Two-point dual-balance wheel off-road aircraft

Abstract

The present invention discloses a two-point dual-balance wheel cross-country aircraft, comprising a fuselage, a left wing and a right wing arranged on the fuselage, an optoelectronic pod installed at the front end of the fuselage, a power system installed at the rear end of the fuselage, a left aileron rudder surface and a right aileron rudder surface respectively arranged on the left wing and the right wing, a wheel hub power cabin pylon fusion body is arranged on the left wing and the right wing, a wheel hub power cabin pylon fusion body is arranged on the wheel hub power cabin pylon fusion body, a tail strut is arranged below the left wing and the right wing, the other ends of the two tail struts are connected to a horizontal tail stabilizer, a heading stabilizer is arranged in the middle of one side of the horizontal tail stabilizer, and a rudder surface is arranged on the heading stabilizer. The two-point dual-balance wheel cross-country aircraft of the present invention has a simple and reliable principle, is simpler than a conventional take-off and landing system, is easier and safer to take off and land, and has a shorter landing distance.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft landing gear systems, and in particular relates to a two-point double-balance wheel cross-country aircraft. Background Art

[0002] Fixed-wing aircraft have excellent endurance and load-bearing capacity, and their application has penetrated into various fields. However, the take-off and landing of fixed-wing aircraft is limited by the site environment. For the take-off and landing on the open hard ground in the wild, the fixed-wing aircraft is required to have off-road take-off and landing, and can adapt to various complex field environments. However, the take-off and landing runways in the open field are uneven, and larger diameter wheels are required to ensure that the fixed-wing aircraft can take off in the field. The large-diameter wheels with a front and rear three-point layout require larger landing gear struts, which will cause the landing gear system to be bulky and have large flight resistance. In addition, the take-off angle of attack of the fixed-wing aircraft is fixed when taking off and landing. The take-off and runway distance remains unchanged when the other performance of the aircraft remains unchanged. Because the main landing gear of the aircraft lands first at a positive angle of attack during landing, the pilot's control technology and flight control technology are required to be more stringent. Therefore, it is urgent to improve the existing off-road aircraft to facilitate the operation of fixed-wing aircraft in various complex sites. Summary of the invention

[0003] To solve the above problems, the object of the present invention is to provide a two-point dual-balance wheel cross-country aircraft.

[0004] A two-point double-balance wheel off-road aircraft comprises a fuselage, a left wing and a right wing arranged on the fuselage, an optoelectronic pod is installed at the front end of the fuselage, a power system is installed at the rear end of the fuselage, a left aileron control surface and a right aileron control surface are respectively provided on the left wing and the right wing, a wheel hub power cabin pylon fusion body is provided on the left wing and the right wing, a wheel hub power cabin pylon fusion body is provided on the wheel hub power cabin pylon fusion body, a tail strut is installed below the left wing and the right wing, the other ends of the two tail struts are connected to a horizontal tail stabilizer, a heading stabilizer is provided in the middle of one side of the horizontal tail stabilizer, and a rudder surface is provided on the heading stabilizer.

[0005] Furthermore, the wheel rim is mounted on the wheel hub power compartment bracket fusion body through a limit shock absorber, the limit shock absorber includes a bearing, a bearing retaining member, a spring and two sleeves, the sleeve is arranged in a hole on the wheel hub power compartment bracket fusion body, a spring is installed outside the sleeve, the bearing retaining member is provided with a pin shaft and a bearing mounting hole that cooperate with the sleeve, the pin shaft is inserted in the sleeve, and the bearing is installed in the bearing mounting hole on the bearing retaining member.

[0006] To ensure the smooth rotation of the wheel rim, the number of the limit shock absorbers is 5.

[0007] Furthermore, a bracket is provided on the outer surface of the wheel hub power compartment bracket fusion body.

[0008] Furthermore, the limit shock absorber is installed in a U-shaped limit base on the wheel hub power compartment bracket fusion body.

