CN114212238A - High-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings - Google Patents
High-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings Download PDFInfo
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- CN114212238A CN114212238A CN202111669416.9A CN202111669416A CN114212238A CN 114212238 A CN114212238 A CN 114212238A CN 202111669416 A CN202111669416 A CN 202111669416A CN 114212238 A CN114212238 A CN 114212238A
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- 238000007906 compression Methods 0.000 claims description 6
- 238000012423 maintenance Methods 0.000 abstract description 4
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- 238000010168 coupling process Methods 0.000 description 6
- 238000005859 coupling reaction Methods 0.000 description 6
- 230000008859 change Effects 0.000 description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/28—Collapsible or foldable blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/04—Ground or aircraft-carrier-deck installations for launching aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model provides an unmanned aerial vehicle during high altitude long endurance with collapsible flexible wing, it relates to the aeronautical technical field. The invention aims to solve the problems that the existing unmanned aerial vehicle at high altitude and long voyage has overlarge wingspan, occupies overlarge space during transportation and storage, has high maintenance cost and is difficult to deploy quickly. The invention comprises a fuselage, two front folding wings, two rear folding wings, two front telescopic wings, two rear telescopic wings, two folding empennages, two folding propeller blades, a plurality of folding mechanisms and a plurality of telescopic mechanisms, wherein the two sides of the front end of the belly of the fuselage are respectively and symmetrically provided with one front folding wing, the outer side end of each front folding wing is inserted with one front telescopic wing, the two sides of the rear end of the top of the fuselage are respectively and symmetrically provided with one rear folding wing, the outer side end of each rear folding wing is inserted with one rear telescopic wing, the two sides of the rear part of the fuselage are respectively and symmetrically provided with one folding empennage, and the tail part of the fuselage is symmetrically provided with two folding propeller blades. The invention is used for the high-altitude long-endurance unmanned aerial vehicle.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to an unmanned aerial vehicle with foldable telescopic wings for high altitude and long endurance.
Background
The high-altitude long-endurance unmanned aerial vehicle has good aerodynamic performance and good fuel economy, is suitable for long-time reconnaissance and monitoring tasks at high altitude, and can be used as an unmanned combat platform, so that the high-altitude long-endurance unmanned aerial vehicle is required to have the characteristics of quick deployment, convenience in maintenance, low running cost and the like. However, the general high-altitude long-endurance unmanned aerial vehicle has a long wingspan and a large wing area, which results in overlarge occupied space of the unmanned aerial vehicle during transportation and storage, increases the difficulty of ground maintenance and transportation, improves the operation cost, and is difficult to deploy quickly.
In order to solve the problem, the mode of wing folding deformation is considered, so that the unmanned aerial vehicle can be folded and placed in the circular launching tube during high-altitude long-endurance, the occupied size is small, the unmanned aerial vehicle is convenient to store and transport, more importantly, the unmanned aerial vehicle can be launched in a shooting or high-altitude launching mode, the unmanned aerial vehicle can quickly reach an appointed task area, the unmanned aerial vehicle can be launched at a proper time, and tactical selectivity is increased. However, the conventional single wing folding mode is difficult to fold the unmanned aerial vehicle with a large span and a large wing area into the cylindrical launcher, and the mode of combining multiple folding modes occupies too much limited space of the fuselage, and the wing folding mechanism is complex and is not easy to arrange. Therefore, a folding and unfolding system suitable for the large-wingspan wings of the unmanned aerial vehicle during high-altitude long-endurance flight needs to be designed.
Disclosure of Invention
The invention provides an unmanned aerial vehicle with foldable telescopic wings, which can change the wing extension length of the unmanned aerial vehicle during storage and transportation, can be folded and folded into a circular launching tube in a wing folding and telescopic mode on the premise of ensuring enough wing area of the unmanned aerial vehicle during high-altitude long voyage, not only reduces the occupied volume and is convenient to store and transport, but also can rapidly deploy the unmanned aerial vehicle in a shot shooting or high-altitude throwing mode, and can launch the unmanned aerial vehicle at a proper time.
