CN113291460B - Short-distance/vertical take-off and landing aircraft adopting variant landing gear - Google Patents
Short-distance/vertical take-off and landing aircraft adopting variant landing gear Download PDFInfo
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- CN113291460B CN113291460B CN202110615198.4A CN202110615198A CN113291460B CN 113291460 B CN113291460 B CN 113291460B CN 202110615198 A CN202110615198 A CN 202110615198A CN 113291460 B CN113291460 B CN 113291460B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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Abstract
The invention relates to a short-distance/vertical take-off and landing aircraft adopting a variant landing gear, belonging to the technical field of aviation. The wings of the short-distance/vertical take-off and landing aircraft adopting the variant landing gear are fixed on the aircraft body, and a power system is arranged on the wings; the wings are provided with ailerons; a wheel type nose landing gear is arranged on the body; the wing top surface and the wing bottom surface of the wing are respectively provided with a tail support system for vertical take-off and landing or short-distance take-off and landing of the aircraft; a wheel type front and rear falling frame is arranged in the tail support system positioned on the bottom surface of the wing; the tail support system is in an outward opening and closing posture or an inward closing and closing posture; the short-distance/vertical take-off and landing aircraft adopting the variant landing gear provided by the invention has the advantages that the posture mode can be adjusted according to the task and environment requirements, and the adaptability to task work in a future complex environment is enhanced.
Description
Technical Field
The invention relates to a short-distance/vertical take-off and landing aircraft adopting a variant landing gear, belonging to the technical field of aviation.
Background
Referring to other novel vertical take-off and landing aircraft types, the design index is mostly set to an STOVL (short-range vertical take-off and landing) aircraft instead of a pure VTOL (vertical take-off and landing) aircraft, and the aim is to avoid the severe requirement of vertical take-off on the power of an engine, so that the take-off weight is limited and the take-off cannot be carried out in full oil or full mounting.
Like F35-B in the united states, at vertical takeoff, the takeoff weight is limited to only 16.8 tons, but the empty weight of F35-B itself has already reached 14.7 tons, thus deducting the empty weight, leaving only 2.1 tons of weight available for payload. In this case, F35-B can only be loaded with 34% of fuel even without any ammunition, and the fuel to carry the ammunition is further reduced, and if 1 ton of ammunition is carried, the fuel of F35-B drops to the poor 18%, which is almost no longer a battle radius.
When F35-B is used for short take-off, in this mode the lift fan also needs to operate and the jet tail also needs to deflect, but not provide full lift. In fact, the jet of the lift fan is inclined backwards at 15 degrees at take-off, the main engine of the aircraft is inclined downwards at 65 degrees, and the engine generates horizontal thrust of about 72% of the total thrust and lift of 68% of the total thrust. In this case, the F35-B race 122 meters can reach a takeoff weight of 22.7 tons. With an empty weight of 14.7 tonnes deducted, and a payload of 8 tonnes, it is possible to fill with fuel (6.1 tonnes) and carry 1.9 tonnes of ammunition. If the running distance of the short takeoff is further lengthened and the sliding deck is matched (167-meter sliding runway is prepared for F35-B by Elizabeth Queen aircraft carrier in England), the F35-B can take off even with the designed maximum takeoff weight of 27 tons, and the effective load reaches 12.3 tons, so that the airplane has extremely strong fighting capacity.
The north atlantic convention organization (NATO) has the following definitions for variant aircraft: by locally or integrally changing the shape of the aircraft, the aircraft can adapt to various task requirements in real time and maintain optimal performance and efficiency under various environments. However, the main development directions at present are a variable-rear (front) sweep aircraft, a variable-span aircraft, a tilt wing variant aircraft, a rolling arc wing aircraft and a combined variant aircraft, the variant technologies for the landing gear are less, and the landing gear can be designed in a retractable function.
Disclosure of Invention
The present invention addresses the above-identified problems by providing a short-reach/vertical-take-off and landing aircraft that employs a morphing landing gear.
The invention adopts the following technical scheme:
the invention relates to a short-distance/vertical take-off and landing aircraft adopting a variant landing gear, which comprises a power system, a fuselage, wings, ailerons, a tail boom system, a wheel type nose landing gear and a wheel type rear landing gear; the wings are fixed on the fuselage, and a power system is arranged on the wings; the wings are provided with ailerons; the machine body is provided with a wheel type nose landing gear; the wing top surface and the wing bottom surface of the wing are respectively provided with a tail support system for vertical take-off and landing or short-distance take-off and landing of the aircraft; a wheel type rear landing gear is arranged in the tail support system positioned on the bottom surface of the wing; the tail support system is in an outward opening and closing posture or an inward closing and closing posture;
the tail support system positioned on the bottom surface of the wing supports the aircraft through the wheel type rear landing gear and the wheel type front landing gear of the aircraft body for a short-distance take-off and landing mode;
and the tail support system positioned on the top surface of the wing and the tail support system positioned on the bottom surface of the wing open and close outwards to form a support posture for a vertical take-off and landing mode of the aircraft.
