Landing gear up-down position detection assembly and landing gear up-down position protection system

Abstract

The invention relates to an undercarriage uplift position detection assembly and an undercarriage uplift position protection system. The undercarriage folding position detection assembly comprises a sensor fixed on a fuselage of an aircraft; and the target assembly is fixed to the landing gear or fixed to the landing gear and the fuselage. The landing gear retracting position protection system comprises a landing gear; an undercarriage uplift position detection assembly according to one aspect of the present invention; and the undercarriage folding and unfolding actuating cylinder is used for actuating the undercarriage to enter or leave the folding position.

Description

Technical Field

[0001] The present invention relates to a landing gear retracted position detection assembly, in particular to a landing gear retracted position detection assembly which indicates the position of the landing gear independently of the upper lock, and may not involve the upper lock structure. The present invention also relates to a landing gear retracted position protection system. The present invention belongs to the technical field of aircraft landing gear. Background Art

[0002] According to the relevant provisions, the landing gear uplock must have positive measures to keep the landing gear and the door in the correct retracted position in the air, unless it can be shown that it is not dangerous to lower the landing gear or the door at any speed. In addition, during the flight of the aircraft, if the uplock fails and opens accidentally, the actuator is required to actuate the landing gear and the door to retract, then the landing gear position indication system is required to indicate that the landing gear is in the unretracted state.

[0003] In the current models, the sensors and targets for indicating the retracted state of the landing gear of the landing gear position indication system of most aircraft are installed on the parts of the uplock. During the retracting and lowering movement of the landing gear, the target detected by the proximity sensor of the landing gear position indication system is usually associated with the rotation of the uplock, and the rotation of the landing gear is detected through the rotation of the uplock, such as the rotation out of the retracted position or the rotation back to the retracted position.

[0004] However, if the lock hook of the upper lock breaks or the locked object escapes from the lock hook due to deformation, the locking joint of the landing gear loses the holding force provided by the lock hook of the upper lock, and the landing gear will drop down automatically due to gravity, but the upper lock does not rotate, so the proximity sensor and target of the existing landing gear position indication system cannot be properly disengaged and cannot correctly indicate the position of the landing gear.

[0005] It has been considered to match the proximity sensor fixed to the fuselage with the target directly fixed to the landing gear. However, considering the movement trajectory of the landing gear, the layout of the sensors at the corresponding positions in the fuselage space is limited. In addition, the target protruding toward the landing gear by connecting the fixed sensor through a bracket has the problem of vibration and shaking and cannot be aligned. Therefore, it is not easy to match the target directly fixed to the landing gear with the proximity sensor fixed to the fuselage. Summary of the invention

[0006] In view of the above problems in the prior art, an object of the present invention is to provide a landing gear retracted position detection assembly that indicates the position of the landing gear independently of the uplock, thereby ensuring the reliability of the landing gear retracted position indication function.

[0007] In a first example of the landing gear retracted position detection assembly of the present invention, the landing gear retracted position detection assembly includes: a sensor fixed on the fuselage of the aircraft; and a target assembly fixed to the landing gear, or to the landing gear and the fuselage.

[0008] In a second example of the landing gear retracted position detection assembly, the target assembly includes: a target link, the target link includes a first link, a second link, and a third link, the first end of the first link is fixed to the landing gear, the second end of the first link is pivotally connected to the first end of the second link via a first pivot shaft, the second link and the third link are fixed to each other at a predetermined angle and are each connected to the second pivot shaft and pivotally connected to the fuselage through the second pivot shaft; a target, the target is fixed to the second end of the third link of the target link, wherein the target corresponds to the proximity sensor when the landing gear is in the retracted position, and wherein the target is disengaged from the proximity sensor when the landing gear leaves the retracted position.

[0009] In the third example of the landing gear retracted position detection assembly, the second pivot shaft of the target link is fixed to the fuselage via a link bracket extending from the fuselage, and the sensor is fixed to the fuselage via a sensor bracket extending from the fuselage.