The technical scheme adopted by the invention for solving the technical problems is as follows:
an unmanned aerial vehicle with foldable telescopic wings for long-term high altitude navigation comprises a fuselage, two front folding wings, two rear folding wings, two front telescopic wings, two rear telescopic wings, two folding tail wings, two folding propeller blades, a plurality of folding mechanisms and a plurality of telescopic mechanisms, wherein the two sides of the front end of the belly of the fuselage are respectively and symmetrically provided with one front folding wing, the outer side end of the front folding wing is inserted with one front telescopic wing, the two sides of the rear end of the top of the fuselage are respectively and symmetrically provided with one rear folding wing, the outer side end of the rear folding wing is inserted with one rear telescopic wing, the two sides of the rear part of the fuselage are respectively and symmetrically provided with one folding tail wing, the tail part of the fuselage is symmetrically provided with two folding propeller blades,
the front folding wing, the rear folding wing and the folding tail wing are respectively connected with the machine body through a folding mechanism, and the folding propeller blades are connected with the machine body through a hinge; when the folding propeller is folded, the front folding wings, the rear folding wings and the folding tail wings are arranged along the length direction of the fuselage, the front folding wings are respectively and closely attached to the ventral positions of two sides of the fuselage, the rear folding wings are stacked on the top of the fuselage, the folding tail wings are respectively and closely attached to two sides of the rear part of the fuselage, and the folding propeller blades are respectively and closely attached to two sides of the tail part of the fuselage; when the foldable propeller is unfolded, the front foldable wing, the rear foldable wing and the foldable propeller blades are respectively arranged along the length direction which is horizontally vertical to the fuselage, and the foldable tail wings are respectively arranged along the length direction which is vertically downward vertical to the fuselage.
Further, folding mechanism includes the spring hook, extension spring, the steel wire, the pulley, the round hole axle bed, semicircle orifice axle bed and pivot, the spring hook, the pulley, the round hole axle bed, the equal rigid coupling of semicircle orifice axle bed on the fuselage, the medial extremity cartridge of pivot is on the round hole axle bed, the outside end cartridge of pivot is on the semicircle orifice axle bed, and the pivot rotates with round hole axle bed and semicircle orifice axle bed to be connected, the one end rigid coupling of steel wire is on the lateral wall of pivot, the other end of steel wire is walked around behind the pulley and is connected with extension spring's one end, the other end rigid coupling of spring is on the spring hook, preceding folding wing, back folding wing, the root of folding fin respectively with the lateral wall rigid coupling of corresponding folding mechanism mesosphere of pivot.
Furthermore, the folding mechanism further comprises a shaft cover which is fixedly connected to the semicircular hole shaft seat to form a complete circular hole shaft seat which is rotatably connected with the outer side end of the rotating shaft.
Furthermore, a U-shaped groove is formed in the side wall of the rotating shaft along the circumferential direction, and the steel wire is wound in the U-shaped groove.
Further, one side rigid coupling in the U type groove has the wedge, and the tip rigid coupling of steel wire one end is on the wedge.
Furthermore, a locking mechanism is arranged between the folding mechanism and the machine body, the locking mechanism comprises a lock pin, a lock pin spring and a lock pin hole, the lock pin hole is formed in the side wall of the rotating shaft, the lock pin is embedded in the machine body, the lock pin spring is fixedly connected between the machine body and the lock pin, and the position of the lock pin hole corresponds to the position of the lock pin.
Furthermore, in the two folding mechanisms corresponding to the rear folding wings, the rotating shaft is a hollow shaft, and the rotating shaft of the rear folding wing on the left side of the body is inserted into the rotating shaft of the rear folding wing on the right side of the body.
Furthermore, the outer side end faces of the front folding wing and the rear folding wing are respectively provided with a slot, and the roots of the front telescopic wing and the rear telescopic wing are respectively inserted into the slots.