The invention relates to a short-distance/vertical take-off and landing aircraft adopting a variant landing gear.A support rod control steering engine and a tail support rod control steering engine of a tail support system for controlling the top surface of a wing and a tail support system for controlling the bottom surface of the wing are respectively arranged in wings at two sides of an aircraft body;
the tail support system positioned on the top surface of the wing comprises a first support rod, a first tail support horizontal tail wing, a first tail support vertical tail wing, a first support rod pull rod and a first tail support rod pull rod; the first support rod and the first tail stay rod are at least two groups and are positioned on the top surfaces of wings on two sides of the fuselage, one end of the first support rod is hinged with the wings through a shaft body, the other end of the first support rod is hinged with one end of the first tail stay rod through the shaft body, and the other end of the first tail stay rod is provided with a first tail stay vertical tail wing; a first tail brace horizontal tail wing parallel to the wing is arranged between the first tail brace rods; one end of the first support rod pull rod is fixedly connected with a wing part shaft body of the first support rod, and the other end of the first support rod pull rod is connected with a driving end of a support rod control steering engine on the top surface of a wing; one end of a first tail support rod is fixedly connected to the shaft body at one end of the first tail support rod, and the other end of the first tail support rod is connected with a tail support rod control steering engine on the top surface of the wing;
the tail support system positioned on the bottom surface of the wing comprises a second support rod, a second tail support horizontal tail wing and a second tail support vertical tail wing; a second support rod pull rod and a second tail support rod pull rod;
the second support rod and the second tail support rod are at least two groups and are positioned on the top surfaces of the wings on two sides of the fuselage, one end of the second support rod is hinged with the wings through a shaft body, the other end of the second support rod is hinged with one end of the second tail support rod through a shaft body, and the other end of the second tail support rod is provided with a second tail support vertical tail wing; a tail brace horizontal tail wing II parallel to the wing is arranged between the tail brace rods II; one end of the second support rod pull rod is fixedly connected with a wing part shaft body of the second support rod, and the other end of the second support rod pull rod is connected with a driving end of a support rod control steering engine on the bottom surface of the wing; one end of the tail stay bar II is fixedly connected to the shaft body at one end of the tail stay bar II, and the other end of the tail stay bar II is connected with the tail stay bar control steering engine at the bottom surface of the wing.
The invention relates to a short-distance/vertical take-off and landing aircraft adopting variant landing gears, which comprises a wheel type nose landing gear, wherein the wheel type nose landing gear comprises: the machine body is connected with a driving mechanism, a retracting rod, a pull rod, a retracting rod connecting piece, a main buffer, a rotating mechanism, a machine wheel connecting piece and a front machine wheel;
the main buffer is hinged with the machine body through a machine body connecting and driving mechanism, and the pull rod connecting piece is used as an outer cylinder and fixedly connected with the main buffer;
the top end of the retracting rod extends to the inner belly of the machine body, the tail end of the retracting rod is connected with the top end of the pull rod, the tail end of the pull rod is hinged to the retracting rod connecting piece, the front machine wheel is fixedly connected with the main buffer through the machine wheel connecting piece and can rotate around the axis of the main buffer through the rotating mechanism, and the rotating angle is 90 degrees.
The invention relates to a short-distance/vertical take-off and landing aircraft adopting a variant landing gear, wherein a wheel type rear landing gear comprises a rear landing gear connecting piece, a rear landing gear sliding rail, a semi-retractable shell, an upper rocker arm, a buffer, a lower rocker arm and a rear aircraft wheel; a rear undercarriage sliding rail and a rear undercarriage connecting piece are arranged in the tail boom vertical tail wing II; the semi-retractable shell is assembled on the rear landing gear sliding rail and slides along the extension direction of the rear landing gear sliding rail; the bottom end part of the semi-retractable shell is provided with a shaft hole of an assembled wheel shaft of the rear wheel;
a buffer is fixed at the lower end of the rear landing gear connecting piece, the outer side wall of the buffer is hinged with one end of an upper rocker arm, the other end of the upper rocker arm is hinged with one end of a lower rocker arm, and the other end of the lower rocker arm is hinged with a wheel shaft of a rear wheel; the bottom end of the buffer is also hinged with the middle part of the lower rocker arm body;
when the wheel type rear landing gear bears, the semi-retractable shell moves up and down in a rear landing gear sliding rail along with the wheel type rear landing gear;
according to the short-distance/vertical take-off and landing aircraft adopting the variant landing gear, the distance between the tail support horizontal tail wing I and the gravity center of the aircraft is the sum of the lengths of the support rod I and the tail support rod I or the support rod II and the tail support rod II.
