CN210592420U

CN210592420U - Manned aircraft

Info

Publication number: CN210592420U
Application number: CN201921109293.1U
Authority: CN
Inventors: 贺军; 房佳琦; 曲长征; 杨鹏; 张秋豪; 熊灿松; 许兴
Original assignee: Zhuhai Tianqing Aerospace Technology Co ltd
Current assignee: Zhuhai Tianqing Aerospace Technology Co ltd
Priority date: 2019-07-15
Filing date: 2019-07-15
Publication date: 2020-05-22
Anticipated expiration: 2029-07-15

Abstract

The utility model discloses a manned aircraft, including aircraft main part, fin, undercarriage, fixed wing subassembly and rotor subassembly. The aircraft utilizes the four rotors formed by the rotor assemblies to realize vertical take-off and landing and cruise of the fixed-wing assemblies, so that the vertical take-off and landing fixed-wing manned aircraft is formed. The utility model discloses realize the quick lift of no needs runway, guarantee the speed and the journey of flight again, and efficient, fast, the journey is long.

Description

Manned aircraft

Technical Field

The utility model relates to an aircraft technical field, in particular to manned aircraft.

Background

Since the Laite brother utility model airplane, the airplane has become an indispensable vehicle in people's life. In recent years, personal airplanes and small manned aircraft have been developed, and there are small fixed-wing manned aircraft and small multi-rotor manned aircraft.

Both of these aircraft have their own disadvantages. The small-sized fixed wing manned aircraft and the large-sized passenger plane need runways for taking off and landing, have higher requirements on the use environment and poor practicability and universality. The multi-rotor manned aircraft does not need a runway for taking off and landing, but because the multi-rotor manned aircraft almost completely depends on the engine to provide lift force, the multi-rotor manned aircraft has the defects of low efficiency, low speed, short flight range and the like.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to solve one of the technical problem that exists among the prior art at least, provide a manned vehicle, neither need the runway, can guarantee the speed and the range of flight again.

According to the utility model discloses an aspect provides a manned vehicle, include: the aircraft comprises an aircraft body, a front end of which is provided with a cockpit, a rear end of which is connected with a tail wing through a connecting rod, and a lower end of which is provided with an undercarriage; the fixed wing assembly comprises a central wing arranged at the upper end of the aircraft body, the central wing comprises a connecting part connected with the upper end of the aircraft body, wing parts extending towards the outer side are arranged on two sides of the connecting part, the rear end of the connecting part is provided with a fixed wing power assembly, and the outer side of each wing part is connected with an outer wing; the rotor subassembly, including setting up in the bracing piece of central authorities' wing and outer wing junction, the bracing piece extends along the fore-and-aft direction, and tip all is provided with horizontal rotor around the bracing piece.

The manned aircraft at least has the following beneficial effects: the aircraft utilizes the four rotors to realize vertical take-off and landing and cruise of the fixed wing assembly, realizes rapid lifting without a runway, ensures the flying speed and range, and has high efficiency, high speed and long range. Meanwhile, the fixed wing power assembly is arranged at the rear part relative to the cockpit, so that the interference to the sight of a pilot is avoided.

According to the utility model discloses first aspect manned vehicle, the vertical rotor that fixed wing power component includes the motor and is connected with the motor. The vertical rotor provides power for this fixed tour of aircraft when navigating.

According to the utility model discloses first aspect manned vehicle, the motor is located connecting portion upper surface rear end.

According to the utility model discloses manned vehicle of first aspect, alar part can be dismantled with the outer wing and be connected. The wing portion and the outer wing can be quickly disassembled and assembled to reduce the storage and transportation space of the aircraft.

According to the utility model discloses first aspect manned vehicle, the fin is T type fin, and fin detachably connects the upside at the connecting rod rear end. The T-shaped empennage has good flight stability, and can complete cruise by being matched with the fixed wing assembly, so that the speed and the range of flight can be guaranteed. The empennage and the connecting rod can be quickly disassembled and assembled so as to reduce the storage and transportation space of the aircraft.

According to the utility model discloses manned vehicle of first aspect, the undercarriage includes front wheel subassembly and rear wheel subassembly. This aircraft undercarriage is wheeled undercarriage, utilizes four rotors to carry out VTOL under the normal condition, if the rotor breaks down the unable VTOL time of reasons such as, can take off and land by the rollingoff.