Furthermore, the telescopic mechanism comprises a linkage rope, a compression spring, a fixed rod, a sliding rod, a steel wire rope, a limiting pin and a guide wheel, the roots of the front telescopic wing and the rear telescopic wing are respectively and fixedly connected with one end of the linkage rope in the corresponding telescopic mechanism, the other end of the linkage rope is connected with the fixed mechanism of the machine body, the slot bottoms of the slots of the front folding wing and the rear folding wing are respectively and fixedly connected with one end of the fixed rod in the corresponding telescopic mechanism, the other end of the fixed rod is inserted into one end of the sliding rod, the compression spring is arranged between one end of the sliding rod and the slot bottom of the slot, the other end of the sliding rod extends into the corresponding front telescopic wing or the rear telescopic wing, the limiting pin is vertically and fixedly connected inside the other end of the fixed rod, two sides of the other end of the sliding rod are respectively provided with a guide wheel, one side of the roots of the front telescopic wing and the rear telescopic wing are respectively and fixedly connected with one end of the steel wire rope in the corresponding telescopic mechanism, the other end of the steel wire rope sequentially rounds the guide wheel and the limiting pin on one side of the other end of the sliding rod and is fixedly connected to the other side of the root of the corresponding front telescopic wing or the rear telescopic wing.
Furthermore, a linkage mechanism is respectively arranged between the front folding wing and the front telescopic wing and between the rear folding wing and the rear telescopic wing.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention adopts a mode of combining wing folding and contraction to fold and place the unmanned aerial vehicle with large wingspan and large wing area in the circular launching tube during high-altitude long-endurance, thereby reducing the occupied volume of the unmanned aerial vehicle, facilitating storage and transportation and reducing the risk of discovery.
2. The high-altitude long-endurance unmanned aerial vehicle provided by the invention can be launched in a gun shooting or high-altitude throwing mode, so that the rapid deployment of the high-altitude long-endurance unmanned aerial vehicle is realized, and the unmanned aerial vehicle can be launched at a proper time.
3. The invention determines the direction vector of the rotating shaft of the folding wing in a coordinate conversion mode, and realizes that the folding wing can reach a straight working state only by rotating a certain angle around a single shaft from a position (non-horizontal state) attached to the belly.
4. The pair of front wings are respectively attached to two sides of the triangular section of the belly of the machine body when being folded, so that the space utilization rate of the circular launching tube is improved, and the available space of the machine body is also increased.
5. The invention adopts the layout of the series wings, and can reduce the chord length of a single wing on the premise of ensuring the enough wing area and the load capacity of the unmanned aerial vehicle, thereby reducing the strength requirements of the folding structure and the telescopic structure of the unmanned aerial vehicle.
6. The passive wing folding and telescoping mechanism adopted by the invention has the advantages of simple structure, high reliability, no influence of high altitude and low temperature, convenient installation, light weight, convenient maintenance and low cost.
7. The wing folding mechanism utilizes the pulley to change the direction of the drawing force, so that the driving part can select a proper installation position according to the internal space of the airplane body, the requirement on the installation space is reduced, and the position layout of other parts in the airplane body is facilitated.
Drawings
Figure 1 is an isometric view of the overall structure of the drone of the present invention when fully deployed and extended;
fig. 2 is an isometric view of the overall structure of the folded wing of the drone of the invention when the extended telescopic wing is not extended;
figure 3 is an isometric view of the overall structure of the drone of the present invention when fully collapsed;
FIG. 4 is a front view of the overall structure of the unmanned aerial vehicle of the present invention after being loaded into the launch canister 6 when fully collapsed;
FIG. 5 is a sectional view taken along line A-A in FIG. 4;
FIG. 6 is a schematic view of a folding mechanism of the present invention;
FIG. 7 is a top view of FIG. 6;
fig. 8 is a schematic view of the folding wings of the drone of the present invention in an intermediate state during folding to unfolding;
FIG. 9 is a front view of FIG. 8;
FIG. 10 is a cross-sectional view of the folding mechanism of the present invention;
FIG. 11 is a cross-sectional view of the locking mechanism of the present invention;
FIG. 12 is a sectional view of the front telescopic wing 3-a and the front folding wing 2-a when the front telescopic wing 3-a is extended in the present invention;
fig. 13 is a partial enlarged view at B in fig. 12;
FIG. 14 is a sectional view of the front telescopic wing 3-a and the front folding wing 2-a when the front telescopic wing 3-a is contracted in the present invention;
FIG. 15 is an enlarged view of a portion of FIG. 14 at D;
fig. 16 is a partial enlarged view at E in fig. 14.
