CN106697261B - A kind of aircraft double freedom control surface - Google Patents

Abstract

The invention discloses a kind of aircraft double freedom control surfaces, comprising: T shape shaft, axial rocker arm, lateral steering engine, cross-brace bearing, control surface, steering engine cable, lateral rocker arm, axial spring bearing, pedestal and axial steering engine；Wherein, the T shape shaft includes lateral shaft and longitudinal shaft, wherein lateral shaft is connected with longitudinal shaft, wherein the longitudinal direction shaft is located in the pedestal；The longitudinal direction shaft is connected by axial spring bearing with pedestal；The control surface is connected by the cross-brace bearing with the lateral shaft.The present invention solves the problems, such as that existing control surface control moment is single, realizes that axially and transversely double freedom rotates control surface around aircraft.

Description

A dual-degree-of-freedom control surface for an aircraft

technical field

The invention relates to the field of overall design of aircraft, in particular to a dual-degree-of-freedom control surface of an aircraft.

Background technique

Conventional aircraft often use multiple control surfaces to generate forces and moments to maintain or change the attitude of the aircraft. Usually, the control surface is limited by the structural form, the control surface in different positions, the direction of the torque is different, and the control function is also different. The advanced aerodynamic layout of the aircraft eliminates multiple control surfaces that are not conducive to stealth, usually with a highly integrated shape, and the radar cross section is greatly reduced. Good maneuverability, the existing technical solution is to use a combination of split rudder/wing tip rudder and multiple sets of elevons.

SUMMARY OF THE INVENTION

The technical problem solved by the present invention is: compared with the prior art, a dual-degree-of-freedom control surface of an aircraft is provided, which solves the problem that the control torque of the existing control surface is single, and realizes the dual freedom of the control surface around the aircraft in the axial and lateral directions. degree of rotation.

The object of the present invention is achieved through the following technical solutions: a dual-degree-of-freedom control surface for an aircraft, which is characterized by comprising: a T-shaped rotating shaft, an axial rocker arm, a lateral steering gear, a lateral support bearing, a control surface, a steering gear cable, a lateral rocker Arm, axial support bearing, base and axial steering gear; wherein, the T-shaped rotating shaft includes a lateral rotating shaft and a longitudinal rotating shaft, wherein the lateral rotating shaft and the longitudinal rotating shaft are connected, wherein the longitudinal rotating shaft is located on the base inside; the longitudinal rotating shaft is connected to the base through an axial support bearing; the control surface is connected to the lateral rotating shaft through the lateral support bearing; the longitudinal rotating shaft is connected to the axial rudder through the axial rocker arm The axial steering gear is arranged in the base; the lateral rotating shaft is connected with the lateral steering gear through the lateral rocker arm, and the lateral steering gear is connected with the control surface; the longitudinal steering gear is connected with the control surface; The upper half of the rotating shaft is provided with a first cavity, the transverse rotating shaft is provided with a second cavity, the first cavity is communicated with the second cavity, and the steering gear cable is passed through the first cavity. A cavity and the second cavity are connected with the lateral steering gear.

In the above-mentioned dual-degree-of-freedom control surface of the aircraft, the axial rocker arm is sleeved on the longitudinal rotation shaft, wherein the axial rocker arm is provided with a through hole, and the longitudinal rotation shaft is provided with a through hole with the axial rocker arm The other corresponding through hole is used for fixedly connecting the axial rocker arm and the longitudinal rotating shaft through the pin passing through the through hole of the axial rocker arm and the through hole of the longitudinal rotating shaft.

In the above-mentioned dual-degree-of-freedom control surface of the aircraft, the lateral rocker arm is sleeved on the lateral rotating shaft, wherein the lateral rocker arm is provided with a through hole, and the lateral rotating shaft is provided with a through hole corresponding to the lateral rocker arm. The other through hole is used for fixing the connection between the lateral rocker arm and the lateral rotating shaft through the pin passing through the through hole of the lateral rocker arm and the through hole of the lateral rotating shaft.

In the above-mentioned dual-degree-of-freedom control surface of the aircraft, the axial rocker arm is provided with a first fork-shaped lug, and the shaft of the axial steering gear is connected with the first fork-shaped lug.

In the above-mentioned dual-degree-of-freedom control surface of the aircraft, the lateral rocker arm is provided with a second fork-shaped lug, and the shaft of the lateral steering gear is connected with the second fork-shaped lug.

In the above-mentioned dual-degree-of-freedom control surface of the aircraft, the control surface is provided with a first mounting bracket, and the lateral steering gear is fixedly connected to the mounting bracket.

