Direct-axis fully actuated variable V-tail motion mechanism

Abstract

The present invention provides a straight-axis, fully movable, variable V-tail kinematic mechanism, belonging to the field of aviation technology. Compared to the traditional "diamond wing + dual-tilted vertical tail + fully movable dual horizontal tail" layout, this reduces a pair of structural wing surfaces, shrinking the aircraft's cross-sectional area, significantly reducing flight drag, lowering the external electromagnetic radiation, and improving stealth performance. Compared to the "diamond wing + dual-tilted, fully movable horizontal tail" layout of the YF-23A demonstrator, this adds the ability to fold and control a pair of tail fins, effectively alleviating the YF-23A demonstrator's problem of excessive tail control. Furthermore, switching to a high-stealth state, a flying-wing layout, further enhances stealth performance.

Description

Technical Field

[0001] The invention belongs to the field of aviation technology and relates to an aircraft tail wing control mechanism. Background Art

[0002] This is a design scheme for a two-degree-of-freedom motion mechanism of a variant tail, which provides the function of switching between the horizontal tail and the V-shaped vertical tail. It provides the aircraft pitch, yaw and roll control torque through a set of mechanisms at the same time, and is widely applicable to the multi-functional control surface structure of variant aircraft.

[0003] In terms of structural layout, it inherits the relatively mature technology of the straight-axis all-moving horizontal tail, and the technical risk is relatively small; there are fewer components, direct force transmission, and high load transmission efficiency; and the entire set of mechanisms is embedded inside, with no protruding external components, and has the stealth performance of a new generation of combat aircraft. Summary of the Invention

[0004] In order to meet the design requirements of the new generation of combat aircraft with high stealth flying wing layout and high maneuverability V-tail layout, such as Figure 1 As shown, the present invention provides a motion mechanism solution for a variable configuration full-motion V-tail: in the high stealth state, the tail is in a horizontal state, which is equivalent to a full-motion horizontal tail; in the high maneuverability state, the tail is folded upward as a whole, which is equivalent to a full-motion V-tail.

[0005] The technical solution adopted by the present invention to solve its technical problem is:

[0006] The straight-axis fully-movable variable V-tail motion mechanism is arranged on the outside of the rear fuselage of the aircraft, and includes the main load-bearing frame of the fuselage, the inner wall of the fuselage, the outer wall of the fuselage, the inner wall slide rail, the actuator bracket, the fork, the sliding joint, the folding actuator, the cross hinge, the tail wing, the rocker arm and the deflection actuator.

[0007] The main load-bearing frame of the fuselage is a ring-shaped fuselage transverse frame plate, which serves as a supporting structure for the engine. A folding actuator connection joint is arranged on the upper edge of the ring frame to connect the folding actuator and at the same time transmit the bending moment load of the tail along the span direction.

[0008] The inner wall of the fuselage is the inner longitudinal frame plate of the fuselage, with a square through hole in the middle. The arc-shaped inner wall slide rail is installed on the edge of the hole to provide guidance for the actuator bracket along the slide rail.

[0009] The outer wall of the fuselage is the longitudinal frame plate on the outside of the fuselage. There is an oblong through hole in the middle for passing the tail shaft. There are square slots on both sides of the oblong through hole for installing cross hinges. There are two sets of joint hinges on the rear belly plate for installing the actuator bracket.

[0010] The actuator bracket is a supporting member composed of three groups of ear joints on the rear, outer and inner sides. The rear joint ear is used to install and connect the deflection actuator, the outer joint ear is used to connect the outer wall joint hinge of the fuselage, and the inner ear joint is used to connect the fork.

[0011] The fork-shaped piece is a humanoid connector composed of three groups of ear joints on the rear side, the upper side and the lower side. The rear side joint ear is used to connect the actuator bracket, and the upper and lower side joint ears are used to connect the sliding joint.

