A roll adjustment method for a twin-hull lift-float integrated aircraft

Abstract

The application discloses a kind of double hulls lift-float integrated aircraft roll adjusting method, it is related to aircraft design technical field, using the form of auxiliary air bag control, main air bag control and full-motion horizontal tail control combination to carry out double hulls lift-float integrated aircraft roll adjusting, using the mode that auxiliary air bag is connected with atmosphere environment and air is pumped out, main air bag is connected and helium is pumped out, full-motion horizontal tail deflection, changes the lift distribution of aircraft, buoyancy distribution, so that aircraft generates roll torque, adjusts aircraft roll angle.The double hulls lift-float integrated aircraft roll adjusting method that the application adopts has significantly improved the aircraft roll adjusting efficiency, is conducive to improving the maneuverability and safety of aircraft, compared with the existing aircraft attitude adjusting mode, combines the characteristics of double hulls lift-float integrated aircraft, aircraft roll adjusting mechanism work can generate greater moment change, aircraft has very high adjusting capacity to attitude.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft design, in particular to a roll adjustment method of a double-hull lift-float integrated aircraft. BACKGROUND

[0002] The double-hull lift-float integrated aircraft is a kind of aircraft with two helium-filled hulls similar to airships and large-aspect-ratio wings similar to solar unmanned aerial vehicles. Due to the need for high-altitude long-endurance flight, it is crucial to maintain the aircraft in the most efficient design flight attitude to complete the uninterrupted flight across day and night. The lift-float integrated aircraft is affected by both lift and buoyancy, which enables the aircraft to change its attitude by adjusting the distribution of lift and buoyancy. This method is quite different from traditional aircraft and airships, and has a great impact on the control ability and flight safety of the aircraft.

[0003] Currently, the roll adjustment method of high-altitude long-endurance solar unmanned aerial vehicles is to adjust the roll by deflecting the ailerons. Stratospheric airships do not have a roll adjustment method. However, due to the structural characteristics of large-scale hulls and large-aspect-ratio wings, the double-hull lift-float integrated aircraft is dangerous in take-off and landing state, and needs to maintain the high-efficiency design state as much as possible in cruising state. If the roll adjustment method is simply based on the traditional aircraft adjustment method, the control surfaces will be arranged on the wings, which will increase the weight, pose a danger to the wings, and reduce the efficiency of attitude adjustment. Therefore, it is important to improve the roll adjustment efficiency of the aircraft with the smallest weight cost by utilizing the structural characteristics of the lift-float integrated aircraft, which is crucial for improving the performance and safety of the double-hull lift-float integrated aircraft. SUMMARY

[0004] The purpose of the present application is to provide a roll adjustment method of a double-hull lift-float integrated aircraft to improve the roll adjustment efficiency of the aircraft and improve the performance and safety of the double-hull lift-float integrated aircraft.

[0005] To achieve the above purpose, the present application provides a roll adjustment method of a double-hull lift-float integrated aircraft, comprising the following steps:

[0006] Step one, turn on the aileron air pump and wing inter-main airbag air pump device in the left hull and right hull;

[0007] Step two, according to the roll direction, one of the left hull aileron air pump and the right hull aileron air pump inhales air, and the other one exhausts air. The wing air duct inter-main airbag air pump device is turned on, and the gas in the main airbag changes with the suction of the main airbag air pump and the change of the volume of the auxiliary airbag;

[0008] Step three, after the aircraft generates a roll moment, turn off the aileron air pump and wing inter-main airbag air pump device of the left hull and right hull, and turn on the elevator control.

[0009] Step four, the full moving horizontal tail of the hull body is deflected in the pitching direction according to the rolling direction;

[0010] Step five, the aircraft is deflected to a certain angle, and the full moving horizontal tail continues to maintain the deflected angle until the rolling action is completed;

[0011] Step six, when the rolling action is completed, the elevator is reversely deflected, and the auxiliary air bag air pump and the wing inter-main air bag air pump device are reversely opened until the aircraft returns to the balanced state.

