CN216834240U - Aircraft of different structure combination of airship and unmanned aerial vehicle - Google Patents
Aircraft of different structure combination of airship and unmanned aerial vehicle Download PDFInfo
- Publication number
- CN216834240U CN216834240U CN202120734525.3U CN202120734525U CN216834240U CN 216834240 U CN216834240 U CN 216834240U CN 202120734525 U CN202120734525 U CN 202120734525U CN 216834240 U CN216834240 U CN 216834240U
- Authority
- CN
- China
- Prior art keywords
- airship
- unmanned aerial
- aerial vehicle
- aircraft
- stratospheric
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model discloses an aircraft of different structure combination of airship and unmanned aerial vehicle, including stratospheric airship and a plurality of unmanned aerial vehicle, the stratospheric airship includes outer covering, main gasbag, preceding ballonet, well ballonet, back ballonet, fin, structure skeleton, structure nacelle and propulsion system, and propulsion system is including distributing at the three motor screw of stratospheric airship both sides and afterbody, and main gasbag is filled with the helium and provides buoyancy, and the ballonet fills with the air and realizes gesture and altitude mixture control, unmanned aerial vehicle hangs the belly of stratospheric airship or buries the structure nacelle at the stratospheric airship, and unmanned aerial vehicle includes fixed wing unmanned aerial vehicle, solar energy unmanned aerial vehicle and variant unmanned aerial vehicle. The utility model discloses make full use of airship high altitude long-term sky and the manifold advantage of unmanned aerial vehicle low-cost function, can realize that regional investigation strikes, operational capacities such as quick response.
Description
Technical Field
The utility model belongs to the technical field of the pneumatic design of aircraft totality, specifically be an aircraft of different structure combination of airship and low-cost unmanned aerial vehicle.
Background
The stratospheric airship provides static lift force by means of buoyancy lift gas, operates and flies by means of a propulsion system and a control system, and can achieve a state of long-term work by means of solar energy in a closed-loop mode; the stratospheric airship can make up the blank of the current air-to-sky field in battle, perfect an air-to-sky integrated battle system, realize all-time and all-weather observation of key and peripheral hot spot areas in China by carrying loads such as visible light, infrared light, hyperspectrum, laser and microwave, and effectively improve the capabilities of reconnaissance and monitoring, target reconnaissance and positioning, attack effect evaluation, area early warning and detection and the like in the battlefield of our army. The stratospheric airship has moderate altitude, and can realize communication relay in areas such as plateau mountain areas and the like. The unmanned aerial vehicle is a low-cost, multi-functional aircraft, divide into low-speed unmanned aerial vehicle, high-speed unmanned aerial vehicle and supersonic speed unmanned aerial vehicle according to the mission of fighting of difference, can divide into fixed wing unmanned aerial vehicle, tailless all-wing aircraft, variant aircraft etc. again according to the overall arrangement characteristics. With the development of high technology such as computer technology, autopilot technology, material technology, information technology, artificial intelligence and the like, the function and intelligence level of the unmanned aerial vehicle is gradually improved, and the unmanned aerial vehicle is more and more widely applied in the civil and military fields. The small and medium-sized unmanned aerial vehicles are generally limited in range and flight time, small in combat radius and high in requirements for take-off and landing sites. The requirement of future operation to the aircraft is higher and higher, not only needs long endurance long voyage range, still will satisfy nimble changeable, the purpose of immediate response, consequently considers the respective advantage of dirigible and unmanned aerial vehicle, and this patent provides a new concept aircraft with the heterogeneous combination of high altitude long endurance dirigible and low-cost unmanned aerial vehicle.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an aircraft of different structure combination of dirigible and low-cost unmanned aerial vehicle to satisfy the long-term long-range voyage distance of aircraft in the modern war, nimble changeable, the requirement of immediate response.
In order to achieve the above purpose, the utility model provides a following technical scheme:
the utility model provides an aircraft of different structure combination of airship and unmanned aerial vehicle, includes stratospheric airship and a plurality of unmanned aerial vehicle, the stratospheric airship includes outer covering, main gasbag, preceding ballonet, well ballonet, back ballonet, fin, structure skeleton, structure nacelle and propulsion system, propulsion system is including the three motor screw who distributes in stratospheric airship both sides and afterbody, the main gasbag is filled with helium and provides buoyancy, and three ballonets are filled with the air and realize the buoyancy and balance and the gesture adjustment, unmanned aerial vehicle hangs the belly of stratospheric airship or buries the structure nacelle at the stratospheric airship.