Detailed Description
The first embodiment is as follows: the embodiment is described with reference to fig. 1 to 16, and the high-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings in the embodiment comprises a fuselage 1, two front folding wings 2-a, two rear folding wings 2-b, two front telescopic wings 3-a, two rear telescopic wings 3-b, two folding empennages 4, two folding propeller blades 5, a plurality of folding mechanisms and a plurality of telescopic mechanisms, wherein two sides of the front part of the fuselage 1 are respectively and symmetrically provided with one front folding wing 2-a, the outer side end of the front folding wing 2-a is inserted with the front telescopic wing 3-a, two sides of the top end of the rear part of the fuselage 1 are respectively and symmetrically provided with one rear folding wing 2-b, the outer side end of the rear folding wing 2-b is inserted with the rear telescopic wing 3-b, two sides of the rear part of the fuselage 1 are respectively and symmetrically provided with one empennage folding empennage 4, the tail part of the machine body 1 is symmetrically provided with two folding propeller blades 5,
the front folding wing 2-a, the rear folding wing 2-b and the folding tail wing 4 are respectively connected with the machine body 1 through a folding mechanism, and the folding propeller blades 5 are connected with the machine body 1 through hinges; when the folding aircraft is folded, the front folding wings 2-a, the rear folding wings 2-b and the folding tail wings 4 are arranged along the length direction of the aircraft body 1, the front folding wings 2-a are respectively and closely attached to the ventral positions at two sides of the aircraft body 1, the rear folding wings 2-b are stacked on the top of the aircraft body 1, the folding tail wings 4 are respectively and closely attached to two sides of the rear part of the aircraft body 1, and the folding propeller blades 5 are respectively and closely attached to two sides of the tail part of the aircraft body 1; when the foldable airplane is unfolded, the front foldable wing 2-a, the rear foldable wing 2-b and the foldable propeller blades 5 are respectively arranged along the length direction which is horizontally vertical to the airplane body 1, and the foldable tail wings 4 are respectively arranged along the length direction which is vertically downward vertical to the airplane body 1.
When the folding wing is unfolded, the front folding wing 2-a rotates a certain angle from the position attached to the belly to enable the front folding wing 2-a to rotate to a straight unfolding state, and the rear folding wing 2-b horizontally rotates ninety degrees from the top of the machine body 1 to enable the rear folding wing 2-b to rotate to a straight unfolding state. Folding screw paddle 5 is installed at 1 afterbody of fuselage, and 1 afterbody of fuselage embeds the motor, and folding screw paddle 5 takes the action to expand with rotatory down at the motor to for unmanned aerial vehicle provides flight power.
The unmanned aerial vehicle after folding can be packed into launch canister 6. Folding screw paddle 5 can make unmanned aerial vehicle possess great paddle and provide power, does not influence unmanned aerial vehicle the launch canister 6 of packing into occasionally.