[0009] To ensure the smooth rotation of the wheel rim, the bearing is a U-groove bearing.

[0010] Furthermore, the wheel hub power tank bracket fusion body is a wheel hub fuel tank bracket fusion body. At this time, the center of the wheel rim 2 is located directly below the center of gravity of the aircraft, and the center of gravity of the aircraft is located before the aerodynamic focus of the aircraft, so as to absorb impact force when the aircraft lands.

[0011] Furthermore, the wheel hub power compartment rack fusion is a wheel hub battery compartment rack fusion, the lower half of the wheel hub battery compartment rack fusion is provided with a battery box and a rack, and the upper half is a hollow structure, so that the center of the wheel rim is located directly below the center of gravity of the aircraft, and the center of gravity of the aircraft is located in front of the aerodynamic focus of the aircraft, so as to absorb impact force when the aircraft lands.

[0012] Furthermore, the horizontal tail stabilizer is provided with elevator surfaces, and the elevator surfaces are evenly distributed on both sides of the heading stabilizer and rotate relative to the horizontal tail stabilizer at the same time.

[0013] Compared with the prior art, the two-point double-balance wheel cross-country aircraft of the present invention has the following beneficial effects: the two-point double-balance wheel cross-country aircraft of the present invention has a simple and reliable principle, is more concise than a conventional take-off and landing system, is easier and safer to take off and land, and has a shorter landing distance. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a schematic diagram of the structure of Embodiment 1 of the present invention;

[0015] Figure 2 is a top view of embodiment 1 of the present invention;

[0016] Figure 3 This is a front view of Embodiment 1 of the present invention;

[0017] Figure 4 It is a left side view of Embodiment 1 of the present invention;

[0018] Figure 5 It is a partial enlarged view of the limit shock absorber of Example 1 of the present invention;

[0019] Figure 6 This is a schematic diagram of the structure of Embodiment 2 of the present invention;

[0020] Figure 7 It is a left view of embodiment 2 of the present invention.

[0021] As shown in the figure, 1-limited shock absorber, 2-wheel rim, 3-wheel hub fuel tank bracket fusion, 4-right wing, 5-right aileron control surface, 6-left wing, 7-left aileron control surface, 8-horizontal stabilizer surface, 9-elevator surface, 10-heading stabilizer surface, 11-direction rudder surface, 12-power system, 13-fuselage, 14-photoelectric pod, 15-wheel hub battery compartment bracket fusion, 16-battery box, 17-rack, 21-bearing, 22-bearing retainer, 23-sleeve, 24-spring. DETAILED DESCRIPTION

[0022] The principles and features of the present invention are described below in conjunction with embodiments. The embodiments are only used to explain the present invention and are not used to limit the scope of the present invention.

[0023] Example 1

[0024] like Figure 1-5 As shown, a two-point dual-balance wheel off-road aircraft comprises a fuselage 13, a left wing 6 and a right wing 4 arranged on the fuselage 13, an optoelectronic pod 14 is installed at the front end of the fuselage 13, a power system 12 is installed at the rear end of the fuselage 13, a left aileron control surface 7 and a right aileron control surface 5 are respectively provided on the left wing 6 and the right wing 4, a hub power cabin pylon fusion body is provided on the left wing 6 and the right wing 4, a wheel rim 2 is provided on the hub power cabin pylon fusion body, tail struts are installed below the left wing 6 and the right wing 4, the other ends of the two tail struts are connected to a horizontal tail stabilizer 8, a heading stabilizer 10 is provided in the middle of one side of the horizontal tail stabilizer 8, and a rudder surface 11 is provided on the heading stabilizer 10.