According to the short-distance/vertical take-off and landing aircraft adopting the variant undercarriage, when the aircraft is in self-adaptive vertical landing, the support rod controls the steering engine and the tail support rod controls the steering engine to drive the support rod I, the tail support rod I, the support rod II and the tail support rod II to rotate, and the support rod I, the tail support rod I, the support rod II and the tail support rod II are adjusted to be changed to postures with high matching degree with the environment of a landing area to land.
According to the short-distance/vertical take-off and landing aircraft adopting the variant landing gear, the symmetrical surfaces of the vertical tail wing II of the tail boom, the semi-retractable shell, the upper rocker arm, the buffer, the lower rocker arm and the rear aircraft wheel are unified and coplanar.
Advantageous effects
The short-distance/vertical take-off and landing aircraft adopting the variant landing gear integrates the advantages of fixed wings and a rotary wing aircraft, can remarkably reduce the requirements of the aircraft on take-off and landing conditions, has strong flight operational capability, and has small platform use such as: the characteristics of large power exertion of medium and small aircraft carriers, amphibious attacking ships, transport ships, ocean reefs and the like are remarkable.
The invention provides a short-distance/vertical take-off and landing aircraft adopting a variant undercarriage, which can adjust an attitude mode according to task and environment requirements, when the take-off and landing environment is severe and vertical take-off and landing are required, a support rod and a tail support rod play a role in supporting and protecting the aircraft parked on the ground, when the aircraft is in a cruising state of flatly flying, the tail support and the support rod which are symmetrically unfolded at two sides can be actively controlled to be mutually butted, after the butting, the additional resistance caused by the structures of the tail support and the support rod is reduced, and because a main body is positioned at the tail part of a machine body, a horizontal tail and a vertical tail which are positioned on the tail support are far away from the gravity center of the aircraft, the force arm for matching and operating is long, the operating capacity is strong, and the matching additional resistance is small, the control capacity and the flying efficiency of the aircraft in flying are improved.
The short-distance/vertical take-off and landing aircraft adopting the variant landing gear can select a running take-off and landing mode according to actual environmental factors, the aircraft is supported on the surface of a take-off/parking area through the wheel type front landing gear and the wheel type rear landing gear before and after running off and landing, the main weight of the aircraft is borne and the attitude balance is kept, the take-off and landing mode is changed by only controlling the wheel type front landing gear to retract and release and controlling the attitude change of the supporting rod and the tail supporting rod, and meanwhile, the supporting rod, the tail supporting horizontal tail wing and the tail supporting vertical tail wing on the side without supporting function are adjusted to be in a flat flight state, so that the short-distance/vertical take-off and landing aircraft is assisted to control and adjust, and the realization of a flexible function is increased through simple structural change.