The second embodiment is as follows: the embodiment is described with reference to fig. 1 to 16, the folding mechanism of the embodiment includes a spring hook 7, an extension spring 8, a steel wire 9, a pulley 10, a circular hole axle seat 11-a, a semicircular hole axle seat 11-b and a rotating shaft 16, the spring hook 7, the pulley 10, the circular hole axle seat 11-a and the semicircular hole axle seat 11-b are all fixedly connected to the body 1, the inner end of the rotating shaft 16 is inserted into the circular hole axle seat 11-a, the outer end of the rotating shaft 16 is inserted into the semicircular hole axle seat 11-b, the rotating shaft 16 is rotatably connected with the circular hole axle seat 11-a and the semicircular hole axle seat 11-b, one end of the steel wire 9 is fixedly connected to the side wall of the rotating shaft 16, the other end of the steel wire 9 is connected with one end of the extension spring 8 after bypassing the pulley 10, the other end of the spring 8 is fixedly connected to the spring hook 7, a front folding wing 2-a, a rear folding wing 2-b, The root parts of the folding tail wings 4 are respectively fixedly connected with the side walls of the rotating shafts 16 in the corresponding folding mechanisms. Other components and connection modes are the same as those of the first embodiment.
When the folding wing is folded, the rotating shaft 16 is fixed in position through the folding locking mechanism in the machine body 1, the extension spring 8 is in a tensioned state at the moment, when the folding wing is unfolded, the folding locking mechanism loosens the fixing of the rotating shaft 16, the extension spring 8 retracts, the rotating shaft 16 rotates by pulling the steel wire 9, and then the front folding wing 2-a, the rear folding wing 2-b and the folding tail wing 4 rotate to the unfolded state, the rotating shaft 16 determines the rotating shaft direction according to the position when the folding wing is folded, the rotating shaft of the front folding wing is obliquely arranged, the rotating shaft of the rear folding wing is vertically arranged, and the rotating shaft of the folding tail wing is horizontally arranged, so that the front folding wing 2-a, the rear folding wing 2-b and the folding tail wing 4 respectively rotate to be unfolded to a set position.
And a rubber damping device is arranged at the position where the root of the front folding wing 2-a is contacted with the machine body 1 so as to reduce impact and collision vibration in the unfolding process. The device can ensure that the wings play a role in limiting and fixing when being unfolded and can not be damaged due to overlarge impact force.
The extension spring 8 can change the position and size according to actual requirements, so that the wing with larger mass can be unfolded.
The third concrete implementation mode: referring to fig. 1 to 16, the folding mechanism of the present embodiment further includes a shaft cover 12, wherein the shaft cover 12 is fixedly connected to the semi-circular shaft seat 11-b to form a complete circular shaft seat, which is rotatably connected to an outer end of the rotating shaft 16. Other components and connection modes are the same as those of the second embodiment.
The fourth concrete implementation mode: referring to fig. 1 to 16, the present embodiment is described, in which a U-shaped groove is formed in a side wall of the rotating shaft 16 along a circumferential direction, and the steel wire 9 is wound in the U-shaped groove. Other components and connection modes are the same as those of the third embodiment.
The design enables the steel wire 9 to move along the guide position of the U-shaped groove in the process of stretching the steel wire 9, and the steel wire 9 is prevented from sliding.
According to the rotating shaft 16 designed in the way, the steel wire 9 is wound in the groove, so that the force arms of the tension spring 8 for pulling the rotating shaft 16 to rotate are the same, and the elasticity of the tension spring 8 for pulling the wing to rotate is sufficient.
The fifth concrete implementation mode: referring to fig. 1 to 16, the embodiment is described, in which a wedge block 13 is fixed to one side of the U-shaped groove, and an end of one end of the steel wire 9 is fixed to the wedge block 13, so as to prevent the steel wire 9 from moving. The other components and the connection mode are the same as those of the fourth embodiment.
The sixth specific implementation mode: the present embodiment is described with reference to fig. 1 to 16, and a locking mechanism is provided between the folding mechanism and the main body 1 in the present embodiment, and includes a lock pin 14, a lock pin spring 15, and a lock pin hole, the lock pin hole is provided on a side wall of the rotating shaft 16, the lock pin 14 is embedded in the main body 1, the lock pin spring 15 is fixedly connected between the main body 1 and the lock pin 14, and the position of the lock pin hole corresponds to the position of the lock pin 14. Other components and connection modes are the same as those of the second embodiment.
