US20170029111A1

US20170029111A1 - Unmanned aerial vehicle and method for launching

Info

Publication number: US20170029111A1
Application number: US15/264,487
Authority: US
Inventors: Andrew Charles Elson
Original assignee: ASTIGAN Ltd
Current assignee: ASTIGAN Ltd
Priority date: 2012-07-20
Filing date: 2016-09-13
Publication date: 2017-02-02
Also published as: EP3219612A1; AU2013291771A1; AU2013291771B2; WO2014013270A1; GB201212922D0; US9169014B2; ZA201501025B; EP2874875A1; CA2878145A1; US20140021288A1; GB2504132A; EP2874875B1; AU2017203967A1; WO2014013268A1

Abstract

An embodiment of an unmanned aerial vehicle, which may be connected to a lighter-than-air carrier, may have a ratio of a lifting force of the carrier to a weight of the vehicle from 1.1:1 to 3:1. The vehicle, excluding payload, may have a mass of from 30 kg to 150 kg. The vehicle may have a wingspan of from 20 m to 60 m.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of U.S. patent application Ser. No. 14/416,035, filed Jan. 20, 2015, which is a national phase application of PCT/GB2013/051942, filed Jul. 19, 2013, which claims priority to United Kingdom (GB) Patent Application No. 1212922.7, filed Jul. 20, 2012, and also which is a continuation-in-part of U.S. patent application Ser. No. 13/569,360, filed Aug. 8, 2012, issued as U.S. Pat. No. 9,169,014 on Oct. 27, 2015, which claims priority to United Kingdom (GB) Patent Application No. 1212922.7, filed Jul. 20, 2012, each and all of the above of which is/are hereby incorporated by reference.

TECHNICAL FIELD

The present invention relates to an unmanned aerial vehicle and a method of launching such a vehicle.

BACKGROUND

High-altitude, long endurance solar powered aircraft concepts have been proposed for some time. Such vehicles at this altitude provide significant potential benefits. For example wind strengths and turbulence levels are at a minimum between around 18,000 m and 30,000 m altitude. Additionally, this altitude range is above normal aviation authority certification needs, and large areas of the planet can be observed, with the distance to the horizon being over 500 km. Such unmanned vehicles are therefore suitable for aerial surveys, surveillance and emergency communications in disaster recovery situations.
In 1974, AstroFlight built the first solar powered drone Sunrise I. The promising results of the 10 m span, Sunrise I, led to the Sunrise II, with 4480 solar cells, theoretically capable of attaining a service ceiling of 23,000 m. Sunrise II flew successfully, but broke up in flight at 7,000 m due to a suspected aeroelastic problem.
In-flight breakup is thought to be caused by a gust-induced aeroelastic wing shape change, leading to a control system instability. The resulting pitch oscillation resulted in excessive speeds which caused failure of the wing covering.
NASA's High Altitude Solar (HALSOL) project in 1995 saw the flight of the Pathfinder, which reached an altitude of 13,000 m. This was followed by the Pathfinder-Plus which reached 24,500 m, with its 19% efficient silicon solar cells and a payload of 67 kg. Centurion followed with a wing span of 63 m with 62,100 bi-fractal solar cells and a payload of up to 270 kg.
Under NASA's Environmental research Aircraft and Sensor Technology Program (1998-2003) the Centurion was modified to become Helios. The Helios prototype was designed as a proof of concept high-altitude unmanned aerial vehicle that could fly on long endurance environmental science or telecommunications relay missions lasting for weeks or months. Helios made use of 19% efficient silicon based solar cells on the upper wing and lithium batteries. Helios had a constant 2.4 m chord and was assembled in six 12.5 m sections with under wing pods at the juncture of each section. Helios reached an altitude of 29,000 m on solar power. Payload was around 300 kg.
In 2005, AC propulsion developed the SoLong aircraft. With the energy storage advances made with Lithium ion batteries (220 WHr/kg), SoLong was able to stay airborne for two half nights, starting with a charged battery at midnight and flying to midnight the next day. This initial 24 hour flight was followed a few months later with a full 48 hour flight.
The present inventor, together with QinetiQ built the Zephyr aircraft (Zephyr III) in 2002 in order to film a balloon altitude record attempt at 40,000 m. QinetiQ went on with European funding to develop a ground launch system. In 2007, QinetiQ flew the Zephyr for 83 hours using both 25% efficient solar cells and 350 Whr/kg Lithium Solar batteries. Zephyr reached a record altitude of 29,000 m in 2008. A payload of around 2.5 kg was carried.
The Zephyr holds the official endurance record for an unmanned aerial vehicle for its flight from 9 Jul. to 23 Jul. 2010, lasting 336 hours and 22 minutes (2 weeks/14 days). Record claims have been verified by the Fédération Aéronautique Internationale (FAI) for both duration and altitude. It beat the previous endurance record for unmanned flight by more than a factor of five.
However, these methods of launching an unmanned aerial vehicle at such altitudes involve a ground launching method, whereby the vehicle propels itself from ground level to the relatively calm stratospheric zone above 15-20,000 m.
US 2006/0278757 discloses a method of launching an unmanned aerial vehicle which involves the vehicle being attached to a lighter-than-air carrier from below and does not involve a ground launching approach. Once at the desired altitude the vehicle remains attached to the carrier and begins to fly in an ever-increasingly horizontal attitude, using the carrier as an anchor around which it flies, until it is at a velocity where it is capable of independent flight, whereupon it is separated from the carrier to begin independent and sustained flight.
However it has been found that such a carrier must carry a significant additional mass, and therefore have a very high lifting force, in order to perform as such an anchor without it itself being moved by the vehicle. It is estimated that the carrier would need a lifting force five to fifteen times that of the weight of the vehicle. If the carrier is a balloon, then such a balloon would have to be very large, e.g. 30 m in diameter for a small unmanned aerial vehicle of 75 kg take-off weight.
WO 00/34122 discloses a method for transporting an aircraft into space by use of a lighter-than-air balloon. The delivery system is proposed as a replacement for conventional rockets and relates to payloads of around 5 tons.
JP 2000187081 discloses an aerial observation device with the launch method involving the use of a lighter-than-air balloon. The altitudes reached by the balloon are less than 7000 m and the aircraft descends to 3000 m before being capable of independent flight.
U.S. Pat. No. 7,313,362 discloses a high altitude airborne craft which is lifted from the ground by a lighter-than-air balloon. The aircraft is disclosed as being lifted from the ground in a horizontal orientation.
An improved method of launching an unmanned aerial vehicle into high altitude zones would therefore be highly desirable.

