Front-tilting and rear-folding composite wing vertical take-off and landing aircraft
By adopting the power layout of forward leaning and rear folding in the composite wing vertical take -off and landing aircraft, the weight and resistance of the power system do not work in the existing technology during the existing technology, and the flexibility of vertical take -off and landing and horizontal flights. The transition and center of gravity are automatically adjusted, extending the flight time.
Patent Information
- Application Number
- CN202411289766.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-14
- Publication Date
- 2025-01-21
AI Technical Summary
Existing composite wing vertical take-off and landing vehicles during horizontal flights result in additional weight and air resistance due to the inability to operate the power system, which affects the performance of long-distance flights.
It adopts a composite wing configuration with forward tilting and rear folding, uses the lift motor system to achieve vertical takeoff and landing, uses the tilting mechanism to achieve horizontal propulsion, and uses the folding mechanism to reduce waste drag and balance the center of gravity during horizontal flight.
It achieves flexible conversion between vertical take-off and landing and horizontal flight, reduces the weight and resistance of the aircraft during horizontal flight, extends the flight time, and automatically completes the movement and re-balancing of the center of gravity.
Smart Images
Figure CN119329792A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the field of aircraft, and relates to a composite wing vertical take-off and landing aircraft with forward tilting and rear folding. Background Art
[0002] Composite wing vertical take-off and landing aircraft are aircraft that have the wings and control surfaces of fixed-wing aircraft and have the ability to take off and land vertically. Against the background of the rapid development of electric motors, composite wing vertical take-off and landing aircraft (manned / unmanned) have entered a rapid development stage. There are two conventional layouts:
[0003] 1. Tilt-rotor type: It has the fuselage, wings and tail of a conventional aircraft, but adds a propeller that can take off vertically. The propeller thrust axis can rotate to change the direction of thrust, achieving vertical take-off and horizontal flight;
[0004] 2. Composite type: It has the fuselage, wings and tail of a conventional aircraft, but adds a propeller that can take off vertically. The propeller works during vertical take-off and stops during horizontal flight. The thrust is provided by a special horizontal propulsion propeller to achieve vertical take-off and horizontal flight.
[0005] The advantage of a tilt-rotor is that the same power and rotor are used for both vertical take-off and landing and horizontal flight, with no extra weight wasted. However, the control system for the tilting process is relatively complex. The two power systems of a composite aircraft are independent of each other and have a simple structure. However, during horizontal flight, one set of power systems is not working, generating extra weight and air resistance, which is not conducive to long-distance flight. Summary of the invention
[0006] Purpose of the invention: To provide a composite wing vertical take-off and landing aircraft based on a distributed power layout, integrated tilting system and folding system. The aircraft uses a lift motor system to achieve vertical take-off and landing, a tilting mechanism to achieve horizontal propulsion, and a folding mechanism to reduce drag and balance the center of gravity.
[0007] Technical Solution
[0008] Provided is a forward tilting and rear folding composite wing vertical take-off and landing aircraft, comprising: a fuselage, a main wing, a horizontal tail, a vertical tail, a forward tilting motor, a forward tilting motor support, a rear folding motor, and a folding motor cabin door;
[0009] The fuselage is the main structural part of the aircraft, connecting the other parts and carrying people and cargo; the main wing is fixed on both sides above the middle of the fuselage, and the horizontal tail and vertical tail are fixed on the rear of the fuselage; the forward tilt motor support is fixed on the lower side of the leading edge of the main wing to carry the forward tilt motor; the forward tilt motor has a 90° rotation capability on the forward tilt motor support, converting from a vertical state to a horizontal state to provide lift or pull;
[0010] Storage compartments are opened on both sides of the fuselage, and a rotating shaft is set at the rear of the storage compartment. The root of the rear folding motor is connected to the fuselage through the rotating shaft, and can be rotated 90° to retract into the storage compartment, so that the rear folding motor can be converted from an open state to a folded state; the folding motor compartment door is fixed on the fuselage and closed after the rear folding motor is folded into the storage compartment to reduce flight resistance.
[0011] Furthermore, the folding motor compartment door is divided into two pieces, the upper piece is connected to the upper side of the storage compartment, and the lower piece is connected to the lower side of the storage compartment.
[0012] Furthermore, the folding motor door provides closing power through a torsion spring.