The front wing shaft is provided with an end face which is contacted with the end faces of the semicircular hole shaft seat 11-b and the shaft cover 12, the end face is provided with three locking pin holes with the same diameter as the locking pins and used for the insertion of the locking pins, the locking pin holes on the end face are positioned at three positions with different radiuses on the end face by taking the shaft center as the circle center, and the locking pins on the shaft seat are in one-to-one correspondence with the mounting holes of the locking pin springs.
The locking mechanism with the design can ensure that only the lock pin on the radius corresponding to each lock pin hole can be inserted into each lock pin hole during rotation, the multi-lock-pin locking structure cannot enable the wings to be unfolded due to the fact that the wings are unfolded in a non-rotating mode and reach the appointed position and the individual lock pins are locked, and the strength of the locking structure can be improved.
The seventh embodiment: in the two folding mechanisms corresponding to the rear folding wings 2-b according to the present embodiment, the rotating shaft 16 is a hollow shaft, and the rotating shaft 16 of the left rear folding wing 2-6 of the body 1 is inserted into the rotating shaft 16 of the right rear folding wing 2-b of the body 1. Other compositions and connection modes are the same as those of the second, third, fourth, fifth or sixth embodiment.
The specific implementation mode is eight: referring to fig. 1 to 16, the embodiment is described, in which the outer end surfaces of the front folding wing 2-a and the rear folding wing 2-b are respectively provided with slots, and the root portions of the front telescopic wing 3-a and the rear telescopic wing 3-b are respectively inserted into the slots. Other components and connection modes are the same as those of the first embodiment.
The specific implementation method nine: the embodiment is described with reference to fig. 1 to 16, the telescopic mechanism of the embodiment includes a linkage rope 17, a compression spring 18, a fixing rod 19, a sliding rod 20, a wire rope 21, a limit pin 22 and a guide wheel 23, roots of a front telescopic wing 3-a and a rear telescopic wing 3-b are respectively fixedly connected with one end of the linkage rope 17 in the corresponding telescopic mechanism, the other end of the linkage rope 17 is connected with the fixing mechanism of the fuselage 1, groove bottoms of slots of the front folding wing 2-a and the rear folding wing 2-b are respectively fixedly connected with one end of the fixing rod 19 in the corresponding telescopic mechanism, the other end of the fixing rod 19 is inserted into one end of the sliding rod 20, the compression spring 18 is arranged between one end of the sliding rod 20 and the groove bottom of the slot, the other end of the sliding rod 20 extends to the inside of the corresponding front telescopic wing 3-a or rear telescopic wing 3-b, the limit pin 22 is vertically fixedly connected inside the other end of the fixing rod 19, two sides of the other end of the slide rod 20 are respectively provided with a guide wheel 23, one side of the root of the front telescopic wing 3-a and the rear telescopic wing 3-b is respectively fixedly connected with one end of a steel wire rope 21 in the corresponding telescopic mechanism, and the other end of the steel wire rope 21 sequentially bypasses the guide wheel 23 on one side of the other end of the slide rod 20, a limiting pin 22 and the guide wheel 23 on the other side of the other end of the slide rod 20 and is fixedly connected with the other side of the root of the corresponding front telescopic wing 3-a or the rear telescopic wing 3-b. The other components and connection modes are the same as those of the eighth embodiment.
At a proper time, the fixing mechanism shears the linkage rope 17 and can release the telescopic motion of the front telescopic wing 3-a or the rear telescopic wing 3-b.
The other end of the linkage rope 17 passes through the bottom of the slot and then is connected with the fixing mechanism to control the stretching time of the front telescopic wing 3-a or the rear telescopic wing 3-b.
The fixing mechanism can be an explosive bolt or an explosive pin, and controls the front telescopic wing 3-a or the rear telescopic wing 3-b to release when needed.
The detailed implementation mode is ten: the present embodiment is described with reference to fig. 1 to 16, and the linking mechanisms are respectively provided between the front folding wing 2-a and the front telescopic wing 3-a and between the rear folding wing 2-b and the rear telescopic wing 3-b. Other components and connection modes are the same as those of the first embodiment, the second embodiment, the third embodiment, the fourth embodiment, the fifth embodiment, the sixth embodiment, the eighth embodiment or the ninth embodiment.
