Rotor wing protection structure for rocket recovery

Abstract

The utility model discloses a rotor wing protection structure for rocket recovery, which effectively realizes the purpose of protecting a rotor wing mechanism for rocket recovery, and comprises a fixing ring fixedly connected with a rocket booster, the outer side of the fixing ring is provided with the rotor wing mechanism which can be folded in the fixing ring, and the rotor wing mechanism is provided with a rotor wing. A protective cover detachably connected with the fixing ring is arranged on the outer side of the fixing ring. The protective cover comprises a plurality of protective plates and two protective rings, the upper side and the lower side of each protective plate are respectively provided with a fixing groove, and the protective rings are matched with the fixing grooves. The pneumatic protective cover is novel in structure, ingenious in conception and easy and convenient to operate, effectively improves the stability of clamping connection between the protective plates, achieves a better pneumatic effect, and is suitable for popularization and application. And the rotor mechanisms can be automatically unfolded, the automatic separation effect of the multiple protection plates is achieved, the separation process of the protection plates is more stable, and the success rate of falling of the protection plates is increased.

Description

TECHNICAL FIELD

[0001] The utility model belongs to aerospace technology field relates to a rotor protection structure for rocket recovery. BACKGROUND

[0002] With the rapid development of aerospace technology, the efficient control of rocket launch cost and the sustainable use of resources have become the core problem of the industry. Most of the traditional rockets are disposable, resulting in high economic cost and space garbage problem. In recent years, although part of the rocket boosters has realized preliminary recovery through complex thruster return technology, the precision control, safety, technical cost and dependence on external energy in the recovery process are still the key factors restricting its wide application.

[0003] In addition, during the rocket recovery process, the rotor mechanism generally needs to be folded and stored, so there is an urgent need for a rotor protection structure for rocket recovery to solve the above problems. UTILITY MODEL CONTENT

[0004] In view of the above problems, the utility model provides a rotor protection structure for rocket recovery, which solves the problems in the prior art.

[0005] In order to achieve the above purpose, the utility model adopts the following technical scheme:

[0006] A rotor protection structure for rocket recovery, comprising a fixed ring fixedly connected with a rocket booster, an outer side of the fixed ring is provided with a rotor mechanism foldable in the fixed ring, and an outer side of the fixed ring is provided with a protective cover detachably connected with the fixed ring.

[0007] The protective cover comprises a plurality of protective plates and two protective rings, a fixed groove is formed on each of the upper and lower sides of the protective plate, and the protective ring is matched with the fixed groove.

[0008] Preferably, a first clamping block is fixedly connected to the left side of each protective plate, and a first clamping groove matched with the first clamping block is formed on the right side of each protective plate.

[0009] Preferably, an inclined plate is fixedly connected to each of the upper and lower sides of each protective plate.

[0010] Preferably, a protective pin matched with the rotor mechanism is fixedly connected to the inner side of each protective plate.

[0011] Preferably, a resilient plate is rotatably connected to each of the upper and lower sides of the outer side of the protective plate, a second clamping block is fixedly connected to one side of each resilient plate close to the protective ring, and a second clamping groove matched with the second clamping block is formed on the position of the protective ring close to each second clamping block.

[0012] Preferably, the middle part of the protective ring is provided with a plurality of disconnection holes, the inside of each disconnection hole is provided with a connecting block, and the side close to the protective plate of each connecting block is fixedly connected with a fixed block.

[0013] Preferably, the inside of the connecting block is provided with a trigger assembly for disconnecting the protective ring.

[0014] Compared with the prior art, the utility model has the following beneficial effects:

[0015] 1. The utility model has the protective cover which is composed of a plurality of protective plates, and the fixed ring and the rotor mechanism inside can be protected.

[0016] 2. The utility model has the inclined plate, and the turbulent flow intensity generated on the upper and lower sides of the protective plate during the rocket advancing process can be reduced through the inclined plate, and the rocket propeller can obtain better propelling effect. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 It is the cooperation state schematic view of the plurality of protective plates in the utility model.

[0018] Figure 2 It is the structure schematic view of the fixed ring in the utility model.

[0019] Figure 3 It is the structure schematic view of the protective plate in the utility model.

[0020] Figure 4 It is the explosion structure schematic view of two adjacent protective plates in the utility model.

[0021] Figure 5 It is the position schematic view of the disconnection hole in the utility model.

[0022] Figure 6 It is the local enlarged schematic view of A area in the utility model. Figure 4

[0023] In the drawing: 1, fixed ring;2, rotor mechanism;3, protective plate;4, protective ring;5, fixed groove;6, first clamping block;7, first clamping groove;8, inclined plate;10, elastic plate;11, second clamping block;12, second clamping groove;13, disconnection hole;14, connecting block;15, fixed block. DETAILED DESCRIPTION

[0024] ​The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of the utility model.

