Automatic telescopic aircraft oil-receiving rod capable of preventing whip from being thrown and control method of automatic telescopic aircraft oil-receiving rod

Abstract

The invention belongs to the technical field of structural dynamics, and particularly relates to an anti-whip-throwing automatic telescopic aircraft oil-receiving rod and a control method. The anti-whip-throwing automatic telescopic aircraft oil-receiving rod comprises a rod body and an oil-receiving plug connected with the rod body; the rod body comprises an inner pipe and an outer pipe; the inner pipe comprises an inner pipe front section, an inner pipe folding section and an inner pipe rear section; the inner pipe folding section is integrally arranged between the inner pipe front section and the inner pipe rear section; a limiting top is arranged on the side wall of the inner pipe front section, a limiting channel is arranged at the position, corresponding to the limiting top, in the inner pipe front section, and a limiting spring is arranged in the limiting channel. The outer pipe comprises an outer pipe body and an outer pipe spring, the front end of the outer pipe spring is connected with the rear end of the oil receiving plug, and the rear end of the outer pipe spring is connected with the front end of the outer pipe body; the flexible pipe whip throwing phenomenon during flexible refueling butt joint can be effectively prevented, the refueling butt joint success rate of an oil receiver aircraft and a refueling machine is increased, the flight cost is reduced, the test flight period is shortened, and the flight safety is guaranteed.

Description

Technical Field

[0001] The present application belongs to the technical field of structural dynamics, and in particular relates to an anti-whiplash automatic retractable aircraft oil receiving rod and a control method. Background Art

[0002] The refueling methods of an aircraft during flight are mainly divided into hard refueling and soft refueling. The most commonly used method is soft refueling, i.e. a hose-drogue refueling system. This system consists of a power unit, a hose winch mechanism, a control system, a brake system, a hose and a drogue. The drogue consists of a stabilizing parachute and a refueling plug. The hose-drogue is affected by the wake of the refueling aircraft, the nose wave of the receiving aircraft, and atmospheric turbulence. It is difficult to stabilize in a fixed position, and the time suitable for docking is short. If the speed is too fast during docking, it is easy to cause the hose to loosen and cause hose whipping.

[0003] At present, refueling pods are equipped with constant force spring devices to maintain the stability of hose tension and suppress hose whipping, but the accident rate in the aerial refueling docking stage is still as high as 2.5%, which is much higher than the landing stage with the highest risk level. Moreover, after the docking of the receiving aircraft's refueling plug and the drogue refueling connector, the reel rewinding response generally has a delay of 0.2 to 0.5 seconds. If the docking speed of the receiving aircraft is too fast or the subsequent reel rewinding is slow, whipping is very likely to occur, which may cause the refueling plug to break at the least, or even cause more serious flight safety accidents at the worst.

[0004] Therefore, how to control the docking speed of the receiving aircraft is a problem that needs to be solved. Summary of the invention

[0005] The purpose of the present application is to provide an anti-whiplash automatic retractable aircraft refueling rod and a control method to solve the problem that whiplash is likely to occur when the refueling aircraft docks too fast or too slow.

[0006] The technical solution of the present application is: an anti-whiplash automatic retractable aircraft refueling rod, comprising a rod body and a refueling plug connected to the rod body; the rod body comprises an inner tube and an outer tube; the inner tube comprises an inner tube front section, an inner tube folding section and an inner tube rear section; the inner tube folding section is integrally arranged between the inner tube front section and the inner tube rear section; a limiting pin is provided on the side wall of the inner tube front section, a limiting channel is provided at a position corresponding to the limiting pin inside the inner tube front section, and a limiting spring is provided in the limiting channel; the outer tube comprises an outer tube body and an outer tube spring, the front end of the outer tube spring is connected to the rear end of the refueling plug, and the rear end of the outer tube spring is connected to the front end of the outer tube body;

[0007] A front limit groove and a rear limit groove are provided on the inner wall of the outer tube body, and the shapes and sizes of the front limit groove and the rear limit groove are adapted to the limit head; the folding section of the inner tube can be telescoped; the upper end shape of the limit head is adapted to the front limit groove and the rear limit groove, the lower end of the limit head is connected to the upper end of the limit spring, the lower end of the limit spring is connected to the bottom of the limit spring channel, and the limit head and the limit spring can slide up and down inside the limit channel.

[0008] Preferably, the front limiting groove and the rear limiting groove are both semicircular in shape.

[0009] Preferably, the inner tube folded section is made of elastic material.