[0012] The sliding joint is a connecting part consisting of three groups of joint ears on the inner side, upper side and lower side, a through hole in the middle and slide grooves on both sides. The joint ears on the inner side are used to connect the piston rod of the folding actuator, the joint ears on the upper and lower sides are used to connect the fork-shaped parts, the through hole in the middle is used to connect the inner fulcrum of the tail wing main shaft, and the slide grooves on both sides are installed on the inner wall slide rails.

[0013] The folding actuator is a linear actuator, which consists of an outer cylinder and a piston rod. The outer cylinder joint is connected to the support joint of the main load-bearing frame of the fuselage, and the piston rod joint is connected to the sliding joint.

[0014] The cross hinge is an annular support with cylinders on both sides. The tail shaft passes through the middle annular through hole with a lubricating layer inside. The tail shaft rotates freely in the through hole. The cylinders on both sides are installed in the slots on the inner wall of the fuselage. The cross hinge as a whole can fold and flip around the cylinder.

[0015] The tail is a straight-axis fully movable control surface. The inner fulcrum is installed to the sliding joint of the inner wall of the fuselage, and the two outer fulcrums are installed to the cross hinge on the outer wall. The tail and the main shaft rotate as a whole along the tail rotation axis.

[0016] The rocker arm is a connecting part with a through hole at the bottom and a fork ear joint at the top. The rocker arm is inserted into the tail wing main shaft through the through hole and fixed. The fork ear joint at the upper end is used to connect the piston rod joint of the deflection actuator.

[0017] The deflection actuator is a linear actuator consisting of an outer cylinder and a piston rod. The outer cylinder joint is connected to the joint ear piece on the rear side of the slide frame, and the piston rod joint is connected to the fork ear joint of the rocker arm.

[0018] Beneficial effects of the present invention:

[0019] Compared with the traditional "diamond wing + double tilted vertical tail + full-moving double horizontal tail" layout, it reduces a pair of structural wing surfaces, reduces the aircraft's cross-sectional area, significantly reduces flight resistance, reduces external electromagnetic radiation, and improves stealth performance;

[0020] Compared with the "diamond wing + double-tilted full-moving horizontal tail" layout of the YF-23A verification aircraft, it has added a pair of tail folding control capabilities, effectively alleviating the problem of excessive tail wing control burden of the YF-23A verification aircraft; and switching to a high stealth state with a flying wing layout can further enhance stealth performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the high stealth layout and high maneuverability layout of an embodiment of the present invention, wherein (a) is a stereoscopic diagram in the high stealth state, (b) is a front view in the high stealth state; (c) is a stereoscopic diagram in the high maneuverability state, and (d) is a front view in the high maneuverability state.

[0022] Figure 2 The schematic diagram of the structure of the embodiment of the present invention is shown in FIG. Figure 1 , (b) is a schematic diagram Figure 2 .

[0023] Figure 3 It is a schematic diagram of the main load-bearing frame structure of the fuselage according to an embodiment of the present invention.

[0024] Figure 4 It is a schematic diagram of the inner side wall of the fuselage and the inner side wall slide rail structure of an embodiment of the present invention.

[0025] Figure 5 Schematic diagram of the outer wall structure of the fuselage of an embodiment of the present invention, wherein (a) is a front stereoscopic view, (b) is a rear stereoscopic view; (c) is a main view, (d) is a side view, and (e) is a top view.

[0026] Figure 6 Schematic diagram of an actuator bracket according to an embodiment of the present invention.

[0027] Figure 7 Schematic diagram of a fork according to an embodiment of the present invention.

[0028] Figure 8 Schematic diagram of a sliding joint according to an embodiment of the present invention, wherein (a) is a front perspective view and (b) is a rear perspective view.

[0029] Figure 9 Schematic diagram of a folding actuator according to an embodiment of the present invention, wherein (a) is a tightened state and (b) is an extended state.

[0030] Figure 10 Schematic diagram of a cross hinge according to an embodiment of the present invention.

[0031] Figure 11 2 is a schematic diagram of a tail wing according to an embodiment of the present invention.