Drawings
FIG. 1 is a schematic diagram of a short-range/VTOL aircraft mode transition state landing gear adaptive adjustment using a variant landing gear;
FIG. 2 is a schematic view of a short-range/VTOL aircraft wheeled nose gear configuration employing a modified landing gear;
FIG. 3 is a schematic view of a short-reach/VTOL aircraft wheeled rear landing gear configuration employing a variation landing gear;
FIG. 4 is a schematic representation of a sprint/VTOL aircraft employing a variant landing gear in a rolloff, landing and parked position;
FIG. 5 is a schematic illustration of a VTOL and park condition of a short-reach/VTOL aircraft employing a variation landing gear;
FIG. 6 is a schematic diagram of a right-side first-landing adaptive landing state for a short-range/VTOL aircraft employing a morphing landing gear;
FIG. 7 is a schematic diagram of a left first-landing adaptive landing state for a short-reach/VTOL aircraft employing a morphing landing gear;
FIG. 8 is a schematic diagram of a ground adaptive attitude adjustment for a short-range/VTOL aerial vehicle employing a variant landing gear;
FIG. 9 is a schematic view of a cruise condition of a short-reach/vertical-takeoff aircraft employing a variant landing gear;
FIG. 10 is a schematic view of two flat states of the landing gear attitude drive structure;
FIG. 11 is a schematic view of two sections of a bending state of an attitude drive structure of the landing gear;
FIG. 12 is a schematic view of a support rod in a wing for controlling a steering engine and connection;
FIG. 13 is a schematic view of a tail stay rod in a wing to control a steering engine and the connection;
the airplane comprises a power system 1, a fuselage 2, a wing 3, a support rod control steering engine 4, an aileron 5, a tail support rod control steering engine 6, a support rod I7, a tail support rod I8, a tail support rod I9, a tail support horizontal tail wing I10, a tail support vertical tail wing I71, a support rod II 81, a tail support horizontal tail wing II 91, a tail support vertical tail wing II 101, a wheel type front landing gear 11, a body 111, a driving mechanism 112, a retraction rod 113, a pull rod 114, a main buffer 115, a rotating mechanism 116, a wheel type connecting piece 117, a wheel type connecting piece 118, a front wheel 12, a wheel type rear landing gear connecting piece 121, a rear landing gear sliding rail 122, a half-shell 123, an upper rocker 124, a buffer 125, a lower rocker 126, a rear rocker 127, a rear wheel, a support rod I13, a tail support rod pull rod I14, a support rod pull rod II 131, a support rod pull rod 141 and a tail support rod retraction rod pull rod II.
Detailed Description
The present invention will now be described in more detail with reference to the accompanying schematic drawings, in which preferred embodiments of the invention are shown, it being understood that one skilled in the art may modify the invention herein described while still achieving the advantageous effects of the invention. Accordingly, the following description should be construed as broadly as possible to those skilled in the art and not as limiting the invention.
As shown in fig. 1: the short-distance/vertical take-off and landing aircraft adopting the variant landing gear comprises a power system 1, a fuselage 2, wings 3, ailerons 5, a tail support system, a wheel type front landing gear 11 and a wheel type rear landing gear 12; the wings 3 are fixed on the fuselage 2, and the power system 1 is arranged on the wings 3; the wings 3 are provided with ailerons 5; the machine body 2 is provided with a wheel type nose landing gear 11; the wing top surface and the wing bottom surface of the wing 3 are respectively provided with a tail support system for vertical take-off and landing or short-distance take-off and landing of the aircraft; a wheel type rear landing gear 12 is arranged in the tail support system positioned on the bottom surface of the wing; the tail support system is in an outward opening and closing posture or an inward closing and closing posture; the tail support system positioned on the bottom surface of the wing supports the aircraft through a wheel type rear landing gear 12 and a wheel type front landing gear 11 of the fuselage 2 for a short take-off and landing mode; the tail support system positioned on the top surface of the wing and the tail support system positioned on the bottom surface of the wing open and close outwards to form a support posture for a vertical take-off and landing mode of the aircraft. The power system 1 provides lift force for the short-distance/vertical take-off and landing aircraft and has attitude control capability, and the motion envelope of the power system 1 is not overlapped with the motion envelope of the landing gear variant.
A tail support system for controlling the top surface of the wing and a support rod control steering engine 4 and a tail support rod control steering engine 6 of the tail support system for controlling the bottom surface of the wing are respectively arranged in the wings 3 at the two sides of the fuselage 2;
the tail boom system positioned on the top surface of the wing 3 comprises a first support rod 7, a first tail boom 8, a first tail boom horizontal tail wing 9, a first tail boom vertical tail wing 10, a first support rod pull rod 13 and a first tail boom pull rod 14; the first supporting rods 7 and the first tail supporting rods 8 are at least two groups and are positioned on the top surfaces of wings 3 on two sides of the fuselage 2, one end of each supporting rod 7 is hinged with the corresponding wing 3 through a shaft body, the other end of each supporting rod 7 is hinged with one end of each tail supporting rod 8 through a shaft body, and the other end of each tail supporting rod 8 is provided with a tail supporting vertical tail wing I10; a tail brace horizontal tail wing I9 parallel to the wing 3 is arranged between the tail brace rods I8; one end of the first support rod pull rod 13 is fixedly connected with the shaft body of the wing 3 part of the first support rod 7, and the other end of the first support rod pull rod 13 is connected with the driving end of the support rod control steering engine 4 on the top surface of the wing; one end of a tail stay rod pull rod I14 is fixedly connected to the shaft body at one end of the tail stay rod I8, and the other end of the tail stay rod pull rod I14 is connected with a tail stay rod control steering engine 6 on the top surface of the wing;
the tail support system positioned on the bottom surface of the wing 3 comprises a second support rod 71, a second tail support rod 81, a second tail support horizontal tail wing 91 and a second tail support vertical tail wing 101; a second support rod pull rod 131 and a second tail support rod pull rod 141;
at least two groups of support rods II 71 and tail support rods II 81 are arranged on the top surfaces of the wings 3 on the two sides of the fuselage 2, one end of each support rod II 71 is hinged with the wing 3 through a shaft body, the other end of each support rod II 71 is hinged with one end of each tail support rod II 81 through a shaft body, and the other end of each tail support rod II 81 is provided with a tail support vertical empennage II 101; a tail brace horizontal tail wing II 91 parallel to the wing 3 is arranged between the tail brace rods II 81; one end of the second support rod pull rod 131 is fixedly connected with the shaft body of the wing 3 part of the second support rod 71, and the other end of the second support rod pull rod 131 is connected with the driving end of a support rod control steering engine 4 on the bottom surface of the wing; one end of the second tail stay rod 141 is fixedly connected to the shaft body at one end of the second tail stay rod 81, and the other end of the second tail stay rod 141 is connected with the tail stay rod control steering engine 6 on the bottom surface of the wing.