SUMMARY OF INVENTION

In a first aspect, the present invention relates to a method of launching an unmanned aerial vehicle at an elevated altitude, the method comprising (i) lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to the elevated location, wherein the vehicle is prevented from entering its flight mode during the ascent, (ii) causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.
The method of the invention thus lifts the unmanned aerial vehicle to an altitude above which the vehicle will reach its flight velocity at. While the vehicle is climbing, the vehicle is prevented from entering its flight mode, e.g. with its wings in a wing-tip-up orientation, i.e. wherein the wings are substantially vertically aligned. Once at a sufficient altitude, the vehicle is released in such a way that its resulting descent increases its air velocity and lift until such descent provides sufficient air velocity for sustained independent flight.
The elevated altitude is typically at least 1000 m in altitude, but is ideally at least 13,000 m in altitude. Preferably the elevated altitude is in the stratosphere. Typically the elevated altitude will be from 18,000 to 30,000 m.
As there is no relative motion between the carrier and the vehicle, other than the minor relative motions induced by the very local atmospheric conditions, the carrier merely has to have sufficient lift to lift the vehicle to its launch altitude.
Thus, in a preferred embodiment, the ratio of the lifting force of the carrier to the weight of the vehicle is from 1.1:1 to 3:1, more preferably from 1.2:1 to 2:1.
Thus, in another aspect, the invention relates to an unmanned aerial vehicle connected to a lighter-than-air carrier, wherein the ratio of the lifting force of the carrier to the weight of the vehicle is from 1.1:1 to 3:1, more preferably from 1.2:1 to 2:1.
The substantially ground-level location is typically at or very near to the land or sea surface of the planet e.g. within 1,000 m, preferably within 100 m of a land or sea surface.
The unmanned vehicle is typically of the sort that resembles a glider, having at least two aerodynamic lifting surfaces, e.g. wings, a fuselage, a tail and at least one propeller powered by a motor and a power supply, although a wide variety of variations on this basic structure can be envisaged.
The method of the invention allows the vehicle to be designed for flight in the stratosphere, which is a considerably calmer region of the atmosphere as compared to the troposphere below. This is because the vehicle can begin its flight and remain in the stratosphere, as it is carried upwards by the carrier through key risk areas of the high wind loads introduced at 4,500 m to 10,500 m.
This results in the removal of a number of significant design constraints, which would otherwise need to be present if the vehicle had to fly itself to such altitudes. Thus, the vehicle can be lighter and more fragile than would be possible for a ground-launched vehicle.
For example, it is well-known that wind loadings are proportional to pu²where p is the air density and u is the air velocity. At 20,000 m altitude the air density is about one-fifth that at 12,000 m, and the typical peak mean and eddy velocities are around one-half to one-third. Thus, dynamic wind loadings at 12,000 m are around 20 to 40 times those in the tropopause or stratosphere.
As the vehicle is typically optimized for stratospheric flight, the vehicle does not need to travel through such a range of air densities. This can result in a simpler design, for example doing away with heavy gearing systems for propellers needed for a ground-launched vehicle. This therefore results in a greater weight available for functional payload equipment.
Thus, typically the vehicle has a wingspan of from 20 to 60 m. Also, the vehicle is typically of very low weight such that the vehicle excluding payload is from 30 to 150 kg, preferably from 30 to 100 kg. Such vehicles can carry payloads that are a significant proportion of the overall weight of the vehicle, such as 15 to 100 kg payloads.
The cord length of the wings is preferably in the range of from 1 to 3 m, with 1.5 to 2.5 being typical. Thus, the surface area of the wings on their upper face is generally from 50 to 150 m², preferably from 70 to 120 m².
One way of characterizing the large wing area in relation to the weight of the vehicle is to use the upper surface wing surface area in relation to the weight of the vehicle excluding payload.
Thus, typically the vehicle will have an upper wing surface area to weight ratio of from 0.5 to 2.0 m²/kg, preferably from 1.0 to 2.0 m²/kg.
For example, one exemplary vehicle has a wingspan of 30 m with a cord length of 2.5 m, giving an upper wing surface area of 75 m². The weight of the vehicle is 50 kg. Thus the upper wing surface area to weight ratio is 1.5 m²/kg.
Additionally, as the weight of the vehicle is so low, the volume of a lighter-than-air balloon required to lift the vehicle becomes correspondingly smaller, resulting in reduced costs and better handling. At ground level 1 m³of helium is capable of lifting approximately 1 kg of vehicle. However at an altitude of 26,000 m, a 1 m³balloon is capable of lifting 0.1 kg. Thus, by having such a high launch altitude the lifting capacity of a lighter-than-air balloon can reduce by an order of magnitude during the ascent. Thus, a balloon with 500 m³of helium is capable of lifting 50 kg at 26,000 m altitude. Thus, even with a lightweight vehicle of 50 kg, a balloon of 500 m³volume is required to lift it to 26,000 m.
It can therefore be seen that the weight of the vehicle is a significant constraint, and heavier vehicles in excess of 200 kg are impractical to launch at such high altitudes as in the present invention.
