CN116022325A - Folding storage type variant aircraft - Google Patents

Abstract

The invention provides a foldable and stowable variant aircraft, comprising: a front fuselage, a rear fuselage, wings, an empennage, a propeller, an overturning mechanism and a barrel; wherein, the front fuselage and the rear fuselage are connected through an overturning mechanism ;The front fuselage fits with the rear fuselage after turning over 180 degrees; the wings are symmetrically placed on both sides of the turning mechanism, and the wings and the front fuselage are connected by oblique shafts. After the wings are rotated and folded, they align with the rear fuselage Parallel; the propeller is placed at the tail end of the rear fuselage, and the empennage is placed at the rear of the rear fuselage; the wing includes a plurality of wing sections; a wing folding device is arranged at the connection of each wing section of the wing, so that the span of the wing The chord direction has a multi-stage folding function; the aircraft is stored in the cylinder after being folded. The invention has the advantages of large wingspan, high lift-to-drag ratio, ultra-long flight time, fast long-distance delivery and the like.

Description

A foldable and stowable variant aircraft

technical field

The invention relates to a foldable and stowable variant aircraft, which belongs to the technical field of unmanned aerial vehicles.

Background technique

Traditional large-aspect-ratio fixed-wing aircraft need better airport support conditions to take off and land, and there are relatively strict requirements on climatic conditions, which affect the application effect of the aircraft. In order to improve the rapid maneuverability and all-weather standby ability of fixed-wing aircraft The aircraft needs to be folded and stored in a cylinder with a smaller diameter for easy portability and transportation. At present, the Massachusetts Institute of Technology and NASA's Draper Laboratory have jointly developed a wide-area reconnaissance and surveillance drone. After unfolding, the wingspan is 1.27m. Pin hinges allow folding to unfold. The FLYRT UAV developed by the U.S. Naval Research Center is a small UAV that can be launched by a ship-borne gun. The UAV has a wingspan of 5.5m and a fuselage length of 1.6m. Minutes after launch, the cross tail is controlled by spring ejection. After the solid rocket burns out, the aircraft discards the rocket propulsion components, the folding wings and the antenna unfold, and the UAV enters a fully working state driven by the motor. However, the wingspan of existing folding aircraft is relatively small, and the storage ratio is not high. Under such technical background, a foldable and stowable UAV is proposed.

Contents of the invention

The technical problem of the present invention is: to overcome the deficiencies of the prior art, and to provide a storage-type variant aircraft that can be used in combination with multiple folding methods, so that the aircraft can be stored in a smaller diameter and length according to a larger shrinkage ratio. Space, in order to facilitate the long-distance delivery and transportation of drones. The UAV folded in this way has the advantages of large wingspan, high lift-to-drag ratio, ultra-long endurance, and fast long-distance delivery.

Technical solution of the present invention is:

A foldable and stowable variant aircraft, comprising: a front fuselage, a rear fuselage, wings, an empennage, a propeller, an overturning mechanism, and a barrel; wherein, the front fuselage and the rear fuselage are connected by an overturning mechanism; After being turned over, it fits the rear fuselage; the wings are symmetrically placed on both sides of the turning mechanism, and the wings are connected to the front fuselage by an oblique shaft. After the wings are rotated and folded, they are parallel to the axis of the rear fuselage; the propeller is placed behind At the tail end of the fuselage, the empennage is placed at the rear of the rear fuselage; the wing includes multiple wing sections; a wing folding device is installed at the connection of each wing section of the wing, so that the spanwise and chord directions of the wing have multi-section folding functions ; The aircraft is folded and stored in the cylinder.

In the above variant aircraft, the wing folding device includes a wing hinge, an actuating device and a locking device to realize v-shaped, z-shaped, w-shaped folding.

In the above variant aircraft, each wing section is composed of a leading edge, a wing box and a trailing edge, and the leading edge, wing box and trailing edge are connected by an actuating mechanism and a locking mechanism to realize folding.

In the above variant aircraft, the empennage includes two empennage surfaces and a root rotating shaft, and the empennage surface is unfolded into a state vertical to the rear fuselage through the rotation of the root rotating shaft.

In the above variant aircraft, the propeller includes two foldable blades, and the propeller in the folded state is deployed into a vertical rear fuselage state by the centrifugal force generated by the rotation of the motor; the foldable blade has a forward or backward folding Function.

In the aforementioned variant aircraft, the wing has a large aspect ratio.

In the above-mentioned variant aircraft, the barrel is a cylindrical shell split configuration, and the aircraft is restrained in the barrel after retracted to prevent the aircraft from being damaged during delivery.

In the above variant aircraft, each component of the wing in the folded state changes from being parallel to the fuselage in the folded state to being perpendicular to the fuselage by rotating around the wing root rotation axis.

