Unmanned aerial vehicle airspeed tube pop-up mechanism with locking function

Abstract

The invention discloses an unmanned aerial vehicle airspeed tube pop-up mechanism with a locking function. According to the extension type airspeed tube mechanism provided by the invention, extension and extension of the airspeed tube of the unmanned aerial vehicle and position locking of the airspeed tube after the airspeed tube is extended in place are realized, and the problems that the distance between a fixed airspeed tube mounted on a traditional barrel (box) type launching unmanned aerial vehicle and a wing / fuselage is relatively small, and data measurement is inaccurate due to turbulent flow of the wing / fuselage to airspeed calculation are solved. Two groups of locking function modules are designed in a limited space envelope, and fit clearances between locking pins and pin holes in the two groups of locking function modules are different in size. The large gap ensures that the pin can be locked in, the small gap ensures that the pin can be locked tightly, the two gaps are matched and complemented with each other, and the reliability of the mechanism locking function module is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of morphing aircraft, and in particular to a UAV airspeed tube ejection mechanism with locking function. BACKGROUND

[0002] In order to achieve long-range flight performance, high lift, etc., the UAV usually adopts large wing span lifting body aerodynamic layout. However, the defect of large wing span lifting body aerodynamic layout occupying large space is contradictory to the constraint of limited loading space of the launch platform, which seriously limits the number of one-time loading and launching of the UAV by the launch platform. The morphing wing technology is the core technology for the UAV to break through the constraint of the narrow loading space of the launch platform, and is the key foundation for improving the mobility and flight distance of the UAV and increasing the number of one-time loading and launching of the UAV by the launch platform. The morphing mechanism is the core component of the morphing wing technology, and is the core device for realizing the switching of the UAV from the folded state in the barrel (box) before launching to the unfolded flight state after launching out of the barrel (box).

[0003] The large wing span lifting body morphing UAV reduces the volume by multiple folding of the main wing, side wing, tail wing and airspeed tube before launching, and is accommodated in the launch barrel (box). After the UAV is ejected from the barrel (box), the main wing, side wing, tail wing and airspeed tube device are unfolded under the common driving of multiple morphing mechanisms, realizing the switching of the UAV from the folded and accommodated state in the barrel (box) before launching to the unfolded flight state after launching out of the barrel (box).

[0004] The core functions of the morphing mechanism include driving the unfolding of the main wing, side wing, tail wing and airspeed tube of the UAV and realizing the position and angle locking after unfolding. Due to the constraint of limited loading space, the airspeed tube installed on the barrel (box) launching UAV is usually close to the wing / fuselage. Due to the small distance between the airspeed tube and the wing / fuselage, the wing / fuselage has a disturbance effect on the airspeed tube, which makes it difficult to accurately measure the airspeed data. SUMMARY

[0005] The present application provides a UAV airspeed tube ejection mechanism with locking function, which can be applied to the morphing mechanism system of a large wing span lifting body morphing UAV, and can realize the extension and position locking of the airspeed tube on the barrel (box) launching UAV after extension.

[0006] In a first aspect, a UAV airspeed tube ejection mechanism with locking function is provided, comprising an ejection function module and a locking function module.

[0007] The pop-out function module includes a pitot tube, a housing, a pop-out compression spring, and an end cap. The pop-out compression spring is housed inside the housing, and the pitot tube and the end cap are respectively located at both ends of the pop-out compression spring. The end cap is fixed to the first end of the housing and contacts and presses against the first end of the pop-out compression spring. The second end of the pop-out compression spring presses against the step of the pitot tube, and the pitot tube extends out from the second end of the housing under the drive of the pop-out compression spring.

[0008] The pitot tube has a recessed groove inside the step for accommodating the locking module 1. The locking module 1 includes a locking pin and a locking compression spring. One end of the locking compression spring presses against the bottom of the recessed groove of the pitot tube step, and the other end presses against the rear end face of the locking pin, for driving the locking pin to move in a direction perpendicular to the extension of the pitot tube. In addition, the inner side wall of the housing has a sliding groove. When the pitot tube moves under the drive of the pop-out compression spring, the locking pin inside the pitot tube step moves in the sliding groove of the housing. The sliding groove restricts the locking pin from popping out of the recessed groove inside the pitot tube step. A pin hole is provided at the end of the sliding groove away from the end cover, and the pin hole is used to engage with the locking pin.