Thus, in another aspect, the invention relates to an unmanned aerial vehicle wherein the total weight of the vehicle is comprised of greater than 30% payload, preferably greater than 40% payload and more preferably greater than 50% payload.
Payload is items carried by the vehicle which do not contribute directly to the flight of the vehicle, e.g. are not involved in providing lift, structure or propulsion. Payload therefore includes solar collectors, batteries and other functional equipment such as cameras, receivers, transmitters, navigational systems, antennas etc. carried by the vehicle. In case of doubt, an item is considered to be payload if it can be removed without compromising the ability of the vehicle to fly.
The vehicle may be attached to the lighter-than-air carrier by a wide variety of methods. One preferred method is to attach the vehicle to the carrier by one or more tethers. Such tethers can be lengthened or shortened as necessary to adjust the orientation of the vehicle. For example tethers may be attached to the fuselage and at one or both wings. Such tethers can be lengthened or shortened according to known methods, such as by paying in/out from a reel. Methods of lengthening such tethers includes a breakable tie holding a loop or multiple loops in the tether. Instead of lengthening or shortening a tether a redundant tether could be included which only supports weight of the vehicle when another tether is severed, for example.
It has been found that, as the vehicle is typically optimized for stratospheric flight and has a large wingspan in relation to its weight, care must be taken during launch.
However at the moment of launch from the ground, it can be inconvenient to launch the vehicle in a wing-tip-up orientation due to the potentially large wingspan. Thus, in a preferred embodiment, the vehicle leaves the ground in a tail-up orientation. This is where the tail is pointing upwards and the wings extend substantially horizontally. For example, the vehicle can be put into a tail-up orientation by use of rolling aids under the fuselage.
In some cases however, such a vehicle can be so fragile that ground-level winds can provide sufficient force on the wings that the vehicle can mechanically fail under the ground level wind loads. Thus, the inventor has developed a ground-level launch housing for the vehicle wherein the housing is not rigidly connected to the ground.
Such a housing is designed to allow the vehicle to slide across the ground in the event of an high wind before launch. Thus, the energy imparted by the winds causes the vehicle and housing to slide along the ground rather than being absorbed by the vehicle structure. In a preferred embodiment the housing contains a slot for receiving the vehicle, preferably in a tail-up orientation, so that the nose of the vehicle is positioned in the housing. The housing is typically of very low material density, e.g. less than 50 kg/m³. For example, it may be manufactured from a foam, such as polystyrene, or could be an inflatable housing.
At the moment of launch, the lighter-than-air carrier is released and begins to lift the vehicle from the ground.
Once the ground launch has occurred, care must be taken that the vehicle does not prematurely enter its flight mode, even without any powered motors, during ascent, when the local wind speeds can be sufficient to induce premature flight conditions.
The inventor has made the insight that, as the vehicle is carried upwards by a lighter-than-air carrier, it will generally be carried along with lateral winds. Thus, the local wind direction experienced by the vehicle during ascent will be almost entirely vertically downwards.
It has been found that arranging for the vehicle to ascend in a wing-tip-up orientation i.e. where the wings of the vehicle are substantially vertically aligned, minimizes the tendency of the vehicle to enter a flight mode, as the local wind direction will be along the wingspan, from wing-tip to wing-tip, and thus not activating the lift which the wings can provide. Alternatively, or additionally, control systems could be introduced to prevent such premature flight.
Thus, once the vehicle has left the ground, the vehicle enters a wing-tip-up orientation if it is not already in that orientation, preferably in the vicinity of the ground, e.g. within 1000 m or preferably within 500 m, or more preferably within 200 m of the substantially ground-level location.
Furthermore, this method of ascension of the vehicle allows it to be lifted at an increased rate. Thus the vehicle is typically able to climb at a rate of from 1 to 10 m/s, preferably from 1.5 to 8 m/s.
Prior to the moment of release the carrier supports the weight of the vehicle, whose velocity is substantially zero relative to the carrier. This means that the vehicle is not performing any powered motion relative to the carrier during the moment of release. Clearly there may be some relative motion due to local atmospheric conditions, but this is not considered to be relative motion between the vehicle and carrier.
Prior to the moment of release the vehicle is typically tipped forward to a nose-down pitch with wings approximately level, so that at the moment of detachment, the vehicle descends in a gliding manner, while increasing its air speed in a controlled manner.
Typically the powered motors of the vehicle are only started after the detachment occurs, although they could be started shortly before detachment, provided this induces substantially no relative motion between the vehicle and carrier.
Typically the vehicle is solar-powered, comprising solar energy collectors and batteries for storing solar energy. The vehicle is also typically of the long-endurance type, capable of independent flight for extended periods, such as days, weeks, months or even years.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention will now be illustrated, by way of example, and with reference to the following drawings, in which:

FIG. 1 is a schematic representation of the stages involved in carrying out the method of the present invention.

FIG. 2 is a schematic representation of a preferred ground launch method according to the present invention.

FIG. 3 is a schematic representation of a further preferred ground launch method according to the present invention.

FIG. 4 is a schematic representation of another launch method according to the present invention.

DETAILED DESCRIPTION

Turning to the figures, FIG. 1 shows an unmanned aerial vehicle 10 attached to a lighter-than-air balloon 12 acting as the carrier. At stage A the vehicle 10 is at rest at a ground-level location in a horizontal position flat to the ground. The vehicle is then tipped forwards to obtain a tail-up orientation at stage B. This may be carried out by the use of tethers (not shown) attached to the vehicle.
The balloon 12 is released and lifts the vehicle up from the ground initially in its tail-up orientation. However, shortly after the ascent begins, the vehicle 10 is maneuvered into a wing-tip-up orientation, as shown in stages C and D.
As the balloon is carried along with any lateral winds, the local wind velocity experienced by the vehicle is vertically along the wingspan. The balloon and vehicle continue to ascend to a launch altitude typically of from 18,000 m to 30,000 m.
Once at the launch altitude, the vehicle 10 is reoriented back into a horizontal position, as shown in stage E. There is a possible extra stage where the vehicle is further tipped forwards into a nose-down orientation.
When it is desired to launch the vehicle, it is released from the balloon 12, whereupon it glides away from the balloon and accelerates due to the fall in altitude. Once the glider has reached a sufficient velocity, its engines are started and it is capable of long-endurance powered flight.
FIG. 2 shows the ground launch stages in greater detail. Initially, the vehicle 10 is at rest at a ground-level location in a horizontal position flat to the ground. The vehicle 10 is attached to balloon 12 by tethers 4, 5 attached to the fuselage and a wing-tip respectively. Tether 4 is attached at a point on the fuselage which is approximately the centre of mass of the vehicle 10. Initially, tether 5 attached to the wing-tip is not under tension.
The balloon 12 is tethered to the ground by tethers 6. When it is desired to launch the vehicle 10 the vehicle enters a tail-up orientation, as shown in stage B. Thereafter the tethers 6 are extended to allow the balloon 12 to rise. As vehicle 10 is attached to balloon 12 by tether 4, the vehicle 10 also rises.
Shortly after leaving the ground tether 5 is shortened until it causes the wing of the vehicle to which tether 5 is attached to tip upwards. Tether 5 is shortened further until the vehicle is completely tipped onto its side as shown in stage C. At this stage, the weight of the vehicle is supported entirely by tether 5 and thus, tether 4 is no longer in tension.
The vehicle then ascends in this position, until it reaches launch altitude.
FIG. 3 shows in greater detail how the ground launch is carried out. Initially, the vehicle 10 is at rest at a ground-level location in a horizontal position flat to the ground. The wings and nose of the vehicle are placed in an inflatable housing 3, which is initially shown deflated in stage A.
When it is desired to launch the vehicle 10, the inflatable housing 3 is inflated. In view of the shape of the housing, the vehicle enters a tail-up orientation as the housing 3 inflates, as shown in stage B.
Once in this position, in the event that any ground level winds occur, the vehicle 10 and housing 3 simply slide along the ground. Thus the vehicle wings do not resist the wind and instead they yield to it, greatly reducing any stresses induces in the vehicle structure and greatly reducing or eliminating the chance that a wind may damage the vehicle.
The balloon 12 is subsequently released from the ground and the vehicle is lifted out of housing 3 in its tail-up orientation.
Shortly after leaving the ground tether 5 is shortened until it causes the wing of the vehicle to which tether 5 is attached to tip upwards. Tether 5 is shortened further until the vehicle is completely tipped onto its side as shown in stage D. At this stage, the weight of the vehicle is supported entirely by tether 5 and thus, tether 4 is no longer in tension.