[0010] In a fourth example of the landing gear retracted position detection assembly, the target assembly includes: a target link, the target link includes a first rod portion and a second rod portion, the first rod portion and the second rod portion are fixed to each other at a predetermined angle and are respectively connected to a rod portion pivot shaft and are pivotally connected to a fuselage through the rod portion pivot shaft; a target, the target is fixed to an end of the second rod portion of the target link facing the sensor; a reset member, the reset member is elastically connected between the target link and the fuselage so that the target on the target link tends to disengage from the proximity sensor; and a push rod, a first end of the push rod is fixed to a landing gear strut of the landing gear, and a second end of the push rod extends toward the first rod portion of the target link and slidably abuts against the first rod portion, wherein the second end of the push rod abuts against the first rod portion at a first point of the first rod portion when the landing gear is in the retracted position, and the target corresponds to the proximity sensor, and wherein the second end of the push rod abuts against the first rod portion at a second point of the first rod portion when the landing gear leaves the retracted position, and the target disengages from the proximity sensor.

[0011] In the fifth example of the landing gear retracted position detection assembly, the proximity sensor, the rod pivot shaft of the target link, and the reset member are fixed to the fuselage via an uplock protective cover extending from the fuselage.

[0012] In a sixth example of the landing gear retracted position detection assembly, the reset member is a spring, one end of which is connected to the fuselage and the other end is connected to the second rod portion of the target link, or the reset member is a coil spring, which is arranged at the rod portion pivot axis, so that the reset member is in a non-neutral position when the landing gear is in the retracted position.

[0013] In the seventh example of the landing gear retracted position detection assembly, the reset member is two magnets that repel each other, wherein the first magnet is fixed to the fuselage and the second magnet is fixed to the target link, so that when the landing gear is in the retracted position, the two magnets of the reset member are closer to each other than when the landing gear is out of the retracted position.

[0014] In an eighth example of the landing gear retracted position detection assembly, the sensor is a non-contact distance measuring sensor, and the target assembly is a marking portion fixed on a landing gear strut of the landing gear, so that the sensor detects the distance to the marking portion on the landing gear.

[0015] In the ninth example of the landing gear retracted position detection assembly, the sensor is an angle sensor, and the target assembly is a marking portion fixed on the rotating shaft of the landing gear strut of the landing gear, so that the sensor detects the rotation angle of the marking portion on the rotating shaft of the landing gear.

[0016] A landing gear retracted position protection system comprises: a landing gear; a landing gear retracted position detection assembly according to one aspect of the present invention; and a landing gear retracting and extending actuator cylinder, the landing gear retracting and extending actuator cylinder being used to actuate the landing gear to enter or leave the retracted position.

[0017] The present invention proposes a landing gear retraction detection assembly for preventing the landing gear from being lowered without command. When the landing gear is lowered without command due to failure of the upper lock, the problem can be detected in time, and the landing gear can be actuated in time through the landing gear retraction and extension actuator to prevent the landing gear from hitting the cabin door, thereby causing serious consequences such as damage to the landing gear cabin door or flying out. Different from the current aircraft that use the upper lock to determine the landing gear position, the present invention proposes a technical path for directly detecting the landing gear position.

[0018] Directly and accurately detecting the position of the landing gear can avoid inaccurate detection of the landing gear position when using the uplock signal. Based on the concept of direct detection of the landing gear, the implementation forms of multi-link, push rod, contactless sensor induction and angle sensor are proposed.

[0019] In the first example, the landing gear retracted position detection assembly of the present invention sets a target on the landing gear body or sets a target through a connecting rod to match the stroke, and drives the connecting rod to drive the target to rotate and match with the proximity sensor. The target has a larger rotation rate angle than the landing gear in the initial stage of the stroke. In the second example, the connecting rod target is pushed to match the proximity sensor by point-line contact, and the retracted position of the landing gear body is detected when the space layout is limited. The landing gear retracted position detection assembly of the present invention has the advantages of simple structure, high reliability and small space requirement. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to describe the implementation of the above and other features of the present invention, a more particular description of the invention briefly described above will be presented with reference to the exemplary embodiments of the invention shown in the accompanying drawings. It will be understood that these drawings only depict exemplary embodiments of the invention and should not be considered as limiting the scope thereof. The invention will be described and explained through the use of the accompanying drawings and with additional features and details. In the drawings:

[0021] Figure 1 is a perspective view of a landing gear stowed position detection assembly according to an embodiment of the present invention;