In the above-mentioned variant aircraft, when the wing is rotated and unfolded, the leading edge of the wing, the wing box, and the trailing edge are also moved from the slit-folded state to the complete splicing state through the actuating mechanism and the locking mechanism.

In the variant aircraft described above, a protruding portion is provided at the front end of the front fuselage, and a constricted portion is provided at the rear end of the rear fuselage, and the protruding portion fits with the constricted portion.

The beneficial effects of the present invention and prior art are:

(1) The present invention can shrink the UAV with large wingspan, large aspect ratio, and conventional layout into a very small cylindrical space, thereby improving the capabilities of long-distance delivery and defense penetration of the aircraft.

(2) The present invention has designed the whole set of form and aircraft configuration that the aircraft is folded and unfolded, and the aircraft is a conventional layout form after unfolding;

(3) The present invention designs a complete set of folding and unfolding forms and the configuration of the aircraft. After the aircraft is folded, it can be efficiently stored in a cylindrical cylinder, and the shrinkage ratio is extremely high.

Description of drawings

Fig. 1 is a cylinder schematic diagram of the present invention;

Fig. 2 is a schematic diagram of the folded state of the drone of the present invention;

Fig. 3 is a schematic diagram of the wing rotation and deployment process of the present invention; (a) is the wing rotation and folding state, (b) is the wing rotation and deployment process, and (c) is the completion of the wing rotation deployment;

Fig. 4 is a schematic diagram of the wing folding and unfolding process of the present invention; (a) is the wing folding state, (b) is the wing folding and unfolding completion, (c) is the wing folding and unfolding completion state;

Fig. 5 is a schematic diagram of the fuselage deployment process of the present invention; (a) is the unfolded state of the fuselage, and (b) is the completion of the fuselage deployment;

Fig. 6 is a schematic diagram of the deployment process of the empennage propeller of the present invention;

Fig. 7 is a schematic structural diagram of the drone of the present invention.

Detailed ways

The patent of the present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

The invention discloses a foldable and stowable variant aircraft, comprising: a front fuselage 1, a rear fuselage 2, wings, an empennage, a propeller, a turning mechanism, and a barrel; wherein, the front fuselage 1 and the rear fuselage 2 pass through The turning mechanism is connected; the front fuselage is fitted with the rear fuselage 2 after being turned 180 degrees; It is axially parallel to the rear fuselage 2; the propeller 13 is placed at the tail end of the rear fuselage 2, and the empennage is placed at the rear of the rear fuselage 2; the wing includes a plurality of wing sections; The wing folding device enables the wings to have multi-stage folding functions in the span and chord directions; the aircraft is stored in the cylinder after being folded. The wing folding device includes a wing hinge, an actuating device and a locking device to realize v-shaped, z-shaped, w-shaped folding. Each wing section is composed of a leading edge, a wing box and a trailing edge, and the leading edge, the wing box and the trailing edge are connected by an actuating mechanism and a locking mechanism to realize folding.

Through the comprehensive application of half-wing sweeping and folding, multi-stage flipping and folding in the span direction of the wing, three-stage folding in the chord direction of the wing, two-stage flipping and folding of the fuselage, forward-swept folding V-shaped tail, and propeller folding, the unmanned aircraft is completed. The high ratio of machine storage.

Fig. 1 is a cylinder diagram of the folded aircraft of the present invention for storage. The cylinder body 14 is a cylindrical shell with two petals, and the aircraft is restrained in the cylinder body 14 after being retracted, so as to prevent the aircraft from being damaged during delivery.

Fig. 2 is a state diagram of the cylinder body 14 being divided into two parts and separated from the aircraft. The cylinder body 14 is separated from the aircraft and then falls. Edge 3, inner wing box 4, inner wing trailing edge 5, second outer wing leading edge 6, second outer wing box 7, second outer wing trailing edge 8, outer wing leading edge 9, outer wing box 10, outer wing trailing edge 11 , front fuselage 1, rear fuselage 2, empennage 12, propeller blade 13 are all in folded state. The leading edge of the wing, the wing box, and the trailing edge are in a slit-folded state to meet the cylindrical envelope of the barrel body 14 .

Fig. 3 (a), Fig. 3 (b), Fig. 3 (c) are the wing rotation and unfolding process, the various parts of the wing in the folded state are from the state parallel to the fuselage in the folded state by rotating around the wing root shaft to be perpendicular to the Airframe status.

Figure 4(a) shows the completed state of wing rotation and deployment. While rotating and unfolding, the leading edge, wing box, and trailing edge of the wing move from the slit-folded state through the actuating mechanism and the locking mechanism to a complete splicing state.

The inner wing includes the leading edge 3, the inner wing box 4, and the inner wing trailing edge 5; the second outer wing includes the second outer wing leading edge 6, the second outer wing box 7 and the second outer wing trailing edge 8; the outer wing includes the outer wing leading edge 9 , outer wing box 10, outer wing trailing edge 11.