FIG. 4 shows an unmanned aerial vehicle 10 attached to a lighter-than-air balloon 12 acting as the carrier at a ground level location at stage A. The vehicle 10 is attached to the balloon by three cords 14, one attached to a wing-tip and two attached to the fuselage.
During launch, the balloon 12 lifts and the vehicle 10 enters a wing-tip-up orientation, as shown in stage B, achieved by pulling on the cord attached to the wing-tip.
The balloon 12 then begins the ascent, carrying the vehicle 10 suspended below in its wing-tip-up orientation, as shown in stage C.
Once at the launch altitude the vehicle is moved back into a horizontal attitude by letting out the cord attached to its wing-tip, as shown in stage D.
The cord attached to the wing-tip is then severed, together with one of the cords attached to the fuselage, causing the vehicle 10 to enter a nose-down configuration, as shown in stage E and F.
Finally the last cord is severed, releasing the vehicle to begin its descent, as shown in stage G. The motors are powered and the vehicle increases its flight velocity until it can control its descent and is capable of independent flight.
The present disclosure may include one or more of the following concepts:
A. Method of launching a powered unmanned aerial vehicle at an elevated altitude, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, wherein the vehicle is prevented from entering its flight mode during ascent, causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.
B. Method in accordance with paragraph A, wherein the wings of the vehicle are substantially vertically aligned during substantially all of the ascent.
C. Method in accordance with either of the previous paragraphs, wherein the vehicle leaves the substantially ground-level location in a tail-up orientation
D. Method in accordance with any of the previous paragraphs, wherein the vehicle is mounted at the substantially ground-level location in a launch housing for the vehicle, wherein the housing is not rigidly connected to the ground.
E. Method in accordance with paragraph D, wherein the housing has a density of less than 50 kg/m³.
F. Method in accordance with any of the previous paragraphs, wherein, once the vehicle has left the ground, the vehicle enters a wing-tip-up orientation if it is not already in that orientation.
G. Method in accordance with any of the previous paragraphs, wherein the vehicle climbs at a rate of from 1 to 10 m/s, preferably from 1.5 to 8 m/s.
H. Method in accordance with any of the previous paragraphs, wherein the ratio of the lifting force of the carrier to the weight of the vehicle is from 1.1:1 to 3:1, more preferably from 1.2:1 to 2:1.
I. Method in accordance with any of the previous paragraphs, wherein the powered motors of the vehicle are only started after the detachment occurs.
J. Method in accordance with any of the previous paragraphs, wherein, at the moment of release the vehicle is tipped forward to a nose-down pitch.
K. Method in accordance with any of the previous paragraphs, wherein the elevated altitude is from 18,000 m to 30,000 m.
L. Unmanned aerial vehicle connected to a lighter-than-air carrier, wherein the ratio of the lifting force of the carrier to the weight of the vehicle is from 1.1:1 to 3:1, more preferably from 1.2:1 to 2:1.
M. Unmanned aerial vehicle wherein the total weight of the vehicle is comprised of greater than 30% payload, preferably greater than 40% payload and more preferably greater than 50% payload.
N. Method or vehicle in accordance with any of the previous paragraphs, wherein the vehicle has a wingspan of from 20 to 60 m.
O. Method or vehicle in accordance with any of the previous paragraphs, wherein the vehicle, excluding payload, has a mass of from 30 to 150 kg, preferably from 30 to 100 kg.
P. Method or vehicle in accordance with any of the previous paragraphs, wherein the vehicle comprises at least two wings, a fuselage, a tail and at least one propeller powered by a motor and a power supply.
Q. Method or vehicle in accordance with any of the previous paragraphs, wherein the vehicle is solar-powered, comprising solar energy collectors and batteries for storing solar energy.
R. Method or vehicle in accordance with any of the previous paragraphs, wherein the vehicle is attached to the carrier via at least one tether.