[0013] Furthermore, when in the vertical take-off and landing and hovering state, the two forward tilting motors are in a vertical state, the folding motor hatch is opened, and the two rear folding motors are unfolded, forming a four-rotor structure together with the forward tilting motor, generating vertical thrust to allow the aircraft to take off vertically; the forward tilting motor and the rear folding motor generate a lift difference through the different rotation speeds, thereby realizing the control force of the aircraft during vertical flight.
[0014] Furthermore, when in a horizontal flight state, the two forward tilting motors slowly tilt forward, and the horizontal component of the thrust generated allows the aircraft to have a horizontal speed; as the tilt angle of the forward tilting motor increases, the flight speed increases; when the flight speed is sufficient for the main wing to generate sufficient lift, the two rear folding motors slowly stop rotating, and after stopping, they fold forward to the storage compartment, and the folding motor compartment door is closed to reduce flight resistance.
[0015] Furthermore, the aircraft transitions from a vertical take-off and landing state to a horizontal flight state, and the movement of the forward tilt motor and the rear folding motor causes the overall center of gravity of the aircraft to move forward, transitioning from the center of the wing to 1 / 3 of the leading edge of the wing.
[0016] Furthermore, the weight and lever arm calculation formula of the rear folding motor (7) required for the transition from the center of the wing to the 1 / 3 of the leading edge of the wing is:
[0017] L×G1=c×G / 6
[0018] Wherein, G1 is the weight of the rear folding motor, L is the length of the rear folding motor arm, G is the total weight of the aircraft including the weight of the rear folding motor, and c is the chord length of the aircraft wing;
[0019] In addition, the formula needs to meet the following premise: when the rear folding motor is in the unfolded state, the distance between the forward tilting motor and the leading edge of the wing is equal to the distance between the rear folding motor and the trailing edge of the wing.
[0020] Furthermore, when in horizontal flight, the forward tilt motor provides horizontal pulling force, and the horizontal tail and vertical tail provide control force.
[0021] Beneficial effects:
[0022] In the present invention, the forward tilting motor can be used as lift for vertical take-off and landing, as well as thrust for horizontal flight, which can reduce the need for a separate set of power for horizontal flight and is beneficial to weight reduction; the rear folding motor is folded into the fuselage when not in use, and has a closable folding motor door, which effectively reduces the drag of the aircraft during horizontal flight and is beneficial to extending the flight time; 3. In conjunction with the movement of the forward tilting motor and the rear folding motor, the conversion of the aircraft between the vertical take-off and landing and horizontal flight modes can automatically complete the movement and re-balancing of the aircraft's center of gravity, without the need to add or move other counterweights for balancing, thereby reducing the number of motion mechanisms. BRIEF DESCRIPTION OF THE DRAWINGS
[0023] Figure 1a Schematic diagram of the folding motor of a composite wing vertical take-off and landing aircraft after unfolding.
[0024] Figure 1b Schematic diagram of the folding motor of the composite wing vertical take-off and landing aircraft after retraction.
[0025] Figure 2a This is a horizontal top view of the aircraft.
[0026] Figure 2b This is the horizontal front view of the aircraft.
[0027] Figure 2c This is a horizontal side view of the aircraft.
[0028] Figure 3 This is an exploded view of a composite wing vertical take-off and landing aircraft with forward tilting and rear folding.
[0029] Figure 4 This is the motion diagram of the forward tilt motor.
[0030] Figure 5 This is the motion diagram of the rear folding motor.
[0031] Figure 6 This is a diagram showing the change in center of gravity displacement before and after tilting / folding.
[0032] Figure 7 This is the center of gravity distribution diagram of the aircraft from the side.
[0033] Figure 8 This is the center of gravity distribution diagram of the aircraft. DETAILED DESCRIPTION
[0034] like Figure 1a-3As shown, the aircraft is composed of the following components: a fuselage 1; a main wing 2; a horizontal tail 3; a vertical tail 4; two forward tilting motors 5; two forward tilting motor supports 6; two rear folding motors 7; and four folding motor doors 8.
[0035] The assembly method of the aircraft:
[0036] The fuselage 1 is the main structural part of the aircraft, connecting the remaining parts and carrying people and cargo; the main wing 2 is fixed on both sides above the middle part of the fuselage 1, and the horizontal tail 3 and the vertical tail 4 are fixed on the rear part of the fuselage 1; the forward tilt motor support 6 is fixed on the lower side of the leading edge of the main wing 2, and is used to carry the forward tilt motor 5; the forward tilt motor 5 has a 90° rotation ability on the forward tilt motor support 6, and is converted from a vertical state to a horizontal state to provide lift or pull.