In the above-mentioned dual-degree-of-freedom control surface of the aircraft, a second mounting bracket is arranged in the base, and the axial steering gear is connected with the second mounting bracket.

The above-mentioned dual-degree-of-freedom control surface of the aircraft further comprises: a rotating shaft support seat, the rotating shaft support seat is arranged in the base, and the T-shaped rotating shaft is arranged in the rotating shaft support seat.

Compared with the prior art, the present invention has the following beneficial effects:

(1) The present invention realizes that the operation surface of the aircraft rotates around the aircraft with two degrees of freedom in the axial and lateral directions through the T-shaped rotating shaft, and realizes the control torque for the three directions of pitch, roll and yaw of the aircraft;

(2) The present invention enables the operation surface to automatically rotate around the aircraft with both axial and lateral degrees of freedom through the axial steering gear and the lateral steering gear.

Description of drawings

1 is a schematic structural diagram of an aircraft dual-degree-of-freedom control surface of the present invention;

Fig. 2 is another structural schematic diagram of the aircraft dual-degree-of-freedom control surface of the present invention;

FIG. 3 is a partial structural schematic diagram of an aircraft dual-degree-of-freedom control surface of the present invention.

Detailed ways

Below in conjunction with accompanying drawing, the present invention is described in further detail:

FIG. 1 is a schematic structural diagram of an aircraft dual-degree-of-freedom control surface of the present invention. FIG. 2 is another structural schematic diagram of the aircraft dual-degree-of-freedom control surface of the present invention. As shown in Figures 1 and 2, the aircraft's dual-degree-of-freedom control surface includes a T-shaped rotating shaft 1, an axial rocker arm 2, a lateral steering gear 3, a control surface lateral support bearing 4, a control surface 5, a steering gear cable 6, a lateral steering gear The rocker arm 7, the axial support bearing 8, the base 9, the rotating shaft support seat 10 and the axial steering gear 11; wherein,

The T-shaped rotating shaft 1 includes a lateral rotating shaft 110 and a longitudinal rotating shaft 120 , wherein the lateral rotating shaft 110 and the longitudinal rotating shaft 120 are connected, wherein the lateral rotating shaft 110 is located in the base 9 . Specifically, the lateral rotating shaft 110 and the longitudinal rotating shaft 120 are vertically connected to each other; the longitudinal rotating shaft 120 is a simply supported beam structure and is a moving shaft; the lateral rotating shaft 110 is a cantilever beam structure and is a fixed axis. It should be noted that the dual-DOF control surface of the aircraft is installed on the aircraft, the lateral rotation shaft 110 is parallel to the lateral direction of the aircraft, and the longitudinal rotation shaft 120 is parallel to the axial direction of the aircraft.

The longitudinal shaft 120 is connected to the base 9 through the axial support bearing 8 . Specifically, the support bearing 8 is fixedly connected to the base 9 , the longitudinal shaft 120 is arranged in the axial support bearing 8 , the axial direction of the longitudinal shaft 120 is the same as the axial direction of the axial support bearing 8 , and the longitudinal shaft 120 can surround its axial direction turn.

The control surface 5 is connected with the lateral rotation shaft 110 through the lateral support bearing 4 . Specifically, the lateral rotating shaft 110 is disposed in the lateral supporting bearing 4 , the axial direction of the lateral rotating shaft 110 is the same as that of the lateral supporting bearing 4 , and the control surface 5 can rotate around the axial direction of the lateral rotating shaft 110 . Further, since the control surface 5 is connected with the lateral shaft 110 , when the longitudinal shaft 120 rotates, the lateral shaft 110 is driven to rotate around the longitudinal shaft 120 , thereby driving the control surface 5 to rotate around the longitudinal shaft 120 .

The longitudinal rotation shaft 120 is connected to the axial steering gear 11 through the axial rocker arm 2 , and the axial steering gear 11 is arranged in the base 9 . Specifically, the axial rocker arm 2 is fixedly connected to the longitudinal rotating shaft 120 , and the axial steering gear 11 is rotatably connected to the axial rocker arm 2 . When the axial steering gear 11 works, the axial rocker arm 2 will move left and right in FIG. 1 . , thereby driving the longitudinal shaft 120 to rotate around its axial direction. It should be understood that the axial steering gear 11 also needs to be connected to an external controller through a cable, and the movement of the axial steering gear 11 is controlled by the controller.