Preferably, the structural framework comprises a longitudinal pull rod and a plurality of stiffening rings, four inclined supports are connected to intersection points of the stiffening ring and the longitudinal pull rod in the middle of the structural framework, free ends of the four inclined supports are connected with the same L-shaped fixed support, and motor propellers on two sides of the stratospheric airship are respectively connected with the L-shaped fixed support on the same side.
Preferably, a solar cell is attached to the top of the stratospheric airship, an energy storage battery is installed in a nacelle of the stratospheric airship, the solar cell and the motor propeller are electrically connected with the energy storage battery, and the unmanned aerial vehicle can be charged through the energy storage battery.
Preferably, the length of the stratospheric airship is 100-250 m, and the slenderness ratio of the stratospheric airship is 2.5-4.
Preferably, the empennage of the stratospheric airship is designed in an inverted Y shape.
Preferably, the stratospheric airship is provided with a communication module connected with the unmanned aerial vehicle.
Adopt above-mentioned technical scheme, the utility model discloses the application has following beneficial effect:
(1) the airship has large load capacity, long air-leaving time and wide coverage range, and realizes long-term standby in the air;
(2) the airship provides static lift force by means of buoyancy lift gas, and solar energy is used as an energy source of the airship body, so that the airship has the advantages of low energy consumption and the like;
(3) the airship can realize the return and the return in the air, can be repeatedly used, and is convenient for load replacement and maintenance;
(4) the airship is of an inflatable flexible structure, and the airship capsule is made of composite materials mostly, so that the airship is low in detectability and good in stealth performance;
(5) the parking height of the airship exceeds the attack range of the existing fighter and the conventional air defense missile, and the airship has stronger survivability;
specifically, the utility model discloses the application has highly fused the respective advantage of airship and unmanned aerial vehicle, utilizes the heavy load of airship can realize carrying many unmanned aerial vehicles simultaneously and rises to the air, because the airship does not need to consume extra fuel that rises to the air, can also practice thrift unmanned aerial vehicle owing to take off the energy of consumption, improves unmanned aerial vehicle's range and time of sailing. The unmanned aerial vehicle is thrown in through the high altitude and the gravitational potential energy that the airship high altitude brought also can be utilized, and the process of unmanned aerial vehicle release also is the process of converting gravitational potential energy into kinetic energy, can improve unmanned aerial vehicle's radius of battle and flight time. The stratospheric airship can utilize solar energy to realize day and night energy closed loop, so that the airship carrying the unmanned aerial vehicle can realize long-term standing-in-the-air standby at any time, and timely response can be realized once a demand exists. The stratospheric airship has moderate altitude, can realize low-resolution detection and communication, and particularly provides high-performance communication navigation service for the unmanned aerial vehicle in plateau mountain areas and other areas. The unmanned aerial vehicle is carried to the high altitude through the airship and has sufficient gravitational potential energy, and once local conflict occurs in an area, the unmanned aerial vehicle can quickly respond to a mode of converting gravitational potential energy into kinetic energy to realize a long-range investigation and striking task. Consequently combination make full use of airship and unmanned aerial vehicle the airship high altitude is long-term to be parked empty and the manifold advantage of unmanned aerial vehicle low-cost function, and aircraft operational capability after the combination obviously increases, can realize that regional investigation strikes, operational capability such as quick response, has effectively promoted current unmanned aerial vehicle's function.
Drawings
Fig. 1 is a schematic structural view of an aircraft with an airship and an unmanned aerial vehicle combined in a heterogeneous manner, the unmanned aerial vehicle being mounted by a hook according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of an aircraft with an airship and an unmanned aerial vehicle heterogeneous combination, which is provided by the embodiment of the present invention, for mounting an unmanned aerial vehicle by using a structural pod;
fig. 3 is a schematic structural diagram of the inclined bracket and the L-shaped fixing bracket.