[0012] Preferably, the left boat and the right boat in step one both comprise a boat body and a full moving horizontal tail, the full moving horizontal tail is arranged at the rear end of the boat body, and the boat body is internally provided with a front auxiliary air bag, a rear auxiliary air bag and a main air bag.

[0013] Preferably, the left boat and the right boat have wings, the wings comprise front wings and rear wings, the rear wings and the front wings are both internally provided with air channels, and the air channels are both internally provided with wing inter-main air bag air pump devices.

[0014] Preferably, the air exhaust direction of the front auxiliary air bag and the air exhaust direction of the rear auxiliary air bag are the same in step two, and the air exhaust direction of the auxiliary air bag of the left boat and the air exhaust direction of the auxiliary air bag of the right boat are opposite.

[0015] Preferably, the gas in the main air bag is helium in step two, and the helium is transported through the wing air channels.

[0016] Preferably, the deflection directions of the full moving horizontal tail of the left boat and the full moving horizontal tail of the right boat are opposite in step four.

[0017] Preferably, the full moving horizontal tail is connected with the boat body through a rotating shaft.

[0018] Therefore, the double-boat-body lifting integrated aircraft rolling adjustment method with the above structure has the following beneficial effects:

[0019] (1) The aircraft rolling adjustment efficiency is significantly improved, and the controllability and safety of the aircraft are improved.

[0020] (2) The aircraft pitching adjustment mechanism can produce a large moment change in combination with the characteristics of the double-boat-body lifting integrated aircraft, and the aircraft has high adjustment ability for the attitude.

[0021] (3) Through the attitude adjustment method, the control surface is avoided to be installed on the wing of the aircraft, the main load-bearing component of the aircraft does not bear additional load in the control state, and the structural safety is high.

[0022] (4) On the basis of the original aircraft shape, only the wing inner main airbag connecting structure and the full-moving tail structure are added, and the weight of the structure and mechanism paid for additional control of the aircraft basic configuration is reduced.

[0023] The technical solutions of the present application are further described below with reference to the drawings and examples. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 Figure 1 is a structural schematic diagram of an embodiment of a roll adjustment method of a dual-hull lifting and floating integrated aircraft of the present application.

[0025] REFERENCE NUMERALS

[0026] 1, left boat; 2, right boat; 3, front auxiliary airbag; 4, rear auxiliary airbag; 5, main airbag; 6, full-moving horizontal tail; 7, air duct, 8, front wing; 9, rear wing. DETAILED DESCRIPTION

[0027] The technical solutions of the present application are further described below with reference to the drawings and examples.

[0028] Unless otherwise defined, technical terms or scientific terms used in the present application shall be understood as their ordinary meanings to those of ordinary skill in the art to which the present application pertains. The terms "first", "second", and similar terms used in the present application do not denote any order, quantity, or importance, but are used to distinguish different components. The terms "include" or "contain" and similar terms mean that the elements or objects before the terms encompass the elements or objects listed after the terms and their equivalents, and do not exclude other elements or objects. The terms "connect" or "connected" and similar terms are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. The terms "up", "down", "left", "right", and the like are used only to indicate relative positional relationships, and when the absolute positions of the described objects change, the relative positional relationships may also change accordingly.

[0029] EMBODIMENT

[0030] The present application provides a roll adjustment method of a dual-hull lifting and floating integrated aircraft, comprising the following steps:

[0031] Step 1: Turn on the auxiliary airbag air pump and the wing inner main airbag air pump device in the left boat and the right boat.

[0032] Step two, according to the rolling direction, one of the left and right boat auxiliary air bag air pump inhales air, and the other one exhausts air, the air exhaust direction of the front auxiliary air bag and the rear auxiliary air bag is the same, the air exhaust direction of the left auxiliary air bag and the right auxiliary air bag is opposite, one side air bag exhaust air, the side of the fuselage becomes light, generates rolling torque, the air valve in the wing air duct is opened, the helium in the main air bag changes with the auxiliary air bag, the helium in the main air bag of one side of the fuselage is drawn into the main air bag of the other side of the fuselage, the side of the fuselage becomes light, generates rolling torque;

[0033] Step three, after the aircraft generates rolling torque, the left and right boat auxiliary air bag air pump and the wing main air bag air pump device are closed, and the elevator control is opened.