After the wing of the folding machine is unfolded to a straight state, the linkage mechanism in the machine body is touched, the linkage mechanism cuts off the linkage rope, and the telescopic mechanism of the telescopic wing starts to work simultaneously.
Although the invention herein has been described with reference to particular embodiments, it is to be understood that these embodiments are merely illustrative of the principles and applications of the present invention. It is therefore to be understood that numerous modifications may be made to the illustrative embodiments and that other arrangements may be devised without departing from the spirit and scope of the present invention as defined by the appended claims. It should be understood that features described in different dependent claims and herein may be combined in ways different from those described in the original claims. It is also to be understood that features described in connection with individual embodiments may be used in other described embodiments.
Claims (10)
1. The utility model provides an unmanned aerial vehicle during high altitude long endurance with collapsible flexible wing which characterized in that: the folding aircraft comprises an aircraft body (1), two front folding wings (2-a), two rear folding wings (2-b), two front telescopic wings (3-a), two rear telescopic wings (3-b), two folding empennages (4), two folding propeller blades (5), a plurality of folding mechanisms and a plurality of telescopic mechanisms, wherein two sides of the front end of the abdomen of the aircraft body (1) are respectively and symmetrically provided with one front folding wing (2-a), the outer side end of the front folding wing (2-a) is inserted with one front telescopic wing (3-a), two sides of the rear end of the top of the aircraft body (1) are respectively and symmetrically provided with one rear folding wing (2-b), the outer side end of the rear folding wing (2-b) is inserted with one rear telescopic wing (3-b), two sides of the rear part of the aircraft body (1) are respectively and symmetrically provided with one folding empennage (4), the tail of the aircraft body (1) is symmetrically provided with two folding propeller blades (5),
the front folding wing (2-a), the rear folding wing (2-b) and the folding tail wing (4) are respectively connected with the machine body (1) through a folding mechanism, and the folding propeller blade (5) is connected with the machine body (1) through a hinge; when the folding aircraft is folded, the front folding wings (2-a), the rear folding wings (2-b) and the folding tail wings (4) are arranged along the length direction of the aircraft body (1), the front folding wings (2-a) are respectively and closely attached to the ventral positions of two sides of the aircraft body (1), the rear folding wings (2-b) are stacked on the top of the aircraft body (1), the folding tail wings (4) are respectively and closely attached to two sides of the rear part of the aircraft body (1), and the folding propeller blades (5) are respectively and closely attached to two sides of the tail part of the aircraft body (1); when the foldable propeller is unfolded, the front foldable wing (2-a), the rear foldable wing (2-b) and the foldable propeller blades (5) are respectively arranged along the length direction which is horizontally vertical to the machine body (1), and the foldable tail wings (4) are respectively arranged along the length direction which is vertically downward vertical to the machine body (1).
2. The high-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings as claimed in claim 1, wherein: the folding mechanism comprises a spring hook (7), an extension spring (8), a steel wire (9), a pulley (10), a round hole shaft seat (11-a), a semicircular hole shaft seat (11-b) and a rotating shaft (16), wherein the spring hook (7), the pulley (10), the round hole shaft seat (11-a) and the semicircular hole shaft seat (11-b) are fixedly connected on the machine body (1), the inner side end of the rotating shaft (16) is inserted on the round hole shaft seat (11-a), the outer side end of the rotating shaft (16) is inserted on the semicircular hole shaft seat (11-b), the rotating shaft (16) is rotatably connected with the round hole shaft seat (11-a) and the semicircular hole shaft seat (11-b), one end of the steel wire (9) is fixedly connected on the side wall of the rotating shaft (16), the other end of the steel wire (9) is connected with one end of the extension spring (8) after passing through the pulley (10), and the other end of the spring (8) is fixedly connected on the spring hook (7), the roots of the front folding wing (2-a), the rear folding wing (2-b) and the folding tail wing (4) are respectively fixedly connected with the side wall of the rotating shaft (16) in the corresponding folding mechanism.