Before and after the short-distance/vertical take-off and landing aircraft vertically take off and landing, the short-distance/vertical take-off and landing aircraft is supported on the surface of a take-off/parking area through a first support rod 7, a first tail support rod 8, a first tail support horizontal tail wing 9, a first tail support vertical tail wing 10, a second support rod 71, a second tail support rod 81, a second tail support horizontal tail wing 91 and a second tail support vertical tail wing 101, and the short-distance/vertical take-off and landing aircraft bears the main weight and keeps posture balance;
in the mode conversion process of the short-distance/vertical take-off and landing aircraft for suspension, rotation, flat flying or hovering, the support rod control steering engine 4 and the tail stay rod control steering engine 6 drive the support rod I7, the tail stay rod I8, the support rod II 71 and the tail stay rod II 81 to rotate, so that the support rod I7, the tail stay rod I8, the support rod II 71 and the tail stay rod II 81 perform posture adjustment relative to the aircraft body 2;
the auxiliary short-distance/vertical take-off and landing aircraft trim, the two tail support horizontal tails and the ailerons 5 are matched to adjust and adapt to the airflow direction, aerodynamic force which is beneficial to the flight of the aircraft body 2 is generated, after the short-distance/vertical take-off and landing aircraft is stable, the undercarriage is gradually closed, the whole structure is located at the tail end of the aircraft body 2, the distance between the two tail support horizontal tails and the center of gravity of the short-distance/vertical take-off and landing aircraft is the sum of the lengths of the supporting rod I7, the tail support rod I8 or the supporting rod II 71 and the tail support rod II 81, and the length parameters of the supporting rod I7, the tail support rod I8 or the supporting rod II 71 and the tail support rod II 81 need to ensure that the tail support horizontal tail wing 9 has good operating performance.
When the short-distance/vertical take-off and landing aircraft is in self-adaptive vertical landing, the supporting rod controls the steering engine 4 and the tail supporting rod controls the steering engine 6 to drive the supporting rod I7, the tail supporting rod I8, the supporting rod II 71 and the tail supporting rod II 81 to rotate, and the posture of the supporting rod I7, the tail supporting rod I8, the supporting rod II 71 and the tail supporting rod II 81 is adjusted to be changed to be high in matching degree with the environment of a landing area so as to be landed.
As shown in fig. 2: the short-distance/vertical take-off and landing aircraft adopting the variant landing gear comprises a body connecting driving mechanism 111, a retracting rod 112, a pull rod 113, a retracting rod connecting piece 114, a main buffer 115, a rotating mechanism 116, a wheel connecting piece 117 and a front wheel 118;
the main buffer 115 is hinged with the machine body 2 through a machine body connecting and driving mechanism 111, and the pull rod retracting connecting piece 114 is used as an outer cylinder and is fixedly connected with the main buffer 115; the top end of the retracting rod 112 extends to the inner belly part of the fuselage 2, the tail end of the retracting rod 112 is connected with the top end of a pull rod 113, the tail end of the pull rod 113 is hinged with a retracting rod connecting piece 114, a front wheel 118 is fixedly connected with a main buffer 115 through a wheel connecting piece 117 and can rotate around the axis of the main buffer 115 through a rotating mechanism 116, and the rotating angle is 90 degrees.