[0010] Preferably, the stretching amount of the outer tube spring and the inner tube folded section in the stretched state is x1, the tensile and compressive stiffness of the outer tube spring is k; the aerodynamic force of the cone sleeve is F D The sum of the aerodynamic force of the cone sleeve and the tension of the outer tube spring exceeds the disengagement force threshold of the limit plug, which is F. S1 , the compression amount of the outer tube spring and the inner tube folding section in the compressed state is x2; when the force between the oil receiving plug and the cone sleeve is a tensile force, the sum of the tensile force and the thrust of the outer tube spring exceeds the disengagement force threshold of the limit head, which is F S2 ; The oil plug pull-off threshold is F.

[0011] Preferably, k·x1<0.5F S1 And k·x2<0.5F S2 .

[0012] Preferably, k·x1+F D >1.5F S1 .

[0013] Preferably, |k·x2-F D |<0.5F S2 .

[0014] Preferably, k·x2+F T >1.5F S2 .

[0015] Preferably, |k·x1-F T |<0.5F S2 .

[0016] Preferably, x2>0.5m, where m is the total length of the folded section of the inner tube.

[0017] As a specific implementation, a whiplash-proof automatic retractable aircraft fuel receiving rod control method includes:

[0018] Before the receiving aircraft is refueled and docked, the limit head is limited in the front limit groove, and the stretching amount of the outer tube spring and the inner tube folding section is controlled to be x1;

[0019] After the oil receiving plug is docked with the tanker cone sleeve, the control limit head moves down along the limit spring channel, the limit head slides out of the front limit slot and releases the front limit state, and the front section of the inner tube moves backward under the joint action of the cone sleeve pneumatic force and the outer tube spring until the limit head slides into the rear limit slot position and forms a rear limit effect. At this time, the outer tube spring and the folded section of the inner tube are in a compressed state, and the compression amount is x2;

[0020] After the refueling process is completed, the receiving machine will actively move away from the refueling machine, control the limit head to move down along the limit spring channel, the limit head slides out of the rear limit groove and releases the rear limit state, and the front section of the inner tube moves forward under the combined action of the cone sleeve tension and the outer tube spring thrust until the limit head slides into the front limit groove position and forms a front limit effect.

[0021] Preferably, the tension and compression stiffness of the outer tube spring is k; the aerodynamic force of the cone sleeve is F D The sum of the cone sleeve aerodynamic force and the outer tube spring tension exceeds the disengagement force threshold of the limit plug under the cone sleeve aerodynamic state, which is F S1 When the tension between the oil receiving plug and the cone sleeve is tensile, the sum of the tensile force and the outer tube spring thrust exceeds the disengagement force threshold of the limit head, which is F S2 ; The oil plug pull-off threshold is F T .

[0022] Preferably, k·x1<0.5F S1 And k·x2<0.5F S2 .

[0023] Preferably, k·x1+F D >1.5F S1 .

[0024] Preferably, |k·x2-F D |<0.5F S2 .

[0025] Preferably, k·x2+F T >1.5F S2 .

[0026] Preferably, |k·x1-F T |<0.5F S2 .

[0027] Preferably, x2>0.5m, where m is the total length of the folded section of the inner tube.

[0028] The anti-whiplash automatic retractable aircraft refueling rod and control method of the present application can effectively prevent the hose whipping phenomenon during soft refueling docking, improve the refueling docking success rate between the receiving aircraft and the refueling aircraft, reduce flight costs, shorten the test flight cycle, and ensure flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0030] Figure 1 This is the axonometric drawing of the overall structure of this application;

[0031] Figure 2 This is a combined effect diagram of the stretched state of the anti-whiplash automatic retractable aircraft fuel receiving rod of this application;

[0032] Figure 3 This is a combined effect diagram of the appearance of the spring balance state in the anti-whiplash automatic retractable aircraft oil receiving rod of this application;

[0033] Figure 4 This is a combined effect diagram of the compressed state of the anti-whiplash automatic retractable aircraft oil receiving rod in this application.

[0034] 1. Oil receiving plug; 2. Front section of inner tube; 3. Folding section of inner tube; 4. Rear section of inner tube; 5. Limiting head; 6. Limiting spring; 7. Limiting channel; 8. Outer tube body; 9. Front limiting groove; 10. Rear limiting groove; 11. Outer tube spring. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0036] An anti-whiplash automatic retractable aircraft oil receiving rod, such as Figure 1-Figure 2 As shown, it includes a rod body and an oil receiving plug 1 connected to the rod body. The rod body includes an inner tube and an outer tube; the inner tube includes an inner tube front section 2, an inner tube folding section 3 and an inner tube rear section 4. The inner tube folding section 3 is integrally arranged between the inner tube front section 2 and the inner tube rear section 4. A limiting plug 5 is provided on the side wall of the inner tube front section 2, and a limiting channel 7 is provided at a position corresponding to the limiting plug 5 inside the inner tube front section 2, and a limiting spring 6 is provided in the limiting channel 7. The outer tube includes an outer tube body 8 and an outer tube spring 11, the front end of the outer tube spring 11 is connected to the rear end of the oil receiving plug 1, and the rear end of the outer tube spring 11 is connected to the front end of the outer tube body 8.