3. The high-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings as claimed in claim 2, wherein: the folding mechanism further comprises a shaft cover (12), wherein the shaft cover (12) is fixedly connected to the semicircular hole shaft seat (11-b) to form a complete circular hole shaft seat which is rotatably connected with the outer side end of the rotating shaft (16).
4. The high-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings as claimed in claim 3, wherein: a U-shaped groove is formed in the side wall of the rotating shaft (16) along the circumferential direction, and the steel wire (9) is wound in the U-shaped groove.
5. The high-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings as claimed in claim 4, wherein: one side in the U-shaped groove is fixedly connected with a wedge block (13), and the end part of one end of the steel wire (9) is fixedly connected on the wedge block (13).
6. The high-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings as claimed in claim 2, wherein: a locking mechanism is arranged between the folding mechanism and the machine body (1), the locking mechanism comprises a lock pin (14), a lock pin spring (15) and a lock pin hole, the lock pin hole is formed in the side wall of the rotating shaft (16), the lock pin (14) is embedded in the machine body (1), the lock pin spring (15) is fixedly connected between the machine body (1) and the lock pin (14), and the position of the lock pin hole corresponds to the position of the lock pin (14).
7. High altitude long endurance drone with foldable telescopic wings according to claim 2, 3, 4, 5 or 6, characterized in that: in the two folding mechanisms corresponding to the rear folding wings (2-b), the rotating shaft (16) is a hollow shaft, and the rotating shaft (16) of the rear folding wing (2-6) on the left side of the machine body (1) is inserted into the rotating shaft (16) of the rear folding wing (2-b) on the right side of the machine body (1).
8. The high-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings as claimed in claim 1, wherein: the outer side end faces of the front folding wing (2-a) and the rear folding wing (2-b) are respectively provided with a slot, and the roots of the front telescopic wing (3-a) and the rear telescopic wing (3-b) are respectively inserted into the slots.
9. The high-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings as claimed in claim 8, wherein: the telescopic mechanism comprises a linkage rope (17), a compression spring (18), a fixed rod (19), a sliding rod (20), a steel wire rope (21), a limiting pin (22) and a guide wheel (23), the roots of a front telescopic wing (3-a) and a rear telescopic wing (3-b) are fixedly connected with one end of the linkage rope (17) in the corresponding telescopic mechanism respectively, the other end of the linkage rope (17) is connected with the fixed mechanism of the machine body (1), the slot bottoms of slots of the front folding wing (2-a) and the rear folding wing (2-b) are fixedly connected with one end of the fixed rod (19) in the corresponding telescopic mechanism respectively, the other end of the fixed rod (19) is inserted into one end of the sliding rod (20), the compression spring (18) is arranged between one end of the sliding rod (20) and the slot bottom of the slot, and the other end of the sliding rod (20) extends into the corresponding front telescopic wing (3-a) or rear telescopic wing (3-b), the limiting pin (22) is vertically and fixedly connected inside the other end of the fixed rod (19), two sides of the other end of the sliding rod (20) are respectively provided with a guide wheel (23), one side of the root of the front telescopic wing (3-a) and one side of the root of the rear telescopic wing (3-b) are respectively and fixedly connected with one end of a steel wire rope (21) in the corresponding telescopic mechanism, and the other end of the steel wire rope (21) sequentially bypasses the guide wheel (23) on one side of the other end of the sliding rod (20), the limiting pin (22) and the guide wheel (23) on the other side of the other end of the sliding rod (20) and is fixedly connected with the other side of the root of the corresponding front telescopic wing (3-a) or the rear telescopic wing (3-b).
10. A high altitude, long endurance drone with foldable telescopic wings according to claims 1, 2, 3, 4, 5, 6, 8 or 9, characterized in that: and linkage mechanisms are respectively arranged between the front folding wing (2-a) and the front telescopic wing (3-a) and between the rear folding wing (2-b) and the rear telescopic wing (3-b).
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