As shown in fig. 3: the wheeled rear landing gear 12 comprises a rear landing gear link 121, a rear landing gear slide 122, a semi-retractable housing 123, an upper swing arm 124, a bumper 125, a lower swing arm 126 and a rear wheel 127; a rear landing gear slide rail 122 and a rear landing gear connecting piece 121 are arranged in the tail boom vertical tail wing II 101; the semi-retractable housing 123 is mounted on the rear landing gear slide rails 122 and slides in the extending direction of the rear landing gear slide rails 122; the bottom end part of the semi-retractable shell 123 is provided with a shaft hole of a wheel shaft of the assembled airplane wheel 127;
a buffer 125 is fixed at the lower end of the rear landing gear connecting piece 121, the outer side wall of the buffer 125 is hinged with one end of an upper rocker arm 124, the other end of the upper rocker arm 124 is hinged with one end of a lower rocker arm 126, and the other end of the lower rocker arm 126 is hinged with the axle of a rear wheel 127; the bottom end of the buffer 125 is also hinged with the middle part of the arm body of the lower rocker arm 126; the bottom of the semi-retractable shell 123 is provided with a sliding chute to avoid interference with the semi-retractable shell 123 when the wheeled rear landing gear 12 is in bearing action, the symmetrical planes of the tail boom vertical tail wing 10, the semi-retractable shell 123, the upper rocker arm 124, the buffer 125, the lower rocker arm 126 and the rear airplane wheel 127 are coplanar, and when the wheeled rear landing gear 12 is in bearing action, the semi-retractable shell 123 moves up and down along with the movement of the wheeled rear landing gear 12 in the rear landing gear sliding rail 122.
As shown in fig. 4: the short-distance/vertical take-off and landing aircraft runs before take-off and after landing, the short-distance/vertical take-off and landing aircraft is supported on the surface of a take-off/parking area through the wheel type nose landing gear 11 and the wheel type rear landing gear 12 to bear the main weight of the short-distance/vertical take-off and landing aircraft and keep the posture balance, when the aircraft is parked and run, the wheel type nose landing gear 11 is unfolded under the control of the aircraft body connecting driving mechanism 111, meanwhile, the postures of the supporting rod 7 and the tail supporting rod 8 on one side of the short-distance/vertical take-off and landing aircraft, which are far away from the ground, are folded towards the tail part of the aircraft body and adjusted to a flat flight state, the short-distance/vertical take-off and landing aircraft is assisted to carry out control and adjustment, the postures of the supporting rod 7 and the tail supporting rod 8 on the other side are adjusted to be coaxial and are unfolded for a certain angle, and the components of the power system 1 cannot interfere with the ground when the wheel type nose landing aircraft 1 and the wheel type rear landing gear 12 touch the ground.
FIG. 5 shows: adopting the vertical take-off, landing and parking states of the short-distance/vertical take-off and landing aircraft of the variant landing gear; the support rod I7, the tail stay rod I8, the support rod II 71 and the tail stay rod II 81 are controlled by the support rod control steering engine 4 and the tail stay rod control steering engine 6 to be unfolded mutually, the support rod I7 and the tail stay rod I8 are deformed into a straight line shape, and the support rod II 71 and the tail stay rod II 81 are formed into a straight line shape; the first supporting rod 7, the first tail supporting rod 8, the second supporting rod 71 and the second tail supporting rod 81 form a herringbone supporting structure.
As shown in fig. 6: when the aircraft rapidly lands and a tail boom system at one side of the aircraft touches the ground, the rebound time length of the tail boom system is longer than the self-adaptive adjustment time length of the supporting rod and the tail boom rod; at the moment, the first support rod 7 and the first tail support rod 8 are deformed into a linear shape to firstly touch the ground, and the second support rod 71 and the second tail support rod 81 are deformed into an inward-folded shape to secondarily touch the ground.
As shown in fig. 7: when the aircraft rapidly lands and a tail boom system at one side of the aircraft touches the ground, the rebound time length of the tail boom system is shorter than the self-adaptive adjustment time length of the supporting rod and the tail boom rod; at the moment, the first support rod 7 and the first tail support rod 8 are deformed into a straight line shape to firstly touch the ground, and the second support rod 71 and the second tail support rod 81 are deformed into an outward curved shape to secondarily touch the ground.
FIG. 8 shows: in the landing process, because the aircraft encounters asymmetric influence, gravity influence and crosswind influence, secondary adjustment is carried out on the first grounding supporting rod 7, the first tail supporting rod 8, the second supporting rod 71 and the second tail supporting rod 81 to stabilize the aircraft body.