[0032] Figure 12Schematic diagram of the rocker arm of an embodiment of the present invention, wherein (a) is a stereoscopic diagram, (b) is a main view, and (c) is a schematic diagram of the connection with the main shaft of the tail wing.

[0033] Figure 13 Schematic diagram of a deflection actuator according to an embodiment of the present invention, wherein (a) is a tightened state and (b) is an extended state.

[0034] Figure 14 It is a schematic diagram of the assembly relationship of the mechanism of an embodiment of the present invention.

[0035] Figure 15 It is a schematic diagram of the assembly relationship of the mechanism of an embodiment of the present invention.

[0036] Figure 16 It is a schematic diagram of the assembly relationship of the mechanism of an embodiment of the present invention.

[0037] Figure 17 Schematic diagram of the folding movement principle of the mechanism of an embodiment of the present invention, wherein (a) is the flattened state and (b) is the folded state.

[0038] Figure 18 Schematic diagram of the deflection motion principle of the mechanism of an embodiment of the present invention, wherein (a) is the tail wing downward deflection state, and (b) is the tail wing upward deflection state.

[0039] In the figure: 1 tail wing, 2 rocker arm, 3 deflection actuator, 4 fuselage outer wall, 5 fuselage inner wall, 6 sliding joint, 7 fuselage main load-bearing frame, 8 folding actuator, 9 inner wall slide rail, 10 fork, 11 actuator bracket, 12 rotating straight shaft, 13 cross hinge, 14 folding actuator connecting joint, 15 oblong through hole, 16 joint hinge, 17 square slot, 18 joint ear on the outer side of the actuator bracket, 19 joint ear on the rear side of the actuator bracket, 20 inside the actuator bracket Joint lug, 21 joint lug on the upper side of the fork-shaped piece, 22 joint lug on the lower side of the fork-shaped piece, 23 joint lug on the rear side of the fork-shaped piece, 24 slide groove, 25 joint lug on the inner side of the sliding joint, 26 joint lug on the upper side of the sliding joint, 27 joint lug on the lower side of the sliding joint, 28 lubrication layer in the hole, 29 fork lug joint, 30 pin hole, 31 through hole, 32 tail rudder surface, 33 tail shaft, 34 pin, A tail rotation axis, B tail folding axis, C outer fulcrum, D inner fulcrum. DETAILED DESCRIPTION

[0040] The straight-axis fully movable variable V-tail motion mechanism is an aircraft tail wing control mechanism, which is arranged on the outside of the rear fuselage of the aircraft. The control mechanism mainly includes the fuselage main load-bearing frame, the fuselage inner wall, the fuselage outer wall, the inner wall slide rail, the actuator bracket, the fork, the sliding joint, the folding actuator, the cross hinge, the tail, the rocker arm and the deflection actuator, as well as several connecting fasteners. The specific structural composition is as follows Figure 2 shown.

[0041] The main load-bearing frame of the fuselage is a circular fuselage transverse frame plate, which serves as the supporting structure of the engine. A folding actuator connection joint is arranged on the upper edge of the ring frame to connect the folding actuator and transmit the bending moment load of the tail along the span direction. Figure 3 shown.

[0042] The inner wall of the fuselage is the inner longitudinal frame plate of the fuselage, with a square through hole in the middle. The arc-shaped inner wall slide rail is installed on the edge of the hole to provide guidance for the actuator bracket along the slide rail, such as Figure 4 shown.

[0043] The outer wall of the fuselage is the outer longitudinal frame plate of the fuselage. There is an oblong through hole in the middle for passing the tail shaft. There are square slots on both sides of the oblong through hole for installing the cross hinge. There are two sets of joint hinges on the rear belly plate for installing the actuator bracket, such as Figure 5 shown.

[0044] The actuator bracket is a supporting member composed of three sets of ear joints on the rear side, the outer side and the inner side. The rear side joint ear is used to install and connect the deflection actuator, the outer side joint ear is used to connect the outer wall joint hinge of the fuselage, and the inner side ear joint is used to connect the fork-shaped piece, such as Figure 6 shown.