[0037] The wing 2 is fixed above the middle of the fuselage 1 and is the main component for generating lift during horizontal flight; the horizontal tail 3 and the vertical tail 4 are fixed to the rear of the fuselage 1 and are used to provide control force for horizontal flight; the forward tilt motor support 6 is fixed to the lower side of the leading edge of the main wing 2 and is used to carry the forward tilt motor 5; the forward tilt motor 5 can be rotated 90° on the forward tilt motor support 6, and converted from a vertical state to a horizontal state to provide lift or pulling force; the rear folding motor 7 is installed on the rear side of the fuselage 1 and can be rotated 90° to convert from an open state to a folded state; the folding motor door 8 is fixed to the fuselage 1 and can be closed after the rear folding motor 7 is folded into the fuselage 1 to reduce flight resistance.
[0038] When the rear folding motor 7 is unfolded, the aircraft can be used as a composite wing UAV; when the rear folding motor 7 is retracted, the aircraft can be used as a quad-rotor UAV.
[0039] The flight principle of the aircraft:
[0040] like Figure 1a and Figure 4 As shown, in the vertical take-off and landing and hovering state, the two forward tilting motors 5 are in a vertical state, the folding motor door 8 is opened, and the two rear folding motors 7 are unfolded, and together with the forward tilting motors 5, a quad-rotor structure is formed to generate vertical thrust to allow the aircraft to take off vertically; the forward tilting motor 5 and the rear folding motor 7 generate a lift difference due to the different rotation speeds, thereby realizing the control force of the aircraft during vertical flight;
[0041] like Figure 1b and Figure 5As shown, in the horizontal flight state, the two forward tilting motors 5 slowly tilt forward, and the horizontal component of the thrust generated allows the aircraft to have a horizontal speed; as the tilt angle of the forward tilting motor 5 increases, the flight speed increases, and when the flight speed is sufficient for the main wing 2 to generate enough lift, the two rear folding motors 7 slowly stop rotating, and fold from the open state to the inside of the fuselage 1, and close the folding motor door 8 to reduce flight resistance. At this time, the aircraft becomes a horizontal flight configuration.
[0042] In addition, if Figure 6 As shown, as the aircraft transitions from the vertical take-off and landing state to the horizontal flight state, the movement of the forward tilt motor 5 and the rear folding motor 7 causes the overall center of gravity of the aircraft to move forward, transitioning from the middle of the wing to 1 / 3 of the leading edge of the wing, which is beneficial to the stability of the flight attitude and the guarantee of maneuverability in the two different states.
[0043] To ensure that the aircraft has a suitable center of gravity for both vertical take-off and landing and horizontal flight in the forward tilt and rear folding modes, the mass G1 and lever arm L of the rear folding motor must satisfy the following formula:
[0044] L×G1=c×G / 6
[0045] Among them, G1 is the weight of the rear folding motor, L is the length of the rear folding motor arm, G is the total weight of the aircraft, and c is the chord length of the aircraft wing. In addition, this formula must meet the following premise: when the rear folding motor is in the unfolded state, the distance between the forward tilting motor and the leading edge of the wing is equal to the distance between the rear folding motor and the trailing edge of the wing.
[0046] Since the movement mechanism of the aircraft is mainly caused by the forward movement of the rear folding motor, in order to ensure that the total center of gravity moves forward by 1 / 6 of the chord length (moving from 1 / 2 chord length to 1 / 3 chord length, the distance is 1 / 6 chord length), the aircraft is simplified to mass point G, and the center of gravity distribution of the aircraft from the side is as follows: Figure 7-8 shown.
[0047] According to the center of gravity balance requirements in horizontal flight, the following formula can be obtained:
[0048] (S2-c / 6)×G1=(S2-L+c / 6)×G1+c / 6×(G-2G1)
[0049] The prerequisite must be met: S1=S2.
[0050] Simplifying, we get the final formula: L×G1=c×G / 6.
[0051] The flight process of the unmanned aerial vehicle is as follows:
[0052] 1) The aircraft is on the ground, the forward tilting motor 5 rotates to a vertical state, the folding motor door 8 opens, and the rear folding motor 7 unfolds to form a quad-rotor configuration, ready for takeoff;
[0053] 2) The two forward tilting motors 5 and the two rear folding motors 7 are accelerated, the total lift is greater than the gravity of the aircraft, and the aircraft leaves the ground vertically;
[0054] 3) After vertical flight reaches a certain height, the two forward tilting motors 5 gradually tilt forward, and the horizontal flight speed of the aircraft gradually increases; when the lift of the main wing 2 is sufficient to support the flight of the aircraft, the rear folding motor 7 gradually stops and folds into the fuselage 1, the folding motor door 8 is closed, and the aircraft enters a horizontal flight state;
[0055] 3) If the aircraft lands vertically, just reverse the take-off action.
Claims
1. A composite wing vertical take-off and landing aircraft with forward tilting and rear folding, characterized in that: include: Fuselage (1), main wing (2), horizontal tail (3), vertical tail (4), forward tilt motor (5), forward tilt motor support (6), rear folding motor (7), folding motor door (8); The fuselage (1) is the main structural part of the aircraft, connecting the other parts and carrying people and cargo; the main wing (2) is fixed on both sides above the middle of the fuselage (1), and the horizontal tail (3) and the vertical tail (4) are fixed on the rear of the fuselage (1); the forward tilt motor support (6) is fixed on the lower side of the leading edge of the main wing (2) and is used to carry the forward tilt motor (5); the forward tilt motor (5) has a 90° rotation capability on the forward tilt motor support (6), and is converted from a vertical state to a horizontal state, providing lift or pulling force; Storage compartments are provided on both sides of the fuselage (1), and a rotating shaft is provided at the rear of the storage compartment. The root of the rear folding motor (7) is connected to the fuselage (1) through the rotating shaft, and can be rotated 90 degrees to be stored and recovered into the storage compartment, so that the rear folding motor (7) can be converted from an open state to a folded state; a folding motor compartment door (8) is fixed on the fuselage (1) and is closed after the rear folding motor (7) is folded into the storage compartment, thereby reducing flight resistance.
2. The aircraft according to claim 1, characterized in that The foldable motor cabin door (8) is divided into two pieces, the upper piece is connected to the upper side of the storage cabin, and the lower piece is connected to the lower side of the storage cabin.
3. The aircraft according to claim 1, characterized in that: The folding motor cabin door (8) is provided with closing power by a torsion spring.
4. The aircraft according to claim 1, characterized in that: When in a vertical take-off and landing and hovering state, the two forward tilting motors (5) are both in a vertical state, the folding motor cabin door (8) is opened, and the two rear folding motors (7) are unfolded to form a four-rotor structure together with the forward tilting motors (5), generating vertical thrust to allow the aircraft to take off vertically; the forward tilting motors (5) and the rear folding motors (7) generate a lift difference due to the different rotation speeds, thereby realizing the control force of the aircraft during vertical flight.
5. The aircraft according to claim 4, characterized in that When in a horizontal flight state, the two forward tilting motors (5) slowly tilt forward, and the horizontal component of the thrust generated allows the aircraft to have a horizontal speed; as the tilting angle of the forward tilting motor (5) increases, the flight speed increases; when the flight speed is sufficient for the main wing (2) to generate sufficient lift, the two rear folding motors (7) slowly stop rotating, and after stopping, they fold forward to the storage cabin, and the folding motor cabin door (8) is closed to reduce flight resistance.
6. The aircraft according to claim 5, characterized in that The aircraft transitions from a vertical take-off and landing state to a horizontal flight state, and the movement of the forward tilting motor (5) and the rear folding motor (7) causes the overall center of gravity of the aircraft to move forward, transitioning from the center of the wing to 1 / 3 of the leading edge of the wing.
7. The aircraft according to claim 6, characterized in that The weight and lever arm calculation formula of the rear folding motor (7) required for the transition from the center of the wing to the 1 / 3 of the leading edge of the wing is: L×G1=c×G / 6 Wherein, G1 is the weight of the rear folding motor, L is the length of the rear folding motor arm, G is the total weight of the aircraft including the weight of the rear folding motor, and c is the chord length of the aircraft wing; In addition, the formula needs to meet the following premise: when the rear folding motor is in the unfolded state, the distance between the forward tilting motor and the leading edge of the wing is equal to the distance between the rear folding motor and the trailing edge of the wing.
8. The aircraft according to claim 5, characterized in that When in a horizontal flight state, the forward tilt motor (5) provides horizontal pulling force, and the horizontal tail (3) and the vertical tail (4) provide control force.