[0037] A front limiting groove 9 and a rear limiting groove 10 are provided on the inner wall of the outer tube body 8 . The shapes of the front limiting groove 9 and the rear limiting groove 10 are both semicircular arcs. The shapes and sizes of the front limiting groove 9 and the rear limiting groove 10 are adapted to the limiting head 5 .

[0038] The inner tube folding section 3 is made of elastic material and has telescopic ability; the upper end shape of the limiting head 5 is adapted to the front limiting groove 9 and the rear limiting groove 10, the lower end of the limiting head 5 is connected to the upper end of the limiting spring 6, and the lower end of the limiting spring 6 is connected to the bottom of the limiting spring 6 channel, and the limiting head 5 and the limiting spring 6 can slide up and down inside the limiting channel 7.

[0039] Combination Figure 3-Figure 4 Before the receiving machine is refueled and docked, the limit head 5 is restricted in the front limit groove 9, the outer tube spring 11 and the inner tube folding section 3 are in a stretched state, the stretching amount is x1, and the tension and compression stiffness of the outer tube spring 11 is k.

[0040] After the receiving plug 1 is connected to the fuel dispenser cone sleeve, the aerodynamic force of the fuel dispenser cone sleeve directly acts on the receiving plug 1. The aerodynamic force of the cone sleeve is F D The sum of the aerodynamic force of the cone sleeve and the tension of the outer tube spring 11 exceeds the disengagement force threshold F of the limit plug 5. S1 , the limit pin 5 moves downward along the limit spring channel 7, the limit pin 5 slides out of the front limit groove 9 and releases the front limit state, the front section 2 of the inner tube moves backward under the joint action of the aerodynamic force of the cone sleeve and the outer tube spring 11, until the limit pin 5 slides into the rear limit groove 10 position and forms a rear limit effect, at this time the outer tube spring 11 and the inner tube folding section 3 are in a compressed state, and the compression amount is x2.

[0041] After the refueling process is completed, the receiving machine will actively move away from the refueling machine, and the pressure between the receiving plug and the cone sleeve is converted into a tensile force. The sum of the tensile force and the thrust of the outer tube spring 11 exceeds the disengagement force threshold F of the limit head 5. S2 , the limit pin 5 moves downward along the limit spring channel 7, the limit pin 5 slides out of the rear limit groove 10 and releases the rear limit state, the inner tube front section 2 moves forward under the combined action of the cone sleeve tension and the outer tube spring 11 thrust, until the limit pin 5 slides into the front limit groove 9 position and forms a front limit effect, at this time the outer tube spring 11 and the inner tube folding section 3 restore the stretched state, the tension between the oil receiving plug and the cone sleeve further increases until the oil receiving plug pull-off threshold F is reached.

[0042] The stiffness k, the stretching amount x1, the compression amount x2, and the release force threshold F of the outer tube spring 11 S1 , Disengagement force threshold F S2 , Oil receiving plug pull-off threshold F T The specific design is:

[0043] Preferably, k·x1<0.5F S1 And k·x2<0.5F S2 ; To prevent the limit head 5 from accidentally sliding out.

[0044] Preferably, k·x1+F D >1.5F S1; To ensure that after the oil receiving plug is docked, the front section 2 of the inner tube can be retracted.

[0045] Preferably, |k·x2-F D |<0.5F S2 ; To ensure that the front section 2 of the inner tube can form a rear limit function after retracting.

[0046] Preferably, k·x2+F T >1.5F S2 ; To ensure that the oil receiving plug can be removed smoothly after refueling is completed.

[0047] Preferably, |k·x1-F T |<0.5F S2 ; To ensure that the front section 2 of the inner tube can form a front limit effect after stretching.

[0048] Preferably, x1+x2>0.5m, where m is the total length of the folded section of the inner tube, to ensure that the retraction amount of the oil receiving rod can play a role in avoiding whiplash.