[0045] The fork is a humanoid connector consisting of three sets of lug joints at the rear, upper and lower sides. The rear lug joint is used to connect the actuator bracket, and the upper and lower lug joints are used to connect the sliding joints, such as Figure 7 shown.

[0046] The sliding joint is a connector consisting of three sets of joint lugs on the inner side, upper side and lower side, a through hole in the middle and slide grooves on both sides. The joint lugs on the inner side are used to connect the piston rod of the folding actuator, the joint lugs on the upper and lower sides are used to connect the fork-shaped parts, the through hole in the middle is used to connect the inner support point of the tail shaft, and the slide grooves on both sides are installed on the inner wall slide rails, such as Figure 8 shown.

[0047] The folding actuator is a conventional linear actuator, consisting of an outer cylinder and a piston rod. Considering the large bending moment transmitted by the tail wing, a double-cylinder or triple-cylinder actuator can be used. The outer cylinder joint is connected to the support joint of the main load-bearing frame of the fuselage, and the piston rod joint is connected to the sliding joint. Figure 9 shown.

[0048] The cross hinge is an annular support with cylinders on both sides. The tail shaft passes through the middle annular through hole with a lubricating layer. The tail shaft rotates freely in the through hole. The cylinders on both sides are installed in the slots on the inner wall of the fuselage. The cross hinge can be folded and turned around the cylinders. Figure 10 shown.

[0049] The tail is a conventional straight-axis full-moving control surface. The inner fulcrum is installed on the sliding joint of the inner wall of the fuselage, and the two outer fulcrums are installed on the cross hinge of the outer wall. The tail and the main shaft rotate as a whole along the tail rotation axis. Figure 11 shown.

[0050] The rocker arm is a connector with a through hole at the bottom and a fork ear joint at the top. The rocker arm is inserted into the tail shaft through the through hole and connected to the shaft with 2 to 3 sets of pins. The fork ear joint at the top is used to connect the piston rod joint of the deflection actuator, such as Figure 12 shown.

[0051] The deflection actuator is a conventional linear actuator, consisting of an outer cylinder and a piston rod. The outer cylinder joint is connected to the joint ear piece on the rear side of the slide frame, and the piston rod joint is connected to the fork ear joint of the rocker arm, such as Figure 13 shown.

[0052] The assembly relationship of the straight-axis full-motion V-tail mechanism is as follows:

[0053] First, complete the positioning and installation of the fuselage main load-bearing frame, the fuselage inner wall, the fuselage outer wall and the inner wall slide rail on the fuselage, then install the sliding joint to the inner wall slide rail, and install the cross hinge into the fuselage outer wall slot, such as Figure 14 shown.

[0054] Then, insert the tail shaft into the cross hinge, rocker arm, and sliding joint of the outer wall of the fuselage. Use nuts to fix the inner support end of the shaft at the sliding joint to prevent the tail and the rotating shaft from falling out. Then connect the outer tube joint and piston rod joint of the folding actuator to the support joint of the main load-bearing frame of the fuselage and the joint ear piece inside the sliding joint respectively. Figure 15 shown.

[0055] Finally, connect the outer joint ear of the actuator bracket to the joint hinge on the outer wall web of the fuselage, and then connect the rear side and upper and lower joint ears of the fork-shaped member to the inner ear joint of the actuator bracket and the upper and lower joint ears of the sliding joint respectively. Connect the outer tube joint and piston rod joint of the deflection actuator to the rear joint ear of the actuator bracket and the fork ear joint at the upper end of the rocker arm respectively. Figure 16 shown.

[0056] The motion principle of the direct-axis full-motion V-tail mechanism is as follows:

[0057] The principle of the folding movement is to use the cross hinge installed inside the outer wall of the fuselage as the turning fulcrum, and to push the sliding joint through the piston rod joint of the folding actuator to move along the inner fulcrum of the inner wall along the slide rail of the inner wall, thereby driving the rotating main shaft to drive the entire tail to fold upward, thereby realizing the switching of the tail from the flat state to the folding state. Figure 17During the entire movement process, the actuator bracket, fork, sliding joint, rocker arm and deflection actuator all follow the sliding joint to move on the inner wall slide rail.