[0025] Furthermore, the wheel rim 2 is installed on the wheel hub power compartment bracket fusion body through a limit shock absorber 1. The limit shock absorber 1 includes a bearing 21, a bearing retaining member 22, a spring 24 and two sleeves 23. The sleeve 23 is arranged in a hole on the wheel hub power compartment bracket fusion body. A spring 24 is installed outside the sleeve. The bearing retaining member 22 is provided with a pin shaft and a bearing mounting hole that cooperate with the sleeve 23. The pin shaft is inserted in the sleeve 23. The bearing 21 is installed in the bearing mounting hole on the bearing retaining member 22. The outer ring of the wheel rim 2 is rubber, and the inner ring is a rigid metal ring.

[0026] Furthermore, a bracket 17 is provided on the outer surface of the hub power compartment bracket fusion body.

[0027] Furthermore, the limit shock absorber 1 is installed in a U-shaped limit base on the wheel hub power compartment bracket fusion body.

[0028] In order to ensure the smooth rotation of the wheel rim 2, the bearing 21 is a U-groove bearing.

[0029] Furthermore, the wheel hub power tank bracket fusion body is a wheel hub fuel tank bracket fusion body 3. At this time, the center of the wheel rim 2 is located directly below the center of gravity of the aircraft, and the center of gravity of the aircraft is located before the aerodynamic focus of the aircraft, so as to absorb impact force when the aircraft lands.

[0030] Furthermore, the horizontal tail stabilizer 8 is provided with elevator surfaces 9, which are evenly distributed on both sides of the heading stabilizer 8 and rotate relative to the horizontal tail stabilizer 8 at the same time. The left and right elevator surfaces 9 and the rudder surface 11 are in the engine propeller slipstream area.

[0031] This embodiment adopts a horizontal two-point layout, and the two wheel rims 2 are fixed on the hub fuel tank rack fusion body 3 through the limit shock absorber 1. The limit shock absorber 1 is arranged along the edge of the hub fuel tank rack fusion body 3, and has the function of fixing the wheel rim and realizing the take-off and landing of the fixed-wing aircraft; the fuel is stored in the hub fuel tank rack fusion body 3, so that the center of the wheel rim 2 is located directly below the center of gravity of the aircraft, and the center of gravity of the aircraft is located in front of the aerodynamic focus of the aircraft, so as to absorb the impact force when the aircraft lands.

[0032] Example 2

[0033] like Figure 6 , 7 As shown, a two-point dual-balance wheel off-road aircraft comprises a fuselage 13, a left wing 6 and a right wing 4 arranged on the fuselage 13, an optoelectronic pod 14 is installed at the front end of the fuselage 13, a power system 12 is installed at the rear end of the fuselage 13, a left aileron control surface 7 and a right aileron control surface 5 are respectively provided on the left wing 6 and the right wing 4, a hub power cabin pylon fusion body is provided on the left wing 6 and the right wing 4, a wheel rim 2 is provided on the hub power cabin pylon fusion body, tail struts are installed below the left wing 6 and the right wing 4, the other ends of the two tail struts are connected to a horizontal tail stabilizer 8, a heading stabilizer 10 is provided in the middle of one side of the horizontal tail stabilizer 8, and a rudder surface 11 is provided on the heading stabilizer 10.

[0034] Furthermore, the wheel hub power compartment rack fusion body is a wheel hub battery compartment rack fusion body 15, the lower half of the wheel hub battery compartment rack fusion body 15 is provided with a battery box 16 and a rack 17, and the upper half is a hollow structure, so that the center of the wheel rim 2 is located directly below the center of gravity of the aircraft, and the center of gravity of the aircraft is located before the aerodynamic focus of the aircraft, so as to absorb the impact force when the aircraft lands. The wheel hub battery compartment rack fusion body 15 is equivalent to an enlarged bearing, and a plurality of steel balls are provided between the inner steel ring and the outer steel ring, and rubber is provided outside the outer steel ring.

[0035] Furthermore, the horizontal tail stabilizer 8 is provided with elevator surfaces 9, which are evenly distributed on both sides of the heading stabilizer 8 and rotate relative to the horizontal tail stabilizer 8 at the same time. The left and right elevator surfaces 9 and the rudder surface 11 are in the engine propeller slipstream area.