Detailed Description
The invention will be described in further detail with reference to the following drawings and embodiments:
reference numerals in the drawings of the specification include: the unmanned aerial vehicle comprises a main airbag 1, an unmanned aerial vehicle 2, a front auxiliary airbag 3, a middle auxiliary airbag 4, a rear auxiliary airbag 5, an empennage 6, a structural nacelle 7, a motor propeller 8, a longitudinal pull rod 9, a stiffening ring 10, an inclined bracket 11 and an L-shaped fixed bracket 12.
As shown in fig. 1 and fig. 2, an aircraft with an airship and an unmanned aerial vehicle combined in a heterogeneous manner comprises a stratospheric airship and a plurality of unmanned aerial vehicles 2, the stratospheric airship comprises an outer skin, a main airbag 1, a front auxiliary airbag 3, a middle auxiliary airbag 4, a rear auxiliary airbag 5, an empennage 6, a structural framework, a structural nacelle 7 and a propulsion system, the empennage 6 of the stratospheric airship adopts an inverted 'Y' type design and is mainly used for realizing the longitudinal and transverse direction stable control of the stratospheric airship, the propulsion system comprises three motor propellers 8 distributed at two sides and at the tail of the stratospheric airship, the main airbag 1 is filled with helium to provide buoyancy, the front auxiliary airbag 3, the middle auxiliary airbag 4 and the rear auxiliary airbag 5 are filled with air to realize the posture adjustment and the floating weight balance of the airship, the three auxiliary airbags are mainly used for adjusting the standing height of the airship by exhausting air and absorbing air, the unmanned aerial vehicles 2 are hung on the belly of the stratospheric airship by a hook or buried in the structural nacelle 7 of the stratospheric airship, when the size of unmanned aerial vehicle 2 is 3-5m, can realize about 20 small-size unmanned aerial vehicle 2's carry and put in through the inside loading of structure nacelle 7, unmanned aerial vehicle 2 is placed inside different structure nacelles 7, when unmanned aerial vehicle 2's size is great, directly carries unmanned aerial vehicle 2 in the belly of airship through the couple for unmanned aerial vehicle 2's size does not receive the constraint of structure nacelle 7. Many unmanned aerial vehicle 2 can be put in simultaneously to the stratospheric airship, forms 2 clusters of unmanned aerial vehicle, and unmanned aerial vehicle 2 adopts independently flight mode to form formation flight, and unmanned aerial vehicle 2 includes fixed wing unmanned aerial vehicle, solar energy unmanned aerial vehicle and variant unmanned aerial vehicle etc..
As shown in fig. 3, the structural framework comprises a longitudinal pull rod 9 and a plurality of stiffening rings 10, four inclined brackets 11 are connected to the intersection point of one stiffening ring 10 in the middle of the structural framework and the longitudinal pull rod 9, the free ends of the four inclined brackets 11 are connected with the same L-shaped fixed bracket 12, motor propellers 8 on two sides of the stratospheric airship are respectively connected with the L-shaped fixed bracket 12 on the same side, the motor propellers 8 are arranged on two sides of the stratospheric airship, and the structure is fixed, so that the stratospheric airship is flexible to steer, stable to stay in the air, and firm in structure.
The top of stratospheric airship is pasted with solar cells, energy storage batteries are installed in the nacelle of the stratospheric airship, the solar cells and the motor propeller 8 are electrically connected with the energy storage batteries, and the unmanned aerial vehicle 2 can be charged through the energy storage batteries. The solar cell supplies power to the propulsion system and the equipment at the same time in daytime, redundant energy is stored in the energy storage battery at the same time, and the energy storage battery works at night to provide energy for the airship.
Be equipped with the communication module of being connected with unmanned aerial vehicle 2 on the stratospheric airship, stratospheric airship 2 can provide services such as reconnaissance and supervision, target reconnaissance location, regional early warning detection for unmanned aerial vehicle, can act as the relay platform of 2 flight communication of unmanned aerial vehicle.
The length of the stratospheric airship is 100-250 m, and the slenderness ratio of the stratospheric airship is 2.5-4.
The stratospheric airship can realize 17-22km of high-altitude residence and can realize wind resistance of not less than 10 m/s.