[0034] Step four, according to the rolling direction, the movable horizontal tail of the boat body is deflected, the deflected side of the movable horizontal tail is deflected downward, the angle of attack is reduced, the lift of the horizontal tail is reduced, and the movable horizontal tail of the other side is deflected upward, the angle of attack is increased, the lift of the horizontal tail is increased, and the rolling torque is generated.

[0035] Step five, the aircraft is deflected to a certain angle, and the movable horizontal tail continues to maintain the deflected angle until the rolling action is completed.

[0036] Step six, when the rolling action is completed, the elevator is reversely deflected, the auxiliary air bag air pump and the wing main air bag air pump device are reversely opened, until the aircraft returns to the balanced state.

[0037] In step one, the left boat 1 and the right boat 2 each include a boat body movable horizontal tail 6, which is arranged at the rear end of the boat body, and a front auxiliary air bag 3, a rear auxiliary air bag 4 and a main air bag 5 are arranged in the boat body.

[0038] The front auxiliary air bag 3 and the rear auxiliary air bag 4 of the left and right boat bodies are controlled by air pump, and the air pump is connected with the inside and outside of the auxiliary air bag and the atmosphere, which can inhale air and exhaust air, adjust the size of the auxiliary air bag and the pressure in the whole boat body, change the position of the whole machine gravity center, and the air exhaust direction of the front and rear auxiliary air bags is the same, but the air exhaust direction of the auxiliary air bags of the left and right sides of the fuselage is opposite, at this time, the gravity distribution of the left and right sides of the fuselage is unbalanced, and the rolling torque is generated.

[0039] The left boat 1 and the right boat 2 are provided with wings, the wings include front wings 8 and rear wings 9, the front wings 8 and the rear wings 9 are provided with air ducts 7, the helium in the main air bag 5 can be transferred from the two air ducts 7, and the transfer efficiency is improved, the air ducts 7 are provided with wing main air bag air pump devices, and the helium is transported through the air ducts 7. The wing main air bag air pump device is connected with the main air bag 5 of the two boat bodies, which can inhale helium and exhaust helium. Adjust the size of the main air bag 5 and the buoyancy distribution of the left and right sides of the fuselage, change the position of the whole machine buoyancy center, and provide rolling torque.

[0040] The movable horizontal tail 6 of the left boat 1 and the movable horizontal tail 6 of the right boat 2 deflect in opposite directions, and the movable horizontal tail 6 is connected to the boat body through a rotating shaft. The horizontal movable horizontal tail 6 can increase and decrease the angle of attack, increase the generated lift and decrease the generated lift, to provide a pitch moment. In addition, the tail of the left and right boat bodies can also be differentially, to generate a roll moment.

[0041] In specific use, when the aircraft wants to roll to the left, the front and rear auxiliary air bags on the left side simultaneously suck in air, the front and rear auxiliary air bags on the right side simultaneously discharge air, the left side of the aircraft becomes heavy and the right side of the aircraft becomes light relative to the balanced state, to generate a left roll moment, and the aircraft generates left roll; at the same time of the auxiliary air bag control, the gas valve between the left main air bag 5 and the right main air bag 5 works, the helium in the left main air bag 5 is extracted into the right main air bag 5, the left side has less helium and small buoyancy, and the right side has more helium and large buoyancy relative to the balanced state, to generate a left roll moment, and the aircraft generates left roll. The auxiliary air bag and the main air bag 5 work simultaneously, after the air bag works, the elevator works, the movable horizontal tail 6 of the left side of the aircraft body deflects upward, the angle of attack decreases, and the horizontal tail lift decreases, while the movable horizontal tail 6 of the right side of the aircraft body deflects downward, the angle of attack increases, and the horizontal tail lift increases, to generate a left roll moment, and the aircraft rolls to the left. The elevator operation plays a fine tuning role, and the elevator provides a smaller force but has high accuracy.