The lateral rotating shaft 110 is connected to the lateral steering gear 3 through the lateral rocker arm 7 , and the lateral steering gear 3 is connected to the control surface 5 . Specifically, the lateral rocker arm 7 is fixedly connected to the lateral rotating shaft 110, the lateral steering gear 3 is rotatably connected to the lateral rocker arm 7, and the lateral steering gear 3 is fixedly connected to the other end of the control surface 5. When the lateral steering gear 3 is working, due to the lateral rocker arm 7 is fixedly connected with the lateral rotating shaft 110, the lateral rocker arm 7 and the lateral rotating shaft 110 are in a static state, and the lateral steering gear 3 will move. The shaft 110 rotates.

The upper half of the longitudinal shaft 120 is provided with a first cavity 121 , the transverse shaft 110 is provided with a second cavity 111 , the first cavity 121 is communicated with the second cavity 111 , and the steering gear cable 6 is passed through the first cavity. The cavity 121 and the second cavity 111 are connected with the lateral steering gear 3 . Specifically, by arranging the steering gear cables 6 , space is saved and the steering gear cables 6 are well protected. The steering gear cable 6 also needs to be connected to the controller, and the movement of the lateral steering gear 3 is controlled by the controller.

During operation, under the control of the axial steering gear 11, the longitudinal rotation shaft 120 is driven to rotate by the axial rocker arm 2 to realize the axial rotation of the control surface 5 around the longitudinal rotation shaft 120; The arm 7 drives the control surface 5 to rotate around the lateral rotation axis 110; the composite control of the axial steering gear 11 and the lateral steering gear 3 can realize the rotation of the control surface around the aircraft's axial and lateral dual degrees of freedom, and realize the pitch and roll of the aircraft. Control torque in 3 directions of turn and yaw.

This embodiment realizes that the operation surface of the aircraft rotates around the aircraft with two degrees of freedom in the axial and lateral directions through the T-shaped rotating shaft, and realizes the control torque for the three directions of pitch, roll and yaw of the aircraft; and in this embodiment, the axial rudder is used. The motor and lateral steering gear can make the control surface automatically rotate around the aircraft with both axial and lateral degrees of freedom.

As shown in FIG. 1 , the axial rocker arm 2 is sleeved on the longitudinal rotation shaft 120 , wherein the axial rocker arm 2 is provided with a through hole, and the longitudinal rotation shaft 120 is provided with another through hole corresponding to the through hole of the axial rocker arm 2 , the axial rocker arm 2 and the longitudinal rotation shaft 120 are fixedly connected through the first pin 121 passing through the through hole of the axial rocker arm 2 and the through hole of the longitudinal rotation shaft 120 .

As shown in FIG. 1 , the lateral rocker arm 7 is sleeved on the lateral rotation shaft 110, wherein the lateral rocker arm 7 is provided with a through hole, and the lateral rotation shaft 110 is provided with another through hole corresponding to the through hole of the lateral rocker arm 7. Two pins 111 pass through the through holes of the lateral rocker arm 7 and the through holes of the lateral rotation shaft 110 to fixedly connect the lateral rocker arm 7 and the lateral rotation shaft 110 .

FIG. 3 is a partial structural schematic diagram of an aircraft dual-degree-of-freedom control surface of the present invention. As shown in FIG. 3 , the axial rocker arm 2 is provided with a first fork-shaped lug 210 , and the shaft of the axial steering gear 11 is connected with the first fork-shaped lug 210 . Specifically, the shaft of the axial steering gear 11 is rotatably connected to the first fork-shaped lug 210 , so that the axial rocker arm 2 is driven to rotate through the axial steering gear 11 , thereby driving the longitudinal rotation shaft 120 to rotate.

FIG. 3 is a partial structural schematic diagram of an aircraft dual-degree-of-freedom control surface of the present invention. The lateral rocker arm 7 is provided with a second fork-shaped lug 710 , and the shaft of the lateral steering gear 3 is connected with the second fork-shaped lug 710 . Specifically, the shaft of the lateral steering gear 3 is rotatably connected to the second fork-shaped lug 710 .

In the above embodiment, as shown in FIG. 1 , the control surface 5 is provided with a first mounting bracket 51 , and the lateral steering gear 3 is fixedly connected to the first mounting bracket 51 . The first mounting bracket 51 plays a role of fixing and supporting the lateral steering gear 3 .

In the above embodiment, as shown in FIG. 1 , the base 9 is provided with a second mounting bracket 91 , and the axial steering gear 11 is connected with the second mounting bracket 91 . The second mounting bracket 91 plays a role of fixing and supporting the axial steering gear 11 .