If the flying height of the airship is 20km, the designed length of the airship is about 120m, and the weight of the unmanned aerial vehicle 2 loaded is about 100kg, the unmanned aerial vehicle 2 satisfies the following energy relation during the unpowered gliding process:
where v is the flight speed of the aircraft, h0Is the initial altitude of the aircraft, h is the altitude at which the aircraft is located, EdragThe energy consumed for the resistance of the aircraft during descent. Add and descend 20% that in-process resistance consumption is gravity, so unmanned aerial vehicle 2 relies on the speed increment that decline glide can obtain to be about 500 m/s's speed, consequently as long as structural strength can satisfy the requirement, the form that adopts the dirigible to put in can the energy saving, improve unmanned aerial vehicle's the radius of combat, realizes improving by a wide margin of unmanned aerial vehicle combat effect.
The stratospheric airship of the embodiment adopts a low-resistance NPL shape design, and the shape equation adopts the following form:
the hull volume is estimated using the following relationship:
the slenderness ratio of the airship is calculated by adopting the following relational expression:
the resistance of the airship is mainly generated by a hull, and the resistance coefficient of the hull is estimated by adopting the following formula:
in the formulae (1), (2), (3) and (4)Where a denotes the longer half axis of the front half of the airship, b denotes the shorter half axis, a2 denotes the longer half axis of the rear half of the airship, a1 is a,
The front half ellipsoid and the rear half ellipsoid adopt the same short half shaft. x is the coordinate of the length direction of the airship profile, y is the coordinate of the height direction of the airship profile, l is the total length of the airship, l is a1+ a2, d is the diameter of the airship, f is the slenderness ratio, Re is the Reynolds number, and the characteristic length is 1/3 times the hull volume. The drag coefficient of the entire boat, taking into account fin and other component interference, etc., can be modified as follows:
Cd,t＝1.5Cd,b (5)
wherein C isd,bAssuming that the main air bag of the airship keeps the volume unchanged during ascending, the buoyancy generated by the air of the airship at different heights can be calculated by adopting the following formula,
Ff＝ρgV
the load capacity of the airship is calculated by the following formula,
mload＝ρV-ρairVair-ρheVhe-mbody
where ρ V is the buoyancy generated by the air at the altitude of flight, ρairVairIs the air quality inside the hull, ρheVheIs the mass of helium, mbodyThe weight of the airship mechanism. ρ represents the air density at flight altitude, ρairRefers to the density of the air within the capsule.
The resistance of the airship flying at high altitude is calculated by the following formula,
wherein V is the hull volume of the airship, V is the flying speed or wind resistance speed of the airship, rho is the atmospheric density corresponding to the flying height, CDThe drag coefficient of an airship is usually estimated by engineering, a numerical modelSimulating or obtaining by a wind tunnel test.
When the airship needs to be balanced by full thrust and resistance during the process of parking or constant-speed cruising, the thrust generated by the propeller should be satisfied,
Tprop＝FD
the thrust generated by the propulsion system is calculated using the following formula,
Tprop＝N·CTρairn2D4
in the formula, CTIn order to evaluate the thrust coefficient of the propeller under the working condition, n is the rotation speed of the propeller per second, D is the diameter of the propeller, rhoairThe density of the ambient atmosphere is N, and N is the number of the propulsion units of the propulsion subsystem.
The propulsion system power may be derived from the design parameters of the propulsion system:
P＝CPρairn3D5/ηreducer/ηmotor
in the formula, CPIn order to evaluate the power coefficient of the propeller under the working condition, n is the rotating speed of the propeller per second, D is the diameter of the propeller, rhoairIs the ambient atmospheric density, ηreducerFor the efficiency of the speed reducer, ηmotorTo the motor efficiency.
The above description is only an example of the present invention, and the detailed technical solutions and/or characteristics known in the solutions are not described too much here. It should be noted that, for those skilled in the art, without departing from the technical solution of the present invention, several modifications and improvements can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (6)
1. The utility model provides an aircraft of different structure combination of dirigible and unmanned aerial vehicle which characterized in that: the airship comprises an outer skin, a main airbag, a front auxiliary airbag, a middle auxiliary airbag, a rear auxiliary airbag, an empennage, a structural framework, a structural nacelle and a propulsion system, wherein the propulsion system comprises three motor propellers distributed on two sides and the tail of the airship on the stratosphere, the main airbag is filled with helium to provide buoyancy, the three auxiliary airbags are filled with air to realize buoyancy balance and posture adjustment, and the unmanned aerial vehicle is hung on the belly of the airship on the stratosphere or is buried in the structural nacelle of the airship on the stratosphere.