[0042] When the aircraft wants to roll to the right, the front and rear auxiliary air bags on the left side simultaneously discharge air, the front and rear auxiliary air bags on the right side simultaneously suck in air, the right side of the aircraft becomes heavy and the left side of the aircraft becomes light relative to the balanced state, to generate a right roll moment, and the aircraft generates right roll; at the same time of the auxiliary air bag control, the gas valve between the left main air bag 5 and the right main air bag 5 works, the helium in the right main air bag 5 is extracted into the left main air bag 5, the left side has more helium and large buoyancy, and the right side has less helium and small buoyancy relative to the balanced state, to generate a right roll moment, and the aircraft generates right roll; the movable horizontal tail 6 of the left side of the aircraft body deflects downward, the angle of attack increases, and the horizontal tail lift increases, while the movable horizontal tail 6 of the right side of the aircraft body deflects upward, the angle of attack decreases, and the horizontal tail lift decreases, to generate a right roll moment, and the aircraft rolls to the right.

[0043] Therefore, the roll adjustment method of a twin-hull lifting integrated aircraft adopted in the present invention significantly improves the roll adjustment efficiency of the aircraft, which is beneficial to improving the maneuverability and safety of the aircraft; the present invention combines the characteristics of the twin-hull lifting integrated aircraft, and the aircraft pitch adjustment mechanism can produce a large torque change, and the aircraft has a high attitude adjustment ability; through this attitude adjustment method, the installation of control surfaces on the aircraft wings is avoided, and the main load-bearing components of the aircraft do not bear additional loads in the control state, and the structural safety is high; on the basis of the original shape of the aircraft, only the main airbag connection structure in the wing and the full-moving horizontal tail structure are added, which reduces the weight of the structure and mechanism paid for control outside the basic configuration of the aircraft.

[0044] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit the same. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solutions of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A roll adjustment method for a twin-hull buoyant aircraft, characterized in that: The following steps are involved: Step 1: Turn on the auxiliary airbag pumps in the left and right boats and the main airbag pump device between the wings; the left and right boats include a hull and a full-moving horizontal tail, a wing is set between the left and right boats, and a main airbag is set in the hull. The gas in the main airbag is helium, and the helium is transported through the wing air duct; Step 2: Depending on the roll direction, the left and right auxiliary airbag pumps draw in air and discharge air respectively. The main airbag pumps in the wing airways are activated, and the gas in the main airbags changes with the pumping of the main airbags and the volume of the auxiliary airbags. The helium in the main airbag on one side of the hull is drawn into the main airbag on the other side. The hull on the side where the helium is drawn in becomes lighter, generating a rolling moment. Step 3: After the aircraft generates a rolling moment, the auxiliary airbag pumps of the left and right boats and the main airbag pump device between the wings are turned off, and the elevator control is turned on; Step 4: Pitch the tail of the full-moving horizontal stabilizer according to the rolling direction of the boat; the full-moving horizontal stabilizer of the left boat and the full-moving horizontal stabilizer of the right boat are deflected in opposite directions; Step 5: The aircraft deflects to a certain angle, and the fully movable horizontal tail continues to maintain the deflection angle until the rolling action is completed; Step 6: When the rolling action is completed, the elevator is deflected in the opposite direction, and the auxiliary airbag pump and the main airbag pump device between the wings are opened in the opposite direction until the aircraft returns to a balanced state.

2. The roll adjustment method for a twin-hull buoyant aircraft according to claim 1, characterized in that: In step 1, the fully movable horizontal tail is arranged at the rear end of the hull, and the hull is provided with a front auxiliary airbag, a rear auxiliary airbag and a main airbag.

3. The roll adjustment method for a twin-hull buoyant aircraft according to claim 2, characterized in that: The wing comprises a front wing and a rear wing. Air ducts are arranged in the rear wing and the front wing, and main air bag air pump devices between the wings are arranged in the air ducts.

4. The roll adjustment method for a twin-hull buoyant aircraft according to claim 3, characterized in that: In step 2, the pumping and exhausting directions of the front auxiliary airbag and the rear auxiliary airbag are the same, and the pumping and exhausting directions of the auxiliary airbags of the left boat are opposite to those of the right boat.

5. The roll adjustment method for a twin-hull buoyant aircraft according to claim 4, characterized in that: The fully movable horizontal tail is connected to the hull through a rotating shaft.

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