[0009] In conjunction with the first aspect, in some implementations of the first aspect, the pop-out function module uses a pop-out compression spring as a power source to drive the airspeed tube to move along the axial direction of the pop-out compression spring, thereby switching the airspeed tube from a retracted state to an extended state.

[0010] The locking pin in the locking function module is driven by a locking compression spring. Before the airspeed tube moves to the target position, the locking pin is always in contact with the groove on the inner wall of the housing. After the airspeed tube moves to the target position, the locking compression spring in the locking function module drives the locking pin to insert into the pin hole on the housing, thereby locking the position of the airspeed tube.

[0011] In conjunction with the first aspect, in some implementations of the first aspect, the mechanism has two symmetrical sets of locking function modules.

[0012] In conjunction with the first aspect, in some implementations of the first aspect, the fit clearance between the locking pin and the pin hole is different in the two sets of locking function modules.

[0013] Compared with the prior art, the solution provided by the present invention has at least the following beneficial technical effects:

[0014] 1) Due to limited loading space constraints, the fixed pitot tube installed on cannon (box)-launched UAVs is usually close to the wing / fuselage. The extended pitot tube mechanism proposed in this invention enables the extension of the UAV pitot tube and its position locking after extension, solving the problem of inaccurate data measurement caused by the turbulence of the wing / fuselage on the pitot tube due to the small distance between the fixed pitot tube and the wing / fuselage on traditional cannon (box)-launched UAVs.

[0015] 2) This invention designs two sets of locking function modules within a limited space. The fit clearance between the locking pin and the pin hole in the two sets of locking function modules is different. The larger clearance ensures that the pin can be "locked in", and the smaller clearance ensures that the pin can be "locked tightly". The two clearances cooperate and complement each other, improving the reliability of the locking function module of the mechanism. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall appearance of the pitot tube in its retracted state.

[0017] Figure 2 This is a schematic diagram showing the overall appearance of the pitot tube in its extended position.

[0018] Figure 3 This is a schematic diagram of the internal structure of the mechanism in the pitot tube extended to its position.

[0019] Figure 4 This is a schematic diagram of the internal structure of the pitot tube in its retracted state.

[0020] Figure 5 This is a schematic diagram of the internal structure of the pitot tube locking function module.

[0021] Explanation of reference numerals in the attached drawings: 1—airspeed tube, 2—outer casing, 3—explosion compression spring, 4—end cap, 5—slide groove, 6—locking pin, 7—locking compression spring, 8—pin hole. Detailed Implementation

[0022] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments.

[0023] like Figure 1 and Figure 2 As shown, this invention proposes a UAV pitot tube ejection mechanism with locking function. The UAV pitot tube ejection mechanism may include an ejection function module and a locking function module. The ejection function module drives the pitot tube to extend to the target position, while the locking function module locks the pitot tube in its extended position.

[0024] like Figure 2 and Figure 3 As shown, the ejection module may include a pitot tube 1, a housing 2, an ejection compression spring 3, and an end cap 4. The housing 2 of the ejection module can be divided into two parts. The ejection compression spring 3 is housed within the housing 2, and the pitot tube 1 and end cap 4 are respectively located at both ends of the ejection compression spring 3. The end cap 4 is fixed to the first end of the housing 2 and contacts and presses against the first end of the ejection compression spring 3. The second end of the ejection compression spring 3 presses against the step of the pitot tube 1. The pitot tube 1 can extend from the second end of the housing 2 under the drive of the ejection compression spring 3.

[0025] like Figure 4 andFigure 5 As shown, the pitot tube 1 has a receiving groove inside its step for accommodating the locking function module 1. The locking function module 1 may include a locking pin 6 and a locking compression spring 7. One end of the locking compression spring 7 presses against the bottom of the receiving groove in the pitot tube 1 step, and the other end presses against the rear end face of the locking pin 6, for driving the locking pin 6 to move in a direction perpendicular to the extension of the pitot tube 1. In addition, the inner side wall of the housing 2 has a sliding groove 5. When the pitot tube 1 moves under the drive of the pop-out compression spring 3, the locking pin 6 built into the pitot tube 1 step can move within the sliding groove 5 of the housing 2. The sliding groove 5 restricts the locking pin 6 from popping out of the receiving groove in the pitot tube 1 step. A pin hole 8 is provided at the end of the sliding groove 5 opposite to the end cover 4, and the pin hole 8 is used to engage with the locking pin 6.