[0022] Figure 2 When the landing gear is in the retracted position Figure 1 A side view of a landing gear retracted position detection assembly;

[0023] Figure 3 When the landing gear leaves the retracted position Figure 1 A side view of a landing gear retracted position detection assembly;

[0024] Figure 4 yes Figure 1 A graph showing a relationship between a rotation angle of a target of a landing gear retracted position detection assembly and a rotation angle of the landing gear;

[0025] Figure 5 is a perspective view of a landing gear stowed position detection assembly according to another embodiment of the present invention;

[0026] Figure 6 When the landing gear is in the retracted position Figure 5 A side view of a landing gear retracted position detection assembly;

[0027] Figure 7 When the landing gear leaves the retracted position Figure 5 A side view of a landing gear retracted position detection assembly;

[0028] Figure 8 is a side view of a landing gear retracted position detection assembly according to another embodiment of the present invention;

[0029] Fig. 9 is a side view of a landing gear stowed position detection assembly according to yet another embodiment of the present invention;

[0030] Fig.10 4 is a system block diagram of a landing gear retracted position protection system according to an embodiment of the present invention.

[0031] The drawings are roughly drawn to scale, however, the dimensions in the drawings are only schematic and do not need to be strictly drawn to scale, but are intended to be more clearly illustrated. In other embodiments, other relative dimensions may be used. Here and in all of the following, the same features appearing in different drawings are represented by the same or similar reference numerals.

[0032] List of reference numerals:

[0033] 1 Landing gear retracted position detection component

[0034] 2 Landing gear

[0035] 2a Landing gear strut

[0036] 2b Landing gear shaft

[0037] 3 Body

[0038] 3a Connecting rod bracket

[0039] 3b Sensor bracket

[0040] 3c Upper lock protective cover

[0041] 10 Sensors

[0042] 20 Target assembly

[0043] 210 Target connecting rod

[0044] 1211 First connecting rod

[0045] 1212 Second connecting rod

[0046] 1213 Third connecting rod

[0047] 1214 First pivot axis

[0048] 1215 Second pivot axis

[0049] 2211 First Pole

[0050] 2212 Second pole

[0051] 2213 Rod Pivot Axle

[0052] 220 Target

[0053] 230 reset piece

[0054] 240 Putter DETAILED DESCRIPTION

[0055] As used herein, the term “fixed” is intended to describe a component that is connected to another component and is capable of maintaining a constant relative position to each other so that forces, torques, etc. can be transferred from one component to the other.

[0056] The term “connection” as used herein is intended to describe that there is a direct or indirect force transmission path from one component to another component, ie, direct or indirect contact, so that force, torque, etc. can be transmitted from one component to another component.

[0057] Directional terms used herein, such as "top", "bottom", "upper", "lower", "inner", "inward", "outer", and "outward", are used to assist in describing the present invention according to the orientation of the embodiments shown in the drawings. Unless otherwise specified, such as "horizontal direction", "direction of gravity", etc., directional terms are not absolute up, down, horizontal, vertical, etc., and should not be interpreted as limiting the present invention to any particular direction.

[0058] As used herein, the terms "comprising," "having," "including," and variations thereof are intended to serve as open-ended transitional phrases, terms or words requiring the presence of specified elements / steps and also allowing for the presence of other elements / steps.

[0059] In the present invention, unless explicitly stated to the contrary, the terms "first", "second", etc. are not intended to indicate any difference in order, position, quantity or importance, but are merely used as labels to distinguish different positions and components, to distinguish one element, component, region and / or position from another element, component, region and / or position.

[0060] In a non-limiting example, the aircraft of the present invention comprises a landing gear 2, which comprises a landing gear strut 2a and a landing gear shaft 2b, and the landing gear strut 2a is pivotable about the landing gear shaft 2b between a retracted position and a lowered position.

[0061] In a non-limiting example, the aircraft of the present invention comprises an uplock for locking the landing gear 2 , and when the landing gear 2 is in the retracted position, the uplock can lock the landing gear 2 , for example, a lock hook of the uplock cooperates with a locking joint of the landing gear 2 .

[0062] In a non-limiting example, the aircraft of the present invention comprises an uplock position detection assembly for indicating whether the uplock corresponding to the landing gear 2 is in a locked position.

[0063] In a non-limiting example, the aircraft of the present invention includes a landing gear retracted position detection assembly 1 for indicating whether the landing gear 2 is in the retracted position. The landing gear retracted position detection assembly 1 may include a sensor 10 and a corresponding target assembly 20. In order to avoid the problem that if the hook of the uplock is broken as mentioned above, the existing landing gear position indication system cannot correctly indicate the position of the landing gear. The sensor 10 is fixed to the fuselage 3 of the aircraft, and the target assembly 20 is fixed to the landing gear 2, or to both the landing gear 2 and the fuselage 3.

[0064] The present invention will be further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0065] A coordinate system is provided in the figures for reference, the z-axis may be the vertical axis (e.g., parallel to the direction of gravity), the x-axis may be the lateral axis (e.g., parallel to the horizontal direction), and the y-axis may be the longitudinal axis (e.g., the xy plane is parallel to the horizontal plane).

[0066] When referring to directions, a positive direction may refer to the direction of the arrows for the y-axis, x-axis, and z-axis, and a negative direction may refer to the opposite direction of the arrows for the y-axis, x-axis, and z-axis. A filled circle may represent an arrow and axis facing toward or positive to the view. An unfilled circle may represent an arrow and axis facing away from or negative to the view.

[0067] First embodiment

[0068] Figure 1 The schematic diagram shows a perspective view of a landing gear retracted position detection assembly 1 according to a first embodiment of the present invention. In this embodiment, the sensor 10 is a proximity sensor, and the target assembly 20 includes a target link 210 and a target 220 , wherein the target 220 is fixed to the target link 210 .

[0069] In this embodiment, the target link 210 includes a first link 1211, a second link 1212, and a third link 1213. The first end of the first link 1211 is fixed to the landing gear 2, for example, the end of the landing gear 2 sleeved on the landing gear shaft 2b. The first link 1211 and the second link 1212 are pivotally connected via a first pivot shaft 1214, specifically, the second end of the first link 1211 is pivotally connected to the first end of the second link 1212. The second link 1212 and the third link 1213 are fixed to each other at a predetermined angle and are each connected to a second pivot shaft 1215. The second pivot shaft 1215 is pivotally connected to the fuselage 3, so that the second link 1212 and the third link 1213 fixed to each other at a predetermined angle can be rotated around the second pivot shaft 1215 as a whole. In addition, the target 220 can be fixed to the second end of the third link 1213 of the target link 210.

[0070] Preferably, if Figure 1As shown, the second pivot shaft 1215 of the target link 210 is fixed to the fuselage 3 via the link bracket 3a extending from the fuselage 3, and the sensor 10 is fixed to the fuselage 3 via the sensor bracket 3b extending from the fuselage 3. The first link 1211 of the target link 210 is arranged on the landing gear 2 to match the stroke of the landing gear 2. It is ensured that at the preset rotation angle of the landing gear 2, the target 220 can be separated from the sensing area of ​​the proximity sensor, and at the full stroke of the landing gear 2 being retracted and lowered, there is no situation where the target 220 or the target link 210 rotates too long or the movement amplitude of the mechanism is too large, and the compact design avoids obstruction by adjacent structures.

[0071] Figure 2 and Figure 3 The side view of the landing gear retracted position detection assembly 1 is schematically shown when the landing gear is in the retracted position and leaves the retracted position.

[0072] The lowering movement of the landing gear 2 causes the first link 1211 to follow, and drives the target 220 via the target link 210, so that the target 220 rotates around the axis of the second pivot shaft 1215 and is matched with the proximity sensor and then disengaged.

[0073] When the landing gear 2 is in the retracted position, the target 220 corresponds to the proximity sensor, and when the landing gear 2 leaves the retracted position, the target 220 is disengaged from the proximity sensor. Therefore, the landing gear retracted position detection assembly 1 can indicate whether the landing gear 2 of the aircraft is in the retracted position.

[0074] Figure 4 The relationship between the rotation angle of the target 220 of the landing gear stowed position detection assembly 1 and the rotation angle of the landing gear 2 of this embodiment is schematically shown, where the horizontal axis is the rotation angle of the landing gear 2 and the vertical axis is the rotation angle of the target 220 .

[0075] In order to achieve the sensitivity requirement of the landing gear retracted position protection system, when the landing gear 2 rotates a small angle, the target 220 can be separated from the sensor 10, and the target 220 needs to have a larger angular rotation rate than the landing gear 2 in the initial stage of the travel of the landing gear 2. This characteristic is achieved by adjusting the lengths of the first link 1211, the second link 1212, and the third link 1213 of the target link 210. The corresponding relationship between the rotation angles of the two is as follows: Figure 4 As shown, when the landing gear 2 is lowered to a smaller angle, the target 220 can be separated from the sensor 10. Therefore, the landing gear retracted position detection assembly 1 has a higher sensitivity to the lowering movement of the landing gear 2.

[0076] The target link 210 transmits the movement of the landing gear 2 to the target 220. To a certain extent, it is not limited by the spatial distance. The link length, arrangement, rotation parameters, etc. can be adjusted to match the matching position of the proximity sensor to avoid the problem that the sensor protruding toward the landing gear through the bracket is vibrated and cannot be aligned with the target. It has a certain versatility and can adapt to various landing gear and bulkhead structural forms to realize the landing gear locking position indication function.

[0077] Second embodiment

[0078] Figure 5 A perspective view of a landing gear retracted position detection assembly according to another embodiment of the present invention is schematically shown. In this embodiment, the sensor 10 is a proximity sensor, and the target assembly 20 includes a target link 210, a target 220, a reset member 230, and a push rod 240, wherein the target 220 is fixed to the target link 21; the reset member 230 is elastically connected between the target link 210 and the fuselage 3, so that the target 220 on the target link 210 tends to be separated from the proximity sensor; and the push rod 240 slidably abuts against the target link 210.

[0079] In this embodiment, the target link 210 includes a first rod portion 2211 and a second rod portion 2212. The first rod portion 2211 and the second rod portion 2212 are fixed to each other at a predetermined angle and are each connected to a rod pivot shaft 2213. The rod pivot shaft 2213 is pivotally connected to the fuselage 3, so that the first rod portion 2211 and the second rod portion 2212 fixed to each other at a predetermined angle can be integrally rotated around the rod pivot shaft 2213. In addition, the target 220 can be fixed to the end of the second rod portion 2212 of the target link 210 toward the sensor 10.

[0080] Preferably, if Figure 5 As shown, the proximity sensor, the rod pivot shaft 2213 of the target link 210 , and the reset member 230 are fixed to the fuselage 3 via an upper lock protective cover 3 c extending from the fuselage 3 .

[0081] Preferably, if Figure 5 As shown, the reset member 230 is a spring, one end of which is connected to the uplock protective cover 3c extending from the fuselage 3 and the other end of which is connected to the second rod portion 2212 of the target link 210, and when the landing gear 2 is in the retracted position, the reset member 230 is in a stretched state, i.e., a non-neutral position, and tends to return to its neutral position, thereby causing the target 220 on the target link 210 to tend to disengage from the proximity sensor.

[0082] It is understood that the form of the reset member 230 is not limited thereto, and may also be a coil spring, for example, provided at the rod pivot shaft 2213, and in a compressed state or a stretched state, i.e., a non-neutral position. In addition, it may also be two magnets that repel each other, wherein the first magnet is fixed on the fuselage 3 and the second magnet is fixed on the target link 210, so that when the landing gear 2 is in the retracted position, the two magnets of the reset member 230 are closer to each other than when the landing gear 2 is out of the retracted position. Therefore, when the landing gear 2 is in the retracted position, the target 220 on the target link 210 tends to be out of the proximity sensor.

[0083] Preferably, if Figure 5 As shown, a first end of the push rod 240 is fixed to the strut 2 a of the landing gear 2 , and a second end of the push rod 240 extends toward the first rod portion 2211 of the target link 210 and slidably abuts against the first rod portion 2211 .

[0084] Figure 6 and Figure 7 The side view of the landing gear retracted position detection assembly 1 is schematically shown when the landing gear 2 is in the retracted position and leaves the retracted position.

[0085] The lowering movement of the landing gear 2 causes the push rod 240 to follow downward, releasing the supporting force acting on the target link 210 by way of point contact, allowing the reset member 230 to return to its neutral position and actuate the target link 210, driving the target 220, so that the target 220 rotates around the axis of the rod pivot shaft 2213 and changes from matching to disengaging with the proximity sensor.

[0086] When the landing gear 2 is in the retracted position, the second end of the push rod 240 abuts against the first rod portion 2211 at the first point A1 of the first rod portion 2211, and the target 220 corresponds to the proximity sensor, and when the landing gear 2 leaves the retracted position, the second end of the push rod 240 abuts against the first rod portion 2211 at the second point A2 of the first rod portion 2211, and the target 220 is disengaged from the proximity sensor. Therefore, the landing gear retracted position detection assembly 1 can indicate whether the landing gear 2 of the aircraft is in the retracted position.

[0087] Third embodiment

[0088] Figure 8 A side view of a landing gear retracted position detection assembly according to another embodiment of the present invention is schematically shown. In this embodiment, the sensor 10 is a non-contact distance measuring sensor, such as but not limited to a visual detection device, a laser detection device, an infrared detection device or an ultrasonic detection device, and the target assembly 20 is a marking portion fixed on the support column 2a of the landing gear 2, so that the sensor 10 detects the distance from the marking portion on the landing gear.

[0089] Fourth embodiment

[0090] Fig. 9 A side view of a landing gear retracted position detection assembly according to yet another embodiment of the present invention is schematically shown. In this embodiment, the sensor 10 is an angle sensor, and the target assembly 20 is a marking portion fixed to the rotating shaft of the landing gear strut, so that the sensor 10 detects the rotation angle of the marking portion on the rotating shaft of the landing gear.

[0091] Now go to Fig.10 , which schematically shows a system block diagram of a landing gear retracted position protection system according to an embodiment of the present invention.

[0092] In a non-limiting example, an aircraft of the present invention includes a landing gear retracted position protection system, which includes the above-mentioned landing gear, a landing gear retracted position detection assembly according to the above description, and a landing gear retracting and extending actuator. The landing gear retracting and extending actuator is used to actuate the landing gear to enter or leave the retracted position.

[0093] The landing gear retracted position protection system may further include an uplock, an uplock position detection assembly, an alarm unit, and a controller. The alarm unit is used to remind the crew of an emergency. The controller receives signals from the landing gear retracted position detection assembly and the uplock position detection assembly, and when the uplock is in the locked position but the landing gear leaves the retracted position, sends a signal to the alarm unit so that the alarm unit reminds the crew, and the landing gear retracting and extending actuator sends a signal so that the landing gear retracting and extending actuator actuates the landing gear to enter the retracted position.

[0094] In order to make the purpose, technical solution and advantages of the embodiments of the present invention more clear, the technical solution of the present invention is clearly and completely described above in combination with the specific embodiments of the present invention and the accompanying drawings.

[0095] Although various embodiments have been described above, it should be understood that the embodiments described are part of the embodiments of the present invention, rather than all embodiments, and they are presented in an exemplary rather than limiting manner. It is obvious to those skilled in the relevant art that the disclosed subject matter can be implemented in other specific forms without departing from its spirit and essential features.

[0096] Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention. The present disclosure also includes various modifications and modifications within the equivalent scope. In addition, various combinations and methods, further including only one element, more than one or less than one other combinations and methods also belong to the scope and scope of thought of the present disclosure.

Claims

1. A landing gear retracted position detection assembly, used to indicate whether a landing gear (2) of an aircraft is in a retracted position, characterized in that: The landing gear retracted position detection component (1) comprises: a sensor (10), the sensor (10) being fixed on the fuselage (3) of the aircraft; and A target assembly (20) is fixed to the landing gear (2), or to the landing gear (2) and the fuselage (3).

2. The landing gear retracted position detection assembly according to claim 1, characterized in that: The sensor (10) is a proximity sensor, and The target assembly (20) comprises: A target link (210), the target link (210) comprising a first link (1211), a second link (1212), and a third link (1213), the first end of the first link (1211) being fixed to the landing gear (2), the second end of the first link (1211) being pivotally connected to the first end of the second link (1212) via a first pivot shaft (1214), the second link (1212) and the third link (1213) being fixed to each other at a predetermined angle and each being connected to a second pivot shaft (1215) and pivotally connected to the fuselage (3) via the second pivot shaft (1215); a target (220), wherein the target (220) is fixed to the second end of the third link (1213) of the target link (210), wherein when the landing gear (2) is in the retracted position, the target (220) corresponds to the proximity sensor, and Wherein, when the landing gear (2) leaves the retracted position, the target (220) is disengaged from the proximity sensor.

3. The landing gear stowed position detection assembly according to claim 2, characterized in that: The second pivot axis (1215) of the target link (210) is fixed to the fuselage (3) via a link bracket (3a) extending from the fuselage (3), and The sensor (10) is fixed to the body (3) via a sensor bracket (3b) extending from the body (3).

4. The landing gear retracted position detection assembly according to claim 1, characterized in that: The sensor (10) is a proximity sensor, and The target assembly (20) comprises: A target link (210), the target link (210) comprising a first rod portion (2211) and a second rod portion (2212), the first rod portion (2211) and the second rod portion (2212) being fixed to each other at a predetermined angle and each connected to a rod portion pivot shaft (2213) and pivotally connected to the fuselage (3) via the rod portion pivot shaft (2213); A target (220), the target (220) being fixed to the end of the second rod portion (2212) of the target connecting rod (210) facing the sensor (10); a reset member (230), the reset member (230) being elastically connected between the target link (210) and the fuselage (3), so that the target (220) on the target link (210) tends to be separated from the proximity sensor; and a push rod (240), a first end of which is fixed to a landing gear strut (2a) of the landing gear (2), and a second end of which extends toward the first rod portion (2211) of the target link (210) and slidably abuts against the first rod portion (2211), wherein, when the landing gear (2) is in the retracted position, the second end of the push rod (240) abuts against the first rod portion (2211) at a first point (A1) of the first rod portion (2211), and the target (220) corresponds to the proximity sensor, and When the landing gear (2) leaves the retracted position, the second end of the push rod (240) abuts against the first rod portion (2211) at a second point (A2) of the first rod portion (2211), and the target (220) disengages from the proximity sensor.

5. The landing gear retracted position detection assembly according to claim 4, characterized in that: The proximity sensor, the rod pivot shaft (2213) of the target link (210), and the reset member (230) are fixed to the fuselage (3) via an upper lock protective cover (3c) extending from the fuselage (3).

6. The landing gear stowed position detection assembly according to claim 4, characterized in that: The reset member (230) is a spring, one end of which is connected to the fuselage (3) and the other end of which is connected to the second rod portion (2212) of the target link (210), or the reset member (230) is a coil spring, which is arranged at the rod portion pivot axis (2213), When the landing gear (2) is in the retracted position, the reset member (230) is in a non-neutral position.

7. The landing gear stowed position detection assembly according to claim 4, characterized in that: The reset element (230) is two magnets that repel each other, wherein the first magnet is fixed on the fuselage (3) and the second magnet is fixed on the target connecting rod (210). When the landing gear (2) is in the retracted position, the two magnets of the reset member (230) are closer to each other than when the landing gear (2) is out of the retracted position.

8. The landing gear stowed position detection assembly according to claim 1, characterized in that: The sensor (10) is a non-contact distance measuring sensor, and The target assembly (20) is a marking portion fixed on a landing gear strut (2a) of the landing gear (2), so that the sensor (10) detects the distance to the marking portion on the landing gear.

9. The landing gear retracted position detection assembly according to claim 1, characterized in that: The sensor (10) is an angle sensor, and The target assembly (20) is a marking portion fixed on the rotating shaft of the landing gear strut of the landing gear, so that the sensor (10) detects the rotation angle of the marking portion on the rotating shaft of the landing gear.

10. A landing gear retracted position protection system, characterized in that: The landing gear retracted position protection system comprises: landing gear; A landing gear retracted position detection assembly according to any one of claims 1 to 9, used to indicate whether the landing gear is in the retracted position; and A landing gear retraction actuator cylinder is used to actuate the landing gear to enter or leave the retracted position.

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