[0049] As a specific implementation, a whiplash-proof automatic retractable aircraft fuel receiving rod control method is also included, which adopts the above-mentioned fuel receiving rod design structure and specifically includes:

[0050] Before the receiving machine is refueled and docked, the limit head is limited in the front limit groove 9, and the stretching amount of the outer tube spring 11 and the inner tube folding section 3 is controlled to be x1;

[0051] After the oil receiving plug 1 is docked with the fuel dispenser cone sleeve, the control limit head 5 moves down along the limit spring channel 7, the limit head 5 slides out of the front limit groove 9 and releases the front limit state, and the inner tube front section 2 moves backward under the joint action of the cone sleeve pneumatic force and the outer tube spring 11 until the limit head 5 slides into the rear limit groove 10 position and forms a rear limit effect. At this time, the outer tube spring 11 and the inner tube folding section 3 are in a compressed state, and the compression amount is x2;

[0052] After the refueling process is completed, the receiving machine will actively move away from the refueling machine, control the limit head 5 to move downward along the limit spring channel 7, the limit head 5 slides out of the rear limit groove 10 and releases the rear limit state, and the front section 2 of the inner tube moves forward under the combined action of the cone sleeve tension and the outer tube spring 11 thrust until the limit head 5 slides into the front limit groove 9 position and forms a front limit effect.

[0053] Preferably, the tension and compression stiffness of the outer tube spring is k; the aerodynamic force of the cone sleeve is F D The sum of the cone sleeve aerodynamic force and the outer tube spring tension exceeds the disengagement force threshold of the limit plug under the cone sleeve aerodynamic state, which is F S1 When the tension between the oil receiving plug and the cone sleeve is tensile, the sum of the tensile force and the outer tube spring thrust exceeds the disengagement force threshold of the limit head, which is F S2; The oil plug pull-off threshold is F.

[0054] Preferably, k·x1<0.5F S1 And k·x2<0.5F S2 ; To prevent the limit head 5 from accidentally sliding out.

[0055] Preferably, k·x1+F D >1.5F S1 ; To ensure that after the oil receiving plug is docked, the front section 2 of the inner tube can be retracted.

[0056] Preferably, |k·x2-F D |<0.5F S2 ; To ensure that the front section 2 of the inner tube can form a rear limit function after retracting.

[0057] Preferably, k·x2+F T >1.5F S2 ; To ensure that the oil receiving plug can be removed smoothly after refueling is completed.

[0058] Preferably, |k·x1-F T |<0.5F S2 ; To ensure that the front section 2 of the inner tube can form a front limit effect after stretching.

[0059] Preferably, x1+x2>0.5m, where m is the total length of the folded section of the inner tube, to ensure that the retraction amount of the oil receiving rod can play a role in avoiding whiplash.

[0060] To sum up, through the above design, the present application can effectively prevent the hose whipping phenomenon during soft refueling docking, improve the refueling docking success rate between the receiving aircraft and the refueling aircraft, reduce flight costs, shorten the test flight cycle, and ensure flight safety.

[0061] Finally, it should be noted that: the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention, and other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other;

[0062] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. An anti-whiplash automatic retractable aircraft refueling boom, characterized in that: The invention comprises a rod body and an oil receiving plug (1) connected to the rod body; the rod body comprises an inner tube and an outer tube; the inner tube comprises an inner tube front section (2), an inner tube folding section (3) and an inner tube rear section (4); the inner tube folding section (3) is integrally arranged between the inner tube front section (2) and the inner tube rear section (4); a limiting pin (5) is provided on the side wall of the inner tube front section (2); a limiting channel (7) is provided at a position corresponding to the limiting pin (5) inside the inner tube front section (2); a limiting spring (6) is provided inside the limiting channel (7); the outer tube comprises an outer tube body (8) and an outer tube spring (11); the front end of the outer tube spring (11) is connected to the rear end of the oil receiving plug (1), and the rear end of the outer tube spring (11) is connected to the front end of the outer tube body (8); A front limiting groove (9) and a rear limiting groove (10) are provided on the inner wall of the outer tube body (8), and the shapes and sizes of the front limiting groove (9) and the rear limiting groove (10) are adapted to the limiting head (5); the inner tube folding section (3) can be extended and retracted; the shape of the upper end of the limiting head (5) is adapted to the front limiting groove (9) and the rear limiting groove (10), the lower end of the limiting head (5) is connected to the upper end of the limiting spring (6), the lower end of the limiting spring (6) is connected to the bottom of the limiting spring (6) channel, and the limiting head (5) and the limiting spring (6) can slide up and down inside the limiting channel (7).

2. The anti-whiplash automatic retractable aircraft refueling boom according to claim 1, characterized in that: The front limiting groove (9) and the rear limiting groove (10) are both semicircular in shape.

3. The anti-whiplash automatic retractable aircraft refueling boom according to claim 1, characterized in that: The inner tube folded section (3) is made of elastic material.

4. The anti-whiplash automatic retractable aircraft refueling boom according to claim 1, characterized in that: The stretching amount of the outer tube spring (11) and the inner tube folding section (3) in the stretched state is x1, the tensile and compressive stiffness of the outer tube spring (11) is k; the aerodynamic force of the cone sleeve is F D The sum of the aerodynamic force of the cone sleeve and the tension of the outer tube spring (11) exceeds the disengagement force threshold value of the limit head (5) under the aerodynamic force of the cone sleeve, which is F S1 , the compression amount of the outer tube spring (11) and the inner tube folding section (3) in the compressed state is x2; when the tension between the oil receiving plug (1) and the cone sleeve is tensile, the sum of the tensile force and the thrust of the outer tube spring (11) exceeds the disengagement force threshold value of the limit head (5) is F S2 ; The pull-off threshold of the oil receiving plug (1) is F T .

5. The anti-whiplash automatic retractable aircraft refueling boom according to claim 4, characterized in that: k·x1<0.5F S1 And k·x2<0.5F S2 .

6. The anti-whiplash automatic retractable aircraft refueling boom according to claim 4, characterized in that: k·x1+F D >1.5F S1 。 7. The anti-whiplash automatic retractable aircraft refueling boom according to claim 4, characterized in that: |k·x2-F D |<0.5F S2 。 8. The anti-whiplash automatic retractable aircraft refueling boom according to claim 4, characterized in that: k·x2+F T >1.5F S2 。 9. The anti-whiplash automatic retractable aircraft refueling boom according to claim 4, characterized in that: |k·x1-F T |<0.5F S2 。 10. The anti-whiplash automatic retractable aircraft refueling boom according to claim 4, characterized in that: x1+x2>0.5m, m is the total length of the folded section of the inner tube.

11. A method for controlling an anti-whiplash automatic retractable aircraft fuel receiving rod, using any method according to claims 1-10, characterized in that: include: Before the receiving machine is refueled and docked, the limiting head (5) is limited in the front limiting groove (9), and the stretching amount of the outer tube spring (11) and the inner tube folding section (3) is controlled to be x1; After the oil receiving plug (1) is connected to the oil filling machine cone sleeve, the control limit head (5) moves downward along the limit spring (6) channel, the limit head (5) slides out of the front limit groove (9) and releases the front limit state, and the front section of the inner tube (2) moves backward under the combined action of the cone sleeve pneumatic force and the outer tube spring (11) until the limit head (5) slides into the rear limit groove (10) position and forms a rear limit effect. At this time, the outer tube spring (11) and the inner tube folding section (3) are in a compressed state, and the compression amount is x2; After the refueling process is completed, the receiving machine will actively move away from the refueling machine, control the limit head (5) to move downward along the limit spring (6) channel, the limit head (5) slides out of the rear limit groove (10) and releases the rear limit state, and the front section of the inner tube (2) moves forward under the combined action of the cone sleeve pulling force and the outer tube spring (11) thrust until the limit head (5) slides into the front limit groove (9) position and forms a front limit effect.

12. The anti-whiplash automatic retractable aircraft refueling boom according to claim 11, characterized in that: The tensile and compressive stiffness of the outer tube spring (11) is k; the aerodynamic force of the cone sleeve is F D The sum of the aerodynamic force of the cone sleeve and the tension of the outer tube spring (11) exceeds the disengagement force threshold value of the limit head (5) F S1 When the acting force between the oil receiving plug (1) and the cone sleeve is a tensile force, the sum of the tensile force and the thrust of the outer tube spring (11) exceeds the disengagement force threshold value of the limit plug (5) to be F. S2 ; The pull-off threshold of the oil receiving plug (1) is F.

13. The anti-whiplash automatic retractable aircraft refueling boom according to claim 12, characterized in that: k·x1<0.5F S1 And k·x2<0.5F S2 .

14. The anti-whiplash automatic retractable aircraft refueling boom according to claim 12, characterized in that: k·x1+F D >1.5F S1 。 15. The anti-whiplash automatic retractable aircraft refueling boom according to claim 12, characterized in that: |k·x2-F D |<0.5F S2 。 16. The anti-whiplash automatic retractable aircraft refueling boom according to claim 12, characterized in that: k·x2+F T >1.5F S2 。 17. The anti-whiplash automatic retractable aircraft refueling boom according to claim 12, characterized in that: |k·x1-F T |<0.5F S2 。 18. The anti-whiplash automatic retractable aircraft refueling boom according to claim 12, characterized in that: x1+x2>0.5m.

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