2. The aircraft of claim 1, wherein the aircraft comprises a combination of an airship and a drone, and wherein: the structure skeleton includes vertical pull rod and a plurality of stiffening ring, the nodical department of a stiffening ring at structure skeleton middle part and vertical pull rod is connected with four bracess, and the free end of four bracess is connected with same L type fixed bolster, the motor screw of stratospheric airship both sides is connected with the L type fixed bolster of homonymy respectively.
3. The aircraft of claim 1, wherein the aircraft comprises a combination of an airship and a drone, and wherein: the solar cell is pasted on the top of the stratospheric airship, the energy storage battery is installed in the nacelle of the stratospheric airship, the solar cell and the motor propeller are both electrically connected with the energy storage battery, and the unmanned aerial vehicle can be charged through the energy storage battery.
4. The aircraft of claim 1, wherein the aircraft comprises a combination of an airship and a drone, and wherein: the length of the stratospheric airship is 100-250 m, and the slenderness ratio of the stratospheric airship is 2.5-4.
5. The aircraft of claim 1, wherein the aircraft comprises a combination of an airship and a drone, and wherein: the empennage of the stratospheric airship is designed in an inverted Y shape.
6. The aircraft of claim 1, wherein the aircraft comprises a combination of an airship and a drone, and wherein: and the stratospheric airship is provided with a communication module connected with the unmanned aerial vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120734525.3U CN216834240U (en) | 2021-04-12 | 2021-04-12 | Aircraft of different structure combination of airship and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120734525.3U CN216834240U (en) | 2021-04-12 | 2021-04-12 | Aircraft of different structure combination of airship and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216834240U true CN216834240U (en) | 2022-06-28 |
Family
ID=82083260
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120734525.3U Active CN216834240U (en) | 2021-04-12 | 2021-04-12 | Aircraft of different structure combination of airship and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216834240U (en) |
-
2021
- 2021-04-12 CN CN202120734525.3U patent/CN216834240U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113086154A (en) | Aircraft of different structure combination of airship and unmanned aerial vehicle | |
| US9169014B2 (en) | Unmanned aerial vehicle and method of launching | |
| US7093789B2 (en) | Delta-winged hybrid airship | |
| US6581873B2 (en) | Hybrid winged airship (dynastat) | |
| US7137592B2 (en) | High-aspect ratio hybrid airship | |
| CN100577511C (en) | Variant type sky airship | |
| CN108688803A (en) | It is a kind of can VTOL aircraft | |
| CN105358428B (en) | Hybrid power VTOL delivery vehicle | |
| JPH06199290A (en) | Semihard long flight type airship using hydrogen | |
| Ilieva et al. | A critical review of propulsion concepts for modern airships | |
| CN104925243B (en) | A kind of variable inflated type buoyance lift integration stratospheric airship of span | |
| JP2000280989A (en) | Super-pressure type high altitude airship | |
| CN104943864A (en) | Long-airborne-period combined stratosphere aircraft system scheme based on solar unmanned aerial vehicles | |
| CN106628099A (en) | Tethered and autonomous flight dual-purpose solar aerostat | |
| CN102717887A (en) | Near space airship using inflatable wings and tiltable propellers | |
| CN104960657A (en) | Combined-separate stratospheric aircraft system scheme | |
| CN112173060A (en) | Stratospheric airship with pressure maintaining device | |
| CN102910280A (en) | Aerodynamic configuration for buoyancy-lifting vehicle in near-space | |
| CN110979625A (en) | Load airship with four-vector duct | |
| CN216834240U (en) | Aircraft of different structure combination of airship and unmanned aerial vehicle | |
| CN114030585A (en) | High-attendance-rate stratospheric airship comprehensive flight layout | |
| CN211253081U (en) | Spiral flying arrow | |
| CN115867484A (en) | Tactical mixed stratospheric airship | |
| JPH05201390A (en) | Airship | |
| Hochstetler | Airships ahoy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |