Aircraft landing lamp
By separating the light source and drive components, and employing forced air cooling and TIR lens optics, the heat dissipation problem of aircraft landing lights was solved, achieving both lightweight design and efficient heat dissipation.
Patent Information
- Application Number
- CN202411292824.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-14
- Publication Date
- 2026-03-17
AI Technical Summary
Existing aircraft landing lights suffer from excessive heat due to insufficient heat dissipation, which affects their lifespan and makes them heavy, hindering weight reduction.
It adopts a separate design for the light source and the drive section, combined with axial fan forced air cooling and TIR lens optical design, to achieve rapid heat dissipation through heat dissipation fins and air holes, and to optimize light energy utilization by using lens array.
It achieves efficient heat dissipation, reduces the weight of the aircraft landing light, and at the same time ensures the temperature control and light energy utilization efficiency of the light fixture.
Smart Images
Figure CN121676923A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to airborne lighting fixtures, and more particularly, to an aircraft landing light. Background Technology
[0002] When an aircraft lands at night, landing lights illuminate the landing area, allowing the pilot to clearly visually assess the aircraft's relative position to the runway and its altitude, enabling safe maneuvering for landing and taxiing, and ensuring a safe landing. There are various options for installing landing lights, such as on the nose landing gear, main landing gear, wing leading edge, and fairing. Currently, existing landing lights have relatively high wattage to provide sufficient illumination, thus generating considerable heat during operation and limiting their longevity. Furthermore, due to stringent heat dissipation requirements, the weight of the heat dissipation material cannot be reduced, resulting in relatively heavy landing lights, which hinders weight reduction requirements for aircraft lighting fixtures. Summary of the Invention
[0003] The purpose of this invention is to solve the problem that existing aircraft landing lights have poor heat dissipation capacity or have adequate heat dissipation capacity but are too heavy overall, and to provide a new type of aircraft landing light.
[0004] To achieve the above objectives, the present invention provides a technical solution: an aircraft landing light, comprising: a light source portion and a driving portion. The light source portion has a light source housing and a light source plate inside the light source housing; the driving portion has a driving housing and a driving plate and an axial fan inside the driving housing; the light source housing is in front, and the driving housing is behind, with a gap between them; the rear wall of the light source housing has heat dissipation fins formed therein, the heat dissipation fins are arranged in a radial annular pattern, and the heat dissipation fins abut against the front wall of the driving housing; the front wall of the driving housing has an opening at the position of the axial fan, and the rear wall and / or the peripheral wall of the driving housing have vents at the position of the axial fan, the axial fan dissipating air forward.
[0005] As a preferred embodiment of an aircraft landing light, the light source portion further includes a lens plate inside the light source housing, the light source plate having an LED array, the lens plate having a lens array, and the LEDs of the LED array having a one-to-one correspondence with the lenses of the lens array.
[0006] As a preferred option for aircraft landing lights, the lens is a TIR lens.
[0007] As a preferred embodiment of an aircraft landing light, the lens has five optical surfaces: refractive surface I, refractive surface II, refractive surface III, refractive surface IV, and total internal reflection surface I. The lens has a lens recess on its rear side, and the LED is housed within the lens recess corresponding to the lens. The bottom surface of the lens recess is refractive surface I, the inner ring of the front of the lens is refractive surface II, the inner peripheral surface of the lens recess is refractive surface III, the outer peripheral surface of the lens is total internal reflection surface I, and the outer ring of the front of the lens is refractive surface IV. Refractive surfaces I and II are configured such that a portion of the LED beam sequentially passes through refractive surfaces I and II to be distributed to the desired space, while the remaining portion of the LED beam sequentially passes through refractive surfaces III, IV, and I to be distributed to the desired space.
[0008] As a preferred embodiment of an aircraft landing light, the LED array includes an inner ring LED, a middle ring LED, and an outer ring LED, wherein the inner ring LED, the middle ring LED, and the outer ring LED are arranged in a compact manner; correspondingly, the lens array includes an inner ring lens, a middle ring lens, and an outer ring lens, wherein the inner ring lens, the middle ring lens, and the outer ring lens are arranged in a compact manner.
[0009] As a preferred embodiment of the aircraft landing light, the light source portion further includes a mounting handle, which is fixed to the peripheral wall of the light source housing and serves as the engagement point for the onboard retraction mechanism.
[0010] Compared with the prior art, the beneficial effects of the present invention are at least as follows: (1) The airflow generated by the axial fan passes through the opening and is discharged from the inside to the outside along the heat dissipation fins, that is, the heat is quickly dissipated by forced air cooling, ensuring the heat conduction and convection of the aircraft landing light, achieving rapid and effective heat dissipation, and ensuring temperature control while meeting the requirements of weight reduction. (2) The lens is configured to meet the requirements of high light output efficiency by combining a TIR lens with 5 degrees of freedom optical surfaces, based on making full use of space and achieving the specified center light intensity and uniformity. Attached Figure Description
[0011] Figure 1 This is a schematic diagram (front view) of an embodiment of the aircraft landing light of the present invention.
[0012] Figure 2 This is a schematic diagram (rear view) of an embodiment of the aircraft landing light of the present invention.
[0013] Figure 3 This is a structural schematic diagram (expanded state) of an embodiment of the aircraft landing light of the present invention.
[0014] Figure 4 This is a lens cross-section of an embodiment of the aircraft landing light of the present invention. Figure 1 .
[0015] Figure 5 This is a lens cross-section of an embodiment of the aircraft landing light of the present invention. Figure 2 . Detailed Implementation
[0016] The present invention will now be described in further detail with reference to specific embodiments and accompanying drawings. It should be noted that these descriptions of embodiments are intended to aid in understanding the invention and do not constitute a limitation thereof. Furthermore, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.
[0017] See Figures 1 to 3 The image shows an aircraft landing light. The landing light assembly is located within a landing light retraction mechanism. This mechanism retracts or extends the landing light assembly. The landing light assembly provides sufficient illumination during aircraft descent to ensure a safe landing.
[0018] The aircraft landing light includes a light source part 1 and a drive part 2, etc. The light source part 1 is in front, and the drive part 2 is behind. The light source part 1 is independent of the drive part 2.
[0019] The light source part 1 includes a light source housing 11, a light source plate 12, a lens plate 13, and a mounting handle 14. The light source housing 11 has a rear wall 111 and a peripheral wall 112. The light source housing 11 does not have a front wall. The rear wall 111 and the peripheral wall 112 together form a forward-opening light source accommodating space. The light source accommodating space houses the light source plate 12 and the lens plate 13. The light source plate 12 is located behind the lens plate 13. The light source plate 12 emits light forward. The light source plate 12 has an LED array. The lens plate 13 has a lens array. The LEDs in the LED array correspond one-to-one with the lenses in the lens array. The light emitted by each LED is emitted forward through its corresponding lens. The mounting handle 14 is fixed to the peripheral wall 112 of the light source housing 11. The mounting handle 14 is the connection point for the on-machine take-up and take-down mechanism.
[0020] In practice, the light source housing 11 is generally circular.
[0021] In a specific implementation, the light source plate 12 abuts against the rear wall 111 of the light source housing 11, and the contact between the two is a surface contact, the purpose of which is to conduct the heat generated by the light source plate 12 during operation to the rear wall 111 of the light source housing 11 as quickly as possible.
[0022] In a specific implementation, the LED array includes: an inner ring LED, a middle ring LED, and an outer ring LED. The inner ring LED, the middle ring LED, and the outer ring LED are arranged compactly. The inner ring LED has 6 LEDs. The middle ring LED has 12 LEDs. The outer ring LED has 18 LEDs. Correspondingly, the lens array includes: an inner ring lens, a middle ring lens, and an outer ring lens. The inner ring lens, the middle ring lens, and the outer ring lens are arranged compactly. The inner ring lens has 6 lenses. The middle ring lens has 12 lenses. The outer ring lens has 18 lenses.
[0023] In specific implementation, the lens is a TIR lens. The lens has five optical surfaces: refractive surface I131, refractive surface II132, refractive surface III133, refractive surface IV134, and total internal reflection surface I135. The lens has a lens recess on its rear side. The LED is housed within the lens recess corresponding to the lens. The bottom surface of the lens recess is the refractive surface I. The inner (center) position of the front edge of the lens is the refractive surface II. The inner peripheral surface of the lens recess is the refractive surface III. The outer peripheral surface of the lens is the total internal reflection surface I. The outer peripheral position of the front edge of the lens is the refractive surface IV. The refractive surfaces I and II are configured such that a portion of the LED beam (e.g., with an incident angle within ±30°) sequentially passes through the refractive surfaces I and II and is distributed to the desired space (see...). Figure 4 The remaining portion of the LED beam (e.g., with an incident angle ranging from ±30° to ±90°) sequentially passes through the refractive surface III, the refractive surface IV, and the total internal reflection surface I to be distributed into the desired space (see...). Figure 5 Among them, the refractive surface I, the refractive surface II, the refractive surface III, the refractive surface IV, and the total internal reflection surface I are all freeform surfaces. The lens is a TIR lens, which has the advantages of compact structure, high light utilization efficiency, and large degree of design freedom, and can effectively combine and distribute the light energy of the light source to achieve the design goal.
[0024] The drive unit 2 includes a drive housing 21, a drive plate 22, and an axial fan 23. The drive housing 21 has a front wall 211, a rear wall 212, and a peripheral wall 213 between the front wall 211 and the rear wall 212. The front wall 211, the rear wall 212, and the peripheral wall 213 together enclose a drive accommodating space. The drive accommodating space houses the drive plate 22 and the axial fan 23.
[0025] The light source housing 11 and the drive housing 21 are spaced apart. Heat dissipation fins 3 and a central sleeve 4 are formed on the rear side of the rear wall 111 of the light source housing 11. The heat dissipation fins 3 are arranged in a radial annular pattern with the central sleeve 4 as the center. Furthermore, the heat dissipation fins 3 abut against the front wall 211 of the drive housing 21. Unlike traditional right-angle fin designs, the structure of the heat dissipation fins 3 increases the heat dissipation area, allowing the heat generated by the light source plate 12 and the drive plate 22 during operation to be conducted to the heat dissipation fins 3 through the rear wall 111 of the light source housing 11 and the front wall 211 of the drive housing 21, respectively.
[0026] The front wall 211 of the drive housing 21 has an opening 24 at the location of the axial fan 23. The rear wall 212 and peripheral wall 213 of the drive housing 21 have vents 25 at the location of the axial fan 23. The axial fan 23 exhausts air forward. The airflow generated by the axial fan 23 passes through the opening 24 and is discharged from the inside to the outside along the heat dissipation fins 3, that is, the heat is quickly dissipated by forced air cooling, ensuring the heat conduction and convection of the aircraft landing light, achieving rapid and effective heat dissipation, and ensuring temperature control while meeting the requirements of weight reduction.
[0027] In practice, the heat dissipation fins 3 have a height of 16mm and a thickness of 1.2mm. In a working environment of 25℃, the simulated junction temperature of the light source board 12 is only about 58℃, and the shell temperature of the light source housing 11 is also only about 58℃.
[0028] In a specific implementation, the cable of the drive board 22 passes through the central sleeve 4 and is electrically connected to the light source board 12. The drive board 22 is used to drive the light source board 12 to work.
[0029] The above description merely illustrates embodiments of the present invention and is quite specific and detailed; however, it should not be construed as limiting the scope of the invention patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. Therefore, the protection scope of this invention patent should be determined by the appended claims.
Claims
1. An aircraft landing light characterized by, Comprising: a light source part and a driving part; the light source part has a light source casing and a light source board inside the light source casing, the driving part has a driving casing and a driving board inside the driving casing, an axial flow fan; the light source casing is in front, the driving casing is in back, both have a space, the casing back wall of the light source casing is formed with a heat dissipation fin, the heat dissipation fin is in a radial ring layout, the heat dissipation fin abuts against the casing front wall of the driving casing; the casing front wall of the driving casing is formed with an open mouth at the position of the axial flow fan, the casing back wall and / or the casing peripheral wall of the driving casing is formed with an air hole at the position of the axial flow fan, the axial flow fan blows air forward.
2. The aircraft landing light of claim 1, wherein, The light source part further has a lens board inside the light source casing, the light source board has an LED array, the lens board has a lens array, the LEDs of the LED array and the lenses of the lens array have a one-to-one correspondence.
3. The aircraft landing light of claim 2, wherein, The lens is a TIR lens.
4. The aircraft landing light of claim 3, wherein, The lens has five optical curved surfaces, which are refractive curved surface I, refractive curved surface II, refractive curved surface III, refractive curved surface IV, and total reflection curved surface I, the back of the lens has a lens groove, the LED is accommodated inside the lens groove corresponding to the lens, the bottom surface of the lens groove is the refractive curved surface I, the inner ring position of the front of the lens is the refractive curved surface II, the inner peripheral surface of the lens groove is the refractive curved surface III, the outer peripheral surface of the lens is the total reflection curved surface I, and the outer ring position of the front of the lens is the refractive curved surface IV; the refractive curved surface I and the refractive curved surface II are configured to sequentially distribute part of the light beam of the LED to the required space through the refractive curved surface I and the refractive curved surface II, and the remaining part of the light beam of the LED is sequentially distributed to the required space through the refractive curved surface III, the refractive curved surface IV, and the total reflection curved surface I.
5. The aircraft landing light of claim 2, wherein, The LED array includes inner ring LEDs, middle ring LEDs, and outer ring LEDs, which are arranged compactly; correspondingly, the lens array includes inner ring lenses, middle ring lenses, and outer ring lenses, which are arranged compactly.
6. The aircraft landing light of claim 1, wherein, The light source part further has a mounting handle, which is fixed to the casing peripheral wall of the light source casing, and is the joint point of the on-board retracting mechanism.