The above description is only a preferred embodiment of the present invention, and does not limit the present invention in any way. It will be understood by those skilled in the art that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (6)
1. A short-reach/vertical-take-off and landing aircraft employing a morphing landing gear, comprising: the airplane tail suspension system comprises a power system (1), an airplane body (2), wings (3), ailerons (5), a tail support system, a wheel type nose landing gear (11) and a wheel type rear landing gear (12); the wings (3) are fixed on the fuselage (2), and the power system (1) is arranged on the wings (3); the wings (3) are provided with ailerons (5); a wheel type nose landing gear (11) is arranged on the body (2); the top surface and the bottom surface of the wing (3) are respectively provided with a tail support system for vertical take-off and landing or short-distance take-off and landing of an aircraft; a wheel type rear landing gear (12) is arranged in the tail support system positioned on the bottom surface of the wing; the tail support system is in an outward opening and closing posture or an inward closing and closing posture;
the tail support system positioned on the bottom surface of the wing supports the aircraft through a wheel type rear landing gear (12) and a wheel type front landing gear (11) of the fuselage (2) for a short-distance take-off and landing mode;
the tail support system positioned on the top surface of the wing and the tail support system positioned on the bottom surface of the wing are opened and closed outwards to form a support posture for a vertical take-off and landing mode of the aircraft;
the wings (3) on the two sides of the fuselage (2) are respectively provided with a tail support system for controlling the top surface of the wing and a support rod control steering engine (4) and a tail support rod control steering engine (6) of the tail support system on the bottom surface of the wing;
the tail boom system positioned on the top surface of the wing (3) comprises a first support rod (7), a first tail boom rod (8), a first tail boom horizontal tail wing (9), a first tail boom vertical tail wing (10), a first support rod pull rod (13) and a first tail boom pull rod (14); the supporting rods I (7) and the tail brace rods I (8) are at least two groups, the supporting rods I (7) and the tail brace rods I (8) are positioned on the top surfaces of the wings (3) on the two sides of the fuselage (2), one end of each supporting rod I (7) is hinged with the wing (3) through a shaft body, the other end of each supporting rod I (7) is hinged with one end of each tail brace rod I (8) through a shaft body, and the other end of each tail brace rod I (8) is provided with a tail brace vertical empennage I (10); a first tail support horizontal tail wing (9) parallel to the wings (3) is arranged between the first tail support rods (8); one end of the first support rod pull rod (13) is fixedly connected with a shaft body of the wing (3) of the first support rod (7), and the other end of the first support rod pull rod (13) is connected with a driving end of a support rod control steering engine (4) on the top surface of the wing; one end of a first tail stay rod (14) is fixedly connected to the shaft body at one end of the first tail stay rod (8), and the other end of the first tail stay rod (14) is connected with a tail stay rod control steering engine (6) on the top surface of the wing;
the tail boom system positioned on the bottom surface of the wing (3) comprises a second support rod (71), a second tail boom rod (81), a second tail boom horizontal tail wing (91) and a second tail boom vertical tail wing (101); a second support rod pull rod (131) and a second tail support rod pull rod (141);
the two supporting rods (71) and the two tail supporting rods (81) are at least two groups and are positioned on the top surfaces of the wings (3) on the two sides of the fuselage (2), one end of each supporting rod (71) is hinged with the corresponding wing (3) through a shaft body, the other end of each supporting rod (71) is hinged with one end of each tail supporting rod (81) through a shaft body, and the other end of each tail supporting rod (81) is provided with a tail supporting vertical tail wing II (101); a second tail brace horizontal tail wing (91) parallel to the wing (3) is arranged between the second tail brace rods (81); one end of the second support rod pull rod (131) is fixedly connected with a shaft body of the wing (3) of the second support rod (71), and the other end of the second support rod pull rod (131) is connected with the driving end of a support rod control steering engine (4) on the bottom surface of the wing; one end of the tail stay bar II (141) is fixedly connected to the shaft body at one end of the tail stay bar II (81), and the other end of the tail stay bar II (141) is connected with the tail stay bar control steering engine (6) on the bottom surface of the wing.