Claims

What is claimed is:

1. An unmanned aerial vehicle connected to a lighter-than-air carrier, wherein a ratio of a lifting force of the carrier to a weight of the vehicle is from 1.1:1 to 3:1, the vehicle, excluding payload, has a mass of from 30 kg to 150 kg, and the vehicle has a wingspan of from 20 m to 60 m.

2. The unmanned aerial vehicle connected to the lighter-than-air carrier according to claim 1, wherein a total weight of the vehicle is comprised of greater than 30% payload.

3. The unmanned aerial vehicle connected to the lighter-than-air carrier according to claim 1, wherein the vehicle, excluding payload, has a mass of from 30 kilograms (kg) to 100 kg.

4. The unmanned aerial vehicle connected to the lighter-than-air carrier according to claim 1, wherein the vehicle comprises at least two wings, a fuselage, a tail and at least one propeller powered by a motor and a power supply.

5. The unmanned aerial vehicle connected to the lighter-than-air carrier according to claim 1, wherein the vehicle is solar-powered, comprising solar energy collectors and batteries for storing solar energy.

6. The unmanned aerial vehicle connected to the lighter-than-air carrier according to claim 1, wherein the vehicle is attached to the carrier via at least one tether.

7. The unmanned aerial vehicle connected to the lighter-than-air carrier according to claim 1, wherein the total weight of the vehicle is comprised of greater than 40% payload.

8. The unmanned aerial vehicle connected to the lighter-than-air carrier according to claim 1, wherein the total weight of the vehicle is comprised of greater than 50% payload.

9. The unmanned aerial vehicle connected to the lighter-than-air carrier according to claim 1, wherein the ratio of the lifting force of the carrier to the weight of the vehicle is from 1.2:1 to 2:1.