According to the utility model discloses first aspect manned vehicle, the front wheel subassembly include the loop bar of being connected with aircraft main part lower extreme, the activity cover is equipped with the movable rod in the loop bar, and it has first connecting piece to articulate on the loop bar, and first connecting piece is articulated with a second connecting piece, and second connecting piece middle part is articulated with the movable rod, and second connecting piece upper end is articulated with first connecting piece, and second connecting piece lower extreme is connected with the front wheel. When the movable rod retracted towards the loop bar, the second connecting piece drives the front wheel to swing upwards, so that the front wheel assembly is stored, and the storage and transportation space of the aircraft is reduced.

According to the utility model discloses the first aspect manned vehicle, the rear wheel subassembly include left and right rear wheel portion, and left and right rear wheel portion all includes rear wheel, telescopic link and two piece at least dead levers, and dead lever one end is articulated with aircraft main part lower extreme, and the other end is articulated with the rear wheel, and telescopic link one end is articulated with aircraft main part wall, and the other end is articulated with the rear wheel. When the telescopic link shrink, the dead lever upwards swings and drives the rear wheel upwards swing, realizes that the rear wheel subassembly is accomodate to reduce depositing and the transportation space of aircraft.

According to the utility model discloses first aspect manned vehicle, still including the machine carry the battery, be used for providing the rotor motor of the integrative motor of initiation of stationary vane power component (430) power and be used for providing rotor component (600) power, the machine carries the battery and is used for supplying power for rotor motor, when the aircraft was patrolled and navigated, the integrative motor of initiation charges for the machine carries the battery, can to a great extent alleviate the weight of machine carrying the battery.

Drawings

The present invention will be further described with reference to the accompanying drawings and examples;

fig. 1 is a first schematic structural diagram of an embodiment of the present invention;

fig. 2 is a schematic structural diagram ii according to an embodiment of the present invention;

FIG. 3 is an enlarged view of a portion of FIG. 2 at A;

FIG. 4 is an enlarged view of a portion of FIG. 2 at B;

fig. 5 is a third schematic structural diagram of the embodiment of the present invention;

fig. 6 is a partially enlarged view of C in fig. 5.

Detailed Description

This section will describe in detail the embodiments of the present invention, preferred embodiments of the present invention are shown in the attached drawings, which are used to supplement the description of the text part of the specification with figures, so that one can intuitively and vividly understand each technical feature and the whole technical solution of the present invention, but they cannot be understood as the limitation of the protection scope of the present invention.

In the description of the present invention, it should be understood that the orientation or positional relationship indicated with respect to the orientation description, such as up, down, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, a plurality of means are one or more, a plurality of means are two or more, and the terms greater than, less than, exceeding, etc. are understood as not including the number, and the terms greater than, less than, within, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless there is an explicit limitation, the words such as setting, installation, connection, etc. should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above words in combination with the specific contents of the technical solution.

Referring to fig. 1, 2 and 5, a manned vehicle according to an embodiment of the present invention includes a vehicle body 100, a tail wing 200, a landing gear 300, a fixed wing assembly 400, and a rotor assembly 600.

Wherein, the front end of the aircraft body 100 is provided with a cockpit 110, and the rear end of the aircraft body 100 is connected with a connecting rod 120. The connecting rod 120 in this embodiment extends in the front-rear direction. The aircraft body 100 is connected to the rear wing 200 by a connecting rod 120, and the landing gear 300 is disposed at the lower end of the aircraft body 100.

The fixed wing assembly 400 includes a central wing 410 disposed at the upper end of the aircraft body 100, the central wing 410 includes a connecting portion 411 connected to the upper end of the aircraft body 100, wing portions 412 extending outward are disposed on both sides of the connecting portion 411, a fixed wing power assembly 430 is disposed at the rear end of the connecting portion 411, and an outer wing 420 is connected to the outer side of the wing portions 412. It is understood that the extension of the wing portion 412 towards the outside means that the wing portion 412 extends towards the other side, i.e. the outside, relative to the central wing 410, and the same applies to the outer wing 420 disposed at the outside of the wing portion 412.