2. The short-reach/vertical-take-off and landing aircraft employing the variant landing gear of claim 1, wherein: the wheeled nose landing gear (11) comprises: the airplane body connecting and driving mechanism (111), the retracting rod (112), the pull rod (113), the retracting rod connecting piece (114), the main buffer (115), the rotating mechanism (116), the airplane wheel connecting piece (117) and the front airplane wheel (118);
the main buffer (115) is hinged with the machine body (2) through a machine body connecting and driving mechanism (111), and the pull rod retracting connecting piece (114) is used as an outer cylinder and fixedly connected with the main buffer (115);
the top of the retracting rod (112) extends to the inner belly of the machine body (2), the tail end of the retracting rod (112) is connected with the top end of the pull rod (113), the tail end of the pull rod (113) is hinged to the retracting rod connecting piece (114), the front wheel (118) is fixedly connected with the main buffer (115) through the wheel connecting piece (117) and can rotate around the axis of the main buffer (115) through the rotating mechanism (116), and the rotating angle is 90 degrees.
3. The short-reach/vertical-take-off and landing aircraft employing the variant landing gear of claim 1, wherein: the wheel type rear landing gear (12) comprises a rear landing gear connecting piece (121), a rear landing gear sliding rail (122), a semi-retractable shell (123), an upper rocker arm (124), a buffer (125), a lower rocker arm (126) and a rear wheel (127); a rear landing gear sliding rail (122) and a rear landing gear connecting piece (121) are arranged in the tail boom vertical tail wing II (101); the semi-retractable shell (123) is assembled on the rear landing gear sliding rail (122) and slides along the extending direction of the rear landing gear sliding rail (122); the bottom end part of the semi-retractable shell (123) is provided with a shaft hole for assembling a wheel shaft of the rear airplane wheel (127);
a buffer (125) is fixed at the lower end of the rear landing gear connecting piece (121), the outer side wall of the buffer (125) is hinged with one end of an upper rocker arm (124), the other end of the upper rocker arm (124) is hinged with one end of a lower rocker arm (126), and the other end of the lower rocker arm (126) is hinged with the axle of a rear wheel (127); the bottom end of the buffer (125) is also hinged with the middle part of the arm body of the lower rocker arm (126);
when the wheel type rear landing gear (12) bears the load, the semi-retractable shell (123) moves up and down along with the wheel type rear landing gear (12) in the rear landing gear sliding rail (122).
4. The short-reach/vertical-take-off and landing aircraft employing the variant landing gear of claim 1, wherein: the distance between the first tail support horizontal tail wing (9) and the gravity center of the aircraft is the sum of the lengths of the first support rod (7) and the first tail support rod (8) or the second support rod (71) and the second tail support rod (81).
5. The short-reach/vertical-take-off and landing aircraft with variant landing gear of claim 1, wherein: when the aircraft carries out the perpendicular descending of self-adaptation, bracing piece control steering wheel (4) and tail vaulting pole control steering wheel (6) drive bracing piece (7), tail vaulting pole (8), bracing piece two (71) and tail vaulting pole two (81) rotate, and adjustment bracing piece (7), tail vaulting pole one (8), bracing piece two (71) and tail vaulting pole two (81) change to descend with the posture of descending regional environment high cooperation degree.
6. The short-reach/vertical-take-off and landing aircraft with variant landing gear according to claim 1 or 3, characterized in that: symmetrical planes of the tail boom vertical tail wing II (101), the semi-retractable shell (123), the upper rocker arm (124), the buffer (125), the lower rocker arm (126) and the rear airplane wheel (127) are uniform and coplanar.
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| CN202110615198.4A CN113291460B (en) | 2021-06-02 | 2021-06-02 | Short-distance/vertical take-off and landing aircraft adopting variant landing gear |
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| CN202110615198.4A CN113291460B (en) | 2021-06-02 | 2021-06-02 | Short-distance/vertical take-off and landing aircraft adopting variant landing gear |
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| CN113291460B true CN113291460B (en) | 2022-11-11 |
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| US7942366B2 (en) * | 2005-06-23 | 2011-05-17 | Karem Aircraft, Inc. | Aircraft landing gear with integrated extension, retraction, and leveling feature |
| CN102897319A (en) * | 2012-08-10 | 2013-01-30 | 江闻杰 | Fuselage variant type vertical take off and landing aircraft |
| US9731816B2 (en) * | 2014-12-08 | 2017-08-15 | The Boeing Company | Multi-position landing gear |
| EP3621876A4 (en) * | 2017-05-13 | 2021-01-27 | Bruno Mombrinie | Stol aircraft |
| CN109911182A (en) * | 2019-01-17 | 2019-06-21 | 清华大学 | A kind of tailstock vertical takeoff and landing vehicle can folding and unfolding shoe undercarriage |
| CN112278228A (en) * | 2019-07-24 | 2021-01-29 | 广州极飞科技有限公司 | Unmanned vehicles's fuselage and unmanned vehicles who has it |
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