[0026] The pop-out function module uses a pop-out compression spring 3 as a power source to drive the airspeed tube 1 to move along the axis of the pop-out compression spring 3, thereby switching the airspeed tube 1 from a retracted state inside the cylinder (box) to an extended state after exiting the cylinder (box). Figure 4 and Figure 5 As shown, the locking pin 6 in the locking function module is driven by the locking compression spring 7. Before the airspeed tube 1 moves to the target position, the locking pin 6 is always in contact with the sliding groove 5 on the inner wall of the housing 2. After the airspeed tube 1 moves to the target position, the locking compression spring 7 in the locking function module drives the locking pin 6 to insert into the pin hole 8 on the housing 2, thereby locking the position of the airspeed tube 1.

[0027] In the embodiments provided in this application, the airspeed tube ejection mechanism of the UAV is basically symmetrically arranged, thus it can have two sets of symmetrical locking function modules. The fitting clearance between the locking pin 6 and the pin hole 8 in the two sets of locking function modules is different. The larger clearance ensures that it can be "locked in", and the smaller clearance ensures that it can be "locked tightly". The two clearances cooperate and complement each other, improving the reliability of the locking function module and ensuring that the airspeed tube 1 does not spring back under the action of external force after it is extended into place.

[0028] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope defined in the claims of the present invention.

Claims

1. A drone pitot tube ejection mechanism with locking function, characterized in that, Includes pop-up and lock functionality modules; The pop-out function module includes an airspeed tube (1), a housing (2), a pop-out compression spring (3), and an end cap (4); the pop-out compression spring (3) is housed inside the housing (2), and the airspeed tube (1) and the end cap (4) are respectively located at both ends of the pop-out compression spring (3); the end cap (4) is fixed to the first end of the housing (2) and contacts and presses against the first end of the pop-out compression spring (3); the second end of the pop-out compression spring (3) presses against the step of the airspeed tube (1), and the airspeed tube (1) extends out from the second end of the housing (2) under the drive of the pop-out compression spring (3); The airspeed tube (1) has a receiving groove inside the step for accommodating the locking function module 1. The locking function module 1 includes a locking pin (6) and a locking compression spring (7). One end of the locking compression spring (7) presses against the bottom of the receiving groove of the airspeed tube (1) step, and the other end presses against the rear end face of the locking pin (6) to drive the locking pin (6) to move in a direction perpendicular to the extension of the airspeed tube (1). In addition, the inner side wall of the outer casing (2) has a sliding groove (5). When the airspeed tube (1) moves under the drive of the pop-out compression spring (3), the locking pin (6) inside the airspeed tube (1) step moves in the sliding groove (5) of the outer casing (2). The sliding groove (5) restricts the locking pin (6) from popping out of the receiving groove inside the airspeed tube (1) step. A pin hole (8) is provided at one end of the sliding groove (5) away from the end cover (4). The pin hole (8) is used to engage with the locking pin (6).

2. The mechanism according to claim 1, characterized in that, The pop-out function module uses a pop-out compression spring (3) as a power source to drive the airspeed tube (1) to move along the axis of the pop-out compression spring (3), thereby switching the airspeed tube (1) from the contracted state to the extended state. The locking pin (6) in the locking function module is driven by the locking compression spring (7). Before the airspeed tube (1) moves to the target position, the locking pin (6) is always in contact with the slide groove (5) on the inner wall of the housing (2). When the airspeed tube (1) moves to the target position, the locking compression spring (7) in the locking function module drives the locking pin (6) to insert into the pin hole (8) on the housing (2) to lock the position of the airspeed tube (1).

3. The mechanism according to claim 1, characterized in that, The mechanism has two sets of symmetrical locking function modules.

4. The mechanism according to claim 1, characterized in that, In the two sets of locking function modules, the fit clearance between the locking pin (6) and the pin hole (8) is different.

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