The central wing 410 and the outer wing 420 form an upper single wing at the upper end of the aircraft body 100. The fixed wing power assembly 430 is aft of the cockpit 110 and does not interfere with the pilot's view. The aircraft adopts the fixed wing assembly 400 to cruise, has good flight stability, and ensures the speed and range of flight.

Rotor assembly 600 includes a support rod 610 disposed at the junction of central wing 410 and outer wing 420, support rod 610 extending in a fore-aft direction, and a horizontal rotor 620 disposed at each of the fore-aft ends of support rod 610. In this embodiment, the support rod 610 extends in the fore-and-aft direction beyond the length of the junction between the central wing 410 and the outer wing 420, and the horizontal rotary wings 620 provided at the fore and aft ends of the support rod 610 are oppositely disposed at the fore and aft sides of the central wing 410 and the outer wing 420, thereby forming a quad-rotor. The aircraft utilizes four rotors to realize vertical take-off and landing, does not need a runway, and is convenient and fast.

It should be noted that, in this embodiment, the term "extending in the fore-and-aft direction" refers to that the aircraft nose side is "forward" and the aircraft tail side is "aft" along the heading direction of the aircraft.

The aircraft utilizes four rotors to realize vertical take-off and landing and cruise of the fixed-wing assembly 400, realizes rapid lifting without a runway, ensures the flying speed and range, and has high efficiency, high speed and long range.

Referring to fig. 3, the fixed wing power assembly 430 includes a motor 431 and a vertical rotary wing 432 connected to the motor 431. In this embodiment, the rotating axis of the vertical rotor 432 is the heading of the aircraft, and the vertical rotor 432 provides power for the fixed cruise of the aircraft. Further, the motor 431 is located at the rear end of the upper surface of the connecting portion 411.

Referring to fig. 1, 2 and 5, the tail 200 is a T-shaped tail having good flight stability, and cooperating with the fixed wing assembly 400 to complete cruising, the speed and range of flight can be guaranteed.

Meanwhile, the rear wing 200 is detachably coupled to an upper side of the rear end of the connection rod 120. The wing part 412 is detachably coupled to the outer wing 420. The aircraft in the embodiment is mainly a small and medium manned aircraft, and the wing part 412 and the outer wing 420, the tail wing 200 and the connecting rod 120 can be quickly disassembled and assembled, so that the storage and transportation space of the aircraft is reduced.

Referring to fig. 2, 4 and 6, the landing gear 300 includes a front wheel assembly 310 and a rear wheel assembly 320. This aircraft undercarriage 300 is wheeled undercarriage, utilizes four rotors to carry out VTOL under the normal condition, if the rotor breaks down when reasons such as unable VTOL, can take off and land by the rollout.

Referring to fig. 4, the front wheel assembly 310 includes a loop bar 311 connected to the lower end of the aircraft body 100, a movable rod 312 is movably sleeved in the loop bar 311, a first connecting member 315 is hinged to the loop bar 311, the first connecting member 315 is hinged to a second connecting member 313, the middle of the second connecting member 313 is hinged to the movable rod 312, the upper end of the second connecting member 313 is hinged to the first connecting member 315, and the lower end of the second connecting member 313 is connected to a front wheel 314.

When the movable rod 312 retracts towards the loop bar 311, the second connecting part 313 drives the front wheel 314 to swing upwards, so that the front wheel assembly 310 is stored, and the storage and transportation space of the aircraft is reduced.

It should be noted that the term "middle portion of the second connecting member 313" in this embodiment is not a middle portion of the second connecting member 313, and may be a position slightly offset from the middle portion, but should be a space for the hinge connection with the first connecting member 315 and the installation of the front wheel 314.

Referring to fig. 6, the rear wheel assembly 320 includes a left rear wheel portion 320a and a right rear wheel portion 320b, each of the left rear wheel portion 320a and the right rear wheel portion 320b includes a rear wheel 321, an expansion link 322, and at least two fixing rods 323, one end of each fixing rod 323 is hinged to the lower end of the aircraft body 100, the other end of each fixing rod 323 is hinged to the rear wheel 321, one end of each expansion link 322 is hinged to the wall surface of the aircraft body 100, and the other end of each expansion link 322 is hinged to the rear wheel 321.

In this embodiment, the position where the telescopic rod 322 is hinged to the wall surface of the aircraft body 100 is higher than the position where the fixing rod 323 is hinged to the lower end of the aircraft body 100. When the telescopic rod 322 is retracted, the fixing rod 323 swings upwards and drives the rear wheel 321 to swing upwards, so that the rear wheel assembly 320 is accommodated, and the storage and transportation space of the aircraft is reduced.

The power system of the aircraft adopts an enlightening integrated design: this aircraft still includes the airborne battery, is used for providing the integrative motor of enlightening of stationary vane power component 430 power and is used for providing the rotor motor of rotor subassembly 600 power, and the airborne battery is used for supplying power for rotor motor, and when the aircraft was patrolled and navigated, the integrative motor of enlightening was charged for the airborne battery, and the weight of the battery of can very big degree lightening airborne. The integrated motor can also supply power for other airborne equipment.

The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.

Claims

1. A manned vehicle, comprising:

the aircraft comprises an aircraft body (100), wherein a cockpit (110) is arranged at the front end of the aircraft body, a tail wing (200) is connected to the rear end of the aircraft body through a connecting rod (120), and a landing gear (300) is arranged at the lower end of the aircraft body;

the fixed wing assembly (400) comprises a central wing (410) arranged at the upper end of the aircraft body (100), the central wing (410) comprises a connecting part (411) connected with the upper end of the aircraft body (100), wing parts (412) extending towards the outer side are arranged on two sides of the connecting part (411), a fixed wing power assembly (430) is arranged at the rear end of the connecting part (411), and an outer wing (420) is connected to the outer side of each wing part (412);

rotor subassembly (600) is including setting up in bracing piece (610) of central wing (410) and outer wing (420) junction, and bracing piece (610) extend along fore-and-aft direction, and tip all is provided with horizontal rotor (620) around bracing piece (610).

2. The manned vehicle of claim 1, wherein: the fixed wing power assembly (430) includes a motor (431) and a vertical rotor (432) connected to the motor (431).

3. The manned vehicle of claim 2, wherein: the motor (431) is positioned at the rear end of the upper surface of the connecting part (411).

4. The manned vehicle of claim 1, wherein: the wing portion (412) is detachably connected to the outer wing (420).

5. The manned vehicle of claim 1, wherein: the tail wing (200) is a T-shaped tail wing, and the tail wing (200) is detachably connected to the upper side of the rear end of the connecting rod (120).

6. The manned vehicle of claim 1, wherein: the landing gear (300) includes a front wheel assembly (310) and a rear wheel assembly (320).

7. The manned vehicle of claim 6, wherein: front wheel subassembly (310) include loop bar (311) of being connected with aircraft main part (100) lower extreme, and the activity cover is equipped with movable rod (312) in loop bar (311), and it has first connecting piece (315) to articulate on loop bar (311), and first connecting piece (315) are articulated with a second connecting piece (313), and second connecting piece (313) middle part is articulated with movable rod (312), and second connecting piece (313) upper end is articulated with first connecting piece (315), and second connecting piece (313) lower extreme is connected with front wheel (314).

8. The manned vehicle of claim 6, wherein: the rear wheel assembly (320) comprises a left rear wheel portion and a right rear wheel portion (320a and 320b), the left rear wheel portion and the right rear wheel portion (320a and 320b) respectively comprise a rear wheel (321), an expansion link (322) and at least two fixing rods (323), one end of each fixing rod (323) is hinged to the lower end of the aircraft main body (100), the other end of each fixing rod is hinged to the rear wheel (321), one end of each expansion link (322) is hinged to the wall surface of the aircraft main body (100), and the other end of each expansion link is hinged to the rear wheel (321).

9. The manned vehicle of claim 1, wherein: the aircraft power assembly comprises a rotor assembly (600) and is characterized by further comprising an airborne battery, an initiation integrated motor and a rotor motor, wherein the initiation integrated motor is used for providing power for the fixed wing power assembly (430), the rotor motor is used for providing power for the rotor assembly, and the initiation integrated motor charges the airborne battery when the aircraft navigates.