[0058] The principle of deflection movement is to drive the rocker arm on the main shaft through the linear telescopic movement of the deflection actuator, and together with the tail wing, to deflect up and down. The outer tube joint of the deflection actuator is hingedly installed on the actuator bracket. One end of the actuator bracket is hinged to the outer wall joint of the fuselage, and the other end is hinged to the sliding joint through a fork to keep the outer tube joint of the deflection actuator in a fixed state. Figure 18 shown.

Claims

1. Direct-axis fully variable V-tail motion mechanism, characterized by: It is arranged on the outside of the rear fuselage of the aircraft, including the main load-bearing frame of the fuselage, the inner wall of the fuselage, the outer wall of the fuselage, the inner wall slide rail, the actuator bracket, the fork, the sliding joint, the folding actuator, the cross hinge, the tail, the rocker arm and the deflection actuator; The main load-bearing frame of the fuselage is a circular fuselage transverse frame plate, which serves as the support structure of the engine. A folding actuator connection joint is arranged on the upper edge of the circular fuselage transverse frame plate, which is used to connect the folding actuator and at the same time transmit the bending moment load of the tail along the span direction; The inner wall of the fuselage is the inner longitudinal frame plate of the fuselage, with a square through hole in the middle. The arc-shaped inner wall slide rail is installed on the edge of the square through hole to provide guidance for the actuator bracket along the slide rail; The outer wall of the fuselage is the outer longitudinal frame plate of the fuselage. There is an oblong through-hole in the middle for passing the tail shaft. There are square slots on both sides of the oblong through-hole for installing cross hinges. There are two sets of joint hinges on the rear belly plate for installing the actuator bracket. The actuator bracket is a supporting member consisting of three sets of joint lugs: rear, outer and inner. The rear joint lugs are used to install and connect the deflection actuator, the outer joint lugs are used to connect to the outer wall joint hinge of the fuselage, and the inner joint lugs are used to connect to the fork. The fork is a humanoid connector consisting of three sets of connector lugs on the rear, upper, and lower sides. The rear connector lugs are used to connect to the actuator bracket, while the upper and lower connector lugs are used to connect to the sliding joint. The sliding joint is a connector consisting of three sets of joint lugs on the inner, upper and lower sides, a middle through-hole, and two side slides. The inner joint lugs are used to connect to the piston rod of the folding actuator, the upper and lower joint lugs are used to connect to the fork-shaped piece, the middle through-hole is used to connect to the inner support point of the tail shaft, and the two side slides are installed on the inner wall slide rails. The folding actuator is a linear actuator, consisting of an outer cylinder and a piston rod. The outer cylinder joint is connected to the support joint of the main load-bearing frame of the fuselage, and the piston rod joint is connected to the sliding joint. The cross hinge is an annular support with cylinders on both sides. The tail shaft passes through the annular hole in the middle. There is a lubricating layer in the annular hole. The tail shaft rotates freely in the annular hole. The cylinders on both sides are installed in the square slots on the outer wall of the fuselage. The cross hinge can be folded and turned around the cylinders. The tail is a straight-axis, fully movable control surface. The inner fulcrum is mounted to the sliding joint on the inner wall of the fuselage, and the two outer fulcrums of the tail are mounted to the cross hinge on the outer wall. The tail and the tail shaft rotate as a whole along the tail axis. The rocker arm is a connector with a through hole at the bottom and a fork ear joint at the top. The rocker arm is inserted through the through hole and fixed to the main shaft of the tail wing. The fork ear joint at the top is used to connect to the piston rod joint of the deflection actuator. The deflection actuator is a linear actuator consisting of an outer cylinder and a piston rod. The outer cylinder joint is connected to the joint ear on the rear side of the actuator bracket, and the piston rod joint is connected to the fork ear joint of the rocker arm.

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