Figure 4(b) shows the state of the wing folding and unfolding process. Through the hinges and actuating devices between the wing sections, the multi-layer folded wings are gradually unfolded to a horizontal state.

Figure 4(c) shows the finished state of wing folding and unfolding. After the unfolding is completed, the connecting surfaces of each section of the wing are locked by an automatic locking device to form a large-span wing that can reliably bear force.

Fig. 5(a) is the state of the fuselage flipping and folding process. The front fuselage 1 in the folded state is flipped forward through the hinge and actuation mechanism between the front fuselage 1 and the rear fuselage 2 to form a complete fuselage state.

Figure 5(b) shows the flipped and folded state of the front fuselage 1. The front fuselage 1 is unfolded and locked automatically. It can be seen that the shapes of the front fuselage 1 and the rear fuselage 2 need to be designed to be suitable for storage. The front fuselage The front end portion of 1 is provided with protruding portion, and the rear end portion of rear fuselage 2 is provided with constriction portion, and protruding portion fits with constriction portion.

6 is a state diagram of the deployment process of the empennage surface 12 and the folding propeller 13. The empennage includes two empennage surfaces 12 and a root rotating shaft, and the empennage surface 12 is deployed into a vertical rear fuselage 2 state through the rotation of the root rotating shaft. The propeller includes two foldable blades 13, and the folded propeller 13 is unfolded into a vertical rear fuselage 2 state by the centrifugal force generated by the motor rotation; the foldable blade 13 has the function of folding forward or backward.

Fig. 7 is a diagram of the completed deployment of the empennage 12 and the propeller 13. After the deployment, the aircraft has a slender fuselage and a large aspect ratio wing, which is a conventional layout form of an ultra-long-endurance drone.

The above is only the best specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily conceive of changes or modifications within the technical scope disclosed in the present invention. Replacement should be covered within the protection scope of the present invention.

The content that is not described in detail in the specification of the present invention belongs to the well-known technology of those skilled in the art.

Claims (10)

1. A folding stowable variant aircraft, comprising: the device comprises a front fuselage (1), a rear fuselage (2), wings, tail wings, a propeller, a turnover mechanism and a barrel; wherein, the front machine body (1) and the rear machine body (2) are connected through a turnover mechanism; the front machine body (1) is attached to the rear machine body (2) after being overturned; the wings are symmetrically arranged on two sides of the turnover mechanism, the wings are connected with the front fuselage (1) through oblique rotating shafts, and the wings are axially parallel to the rear fuselage (2) after being rotationally folded; the screw propeller (13) is arranged at the tail end of the rear machine body (2), and the tail wing is arranged at the rear part of the rear machine body (2); the wing comprises a plurality of wing segments; the wing folding device is arranged at the joint of each wing section of the wing, so that the wing span direction and the chord direction have a multi-section folding function; the aircraft is folded and then is accommodated in the cylinder.

2. A folding stowable variant aircraft according to claim 1, wherein: the wing folding device comprises a wing hinge, an actuating device and a locking device, and realizes v-type, z-type and w-type folding.

3. A folding stowable variant aircraft according to claim 1, wherein: each wing section consists of a front edge, a wing box and a rear edge, and the front edge, the wing box and the rear edge are connected through an actuating mechanism and a locking mechanism to realize folding.

4. A folding stowable variant aircraft according to claim 1, wherein: the tail wing comprises two tail wing surfaces (12) and a root rotating shaft, and the tail wing surfaces (12) are unfolded into a state perpendicular to the rear fuselage (2) through the rotation of the root rotating shaft.

5. A folding stowable variant aircraft according to claim 1, wherein: the propeller comprises two foldable blades (13), and the folded propeller (13) is unfolded into a vertical rear machine body (2) state through centrifugal force generated by motor rotation; the foldable blade (13) has a function of folding forward or backward.

6. A folding stowable variant aircraft according to claim 1, wherein: the wing has a large aspect ratio.

7. A folding stowable variant aircraft according to claim 1, wherein: the cylinder body (14) is in a cylindrical shell split configuration, and the aircraft is restrained in the cylinder body (14) after being retracted, so that the aircraft is prevented from being damaged in the delivery process.

8. A folding stowable variant aircraft according to claim 1, wherein: the wing parts in the folded state are rotated to be perpendicular to the fuselage from a state parallel to the fuselage in the folded state around the root rotating shaft of the wing.

9. A folding stowable variant aircraft according to claim 3, characterized in that: the wing is rotated and unfolded, and meanwhile, the front edge, the wing box and the rear edge of the wing are also moved from a slotting folding state to a complete splicing state through an actuating mechanism and a locking mechanism.

10. A folding stowable variant aircraft according to claim 1, wherein: the front end part of the front machine body (1) is provided with a protruding part, the rear end part of the rear machine body (2) is provided with a shrinking part, and the protruding part is matched with the shrinking part.

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