[0025] The utility model discloses a rocket booster fixed ring protection device, as shown in the accompanying drawings, Figures 1 to 6 The specific implementation of the utility model will be further described in detail.

[0026] As shown in the accompanying drawings, Figures 1 to 6 The utility model discloses a rocket booster fixed ring protection device, as shown in the accompanying drawings, in order to be able to protect the rotor mechanism 2 for rocket recovery, the outside of fixed ring 1 is equipped with the rotor mechanism 2 that can be folded in the inside of fixed ring 1, the outside of fixed ring 1 is equipped with the protective cover that can be dismantled with fixed ring 1,

[0027] The protective cover includes five protective plates 3 and two protective rings 4, one fixed groove 5 is formed on the upper and lower sides of protective plate 3 respectively, and protective ring 4 is matched with fixed groove 5.

[0028] It should be noted that the rotor mechanism 2 is used for recovering the rocket propeller, in the process of rocket advancing, the rotor mechanism 2 is accommodated in the groove formed on the side wall of fixed ring 1 in the inside of the protective cover, after the protective cover and fixed ring 1 are disengaged, the rotor mechanism 2 will rotate relative to fixed ring 1, and then adjust the posture of the rocket propeller.

[0029] In use, in the process of rocket advancing, the protective ring 4 is sleeved in the inside of two fixed grooves 5, under the action of protective ring 4, each protective plate 3 can be fixed, so that multiple protective plates 3 can be jointly attached to fixed ring 1, and fixed ring 1 and the rotor mechanism 2 accommodated in the side wall of fixed ring 1 are protected, after the rocket propeller is separated from the rocket head, the protective ring 4 will be disconnected at the right time, so that multiple protective plates 3 are disengaged from fixed ring 1, and then fixed ring 1 and the rotor mechanism 2 are exposed, and the rocket propeller is protected by the rotor mechanism 2.

[0030] Further, as shown in the accompanying drawings, Figures 1 to 6 In order to increase the stability of the clamping between multiple protective plates 3, a first clamping block 6 is fixedly connected to the left side of each protective plate 3, and a first clamping groove 7 matched with the first clamping block 6 is formed on the right side of each protective plate 3.

[0031] In use, each two adjacent protective plates 3 are matched by the mutual clamping of the first clamping block 6 and the first clamping groove 7, and then the inside of the protective cover can be well protected.

[0032] Further, as shown in the accompanying drawings,Figures 1 to 6 As shown, in order to achieve better aerodynamic effect, the upper and lower sides of each protective plate 3 are fixedly connected with an inclined plate 8;

[0033] In use, by setting the inclined plate 8, the turbulence intensity generated on the upper and lower sides of the protective plate 3 during the rocket running process can be reduced, thereby making the rocket thruster obtain better propulsion effect.

[0034] Further, by Figures 1 to 6 As shown, in order to automatically deploy the rotor mechanism 2, the inner side of each protective plate 3 is fixedly connected with a protective pin matched with the rotor mechanism 2;

[0035] It should be noted that the outer side wall of the fixed ring 1 is provided with a connecting hole corresponding to the position of each protective pin. When the rotor mechanism 2 is received in the side wall of the fixed ring 1, the protective pin passes through the connecting hole and cooperates with the rotor mechanism 2, thereby limiting the angle of the rotor mechanism 2 relative to the fixed ring 1. After the protective plate 3 is separated from the cooperation between the fixed ring 1, the protective pin and the connecting hole are disengaged, so that the rotor mechanism 2 can rotate and deploy relative to the fixed ring 1. The protective plate 3 and the protective ring 4 are made of high-temperature resistant material, which can protect the high temperature during the rocket running;

[0036] Further, by Figures 1 to 6 As shown, in order to realize the automatic separation effect of the plurality of protective plates 3, the upper and lower sides of the outer side of the protective plate 3 are rotatably connected with a resilient plate 10. The side of each resilient plate 10 close to the protective ring 4 is fixedly connected with a second clamping block 11. The position close to each second clamping block 11 of the protective ring 4 is provided with a second clamping groove 12 matched with the second clamping block 11;

[0037] It should be noted that the resilient plate 10 is made of elastic material. In the state of not being forced, there is an included angle between the resilient plate 10 and the protective plate 3, thereby under the action of resistance during the running of the rocket thruster, the resistance is applied to the protective plate 3, so that the torque of rotation exists;

[0038] Further, by Figures 1 to 6 As shown, in order to make the separation process of the protective plate 3 more stable, the middle part of the protective ring 4 is provided with a plurality of disconnection holes 13. The inside of each disconnection hole 13 is provided with a connecting block 14. The side of each connecting block 14 close to the protective plate 3 is fixedly connected with a fixed block 15. The fixed block 15 is clamped with the protective plate 3;

