system in flight can be seen in Figure 5B.

4. Discussion

The high precision and low-drift measurements offered by cold atom systems, once realised in a UAV portable package, have the opportunity to enhance sensing capability, particularly in a number of hard to reach, inaccessible or hazardous locations (examples include steep sides of volcanoes and dense forests) as well as rapid redeployment in cases of time-varying features for applications such as hydrological monitoring. Furthermore, a future UAV portable system could allow for deployment and redeployment of sensors to enable automated large area surveys, for example in archaeological applications, enabling the detection of tombs or buried cities or used for the mapping of aquifers.

To push cold atom based sensors towards the SWaP profile that is required for deployment and operation on UAVs, the first UAV portable cold atoms system has been developed. This system is capable of generating atom clouds consisting of $2.1\pm 0.2\times {10}^7$ laser-cooled atoms in a system package of 370 mm × 350 mm × 100 mm, weighing 6.56 kg and power consumption of 80 W. The system has successfully shown autonomous operation during a 10 minute flight ∼10 m above the ground on-board a commercial-off-the-shelf UAV.

To upgrade the demonstrator shown here to a full sensor, additional functionality will need to be implemented, primarily needing extensions to the control and laser system, while meeting the requirements for UAV operation. These requirements can be split into two categories, namely sufficiently small SWaP and robustness to platform motion, both of which are active research areas. For example, for the gravimeter gradiometer in reference [9] to have the same weight, and hence similar flight time, as the MOT demonstrator presented here, it would need to be reduced in weight by a factor of ≈50 times while having techniques such as those implemented in references [12,13,15] incorporated into the system to allow for measurements while in motion. While there is a clear route to further reduce the SWaP and realise sensing capabilities, achieving a UAV portable MOT is the first step towards achieving cold atom-based sensing on UAVs.

Author Contributions

Conceptualization, M.H.; methodology, L.E.; software, L.E.; validation, L.E. and M.W.; formal analysis, L.E.; investigation, L.E., J.V., J.W., F.H., M.W., D.R., M.P.-O. and A.L.; resources, M.H. and J.W.; data curation, J.V.; writing—original draft preparation, J.V.; writing—review and editing, J.V., L.E., J.W., M.H., J.W., F.H., N.M., A.L., P.G., M.W. and K.B.; visualization, J.V. and L.E.; supervision, M.H., N.M., M.P.-O., K.B. and P.G.; project administration, M.H. and K.B.; and funding acquisition, M.H. and K.B. All authors have read and agreed to the published version of the manuscript.

Funding

We acknowledge support from EPSRC through grants EP/M013294/1 and EP/T001046/1 as part of the UK National Quantum Technologies Programme.

Institutional Review Board Statement

Not applicable.

Informed Consent Statement

Not applicable.

Data Availability Statement

Data available upon request.

Conflicts of Interest

J.V. is acting as a guest editor for the special issue of Atoms in which this article is being submitted to. The other authors declare no conflicts of interest.

Abbreviations

The following abbreviations are used in this manuscript:

EDFA	Erbium-Doped Fiber Amplifier
EOM	Electro-Optical Modulator
LiPo	Lithium Polymer
MOT	Magneto Optical Trap
PPLN	Periodically Poled Lithium Niobate
SWaP	Size Weight and Power
UAV	Unstaffed Aerial Vehicle

Publisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations.

Figures and Table

Figure 1. (A) The compact MOT system, which is contained within a custom light weight carbon fibre enclosure with dimensions of 370 mm × 350 mm × 100 mm. (B) Schematic of the custom titanium science chamber in which the atom cloud is formed. The science chamber design is similar to that in reference [26]. A camera off axis to the input beam is used to observe the MOT through the same window as the input beam.

Figure 2. A block diagram of the electrical and optical components in the payload. The 22.2 Volt line from the batteries is fed into the payload; this is then converted into the required powers for each component. The output light from a seed laser (1560 nm) is modulated by an EOM driven by an oscillator to generate frequency sidebands, this is then amplified by a 1 W EDFA before being frequency doubled via second harmonic generation using a PPLN waveguide. The output of the fibre passes through two beam expanders and a quarter waveplate. This light is then input into the MOT vacuum chamber. A user interface allows for users to communicate with various sub-components and monitor the status of the payload. While in flight, the camera feed is broadcast in real time to the operator on the ground.

Figure 3. Photo showing the laser system and vacuum system integrated into the carbon fibre enclosure.

Figure 4. Example MOT loading curve taken while on the ground with the ion pump in operation. The loading curve has been fitted with equation 2 from reference [28]. The inset shows a photo of prism MOT. The atom cloud is highlighted within the red square.

Figure 5. (A) The VulcanUAV Raven complete with (LiPo) batteries and compact MOT payload. (B) The MOT system in flight. The inset shows a photo of an atom cloud generated in the system during flight, after background subtraction.

Table 1

The weight and power budget of the UAV with the portable compact MOT system in flight. The brackets show the effect of running the system with coils instead of magnets has on the power consumption of the system.

Subsystem	Weight (kg)	Power/Energy
Vacuum Chamber	1.58	15.00 W
Magnetic field generation	0.02	— (6.4 W)
Laser and control system	4.46	65.00 W
Housing and mounting	0.50	—
UAV	7.40	3.00–15.55 kW
Batteries	5.40	977.00 Wh
Total	19.36	3.08–15.63 kW(3.09–15.64 kW)

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