In the above embodiment, as shown in FIG. 1 , the aircraft dual-degree-of-freedom control surface further includes: a rotating shaft support seat 10 , which is arranged in the base 9 , and a T-shaped rotating shaft 1 is arranged in the rotating shaft support seat 10 . The rotating shaft support seat 10 plays a supporting and fixing role on the T-shaped rotating shaft 1 .

The invention realizes that the operation surface of the aircraft rotates around the aircraft with two degrees of freedom in the axial direction and the lateral direction through the T-shaped rotating shaft, and realizes the control torque for the three directions of pitch, roll and yaw of the aircraft; and the invention uses the axial steering gear and The lateral steering gear can automatically rotate the control surface around the aircraft with two degrees of freedom in the axial and lateral directions.

The above-mentioned embodiments are only preferred specific implementations of the present invention, and general changes and substitutions made by those skilled in the art within the scope of the technical solutions of the present invention should be included in the protection scope of the present invention.

Claims (8)

1. A two degree-of-freedom control surface for an aircraft, comprising: the device comprises a T-shaped rotating shaft (1), an axial rocker arm (2), a transverse steering engine (3), a transverse supporting bearing (4), a control surface (5), a steering engine cable (6), a transverse rocker arm (7), an axial supporting bearing (8), a base (9) and an axial steering engine (11); wherein,

the T-shaped rotating shaft (1) comprises a transverse rotating shaft (110) and a longitudinal rotating shaft (120), wherein the transverse rotating shaft (110) is connected with the longitudinal rotating shaft (120), and the longitudinal rotating shaft (120) is positioned in the base (9);

the longitudinal rotating shaft (120) is connected with the base (9) through an axial supporting bearing (8);

the control surface (5) is connected with the transverse rotating shaft (110) through the transverse supporting bearing (4);

the longitudinal rotating shaft (120) is connected with an axial steering engine (11) through the axial rocker arm (2), and the axial steering engine (11) is arranged in the base (9);

the transverse rotating shaft (110) is connected with a transverse steering engine (3) through the transverse rocker arm (7), and the transverse steering engine (3) is connected with the control surface (5);

first cavity (121) have been seted up to first half of longitudinal rotating shaft (120), second cavity (111) have been seted up in transverse rotating shaft (110), first cavity (121) with second cavity (111) are linked together, steering wheel cable (6) wear to locate first cavity (121) with second cavity (111) and with transverse steering wheel (3) are connected.

2. The aircraft two-degree-of-freedom control surface of claim 1, wherein: the axial rocker arm (2) is sleeved on the longitudinal rotating shaft (120), wherein a through hole is formed in the axial rocker arm (2), another through hole corresponding to the through hole of the axial rocker arm (2) is formed in the longitudinal rotating shaft (120), and the axial rocker arm (2) is fixedly connected with the longitudinal rotating shaft (120) through the through hole of the axial rocker arm (2) and the through hole of the longitudinal rotating shaft (120) which are penetrated through pins.

3. The aircraft two-degree-of-freedom control surface of claim 1, wherein: horizontal rocking arm (7) cover is located horizontal pivot (110), wherein, the through-hole has been seted up in horizontal rocking arm (7), another through-hole corresponding with the through-hole of horizontal rocking arm (7) is seted up in horizontal pivot (110), passes the through-hole of horizontal rocking arm (7) and the through-hole of horizontal pivot (110) through the pin with horizontal rocking arm (7) and horizontal pivot (110) fixed connection.

4. The aircraft two-degree-of-freedom control surface of claim 2, wherein: the axial rocker arm (2) is provided with a first fork lug (210), and the shaft of the axial steering engine (11) is connected with the first fork lug (210).

5. The aircraft two-degree-of-freedom control surface of claim 3, wherein: the transverse rocker arm (7) is provided with a second forked lug (710), and the shaft of the transverse steering engine (3) is connected with the second forked lug (710).

6. The aircraft two-degree-of-freedom control surface of claim 1, wherein: the control surface (5) is provided with a first mounting bracket (51), and the transverse steering engine (3) is fixedly connected with the first mounting bracket (51).

7. The aircraft two-degree-of-freedom control surface of claim 1, wherein: a second mounting bracket (91) is arranged in the base (9), and the axial steering engine (11) is connected with the second mounting bracket (91).

8. The aircraft two degree-of-freedom control surface of claim 1, further comprising: the rotating shaft supporting seat (10), the rotating shaft supporting seat (10) is arranged in the base (9), and the T-shaped rotating shaft (1) is arranged in the rotating shaft supporting seat (10).