[0039] Further, by Figures 1 to 6 As shown, in order to increase the success rate of the protective plate 3 falling off, the inside of the connecting block 14 is provided with a trigger assembly for disconnecting the protective ring 4;

[0040] It should be noted that the triggering assembly disconnects the protective ring 4 in the following ways, including but not limited to: scheme 1. The protective ring 4 comprises a plurality of protective strips connected end to end, and a pressing block is arranged at the connection position of each two adjacent protective strips. The left and right ends of the pressing block are arranged on the side of the protective strip away from the protective plate 3. An electromagnet is arranged on the side of each pressing block close to the protective plate 3. The electromagnet and the pressing block are connected by magnetic force. After the electromagnet is powered off, the pressing block releases the restriction on the protective strip, and the limiting between the plurality of protective plates 3 by the protective ring 4 is completed. Scheme 2. The triggering assembly comprises a spark plug, a primer and an explosive. The spark plug is connected with the control system of the rocket booster. After the control system controls the spark plug to generate an electric spark, the primer is ignited, and then the explosive is ignited to damage the upper and lower areas of the connecting block 14 and the disconnection hole 13, and then the connecting block 14 and the protective ring 4 are disconnected.

[0041] When the protective ring 4 is disconnected, the second clamping block 11 and the second clamping groove 12 are disengaged, the elastic plate 10 loses the restriction of the protective ring 4, and is bounced up relative to the protective plate 3 to form an angle with the protective plate 3. Then, under the action of wind resistance, a lateral force is applied to each protective plate 3 to help the plurality of protective plates 3 to be separated from the fixing ring 1.

[0042] In use, the protective ring 4 is sleeved in the two fixing grooves 5 during the rocket advancing process. Under the action of the protective ring 4, each protective plate 3 can be fixed, so that the plurality of protective plates 3 can be jointly attached to the fixing ring 1 to protect the fixing ring 1 and the rotor mechanism 2 stored in the side wall of the fixing ring 1. After the rocket booster is separated from the rocket head, the triggering assembly operates to disconnect the protective ring 4, thereby releasing the limitation between the plurality of protective plates 3 and the plurality of elastic plates 10. At this time, under the wind resistance of the elastic plate 10, each protective plate 3 is driven to be separated from the fixing ring 1, and the fixing ring 1 and the rotor mechanism 2 are exposed, and the rotor mechanism 2 protects the rocket booster.

[0043] The utility model discloses novel structure, clever idea, easy operation, through the design effectively realized the purpose of being able to protect the rotor mechanism 2 of rocket recovery, increased the stability of the clamping between the plurality of protective plates 3, realized better aerodynamic effect, can automatically unfold the rotor mechanism 2, realized the automatic separation effect of the plurality of protective plates 3, make the separation process of protective plate 3 more stable, increase the success rate of the falling of protective plate 3.

[0044] Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions recorded in the foregoing embodiments or make equivalent replacement to part of the technical features, and any modification, equivalent replacement, improvement, etc. within the spirit and principle of the utility model should be included in the protection scope of the utility model.

Claims

1. A rotor protection structure for rocket recovery, comprising a fixed ring fixedly connected with a rocket booster, characterized in that: The outer side of the fixed ring is provided with a rotor mechanism foldable inside the fixed ring, and the outer side of the fixed ring is provided with a protective cover detachably connected with the fixed ring. The protective cover comprises a plurality of protective plates and two protective rings, and the upper and lower sides of each protective plate are provided with fixing grooves, and the protective rings are matched with the fixing grooves.

2. The rotorcraft protective structure of claim 1, wherein: The left side of each protective plate is fixedly connected with a first clamping block, and the right side of each protective plate is provided with a first clamping groove matched with the first clamping block.

3. The rotorcraft protective structure of claim 1, wherein: The upper and lower sides of each protective plate are fixedly connected with an inclined plate.

4. The rotorcraft protective structure of claim 1, wherein: The inner side of each protective plate is fixedly connected with a protective pin matched with the rotor mechanism.

5. The rotorcraft protective structure of claim 1, wherein: The upper and lower sides of the outer side of the protective plate are rotatably connected with elastic plates, one side of each elastic plate close to the protective ring is fixedly connected with a second clamping block, and the protective ring is provided with a second clamping groove matched with the second clamping block at a position close to each second clamping block.

6. The rotorcraft protective structure of claim 1, wherein: The middle part of the protective ring is provided with a plurality of disconnection holes, the inside of each disconnection hole is provided with a connecting block, one side of each connecting block close to the protective plate is fixedly connected with a fixing block, and the fixing block is clamped with the protective plate.

7. The rotorcraft protective structure of claim 6, wherein: The inside of the connecting block is provided with a trigger assembly for disconnecting the protective ring.

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