[0036] During the take-off and landing stage of the present invention, the aircraft relies on the principle of a tumbler and can be parked horizontally. When the aircraft starts to taxi, the flight control system is used to drive the elevator surface 9 to ensure the balance of the aircraft's attitude. The elevator surface 9 is located behind the propeller, and the slipstream generated by the propeller is used to make the elevator surface 9 more efficient. When accelerating to the take-off speed, the elevator surface is stretched to take off. When landing, the aircraft is kept stable in the flight control system laterally, and the pitch direction does not need to consider attitude control. It can land at a negative angle of attack. In the landing taxiing stage, the inertia of the aircraft nose is used to increase the windward area downward to achieve a short-distance landing.

[0037] The two-point double-balance wheel cross-country aircraft of the present invention has a simple and reliable principle, is more concise, easier and safer to take off and land, and has a shorter landing distance than a conventional take-off and landing system.

[0038] The protection scope of the present invention is not limited to the technical solutions disclosed in the specific implementation methods. Any modifications, equivalent replacements, improvements, etc. made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. Two-point dual-balance wheel off-road aircraft, characterized by: The invention comprises a fuselage, a left wing and a right wing arranged on the fuselage, an optoelectronic pod is installed at the front end of the fuselage, a power system is installed at the rear end of the fuselage, a left aileron control surface and a right aileron control surface are respectively provided on the left wing and the right wing, a wheel hub power cabin pylon fusion body is provided on the left wing and the right wing, a wheel rim is provided on the wheel hub power cabin pylon fusion body, the center of the wheel rim is located directly below the center of gravity of the aircraft, and the center of gravity of the aircraft is located before the aerodynamic focus of the aircraft, tail struts are installed below the left wing and the right wing, the other ends of the two tail struts are connected to a horizontal tail stabilizer, a heading stabilizer is provided in the middle of one side of the horizontal tail stabilizer, and a rudder surface is provided on the heading stabilizer.

2. The two-point dual-balance wheel off-road aircraft according to claim 1, characterized in that: The wheel rim is mounted on the wheel hub power compartment bracket fusion body through a limit shock absorber. The limit shock absorber includes a bearing, a bearing retaining member, a spring and two sleeves. The sleeve is arranged in a hole on the wheel hub power compartment bracket fusion body. A spring is installed outside the sleeve. The bearing retaining member is provided with a pin shaft and a bearing mounting hole that cooperate with the sleeve. The pin shaft is inserted in the sleeve, and the bearing is mounted in the bearing mounting hole on the bearing retaining member.

3. The two-point dual-balance wheel off-road aircraft according to claim 1 or 2, characterized in that: The outer surface of the wheel hub power compartment bracket fusion body is provided with a bracket.

4. The two-point dual-balance wheel off-road aircraft according to claim 2, characterized in that: The limit shock absorber is installed in a U-shaped limit base on the wheel hub power compartment bracket fusion body.

5. The two-point dual-balance wheel off-road aircraft according to claim 2, characterized in that: The bearing is a U-groove bearing.

6. The two-point dual-balance wheel off-road aircraft according to claim 1 or 2, characterized in that: The wheel hub power compartment bracket fusion body is a wheel hub fuel compartment bracket fusion body.

7. The two-point dual-balance wheel off-road aircraft according to claim 1, characterized in that: The wheel hub power compartment rack fusion body is a wheel hub battery compartment rack fusion body, the lower half of the wheel hub battery compartment rack fusion body is provided with a battery box and a rack, and the upper half is a hollow structure.

8. The two-point dual-balance wheel off-road aircraft according to claim 1, characterized in that: The horizontal tail stabilizer is provided with elevator surfaces, and the elevator surfaces are evenly distributed on both sides of the heading stabilizer.

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